|국가/구분||United States(US) Patent 등록|
|미국특허분류(USC)||416/097R ; 416/096R ; 416/096A ; 416/241R ; 416/241B ; 415/115|
|발명자 / 주소|
|출원인 / 주소|
|대리인 / 주소||
|인용정보||피인용 횟수 : 21 인용 특허 : 1|
A turbine blade which can be subjected to a hot gas flow includes a substrate, at least one interior space and a plurality of bores leading from the interior space out of the substrate. The substrate is at least partly covered by a heat-insulating-layer system at a suction side and/or a pressure side. At least one of the bores is closed by the heat-insulating-layer system and at least one further bore is open for developing film cooling.
[ I claim:] [1.] A turbine blade to be subjected to a hot gas flow, comprising:a suction side;a pressure side;a substrate having at least one interior space and a plurality of bores leading from said interior space out of said substrate; anda heat-insulating-layer system at least partly covering at least one of said suction and pressure sides, said heat-insulating-layer system closing at least one bore and leaving at least one further bore open to emit cooling fluid for developing film cooling of said heat-insulating-layer system.