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Allison J33

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This page is a soft redirect.Allison J33-A-35 Turbojet Engine #REDIRECTmw:Help:Magic words#Other
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J33
Type

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This page is a soft redirect. Turbojet #REDIRECTmw:Help:Magic words#Other
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Manufacturer

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This page is a soft redirect. General Electric
Allison Engine Company #REDIRECTmw:Help:Magic words#Other
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First run

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This page is a soft redirect. 1942 #REDIRECTmw:Help:Magic words#Other
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Major applications

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This page is a soft redirect. Lockheed P-80 Shooting Star
Lockheed T-33 Shooting Star
Lockheed F-94A/B Starfire
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Developed from

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This page is a soft redirect. General Electric J31 #REDIRECTmw:Help:Magic words#Other
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The General Electric/Allison J33 was a development of the General Electric J31, enlarged to produce significantly greater thrust, starting at Script error: No such module "convert". and ending at Script error: No such module "convert". with an additional low-altitude boost to Script error: No such module "convert". with water-alcohol injection.

Development

The J33 was originally developed by General Electric as a follow-on to their work with the designs of Frank Whittle during World War II. Their first engine was known as the I-A, but after major changes to adapt it to US production and to increase thrust, it started limited production as the I-16 in 1942, the 16 referring to its Script error: No such module "convert". thrust. Full production started as the J31 when the United States Army Air Forces introduced common naming for all their engine projects.

Along with the I-16, GE also started work on an enlarged version, known as the I-40. As the name implied, the engine was designed to provide Script error: No such module "convert".. The development cycle was remarkably rapid. Design work started in mid-1943 and the first prototype underwent static testing on January 13, 1944.

Lockheed was in the midst of the XP-80 project at the time, originally intending to power their design with a US-produced version of the Halford H-1 of about Script error: No such module "convert".. Production of the H-1 ran into delays, and since the I-40 would dramatically improve performance, plans were made to fit the prototypes with the I-40 instead.

The I-40 became important to the USAAF's plans when the I-16 powered P-59 was skipped over in favor of the I-40 powered P-80 as the US's first production jet fighter. In 1945 the license to actually produce the engine was not given to General Electric, but Allison instead. Allison, working largely from government-owned wartime factories, could produce the engine in quantity more quickly and cheaply.

By the time the production lines were shut down Allison had built over 6,600 J33's, and General Electric another 300 (mostly the early runs).

In 1958, surplus J33s were used in jet donkeys pushing dead loads at 200 knots to test aircraft carrier arresting gear cables and tailhooks at Lakehurst.[1]

Variants

J33-A-14
A short life engine powering the Chance-Vought Regulus, Script error: No such module "convert". thrust.
J33-A-16A
Powering the Grumman F9F-7, Script error: No such module "convert". thrust.
J33-A-18A
A short life engine powering the Chance-Vought Regulus.
J33-A-21
Script error: No such module "convert". thrust.
J33-A-22
Powering the Lockheed T2V-1 with bleed air for boundary-layer control.
J33-A-23
Script error: No such module "convert". thrust.
J33-A-24
Script error: No such module "convert". thrust, powers the Lockheed T2V.
J33-A-24A
Script error: No such module "convert". thrust, powers the Lockheed T2V.
J33-A-33
Script error: No such module "convert". re-heat thrust.
J33-A-35
Script error: No such module "convert". thrust / Script error: No such module "convert". with water-alcohol injection, powers the Lockheed T2V and Lockheed T-33.
J33-A-37
A short life engine powering the Martin Matador, Script error: No such module "convert". thrust..

Applications

Specifications (Allison J33-A-35)

Data from [2]

General characteristics

  • Type: Centrifugal compressor turbojet
  • Length: Script error: No such module "convert".
  • Diameter: Script error: No such module "convert".
  • Dry weight: Script error: No such module "convert".

Components

  • Compressor: single-stage double-sided centrifugal compressor
  • Combustors: 14 can type stainless steel combustion chambers
  • Turbine: Single-stage axial
  • Fuel type: Kerosene (AN-F-32) or 100/130 gasoline
  • Oil system: Wet sump, pressure spray at Script error: No such module "convert".

Performance

  • Maximum thrust: Script error: No such module "convert". at 11,500 rpm at sea level for take-off
Normal thrust, static: Script error: No such module "convert". at 11,000 rpm at sea level

See also

Related development

Comparable engines
Related lists

References

Notes
  1. ^ Dempewolff, Richard F. (June 1958). "Jet "Donkeys" for the Jets". Popular Mechanics. pp. 72–75. Retrieved 25 October 2012. 
  2. ^ Bridgman, Leonard (1955). Jane's all the World's Aircraft 1955-56. London: Jane's all the World's Aircraft Publishing Co. Ltd. 
Bibliography
  • Gunston, Bill. World Encyclopedia of Aero Engines. Cambridge, England. Patrick Stephens Limited, 1989. ISBN 1-85260-163-9
  • 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. 
  • Wilkinson, Paul H. (1946). Aircraft Engines of the world 1946. London: Sir Isaac Pitman & Sons. pp. 272–273. 
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External links

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