Pratt & Whitney JT12

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^[3]

YJ60-P-1

prototype

J60-P-3

J60-P-3A

J60-P-4

J60-P-5

J60-P-6

J60-P-9

T73

Military designation of the Pratt & Whitney JFTD12 free power turbine turboshaft version of the J60.

JT12A-3LH

JT12A-5

(J60-P-3 / -3A / -5 / -6 / -9) 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-6A

JT12A-7

(J60-P-4) up-rated to 3,300 lbf (15 kN)

JT12A-8

JT12A-8A

JT12A-21

An after-burning version developing 4,023 lbf (18 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.

• Lockheed JetStar
• North American Sabreliner
• Aérotrain Experimental 02 (French Touch in 60')

• Lockheed XH-51
• Lockheed XV-4 Hummingbird
• Martin/General Dynamics RB-57F Canberra
• North American T-2B Buckeye
• North American T-39 Sabreliner
• Republic SD-4 Swallow
• Fairchild SD-5 Osprey
• Sikorsky S-69

Data from Aircraft engines of the World 1966/67^[4]

• 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 (22.9 kg) per second
• 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

Related development

• Pratt & Whitney T73

Comparable engines

• Fairchild J83
• General Electric J85
• Ishikawajima-Harima J3
• Rolls-Royce RB.108
• Rolls-Royce RB.145
• Rolls-Royce RB.162
• Rolls-Royce Soar
• Armstrong Siddeley Viper

Related lists

• List of aircraft engines

• 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.

• Pratt & Whitney J60
• Atlantic Canadian Aviation: JT12 for Canadair aircraft