31
HAN based green propellant - Application and its Combustion Mechanism - Toshiyuki KATSUMI and Keiichi HORI(ISAS/JAXA)

HAN based green propellant - Application and its Combustion Mechanism - Toshiyuki KATSUMI and Keiichi HORI(ISAS/JAXA)

Embed Size (px)

Citation preview

Page 1: HAN based green propellant - Application and its Combustion Mechanism - Toshiyuki KATSUMI and Keiichi HORI(ISAS/JAXA)

HAN based green propellant- Application and its

Combustion Mechanism -

Toshiyuki KATSUMI and Keiichi

HORI(ISAS/JAXA)

Page 2: HAN based green propellant - Application and its Combustion Mechanism - Toshiyuki KATSUMI and Keiichi HORI(ISAS/JAXA)

HAN-based liquid propellant

Hydroxyl Ammonium Nitrate (NH2OH ・HNO3)

High Oxidizability Low Toxicity High Deliquescent

High Density Low Freezing Point

Water Solution Liquid Oxidizer Monopropellant

Page 3: HAN based green propellant - Application and its Combustion Mechanism - Toshiyuki KATSUMI and Keiichi HORI(ISAS/JAXA)

Hydrazine

HAN-based propellant(SHP163)

Density ρ [×103 kg/m3] at 20 ˚C 1.0 1.4

Freezing temperature [˚C] 1.4 -68

Specific Impulse Isp** [s] 233 276ρ ・ Isp** [×103 s*kg/m3] 233 386

Toxicity High Low* SHP163: HAN/Ammonium Nitrate/Water/Methanol=95/5/8/21 (mass

ratio)** Nozzle area ratio (Ae/At);50, CF;1.875, Combustion chamber pressure;

0.7MPa

ρ ・ Isp of HAN-based propellant is approximately 70% higher than Hydrazine

Comparison of HAN-based solution with Hydrazine

Page 4: HAN based green propellant - Application and its Combustion Mechanism - Toshiyuki KATSUMI and Keiichi HORI(ISAS/JAXA)

0.1

1

10

100

1000Sample #1 (95/5/8/0)

1 10

RE

GR

ES

SIO

N R

AT

E /

mm

/s

PRESSURE / MPa

5 73

Control

Burning rate

0.1

1

10

100

1000Sample #1 (95/5/8/0)Sample #2 (95/5/8/8)

1 10

RE

GR

ES

SIO

N R

AT

E /

mm

/s

PRESSURE / MPa

5 73

Control SHP069

Control HAN/AN/Water/Methanol = 95/5/8/0SHP069 HAN/AN/Water/Methanol = 95/5/8/8SHP163 HAN/AN/Water/Methanol = 95/5/8/21

0.1

1

10

100

1000Sample #1 (95/5/8/0)Sample #2 (95/5/8/8)Sample #3 (95/5/8/21)

1 10

RE

GR

ES

SIO

N R

AT

E /

mm

/s

PRESSURE / MPa

5 73

Control SHP069 SHP163

• Hydrodynamic instability triggers the jump of the burning rate to very high rate region• Methanol addition shifts the critical pressure to higher pressure.

Combustion mechanism has not been clarified

AN and methanol are eliminated

Page 5: HAN based green propellant - Application and its Combustion Mechanism - Toshiyuki KATSUMI and Keiichi HORI(ISAS/JAXA)

1

10

100

1000

1 10Pressure [MPa]

Line

ar b

urni

ng r

ate

[mm

/s]

3 5 72 4 6 8 9

80mass%

77.5mass%

64mass%

50mass%

95mass%

85mass%

Burning rates of aq. solutions

82.5mass%

Crystal*

64mass%*

*B. N. Kondrikov, V. E. Annikov, V. Yu. Egorshev, and L. T. De Luca, “Burning of Hydroxylammonium nitrate”, Combustion, Explosion and Shock waves, Vol.36,No.1 ,2000

The linear burning rate has the peak at approximately 80mass% of HAN concentration

Page 6: HAN based green propellant - Application and its Combustion Mechanism - Toshiyuki KATSUMI and Keiichi HORI(ISAS/JAXA)

1

10

100

1000

1 10Pressure [MPa]

Line

ar b

urni

ng r

ate

[mm

/s]

3 5 72 4 6 8 91

10

100

1000

1 10

95mass%

85mass%

82.5mass%

80mass%

77.5mass%

64mass%

50mass%

Crystal by De Luca

3 5 72 4 6 8 9

Zone3

Zone2

Zone1

0 5 10 15300

400

500

600

700

800

Tem

pera

ture

T /

K

Distance x / mm

0 5 10 15300

400

500

600

700

800

Tem

pera

ture

T /

K

Distance x / mm

High burning rate

Low burning rate

The linear burning rates are classified to three zones

Page 7: HAN based green propellant - Application and its Combustion Mechanism - Toshiyuki KATSUMI and Keiichi HORI(ISAS/JAXA)

