| 发明名称 |
ALUMINUM FAN BLADE TIP WITH THERMAL BARRIER |
| 摘要 |
A fan blade for a gas turbine engine is described. The fan blade may comprise a body portion formed from a metallic material, and it may include a suction side, a pressure side, a leading edge, a trailing edge, and a tip. A coating may be applied to the tip, and the coating may have a thermal conductivity of no more than about 10 watt per meter kelvin. The coating may be a thermal barrier coating comprising yttria-stabilized zirconia. |
| 申请公布号 |
US2016040538(A1) |
申请公布日期 |
2016.02.11 |
| 申请号 |
US201514711237 |
申请日期 |
2015.05.13 |
| 申请人 |
United Technologies Corporation |
发明人 |
Chen Yan;Guo Changsheng |
| 分类号 |
F01D5/28;B05D7/14;F01D5/14 |
主分类号 |
F01D5/28 |
| 代理机构 |
|
代理人 |
|
| 主权项 |
1. A fan blade for a gas turbine engine, comprising:
a body portion formed from a metallic material, the body portion including a pressure side, a suction side, a leading edge, a trailing edge, and a tip; and a coating applied to the tip, the coating having a thermal conductivity of no more than about 10 watt per meter kelvin. |
| 地址 |
Hartford CT US |
