TJ23U 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.

Form for providing information on the engine TJ23U

Technical parameters:

Thrust: Take-off (max. 5 min) 210 N
Weight (dry) < 2,1 kg (< 4.63 lb)
Engine length 316 mm (12.4 in)
Outer diameter  121 mm (4.8 in)
Fuel Jet A1 or equivalent with 3% of turbine oil, or diesel with 3% of turbine oil
Oil MIL-L-23699
Operating altitude 6 000 m
Starting altitude information not available

Examples of use