Gas turbine engine blade outer air seal cooling hole configuration
US10619504B2 · kind B2 · utility
2Cited by
4References
23Claims
0Family size
Assignee
Inventors
Key dates
| Filing date | Oct 31, 2017 |
| Grant date | Apr 14, 2020 |
| Priority date | — |
| Expiry date | Jul 20, 2038 |
Classification
- Technology area (CPC Y)Emerging Cross-Sectional Technologies
- CPC primaryY02T50/60
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
A blade outer air seal includes a body that extends axially between forward and aft rails and circumferentially between lateral faces. The body has an inner arcuate surface that is configured to seal relative to a blade tip. The body includes a plurality of cooling holes that extend through an exterior surface of the body. Each of the plurality of cooling holes break through the exterior surface at geometric coordinates in accordance with Cartesian coordinate values of X, Y and Z as set forth in Tables 1, 2 and 3. Each of the geometric coordinates is measured from a reference point on the body.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.