Allison J35
The General Electric/Allison J35 was originally developed by General Electric (GE company designation TG-180) in parallel with the Whittle-based centrifugal-flow J33, and was the United States Air Force'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.
Like the J33, the design of the J35 originated at General Electric, but major production was by Allison.
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.[1] 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-GE-2 3,820 lb (17 kN) thrust
- J35-A-3: 4,000 lb (17.8 kN) thrust
- J35-C-3: 3,820 lb (17. kN) thrust
- J35-C-3: 4,000 lb (17.8 kN) thrust
- J35-A-5: 4,000 lb (17 kN) thrust
- J35-A-9: 4,000 lb (17.8 kN) thrust
- J35-A-11: 6,000 lb (26.7 kN) thrust
- J35-A-13: 5,200 lb (25 kN) thrust
- J35-A-15: 4,000 lb (17.7 kN) thrust
- J35-A-15C: 4,000 lb (17.7 kN) thrust
- J35-A-17: 4,900 lb (21.8 kN) thrust
- J35-A-17D: 5,000 lb (22.2 kN) thrust
- J35-A-19: 5,000 lb (22.2 kN) thrust
- J35-A-21: 5,600 lb (25 kN) thrust, 7,400 lbf (32.0 kN) with afterburner
- J35-A-23: 10,090 lb (45 kN) thrust
- J35-A-29: 5,600 lb (24.9 kN) thrust
- J35-A-35: 7,200 lb (32.0 kN) with afterburner
- J35-A-33: 5,600 lb (25.0 kN) thrust, 7,400 lb (32 kN) with afterburner
- J35-A-35: 5,440 lb (24.26 kN) thrust, 7,200 lb (32.11 kN) with afterburner
Applications
Specifications (J35-A-35A)
General characteristics
- Type: Afterburning turbojet
- Length:
- Diameter:
- Dry weight: 2,850 lb (1,293 kg) including afterburner
Components
Performance
See also
- Related development
- Comparable engines
- Related lists
References
External links
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