Stall of axial flow type compressor limits flexibility of operation of one- and two-spool turbojet engines; rotating stall at low values of equivalent rotative speed is serious source of blade vibrational failure; latter problem is also aggravated by inlet flow distortions.
Compressor-stall problems in gas-turbine type aircraft engines
Soc Automotive Engrs -- Paper
Society of Automotive Engineers -- Meeting ; 1956 Surges
1956
15 pages
Aufsatz (Konferenz)
Englisch
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COMPRESSOR STALL PROBLEMS IN GAS-TURBINE-TYPE AIRCRAFT ENGINES
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