Pratt & Whitney J48
| J48 | |
|---|---|
 |
|
| A Pratt & Whitney J48 | |
| Type | Turbojet |
| Manufacturer | Pratt & Whitney |
| Major applications | Grumman F9F Panther Grumman F-9 Cougar Lockheed F-94 Starfire |
| Number built | 4,108 |
| Developed from | Rolls-Royce RB.44 Tay |
The Pratt & Whitney J48 (company designation JT7) is a turbojet engine developed by Pratt & Whitney as a license-built version of the Rolls-Royce Tay. The Tay/J48 was an enlarged development of the Rolls-Royce Nene (Pratt & Whitney J42).
Contents
Design and development
In 1947, at the behest of the United States Navy, Pratt & Whitney entered into an agreement to produce the Rolls-Royce Nene centrifugal-flow turbojet engine under license as the J42 (company designation JT6), for use in the Grumman F9F Panther fighter aircraft.[1] Concerned that the Nene would not have the potential to cope with future weight growth in improved versions of the Panther, Luke Hobbs, vice president of engineering for P&W's parent company, the United Aircraft Corporation, requested that Rolls-Royce design a more powerful engine based on the Nene, which Pratt & Whitney would also produce.
By 1948, Rolls-Royce had designed the Tay turbojet, also a centrifugal-flow design. However, as Rolls-Royce was then developing an improved design with an axial compressor, which would become the Avon, the development and production of the Tay turbojet was left to Pratt & Whitney.[1][2] However, Rolls-Royce retained the rights to the Tay outside of the United States.
The Tay/J48 was a thirty percent enlargement of the preceding Nene/J42, and was produced both with and without afterburning.[2]
Operational history
Several aircraft types used the J48 engine during the 1950s, including the Grumman F9F-5 Panther.[3] and Grumman F9F-6/F9F-8 Cougar,[4] The U.S. Air Force's Lockheed F-94C Starfire[5] and North American YF-93 used afterburning versions of the J48 engine.[6]
Variants
Data from The Engines of Pratt & Whitney: A Technical History.[7]
- J48-P-1: 6,000 lbf (26.7 kN), 8,000 lbf (35.6 kN) thrust with afterburning
- J48-P-2: 6,250 lbf (27.8 kN), 7,000 lbf (31.1 kN) thrust with water injection
- J48-P-3: 6,000 lbf (26.7 kN), 8,000 lbf (35.6 kN) thrust with afterburning
- J48-P-5: 6,350 lbf (28.2 kN), 8,750 lbf (38.9 kN) thrust with afterburning
- J48-P-6: 6,250 lbf (27.8 kN), 7,000 lbf (31.1 kN) thrust with water injection
- J48-P-7: 6,350 lbf (28.2 kN), 8,750 lbf (38.9 kN) thrust with afterburning
- J48-P-8: 7,250 lbf (32.2 kN) thrust
- J48-P-8A: 7,250 lbf (32.2 kN) thrust
Applications
Specifications (J48-P-8A)
Data from The Engines of Pratt & Whitney: A Technical History.[7]
General characteristics
- Type: Turbojet
- Length: 109.75 in (2,788 mm) without fixed nozzle
- Diameter: 50.5 in (1,280 mm)
- Dry weight: 2,080 lb (940 kg) dry
Components
- Compressor: single-stage double-sided Centrifugal compressor
- Combustors: Nine interconnected can combustion chambers
- Turbine: single stage axial
- Fuel type: Aviation kerosene
- Oil system: Pressure spray with scavenge
Performance
- Maximum thrust: 7,250 lbf (32.2 kN) thrust for take-off / military power
- Specific fuel consumption: 1.14 lb/lbf/hr (116.2 kg/kN/hr)
- Power-to-weight ratio:
See also
- Related development
- Related lists
References
- Notes
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External links
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- ↑ 1.0 1.1 Connors, p.202
- ↑ 2.0 2.1 Gunston 2006, p.195.
- ↑ F9F Panther, U.S. Navy Historical Office. Accessed 2011-01-06.
- ↑ Bishop and Chant 2004, p. 154
- ↑ RAF Flying Review "TECHNICAL GEN" authors: staff, September 1962 page 59
- ↑ North American YF-93A. National Museum of the US Air Force fact sheet. Accessed 2011-01-06
- ↑ 7.0 7.1 Connors, p.210
