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).
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, boost engines
Increased mass flow version delivering 1,400 lbf (6.23 kN) at 18,000 rpm at sea level, added gearbox to allow engine to be a prime driver
Company designation for WE-20.
1,600 lbf (7.1 kN) for
Northrop X-4 XJ30-WE-8
J43  XJ30-WE-9
1,600 lbf (7.1 kN) for
Northrop X-4 J30-WE-20
production engines delivering 1,600 lbf (7.1 kN) thrust, Internal model 19XB-2B 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⋅h) (38 g/(kN⋅s)), Specific fuel consumption: 19B 1.28 lb/(lbf⋅h) (36 g/(kN⋅s))
1.639, Thrust-to-weight ratio: 19B 1.724
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
^ 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
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, USA: Bleeg Publishing, LLC. pp. 360–361.
Wikimedia Commons has media related to Westinghouse J30.
Minijets website Westinghouse 19