Turbojets are used as high performance jet engines in combat aircraft and to provide the core of the very successful turbofan engines used on the great majority of airliners.
Turbojet Engine Test Stand provides a fully functioning, aero derivative small jet turbine. The jet turbine thrust can be measured and outputs from 10 to 100N can be achieved.
The unit is provided with a mimic diagram displaying the temperatures of the gas flow and engine pressure ratio. Air flow, fuel flow and rotational speed measurement mean that an energy balance for the engine can be undertaken.
We have developed a turbo jet engine test stand to provide a cost effective method of testing the performance of an operational aero jet engine. The turbo jet test stand is mounted on a wheeled trolley allowing it to be moved to an operational area or stored in a convenient location.
The test stand provides a fully functioning and instrumented engine. The engine used incorporates a single stage centrifugal compressor, feeding air into a combustion chamber fed by multiple fuel injectors, and through to a single stage centrifugal turbine. A tailpipe ducts the gas into a thrust producing jet. The turbine uses ceramic bearings eliminating the need for lubricating oil.
Air is ducted into the engine via a calibrated nozzle such that air mass volume can be determined, and fuel is pumped into the engine by a small electrically driven gear pump. The pump is precisely controlled by the Engine Control Unit so as to directly control the engine speed. Operator control is provided by a throttle lever. Fuel is in the form of kerosene, with a lubricant mix, and starting is provided with a decoupling electric starter.
The whole engine and air inlet unit is mounted on two sliding rails, constrained by a linear thrust transducer.
Temperatures are measured for air inlet, fuel inlet compressor outlet, combustion chamber outlet and tail pipe stream. Pressures are measured as ambient air pressure, air inlet differential pressure and compressor outlet pressure.
This product displays indications on a physical mimic of the turbo jet, whilst data acquisition based system includes a data acquisition system that records and displays indications on a screen mimic.
Software TH-3133SW (optional)
DAQ software specially designed in National Instrument™, LABVIEW™ environment to measure and calculate the results of apparatus. The software is optional and while using software a set of electronic sensors are included. Software can be run with any Windows™ environment.