Axial retention geometry for a turbine engine blade outer air seal
US11274566B2 · kind B2 · utility
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1References
7Claims
0Family size
Assignee
Inventors
Key dates
| Filing date | Aug 27, 2019 |
| Grant date | Mar 15, 2022 |
| Priority date | — |
| Expiry date | Dec 13, 2039 |
Classification
- Technology area (CPC F)Mechanical Engineering; Lighting; Heating
- CPC primaryF05D2240/11
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
A blade outer air seal for a gas turbine engine includes a platform having a leading edge and a trailing edge. A pair of circumferential edges connect the leading edge and the trailing edge. An end wall protrudes radially outward from the platform at the trailing edge. A first support rib connects one of the circumferential edges to the end wall and structurally supports the end wall. A first boss portion extends axially forward from the end wall and is disposed radially outward of the first support rib.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.