| 发明名称 | Gas turbine engine airfoil with vane platform cooling passage | ||
| 摘要 | A stator vane for a gas turbine engine includes an airfoil extending in a radial direction and supported by a platform having a gas flowpath surface. A cooling passage is arranged in the platform and includes a circumferential passage that is fluidly connected to an inlet passage extending through and edge of the platform, and film cooling holes extending from the gas flowpath surface to the circumferential passage, radial extending passage through the edge of the platform. A void is interconnected to at least one of the radially extending passage and the inlet passage. | ||
| 申请公布号 | US9080452(B2) | 申请公布日期 | 2015.07.14 |
| 申请号 | US201213630419 | 申请日期 | 2012.09.28 |
| 申请人 | UNITED TECHNOLOGIES CORPORATION | 发明人 | Boeke Mark A.;Gregg Shawn J.;Riley Sarah;DeGray Jeffrey J.;Salzillo Richard M. |
| 分类号 | F01D5/18;F01D25/12;F01D25/24;F01D9/02 | 主分类号 | F01D5/18 |
| 代理机构 | Carlson, Gaskey & Olds, P.C. | 代理人 | Carlson, Gaskey & Olds, P.C. |
| 主权项 | 1. A stator vane for a gas turbine engine comprising: an airfoil extending in a radial direction and supported by a platform having a gas flowpath surface, a cooling passage arranged in the platform and including a circumferential passage fluidly connected to an inlet passage extending through an edge of the platform, and film cooling holes extending from the gas flowpath surface to the circumferential passage, radically extending passage through the edge of the platform, and a void interconnected to at least one of the radially extending passage and the inlet passage. | ||
| 地址 | Hartford CT US | ||