Allison J71

The Allison J71 is a turbojet engine of the U.S. producer Allison.

The engine was a further development of the Allison J35 and was originally intended to receive the designation J35 -A-23. The main change involved the type and shape of the combustion chamber. While the J35 still had ten single, separate combustion chambers, were held at J71 injection and combustion in an annular combustion chamber large. This design was described by Allison as " cannular ".

The compression was done in a 16 -stage axial compressor, driven by a three-stage axial turbine also. The engine was completely weather resistant and had in the inlet own de-icing, which was heated with bleed air. A hydraulic supplied the setting elements in the inlet and at the outlet nozzle. The engine control was performed electro-hydraulically with a control unit, which was designed and built by Honeywell.

In the entrance examination the engine yielded a takeoff thrust of 44.5 kN at 6100 min -1.

J71 -A-2

Initial production version for the McDonnell F3H. Equipped with an afterburner they provided a static thrust of 62.2 kN.

J71 -A-3

Execution for the Northrop SM -62 Snark as a loss engine. This design was originally intended for a development of the Northrop F -89, F- 89E. This engine provided a thrust of 43.2 kN.

J71 -A-4

Design for the Martin P6M with a comparison to the embodiment A-2 shortened afterburner. The maximum thrust with afterburner was 57.9 kN.

YJ71 -A-5

Version for non-produced Boeing B- 47C with 47.7 kN of thrust.

J71 -A-7

Improved embodiments of the J71 -A-2, should be used in the Republic F -105.

J71 -A-9

Execution for the Douglas B- 66A without afterburner. The decision for the production of this version was on 5 August 1952.

J71 -A-11

Improved version of the Douglas RB- 66B, also without afterburner.

J71 -A -13

For the variants Douglas B- 66B, EB- 66C / E, RB- 66B / C, WB- 66D

Specifications ( J71 -A -2)

  • Compressors: axial, 16 -stage
  • Turbine: axial, three-stage
  • Compression ratio: 8:1
  • Air flow: 72.57 kg / s
  • Length: 7230 mm (with afterburner )
  • Diameter: 1067 mm
  • Weight: 2208 kg
  • Off thrust: 62.2 kN

Specifications ( J71 -A-11 )

  • Compressor: such as A- 2
  • Turbine: as A-2
  • Length: 4850 mm
  • Diameter: 1209 mm
  • Weight: 1855 kg
  • Off thrust: 45.4 kN

Swell

  • Jane's all the world aircraft 1956/57,

J30 | J31 | J32 | J33 | J34 | J35 | J36 | J37 | XJ38 | J39 | J40 | J41 | J42 | J43 | J44 | J45 | J46 | J47 | J48 | J49 | J51 | J52 | J53 | J54 | J55 | J56 | J57 | J58 | J59 | J60 | J61 | J63 | J65 | J67 | J69 | J71 | J73 | J75 | J79 | J81 | J83 | J85 | J87 | J89 | J91 | YJ93 | J95 | J97 | J99 | J100 | YJ101 | J102 | J400 | J401 | J402 | J403 | J700

See also: turbofan engines of the U.S. armed forces

  • Turbojet
Allison Engine Company McDonnell F3H Demon SM-62 Snark Northrop F-89 Scorpion Martin P6M SeaMaster Allison J33 Westinghouse J34 De Havilland Goblin Westinghouse J40 Rolls-Royce Nene General Electric J47 Rolls-Royce Avon Wright J65 General Electric J73 General Electric J79 Rolls-Royce Soar
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