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 a thrust of 7,400 lbf (32.92 kN).
Like the J33, the design of the J35 originated at General Electric, but major production was by the Allison Engine Company.
Operational history
The General Electric J35 first flew in the Republic XP-84 Thunderjet in 1946. Late in 1947, complete responsibility for the development and production of the engine was transferred to the Allison Division of the General Motors Corporation and some J35s were also 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 Douglas XB-43 Jetmaster, North American XB-45 Tornado, Convair XB-46, Boeing XB-47 Stratojet, Martin XB-48, and Northrop YB-49. It is probably best known, however, as the engine used in two of the leading fighters of the United States Air Force (USAF) in the 1950s; the Republic F-84 Thunderjet and the Northrop F-89 Scorpion.
A largely redesigned development of the J35 was later produced as the Allison J71, developing 10,900 lbf (48.49 kN) thrust.
Variants
- J35-GE-2
- 3,820 lbf (16.99 kN) thrust, prototypes built by General Electric.
- J35-GE-7
- 3,745 lbf (16.66 kN) thrust, built by General Electric, powered the 2 Republic XP-84 Thunderjet prototypes
- J35-GE-15
- 4,000 lbf (17.79 kN) thrust, built by General Electric, powered the sole Republic XP-84A Thunderjet
- J35-A-3
- 4,000 lbf (17.79 kN) thrust
- J35-C-3
- 3,820 lbf (16.99 kN) thrust, production by Chevrolet.
- J35-C-3
- 4,000 lbf (17.79 kN) thrust, production by Chevrolet.
- J35-A-5
- 4,000 lbf (17.79 kN) thrust
- J35-A-9
- 4,000 lbf (17.79 kN) thrust
- J35-A-11
- 6,000 lbf (26.69 kN) thrust
- J35-A-13
- 5,200 lbf (23.13 kN) thrust
- J35-A-13C
- J35-A-15
- 4,000 lbf (17.79 kN) thrust, powered the 15 Republic YP-84 Thunderjets
- J35-A-15C
- 4,000 lbf (17.79 kN) thrust
- J35-A-17
- 4,900 lbf (21.80 kN) thrust
- J35-A-17D
- 5,000 lbf (22.24 kN) thrust
- J35-A-19
- 5,000 lbf (22.24 kN) thrust
- J35-A-21
- 5,600 lbf (24.91 kN) thrust, 7,400 lbf (32.92 kN) with afterburner
- J35-A-23
- 10,900 lbf (48.49 kN) thrust, original designation for the Allison J71
- J35-A-29
- 5,560 lbf (24.73 kN) thrust
- J35-A-35
- 7,200 lbf (32.03 kN) with afterburner
- J35-A-33
- 5,600 lbf (24.91 kN) thrust, 7,400 lbf (32.92 kN) with afterburner
- J35-A-35
- 5,440 lbf (24.20 kN) thrust, 7,200 lbf (32.03 kN) with afterburner
Applications
Specifications (J35-A-35)
Allison J35 (GE), 1947 (National Naval Aviation Museum, Pensacola, FL).
Cutaway of J35 fuel atomizer
Data from [2]
General characteristics
- Type: Afterburning turbojet
- Length: 195.5 in (4,970 mm) including afterburner
- Diameter: 43 in (1,100 mm)
- Dry weight: 2,315 lb (1,050 kg) dry, 2,930 lb (1,330 kg) including afterburner
Components
- Compressor: 11-stage axial compressor
- Combustors: Eight tubular inter-connected combustion chambers
- Turbine: Single-stage axial
- Fuel type: Aviation kerosene, JP-4, MIL-F-5624 or 100/130 octane gasoline
- Oil system: Dry sump pressure system with spur gear pressure and scavenge pumps at 35 psi (241.32 kPa)
Performance
See also
- Related development
- Comparable engines
- Related lists
References
- Notes
- ↑
- ↑ Bridgman, Leonard (1955). Jane's all the World's Aircraft 1955-56. London: Jane's all the World's Aircraft Publishing Co. Ltd.
- Bibliography
- 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.
External links
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