Ishikawajima-Harima J3

The Ishikawajima-Harima J3 was a Japanese turbojet aircraft engine. It was the first jet engine designed and built in Japan after the Second World War and was used to power the Fuji T-1 trainer and as a booster engine in the Kawasaki P-2J patrol aircraft.

J3
Type	Turbojet
National origin	Japan
Manufacturer	Ishikawajima-Harima
Major applications	Fuji T-1 Kawasaki P-2J

Design and development

Development of the J3, the first Japanese post-war jet engine,^[1] intended to power the Fuji T-1 jet trainer, was begun in 1955 by the Nippon Jet-Engine Company, with Ishikawajima-Harima Heavy Industries (IHI) being designated prime contractor in 1959.^[2][3] The resulting engine was a small, simple axial-flow turbojet.

The first pre-production engine began flight testing in a Curtiss C-46 testbed in February 1960, with production deliveries beginning in April 1962.^[4]

Operational history

While the J3 was designed to power the Fuji T-1, it was not ready in time and the first version of the T-1 was powered by imported British Bristol Orpheus engine. The J3-IHI-3 version of the engine equipped the later T-1B version.^[4] A more powerful version of the J3, the J3-IHI-7 was used to re-engine the T-1Bs and as booster engines for the Kawasaki P-2J maritime patrol aircraft.^[5]

Variants

J3-1

Nippon Jet-Engine Company prototype.^[3][6]

J3-IHI-3

Initial production version for Fuji T-1B trainer. 11.8 kN (2,645 lbf) thrust.^[4]

J3-IHI-7

More powerful version used as auxiliary engine in the P-2J and to re-engine T-1B trainers. 13.7 kN (3,080 lbf) thrust.^[5]

J3-IHI-7C

13.7 kN (3,080 lbf) for take-off.

J3-IHI-8

15.19 kN (3,415 lbf) for take-off.

J3-IHI-F

Aft-fan variant, 16.7 kN (3,750 lbf).^[4] — the later Ishikawajima-Harima F3 turbofan engine began flights in 1985.^[7][8]

Applications

• Fuji T-1
• Kawasaki P-2J

Specifications (J3-IHI-7C)

Data from Jane's All The World's Aircraft 1976–77^[5]

General characteristics

• Type: axial flow turbojet
• Length: 1,661 mm (65.4 in) (without tailpipe)
• Diameter: 627 mm (24.7 in)
• Dry weight: 430 kg (948 lb) (with accessories)

Components

• Compressor: eight-stage axial compressor
• Combustors: annular combustion chamber with 30 fuel supply pipes and vapouriser tubes
• Turbine: single-stage axial-flow
• Fuel type: JP-4 jet fuel

Performance

• Maximum thrust: 13.7 kN (3,080 lbf) (take-off power)
• Overall pressure ratio: 4.5:1
• Air mass flow: 25.4 kg/s (56 lb/s)
• Specific fuel consumption: 106.9 kg/kN hr (1.05 lb/lbf hr)
• Thrust-to-weight ratio: 3.2

See also

Comparable engines

• Armstrong Siddeley Sapphire
• Rolls-Royce Avon

Related lists

• List of aircraft engines