SNECMA M45

Summary

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.

SNECMA M45
Type Turbojet engine
National origin France
Manufacturer SNECMA
Variants Rolls-Royce/SNECMA M45H

VariantsEdit

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)Edit

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

See alsoEdit

Related development

Related lists

ReferencesEdit

  1. ^ a b Wilkinson, Paul H. (1964). Aircraft Engines of the World 1964/65 (20th ed.). London: Sir Isaac Pitman & Sons Ltd. p. 158.
  2. ^ a b c d Wilkinson, Paul H. (1966). Aircraft engines of the World 1966/67 (22nd ed.). London: Paul H. Wilkinson. p. 165.
  3. ^ Wilkinson, Paul H. (1966). Aircraft engines of the World 1966/67 (22nd ed.). London: Paul H. Wilkinson. p. 166.