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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. 
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.
Prototypes and initial production
Increased mass flow version delivering 1,400 lbf (6.23 kN) at 18,000 rpm at sea level
production engines delivering 1,600 lbf (7.1 kN) thrust
Specifications (Westinghouse 19A)
Data from 
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)
Compressor: 6-stage axial
Combustors: Annular stainless steel
Single-stage axial Turbine:
Fuel type: 100/130 gasoline
Oil system: pressure spray at 40 psi (275.8 kPa) dry sump, 60 S.U. secs (10.2 cSt) (AN-0-6A) grade oil
Maximum 1,360 lbf (6.05 kN) at 18,000 rpm at sea level, thrust: 19B 1,400 lbf (6.23 kN) at 18,000 rpm at sea level
3:1 Overall pressure ratio:
Air mass flow: 26.5 lb (12.02 kg) /s at 17,000 rpm, 19B 30 lb (13.61 kg) /s at 18,000 rpm
Turbine inlet temperature: 1,500 °F (816 °C)
1.35 lb/(lbf hr) (137.6 kg/(kN h)), Specific fuel consumption: 19B 1.28 lb/(lbf hr) (130.48 kg/(kN h))
1.639 lbf/lb (0.016 kN/kg), Thrust-to-weight ratio: 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
^ Gunston, p. 241-240
^ Wilkinson, Paul H. (1946). Aircraft Engines of the world 1946. London: Sir Isaac Pitman & Sons. pp. 278–281.
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.