Westinghouse J30
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| J30 | |
|---|---|
| Script error: No such module "InfoboxImage". | |
| Type | Turbojet |
| National origin | United States |
| Manufacturer | Westinghouse Aviation Gas Turbine Division |
| First run | 19 March 1943 |
| Major applications | FH Phantom |
| Developed into | Westinghouse J32 Westinghouse J34 |
The Westinghouse J30, initially known as the Westinghouse 19XB, was a turbojet engine developed by Westinghouse Electric Corporation. It was the first American-designed turbojet to run, and only the second axial-flow turbojet to run outside Germany (after the British Metropolitan-Vickers F.2).[1]
A simple and robust unit with six-stage compressor, annular combustor, and single-stage turbine, it initially gave 1,200 pounds of thrust but improved to 1,600 in production versions. Its first flight was under a FG Corsair in January 1944. It was developed into the smaller J32, and the successful Westinghouse J34, an enlarged version which produced 3,000 pounds of thrust.
Variants
- 19A
- Prototypes and initial production, boost enginesScript error: No such module "Unsubst".
- 19B
- Increased mass flow version delivering Script error: No such module "convert". at 18,000 rpm at sea level, added gearbox to allow engine to be a prime driverScript error: No such module "Unsubst".
- 19XB-2B
- Company designation for WE-20.[2]
- XJ30-WE-7
- Script error: No such module "convert". for Northrop X-4Script error: No such module "Unsubst".
- XJ30-WE-8
- originally designated J43[3]
- XJ30-WE-9
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- J30-WE-20
- production engines delivering Script error: No such module "convert". thrust, Internal model 19XB-2BScript error: No such module "Unsubst".
Applications
Specifications (Westinghouse 19A)
Data from [4]
General characteristics
- Type: Axial flow turbojet
- Length: Script error: No such module "convert"., 19B Script error: No such module "convert".
- Diameter: Script error: No such module "convert".
- Dry weight: Script error: No such module "convert"., 19B Script error: No such module "convert".
Components
- Compressor: 6-stage axial
- Combustors: Annular stainless steel
- Turbine: Single-stage axial
- Fuel type: 100/130 gasoline
- Oil system: pressure spray at Script error: No such module "convert". dry sump, 60 S.U. secs (10.2 cSt) (AN-0-6A) grade oil
Performance
- Maximum thrust: Script error: No such module "convert". at 18,000 rpm at sea level, 19B Script error: No such module "convert". at 18,000 rpm at sea level
- Overall pressure ratio: 3:1
- Air mass flow: Script error: No such module "convert". at 17,000 rpm, 19B Script error: No such module "convert". at 18,000 rpm
- Turbine inlet temperature: Script error: No such module "convert".
- Specific fuel consumption: Script error: No such module "convert"., 19B Script error: No such module "convert".
- Thrust-to-weight ratio: 1.639, 19B 1.724
- Normal thrust, static: Script error: No such module "convert". at 18,000 rpm at sea level, 19B Script error: No such module "convert". at 17,000 rpm at sea level
- Military thrust, flight: Script error: No such module "convert". at 17,200 rpm at altitude, 19B Script error: No such module "convert". at 18,000 rpm at altitude
- Normal thrust, flight: Script error: No such module "convert". at 16,260 rpm at altitude, 19B Script error: No such module "convert". at 17,000 rpm at altitude
See also
Related development
Comparable engines
Related lists
Notes
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References
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External links
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