| 发明名称 | Turbine compressor blade tip resistant to metal transfer | ||
| 摘要 | A gas turbine engine having an engine casing extending circumferentially about an engine centerline axis; and a compressor section, a combustor section, and a turbine section within said engine casing. At least one of said compressor section and said turbine section includes at least one airfoil and at least one seal member adjacent to the at least one airfoil, wherein a tip of the at least one airfoil is metal having a thin film ceramic coating and the at least one seal member is coated with an abradable. | ||
| 申请公布号 | US9341066(B2) | 申请公布日期 | 2016.05.17 |
| 申请号 | US201213525420 | 申请日期 | 2012.06.18 |
| 申请人 | United Technologies Corporation | 发明人 | Bintz Matthew E.;Strock Christopher W. |
| 分类号 | F01D5/28;F01D5/20;F01D11/12 | 主分类号 | F01D5/28 |
| 代理机构 | Kinney & Lange, P.A. | 代理人 | Kinney & Lange, P.A. |
| 主权项 | 1. A gas turbine engine comprising: an engine casing extending circumferentially about an engine centerline axis; and a compressor section, a combustor section, and a turbine section within said engine casing; wherein at least one of said compressor section and said turbine section includes at least one airfoil and at least one seal member adjacent to the at least one airfoil, wherein a tip of the at least one airfoil is metal having a smooth thin film ceramic coating and the at least one seal member is coated with an abradable coating, the thin film ceramic coating having a melting or softening point higher than that of the abradable coating and the tip of the at least one airfoil, wherein the thin film ceramic coating is selected from the group consisting of a metal oxide layer, a nitride layer, a carbide layer, a boride layer, and combinations thereof. | ||
| 地址 | Hartford CT US | ||