发明名称 BLADE USED IN GAS TURBINE ENGINE
摘要 PROBLEM TO BE SOLVED: To cool the intersecting part of the rear edge of an air foil and a blade platform by providing the air foil with the front edge and the rear edge, and providing a platform cooling supply channel and plural cooling holes on a surface, which are respectively communicated with a cooling passage. SOLUTION: A platform cooling supply channel 34 is extended from a first side 30 through a blade platform 24 to a second side 32. Plural cooling holes 36 are provided in a second surface 28, and connected to the platform cooling supply channel 34 by one of plural cooling passages 38. The cooling hole 36 is communicated with the platform cooling supply channel 34 through one cooling passage 38. An air foil cooling supply channel 40 is extended from the blade root above the air foil 40, thereby supplying cooling air to the air foil 40 during the operation of an engine. The platform cooling supply channel 34 decreases the total weight of the blade.
申请公布号 JP2000186503(A) 申请公布日期 2000.07.04
申请号 JP19990358582 申请日期 1999.12.17
申请人 UNITED TECHNOL CORP <UTC> 发明人 LIANG GEORGE P
分类号 F01D5/12;F01D5/18 主分类号 F01D5/12
代理机构 代理人
主权项
地址