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Effect of casing treatment on performance of an inlet stage for a transonic multistage compressor

D. C. Urasek

出版	U.S. National Aeronautics and Space Administration, 1976
URL	http://books.google.com.hk/books?id=QYC-MQEACAAJ&hl=&source=gbs_api

註釋

An inlet stage of a transonic compressor was tested with three rotor tip casing treatment configurations: blade angle slots, circumferential grooves, and axial skewed slots. Significant increases in both rotor and stage total pressure ratio, total temperature ratio, efficiency, flow range, and very large improvements in stall margin were obtained with all three casing treatment configurations. The greatest improvement in performance was achieved with axial skewed slots.