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

• Convair XF-92
• McDonnell FH Phantom
• Northrop XP-79
• Northrop X-4 Bantam

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