~~ \.•

I • \' •

, f

; .I"t.,.. t. 4. ••

~" .

NASA TECHNICAL NASA 1M X-S2043: MEMORAt-JDUMI·

~:--:--- ..:--L-(_V.lL--~~cuJ 2--------.------.- ----1 (If.ASA-TII-X-52043) .. IIUCLEAB BOCKBT .---------. -_. -.. -~--._ ... SIIIULA!OR TESTS PACILITY AID RESEARCH . 1173-71851 j

APPABA7DS DBSCRIPTION flfASA).·- 99 P j I

Unclas I

54955 .' .'.I "

fNUCLEAR ROCKET S'MULATOR TESTS I

FACILITY AND RESEARCH APPARATUS DESCRIPTION

Lewis Research Center Cleveland, Ohio

.I

-: .; .LI __ . . [,r:r. -2 ... ');10Q\t Ll' .'U

.~ i'!'". ' . r·;l~~~ Cit.' ~ $1;kJIIUi ..

., \ NATIONAL AERONAUTICS AND SPACE ADMINISTRATION . WASHINGTON, D.C.. 1964 ,1 '. .

, )..,~ " ,¥",,, ""'. ,.... ".:& . «01&."v...;;._.•" ....

\

ceDIS•••"I. !zIs: .. r ':. ..

'l'ECHNICAL MEMORANDUM

NUCLEAR ROCKET SIMULATOR TESTS

(UJFACILITY AND RESEARCH APPARATUS DESCRIPTION

Coordinator ... ' Donald D. Lacy

Contributors

John R. Esterly David- M . .str.aiglit··

John G. Pierce Francis M. Humenik Daniel C. Hippman

:'

JiUki.ni8 '1'~J3 rh\'fJt attatiomic BUd gy Ace of H64

-Jill laded £rb111 aueOiiiaClc t!OWIJ=

STadjp8 and dechssifiuti.R ,

,f

.JshSSIPliiiij i1i9"U14ENT TIT! E lIN,,! 0 CillPil!J8 Th" terial contains information affecting the National Defense of the United States WI In • • C. , Sections 7 s ransmission or e contents in a anner to an unauthorized person is prohibited by law.

NATIONAL AERONAUTICS AND SPACE ADMINISTRATION

" NUCLEAR ROCKET SIMULATOR TESTS

'.

FACILITY AND RESEARCH APPARATUS DESCRIPrION

Lewis Research Center

ABSTRACT

A detailed description of the facility, the rese~ch apparatus, the instrumentation, the data acquisition system, and the data processing system used to conduct full-scale cold flow nuclear rocket simulator tests is presented. The facility utilizes steam to provide a minnnum pressure (no flow) of 0.5 pound per sqUEire inch absolute at the exhaust nozzle exit during test runs. The use o~ liquid hydrogen requires that the tests be conducted remotely. There are about 875 data sensing parameters of temper­ature, pressure, flow, and acceleration that can be recorded on digital and/or analog data acquisition equipment.

TABLE OF CONTENTS

Page

HH INTRODUCTION -------------------------------------- 1

I r0 r-­ PART I - DESCRIPTION OF B-1 FACTI.m 2<0 N

I fil STRUCTURE ------------------------------- _ 2

ALTrrUDE EXHAUST SYSTEM -- _ 2

Capability ----------------------------~--- 2 Boiler House ------------------------.------ 2 Accumulators ------------------------------ 3 Primary and Secondary Ejectors ------------ 3 Zero Flow Ejector ------------------------- 3 Flares ----------------------------.-------- 4

GASEOUS AND CRYOGENIC SUPPLY ----------~------- 4 MAJOR SUBSYSTEMS ------------------------------ 4

Nitrogen System ---~----------------------- 4 Helium System ------------.--.-----------:---- 5 Hydrogen System --------------------------- 5 Hydraulic and Lube Systems ---------------- 5 Eductor ----------------------------------- 5 Safety System ----------------------------- 6 Electrical Systems ------------------------ 6

Cables ------------------~------------- 6Television, Videorecorder, Motion

.. Pictures· ---------------------------- 6

CONTROL BUILDING ----- ...------------------------ 7 TEST PROCEDURE -----~-------------------------- 7

PART II - DESCRIPTION OF RESEARCH APPARATUS 9

RUN TANK -------------------------------------- 9 MARK IX TURBOPUMP ASSEMBLY -------------------- ~

Pump -------------------------------------- 9 Torque Meter ------------------------------ 10 Turbine ----------------------------------- 10

P FrWWTH

-------------------

OOIWl&2i1 £ gg

TABLE OF CONTENTS, Cant r d

Page

REACTOR --------------------------------------- 10

De~cription ------------------------------- 10 Assembly ----------------------------------- 11 Installation ------------------------------ 11

PROPELLANT DUCTING ---------------------------- 12

Tank Discharge to Pump-Inlet -------------- 12 Pump Discharge tG Nozzle Inlet ------------ 13

NOZZLE 13

Description ----------------~-------------- 13 Modifications ----------------------------- 14

PART III - INSTRUMENTATION, DATA ACQUISITION, AND DATA PROCESSING ---------------------------------- 16

INSTRUMENTATION ------------------------------- 16

Signal Transmission System --~------------- 16

Terminal Room and Equipment ----------- 16 B-1 Control Building ------------------ 17 H Building --------------~------------- 17

.. . -Research Measurements 17

Measurement -Points in Research Apparatus --------------------------- 17

Description of Transducers} Thermocouples} Camera, etc. ------------------------ 18

DATA ACQUISITION ------------------------------ 19

Digital System ---------------------------- 19 Analog System ----------------------------- 19

DATA PROCESSING 20

Computer Equipment ------------------------ 20

-."

CpWTWITI9 T

..... -.

". TABLE OF CONTENTS, Cont I d

Page

Computer Program ------------------------­ 21

~"

Calibration --------------------------Averaging -----------------------------Conversion ---------------------------Terminal Calculations ----------------

Data Processing Procedure

21 21 21 22

22

APPENDIX A 24

REFERENCES 26

LIST OF FIGURES ---------------------------------­ 27

gPiilUiUMiJIIg

QADWlii!ll( I btL

NUCLEAR ROCKET SIMULATOR TESTS:

FACnITY AND RESEARCH APPARATUS DESCRIPI'ION

INTRODUCTION

The successful development of the nuclear rocket depends in part on the ability to specify control system parameters and heat transfer phenomena which will insure safe programmed startup. The selection of a possible programmed startup is usually developed with the aid of an analog computer. Current analog studies of nuclear rocket systems under way at Lewis, however, begin With about 10 percent of rated propellant flow and 1 percent of rated reactor power; furthermore, difficulties are encountered in adequately simulating the start .of transient conditions and detailed component characteristics.

In order to obtain necessary information at and immediately fo~lowing initiation of flow for use in both present and future analog and design studies, a full-scale cold flow nuclear rocket simulation test program was.:initiated at the Plum Brook Station of the Lewis Research Center. A detailed description of the facility, the research apparatus, the instrumentation, the data acquisition system and the data processing system is contained herein.. The initial operation of the apparatus with liquid hydrogen as the fluid yielded some preliminary experimental data which are presented in reference 1.

gmTn?l"~1!i

,•

2 gmTTpEz ¥ '_

PART'I - DESCRIPTION OF B-1 FACILITY

STRUCTURE

The B-1 facility (see figure i) consists of a vertical tower with a height of 135 feet and a base 34 feet by 42 feet. The test stand is enclosed above the 68-foot level with roll-up doors on the north, south and west sides. The doors are req~ired to provide adequate ventilation in the event of a hydrogen leak. Two open floor areas below the 68 foot level are used for some of the auxiliary systems; at the base of the test stand, is a concrete shelter for liquid hydrogen dewar parking. Adjacent to this is the ins~rumentation terminal room, terminal and relay cabinets, and a limited working'area for the facility personnel.

The research apparatus is located within, the enclosed area of the ,test stand and consists of atank"turbopump, reactor and exhaust nozzl~ in a system configuration as shown schematically in figure 2~ In order to have working access to the various system components, four floors are provided, one each at the top and bottom of the tank, one at the pump level, and the main floor at the exhaust nozzle exit. The reactor is mounted in a carriage on'tracks beneath the turbopump and is capable of ­being rolled out into'the bay area where' it can be handled by a 20 ton bUilding crane.

An existing 500 pound elevator is being replaced with one having a 3000 pound capacity. A spur of the pium.Brook railroad system will be extended to the facility for expanding the gaseous and cryogenic supply capabilities and for the installation of a new 20,000 gallon liquid hydrogen run tank. Both will be completed in fiscal year 1965.

ALTlTUDE EXHAUST SYSTEM

Capability

An altitude exhaust system is prOVided which is composed of boilers, accumulators, valves and ejectors capable of providing a minimum pressure (zero flow) of 0.5 pounds per square inch for four minutes at the exhaus t nozzle exit.

Boiler House

, The boiler house contains four Babcock and Wilcox boilers, each with a capacity of 28,000 pounds per hour of 500 pounds per square inch gage saturated steam. About 25,000 pounds per ·hour per boiler are available

,-'for charging the accumulators; the remaining 3000 pounds per hour per

. ~eIWI:B!!'i'!&;L

i

3

boiler are used for preheating feedwater and fuel oil and driving the turbines used in conjunction with the water pumps. The boilerS' maximum operating time is limited only by the amount of fuel oil and feedwater available. Currently, two boilers are operational.

Accumulators

Located next to the facility are three accumulators (see figure 1) used for the storage of steamahdhot water. Each has a 12 foot outside diameter, 53.5 foot long cylindrical section, 2:1 elliptical heads, 2-3/16 inch plate thickness, 3 inch foam glass insulation, and a usable storage of 42,000 gallons of charged water at 500 pounds per square inch gage. The two boilers presently in use can cblrge the accumulators in five hours.

Primary and Secondary Ejectors

Two Elliot steam jet ejectors are driven by steam supplied as the accumulators are blown down through a pressure regulating system located in the valve house. The ejectors pump down the exhaust duct to simulate altitude conditions at the nozzle exit.

The first stage ejector has.a throat area of 34.45 square inches; the second stage ejector, 134.46 square inches. The total steam weight flow at a 150 pounds per square inch regulated inlet pressure is 363 pounds per second; the second stage alone accounts for 290 pounds per second. The pumping capacity of these ejectors are 10, 20,._3.0 Pond 48 pounds of gaseous hydrogen with exhaust nozzle exit pressures-of 1.5, 4, 8 and 14.7 pounds per square inch respectively. The system can evacuate the 30,000 cubic feet of duct to 0.5 pounds per square inch in approximately 45 seconds.

Zero Flow Ejector

A zero flow ejector shown in figure 3 was used to maintain low engine exhaust nozzle back pressure. This ejector, utiliZing the kinetlc energy of the hydrogen propellant, in comb.ination with the two stage steam driven ejectors, keeps the engine nozzle flOWing full throughout most of the test duration. The contraction area ratio of the zero flow ejector is 1.6, with diffuser inlet diameter of 32.5 inches; and the contraction angle is 6 degrees. The length of the second throat is 6 times the diameter and the subsonic diffuser expansion angle is 15 degrees •

•"sUE .Ii*

; 'CgNrtnpmITiN 4.

Flares

,In order to have a coritrolled source of ignition for the disposal of the hydrogen in the eXhaust system, 12 equally spaced, continuously burning natural gas flares are mounted at the exit of the second stage ejector. These flares are ignited by the propagation of a flame initiated from the valve house and passing up a tube. A schematic of the altitude exhaust system is shown in figure 4.

GASEOUS AND CRYOGENIC SUPPLY

All of the gaseous and cryogenic supplies are stored at the ground level either in compressed gas cylind~r semi-trailers, fixed compressed gas storage bottles or mobile liquid, dewars. ' A present, two liquid dewars, four gas trailers and 100,000 standard cubic feet of permanent storage can be used to conduct a test run.

The mobile dewars are of the standard typ~ with vacuum jacketed tanks and reflector shields. Through the use of a liquid boiloff heat

,exbhanger, 'the 'dewars are'self-pressurized for transfer of the liquids. ,They have multiple size outlets and capacities ranging from 3600 to 6000 gallons. Due to the height of the test stand, liqui~ nitrogen is transferred by an external ,facility pump.,

The compres'sed gas trailers'have a capacity of 70,000 standard cubic feet" each 'at 2400 pounds per squS:re inch. "The permanent storage of 100,000 standard cubic feet consists pf' fo~ cylindrical, hemispherical end sh8.pe bottles. The'dewars, trailers and bottles are shown in figure 5 as they are connected,to the facility.-

MAJOR SUBSYSTEMS

There are a number of support systems needed to conduct a research test run and they are located at several locations ,within the test stand. The largest of these systems is that fqr gaseous nitrogen.

Nitrogen System

" In'gene!al, 'the' permanent storage is used to purge the large exhaust "duct and the trailer .is used for pneumatic valve control, vent stack and pump, reactor and terminal cabinet purging;' The system is shown in figures 4 and 6.

, ",,' ' . ... ' " ,',iI. --tHHWliiillflf:&'tL

5 8BIW!£EN!iAL

Helium Sys tem

One helium gas trailer is sufficient to carry out a test run. In addition to purging the research hardware, it is used to keep frost from collecting on viewing windows in the reactor and nozzle during the test run. Other uses include transfer line, critical electrical cabinets and tank insulation purging. The helium system is shown in figure 7.

