Pratt and Whitney JT12

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

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.

Civilian (JT12)

Lockheed JetStar

North American Sabreliner

Military (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

General characteristics

Type: Turbojet

Length: 1930 mm (75.98 in)

Diameter: 556 mm (21.89 in)

Dry weight: 212 kg (467.38 lb)

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: