Aerospace 410 Aerospace Propulsion.

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Presentation transcript:

Aerospace 410 Aerospace Propulsion

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

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

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

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

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

130,000 rpm 19 lbf turbojet engine

Sophia J-850 Engine Compressor Single Centrifugal Turbine Single Radial Combustion chamber Annular Maximum Thrust 8.0 kgf 19.1 lbsf Maximum Rotor RPM 130,000 Maximum Airflow 0.15kg/sec Compressor Ration 2.70

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 Consumption 270cc/min Fuel Feed Gear Pump with DC Motor Throttle Control Automatic Start/Shutdown, ECU-Controlled Lubrication Total Loss Oil ECU-Controlled Pump

Ignition On Board ECU-Controlled Glow Fuel Cells 1.5 –2.0 Litters Recommended Oil Tank 180 – 250cc Recommended Starting Compressed Air (Scuba/Regulator, not supplied) Fuel JP-4,White Gas,Coleman Fuel Jet A-1 Oil Turbojet Oil Exxon 2380, Castrol 5000,MIL-L-23699E

Sophia J850 Engine Compressor Single Centrifugal Turbine Single Radial Combustion chamber Annular Maximum Thrust 8.0 kgf 19.1 lbsf Maximum Rotor RPM 130,000 Maximum Airflow 0.15kg/sec Compressor Ration 2.70

Aerospace 410 Aerospace Propulsion