Hydrogen Sys tem

The hydrogen systems, both gaseous and liqUid, are shown in figu~e 8. The liquid hydrogen is transferred to the top of the tank through a vacuum jacketed line. During the test run, gaseous hydrogen is used to pressurize the tank. The thermal insulated propellant feed lines connecting the tank, pump, nozzle and reactor are also shown in figure 8.

Hydraulic and Lube Systems

To maintain the proper pressure in the tank and weight flow through the research hardware, hydraulic servo valves are used. The hydraulic system used to operate these valves consists of two independent units, each pumping 20 gallons per minute through a 10 micron nominal filter at 3000 pounds per square inch. Should one unit fail, the load can be switched to the other.

A separate oil system provides lubrication for the Mark IX turbine and torque meter bearings; A flow rate of 5 gallons per minute of MIL25336 type oil is maintained at 350 pounds per square inch pressure. The schematics of the hydraulic and lubrication systems are shown in figure 9.

Eductor

An eductor system is used to expedite the cleaning and inerting of the tank, hydrogen fill line and pressurization lines. The eductor is a nitrogen gas driven aspirator pump which reduces the pressure in the tank and_lines from atmospheric to 80 millimeters of mercury absolute in about 15 minutes. Additional evacuation from 80 to 10 millimeters is provided by an oil diffusion pump. The vacuum is broken with helium and the process repeate.d several times after which the system is safe for use with hydrogen.

,mET IIJI!mI 6·

Safety System

Standard gas analyzers are used to detect hydrogen leaks at stratigic- lOcations throughout the test stand. Upon the detection of any minute quantity, the amount of hydrOgen and location is immediately displaled on the safet~ panel-and annunciator panel in the control room. Large amounts of hydrogen in the top of the test stand will initiate a shutdown and a carbon dioxide fire extinguishing system can be triggered from the control room.

Electrical Systems

-Cables.- The test stand, including the altitude ~xhaust system, and research apparatus are connected to the control/t(uilding by under­ground conduit-and overhead- transmission lines. Cables also tie into the pump, valve house and boiler house.

There are six 125 conductor externally shielded, number 16 AWG wire cables running from the test stand to the control room for operating the many systems preViously described. In addition, three more cables, each containing ten four conductor- shielded, number 18 AWG Wire, run from the cabinets on the 85 foot level in the test stand to the servo control­cabinets in the control room in one continuous,r~broken line.

The pump house, valve house and boiler house have two 50 conductor and one 25 conductor externally shielded, Number 16 AWG wire, cable respectively running to the test stand primarily for control and monitoring of the steam system.

The cabinets at the base of the test stand contain ~elays and terminal strips. The transmission cables terminate at this point and facility cables ~xtend from here into all areas of- the test stand. Power is applied to the normally-open contacts of the relays and sent to the various valves, solenoids and sWitches on command from the control room. This. enables large amounts of power to be controlled remotely and not carried over the long transmiss ion caqles •

.Television, Videorecorder,·Motion Pictures.- To aid the control room operators in conducting a test run, television coverage of the trailer, secondary steam ejector and research apparatus is required. The television cameraS have pan, tilt and zoom features which are controlled at the control' room. Motion picture photography from a safe distance provides documentary coverage of the area during the run when desired. Information on the various TV monitors in the control room can be recorded by selective SWitching onto a videerecorder.

C02tTI.W!i I!i

7 ..

CONTROL BUILDING

The control room is lo~ated approximately 2300 feet from the test stand in a reinforced concrete structure. Through the transmission cables and appropriate circuitry, all of the test runs are conducted from this building. Much like in the test stand, cabinets are used to termin­ate the transmission cables and,connect the various cables that are routed to the control panels.

There are 20 facility control cabinets with space to house equipment for future experiments, and 7 servo control cabinets positioned in an ilL" shape. The controls of the carbon dioxide system and hydrogen detection system are shown in figure ~O._ To the right of this are the steam system and nitrogen altitude exhaust purge system control panels. With the aid of the graphic panel and closed circuit television, two people are able to operate these systems.

The cabinets extend to the right in figure 10 and are shown in figure 11. This constitutes the main facility control panel from which the run'is conducted. Event recorders are used to set up the automatic timers and record the open and closed position of all the valves during a te~t ,run. Each valve is sequenced in a proper order and the test run proceeds automatically upon starting the main timer •

.Tb.eannunciator system monitors key safety limit parameters and will initiate a shutdown or warning. The graphic panel indicates the condition of the test run at all times. Area warning, television and motion picture camera. controls are also shown. Again, two people operate the facility control panels.

The servo control panels are located to the right of the facility control panels and are shown in figure 12. They contain eqUipment for

,programing'a test run. Pump performance monitoring pane~ servo controllers, amplifiers, servo control programer and over-speed indicators are some of the items needed to support a test run. Three people. monitor and control the test run from this ~vantage point.

TEST PROCEDURE

In preparing the .facility for a test run, some 25 engineers, mechanics .and technicians are required for a two day countdown. During this time all instrumentation is checked and calibrated, all supporting system operations verified, high pressure gas trailers and liquid dewars brought into position and run programer and timers set up for the-particular test sequence.

QQ)1i'IMltfBtL

Prior to ~oading liquid hydrogen ~n the propellant tank, the transfer lines and. tank are evacuated and inerted with. helium, the exhaust 'ciUct inertedwith nitrogen, and a final electrical calibration .signal (EC) for the data system is taken.

With. all systems in a ready condition and precooling of pump and feedline accomplishe~.the steam driven ejector system is initiated. When the· 'exhaust duct reaches about' 2 pounds per square .inch absolute, the ~rogram timers start the,test run. After the test is completed" any remaini~g hydrogen in the tank is back transferred' and necessary procedures for securing the facility are carri~d out.

I,

Ii ilWIRIilJiiisPzL .. ..,.,

9

.. cgwrDl!tiI IAfJ

PART II - DESCRIPrION OF RESEARCH APPARATUS

RUN TANK

The run tank has a maximum capacity of 2000 gallons of hyp,rogen. It bas a le~gth of 15 feet, a diameter of-5 feet and is constructed of type 304 stainless steel. The ends of the tank are elliptical with a 2:1 ratio. It was hydrostatically tested at a pressure of 150 pounds per square inch gage and has an operating pressure of 100 pounds per square inch. The tank is insulated with 4 inches of polyurethan~_ type insulation.

-,

The top of the tank has two 4-inch, one 3-inch, one 2.5 inch and four 2-inch ports extended through the insulation. They are used for the liquid level probe, hydrogen fill and pressurization, return line, purge and burst disc connections.. ,ll

At the bottom outlet of the tank {~/a liquid anti-swirl vane , -assembly followed by a wire mesh filter/below the conve:r.ging transition spool. After the filter the liquid hydrogen flows through straightening

I 'vanes before entering the 4-inch'flowmeter. .

MARK IX TURBOPUMP ASSEMBLY

The Mark IX turbopump assembly consists of three ,separate components: (1) the'pump, (2) the torque meter and (3) the turbine. The three compon­ents are mounted in line .in a_ vertical 'configuration by using a tripOd type mounting frame which has the capability of indiVidually positioning each component in order to obtain an accurate alignment. Power from the turbine is transmitted through the torque meter to the pump by use of spline gear­couplings. A photograph of the assembly is shown as figure 13. ,

Pump

The pump is composed of an axial entrance mixed-flow axial-discharge inducer stage, six identical high-pressure axial flow stages and a single outlet collecting volute. The pump is designed for pumping liquid hydrogen and is capable of producing the flow-rate and pressure requirements of-a NERVA ,type engine. The unit is self lubricating, using liquid hydrogen as the lubricating and cooling fluid for the bearings, and has a rotating balance piston to compensate for internal axial thrust loads.

, .,

10

. t":.­.,TorqueMeter

. '.The ,torque.meterass,embly is composed of a calibrated torque shaft with a 60 tooth rotor and spline cat e,ach' erid, two. magnetic pickups and a housing containingtwQ oil lUbricated bearings~ The. angle of twist in the shaft during operation is determined by· meal;>uring the, .pha~e difference between two signals generated by ~~e. toothe4rotors .and magnetic. pickups. The current configuration ~s capable ()f ~easuring torque values up to 28,000 inch-pounds~ .A thinn~r walled calib~ated torque spaft ,ba~ been fabricated for measuring torque ·values. for Ib~ speed anq,powerlevels and will be used for measuring't()rque values .up·to .1800,inch-pol,lll~.

Turb,ine

The turbine is a six-stage pr-~ssure~~omppundedaxialflow unit ·which is designed for operation;using the products of combustion from 02~H2' hot H2 or ambient temper~ture H2o The unit wa~ designed to deliver 15,000 horsepower using.the combustion products of H2-02 and is capable of, deliverying NERVA power reqUirements using ambient temperature H2 •· The first' three stages .u~e impulse ·typ~ blading .and the last three use free-vortex type blading. The working fluid enters the turbine thro~~ a singie-entrance collecting scroll and is discharged'through an axial core type diffuser. , Oil is used as the lubricating fluid for the bearings.. .

-:~REAcrOR .

Description

The reactor (figure 14) used in the e;'Xperimental' program is ~sically the same as the Ki.wi B-lB as uped in the ROVER program. However, certain modifications and compromises to the hardware design were made to effect economy in fabricating while still satisfying the particular cold flow ' test requirementso The various diameter coolant passages in the graphite fuel elements were averaged to a singJ.,e q.iameter providin,g the. Same total flow area as in the Kiwi B..J.;B reactor ~ Additionally the extruCl.~d .graphite

,.fuel element coolant passages are not c~ated wit~ niobium carbide' nor are the elements loaded with uranium., The material of the reflector is aluminum rathe~, than:beryllium'. The s.imula~~d:,co~t:rol r~ds '~d poison plates. are alum?-I1um and no ,provis.i<?n ..is. mac1e for their external movement by actua;tors· as in the Kiwi hardware. The._ alum~num pres'sure vessel,. is provided with twelve' 1-7/8 inG~ diameter viewing ports, 6 each at the plane of the reflector inlet and at the reflector outlet. These ports allow ·visual recording, by hi-speed motion picture photography and/or a television camera, of the q~litati~e c,Qndition of the propellant passing through the reflector system.

11 Cm%lutfr btL

The reactor components were supplied to the Center by ACF Industries, Albuquerque, New Mexico for the U. S. Atomic Energy

.~ommission. Upon receipt. and inspection of the various components, extensive pressure and temperature instrumentation were installed prior to final assembly.

Assembly

Figures 15 through 19 are provided to illustrate the components contained within the reactor as well as some of the steps required in the assembly. Figure 15 is typical of the graphite fuel modules and fuel elements and indicates some of the installed instrumentation. Figure 16 shows the assembled core.. Figure 17 shows the cylindrical graphite reflector installed on tqe core. Figure 18 is a view of the assembled outer aluminum reflector assembly. Figure 19 shows the final .closure of the pressure vessel~reflector assembly with the core, inner reflector system and pressure vessel dome end.

Inasmuch as the reactor Was assembled at ~ewis and the test stand located at Plum Brook Station some 50 miles away,. the transportation of the reactor to the test 'site was cause for some concern. A history of the possible "g" lOads to which the hardware might be subjected in transit was felt necessary ~o assure core structural integrity. Accordingly the three axes of Vibratory motion were monitored during transport using accelerometers mounted externally on the pressure vessel. Figure 20 is a view of the reactor' mounted on a trailer equipped with an engine generator and an instrumentation housing.

Additional precautions taken to minimize the transportation shock loads were the addition of teflon shims between adjacent modUles, the reduction of trail.er tire pressure to 40 pounds per sqUare inch from 75 pounds per square inch, the use of· a commercial waffle-like rubber shock padding under the reactor assembly stand, and driving the vehicle at speeds of 10 to 30 miles per hour depending on highway conditions.

The analysis of the accelerometer data indicated maximum acceleration of 5.50, 1.65 and 0.80 "g" peak to peak in the vertical, horizontal (in the direction of travel) and horizontal (normal to direction of travel) directions respectively. The normal running condition indicated an average acceleration of 0.50 g.

Installation

After delivery of the reactor to Plum Brook, the teflon shims were removed from between the modules and the RN-2 nozzle was installed (see figure 21). The assembly WaS thus mounted in a special turnover fixture (figure 22) provided to orient the nozzle in a down;.firing attitude and then lifted into the test stand. ~

e6hi lDEiHm

12

gPTTEWlIi'iEMJ" ,-3">

After ini~ial helium,gas checkout tests, there~ctor'was removed from its 1IlC?unt, placed in the turnover stand (figure ~2) and"'theq:ozzle removed' for inspection .and permanent shimming' of the core modules.' The center hole in each fuel "element was inspected along the entire" length with a Lewis developed helium crack detector probe·to·determine whether any structural damage to the core resulting from delivery and sUbsequence checkout tests had occur~ed. The inspection ind~cated n~ broken modules or fuel elements.

The structural int.egrity of the core was of concern .because of the .number of tests to be ,conducted in the. 'experimental program. There­fore, st~ps wel;'~ taken to minimize cor~__damage due' to vibrations 'during .test by bonding aluminum s.hims (f,igtfre- 23)- between the. modules' wi th an epoxy adhesive. Shim thic~ess~s of 0.030 inches and 0.125 inches was sufficient to fiii in the" 'void and leave the module in its originai position~ After all" th;' shims were installed," the modules could 'Il:0t move laterally. The bottom -of the core was painted wh~t~ for better l.ight distribution and photographic resolution.

Figure 24 shows the hydrogen feed line, nozzle and reactor as they are mounted within the test stand.