Objective

Combustion Model of HAN-based propellant solution

Combustion model of HAN aqueous solution

Page 8: HAN based green propellant - Application and its Combustion Mechanism - Toshiyuki KATSUMI and Keiichi HORI(ISAS/JAXA)

95mass% solution 80mass% solution

T

Tf

Liquid phase Gas phase

Two-phase

Reaction zone

T

Two-phaseLiquid phase

Tbp Tbp

The combustion wave structure of HAN aq. solution

Page 9: HAN based green propellant - Application and its Combustion Mechanism - Toshiyuki KATSUMI and Keiichi HORI(ISAS/JAXA)

95mass% solution 80mass% solution

T

Tf

Liquid phase Gas phase

Two-phase

Reaction zone Reaction zone

T

Two-phaseLiquid phase

Tbp Tbp

Combustion wave structure changes by the water content

The combustion wave structure of HAN aq. solution

Page 10: HAN based green propellant - Application and its Combustion Mechanism - Toshiyuki KATSUMI and Keiichi HORI(ISAS/JAXA)

Two-phase region

1. Fine bubbles are generated in front of the combustion wave

2. Chemical reaction starts in the bubble

Reaction zone

Two-phaseLiquid phase

High rb mode

Page 11: HAN based green propellant - Application and its Combustion Mechanism - Toshiyuki KATSUMI and Keiichi HORI(ISAS/JAXA)

Two-phase region

1. Fine bubbles are generated in front of the combustion wave

2. Chemical reaction starts in the bubble3. Significant superheat (T) is generated

Reaction zone

Two-phaseLiquid phase

T

High rb mode

Page 12: HAN based green propellant - Application and its Combustion Mechanism - Toshiyuki KATSUMI and Keiichi HORI(ISAS/JAXA)

Two-phase region

1. Fine bubbles are generated in front of the combustion wave

2. Chemical reaction starts in the bubble3. Significant superheat (T) is generated4. Rapid nucleation is caused by superheat

T

Reaction zone

Two-phaseLiquid phase

High rb mode

Page 13: HAN based green propellant - Application and its Combustion Mechanism - Toshiyuki KATSUMI and Keiichi HORI(ISAS/JAXA)

Reaction zone

Two-phaseLiquid phase

High rb modeTwo-phase region

1. Fine bubbles are generated in front of the combustion wave

2. Chemical reaction starts in the bubble3. Significant superheat (T) is generated4. Rapid nucleation is caused by

superheat5. High rb mode is established

Nucleation rate may determine the burning rate

Page 14: HAN based green propellant - Application and its Combustion Mechanism - Toshiyuki KATSUMI and Keiichi HORI(ISAS/JAXA)

Superheat & Nucleation rate

TMpi

RTr

ffg

SAT

2* 2

SATg TTT

hkTg / **

3

4)( rrG

gkTrGNedt

dn )( *

T; superheatTg; vapor temperatureTSAT; saturation temperaturedn/dt; nucleation rateN; number of molecules per unit volumek; Boltzmann constanth; Plank’s constantr*; radius of the vapor nucleus; surface tensionR; universal gas constantifg; latent heat of vaporizationM; molecular weightpf; pressure in liquid space

Tg TSAT

Liquid Bubble

,

Page 15: HAN based green propellant - Application and its Combustion Mechanism - Toshiyuki KATSUMI and Keiichi HORI(ISAS/JAXA)

1.E-09

1.E-08

1 10

Pressure (MPa)

r* (

m)

2 3 4 5 6 7 8 9

5E-09

Tg=900KTg=800K

Tg=1300K

Tg=1200K

Tg=1100KTg=1000K

1.E-09

1.E-08

1 10

Pressure (MPa)

r* (

m)

2 3 4 5 6 7 8 9

5E-09

Tg=900KTg=800K

Tg=1300K

Tg=1200K

Tg=1100KTg=1000K

r*min=2x10-9m

Radiuses of vapor nucleuses

(10A)

Parameter; Pressure1~8MPa

Gas temperature800~1300K

Page 16: HAN based green propellant - Application and its Combustion Mechanism - Toshiyuki KATSUMI and Keiichi HORI(ISAS/JAXA)

Nucleation rate (dn/dt)

1E+00

1E+02

1E+04

1E+06

1E+08

1E+10

1E+12

1E+14

1E+16

1E+18

1E+20

1E+22

1E+24

1E+26

1E+28

1E+30

1 10Pressure [MPa]

