Aerospace 410

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Aerospace 410 Aerospace Propulsion
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DESIGN AND DEVELOPMENT OF SMALL TURBO-JET
ENGINES THRUST lt 100 Lbf
Prepared by Cengiz Camci November 2002
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A LABORATORY DEMONSTRATION IS SCHEDULED ON THIS
FRIDAY 11/22/2002 1200-110 pm
Department of Aerospace Engineering
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• 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

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1. General Small Engine Details Engines up to a
few hundred pounds
Department of Aerospace Engineering
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2. Sophia J-850 19 lbs Turbo-jet Engine
Department of Aerospace Engineering
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130,000 rpm 19 lbf turbojet engine
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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
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Maximum Exhaust Gas Temp. 800 C 1472F Full
Throttle Exhaust Gas Temp. 750 C 1382F Low
Throttle Exhaust Gas Temp. 450 C
842F Maximum Fuel Consumption 270cc/min Fuel
Feed Gear Pump with DC Motor Throttle
Control Automatic Start/Shutdown, ECU-Controll
ed Lubrication Total Loss Oil ECU-Controlled
Pump
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Ignition On Board ECU-Controlled
Glow Ignition Fuel Cells 1.5 2.0 Litters
Recommended Oil Tank 180 250cc
Recommended Starting Compressed Air
(Scuba/Regulator, not supplied) Fuel JP-4,Whi
te Gas,Coleman Fuel Jet A-1 Oil Turbojet
Oil Exxon 2380, Castrol 5000,MIL-L-23699E

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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
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Aerospace 410 Aerospace Propulsion