PROPELLANT DUCTING

The propellant fee~ line, shown in figure'2, may. be separated into two sections: the. tank discharge t.o pump inlet section _and' ,the p'ump dis­charge to nozzle inlet manifold. section.

Tank Di~charge to pJmp.Inlet

The tank discharge to pump inlet section is nominally' an eight-inch diameter vertical duct. One foot below the· tank discharge opening the line reduces to a four-inch .diameter to accommodate a four-inch diameter flowmeter •. The flowmeter is.a t~rbine type·meter capable' of measuring liquid flows in the range of zero to 20 pounds per second. Directly up­stream of the flowmeter, and extending' into the' tank discharge nozzle, is' a filter and straightening vane section. The -'conical filter screen is made of perforated sheets of sta:inless steeL;....~ The straightening vanes are in accordance with ASME specifications.· From the flowmeter discharge to the pump inlet, the duct diameter is eight inches. Within this section there are two 8-inch butterfly 'type valves in series. The upstream valve is a pneumatically operated open and close facility tank shut-off valve. The downstream valve is a servo-hydraulically operated flow control valve. Below the flow control ,v~lve is an instrumentation section 'where pump inlet conditions are-~easured.

121_. dSdP

13

The total .1ength of the tank discharge to pump inlet section is 8-1/2- feet. Four inches of foam-in-place insulation covers the entire length of the duct.

Pump Discharge to Nozzle Inlet

The pump discharge to nozzle inlet manifold section' is nominally a 4 inch diameter duct. One and one-half feet downstream of the 'pump discharge is a venturi type flow meter with a 1.9 inch diameter throat. Two feet·be1ow the venturi meter the line branches into two sections. One section is a two-.inch diameter tank return line with a servo controlled butterfly valve used for flow control, if needed; and the other section is the main propellant line •. A four-inch servo operated butterfly control valve is lOcated two feet downstream of the tank' return. tee. Immediately ahead of this main fiow control valve are two bleed lines. One bleed line is vented-to atmosphere to allow a small flow during pump chi11down, and the other bleed line is connected to the ejector system to .a11ow disposal of chi11down fluid immediately before the ma~ flow valve .is opened. Both bleed lines contai~ two-inch on-off plug type valves. .

Approximately 18 feet downstream from the main flow control valve, the propellant line is divided equally into three 2-3/8 in~h diameter ducts which feed the nozzle inlet manifold.. Immediately upstream of the three.equa11y spaced ducts is a quality meter for determineing the state of the. fluid at the nozzle inlet. This section of the propellant feed line. from the pump discharge to the spider is covered with four inches of foam-in-place insulation. -

NOZZLE

Description

A regeneratively cooled (liquid hydrogen) tubular-wall nozzle, figure 25, is currently being used for this series of tests. This nOZZle, designated RN-2, has a contraction ratio of 17.3:~, an expansion

. ratio of 12:1, an. overall length of 58.02 inches and a maximum diameter\ of 40.72 inches at the nozzle flange. The inside diameter at the reactof end is 36.25 inches, the throat diameter is 8.72 inches and the exit I inside diameter is 30.21 inches.

The nozzle consists of tubular wall construction, fabricated from 180 tUbes and utilizes single pass cooling. The liqUid hydrogen enters the nozzle tupes through three equally spaced inlet connections on the manifold located at the exit end of the bell-contoured expansi.on nOZZle,

IiIWII,aLd.

·.7tEE'ITifm '14

and flows toward the reactor end. The formed and tapered tubes are made of Inconel-X material having a constant Wall· th:j.ckness·.of .0.009 inches. For the majority of their length, the tubes hav~ an octagon cross section. The cross section changes to round ends where"the tubes join with the fuel inlet manifold and to square ends where the tUbes join the r~actor end ring.

A continuous Inconel-X shell (extending from the reactor end of the nozzle to the throat and providing the necessary external structural'support) surrounds the tube bundle ·and.as a result of furnace brazing forms an integral assembly. Bands made from Inco~el~X surround the tubes in the divergent region of the nozzle •. The main flange, which 'b~lts to the reactor pressure vessel,as well as the fastening bolts, are cooled by liquid hydrogen. Normally the hydrogen coolant passes into the flange manifold and through. the holes drille4 throught

~ . .'

the center of·the boltsirito the reactor pressure vessel. However for these tests there were no holes in the bolts that were .used.

Previous proof tests with chemical propellants (heat-flux simulation tests ) had resulted .in transverse thermal buckling of the hot-gas side tubular wall structure and in progressive transvers~ cracking. These failures were repaired by means of "saddle" patching. SUbseqli~nt to discovery of the existence of the tube buckling condition, c~acks and repairs, the nozzle was tested to determine means of eliminating the tube buckles. Methods evaluated included braze fillets between tubes, shot peening of gasoside tube surface, effect of coatings, etc. As a result .of these tests, additional cracks were produced. It was in this condition that the nozzle was received. Inasmuch as the proposed use of the nozzle in the B-1 facility consisted of "cold flow ll startup ·test::;, soft solder was used. for the necessary repairs •. These repairs to the hot gas side o~ the tubes were difficult to accomplish because of the contamination of the ~ube surface as a result of previous firing and modifications. The repairs were SUbjected to 15 pounds per square inch pressure for leak checking. Leaks between the tubes and the pressure shell were also discovered but these could not be repaired. A manifold was welded to the pressure shell and the leakage was collected to be vented into the altitude exhaust system. During initial test rUns, the tubes have been SUbjected to 50 pounds per square inch withou.t apparent damage.

The warped main flange of the nozzle was, re~machined to accomplish good s~aling be~ween nozzle and reactor pressure vessel. To.perform this machining operation, a complicated fixture had to be designed and fabricated.

Modifications

The experimental program requirej·two· modifications to the nozzle. A camera .and light.port were added SO that films could be taken of the reactor core exit face .during the test and a por~ from which turbine

•F 3IB&hWl

15 smTPIilui!i i!I

gas is taken in the hot gas bleed cycle simulation. Figures 26 and 27 illustrate the nozzle alterations. In both of these alterations the coolant flow is redistributed around the ports.

germTiM"!!f!I!;

18

_Description of Transducers, Thermocouples, Camera? etc.- Several types of transducers are used to measure temperatu!e, pressure, speed and flow. The resistance thermometer transducer utJl:izes a variable resistance sensor for measuring temperatures. Signal conditioning. equip­ment p~ovides proper signal voltage for analog.and digital. recording systems. Fast. response and accurate cryogenic temperatur~s are desired character­istics using this type of temperature measurement.

Thep;ressure transducers in use are of the bonded anci unbonde.d strai~ gage type of sensing element. Again, signal conditioning eq~ipment pro­vides zero set and span coilt~ol and appropriate recording voltages. The transducers can be used either in.absolute or differ~ntia.l applications.

Copper-~onstantan thermocouples are used in many temperature measure­ments.•. For metal temperatures, number 30 AWG copper-constantan wires are embedded in a round copper bead~and installed as shown in figure 44a. On the nozzle tUbes, the thermocouple junction is welded (figure 44b). ·For installation of thermocouples in graphite, the point junction was installed in a drilled hole and a graphite mixture packed around the wires (figure 44c). Iron-constantan thermocouples are also used to measure temperatures.

Piezoelectirc type transducers and the associated eqUipment provide acceleration data on the research apparatus items. _

Turbine and venturi type flow meters are used for liquid hydrogen flow measurements. The capacitive type liquid level gage in the porpellant tank is also used to indicate flow. .. .

. Electro-magnetic tyPe pickUps are mounted close to a tooth ·rotor on the turbine for speed indication.

A· torque meter, between the pump and turbine, indicates torque by measuring the· electrical phase displacement of signals from two electro­

.magnetic pickups mounted ciose to two tooth rotors on a calibrated torque shaft (figure 32).

A capacitance grid type quality meter located in the propellant duct is used to measure the quality of the liquid hydrogen flowing into the nozzle (figure 24).

Both high and low speed motion picture ·cameras are used for data purposes. Variable speeds of 1000 to 18000 pictures per 'second on a 400 foot capacity reel and 1000 to 3000 frames per second on a 1200 foot reel are available for obtaining the desired data.

..1'''' ..

I '/

19

DATA ACQUISITION

The data acquisition equipment is located in the H building, approximately 5500 feet from the test stand. The central automatic data recording system is selectively available to all test facilities at the Plum Brook station. The recording is done by types of equipment which are classified as analog and digital. These two recording systems are independent and complement each other. The analog system has the advantage of high-frequency response, while the digital system gives greater accuracy but with lower frequency response characteristics.

Digital System

For the digital system, the low-level signals from the transducers are transmitted over the previously described cables. Any voltage

. amplification required is provided internally to the equipment. The prob­lems encountered in transmitting such low-level signals are the effect on the signal of the electri~al characteristics of the cable itself and the addition of extraneous e~ectrical noise to the signal. The. combination of these effects contri.bute·from 30 to 80 microvolts of noise on all input channels to the recording equipment.

The 10 KC (figure 46) unit is a self-contained, 100-channel, low­level input, digltal data acquisition system. The system consists of two 50-channel low-level, solid state multiplexers, an eleven-bit binary analog­to~digital converter, a format control unit, a digital tape recorder and five digital-to-analog converters with incandescent displays. Each low-level multiplexer accepts up to 50 channels of bipolar inputs (0 to 10 millivolts) and commutates the analog voltages at a rate of 10,000 samples per second. The system has an overall accuracy bet~er than three tenths of one percent.

The 4 KC (figure 47) unit is a 192-channel, low-level input digital data acqu'isition system. The system uses a mechanical type multiplexer sampling each 20.8 times per second for B-1 data. The premultiplexer switches the 192 input, two-wire circuits to 8 two-wire circuits sequentially. The 8 signals are amplified and mUltiplexed again according to the master programming and control panel with:t.n the system. The signal is then con­verted to an ll-bit binary signal and recorded similarly to the 10 KC system. The system has an overall accuracy of four tenths of one percent.

Analog System

The analog system includes FM tape recorders, pen type oscillographs, light sensitive oscillographs, and voltage balance strip charts. The low level transducer signals, which are to be recorded, are amplifi~d (0 to 1 volt) in the terminal room at the tes4~6tand and transmitted:!on cables similar to the low level digital recorder.

S 2OrTII!!1iI B&

if? tIDtL 20

The FM system is capable of recording 24 channels of .high frequency analog signals. The method of recording is frequency modulation. of a 20 KC carrier. The accuracy to which a signal can be recorded and played back is 1 percent of full-scate voltage. The frequency· response of the system is ±1/2 decibel from zero to 10,000 ·cycles per second exclusive of the input cable characteristics.

Four light sensitive oscillographs, each capable of recording 36 channels of information are available.. Using high frequency galvan­omete-rs, information containing oscillations as· high as 3000 cycies per second can be conveniently recorded and a~lyz~d.

There are several other types of analog recorders in use, each .having its own merits. The most common one in use is the B channel, direct writing, pen type oscillograph.. The maximum full~6cale frequency response is 58 cycles with one .half percent full-scale linearity.

The vol:tage balance .strip charts in use have a fixed 0-10 ·millivolt input. Although they have good accuracy, they lack the versatility of signal input and frequency response. The.accuracy is one half of one percent and a response time from zero to full scale of one second.: In general, these strip charts are used to record facility parameters •

./

DATA PROCESSING

Computer EqUipment

The Lewis digital data process·ing System which is used to retrieve data from the B-1 facility digital data records consists of a modified Univac 1103 computer with auxiliary equipment and the IBM 1401 input­output system. ·(See figures 47-49). The 1103 computer has bee;J.. modified in several ways. A magnetic tape system has been added with 8 tape handlers to handle input and output information along with internal storage. A 20 K magnetic core storage has replaced the original 1 K core and 16 K drum storage. The number of internal commands has also be doubled.

Auxiliary to the 1103 is a data playback and display system through which the raw data may be displayed on a storage type oscilloscope. A paper tape punch, and a paper tape reader and punch directly coupled to the 1103 complete the system.

The 1401 input-output system utilized for B-1 data processing consists of the 1401 computer, a card reader and punch, a printer, an additional core for the 1401 and an inquiry station for initializing the 1401 system.

SS?IfIIII'lI8S &

•

21'-

Computer Program

Computer processing is done in four main steps. The first stage of the program consists of instrument calibration. The purpose of calibration is to-adjust the measurements·for systematic. errors, such as instrumentation drift and line losses in the transmittal of the signal to the recording ·system. This is· accomplished by use of_the electircal calibrations recorded just prior to the test. The average values of the high and low voltages re­corded during the electrical calibration are determined for each channel and used as calibration points. These averages can be taken over any number of data points, and in such a way as to eliminate the transient response of the instrumentation during the electrical calibration.

Calibration.- For all measurements, such as pressure transducers, where the measured value in engineering units is a linear function of the measured voltage, a two point ''Hi Lo" calibration is used. During electrical calibration, conditions of zero and 95 percent full scale are simulated for the transducer. The average values of the voltage recorded at these points are used to determine the slope and intercept of the calibrated straight line, which is then used for any future conversion of recorded voltage to engineering units.

For measurements in which the value in engineering units is nonlinear ·with respect to voltage, a one point zero adjust calibration is used. In this case, a voltage is placed in the circuit of the transducer to simulate a known measurement. The difference between the average value of the recorded voltage and the voltage expected is assumed-to be the error in every measured voltage. Each voltage measured during the run is then adjusted by adding this error before converting to engineering units.

