| J73 | |
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| Cutaway of a J73 at the NMUSAF |
The General Electric J73 turbojet was developed by General Electric from the earlier J47 engine. Its original USAF designation was J47-21, but the innovative features (variable inlet guide vanes, and single-shell combustor case) led to its redesignation as J73.
Applications[]
Specifications (J73-GE-5)[]
Data from Flight.[1]
- General characteristics
- Type: Turbojet
- Length: 200 in (5 m)
- Diameter: 39.5 in (1 m)
- Dry weight: 3,650 lb (1,656 kg)
- Components
- Compressor: 12 stage, axial flow, variable inlet guide vanes
- Combustors: 10 cannular combustion chambers
- Turbine: 2 stage
- Performance
- Maximum thrust: 9,500 lbf (42 kN) dry, 12,500 lbf (55.6 kN) with afterburner
- Overall pressure ratio: 7.5:1
- Air mass flow: 155 lb/sec (70 kg/s)
- Specific fuel consumption: 0.9 lb/hr/lbf (dry power)
- Thrust-to-weight ratio: 3.4 lbf/lb
See also[]
- General Electric J47
- General Electric J79
- General Electric YJ93
- Armstrong Siddeley Sapphire
- Rolls-Royce Avon
- SNECMA Atar
- Tumansky R-13
- Tumansky R-25
- United States military aero engine designations
References[]
- Notes
- ↑ Flight, 9 April 1954, p.457. Retrieved: 6 February 2009
- Bibliography
- Gunston, Bill (2006). World Encyclopedia of Aero Engines, 5th Edition. Phoenix Mill, Gloucestershire, England, UK: Sutton Publishing Limited. ISBN 0-7509-4479-X.
- 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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The original article can be found at General Electric J73 and the edit history here.