Affiliation:
1. NASA, Lewis Research Center, Cleveland, Ohio
Abstract
From a study of multistage compressors operating in gas-turbine engines the sequence of events which occur during the stall process was determined. By using this information and stage-characteristic curves, it is shown that the compressor stall limit may be computed for any disturbance.
Cited by
2 articles.
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1. Stability of an Axial Flow Compressor with Steady Inlet Conditions;Journal of Mechanical Engineering Science;1974-12
2. Separation of flow;Journal of the Franklin Institute;1961-12