Westinghouse J34: Difference between revisions
→Variants: lb -> lbf |
→Specifications (J34-WE-36): units |
||
| Line 91: | Line 91: | ||
|thrust=3400 lbf (15.12 kN) |
|thrust=3400 lbf (15.12 kN) |
||
|compression= 4.35:1 |
|compression= 4.35:1 |
||
|aircon=50-55 |
|aircon=50-55 lb/s |
||
|turbinetemp= |
|turbinetemp= |
||
|fuelcon= |
|fuelcon= |
||
|specfuelcon=1.04 lb/ |
|specfuelcon=1.04 lb/(h lbf) |
||
|power/weight= |
|power/weight= |
||
|thrust/weight=2.82:1 |
|thrust/weight=2.82:1 |
||
Revision as of 00:14, 29 December 2016
| J34 | |
|---|---|
| |
| J34 on display at the Wright-Patterson Air Force Base Museum | |
| Type | Turbojet |
| National origin | United States |
| Manufacturer | Westinghouse Aviation Gas Turbine Division |
| First run | 11 January 1947 |
| Major applications | F2H Banshee F3D Skyknight P-2 Neptune |
| Developed from | Westinghouse J30 |
| Developed into | Westinghouse J46 |
The Westinghouse J34, company designation Westinghouse 24C, was a turbojet engine developed by Westinghouse Aviation Gas Turbine Division in the late 1940s. Essentially an enlarged version of the earlier Westinghouse J30, the J34 produced 3,000 pounds of thrust, twice as much as the J30. Later models produced as much as 4,900 lbs with the addition of an afterburner. It first flew in 1947. The J46 engine was developed as a larger, more powerful version of Westinghouse's J34 engine, about 50% larger.
Development
Built in an era of rapidly advancing gas turbine engine technology, the J34 was largely obsolete before it saw service, and often served as an interim engine.[1] For instance, the Douglas X-3 "Stiletto" was equipped with two J34 engines when the intended Westinghouse J46 engine proved to be unsuitable. The Stiletto was developed to investigate the design of an aircraft at sustained supersonic speeds. However, equipped with the J34 instead of its intended engines, it was seriously underpowered and could not exceed Mach 1 in level flight.[2]
Developed during the transition from piston-engined aircraft to jets, the J34 was sometimes fitted to aircraft as a supplement to other powerplants, as with the Lockheed P-2 Neptune and Douglas Skyrocket (fitted with radial piston engines and a rocket engine, respectively).
The afterburner was developed by Solar Aircraft, the first U.S. company to produce a practical afterburner.[3]
Variants
- J34-WE-2: 3,000 lbf (13.35 kN) thrust
- XJ34-WE-7: 3,000 lbf (13.35 kN) thrust
- J34-WE-13: 3,000 lbf (13.35 kN) thrust
- J34-WE-15: 3,000 lbf (13.35 kN) thrust
- J34-WE-15: 4,100 lbf (18.24 kN) thrust
- J34-WE-17: 3,370 lbf (14.99 kN) thrust (4,850 lbf (21.57 kN) thrust with afterburner)
- J34-WE-19: 3,250 lbf (14.46 kN) thrust
- J34-WE-22: 3,000 lbf (13.35 kN) thrust[4]
- J34-WE-30: 3,150 lbf (14.01 kN) thrust (4,200 lbf (18.68 kN) thrust with afterburner)[4]
- J34-WE-30A: 3,150 lbf (14.01 kN) thrust (4,200 lbf (18.68 kN) thrust with afterburner)[4]
- J43-WE-32: 3,370 lbf (14.99 kN) thrust (4,900 lbf (21.8 kN) thrust with afterburner)[4]
- J34-WE-34: 3,250 lbf (14.46 kN) thrust[4]
- J34-WE-34A: 3,000 lbf (13.35 kN) thrust
- J34-WE-36: 3,400 lbf (15.12 kN) thrust[4]
- J34-WE-36A: 3,400 lbf (15.12 kN) thrust[4]
- J34-WE-38: 3,800 lbf (16.9 kN) thrust[4]
- J34-WE-40: 3,000 lbf (13.35 kN) thrust
- J34-WE-42: 3,400 lbf (15.12 kN) thrust (4200 lbf (18.68 kN) thrust with afterburner)[4]
- J34-WE-46: 3,400 lbf (15.12 kN) thrust[4]
Applications
- Fairchild C-119 Flying Boxcar (civilian variant modification)
- Convair F2Y Sea Dart
- Curtiss-Wright XF-87 Blackhawk
- Douglas F3D Skyknight
- Douglas Skyrocket
- Douglas X-3 Stiletto
- Lockheed XF-90
- Lockheed P-2E/G/H Neptune
- McDonnell 119/220
- McDonnell F2H Banshee
- McDonnell XF-85 Goblin
- McDonnell XF-88 Voodoo
- Ryan XFR-4 Fireball
- Vought F6U Pirate
- Vought F7U Cutlass
Water speed record application
- Ken Warby's Spirit of Australia jet boat
Jet Truck application
Snow removal
Specifications (J34-WE-36)
Data from [5]
General characteristics
- Type: Turbojet
- Length: 112 in (2.84 m)
- Diameter: 27 in (0.69 m)
- Dry weight: 1207 lb (547.5 kg)
Components
- Compressor: Single-Spool, 11-stage Axial
- Combustors: Annular
- Turbine: 2-stage turbine
Performance
- Maximum thrust: 3400 lbf (15.12 kN)
- Overall pressure ratio: 4.35:1
- Air mass flow: 50-55 lb/s
- Specific fuel consumption: 1.04 lb/(h lbf)
- Thrust-to-weight ratio: 2.82:1
See also
Related development
Comparable engines
Related lists
References
Notes
- ^ "F6U Pirate." globalsecurity.org. Retrieved: 29 May 2015.
- ^ "Douglas X-3 Stiletto," shanaberger.com. Retrieved: 29 May 2015.
- ^ Leyes & Fleming 1999, p. 78.
- ^ a b c d e f g h i j Roux 2007, pp. 217–220.
- ^ Westinghouse Turbojets (1953). Flight. 13 Nov 1953, p. 642.
Bibliography
- Gunston, Bill. World Encyclopedia of Aero Engines, 5th Edition. Phoenix Mill, Gloucestershire, England, UK: Sutton Publishing Limited, 2006. pp. 240–241. ISBN 0-7509-4479-X.
- Kay, Anthony L. Turbojet History and Development 1930-1960 Volume 2: USSR, USA, Japan, France, Canada, Sweden, Switzerland, Italy and Hungary (1st ed.). Ramsbury, UK: The Crowood Press, 2007. ISBN 978-1861269393.
- Leyes, Richard A., II and William A. Fleming. The History of North American Small Gas Turbine Aircraft Engines (Library of Flight). Reston, Virginia: American Institute of Aeronautics and Astronautics, Inc, 1999. ISBN 978-1-56347-332-6.
- Roux, Élodie. Turbofan and Turbojet Engines: Database Handbook. Raleigh, North Carolina: Éditions Élodie Roux, 2007. ISBN 978-2-9529380-1-3.
External links
