发明名称 Structure of output section of jet propulsion engine or gas turbine
摘要 A tandem blade lattice having characteristics enhanced is provided. In a high pressure ratio blade lattice, inevitable generation of an shock wave is shifted, as much as possible, toward a rear portion of an upper surface of a front blade to inhibit separation from a blade surface from being caused by interference of the shock wave and a boundary layer, and boundary layer control is performed such that a speed, a momentum and the like of a jet flowing from a trailing edge of a lower surface of the front blade onto an upper surface of a rear blade are regulated to obtain a flow along the upper surface of the rear blade, so that separation of the boundary layer on the upper surface of the rear blade is restricted to a vicinity of a trailing edge.
申请公布号 US6099249(A) 申请公布日期 2000.08.08
申请号 US19970877173 申请日期 1997.06.17
申请人 KAWASAKI JUKOGYO KABUSHIKI 发明人 HASHIMOTO, KEISUKE
分类号 F01D5/14;F01D9/04;F02K3/04;(IPC1-7):F01D1/02 主分类号 F01D5/14
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