TJ20 Turbojet Engine
Small turbojet engine with the technology of "big" engines. It consists of a single-stage radial compressor, radial and axial diffuser, annular combustion chamber, and single-stage axial turbine.
It reaches up to 210 N thrust with the weight less than 2.1 kg. Engine bearings are lubricated with the mixture of fuel and 3% of oil. The engine is controlled by a digital electronic system integrated in the engine together with fuel pump and two electromagnetic valves. Starting is electrical. Spark plug is built in the jacket of the combustion chamber. Engine clamp and intake screen can be ordered as optional accessories.
|Dimensions and weight|
|Engine length||316 mm|
|Take-off Thrust max 5min)||210 N||47.2 lbf|
|Verified longitudinal overload||+/- 20 G|
|Operating altitude||0 - 6000 m||0 - 20,000 ft|
|Flight speed range||< Mach 0.6|
|Power supply||12 v|
|Specific fuel consumption*||=< 0.165 kg/Nh||=< 1.47 lb/lbf/hr|
|Fuel consumption min. (idle)||126.6 ml /min||4.26 oz/min|
|Fuel consumption max.||650.0 ml/min.||21.98 oz/min|
* (SFC at max. thrust)
Fuel JET A–1 or equivalent with 3 % turbine oil