Pratt & Whitney JT12
|A Pratt & Whitney JT12A turbojet|
|Manufacturer||Pratt & Whitney|
|Major applications||North American Sabreliner|
|Variants||Pratt & Whitney T73|
Design and development
The J60 conception and project design began in July 1957 at United Aircraft of Canada (now Pratt & Whitney Canada) in Montreal. The project design details were transferred to the main P&W company in East Hartford and in May 1958, the first prototype, with military designation YJ60-P-1 commenced testing.
Flight tests were completed in early 1959; followed by the delivery of the new JT12A-5 engines in July 1959. These were for the two Canadair CL-41 prototype trainers with a rating of 12.9 kN (2,900 lb st). The modified JT12A-3 turbojets with a basic rating of 14.69 kN (3,300 lb st) were tested in the two Lockheed XV-4A Hummingbird VTOL research aircraft. The next version, JT12A-21, had an afterburner which delivered a maximum thrust of 17.91 kN (4,025 lb st).
- Data from Janes
- Military designation of the Pratt & Whitney JFTD12 free power turbine turboshaft version of the J60.
- (J60-P-3 / -3A / -5 / -6 / -9) Take-off ratings from 2,900 lbf (12.9 kN) to 3,001 lbf (13.35 kN).
- Essentially similar to the -5
- (J60-P-4) up-rated to 3,300 lbf (15 kN)
- An after-burning version developing 4,023 lbf (18 kN) thrust wet.
- Turboshaft versions for marine use.
- Company designation of the Pratt & Whitney T73 free power turbine turbo-shaft version of the J60.
- Lockheed XH-51
- Lockheed XV-4 Hummingbird
- Martin/General Dynamics RB-57F Canberra
- North American T-2B Buckeye
- North American T-39 Sabreliner
- Sikorsky S-69
Data from Aircraft engines of the World 1966/67
- Type: Commercial turbojet
- Length: 78 in (2,000 mm)
- Diameter: 22 in (560 mm)
- Dry weight: 468 lb (212 kg)
- Compressor: 9-stage axial compressor
- Combustors: Cannular - 8 burner cans in an annular casing
- Turbine: 2-stage axial turbine
- Fuel type: ASTM-A-1 / MIL-J-5624 / JP-1 / JP-4 / JP-5
- Oil system: Return pressure spray system at 45 psi (310 kPa)
- Maximum thrust: 3,300 lbf (14.68 kN)
- Overall pressure ratio: 6.7:1
- Air mass flow: 50.5 lb/s (1,370 kg/min)
- Turbine inlet temperature: 872 °C (1,602 °F; 1,145 K)
- Specific fuel consumption: 0.89 lb/lbf (91 kg/kN) per hour
- Thrust-to-weight ratio: 7.05 lbf/lb (0.0691 kN/kg)
- Related development
- Comparable engines
- Related lists
- Connors, Jack; Allen, Ned (2010). The Engines of Pratt & Whitney: A Technical History. Reston. Virginia: American Institute of Aeronautics and Astronautics. ISBN 978-1-60086-711-8.
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