Averaging.- The second step in the processing of data consists of averaging the measured voltages over· a specified number of data points for each measurement. The averaging routine is useful in minimizing the effects of noise on the recorded signal. . The number of points over which the average is taken can be easily varied. Output from the averaging routine consists of the number of points over which the average is taken, the average voltage, and the~andard deviation for each measurement; these can all be printed on paper .. for any part of the run. Faulty information is automatically eliminated from the averaging.

Conversiori.- The third step in the reduction of data is conversion from voltage to engineering units. Curve fits of engineering units versus voltage are made from calibration data for each measurement which is nonlinear with respect to voltage, and stored in the program. The measured voltage, corrected if possible by a zero adjust calibration, is then substituted into the curve fit equations to obtain the value in engineering units. For the measurements

..which are linear with respect to voltage, the value in engineering unit is determined using the slope and intercept calculated from the 'Ei Lo" cali~ration.

I UilWlb&4Pm'

22.

Output data in engineering units are printed out for each channel in column form versus time. Time t =0 corresponds to the point in time where the governing valve was opened to initiat~ flow through the system.

Terminal Calculations.- The fourth step in the P!~cessing of data con­sists of calculations (tern.J,inal calculations) based'upon the output data in engineering units. These, for example, consist of the calculation of fluid flow and heat transfer parameters. The thermodynamic and transport properties required for these calculations are available in a parahydrogen properties subroutine ("B.W .R. ") based upon the modified Benedict ..Webb Rubin equation of state and related equations from references 2 and 3.

Data which is faulty for any combination or four reasons is printed out with an alphabetical tag. Azi "A ir tag. is received· if the input informa­tion to a CUrve 'fit lies outside the area in which the curve fit is accurate. A "B" tag is used ifan·1.l1egal operation (such as taking the square root of a negative number or dividing by zero) was performed some­where during th~ calculation. A "nil tag is used if.a number occurs which is too large or too small for the computer to handle. An.,r~1I tag is used if pa~t of the input has been coded out of the calculations. Combinations of the above faults are identified by additional letter t~gs. Any number so tagged is not included in an average of several variables.

The output from the 'c~lculations is also printed in a column form versus time. The exper-imental output data and results of the calculations can als~ be printed in plot form versus time.

The, computer program for processing B-1 data is prepared as far in advance of the run as possible. The engineer ,gives the programmer calibra­tion data, terminal equations and material properties, (see figure 50, step. 9). The program is .then s-libmitted in typewritten form to be punched out on cards on the 1401, (step 10). The cards are then ~sed as input for the tape asse~bly (step 11) process on the 1401, in which the program is put on magnetic tape. This tape' is then used as direct input to the 1103 for data processing.

Data Processing Procedure

The data tapes from the 4KC and 10 KC'digital recording systems at PlUm Brook are brought to Lewis for processing on the Univac 1103 computer (figure 50, step 1). The engineer initiates the procedure by'observing the recorded si'gnal on a display unit auxiliary to the 1103 consisting of 'magnetic tape reading equipment and a storage type oscilloscope (step 2). In this manner both calibrations and run data are checked for electrical noise,' shorts, and other flaws in the recorded signals. All measurements found to be defective are then eliminated'(coded out) from all further processing~ In addition., the engineer determines the blocks of data which are of interest and to be processed further.

&U2&£iIM

'~, ---'" ......

gmw &1IBfiJ 23

The identification numbers of the blocks of data which are to be processed are 'then punched on paper tape (step 3). This tape, along with the magnetic data tape is then used as input to the 1103 for the retrieval process (step 4). Retrieval consists of changing the format of information on the data tape into a format more convenient for" calculating on the 1103.· In addition, all recorded data are examined during, retrieval for parity errors, and other errors due to flaws in the recording systems. Any faulty data is automatically tagged out of subsequent calcUlations. The magnetic output tape from retrieval is then used for any further processing, and the data tape itself is placed in storage (step 5).

The engineer also submits data processing instructions to the programmer (step 6). This informatio~ consists of input particular to each run. Included in this information are the areas of information to be processed, measurements to be coded out, calibration instructions, and minor changes in the terminal calculations due to changes or flaws in the recorded instrumenta­tion.

The programmer submits this information along with program controls on a typewritten data plan. This data plan is then punched on a paper tape (step 7). In the plan assembly process (step 8) this paper tape is read into the 1103 through the paper tape reader, and processed to change the format of information on the tape into a format compatible with the magnetic pro­gram tape. Output from the plan assembly is then punched on a final plan tape, which is used, along with the magnetic program tape and the magnetic retrieval tape, as input for dat~ processing on the 1103., The advantage of this system lies in the ability to modify calculations in.the main program qUickly and efficiently to suit the particular needs of each run.

The 110} output is recorded on magnetic tape.. The information is then changed into a format compatible with the 1401 system during the transcription process (step 13) and transferred to another magnetic tape. This tape is then read into the 1401 system (step 14) and the data lists and plots are printed.

A system is also in operation to automatically process output data from the 1103 for input to 7094 computer prediction codes written for the Various components of the nuclear rocket system. The information on the transcrThed output tape is changed to 7094 format on the 1401 (step 15) and recorded on another magnetic tape. This tape is then processed on the 7094. All data that are to be used as input to the 7094 prediction codes are fit to a quadratic curve. Data points are then calcuiated from the curve fit equations at speci­fied times. The output tape from the 7094 curve fitting routine is then

'punched out on cards (step 17) in a format acceptable to the 7094 prediction codes (steps 18-21). This system allOWS the capability of eliminating obviously wild data points from calculations in the prediction codes, and produces a quasi-steady state input to the codes, which are based essentially upon steady state approximations.

--

APPENDIX A

SYMBOLS

Instrumentation i~em number pref.ix letters:.

First letter

T Tank

P Pump and piping

N Nozzle

R React0r

E Exhaust system

Second letter

R Resistance thermometer probe

P Pressure

T Therm0couple (copper-constantan.except where ·noted otherwise) - ...

F Flow meter

S Speed

A Accelerometer

M Resistance thermometer, surface mount

L Liquid level

Q Quality

I Reflector inlet window

o Reflector outlet window

c Nozzle window

....

25

APPENDIX A, (Cont'd)

Measurement description symbols:

Tfl Fluid temperature

Tw Wall temperature (surface thermocouple)

Tm Material temperature (embedded thermocouple)

P~ Static pre~sure

Pt "Total (or velocity) pressure

. w Flow rate

26

REFERENCES

1. Livingood, John N°. B.et. °a1.: Nuclear Rocket Simulator Tests: Flow Initiation with No Turbine GasjTarik Pressure, 35 PSIA; Run 1. NASA-Lewis Research Center, July 1964.

2. Roder, Hans M. and Goodwin, Robert D.: Provisional Thermodynamic Functions for Parahydrogen. N.B. S.'~oT.N. 130, N.B.S. CrYQgenic

°Lab., December 196L.

3. Goodwin, R. D., Diller, D. E., and Roder, n. M.: ~ovisional

Thermodynamic Functions for Parahydrogen in Liquid, Fluid and Gaseous States at T~mperatures up to lOOoK and at Pressures up to 340 Atmospheres, N.B.S. Report No. 6791, N.B.S. Cryogenic Lab., August 1961.

2mWilZtILtB

27

LIST OF FIGURES

Facility

1 B-1 Facility

2 Nuclear Rocket Cold Flow Experiment in B-1 Facility

3 ,Altitude Exhaust Duct System and Instrumentation

4 Bottled Nitrqgen and,Steam Systems

5 B-1 Facility Gaseous and Cryogenic Supply

6 Nitrogen System

7 Helium System

8 Hydrogen System

9 Hydraulic and Lube Systems

10 B-1 Control Room Panels

11

12

B-1 Main Control Panels

B-1 Servo Control Panels

) l f

13 Mark IX Liquid Hydrogen Turbopump Installation

14 Reactor Sketch

15 Instrumented Fuel Elements and Module \

16 Assembled Core on Support Plate

17 Installation of Plunger, Spring, and Plug Assembly

18 Reflector' Sector Assembly in Assembly Stand I

19 Lowering of Reflector Assembly over Dome and Core Assembly

20 Assembled Reactor and Motor-Generator on Transporting Vehicle

21 Nozzle Installation on Reactor

22 , Reactor-Nozzle Assembly in Turnover Stand

OOlW1MIaM

WJl?IflEN Et;1UJ.

28

LIST OF FIGURES, Cont'd

Facility

23 View of Reactor Core Exit

24 Hydrogen Feed Line, Nozzle, and Reactor

25 RN-2 Nozzle

26 Camera and Light Port on RN-2 Nozzle

27 Bleed Port on RN-2 Nozzle

28 B-1 Test Stand Instrumentation Terminal Room

29 Block Diagram of Facility Instrumentation

30 Tank Instrumentation

31 Turbo-Pump Instrumentation

32 Piping Instrumentation

33 Nozzle Instrumentation

34 Nozzl~ Inlet Manifold and Spider Instrumentation

3~. Nozzle Coolant Tube Instrumentation

36 Nozzle Chamber InstrUmentation

37 Reflector Inlet Plenum Instrumentation

38 Reflector Pressure Instrumentation

39 Reflector Temperature Ins.trumentation

40 Pressure Shell, Control Rod, and Graphite Cylinder Temperature and Acceleration Instrumentation. (Z:Reference Plane Given in Figure 43). .

41 Reflector Outlet Plenum Instrumentation

42 Dome and Core Support Plate Instrumentation

43 Core Instrumentation

qnsuws:?!

29

LIST OF FIGURES, Cont'd

. Facility

44 Details of Typ.ical Pressure .and Thermocouple Installations

45 10 KC Data System

46 4 KC na.ta Sys tem

47

48

1103 Tape Handlers, Paper Tape Punch, and Data Display Unit

1103 Console and Paper Tape Reader

49 1401 System Showing 1401 Computer, 1402 Card Reader and Punch, and 1403 Printer

50 Block Diagram of Automated Data Reduction Procedure

".

gSIli'Hll!llii IA1

gg &

TABLE I.- RESEARCH INSTRUMEIn'ATION LIST, B-1 FACn.ITY

Messure­~m Description Measure­

lJeocript Ion meiitItem Description Number ~

Figure ):l. Run Tank Figure 31, Turbopulllp, (cont 'd) Figure 32, Piping, (Cont'd)

TR-l ;'f1' Ga5 Temp. -Top of Tank PT-9 T"w, Turbine Outlet Surface,r}c PP-40 ~,s' Feed Line Station B TR-2 Liq. Temp. -Bottom of Tank PT-lO " "Boss, Ire PP-41 Main Valve Inlet

II " nTR-3 " T~nk Ada~ter PT-ll Tn, Lube Oil InbOard, Ilc pp-42 II II IITR-4 PT-12 Outboard, llc PP-43 Feed Line Station E

TR-5 PT-13 Tv' Torquemeter Inboard PP-1i4 " " H H

TP-l Bearing 110. 1, Ilc PP-45 I TP-2 PT-14 Torquemeter Outboard pp-46 ~tl

II) Beari"ll No.2, llc PP-47TP-3 r­ PT-15 Turbine Inboard Bearing, PT-23 ;:w, Turbine Flow Station, llcTP-4w PT-24 By.paa5 Flow Station, IlcTP-5 Ilc(\l PT. 16 Turbine Outboard Beariag, PT-29 Tn' DJmp LineTP-6I

Ilc PT-30 Tw, Gimbal TT-2 'l'T-lriI

PT-31 " Mair. Valve Inlet Station

TT-3 PT-28 Pump Volute PT-26 On Tranoducer at PP-12

PT-32 Main Valve PT-33 ;,..' Main Valve Flange NeckTT-4 PT-41 ;fl' Tur~ine In;et PT-34 Gimbal Inlet Hinge RingTT-5 PT-42

TT-6 PT-35 Gimbal Exit Hinge RingPT-1i3 : Tur~ine Ou~let TT-7 PT-1i4 PT-36 Flange Near Station B (neck)

n II n"TT-8 PS-l Pump Speed PT-37 TT·9 PS-2 Pump Speed PT-38 Gimbal Inlet Hinge Ring

PT-39 Gimbal Exit Illnge RingTT-IO Torque Torquemeter TT-ll ;:... , Tank Adapter Flange PA-l Pump Inlet-Radial PT-~5 ~flJ Tur~ine F~o... Sta~,l0n

TT·12 Tank Shut-off Valve, upper PA-2 Pump Inlet-Radial PT-46 TT-13 " "" lo...er PA-3 Pump Torquemeter-Radial PT-54 Elbow-Inside RadiUS

II

n Elbow-Outs Ide Radiu5TT-15 On Tran5ducer at TP-4 PA-4 n ,. PT-55 Pipe l/all-1/2 in. from GimbalTL-l W Tank Liquid Level PA-5 Pump Torquemeter-Axial PT-56

PT-57 Gimbal Hic.I!je Ring.Outside EdgeTF-l Tank Exit Flowmeter PA-6 Turbine Inlet-Radial II n PT-58 Pipe I/all-Station ATSOV Tank Shut-off Valve P05itlon PA-7 n

PA-8 Turbine Exit, Radial Bo55 Station APT-59 PT-60 PT-61 PT-62 Pipe I/all 1/2 in. from flange

Figure 31, Turbopum.P PA-9 Turbine Exit, Axial P~lpe W~ll

Figure 32! Piping PT-63 Outoide Edge of Flanse PT-64 In5ide Wall-OPP. PT-62PR-IO Turbine Flow StationPR-3 ;,rl' PT-65 n II Pr-6l