Nuc

leat

ion

rate

[m

-3s-

1]

2 3 4 5 6 7 8 9

Tg=1100KTg=900K

Tg=1000KTg=800K

Tg=1200K

Tg=1300K

Parameter; Pressure1~8MPa

Gas temperature800~1300K

r*min=2x10-9m

Page 17: HAN based green propellant - Application and its Combustion Mechanism - Toshiyuki KATSUMI and Keiichi HORI(ISAS/JAXA)

1E-501E-471E-441E-411E-381E-351E-321E-291E-261E-231E-201E-171E-141E-111E-081E-051E-021E+011E+04

1 10

Pressure (MPa)

dv/dt

(m3 /s

)

Tg=1100K Tg=900K

Tg=1000K

2 3 4 5 6 7 8 9

Tg=800K

Tg=1200K

Tg=1300K

dv/dt (4/3r*3dn/dt)1000mm/s

1mm/s

Linear burning rate

In Zone2, bubble nucleation rate governs the burning rate.

1

10

100

1000

1 10Pressure [MPa]

Line

ar b

urni

ng r

ate

[mm

/s]

3 5 72 4 6 8 9

80mass%

77.5mass%

82.5mass%

64mass%

50mass%

Page 18: HAN based green propellant - Application and its Combustion Mechanism - Toshiyuki KATSUMI and Keiichi HORI(ISAS/JAXA)

dv/dt (4/3r*3dn/dt)

1E-501E-471E-441E-411E-381E-351E-321E-291E-261E-231E-201E-171E-141E-111E-081E-051E-021E+011E+04

1 10

Pressure (MPa)

dv/dt

(m3 /s

)

Tg=1100K Tg=900K

Tg=1000K

2 3 4 5 6 7 8 9

Tg=800K

Tg=1200K

Tg=1300K

1000mm/s

1mm/s

Linear burning rate

80-50mass%; The gas temperature in bubbles may be lower than 80 mass% aq. solution because of higher water content. The nucleation and burning rates become lower.

95-80mass%; The gas temperature in bubble may be lower than 80 mass% aq. solution, as the two-phase region is relatively short. The nucleation and apparent burning rates become lower.

Page 19: HAN based green propellant - Application and its Combustion Mechanism - Toshiyuki KATSUMI and Keiichi HORI(ISAS/JAXA)

Combustion mode in Zone3

(4) Expansion into liquid phase (5) Expansion stops

(3) Concentration of reactive gas into concave area

Surface propagation rate increases rapidly by the local disturbance

(2) Local disturbance(1) Stable combustion

wave

Page 20: HAN based green propellant - Application and its Combustion Mechanism - Toshiyuki KATSUMI and Keiichi HORI(ISAS/JAXA)

Comparison of combustion wave structure

1

10

100

1000

1 10Pressure [MPa]

Line

ar b

urni

ng r

ate

[mm

/s]

3 5 72 4 6 8 9

Zone3

Zone2

Zone1

Propellant solution

0.1

1

10

100

1000Sample #1 (95/5/8/0)Sample #2 (95/5/8/8)Sample #3 (95/5/8/21)

1 10

RE

GR

ESS

ION

RA

TE

/ m

m/s

PRESSURE / MPa

5 73

Control SHP069 SHP163

Aqueous solution

The jump mechanism of burning rate to high rate region is not clarified

Low rb

High rb

Combustion wave structures of propellant solutions are similar to aqueous solution in

each burning rate zone

Page 21: HAN based green propellant - Application and its Combustion Mechanism - Toshiyuki KATSUMI and Keiichi HORI(ISAS/JAXA)

Phenomena of Burning Rate Jumping

Transition Process

Liquid

Liquid(4) New bubbles develop quickly

(5) Extremely high burning rate is established

Liquid New BubbleLiquid(1) Stable

combustion wave propagates

(3) New fine bubble are generated

Liquid(2) Brown bubble invade into liquid phase

Hydrodynamic instability is the trigger to jump to extremely high

burning rate region

Page 22: HAN based green propellant - Application and its Combustion Mechanism - Toshiyuki KATSUMI and Keiichi HORI(ISAS/JAXA)

Hydrodynamic instability - 1

◆Margolis model; extended model of Landau/Levich instability

Stable at high pressure, and at low methanol content Our results; Unstable at high pressure and at low methanol content

Estimation result is opposite tendencies to

our results

KaMaSu

- SuSu

(l)

(s)(l) Su(s); Burnign rate of stretched flame

Su(l); Laminar burning rate

Ka; Flame stretch ratio

Markstein number (Ma)

