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

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

Performance

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See also

Related lists

References
  1. Flight International 9 October 1976, p. 1150.
  2. Flight International 28 June 1962, p. 1012.
  3. Taylor 1966, p. 492.
  4. Taylor 1966, pp. 492–493.
  5. Taylor 1976, pp.735–736.
  6. Bridgman, Leonard, ed. (1959). Jane's all the World's Aircraft 1959–60. London: Sampson Low, Marston & Co. Ltd. p. 512.
  7. Hamada, T., Akagi, M., Toda, D., Shimazaki, H., & Ohmomo, M. (1989). T-4 Inlet/Engine Compatibility Flight Test Results. Presented at the AIAA/ASME/SAE/ASEE 25th Joint Propulsion Conference, Monterey, CA: American Institute of Aeronautics and Astronautics.
  8. Wilkinson, Paul H. (1964). Aircraft engines of the World 1964/65 (20th ed.). London: Sir Isaac Pitman & Sons Ltd. p. 192.

Further reading
  • Taylor, John W.R., ed. (1966). Jane's All the World's Aircraft 1966–67. London: Sampson Low, Marston & Co. Ltd.
  • Taylor, John W.R., ed. (1976). Jane's All the World's Aircraft 1976–77 (67th ed.). London: Jane's Yearbooks. ISBN 0-3540-0538-3.
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