PR-~ ~ Outlet DJct PR-ll By-pass Flow Station PT-66 P~pe W~ll-Station BPR-5 PR-12 4" Feed Line-Station A PT-67PR-6 PR-13 n " " PT-68PR-7 Turbine Inlet PR-14 " PT-69PR-8 Turbine Outlet PR-15 B CPT·70PR-9 Balance Piston Bleed (carbon) PR-16 C PT-71 Pipe Wall 1/2 in. from gimbal

PR-23 AFT Beari"ll Bleed (carbon) PH-17 D PT-72 Outside Edge of Gimbal Binge Ring

PP-l PR-18· D~s, ~mp In:et ~ct ElbOw-Ins ide Radiu5PT-73PP-2 PR-19 D PT-74 Elbow-Outoide Radiu5

PP-3 PH-20 E PT-75 Pipe Wall-Station Dpp-4 PR-21 E

" IIPT-76PP-5 PR-22 E

PT-77pp-6 PR-24 Inlet Line UpatreBlll of EPT-78PP-7 (Do""" treBlll) Main Valve

PT-79 Pipe l/all-1/2 in. from Flangepp-8 PR-25 Main Valve Inlet

linn PT-80 Outside Edge of Flange near E PR-26PP-9 PT-81 Flange at Station E

PP-IO PP-19 Turbine Flow Station PT-82 Quality Meter (Wide Section)PP-ll Pump Outlet Line PP-20 By-pas5 Flow Station

• II (Narrow Sec tion)PT-83PP-12 Venturi Inlet PP-21 4" Feed Line-Station A~s, PF-l '::' Pump By-pas5 Line FIOWlDeterBPP-13 Venturi Throat PP-22 PF-2 Turbine Fl"""",terpp-14 Turbine Inlet PP-23 Ptl n

PQ-l Quality Meter PP-15 11 " Upotream pp.16 Turbine Outlet pp-24 Ii" Feed Line-Station B Figure 33. Nozzle PP-17 DJ...ns tream" PF-18 PP-25 Po, 4" Feed Line-Station C

II n II II 0 :=~ ~5' Nozzle Tb:;0atPP-30 Turbine Lube Oil PP-26 II

PP-32 Interseal Bleed Pressure PP-27 E NP-40 Exit Bell PF-33 NP-41Balance Pi5ton Bleed PP-28 P " PP-3~ Pump DIscharge Pressure

t' UpstreBlll NP-42 PT-l Inducer Surface Inlet Flanse , PP-29 Ii" Feed Line-Station E NP-43

Downstre....Ilc NP-1i4 PT-2 Pump Dlscbarge Flange, Ilc PP-31 ;'s, Bydraulic Pressure NP-45 PT-3 Pump Outlet Pipe Wall, Ilc PP-35 Inlet Line Upstre.... of NP-50 Chamber PT-4 Pump Outlet Pipe Booo, Ilc Main Valve NP-51

PF.3€)PT-5 Venturi Inlet Flange, Ilc ~t, F~ed L~e Sta;10u C NT·33 ;:w, sup~rt Sk~,rtPT-6 Venturi Throat Flange, rIc PP-37 NT-34 PT-7 Turbine Inlet Wall, Ilc PF-38 NT-35 T , Throat RingmPT-8 Turbine Inlet Bo55, Ilc PP-39

Bottom T~nk Aw:-,pter

~fl, T~nk R~ke

PR-l PR-2

2

TABLE I. - RESEARCH INSTRtmNTATION LIST, :B-1 F'ACll.ITY, Cont '0

Measure­~m Description

Number

Figure 33, Nozzle, (Cont'd)

:=~ ~.." SUP:f.'rt Sk~,rt

NT-38 Tm, Throat Ring NT-39 T", Su~rt Sk:~I["t NT-40 T", NT-41 Tm, Throat Ring NT-42 ~.." su~port S~irt NT-43 NT-44 ;,m' SUf,port Skirt NT-45 NT-46 NT-47 ~m, Throat Ring NT-1,8 Su~port Skirt NT-49 NT-51 ::.." NT-52 liT-53 Tm, Throat Ring NT-54 ~v, Sur-port Sk~rt NT·55 NT-56 ;,m' ~oat ~~ NT-57

;:w,NT-58 No~zle Fl~e NT-59 NT-59 Band NT-70 NT-71 lIA-O Nozzle Inlet Manirold NA-270 NC-212 Camera Bart NC-335 Ligbt "'indo"

Figure 34, Nozzle Inlet Manifold and Spider

NR-l ~fl, Nozzle In~et ManUold NR-2 NR-3 NR-4 NR-5 NR.6 NP-l NP-2 NP-3 NP-4 NP-5 NP-6 NP-35 ~, ManUold Port 820

NP-36 2Q2O NP-37 3220

NP-46 82" NP-47 2020

NP-48 3220

NP-52 Nozzle Inlet ManUold NT-I NT-2 NT-3 NT-4 NT-5 NT-6 NT-72 Sp~der Leg 820 NT-73 " 2C2° NT-74 3220

NT-75 " 82° NT-76 II 2020

NT-77 " 322"

Figure 35, Nozzle Tubes

NP-7 ~s, No~t.le T~be No. ?3 NP-8 NP-9 lIP-IO NP-11

Measure­~ Description

Number

Figure 35, Nozzle Tubes, (Cont 'd)

lIP-12 ;,or, No~zle T~be ~o. 93 HP-13 HP-14 103 lIP-IS 113 NP-16 123 NP-17 133 lIP-IS 83 NP-19 13 NP-28 11 NP-29 103 NP-30 113 HP-31 123 NP-32 133 NP-33 83 NP-34 73 NT-7 ?,3 NT-8 NT-9 NT-IO NT-ll NT-12 1l'l'-13 NT-14 NT-IS 1l'l'-16 NT-17 23 1l'l'-18 " NT-19 NT·2C NT-21 NT-22 NT-23 1l'l'-24 NT-25 ~78 NT-26 NT-27 NT-28 NT-29 NT-3D NT-31 NT-32

Figure 36, Nozzle Cbamber

NP-2C NP-21 NP-22 NP-23 ~, Instr~ntation ~ke NP·24 NP-25 NP-26 NP-27 NP-49 Ps , :Bleed Port NR-7 Tn, Bleed Bart NT-60 ~fl, Instr~Dtatlon ~k.e NT-61 1n'-62 NT-63 NT-64 NT-65 Nozzle Cbamber NT-66 NT-67 NT-6B NT>78 Tv, Bleed Port

Figure 37, Reflector Inlet Plenum

RR-601 RR-602 RR-603 RR-604 RR-605 RR-606 RR-607

Measure ... ~ Description Number

Figure 37, Reflector Inlet Plenum, (Cont'd)

RR-608 RR-609 RR-610 RR-61l tr:lRR-612 I RP-115 N

(])RP-116 -...IRP-138 CJlRP-139 IRP-l40 HRP-141 H

RP-l42 RI-165 Wl?dov, Reflector In~et Ple~um RI-175 RI-285 RI-295 RI-345 RI-355

Figure 38, Renector Pressure

RP-46 RP-47 RP-48 RP-49 RP-5O RP-51 RP-52 RP-53 RP-54 RP-55 RP-56 RP-57 RP-58 Reflector Segment,O.l88" Hole

II II II IIRP-59 RP-60 RP-61 RP-62 RP-63 RP-64 RP-65 RP-66 RP-67 RP-6B RP-69 RP-70 Control ~,umJl Ann~luSo .. '!' II

RP-71 RP-72 RP-73 RP-74 RP-75 RP-76 RP-77 RP-78 RP-79 RP-80 RP-81 RP-I03 0.188" Hole

II nRP-I04 RP-I05 RP-I06 RP-I07 RP-loB RP-I09 RP-110 RP-lll RP-l12 RP-113 RP-114 RP-117 RP-118 RP-119 RP-l2O RP-124 PSI Reflector, 0.06" AnQulus

3 2&

TABLE I. - RESEARCH DiSTRUHENTATION LIST. B-1 FACILITY. Cant'd

H H

I to') r"­eD t\J

I I"iI

sn

TABLE I.- RmEARCB INSTRUMElfl'ATION LIST, B-l FACUITY,

Measure­ Measure­iiieiit'ftem Description ~ Description

Number Number

Firre 40, Pressure Shell, ContrOl Rod, Figure 41, Reflector Outlet Plenum an~Graphite Cylinder, (Cont'd)

RR-613 Tfl, Reflector Outlet Plenum RT-28l RR_614 Un" n

RT-282 RR-615 RT-283 RR-616 RT-284 RR-617 RT-285 RR-618 RT-286 RR-619 RT-287 RR-620 RT-288 RR_621 RT-289 RR-622 RT-290 RR-623 RT-29l RR-624

t':I I t\) (J) -...I (.II, H H

RT-292 ~:~ !:T' Refl~ctor se~nt, 0:.188" ~Ole RT-293 RT-294 RP-84 RT-295 RP-85 0.06" Amlulus RT-296 RP-86 " RT-297 RP-87 RT-298 RP-88 Se~nt, 0:.188" ~ole RT-299 RP-89 RT-300 RT-3Dl RT-302

RP-90 RP-94 RP-95

Con~rOl ~,um, O. -;88" Hole

RT-3D3 RP-96 RT-304 RP-97 0.06" Annulus RT-305 RP-98 " " RT-3Q6 RP-99 RT-307 RP-1OO IllIpedance Ring Passage RT-308 RT-309

.~ RP-IOI RP-I02

" II "

RT-3l0 ~:~i ~,s' Refl;ector OU~let Plenum RT-311 RT-312 RP-143 RT-313 RP-l44 RT-3l4 RP-145 RT-315 RP-l46 RT-3l6 RP-147 RT-355 Tm, Pressure Shell, :i:~~~ RT-356 " " "

RT-244 RT-358 RT-357

RT-245 RT-359 RT-246 RT-360 RT-247 RT-36l RT-248 RT-362 RT-249 RT-363 RT-250 RT-364 RT-25l,.

RT-365 RT-255 RT-366 RT-256

RT-367 RT-257 RT-258RT-368

RT-369 RT-259 RT-370 RT-260

RT-261RT-37l RT-262RT-372

RT-373 ~:i~; RT-374

RO-285BT-375 RT-376 RO-295

RO-345RT-m RO-355RT-378

RT-379

"

;'fll Reflector Se~nt, 0.;,88" B?,le

Sel!lll"nt, 0.188" Hole n n"

0.06 11 Annulus " "

Illlpedance Ring Passage nil"

lIin?;"w, Refl~ctor Ou~let Pl~UIII

Figure 42, Ikome and Core Support PlateRT-380 RT-38l

RP-121RT-382 RP-122RT-383 RP-123RT-384 RT-346RT-385 RT-347RT-386 RT-349RT-387 RT-350RT-388 RT-353

RT-389 RT-354RT-390 RT-391RA-o :,8' Pre~lsure Sh~,ll, Radial RT-392RA-ZTO RT-402RA-A Axial RT-403 RT-404

Ps , Core Inlet Plenum II If n "

;,fl' Core Support Plate Flov Passage Core Inlet Plenum

11 " n

-r." Core Support Plate Tfl, Core Support Plate Foov Passage Tm, Reactor Dome n n "

4

Cont'd

Measure­iiie'iit'Item Descript ion ~

~' Ikome and Core Supoort Plate Cont d

RT-405 RT-406 RT-407 RT-408 RT-409 RT-410 RT_411 RT-412 RT-413 RT_414 RT-415 RT-335 S~ort Plate RT-336 RT-337 RT-338 RT-339 RT-340 RT-341 RT-342 Tfl' Core Support Plate Flow

~Bage RT-343 RT-344 RT-345

Figure 43, Core

RP-l Ps ,

RP_2 RP-3 RP_l,. RP-5 RP-6 RP-7 RP-8 RP-9 RP-ID RP-ll PT, RP-12 "

RP-i3 RP_14 RP-15 RP-16 . RP-28 RP-29 RP-30 RP-31 RP-32 RP-33 RP~34

RP-35 RP-36 RP-37 RP-38 RP-39 RP-40 RP-41 RP-42 RP-43 RP-44 RP-45 RP-l36 ;,&'

Fuel Element Ho. 11, 0.153" Hole

"

110. 16

Fuel Element Hole Exit 11 n II

Element Inlet Plenum Exit PlenUIII Inlet Plenum

" "

Exit Plenum " "

~re S~de Pre~,sureRP-l37 RT-l RT-2

:,lIl' F~l Elem;nt lio. ,,1

RT-3 RT-4 R"'-5 RT-6 RT-7 RT-8 RT-9 RT-IO RT-ll No. 11 RT-12 " RT-13 RT-14 RT-15

SST

TABLE 1.- RESEARCH IllSTRtRolEN'1'ATION LIST, B-1 FACILITY, Cont'd

Measure- Measure­lDent IteID Description ~eID Descr ipt ion

~ Number

Figure 43. Core. (Cont'd) Figure 3. Exhaust System, (Cor.t'd)

RT-16 ';,m, Fuel ElelDent No. 14 RT-17 " " " RT-18 RT-19 RT-20

EP-20 !'r, Eje~tor ~lt EP-21 Ps ' EP-22 Ps ' Ejector Mid-point, Ref/S ET-l ;", Exhaust DJct ET-2 .. "

H H

I

RT-21 No. 16 RT-22 " RT-23

ET-3 ET-4 ;,t1 1 Eje~,tor DJct ET-5 "

tf) RT-24 ET-6 r­<0 (\J

I J":iI

RT-25 RT-26 No. 18 RT-27 " RT-28 RT-29

ET-7 ET-8 ET-9

RT-30 RT-31 !m, Mo~ule R"'.l.6" RT-32 RT-33 " RT-34 RT-35 " RT-36 R-7.2"

RT-~ " RT­RT-39 RT-40 " RT-41 Ra9.6" RT-42 " RT-43 " RT-44 RT-Io5 RT-106 Ra13.9" RT-47 " RT-48 RT-49 lIT-50 lIT-51 Ra16.1" RT-52 RT-53 RT-54 RT-55 lIT-56 ;,r1 1 Core ~1t ... Jn~Dt No. RT-57 " No.

