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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.^{[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.

- 19A
- Prototypes and initial production
- 19B
- Increased mass flow version delivering 1,400 lbf (6.23 kN) at 18,000 rpm at sea level
- J30-WE-20
- production engines delivering 1,600 lbf (7.1 kN) thrust

*Data from* ^{[2]}

**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**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

**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 hr) (137.6 kg/(kN h)),**19B**1.28 lb/(lbf hr) (130.48 kg/(kN h))**Thrust-to-weight ratio:**1.639 lbf/lb (0.016 kN/kg),**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

- Related development

- Comparable engines

- Related lists

- 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.

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