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Basic Turbojet Engine

Basic Turbojet Engine. 5. 1. 4. 2. 3. 1 – Inlet 2 – Post compression 3 – Post combustion 4 – After turbine 5 – Exhaust. GENX Engine. Same scale. GE I-A 1,250 pounds of thrust. GE90-115B 115,000 lbs. thrust. GP7200 for the Airbus A380. T.O. Thrust 70,000 lb

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Basic Turbojet Engine

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  1. Basic Turbojet Engine 5 1 4 2 3 1 – Inlet 2 – Post compression 3 – Post combustion 4 – After turbine 5 – Exhaust

  2. GENX Engine

  3. Same scale GE I-A 1,250 pounds of thrust GE90-115B 115,000 lbs. thrust

  4. GP7200 for the Airbus A380 T.O. Thrust 70,000 lb Bypass ratio 8.7 to 1 Fan Diameter 116 in (295 cm)

  5. Water Ingestion - Peebles, Ohio Crosswind Testing (Site 6A at Peebles, Ohio) Hail Ingestion (Site 4A, Peebles, Ohio) GE90-115B Certification

  6. Propulsion Driving Industry Advances 0.9 JT3C Turbojet Low Bypass Turbofan High Bypass Turbofan 2nd Gen High Bypass Turbofan 0.8 JT3D-1 JT8D-9 CJ805 0.7 JT8D-217 TAY 620 JT9D-7A SFC 35K/0.8Mn Uninstalled JT9D-3A CFM56-2 CF6-6D RB-211-524D CFM56-5A BR 715 V2500 A1 0.6 JT9D-7R4G2 RB-211-535E4 CF6-80A CF6-80C2-B6F CFM56-5C4 PW2037 PW4056 CF6-80E1-A2 PW4168 PW4098 PW4084 TRENT 895 GE90-85B 0.5 GE90-115B 0.4 1950 1960 1970 1980 1990 2000 2010 2020 Certification Date

  7. Noise Reduction Advancements Turbojet 120 • Normalized to 100,000-lb. thrust • Noise levels are for airplane/engine configurations at time of initial service 707-100 110 Noise Level, EPNdB (1500-ft. sidelines) Second Generation Turbofan DC-9-10 737-200 727-200 100 737-200 A321 747-200 A310 First Generation Turbofan A330 747-400 DC-10-30 737-300 90 1950 1960 1970 1980 1990 2000 Year of Initial Service

  8. SR-30 Turbojet Engine

  9. SR-30 Gas Turbine Engine – Cut Away Axial Turbine Radial Compressor Counterflow Combustor Fuel Injector Impingement Start 1 5 Air Intake Thrust Producer 4 3 Flame 2

  10. SR-30 Gas Turbine Engine – Side View Oil Inlet spark Inlet nozzle T2 T1 T3 Oil Outlet

  11. SR-30 Gas Turbine Engine – Exhaust View Fuel Injectors Exhaust Nozzle Fuel Input T5 Throttle arm

  12. Pitot used to traverse the exhaust plane Nozzle (guide vanes) 2 Oil inlet combustor combustor 3 1 Exhaust nozzle 4 6 Radial Compressor Axial Turbine Fuel Injector combustor Oil outlet Hatched regions indicate blading Ignitor

  13. SR-30 Components Radial diffuser Guide vanes to turbine Outer Housing Inlet Nozzle Combustor Flow direction Fuel manifold Radial Compressor Ceramic Ball bearings Turbine

  14. SR-30 Turbojet Engine -- Plumbing cooling fans oil pump fuel tank (red) oil return fuel pump oil delivery fuel filters oil filters oil tank

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