3 7

RT-58 No. 11 lIT-59 No. 14 RT-60 No. 16 RT-61 No. 18

Figure 3, Exhaust SystelD

EP-l EP-2

~81 E.je;tor In~et

EP-3 EP-4 EP-5 EP-6 EP-7 EP-8 EP-9 EP-10 <:1'-11 EP-12 EP-13 EP-14 EP-15 EP-16 EP-17 EP-18 EP-19

alL

t.:r:l I t\)

~ til IHH

VE~T

'~ "PRE'OSURE v t::N "\ " A.'-\J 'Eo c::. (SERVO)

24-00 c.. \-11­SUf'~L'(

H H ~A.\.L O"lI I/') r ­eD (\l

I I'z:1

VALVE. S~U\-OFF

OU"I\..1:.\

B'( P~~5 ,0 MAI~ 'DlscHARuE.

"PIPE. STATIONS

LIQUID \-\, FLO""" tJ\E"TER. "DUMP VALVE.

-5NozZLE

4 - INCH INLETBLEED POIti.,. Facility turbine ............ -PIPE. valve TUR~\~~ ~~S BLEEC c LINE ~IOZZLE..

f' " Co \ \..\ "\ "( '\J ,." Co \} \,)t'\ E'XH~\,)~T

"8 f"ttT A.60"lE ~R.ouWO LE"VEL

1--- A

PUMP

,000 RUW .,.A.~,n<...

k PUMf'

W \JEN"TUR.\ puMP

,./ IA.N~ R.E"UVf..~ \..\~~ / PUMP

VALVE-

"'UR.8\"lE F\.O""M£T~R.

lANK rAC\L\T'( ,// .,......WK.Y V",-VE (SE.RVO)

10\ FE.'f..'"

Turbine power control valve .-::J.-'-'-'

85 FEEl ----'-- II-~--\ \

\ ' , '\

TURBINE \ '\, \

EXHAU'bT ./\ '\

"DUeT --' ',', , \

\ I I I

'REACTOR. I I I

I

;====8:E¢:::3 -

"TUR6\~£

"'-~

'

lifo FEt:: 'T------:-=--JJ

FIGURE ~ - Nuclear Rocket Cold Flow'Experiment in B-1 Facility.

ID~NTIFI-

CAlioN

E.P - I EP-2.

EP-3

E.P - ..

Eo" - 5 E.P-G,

EP-7

E.p-e E.P-9

E.'-At ET-5

ET - 6 E.T-7 a:.T-8 E:..T -9

2E~O

z -=

Z~70'

&Afil;lE'

0

2.40

120 30

30

30

2/0

210

a 1·0 30

30

30

2. 1·0

2. '·0

,10

RJi'~IUS \'A '14"

" 4 '14" II 4'J~"

10.,,' 7.25"

5.25" 10.,"Z·

7.25" t<.I . I5.Z5" N

m10.'''Z.'' .....:I

7.25" ~ I5.25" H H10,<.2."

7.2S" 5,2.5"

r:LOW EJECTOR

"

~'"

I ,,/C+i"'~'"\',':il

I j;

I /

"'~=t~ SEC..], B

--:... _-":-..::~~~~

E-P 10,11

E.P 1'2., \3

EP \+,15

':::'~".

E.,-a E.T- ,

E."T-3

<00 '----I~~;;;;;;;;;~ ~I'r_r_-rr_-+-__f-__n-_,

FI~URE.. 3 - ALl'ITuDE. EXHAUST DUCT SYSTE.M AND INSTRUME.NTATION

E-2673-I1

~·r

,Prom bo1ler house

GN2 load.

/valve

l J

To retentIon basIn

transduoer

Second.aryejector·

® f1lterejector 4;9. liquid. level

~ facility temperaturetransd.ucer

@ prenure sWitch

~ pressure regulator

'£. hand. valvs

~ remote control valve

oH:' relief valve

N check valve

faoility pressure~

o accumulator

$- burst disk

~

~

Figure ~. - Bottled. nitrogen and. steam systems.

tr:.l I to

~ 01 IHH

E-267:3-I1

~~e"-""-~""" Liquid N2 dewar

To remote .20 psig

tank control valves fillLN2~••.•• .,From IJl2

Une To PR

lTo vent..--l ~ T I

To remote control valves

To PR To To PH PR

To PR~~J--{'}

From GN2 bottles

- f I Down c>ql-----'----~ N2 gas trailer

stream~~ To PR( II.. r ~ ~t:'<l----r-N-®~I I ~'-"--2400 psigf ~ ~ I I-~

~ 1lie supply

To PR To PR ToPR~® fllter

© loader

@ pressure switch To PR

@ pressure regulator

oK hand valve

remote control valve

~ "i-M oft' reUe! valve

ReUefvalvee"N cheok valve To remoteo~••" ."••• "l "?,...,.!IJ facility pressure

transducer

flexible hose

.. G He Une..

IJl2 dewar valve actuation

'" .,.,,~. "ffi 11 t :t

Figure 6. - Nitrogen system.

2 d.ump line

Figure 7•• -

/

[ ~ervi~j

ntr To re ctor 1window To L112

tank insulation

To ejectorbox purge

•

To LH2 line

~To ejector

.••••-{>Ic:l , rLiquid

H2 To vent tank

...... ~ To LH2 ~'--t ...••_ trailer

line

TO eN, LI"'.'

r r Helium gaatrailer

NOO psig L··.....~-

I filter

! ,. preeeure awitch

pressure regulator Ii: hand valve

D-i: remote oontrol valve servo control valve

~ relief valve 11:7 check valve

To QH2 M flow metertrailer ~ faoility pressure tranSducermanifold ••••••.J flexible hose

Helium System.

II-£L.92-3:

.-.

,Ejeotor vent

~ H2

trailer

Liquid

ClHafvent purge /

l' ..... I I

I ~ I

~ Cl He . II purge i

Pigure e. - lIycrogen syatem.

E-2673-II

, .~ H2 gaB trailer I 24.00 paig

_.~ I

o i......_~.-J

H2 gaa trailer

24.00 paig.Q.

® filter

@ p..essure sWitoh

@ presaure regulator

~ hand valve

~ romote oontrol valve

~ reUef valve

~ ssrvo oontrol valve

N oheok valve

r><l fl owmeter

.....:/ flex1ble hoee

[!J faoility p...eaure t ..anaduoe..

burst d1sk

To servo valve

) I x '"l, I~, ® t~ 'T' !-_ To servo valveHydraulic NO.1 1

To servo valve

_--'--_-.!.-_ .Ydraul1cl~ I I • ® I

i 0 I I - To servo valve No.2 ~ J

® filter

c:=::> @ pressure sWitch

pressure regulator® !oK hand valve

& relief valve

To servo To servo -N check valvevalve valve

<=) ~cumulator

[!J facility pressuretransducer

~

Figure 9. - Hydraulic and lube systems.

. rl FTO turbopump

pump

II-£L9Z-:3:

H H

I tI)

&; N

I ~

t>:l I

t\:)

~ ()l I

H H

HH

I t() t­eo N

I r:.:l

Gw.nmiIlXn

Figure l3. Mark IX l1quid hydrogen turbopump installation.

I ••VII ••1' I

G8UflB£1 IfIM:

Sp1"ing retainer

Support Plat Mylar .eo.l -t----~-----~_ild__tl-

H H

I 1'0 r­to t\J

I fxl

Renector Cylinder

1mpo~anoe r1ng

Reneotor segment

Control :l1"Um

Module-

Fuel el...en~

Asbestos l!Ieal,~==j=======::==~ Support Tube-

T1e rod --~..--

Pressure veaeel

.3l.t-----....

Mylar .oal

Puel el"""",t aupport

Retlecto:' bracket

Stand-oft nozzle:Bear1rlgnozzlep~~a:te:-:~[~~~======~~~;~~§~~~~~~~J'ozzl,.,

Figure H. - Roactor a1cetch.

l:rJ I [\)

~ (jI I H H

·"'7777.

H H

I I<) t ­eo N

I 111

II au /

'7

l?j J N O'l -...l (Jl I H H

••

......

H H

I ti) r ­to C\l, JI:l

.2'057 Ed

txJ I ro 0> -.l CJl I H H

.. T--t--+--L

Figure 19. - Lowering of reflector assembly over dome and core e62 it IBl'!!h i lAb­

H H

I l") r­eo C'J

I r:iI

t<:I I [\)

'0) -..l C1l I H H

H H

I t() I"'­eo (\1

I ~

-....­\ \

~'", " (''''

...... f'"", J''?

~

\

... II

" .../' ~ #' \ ." "",,,,

? ... £;;:t' " ..., /

.;,y . \. I' ... ... ... , .I ... \

$

& ~

~.,.., .I ...,,"

~

\ ...\

\ " ...."

;l \"'"' ...\. '" 4' #'''' <~ ~

:> '" ... \1... '\ ,l a .... /

~ ,y' ~.. . \" ...z 1, "c ... 'I. .J' "

/ .... ;.4~ ...! , '" \

\

...'';.<t \ J' ...... ~;,},

~

\ ." ...

II

Ii_ t-/ .\

l .,f'4' ,"\,..;I\:;'\!

, " *".,' '; ") ..., \

, ,.....

.•;t"'" " • ,. ,l" ... \ ....

... \ ~..... (p'

"'" .. '" ... ..,.... " "'" 'I {r #' (#'

~ ... ~ -"'4 '1, .; ,- #' ...~. \

.... '" , , ~ ".-. .I \

.~ "....I' .... 4'

\~I- -..

lII!l M 'l!ll'.,

'I\ liItl"llt.... \ ".J ..,. tr:l . ~.r;; " I

~ N ~ en

\~ J' -J\ \

... ~" • H

I- -p

:: CA

H\ OJ J' l...

, ..\-,.\ .... , , " ,

,~; .... ~ .\ ;:'

.; . .....\ #' ....... \0 \

iI J' \.\'1 .... "'" ;l'" ~,,f'

",... \,,' #'

,',\ ... ., "'", ?j, .., 1 .... \

l'

\ F .... .,.'" \ \

~"" 1> \

\ "., <Jf/I .~

1IIIIl

E-2673-II

Figure 24. Hydrogen feed line, nozzl.e, and reactor.

•

R.aoto~k;zd ~ end &IIIr1ng

l"1.gure 25. - RN-2 Nozzle.

58.02 1n.

.·.····r.. ·T)lf

._._._-J

E,,1t

30.?O in.

~1'

Inlet c.onn<.!ot1on • \ J

II-£L9Z-:i[

E-2673-I1

HYDROGEN

FROrv1 REACTO~ CCRE r--:-:-- '.00 , .....

T&~.""' ••" I _•.~_.. "" I -_ ..,

~/._.-

l:~ .... ""'''. 11( I-L'­~_c......C""'U"'-'-........ U> 7'10...' ~

~-~ ~ _... ....

gt:1~1/'~~ ""f~ ~ ..1":'"'... -.&HYDROGE~N ~" ~E~~'L

,0 'R'EACiO L. llI'~~ ...,:...OI(O"."l('~ ~~~ t,~ mow ... a "",""""_",,,y .. \J6",T WI~DOW "1t,,I.~!\,Y - CAMP.... -.0.,. ~ \"'Q

( ItIIfl,,)'t.<..... TO "'•...,. ..»~'IJ C.ll<'''PT Moo ."".~).R..Q

axo ......._ -,/~. =~~ .......

....r. '(l&t..r.. (.

2.-111;. .. ,.,0 "'JlIe .\.S .....

~0'>

.....<."0'"' B-B

FIGURE 26,-CAMERA AND LIGHT PORT ON RN -2 NOZZLE,

"\l'

HYDROGEtJ TO TURBINE

---~- z;. 00 x .O(..S \l,)"'""­I( ~.o ...Go TuaL

-.oc.l. Tll'<: ""'CU'

-l.1l APPtlO~ R

t­ - :,~. ~~g,,~ ~ ---+­, (!>t!ilOJ(o»~cmW,)

: .0<. ,_~ \ ,:~ • ----' R.. TVP ,<45

B i \~~~~~l~>.l'

</' /AJ~

/~ I"HYtlROGEN"- ,tcu", 0

ROM PI,' <c..o'-";~E.~AU. 4.1"1 vMP

HYDROGEN

. ~'-"~

FROM Rt.ACTO~

FROf't1 PUMP

\... T~(~ Wt,o IF Ol~\'Q.lb

t>e.T"'L 1)

,-. O~ A"PIlOK 'R • "F-L.A.c,...,.

/ 4,17

...

".117 D14 2(.1'

,0 'Up /.~ r-.IHYDROGt:N REACTOR ~e7 I)lA ~"­~,hOtWOF'~F'#c.IJt"T'O ' ,~ TullE~

.1.S_O~ Ii ~ \. ,/'./ ~'~\:.{~.T'P .' /:;1;;'5-,tS

B~"~r. ' 'K.. ,...s~" "­~ ." >'.l5 "'­~ /' ..

