Allison J35

Allison J35

The Allison J35 was originally developed by the General Electric Company in parallel with the Whittle-based centrifugal-flow J33, and was the USAF's first axial-flow (straight-through airflow) compressor engine. The J35 was fairly simple, consisting of an eleven-stage axial-flow compressor and a single-stage turbine. With the afterburner, which most models carried, it produced 7,400 lbf.

Operational History

The J35 first flew in the XP-84 in 1946. Late in 1947, complete responsibility for the production of the engine was transferred to the Allison Division of the General Motors Corporation. Some J35s were built by GM's Chevrolet division. [http://www.vectorsite.net/avf86_1.html] More than 14,000 J35s had been built by the time production ended in 1955.

The J35 was used to power the Bell X-5 variable-sweep research aircraft and various prototypes such as the XB-43 Jetmaster, XB-45 Tornado, Convair XB-46, XB-47 Stratojet, Martin XB-48, and Northrop YB-49. It is probably best known, however, as the engine used in two of the USAF's leading fighters of the 1950s, the F-84 Thunderjet and the F-89 Scorpion.

A larger development of the engine was later produced as the Allison J71, producing around 10,000 lbf.

Variants

*J35-A-11: 6,000 lbf (27 kN) thrust
*J35-A-15C: 4,000 lbf (18 kN) thrust
*J35-A-17: 4,900 lbf (22 kN)
*J35-A-35: 7,200 lbf (32 kN) afterburning thrust

pecifications (J35-A-35A)

jetspecs

type=Afterburning turbojet
length=
diameter=
weight=2,850 lb (1,293 kg) including afterburner
compressor=11-stage axial compressor
combustion=
turbine=Single-stage
fueltype=
oilsystem=
power=
thrust=
*5,600 lbf (25 kN) at 8,000 rpm
*7,400 lbf (33 kN) with afterburner
compression=
fuelcon=
specfuelcon=
power/weight=
thrust/weight=2.60 (25.5 N/kg)

  • Maximum operating altitude: 50,000 ft (15,000 m)
  • Cost: US$46,000

    External links

    * [http://www.shanaberger.com/engines/J35.htm Allison J35 Turbojet]


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