Turbojet Engine TMM 40

TMM40 is a small expendable turbojet engine rated for 40daN of static thrust. It has been designed to meet the low-cost engine approach, but to keep thrust-to¬-weight and thrust-to-cross section ratio at a competitive level. Also, the design goal was that the engine could be easily resizable to bigger engines, up to 500daN.The engine consists of three stage axial compressor, annular combustion chamber with six injectors and axial turbine. Intake and exhaust nozzle modules can be modified for certain missile designs.

Overall dimensions and weight:	Value
Weight (dry engine)	5.6 kg
Size (mm) LxD	560×150

ISA sea level conditions:	Value
Maximum static thrust	40 daN
Specific fuel consumption	1.42 kg/daNh
Minimum engine life	10 h

Operating envelope:	Value
Mach number	0/0.8
Altitude	0/5000 m
Max. rotor speed	90000 rpm

Fuel system:	Value
Fuel specification	MIL-T-5624

Technical characteristics:	Value
Engine thrust	40 daN
Specific fuel consumption up to	1.5 kg/daNh
Dry engine mass up to	6 kg
Engine length up to	600 mm
Engine diameter up to	155 mm
Working life	10 h
Minimal number of starts	50

Oil system:	Value
Altitude	MIL-L-7808
Air/oil mist system or self lubricated bearings with grease.

Starting system:
Windmilling
Pyrotechnic cartridge

Ignition:
Pyrotechnic ignitor