Westinghouse J30
American pioneering jet aircraft engine
From Wikipedia, the free encyclopedia
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]
| J30 | |
|---|---|
| |
| Type | Turbojet |
| National origin | United States |
| Manufacturer | Westinghouse Aviation Gas Turbine Division |
| First run | 19 March 1943 |
| Major applications | FH Phantom |
| Developed into | |
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
Thrust given in foot-pounds (lbf) and kilonewtons (kN).
- 19A
- Prototypes and initial production, boost engines[citation needed]
- 19B
- 1,400 lbf (6.23 kN) at 18,000 rpm at sea level. Increased mass flow version, 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
- 1,600 lbf (7.1 kN) production engine. 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/s (12.02 kg/s) at 17,000 rpm, 19B 30 lb/s (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
See also
Related development
Comparable engines
Related lists
