General Electric J73
| J73 | |
|---|---|
| |
| Cutaway of a J73 at the NMUSAF | |
| Type | Turbojet |
| National origin | United States |
| Manufacturer | General Electric
|
| Major applications | North American F-86H Sabre
|
| Number built | 870 |
| Developed from | General Electric J47 |
| Developed into | General Electric J79 |
The General Electric J73
Design and development
An engine, uprated from the J47, was required for the F-86H. The mass flow was increased by relocating
The pressure ratio was increased and variable inlet guide vanes fitted to prevent low-RPM problems (rotating stall/blade flutter) with the higher design pressure ratio. A 2-stage turbine was required.[2][3]
A low boost (10% at take-off) afterburner was fitted. It was known as a tailpipe augmentation (TPA) system.[3]
Nuclear powered
Four J73 engines were converted to produce thrust using nuclear energy instead of jet fuel. Testing was done in 1957 at the Atomic Energy Commission's National Reactor testing station. The engines were modified to pass the compressor air through a heat exchanger, in which heat was transferred from a nuclear reactor, before entering the compressor turbine at 1,400 degrees F.[4]
Variants
- J73-GE-1
- J73-GE-3
- 9,200 lbf (40.92 kN) for the North American F-86H Sabre.
- J73-GE-5
- Variant intended for a proposed Advanced F-89.[5]
Applications
- North American F-86H Sabre
- Republic YF-84J Thunderstreak, two prototypes
Specifications (J73-GE-3)
Data from Flight 9 April 1954 : Aero Engines 1954,[6] Aircraft engines of the World 1953[7]
General characteristics
- Type: non-afterburning turbojet
- J73-GE-5 with afterburning
- Length: 200 in (5,080 mm)
- Diameter: 39.5 in (1,003 mm)
- Dry weight: 3,600 lb (1,630 kg)
Components
- Compressor: 12 stage, axial flow, variable inlet guide vanes
- Combustors: 10 cannular combustion chambers
- Turbine: 2 stage axial turbine
- Fuel type: MIL-F-5624A / JP-4
- Oil system: dry sump, pressure spray with gear pumps
Performance
- Maximum thrust: 9,000 lbf (40 kN)
- J73-GE-5 - 9,500 lbf (42 kN) dry, 12,500 lbf (56 kN) with afterburner
- Overall pressure ratio: 7.5:1
- Air mass flow: 155 lb/s (70 kg/s)
- Specific fuel consumption: 0.9 lb/(lbf⋅h) or 25 g/(kN⋅s)
- Thrust-to-weight ratio: 2.5
- J73-GE-5 - 2.64 dry, 3.47 with afterburner
See also
Related development
Comparable engines
Related lists
References
- ^ "Aero Engines 1957". Flight: 133. 26 July 1957.
- ^ Johnsen, Irving A.; Bullock, Robert 0. (1965). NASA SP-36 : AERODYNAMIC DESIGN OF AXIAL-FLOW COMPRESSORS (PDF). Washington D.C.: NASA. pp. 27a, 44. Archived from the original (PDF) on 20 July 2018. Retrieved 24 February 2019.
{{cite book}}: CS1 maint: numeric names: authors list (link) - ^ ISBN 9780816883554.
- ^ https://archive.org/details/Aviation_Week_1957-03-18/page/n13/mode/2up, p.27
- ^ "Standard Aircraft Characteristics: Advanced F-89" (PDF). US Air Force. 3 December 1951. Retrieved 30 December 2018.
- ^ "Aero Engines 1954 : The World's Leading Aero-engine Constructors and their Products Reviewed". 9 April 1954: 457. Retrieved 24 February 2019.
{{cite journal}}: Cite journal requires|journal=(help) - ^ Wilkinson, Paul H. (1953). Aircraft engines of the World 1953 (11th ed.). London: Sir Isaac Pitman & Sons Ltd. pp. 82–83.
Further reading
- 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 1930֪–1960 Volume 2:USSR, USA, Japan, France, Canada, Sweden, Switzerland, Italy and Hungary (1st ed.). Ramsbury: The Crowood Press. ISBN 978-1861269393.
External links
