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RESEARCH PAPERS

The J83 Seven-Stage Transonic Compressor

[+] Author and Article Information
J. A. King

AiResearch Manufacturing Division, The Garrett Corporation, Los Angeles, Calif.

J. Eng. Power 83(3), 291-301 (Jul 01, 1961) (11 pages) doi:10.1115/1.3673190 History: Received July 26, 1960; Online January 10, 2012

Abstract

The J83 turbojet engine was a high-performance, lightweight engine with a maximum thrust of 2450 lb, a diameter of 18 in., and a weight of approximately 300 lb. The compressor for this engine was a seven-stage, transonic, axial-flow compressor with an inlet tip diameter of 15.2 in. and a hub-lip ratio of 0.433. Details of the aero-thermodynamic design of this compressor and the problems encountered during its development are given in this paper.

Copyright © 1961 by ASME
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