From Wikipedia, the free encyclopedia
American pioneering jet aircraft engine
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
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]
- 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
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]
Specifications (Westinghouse 19A)
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]
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
See also
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]
Related development
Comparable engines
Related lists
Notes
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]
- ^
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
[
edit
]
- 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.
External links
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]