
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 |
