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The Mach 2 Axial Flow Compressor Stage

Name: The Mach 2 Axial Flow Compressor Stage
Creator: F. A. E. Breugelmans

descriptionPublicationkeyboard_double_arrow_right Article , Other literature type 02 Mar 1975Publisher:American Society of Mechanical EngineersJournal:Volume 1A: General

Authors: F. A. E. Breugelmans;

doi: 10.1115/75-gt-22

The Mach 2 Axial Flow Compressor Stage

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Abstract

A supersonic compressor stage has been designed for a high pressure ratio at a tip relative inlet Mach number of 2. The stage was operated in the original configuration, but serious inlet stall occurred at part-speed operation. An inlet blockage ring, a bleed system and a variable geometry inlet guide vane have been analyzed and applied to this configuration. The results obtained with the bleed system in the complete stage are presented. The rotor performance is discussed and compared with the stage performance.

Related Organizations

Von Karman Institute for Fluid Dynamics
Belgium

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