turbo jet engine
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Air Flow and ThermodynamicsTurbo Jet Engine – 200N Thrust
The engine is a small turbo jet engine and modified for educational purposes. The unit has a radial flow compressor and an axial flow turbine as in the modern jet plane.
Inlet air through an orifice flow measuring device is compressed by a single stage radial flow compressor. The turbine is air started and runs on jet A fuel. The turbine unit is complete with control and monitoring instruments including engine data terminal and automatic start unit. The turbine runs on ceramic bearings. Lubrication is provided by jet oil in the fuel, and no separate lubrication system is required. A fan is provided for engine cooling.
An Electronic Control Unit (ECU) controls the basic turbine operation. Additional instruments are provided for monitoring and controlling the engine performance.
A touch screen computer with an interface unit, and software are provided for speed control, data display analysis, and to assist the ECU.
A transparent engine cover and over speed shutdown are provided.
Instruction manual is also included.
TYPICAL EXPERIMENTS- Understanding the thermodynamic process
- Static thrust vs turbine speed
- Power input and output and propulsive efficiency.
TECHNICAL DATAEngine construction – Diffuser High strength aluminium. – Combustion chamber Inconel. – Bearings Ceramic ball bearing. – Turbine Vacuum cast inconel – Compressor High grade aluminium alloy. Engine performance specifications. – Maximum static thrust Up to 220 N at approx 108,000 rpm. – Starting and running fuel Jet A or Kerosene with jet oil. Sensors: – Temperatures Inlet air, diffuser exit, turbine guide vane entry and exit and nozzle exit. – Pressures Diffuser exit and turbine exit. – Thrust – Speed – Fuel flow rate – Air flow rate Differential pressure at inlet orifice. Accessories: - Engine cooling fan
- Jet oil, 1 L.
- 2 Ear muffs
- Barometer
Power supply 220V, 1 Ph, 50Hz. Other power supply is available on request. (0 reviews) -
Air Flow and ThermodynamicsTurbo Jet Engine – 70N Thrust
The engine is a small turbo jet engine and modified for educational purposes. The unit has a radial flow compressor and an axial flow turbine as in modern jet plane.
Inlet air through an orifice flow measuring device is compressed by a single stage radial flow compressor. The turbine is motor started and runs on Jet A fuel. Fuel is injected and ignited in the combustion chamber providing hot gas for a single stage axial flow turbine which inturn drives the compressor. The gas is exhausted through a nozzle at high velocity providing a thrust. The turbine runs on ceramic bearings. Lubrication is provided by jet oil in the fuel, and no separate lubrication system is required. A fan is provided for engine cooling.
An Electronic Control Unit (ECU) controls the basic turbine operation. Additional instruments are provided for monitoring and controlling engine operation and performance.
A touch screen computer with an interface unit, and software are provided for speed control, data display and analysis, and to assist the ECU.
A transparent engine cover and over speed shutdown are provided.
Instruction manual is also included.
TYPICAL EXPERIMENTS- Understanding the thermodynamic process
- Static thrust vs turbine speed
- Power input and output and propulsive efficiency.
TECHNICAL DATAEngine construction – Diffuser High strength aluminium. – Combustion chamber Stainless steel. – Turbine Vacuum cast inconel. – Compressor High grade aluminium alloy. Engine performance specifications. – Maximum static thrust Up to 70 N at approx. 150,000 rpm. – Starting and running fuel Jet A or Kerosene with jet oil. Sensors – Temperatures Inlet air, diffuser exit, turbine guide vane entry and exit and nozzle exit. – Pressures Diffuser exit and turbine exit. – Thrust. – Speed. – Fuel flow rate. – Air flow rate Differential pressure at inlet orifice. Accessories - Engine cooling fan
- 2 Ear muffs
- Jet oil, 1 L.
- Barometer
Power supply 220V, 1 Ph, 50Hz. Other power supply is available on request. (0 reviews)
