The SNECMA M45, also called the SNECMA Mars, was a turbojet engine designed and produced by SNECMA in France during the late 1950s and early 1960s. The M45 was the precursor to a family of turbojet and turbofan engines, culminating in the collaborative Rolls-Royce/SNECMA M45H, high bypass turbofan engine.
Variants
Data from: Aircraft Engines of the World 1964/65
- M45A
- A compact moderate thrust turbojet.
- M45A-3
- for civil applications.
- M45AF
- Aft-fan turbofan engine intended for civil aircraft.
- M45B
- Turbojet with afterburning for military aircraft.
- M45B-3
- With afterburner.
- M45F-3
- Civil non-afterburning for small airliners / business jets.
- M45L-1
- Lightweight civil version for small business jets.
- SNECMA/Bristol Siddeley M45G
- Afterburning turbofan engine for AFVG, from the civil M45F.
Specifications (M45A)
Data from Aircraft Engines of the World 1964/65
General characteristics
- Type: 2-spool turbojet engine
- Length: 1,620 mm (63.8 in)
- Diameter: 550 mm (21.7 in)
- Dry weight:
Components
- Compressor:
- Combustors: annular combustion chamber
Performance
- Maximum thrust: 19.57 kN (4,400 lbf)
- Overall pressure ratio: 16:1
See also
Related development
- Rolls-Royce/SNECMA M45H
Related lists
- List of aircraft engines
References
