Pratt & Whitney JT12
| JT12/J60 | |
|---|---|
 |
|
| A Pratt & Whitney JT12A turbojet | |
| Type | Turbojet |
| Manufacturer | Pratt & Whitney |
| First run | 1957 |
| Major applications | North American Sabreliner T-2 Buckeye |
| Number built | 2621[1] |
| Variants | Pratt & Whitney T73 |
The Pratt & Whitney JT12, (US military designation J60) is a small turbojet engine. The Pratt & Whitney T73 (Pratt & Whitney JFTD12) is a related turboshaft engine.[2]
Contents
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).
Variants
- Data from Janes[3]
- YJ60-P-1—prototype
- J60-P-3
- J60-P-4
- J60-P-5
- J60-P-6
- T73
- Military designation of the Pratt & Whitney JFTD12 free power turbine turboshaft version of the J60.
- JT12A-3LH
- JT12A-5
- (J60-P-3/-5/-6) Take-off ratings from 2,900 lbf (12.9 kN) to 3,001 lbf (13.35 kN).
- JT12A-6
- Essentially similar to the -5
- JT12A-7
- (J60-P-4) up-rated to 3,300 lbf (15 kN)
- JT12A-8
- JT12A-21
- An after-burning version developing 4,024 lbf (17.9 kN) thrust wet.
- FT12
- Turboshaft versions for marine use.
- JFTD12
- Company designation of the Pratt & Whitney T73 free power turbine turbo-shaft version of the J60.
Applications
Civilian (JT12)
Military (J60)
Specifications
General characteristics
- Type: Turbojet
- Length: 1930 mm (75.98 inches)
- Diameter: 556 mm (21.89 inches)
- Dry weight: 212 kg (467.38lbs)
Components
- Compressor: 9 stage axial compressor
- Turbine: 2 stages
Performance
- Maximum thrust: 14.6 kN (3,282.21 lbf)
- Turbine inlet temperature: 872 °C (1,601.6 °F)
- Power-to-weight ratio:
See also
- Related development
- Comparable engines
- Related lists
References
- ↑ Connors, p.285
- ↑ Greg Goebel's Vectorsite
- ↑ Janes: JT12
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External links
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