| 发明名称 | Turbine blade with mate face cooling air flow | ||
| 摘要 | A gas turbine engine blade comprises a dovetail, a shank extending from the dovetail, an airfoil, and a platform between the shank and the airfoil. The platform comprises a side wall extending between an upstream side and a downstream side of the platform. A first pin channel extends from the upstream side of the sidewall and a second pin channel, co-axial with the first pin channel, extends from the downstream side of the sidewall. The first channel includes a radial notch at the upstream longitudinal end of the first pin channel. | ||
| 申请公布号 | US8951014(B2) | 申请公布日期 | 2015.02.10 |
| 申请号 | US201113048634 | 申请日期 | 2011.03.15 |
| 申请人 | United Technologies Corporation | 发明人 | Corcoran Christopher;Thomen Seth J. |
| 分类号 | F01D5/10;F01D11/00;F01D5/22 | 主分类号 | F01D5/10 |
| 代理机构 | O'Shea Getz P.C. | 代理人 | O'Shea Getz P.C. |
| 主权项 | 1. A gas turbine engine blade assemblage, comprising: a dovetail; a shank extending from the dovetail; an airfoil; a platform between the shank and the airfoil, the platform comprising a sidewall extending between an upstream side and a downstream side of the platform, wherein a first pin channel extends from and through the upstream side of the sidewall, wherein a second pin channel extends from and through the downstream side of the sidewall, wherein the first and second pin channels are co-axial, and wherein the first pin channel includes a radial notch at an upstream longitudinal end of the first pin channel, and the second pin channel is at least partially formed by a second pedestal surface that is substantially planar and extends to and through the sidewall at the downstream side of the platform; and a pin within the first and second pin channels, wherein the pin includes a radial projection that sits within the notch. | ||
| 地址 | Hartford CT US | ||