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Ishikawajima Harima J3

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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.

Contents

Design and development

Development of the J3, the first Japanese post-war jet engine, 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. 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.

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. 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.

Variants

J3-1
Prototype.
J3-IHI-3
Initial production version for Fuji T-1B trainer. 11.8 kN (2,645 lbf) thrust.
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.
J3-IHI-F
Proposed turbofan variant.

Applications

  • Fuji T-1
  • Kawasaki P-2J
  • Specifications (J3-IHI-7C)

    Data from Jane's All The World's Aircraft 1976–77

    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: 3.2:1
  • References

    Ishikawajima-Harima J3 Wikipedia