General Electric YJ93: Difference between revisions
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* [[North American XF-108 Rapier]] (intended) |
* [[North American XF-108 Rapier]] (intended) |
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==Specifications ( |
==Specifications (J93-GE-3)== |
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{{jetspecs |
{{jetspecs |
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|ref=Aircraft engines of the World 1966/77<ref name=AEotW66-67>{{cite book |last=Wilkinson |first=Paul H. |title=Aircraft engines of the World 1966/77 |year=1966 |publisher=Sir Isaac Pitman & Sons Ltd. |location=London |edition=21st|page=83}}</ref>, Military Turbojet/Turbofan Specifications<ref name="turbo">{{cite web|title=Military Turbojet/Turbofan Specifications|url=http://www.jet-engine.net/miltfspec.html|website=www.jet-engine.net|accessdate=31 December 2017}}</ref>, North American XB-70A Valkyrie<ref name="Jenkins_Landis">{{cite book|last1=Jenkins|first1=Dennis R.|last2=Landis|first2=Tony|title=North American XB-70A Valkyrie|date=2002|publisher=Specialty Press Publishers and Wholesalers|location=North Branch [USA]|isbn=1-58007-056-6}}</ref> |
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|ref={{citation needed|date=March 2015}} |
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|type=[[Turbojet]] |
|type=[[Turbojet]] with afterburner |
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|length= |
|length={{cvt|237|in}} |
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|diameter= |
|diameter={{cvt|52.5|in}} |
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|weight= |
|weight={{cvt|5000|lb}} |
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|compressor=11-stage [[Axial compressor|axial]] |
|compressor=11-stage [[Axial compressor|axial]] |
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|combustion= |
|combustion=Annular with 36 dual fuel nozzles |
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|turbine=Two-stage axial |
|turbine=Two-stage axial |
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|fueltype=Special high-temperature JP-6 Fuel |
|fueltype=Special high-temperature [[JP-6]] Fuel to MIL-F-25656 |
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|oilsystem= |
|oilsystem=Return oil spray system at {{cvt|60|psi}} |
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|power= |
|power= |
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|thrust={{cvt|22000|lbf|kN}} dry; {{cvt|30000|lbf|kN}} with afterburner |
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|thrust={{convert|19000|lbf|kN|abbr=on}}<ref name="Jenkins_Landis">Jenkins, Dennis R. and Tony R. Landis. ''North American XB-70A Valkyrie'' WarbirdTech Volume 34. North Branch, Minnesota: Specialty Press, 2002. {{ISBN|1-58007-056-6}}.</ref> ({{convert|28800|lbf|kN|abbr=on}} with afterburner)<ref name="Jenkins_Landis"/> |
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|compression= |
|compression= |
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|aircon={{ |
|aircon={{cvt|275|lb/s|kg/s}} |
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|turbinetemp= |
|turbinetemp={{cvt|1149|C|F K}} |
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|fuelcon= |
|fuelcon= |
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|specfuelcon={{ |
|specfuelcon={{cvt|0.700|tsfc}} dry; {{convert|1.800|tsfc|abbr=on}} wet |
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|power/weight= |
|power/weight= |
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|thrust/weight= |
|thrust/weight=6 lbf/lb (0.129 kN/kg) with afterburner |
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}} |
}} |
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Revision as of 00:20, 1 January 2018
| YJ93 | |
|---|---|
| |
| YJ93-GE-3 engine at National Museum of the United States Air Force | |
| Type | Turbojet |
| National origin | United States |
| Manufacturer | General Electric Aircraft Engines |
| Major applications | North American XB-70 Valkyrie |
| Developed into | General Electric GE4 |
The General Electric YJ93 turbojet engine was designed as the powerplant for both the North American XB-70 Valkyrie bomber and the North American XF-108 Rapier interceptor. The YJ93 was a single-shaft axial-flow turbojet with a variable-stator compressor and a fully variable convergent/divergent exhaust nozzle. The maximum sea-level thrust was 28,800 lbf (128 kN).[1]
Design and development
The YJ93 started life as the General Electric X275, an enlarged version of the General Electric J79 turbojet. This evolved to the X279 when Mach 3 cruise became a requirement, and ultimately became the YJ93.[2]
The engine used a special high-temperature JP-6 fuel. The six YJ93 engines in the XB-70 Valkyrie were capable of producing a thrust to weight ratio of 5:1 allowing for a speed of 2,000 mph (3,200 km/h) (approximately Mach 3) at an altitude of 70,000 feet (21,000 m).[3]
The XF-108 interceptor was cancelled outright and the B-70 project was reoriented to a research project only.[4]
Applications
- Convair NB-58A Hustler (testbed)
- North American XB-70 Valkyrie
- North American XF-108 Rapier (intended)
Specifications (J93-GE-3)
Data from Aircraft engines of the World 1966/77[5], Military Turbojet/Turbofan Specifications[6], North American XB-70A Valkyrie[1]
General characteristics
- Type: Turbojet with afterburner
- Length: 237 in (6,000 mm)
- Diameter: 52.5 in (1,330 mm)
- Dry weight: 5,000 lb (2,300 kg)
Components
- Compressor: 11-stage axial
- Combustors: Annular with 36 dual fuel nozzles
- Turbine: Two-stage axial
- Fuel type: Special high-temperature JP-6 Fuel to MIL-F-25656
- Oil system: Return oil spray system at 60 psi (410 kPa)
Performance
- Maximum thrust: 22,000 lbf (98 kN) dry; 30,000 lbf (130 kN) with afterburner
- Air mass flow: 275 lb/s (125 kg/s)
- Turbine inlet temperature: 1,149 °C (2,100 °F; 1,422 K)
- Specific fuel consumption: 0.700 lb/(lbf⋅h) (19.8 g/(kN⋅s)) dry; 1.800 lb/(lbf⋅h) (51.0 g/(kN⋅s)) wet
- Thrust-to-weight ratio: 6 lbf/lb (0.129 kN/kg) with afterburner
See also
Related development
Comparable engines
Related lists
References
Wikimedia Commons has media related to General Electric YJ93.
- ^ a b Jenkins, Dennis R.; Landis, Tony (2002). North American XB-70A Valkyrie. North Branch [USA]: Specialty Press Publishers and Wholesalers. ISBN 1-58007-056-6.
- ^ Jenkins, Dennis R. and Tony R. Landis. Valkyrie: North American's Mach 3 Superbomber. North Branch, Minnesota: Specialty Press, 2005. ISBN 1-58007-072-8.
- ^ National Museum of the USAF Retrieved: December 21, 2016
- ^ NB-58A Testbed for General Electric J93 Archived 2008-07-24 at the Wayback Machine
- ^ Wilkinson, Paul H. (1966). Aircraft engines of the World 1966/77 (21st ed.). London: Sir Isaac Pitman & Sons Ltd. p. 83.
- ^ "Military Turbojet/Turbofan Specifications". www.jet-engine.net. Retrieved 31 December 2017.