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]
| J30 | |
|---|---|
 | |
| Type | Turbojet |
| National origin | United States |
| Manufacturer | Westinghouse Aviation Gas Turbine Division |
| First run | 19 March 1943 |
| Major applications | FH Phantom |
| Developed into | |
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
editThrust given in foot-pounds (lbf) and kilonewtons (kN).
- 19A
- Prototypes and initial production, boost engines[citation needed]
- 19B
- 1,400 lbf (6.23 kN) at 18,000 rpm at sea level. Increased mass flow version, added gearbox to allow engine to be a prime driver[citation needed]
- 19XB-2B
- Company designation for WE-20.[2]
- XJ30-WE-7
- 1,600 lbf (7.1 kN) for Northrop X-4[citation needed]
- XJ30-WE-8
- originally designated J43[3]
- XJ30-WE-9
- 1,600 lbf (7.1 kN) for Northrop X-4[citation needed]
- J30-WE-20
- 1,600 lbf (7.1 kN) production engine. Internal model 19XB-2B[citation needed]
Applications
editSpecifications (Westinghouse 19A)
editData from Aircraft Engines of the world 1946[4]
General characteristics
- Type: Axial flow turbojet
- Length: 100 in (2,500 mm)
- Diameter: 19 in (480 mm)
- Dry weight: 830 lb (380 kg)
Components
- Compressor: 6-stage axial
- Combustors: Annular stainless steel
- Turbine: Single-stage axial
- Fuel type: 100/130 gasoline
- Oil system: pressure spray at 40 psi (280 kPa) dry sump
Performance
- Maximum thrust: 1,360 lbf (6.0 kN) at 18,000 rpm at sea level
- Overall pressure ratio: 3:1
- Air mass flow: 26.5 lb/s (12.0 kg/s) at 17,000 rpm,
- Turbine inlet temperature: 1,500 °F (820 °C)
- Specific fuel consumption: 1.35 lb/(lbf⋅h) (38 g/(kN⋅s))
- Thrust-to-weight ratio: 1.64
- Normal thrust, static: 1,160 lbf (5.2 kN) at 18,000 rpm at sea level
- Military thrust, flight: 660 lbf (2.9 kN) at 17,200 rpm at altitude
- Normal thrust, flight: 570 lbf (2.5 kN) at 16,260 rpm at altitude
See also
editRelated development
Comparable engines
Related lists
Notes
edit- ↑ Gunston, p. 240-241
- ↑ Wilkinson, Paul H. (1950). Aircraft engines of the World 1950 (11th ed.). London: Sir Isaac Pitman & Sons Ltd. pp. 60–61.
- ↑ "Designations of U.S. Military Aero Engines".
- ↑ Wilkinson, Paul H. (1946). Aircraft Engines of the world 1946. London: Sir Isaac Pitman & Sons. pp. 278–281.
References
edit- Gunston, Bill (2006). World Encyclopedia of Aero Engines, 5th Edition. Phoenix Mill, Gloucestershire, England, UK: Sutton Publishing Limited. pp. 240–241. ISBN 0-7509-4479-X.
- Wilkinson, Paul H. (1946). Aircraft Engines of the world 1946. London: Sir Isaac Pitman & Sons. pp. 278–281.
- Christiansen, Paul J. (2019). Early Westinghouse Axial Turbojets. Olney, Maryland: Bleeg Publishing. pp. 360–361.
External links
edit