发明名称 |
Thermal barrier coating material, gas turbine parts and gas turbine |
摘要 |
A thermal barrier coating material can prevent spall-off from occurring during operation at high temperatures and has a high heat insulating effect. A turbine parts and a gas turbine that are protected with the thermal barrier coating material are also provided. The thermal barrier coating material of the present invention comprises a ceramic layer 23, which is formed on a high temperature heat-resistant alloy base 21 to protect the base 21 from high temperatures, the ceramic layer 23 being applied via a bonding coat layer 22 provided as a metal bonding layer and is made of ZrO2 with Er2O3 added thereto as a stabilizing agent. The turbine parts and the gas turbine of the present invention are coated with the thermal barrier coating material on the surfaces thereof.
|
申请公布号 |
US2003087120(A1) |
申请公布日期 |
2003.05.08 |
申请号 |
US20020274132 |
申请日期 |
2002.10.21 |
申请人 |
MITSUBISHI HEAVY INDUSTRIES, LTD. |
发明人 |
TORIGOE TAIJI;AOKI SUNAO;MORI KAZUTAKA;OKADA IKUO;TAKAHASHI KOUJI |
分类号 |
F01D5/28;C23C4/10;C23C28/00;C23C30/00;F02C7/00;(IPC1-7):B32B15/04 |
主分类号 |
F01D5/28 |
代理机构 |
|
代理人 |
|
主权项 |
|
地址 |
|