", ...~c:.nolJ C·c. ""'lL k.T"~~ t, HOlt~J £:..Qv......l,...,.. ~AAc."t> "Q.oU~O

~~~~~l\:~~~~;~t~ TOT~L 7l. ,,:xL\

J:l,-B

FIGURE 27.- 'BLEED PORT ON RN-2 t'JOZZLE

II-£1.9~-m:

H H, tI') r­eD C\J

I !Xl

I-- :8-1 oontrol bulld1ng­'!'ran.­

mi••1on Term1nal rooID oabl ••

'Balanc, AlIplU1Ol'I

I-Y panel. f----. plott....

J Carbon and

Prequenoy plat1n\llll Analog DC relietana.

R.oord.r ~oonv.rter t1'l.ermOClletll' ba1an•• anlll

I

I I

I :8 • 1 hit .tand

H bVlld1ng

1'1'0_

b.,...d

,-..

! Remot,

Soann.r Iyet.

T•• t ,tend

Trani" Inltrumentation RileI' m1lllon

~r111lental apparatus terminal .ab1nets .ablaB oablee

Pr•••u.re: Tsl'lll1nal f-

Ooc1110.. tranaducerl Itr1ps ~ graph

r-eool'der 4 KC

d1j!1ta1

Iy.temThINooouple r----- Monitor

oven'

If panel

'I'hltmow Looupl. Themooouple I- ­ :8 - 1oven. oontrol

Jack ro_ patoh

panels board

ThertlltOQOup16 ~OV6nl

Thel"lll.ooouple avena

LJ 'B - 1 oontl'ol

. Thlt1locO\I,ple bll11d1ng 0.1118

patoh b....d

Carbon

NI11tanoi

ttwmom.ete:t:"8

!PlatInum TIJ'1Il1nal res1etano..,

str1p,thermometers

'otanU· at.lnti ... ","tar ~_tar

.oann~ ''''It.... ~~t... '!'urbina ba1&l101ng ...~:~;:::Iylt... reoorder. n ......t ....

LlI2 run LlI2 run tank

tank l,vel

probe level 'Tlt.

H- bullding

10 KC

digital

IYBtem

__ t

patoh board

0101110­

graph

reoorder,

,~ 29•• Bl",* en....... of f..111ty 1n.tl'Ullantat1<m.

II-£L9Z-:;r

FLAII6E /)£17111-5

HH ~~TR-'

I t() l"­(l) N

I I"il Y-:><

7l"~ Tf'-Ii1'-"

/

rr- ;z.

17-3

TT-r

7,-.

rr-7

TT-8

rr-/p

"" l't'f-A 77-~ I V --IA~K ~D"PTf:'"

rR-S"

T'T-II

, ...--- J:llnR. ,AN D STRA Ie HTUIIIICr YA~ES

_ TifNf( £.rff F~IoI~E'T6R rF-1

~---VAL~E

.......---.s~ PIE'LE.

I----~AL'I£. -T.5.av.

P6RT

__--l----- CAI'AC/'''.Jt:£ rYPE e-NtTtNtI'US ~£IIU $£1/I'Sb1{,

TL-/

PT-?

()

P1"-7-_=-r

PT-13---~

PA-2, PA-3

PA-I PII,., P ____

Pf.2fl

PT-4~ PF-+f

~ -If rPP-/~

I.,-PR-B

PP-17 __ \ + )fT-/O

EXH~~ PP-/8 I

LJQIJID HrIJR(J<iEN BY-PASS i./NC---f

t.:r;I I N (J) -...l ~ I H H

~IGUR[3/.-TURBO-PV"'PIKsnfIlI>1EAlTAT/OH

LIQUID ~YORoCrt:jJ

13y- PA5S LI U£

TOP YIEW OF PROP£LLAIIT OI./(.T/~r;.

filLET H srltruJl( .... 41 .. VALl/&'H

I l') Acrv"roRr­to HYDRAULl~ N

I OIL- PP-3/ f:il

--PT-t8

~ PT-~f( t PT-7~

Pr-7J PT-38

=:I-~ Pr-12

P'F39

PT-7.p

PQ-, QU~I.ITY Mtn~

F"lGtlR E 3 2.­

txj I N 0) --oJ Vl I H H

~ &A~GcL .zN4T~"M(flT!47t,J{

Ji,,,,d. -A-~

#7-"-8 7.S' 18S'} ~ Nr- s'l 7..r ;US'"JR ~

!

...llflDEtlTltl

FJt!iURE 33. - NOZZLe

~¢-+t-'==-:-=-:-:-:--:-=-:-:-:--:-:-:--::-:":::-+-ti:--:-'::::::'-:-:-'=-:':-':'-:-:-:'~:"=:':':--:"":-:':±~~=-=~:H

.... NfI.1.,U.e 6t1't1J J"~",,,vAl'I(TA7t.N

..Irl.-1 1tI_ .-A... .....fZ..-

INSTRUMENTATION

._--)(=/].~

£ioOIAST ~.tJ. :Z~.sTIt.II""N"ATUJH

7",,,, Nt. --"L- .Jfl_

.:z..s;,~ ~ct·

.l.s'#'~ .:lC· lilt ••• 4T."S ,4,,' "" SS."O JlJ.' ~'.tlo ""8' 4$.= :l.IO·..s'.r..,. ol.I.'/.'~:l • .:t4­ H<o'

:,:,a • .a.I- c'

-@em 'lEN liAr

11·S-· / ...

...J ::;::======5.L_...."J

..seCTION )\-Jl

H H

I t<)

fa N

I I"il

...:zTcM No ...sL. ";P-z I/S"

Nr-2.. /IS"

NR-2 lIS"

I'll'- 3 18$'

NT-3 18s' 1<IR.-3 18S'

111"" US'

N7-~ 2.;#,s"'

IlI/l-4 ~6'" +

..IIIM No ~

1Ir-- I 4.$'

IVT- 1 A.,S'

NIC-I -4,$""

!liP-€> .ls.s-· NT-6 ~s'

tVP- tJ :ISS'

NP-5 2U"

NT-5 21S'

NIi'-5 ~AS'

L. ~ 1/." II'~~~S

L;;a.;t 8.(J ,_i~.

L 1/;; 5'•.r ."cJr~.1

L'I ~ '.G"IIuIw4

L. :: I/.() "".~~S

u:; 8." ",.It~$

l'llf,tJ,fE 34l-tl.,uu I«,~r t'7tt«/J:j!!r..l> I1H~

SP/PB IUl'7'tf(H#/ffI'tr.-etV

I8tliRitl1l tL

~ Nonu -r.,4~ L.sT'Il.VME"IiI/TA T/~J(

X= 0 LT<MNo CQMeaNeNT~.J:L ~

~.SO 1M- ';e~ 693 ~II/P­ 7

/{F­ 8 x~ .3.S

9)(" .... 0 NP-

NP­ ro NP- II

tVI'­ lL

tVP­ /3

NT­ 7

NT­ 8 X=/.l.~

NT­ '1 IIT­ 10

NT- II

NT- o. 11/7- I~

X= 11./ NT- 14-

NT- IS

NT- /' NT- 17

NT­ 18

Nr­ 1'1 X=.lS:7

NT­ ~

#7­ ~

IIT- .U

NT- J.3

NT- ~+

117­ ~s

HT­ .u XE~'.O m- 027

1011- J.!

NT- J..9 NT- ,JD

HT- ~I

I/T- .32.

NI'­ 14-XC 4S.z.S

111"- If

/111'- I(.

NP-Il

111'- "

"',.- 1'1 1<11'- .2'/

X-Ss:o NI"- Jo

111'- :JI

X= sa.a).. /'11'- ')J.

lil'- .JJ

Nf'- H·

1:l.Sa

;"S.70

4.r.ilS ,s..r.D(J

1;l.SO

4'>'2S"

3.so

/.J..~o

I". I ()

~s. 70

3'.OD

·U:.u ';3&•• DO

4,s.).6"

II•• 5'

41.00

...:. ~

<l

0

..:­0

..:.. tr:1

.; I l.\:l m".: .....:J ~.i. I H.i H

.L.

0

.. 0

a

4~o.!.SO TiJ8t - oiL:! ..i. /.2. S(J .. If. 10

II ...:

.:J.S: 70 ..:.. i,J'.oo

4S;~S .l.

.J6. DO " 4S;.;.S" 0

:J.sa JSS· ';61."'/76

IJ.SO

11. /0

-'S. 7D

~.oo

4.s: l.)

,J'.OD

4S.J.S"

.;.

... .... .l.

.....

0

0

"S".3S .J..aS· T"II~·,o3 0

4$.~ .J.U· "'SIf.lt 11.3 0

4r.).. ...... 5· "'BE ·/.23 0

4.r. )S' .J.I..r0 -';;-8 E B/.33 0

4&:2G' /&s' 7dIlL II: 113 <>

4S.15 14S' -r.i8E 'ns. <l

-U:;1S .J.oS· "TUBE "/03 ., -IS.~ ;;l.~S<> "'BE '6 1/3 0

45. :>.S 24~' ...,....41 '6/..u 0

4S'.;;l.S ~" S· 7fiu BIJ.J 0

4-r.~ If.S' -';;~E ~ 4.J a

4S.::I.S I'IS' ~IU :1/.7.J 0

NI'- 21 ,;l.S. '3 .2.2- .30 1 "'BE "II .A..

J.-c INS/DEj o-OUTSIK hIQLlI.l!l 345: - No 'l."L1.£. Cpe.ruwr Tulllj

SEE F/G.33 FOR e ANI) TUBE NUMBER

INsr*"""EHZ7t r"DN

~

...

~.6 &10~\-1_\ \ \

c.SFCTION~

H H, I() l"­to C\J

I P<1

\~.I+2.·\ J

111'- 2./ ;_

.GQUFtBEI1 rtr

..---------~.o--------~

,sECTION LB-.L3

\

ftTA IL l2:Jl hGt/RE. ,3,;;- NOZK-L£. CHAMt:UR INSTRUMENTATION

x = 1.<. • .1.4­-IltifilI8t11M:

1=53 t3:j

-r: r",~-Z=57

I ro ~ CA I H H

Section ~~

Proeaure ahe1l

Itelll lio. 9It- 10. ..L. -!..... ..!...

RP-1l5 53 65RR-6OSI 511

RR-608 53 65RR-610 63

1lJ'-lU 53 RR-607 53 45

RP-138 53 156 53 30

HI-165 5S 165

RR-6ot 57 185 57 365

53 356

53 346 RR-611 53 U5

5.3 335

53 295

Rll-612 611 Z3& 53 285

llf-175 511 175 67 5

RR-603 57 175

RP-1l6 53 2~

57

51

285

275

&OtiFlEiitlllAL RP-l42 53 270

Figure 37. - Jlal'lector inlet plemm iDatrummltatlon.

..

f

It.. No. t I

RP-1l9 150 1.25 RP-120 150 7.25

RP-64 168°20 ' 1.25 RP·65 .. 7.25 RP-66 .. 13.25 RP-67 .. 24.25 RP·68 .. 36.25 RP·69 .. 51.25

RP-130 170 1.00 RP-132 .. 13.25 RP-133 .. 24.25 RP·134 .. 36.25 RP-IH .. 51.25

RP·52 171°40 • 1.25 IlP-53 .. 7.25 RP-54 .. 13.25 IlP-SS .. 24.25 IlP-56 .. 36.25 RP-57 .. 49.38

RP·16 177 1.25 RP·77 " 7.25 RP-78 " 13.25 r.p-79 .. 24.25 IlP-SO .. I 36.25 lIP-BI .. 51. 25

RP·I09 177 1. 25 IlP·110 " 7.25 RP-l11 .. 12.25 RP·112

., 24.25

JlOIIFlBEltTlAL

t

I "' teullGe pl_ li"11 111 tleure 43. ..llP-113 36.25

RP·1l4 " I 51. 25

ao·,r'OC"TI &,

n~re u .. Ilefhotor pre..un in.trUJuntatloD.

-M""

E-2673-II

Ite. 110.

lU'-103 llP·I04 lU'-105 1U'-106 RP·I07 RP-I08

RP-70 RP·71 RP-72 RP-73 liP. 74 1U'-7S

RP·46 RP-47 llP-48 RP-49 RP-50 1lP-51

1U'-124 llP-126 1lP-127 RP-128 RP-129

RP-58 RP-59 IlP-60 RP-61 gp·62 gp·63

gp-1l7 RP.1l8

i .'

Ii • :f , 'I

I

-....J... / / J ..... '/.., ,_ 111

i---'

• 357.. .. " " "

357 " .. " "

\ " I

! 351°40'.. ! .. .. ~ I "

"

350 " .. " "

348020 I

" " .. " ..

330 330

I

1.25 7.25

12.25 24.25 36.25 51.25

1.25 7.25

13.25 24.25 36.25

1. 25'It#l7.25 , 13.25 29.25 36.25 49.38

1.00 13.25 24.25 36.25 51.25

1.25 7.25

13.25 24.25 36.25 51.25

1.25 7.25

.A.A......... rUTt i I

23.a 7 R.

&O'lS",r',!lltl

Figu... 39. Renector ~mperat....a inatrUlOentat.ion. Hote. Z r.r....ne.. plane ginn in fi&"l'et3.

11-£1.93-:3:

--

--

--

--

----

--

E-2673-II

It... 10.

lIt-a68 ll'r-all~

lIt-lilIO

1!'.f.ITIl R1'-STT R1'-3T8

M-28T M-288 1l1'-280

Rt-281 Rt-282 ll'r-285

Rt-2S' R1'-ISII !If-2SB

