Basic Turbojet Engine

2

1

34

5

1 – Inlet2 – Post compression3 – Post combustion4 – After turbine5 – Exhaust

GENX Engine

GE90-115B 115,000 lbs. thrust

GE I-A 1,250 pounds of thrust

Same scale

GP7200 for the Airbus A380

T.O. Thrust 70,000 lbBypass ratio 8.7 to 1Fan Diameter 116 in (295 cm)

Water Ingestion - Peebles, OhioWater Ingestion - Peebles, Ohio

GE90-115B Certification

Hail Ingestion(Site 4A, Peebles, Ohio)

Hail Ingestion(Site 4A, Peebles, Ohio)

Crosswind Testing(Site 6A at Peebles, Ohio)

Crosswind Testing(Site 6A at Peebles, Ohio)

Propulsion Driving Industry Advances

PW4098

PW4084

JT8D-217

JT8D-9

JT3D-1

JT9D-7R4G2

JT9D-3A

JT9D-7A

PW4056PW2037

V2500 A1

PW4168

CJ805

CF6-6DCFM56-2

CFM56-5A

GE90-85B

CF6-80ACFM56-5C4

CF6-80C2-B6F

CF6-80E1-A2

RB-211-535E4

TRENT 895

RB-211-524D

TAY 620

BR 715

1950 1960 1970 1980 1990 2000 2010 2020Certification Date

SF

C 3

5K/0

.8M

n U

nin

stal

led

JT3C

Low Bypass Turbofan

2nd Gen High Bypass Turbofan

High Bypass Turbofan

Turbojet

GE90-115B

0.9

0.8

0.7

0.6

0.5

0.4

Noise Reduction Advancements

120

110

100

901950 1960 1970 1980 1990 2000

707-100

DC-9-10

737-200

727-200

747-200

DC-10-30

A310

737-300

737-200 A321

747-400 A330

NoiseLevel,

EPNdB(1500-ft.

sidelines)

Turbojet

First GenerationTurbofan

Second GenerationTurbofan

• Normalized to 100,000-lb. thrust• Noise levels are for airplane/engine

configurations at time of initial service

Year of Initial Service

SR-30 Turbojet Engine

Flame

Radial Compressor

FuelInjector

Axial Turbine

ThrustProducer

CounterflowCombustor

SR-30 Gas Turbine Engine – Cut Away

AirIntake

1

2

3

5

4

Impingement Start

Oil InletOil Inlet

Oil OutletOil Outlet

T3T3

T2T2

sparkspark

Inletnozzle

T1T1

SR-30 Gas Turbine Engine – Side View

Exhaust NozzleExhaust Nozzle

Throttle armThrottle arm

T5T5

Fuel InjectorsFuel Injectors

Fuel InputFuel Input

SR-30 Gas Turbine Engine – Exhaust View

FuelInjector

Ignitor

Oil outlet

Oil inlet

Exhaust nozzle

combustorcombustor

Axial Turbine Radial Compressor

Hatched regions indicate blading

1

2

3

4

6

Nozzle (guide vanes)Pitot used to traversethe exhaust plane

combustor

combustor

Inlet Nozzle Combustor

Turbine

Fuel manifold

Radial Compressor

Outer Housing

Radial diffuser

Guide vanes to turbine

Ceramic Ball bearings

SR-30 Components

Flow directio

n

fuel pump

oil pump

cooling fans

oil tank

fuel tank(red)

fuel filters

SR-30 Turbojet Engine -- Plumbing

oil delivery

oil return

oil filters