发明名称 |
High temperature components with thermal barrier coatings for gas turbine |
摘要 |
The most principal feature of the present invention is as follows: Namely, in the gas-turbine-use high-temperature component including the thermal barrier coating and a cooling structure, micro passages are provided inside an alloy bond-coat layer (2) and a thermal-barrier ceramic top-coat layer (3) of the thermal barrier coating, the micro passages being in communication from the substrate side to the surface side. Moreover, a partial amount of coolant of a coolant (8) for cooling the high-temperature component is caused to flow out to the outside of the high-temperature component via these micro passages. The employment of the structure like this makes it possible to expect the implementation of a high-temperature component's heat-resistant-temperature enhancement effect based on the transpiration cooling effect. |
申请公布号 |
EP2725120(B1) |
申请公布日期 |
2016.07.27 |
申请号 |
EP20130189647 |
申请日期 |
2013.10.22 |
申请人 |
MITSUBISHI HITACHI POWER SYSTEMS, LTD. |
发明人 |
ARIKAWA, HIDEYUKI;KOJIMA, YOSHITAKA;KASUYA, TADASHI;MEBATA, AKIRA;ICHIKAWA, KUNIHIRO;ENDO, HIROYUKI;ENDO, TAKAO |
分类号 |
C23C24/08;C23C4/08;C23C28/00;F01D5/18;F01D5/28 |
主分类号 |
C23C24/08 |
代理机构 |
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代理人 |
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主权项 |
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地址 |
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