发明名称 |
THERMAL BARRIER COATING MATERIAL, GAS TURBINE PARTS AND GAS TURBINE |
摘要 |
<p>A thermal barrier coating material can prevent spall-off from occurring duri ng 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 a re 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 protec t the base 21 from high temperatures, the ceramic layer 23 being applied via a bonding coa t layer 22 provided as a metal bonding layer and is made of ZrO2 with Er2O3 added there to 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.</S DOAB></p> |
申请公布号 |
CA2408881(C) |
申请公布日期 |
2006.08.08 |
申请号 |
CA20022408881 |
申请日期 |
2002.10.18 |
申请人 |
MITSUBISHI HEAVY INDUSTRIES, LTD. |
发明人 |
OKADA, IKUO;TAKAHASHI, KOUJI;MORI, KAZUTAKA;AOKI, SUNAO;TORIGOE, TAIJI |
分类号 |
C23C30/00;F01D5/28;C04B35/48;C23C4/10;C23C28/00;F02C7/00 |
主分类号 |
C23C30/00 |
代理机构 |
|
代理人 |
|
主权项 |
|
地址 |
|