B-8 高負荷ディフューザパッセージ圧縮機の技術検討(空力II,一般講演)

概要

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For small aircraft engines, adverse effects of tip leakage flow on axial flow compressors' performance must be minimized in order to achieve high efficiency, high loading and wide operating range in compressors because compressor's blade height in rear stages is quite low and tip leakage flow is relatively large. In order to reduce tip leakage flow, new concept compressor rotor blades are proposed. The new concept compressor rotor blades produce pressure rise by reducing axial velocity with divergent passage at blade rows, whereas conventional compressor rotor blades produce pressure rise by turning the flow. CFD analyses and cascade tests are conducted and it is shown that the new concept compressor rotor blades are capable of reducing adverse effects of tip leakage flow.
社団法人日本ガスタービン学会の論文
2004-10-01