发明名称 |
Coating for gas turbine blades |
摘要 |
<p>The present invention provides a turbine moving blade, a turbine stationary blade, and a turbine split ring which are capable of restraining the deterioration and peeling-off of a thermal barrier coating easily and surely, and a gas turbine capable of enhancing the energy efficiency by increasing the temperature of combustion gas. The turbine moving blade provided in a turbine constituting the gas turbine includes a platform having a gas path surface extending in the combustion gas flow direction, and a blade portion erecting on the platform. The thermal barrier coating covering the gas path surface is formed so as to go around from the gas path surface to an upstream-side end face and a downstream-side end face of the outer peripheral faces of the platform. <IMAGE></p> |
申请公布号 |
EP1239058(A2) |
申请公布日期 |
2002.09.11 |
申请号 |
EP20020003340 |
申请日期 |
2002.02.13 |
申请人 |
MITSUBISHI HEAVY INDUSTRIES, LTD. |
发明人 |
TOMITA, YASUOKI;SHIOZAKI, SHIGEHIRO;YAMAGUCHI, KENGO;KANEKO, HIDEAKI;OHSHIMA, KOTARO |
分类号 |
C23C28/00;F01D5/12;F01D5/28;F01D9/02;F01D9/04;(IPC1-7):C23C26/00 |
主分类号 |
C23C28/00 |
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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