Westinghouse J30
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 of Germany.[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
- 19B
- Increased mass flow version delivering 1,400 lbf (6.23 kN) at 18,000 rpm at sea level
- J30-WE-20
- production engines delivering 1,600 lbf (7.1 kN) thrust
Applications
Specifications (Westinghouse 19A)
Data from [2]
General characteristics
- Type: Axial flow turbojet
- Length: 100 in (2,540.0 mm), 19B 104.5 in (2,654.3 mm)
- Diameter: 19 in (482.6 mm)
- Dry weight: 830 lb (376.5 kg), 19B 809 lb (367.0 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 (275.8 kPa) dry sump, 60 S.U. secs (10.2 cs) (AN-0-6A) grade oil
Performance
- Maximum thrust: 1,360 lbf (6.05 kN) at 18,000 rpm at sea level, 19B 1,400 lbf (6.23 kN) at 18,000 rpm at sea level
- Overall pressure ratio: 3:1
- Air mass flow: 26.5 lb (12.02 kg) /sec at 17,000 rpm, 19B 30 lb (13.61 kg) /sec at 18,000 rpm
- Turbine inlet temperature: 1,500 °F (816 °C)
- Specific fuel consumption: 1.35 lb/lbf/hr (137.6 kg/kN/hr), 19B 1.28 lb/lbf/hr (130.48 kg/kN/hr)
- Thrust-to-weight ratio: 1.639 lbf/lb (0.016 kN/kg), 19B 1.724 lbf/lb (0.0169 kN/kg)
- Normal thrust, static: 1,160 lbf (5.16 kN) at 18,000 rpm at sea level, 19B 1,170 lbf (5.20 kN) at 17,000 rpm at sea level
- Military thrust, flight: 660 lbf (2.94 kN) at 17,200 rpm at altitude, 19B 525 lbf (2.34 kN) at 18,000 rpm at altitude
- Normal thrust, flight: 570 lbf (2.54 kN) at 16,260 rpm at altitude, 19B 465 lbf (2.07 kN) at 17,000 rpm at altitude
See also
- Related development
- Comparable engines
- Related lists
Notes
- ↑ Gunston, p. 241-240
- ↑ Wilkinson, Paul H. (1946). Aircraft Engines of the world 1946. London: Sir Isaac Pitman & Sons. pp. 278–281.
References
- 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.
External links
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