Number Lewis ;Numberdovich Zel';,

1ln

1

1

2

1ln

1

20

1

0

D

aLe

T

TTT

dxx

xLeMa

s

addbu

By Clavin P., Energy Combust. Sci., vol.11, pp.1-59, 1985

Markstein number (by asymptotics)

◆ Flame stretch effect

Lewis number effect; out of consideration

(Lewis number; no pressure dependency)

Page 23: HAN based green propellant - Application and its Combustion Mechanism - Toshiyuki KATSUMI and Keiichi HORI(ISAS/JAXA)

Hydrodynamic instability - 3

4

4.5

5

5.5

6

6.5

7

7.5

0 2 4 6 8 10Pressure [MPa]

Mar

kste

in N

umbe

r

ControlSHP069SHP163

Unstable at high pressure, and at low methanol content Our results; Unstable at high pressure and at low methanol content

Ma=Ma,cr

Estimation results supports our results0.1

1

10

100

1000Sample #1 (95/5/8/0)Sample #2 (95/5/8/8)Sample #3 (95/5/8/21)

1 10

RE

GR

ESS

ION

RA

TE

/ m

m/s

PRESSURE / MPa

5 73

Control SHP069 SHP163

3.3MPa5.0MPa

6.6MPa

Hydrodynamic instability of propellant solutions is affected by

flame stretch and determines the jump

pressure.

Page 24: HAN based green propellant - Application and its Combustion Mechanism - Toshiyuki KATSUMI and Keiichi HORI(ISAS/JAXA)

Application to thruster

Development of HAN-based Monopropellant Thruster

ObjectiveObjective

HeaterHeaterHeaterHeater

CatalystCatalystCatalystCatalyst

Burning process1.Monopropellant is injected into the preheated catalyst bed.2.Chemical reaction of monopropellant occurs at the catalyst bed.3.Gas products burn thoroughly in the combustor.4.Combustion product gas is exhausted through the nozzle.

Propellant; SHP163Catalyst; S405

PropellantPropellantPropellantPropellant

Page 25: HAN based green propellant - Application and its Combustion Mechanism - Toshiyuki KATSUMI and Keiichi HORI(ISAS/JAXA)

Free fall test 1/2

Launch

[email protected] Y=0 sec

Y+20 secStart

Y +50 secFinish

Thrusters burnfor 30 seconds

Sequence

HAN-based thruster system

ObjectiveObjectivePretest of supersonic vehicle test flight • Balloon operation• Attitude control by N2 gas jets• HAN thrusters help the acceleration at free fall

Supersonic vehicle mock-up

Page 26: HAN based green propellant - Application and its Combustion Mechanism - Toshiyuki KATSUMI and Keiichi HORI(ISAS/JAXA)

Flight system

Free fall test 2/2

Catalyst bed

Injector

Combustion chamber

Pressure sensor

Thermocouple

Nozzle

Diameter; 75 mm Length; 992.5 mm

Thruster

Thruster

Valve

Propellant Tank

Page 27: HAN based green propellant - Application and its Combustion Mechanism - Toshiyuki KATSUMI and Keiichi HORI(ISAS/JAXA)

Static firing testSimulated environmental test (Vacuum and Low temperature)

• Thruster burned stably for 30 seconds in simulated condition

Page 28: HAN based green propellant - Application and its Combustion Mechanism - Toshiyuki KATSUMI and Keiichi HORI(ISAS/JAXA)

Static firing test (movie)

Page 29: HAN based green propellant - Application and its Combustion Mechanism - Toshiyuki KATSUMI and Keiichi HORI(ISAS/JAXA)

Result of free fall test

• Thruster burned well for 30 seconds in the flight• Density*Isp is approximately 1.46 times higher than the hydrazine• This results show the potential for the application to space programs

Specific impulse; 230 secCombustion efficiency; 0.88

Page 30: HAN based green propellant - Application and its Combustion Mechanism - Toshiyuki KATSUMI and Keiichi HORI(ISAS/JAXA)

Summary -Combustion mechanism-

• Bubble nucleation rate by superheat governs the apparent linear burning rate in very high burning rate zone.

• The water content dominates the burning rate zone in the case of aqueous solutions.

• The hydrodynamic instability determines the burning rate zone in the case of propellant solutions.

Page 31: HAN based green propellant - Application and its Combustion Mechanism - Toshiyuki KATSUMI and Keiichi HORI(ISAS/JAXA)

Summary -Application to thruster-

• Flight system is developed and burnt for 30 seconds successfully in vacuum and -50 C

• Isp is approximately 230 seconds

• The high potential of HAN-based thruster for the application to space programs was shown