| 发明名称 | Stress-relieved wire seal assembly for gas turbine engines | ||
| 摘要 | A sealing assembly for use in a gas turbine engine having a disk arranged relative to an axis, the assembly including a circumferential groove defined in the disk and an annular wire seal positioned at least partially within the groove. The groove includes a first sidewall, a base portion adjoining the first sidewall, and a second sidewall adjoining the base portion opposite the first sidewall, wherein the second sidewall is angled in a range greater than 0° and less than 90° with respect to the axis. | ||
| 申请公布号 | US9140136(B2) | 申请公布日期 | 2015.09.22 |
| 申请号 | US201213485491 | 申请日期 | 2012.05.31 |
| 申请人 | United Technologies Corporation | 发明人 | Corcoran Kevin L.;Boyington Kimberly Pash |
| 分类号 | F01D5/30;F01D25/00;F01D11/00 | 主分类号 | F01D5/30 |
| 代理机构 | Kinney & Lange, P.A. | 代理人 | Kinney & Lange, P.A. |
| 主权项 | 1. A sealing assembly for use in a gas turbine engine having a disk arranged relative to an axis of rotation of the gas turbine engine, the assembly comprising: a circumferential groove defined in the disk, the groove including: a first sidewall;a base portion adjoining the first sidewall; anda second sidewall adjoining the base portion opposite the first sidewall, wherein the second sidewall adjoins the base portion at a location where a concave curvature of the base portion terminates, wherein the second sidewall includes a smooth convex curve, and wherein the entire second sidewall is angled away from the base portion such that the second sidewall is angled in a range greater than 0° and less than 90° with respect to the axis; and an annular wire seal positioned at least partially within the groove. | ||
| 地址 | Hartford CT US | ||