Allison J71

The Allison J71 was a single spool turbojet engine, designed and built in the United States. It began development in 1948 as a much modified J35, originally designated J35-A-23.[1]

J71
J71 engine change in progress on a F3H-2 Demon, 1963.
Type Turbojet
Manufacturer Allison Engine Company
First run 1950
Major applications B-66 Destroyer
F3H Demon
Developed from Allison J35

Operational history

The Allison J71 turbojet powered the Douglas B-66 Destroyer and the McDonnell F3H-2 Demon after the failed Westinghouse J40 proved unworkable. The prototype P6M SeaMasters were also fitted with the engine.

Variants

Data from: Aircraft engines of the World 1953[2]

J71-A-1
J71-A-2
Powered the McDonnell F3H Demon
J71-A-2B
J71-A-2E
9,700 lbf (43.15 kN) thrust (14,000 lbf (62.28 kN) thrust with afterburner), for the McDonnell F3H-2 Demon.
YJ71-A-3
7,000 lbf (31.14 kN) thrust (9,500 lbf (42.26 kN) thrust with afterburner)
J71-A-4
Afterburning turbojet engines for the Martin XP6M-1 Seamaster flying boat prototypes.
J71-A-6
Afterburning turbojet engines for the Martin YP6M-1 Seamaster pre-production flying boats.
J71-A-7
14,000 lbf (62.28 kN) thrust with afterburner
J71-A-9
Powered the Douglas RB-66 Destroyer
J71-A-11
10,200 lbf (45.37 kN) thrust
J71-A-13

Specifications (Allison J71-A-2)

Data from Aircraft engines of the World 1957[3]

General characteristics

  • Type: afterburning turbojet
  • Length: 284.5 in (7,230 mm)
  • Diameter: 39.5 in (1,000 mm)
  • Frontal area: 8.5 sq ft (0.79 m2)
  • Dry weight: 4,890 lb (2,220 kg)

Components

  • Compressor: 16-stage axial compressor
  • Combustors: cannular with 10 flame tubes
  • Turbine: 3-stage axial
  • Fuel type: JP-4 / aviation kerosene
  • Oil system: pressure spray with scavenge at 10–60 psi (69–414 kPa)

Performance

  • Maximum thrust: take-off, dry 10,000 lbf (44,000 N); take-off, wet 14,000 lbf (62.28 kN)
  • Overall pressure ratio: 8.0:1
  • Air mass flow: 160 lb/s (73 kg/s) at 6,100 rpm (static)
  • Specific fuel consumption: 1.8 lb/(lbf⋅h) (51 g/(kN⋅s)) with afterburner (wet)
  • Thrust-to-weight ratio: 2.857
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See also

Related development

Related lists

References
  1. Gunston, Bill (1989). World Encyclopaedia of Aero Engines (2nd ed.). Cambridge, England: Patrick Stephens Limited. p. 11. ISBN 978-1-85260-163-8.
  2. Wilkinson, Paul H. (1953). Aircraft engines of the World 1953 (11th ed.). London: Sir Isaac Pitman & Sons Ltd. pp. 64–65.
  3. Wilkinson, Paul H. (1957). Aircraft engines of the World 1957 (15th ed.). London: Sir Isaac Pitman & Sons Ltd. pp. 74–75.

Further reading
  • Kay, Anthony L. (2007). Turbojet History and Development 1930-1960 Volume 2:USSR, USA, Japan, France, Canada, Sweden, Switzerland, Italy and Hungary (1st ed.). Ramsbury: The Crowood Press. ISBN 978-1861269393.
  • "Aero Engines 1957". Flight and Aircraft Engineer. 72 (2531): 111–143. 26 July 1957. Retrieved 16 March 2019.
  • "J71 Allison's Big Axial Turbojet". Flight and Aircraft Engineer. 67 (2418): 733. 27 May 1955. Retrieved 16 March 2019.
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