Westinghouse J30

J30
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 engines^{[citation needed]}
19B: 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^{[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: production engines delivering 1,600 lbf (7.1 kN) thrust, Internal model 19XB-2B^{[citation needed]}

Applications

Specifications (Westinghouse 19A)

Data from ^[4]

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 cSt) (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) /s at 17,000 rpm, 19B 30 lb (13.61 kg) /s at 18,000 rpm
Turbine inlet temperature: 1,500 °F (816 °C)
Specific fuel consumption: 1.35 lb/(lbf⋅h) (38 g/(kN⋅s)), 19B 1.28 lb/(lbf⋅h) (36 g/(kN⋅s))
Thrust-to-weight ratio: 1.639, 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

Notes

^ 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: Bleeg Publishing. pp. 360–361.