1. Aerospace 410 Aerospace Propulsion

2. DESIGN AND DEVELOPMENT OF SMALL TURBO-JET ENGINES THRUST < 100 Lbf Prepared by : Cengiz Camci November 2002

3. A LABORATORY DEMONSTRATION IS SCHEDULED ON THIS FRIDAY 11/22/2002 12:00-1:10 pm Department of Aerospace Engineering

4. There are two parts in this presentation 1.General Small Engine Details Engines up to a few hundred pounds 2. Sophia J-850 19 lbs Turbo-jet Engine Used in our laboratory demonstration THIS FRIDAY !!! 12: 00 pm

5. 1. General Small Engine Details Engines up to a few hundred pounds Department of Aerospace Engineering

16. 2. Sophia J-850 19 lbs Turbo-jet Engine Department of Aerospace Engineering

17. 130,000 rpm 19 lbf turbojet engine

18. Sophia J-850 Engine CompressorSingle Centrifugal TurbineSingle Radial Combustion chamberAnnular Maximum Thrust8.0 kgf 19.1 lbsf Maximum Rotor RPM 130,000 Maximum Airflow0.15kg/sec Compressor Ration2.70

21. Maximum Exhaust Gas Temp. 800 C 1472°F Full Throttle Exhaust Gas Temp.750 C 1382°F Low Throttle Exhaust Gas Temp. 450 C 842°F Maximum Fuel Consumption270cc/min Fuel FeedGear Pump with DC Motor Throttle ControlAutomatic Start/Shutdown, ECU-Controlled LubricationTotal Loss Oil ECU-Controlled Pump

22. Ignition On Board ECU-Controlled Glow Ignition Fuel Cells1.5 –2.0 Litters Recommended Oil Tank180 – 250cc Recommended StartingCompressed Air (Scuba/Regulator, not supplied) FuelJP-4,White Gas,Coleman Fuel Jet A-1 OilTurbojet Oil Exxon 2380, Castrol 5000,MIL-L-23699E

36. Sophia J850 Engine CompressorSingle Centrifugal TurbineSingle Radial Combustion chamberAnnular Maximum Thrust8.0 kgf 19.1 lbsf Maximum Rotor RPM 130,000 Maximum Airflow0.15kg/sec Compressor Ration2.70

37. Aerospace 410 Aerospace Propulsion