1It-71 RT-11 RT-711

Jl1'-88 Rt'-8t !If-TO

Ito.. 110.

Rr-liSl Rt'-lI81 Rl'-383

Rl'-lIT9 Rt-liSO lIT-liU

ll'r-296 lit-ItT RT-It8

lIT_IOO RT-Itl RT-292

RT-ZOli Rl'-ZU Rt-2911

Rl'-T7 llf-T8 Rl'-T9

Rt-1' RT-TII lIT-TS

I

a (In.)

1.211 28.26 61.211

1.60 28.60 61.80

1lf-2n Ilf_ITS Jl1'-%TT

Itell 110. Z (11:1.)

Ilf-ZTa lit-IT. Ilf-&T'

I_liD.

2.2S 2s,2S ~.Z6

ll.~

Is.llo ~.oo

Z (In.) 0 6 ~~f. r:f) lYo-ric")

,\;1!5 to 2..

IWIll liD.

1It-266 RT-267 1tt-168

IIT-16ll RT-2640 lIT-ISS

I

1.25 28.26 60.26

2.60 28.60 60.00

2.26 IS.26 110.25

1.26 2S.26 ~.llS

1.~ U.60 '0.81

1.26 2S.26 Ill.21l

1.~

2S.60 &1.&0

Itt.1l0.

lIT-8S Rr-Bf JiT-BS

Rr-St PT-90

Z (111••)

1.60 26.n ,e.62

1.211 2S.16

Jl'1-269 IIT-2TO RT-I71

1lA-0 1lA-4

lIT-aTO Rt-S71 RT-ST2

R'r-S8lI itt-SIlt R1'-SOO

Il'l'-S6 lIT-1I8 lIT-OT

!If-02 JI'l'-Oli IIT-9'

PT-Ol 'O.SS

llf-Sll 2.15 IIT-lI12 16.26 lIT-sa 60.16

lIT-SOB 2.1l0 RT-ll09 28.60 JI'l'-lII0 1l0.00

rrJ'-31' 2.21l 1l'1'-alll 28.26 lIT-U6 6O.21l

RT-ll66 1.50 RT-S86 28.60 IIT-a6T 61.60

ll'r-a6T 1.25 R'r-S68 28.60 'IT-SSS 61.25

18

1.60 2S.60 '0.82

1.111 28.26 '0.38

2.IS 26.26 .'''O~"n'l60.26

!

FiFI W. Prl..url theIl, control rod, and graphltt cylindlr _perature lAd aoolllratioD lutruuDtation. (I rlrlrlDot pllOo1 ,1nD In flplre+3.)

I (In.)

I.U 26.26 50.25

2.1l0 28.60 50.00

2.26 2S.25 50.25

III 11.6

1.25 28.16 1l1.16

1.60 28.50 1l1.50

1.26 28.26 'O.SS

1.60 28.60 '0.81

-3.OC

-0.26

-0.7£

-&.0

-0.2

-0.7 -~

\ "'1~4

I

\, HI1F1O[I111:'1 .t

-3.0

-5.0

-S.O RP-9~ 295lIt-t

enSeaio/) A-A ..,.Je z (Jlltea Bo. (deg.) (loA.) I H• 106 -3.0RR-621 & Z H

Ito. Bo. (..g.) (m...L RP-125 65 -3.0

llR-620 55 -5.0

RR-S19 "5 -5.0

RP-l45 50 -5.0

RP-100J

RR-622 115

U9 -0.25!!T-260RP-1.e 150

1lP-1olS 151i -0.26::::J S51

RR.06lol 5 -3.0RP-e:J 188 -0.25!!T-2

1\0-165 165 -o.n RP-91 } \ 368 -0.26Rf-251IlP-8S J 114. -0.25

IIt-U8 5U -0.25~JlUl-616 176 -&.0 10-356 355 -0.16 10-176 116 .0.75

RR-8U 356 -&.0 ~ 1IP-89 1115 -0.25' IIt-Ull

35<l. -0.25~JRP-98 J 118 1l'l-268 JI().-M5 US -0.15

US -0.25RR-818 165 -3.0 ~~ 1lJl-14.t 536 -S.ORP-96 } 111 IlJl-l:11l'l-2&6 289 -0.26Rf-2

RP-I0~ 16& -0.26 1lJl-99JIl'l-ZS U8 -0.251l'l-25 llIl-6U 226 -S.O

RP-9:J ta7 -0.251It-21IR-6U 256 -3.0

RP-151 246

RP-U1 210 -0.25

RR-611 215

288~4.t} Rc-286 286

lUl-1il8 2llb

!lP-41J 2MIl'l-Zt1

RO-296 296

COtlRiit lTIJet

Top of ",o<lvl,s,c"O

.e= -4 ~= -3

2-·0.75 -!; = -0.2.5"

tzj . I

N

Figure 4-1. - Re.f/~Gtor outlet plenum instrumentation.

I -----------------------------------.-

I. ... i

H H

I 1't) r­eD (\:l

I I'il

'-. "

/~20.000

Ie-I':'" Rt>. 2

~-/.zl -I().O

RI'-12'2­ -?5

;f,P-/23 -7.75

/

l ,

!

\ •

e­

0-1

I'Ir--I"9 35'1 ~!i

174" SS

/(r-4/CI

Ar-rlll

/l'r--I12­/lr-~/!}

/IT-4/1­

"'T-4/5

·eettf'8EtITIA~

rtC/ff t/t). e R

~r-,," $Sf" /7

~r-.H' .34~ 11 ~T-M(J J7"Z·

" .....--------.:::i=--t---X , (9It-el'1 '1(/. e Z-C'AI 'Ill"'-...- ­

/?f)0 Rr-f60f­ ~

Ar-4tUJ ",r- ""z.

3S.· Ifr~,," 110

2.0.000---+ R'T-4'" /70-Ifr-407 230fee", I/O e R /(r-~8 290 '" 350

Z

U; IM/ /;.13

33.1J'

~9.5' 2., IMI IU3 33.S'> 4f,~

3.11

1~92

/1.]'3 gl.u. ~O

1.5 5/.5

2.' /tMII

1.t.23 3S.B'

-f;?5 Z, /~.41

I/.Z3 33.8f,

4105'

$.11

/t?fL

,If. 73 .3~~

S4~

~./I

/".f'2 /1.73 3~.Jt,

~dJX>

l.aO

8.f/

IU3 32.U.

47.11

e-IS"'

/5 0

/5°

/~"

/~.

/.5'''

Ice", Jf().

tfT- 2~

tfT- 27 Ifr- 26

/l'T-2 'f Ifr-3t7 IIT-21

/fT-22 tPT-2~

/f"T- 24

A'r-Z'" Rr-.,,~

/f7'-"I7

IIT-4'

1IT-.f1 "rT- ftJ ;fl'-~(,

",,-,07"'7--/.-"7-/7 .1'r-/B /l'r-/?

"'7-20

-rr- II /1'7-12.­

If7-13

A'T-!'1

"r-/~

"1'-36 ,f;r- 37

IfT-3B

""7-91

R

17.0 11. ()

I;':

1'1.,'·

/~I..J

;4.4

/-14­

d.'! /1-1 N ../ /3. '1 ~.r

/3. '1 13.'1

/~ '1 /8.2­

/&.Z.

12.5 /2.5

/2.5 /2.5 /2.5 ?~

9.~

;:~

r.~

j1.~

?Z

U. 7.2 7.Z.

AT-~ 7.t. 0.2- /:5',1T- 31 O.t2- I;~:!!

/r,v -/I 1.7 /?:f"

;fY-33 O.bZ

/!T-3Z {).•z /'/',17-/2 t.3 /3::;<'

h-~ O... z. /;',P-/:::- a. '7 /3~'~

/f/-/4 /.$.0 /8~~

/f/'-/S /4.tJ 13f5"

IT-I (J,n

"'1'-33 C.(,Z­

/'f'/-/~ /U /36·-Z~ 4­/?T-~G /.7 1,r11'1'- 2- 0.17 .f'T-:3? 6.3 lr

1f"T-~ (J.l1 "'1'-3 0.17

/f1'-5F i.a 75'

Ifr-s o.n = /1.2.

If1'-5,,/ 11.9 75' /1'T-<:.a 7.5'I~r

.I~e/1l Ild. I( ~/-~I !7.0 75 '

/f/'-.(o I. '7 75 " /i /'--1/ (,,3 75' ,-r,t'--Ie.. U 76" /".. . .;'::' 12.9 7:5.0

/./-'-11 /$9 7.j''''

/, " ',1" 170 75"

.Fv41 ,z/e/7)o) r

/'fod,,/I{.

0-fJ'cal .l'vel elehJ e/J t: /) ...",t.~rs

R,P-ZC1 17.3

If,"-]§' h.2 ;f'P-36 a2 /1',v-37 I1.Z ",f,P-J/8 13.1 /f'/'-td /4/J

(F)

(M)

40llfl8E1fTlAt 0 .Fi.!1'H·t!! iU,- Core .Io,st-rvtoteo rat- ion

It..: P! /',J. R

tf'T-QI

1fT-52

;fiT-53

A'T-51­

117-55'

/fl'-' /1'1' - 7

If~-&

11'-'1 If' -/D

"~-I

,,;>- z

""-3 RI'-4 ,1,0-5'

,f1'- 41

"r--Iz ;rr-~3

trT-H

"I -ff er- , tfr - 7 /Ir-g

II'T-"/ 1fT-A?

IUP/1°'

~/J- ;'8 /f,P-.!l')

,f,P- 3Z.

t'f,P- .l!J

Ii'P-34

~I A"-I

A', I

4:.1 16.1 /{.3

1.r/.3

/</; 1'1.3 /¢.~

?-6' ?~

1- ~-• J

9.5 ?:f' ? (Z

7'.,z. y.~z.

}?b2

?1.2.

:f.'1

~1

£.'1 5:'/ 5'1

,f

/7.3 t.t. 8.2 /3,./

101.0

2

.:J.1f

ItJ.f'Z

/9.73

3431, oo.<:l:I

2." /i?4/ /3.Zl,

3.J.'J',

49.5

2.t:.

/~41

/1.13 3.;. &t 41.5 3.ft

/II.f'z.

/(.71

g",~

5d./0

2.(0

/0.4/

11.2.3

33." 4?S

9

/5°

/5°

/5c

1:5 " .

IS°

t.:xj I N 0> -J UI I H H

E-2673-rr'

llled through Thermocouple welded on P" t&P dr d on oute1de.ror Tw &ncl plugge PO

Epoxy rea in. ../. Filler plug ,,_ material I." bABe. .-"'\ r Ban m&teria1.

Coppe~ .p1ug.

Pr probe. (brazed in plug). Copper oon"tantllA thermocouple

Fine wire thermooouple(a) Thllnnooouple installation for (0.001 in. wire).Till mea"uremant. in I!II!Ital part".

(b) Noule tube lnetrwnentatlon techniqueB.

~ 1iBin. dla. tube

(0.012 in. wall).

Graphite baee material.

0.040 in. 4ia. tube (0.006 in. wall) brand to ri-:!:n. dia. tl.\be.

Copper-constantan in. drill for Ps tap. th:erlllOooupl••

(c) Thermocouple lnsta.llatlo11 in graph!te parte. ~ (d) Static preul.\re tap inatallation in reaotor oompol1llnts.

Figure 4•• - Details of typical pr.e.ure and thennoooupl. installations.

H H

I to r­eD (\J

I p::j

I:>l I N (J) -l CJI I HH

H H

I I() r­eo t\J

I r:<l

-Figure .i9.. 0l.o.'1401 system showing "1401 conr,puter; ...-,-,-,~~_.1405 p.~i~er. ,

~ II-~L.9Z-:ir

------ -

- - -_______

E-2675-III ., ·

r------I I

I '(voltege)

I I I

'- - ­

EdH ina (ecope)

2

RHri.".1 Tn.'~"ctio", (vri tt",,)

nat. In.truction. Proar_r

~ er) D"," T....Tip" Punch D.U Storaa"(..Ig"etic) ,'!

Hydroae.. Propertie. Subrouti"e In" Library of 1103

Cilculation Subroutine. n••• Tan"

"r1tUnJ D.to '10"

T.p. 'unch (p.per) .1." he.bly (1103)

7 R6

~

Digital a.cor"er

1'1... Brook 1

--, I I

Dltl Tnpe I RHrivv,," Darl T.....DIU Ta..,. ae tri.".l,(magnetic) I (...gnatic) (...gneUc)(1103) 4I -

I Retri.".l ,I1'1 nI..J TI e

Pro....Pron...D.,i••" Info.... tion Progr_r Cord 'unch(Type­ (cord.)(calibroti,," d.U••1",inl1" equatione and .. terll1 "ritt.,,)

9propetti..) 10

11_1 ('"A..

"" Pip.I J-PIota

Output Tip.Listing TunleriptioD(1401) ..etic)1("· (1103) (1103)1.18t1

I lIoul. 14 13 19r­

~

Tip. A....bly ~-••an" lc)(1"01)

11

1103 Out--Put 'ta... Data ProC:"le1ng

T·.anvUe)

Il.flectorI 20~ Output Tlpel!hIt"ut T....Cord Punch Curve FH Rout!ne - Cheng" to 7094 Porma t(.Ig"ettc)I(".&DItic) (7094) (1401)

I Con 1617?,r­'laure fO.· BLOCK DIllGlWl OF AUmHATilD DATA REDUCTION PROCEDURE

12

15