Engineering:SNECMA M45
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Revision as of 07:22, 8 June 2022 by imported>NBrushPhys (change)
| SNECMA M45 | |
|---|---|
| Type | Turbojet engine |
| National origin | France |
| Manufacturer | SNECMA |
| Variants | Rolls-Royce/SNECMA M45H |
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[1]
- M45A
- A compact moderate thrust turbojet.
- M45A-3
- for civil applications.[2]
- M45AF
- Aft-fan turbofan engine intended for civil aircraft.
- M45B
- Turbojet with afterburning for military aircraft.
- M45B-3
- With afterburner.[2]
- M45F-3
- Civil non-afterburning for small airliners / business jets.[2]
- M45L-1
- Lightweight civil version for small business jets.[2]
- SNECMA/Bristol Siddeley M45G
- Afterburning turbofan engine for AFVG, from the civil M45F.[3]
Specifications (M45A)
Data from Aircraft Engines of the World 1964/65[1]
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
- Power-to-weight ratio:
See also
Related development
- Rolls-Royce/SNECMA M45H
Related lists
References
- ↑ 1.0 1.1 Wilkinson, Paul H. (1964). Aircraft Engines of the World 1964/65 (20th ed.). London: Sir Isaac Pitman & Sons Ltd.. p. 158.
- ↑ 2.0 2.1 2.2 2.3 Wilkinson, Paul H. (1966). Aircraft engines of the World 1966/67 (22nd ed.). London: Paul H. Wilkinson. p. 165.
- ↑ Wilkinson, Paul H. (1966). Aircraft engines of the World 1966/67 (22nd ed.). London: Paul H. Wilkinson. p. 166.
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