American pioneering jet aircraft engine
TheWestinghouse J30 , initially known as theWestinghouse 19XB , was aturbojet engine developed byWestinghouse Electric Corporation . It was the first American-designed turbojet to run, and only the secondaxial-flow turbojet to run outside Germany (after the BritishMetropolitan-Vickers F.2 ).[ 1]
A simple and robust unit with six-stage compressor, annular combustor, and single-stage turbine, it initially gave 1,200pounds of thrust but improved to 1,600 in production versions. Its first flight was under aFG Corsair in January 1944. It was developed into the smallerJ32 , and the successfulWestinghouse J34 , an enlarged version which produced 3,000 pounds of thrust.
Thrust given infoot-pounds (lbf) andkilonewtons (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) forNorthrop X-4 [citation needed XJ30-WE-8 originally designatedJ43 [ 3] XJ30-WE-9 1,600 lbf (7.1 kN) forNorthrop X-4 [citation needed J30-WE-20 1,600 lbf (7.1 kN) production engine. Internal model 19XB-2B[citation needed [ edit ] Data from [ 4]
General characteristics Type: Axial flowturbojet 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 steelTurbine : Single-stage axialFuel type: 100/130 gasoline Oil system: pressure spray at 40 psi (275.8 kPa) dry sump, 60S.U. secs (10.2 cSt) (AN-0-6A) grade oil
Performance Maximumthrust : 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 : 3:1Air 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 1.724Normal 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 levelMilitary thrust, flight: 660 lbf (2.94 kN) at 17,200 rpm at altitude,19B 525 lbf (2.34 kN) at 18,000 rpm at altitudeNormal thrust, flight: 570 lbf (2.54 kN) at 16,260 rpm at altitude,19B 465 lbf (2.07 kN) at 17,000 rpm at altitudeRelated development
Comparable engines
Related lists
^ 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. 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.
