发明名称 GAS TURBINE BLADE
摘要 The present invention provides a gas turbine blade in which the tip end thereof is cooled effectively to decrease the metal temperature for the prevention of burning and the temperature gradient of blade metal is decreased to prevent the occurrence of a crack. In the gas turbine blade provided with a cooling passage therein, a protrusion is provided on the inside from the extension of blade profile on the outer surface of blade tip end.
申请公布号 CA2231035(A1) 申请公布日期 1998.09.04
申请号 CA19982231035 申请日期 1998.03.03
申请人 MITSUBISHI HEAVY INDUSTRIES, LTD. 发明人 TOMITA, YASUOKI;SUENAGA, KIYOSHI;FUKUNO, HIROKI
分类号 F01D5/18;F01D5/20;F01D5/30;F01D11/08;F02C7/16;F02C7/18;(IPC1-7):F01D5/20 主分类号 F01D5/18
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