Cooled component for a gas turbine engine
US11326518B2 · kind B2 · utility
0Cited by
9References
20Claims
0Family size
Assignee
Inventors
Key dates
| Filing date | Jan 24, 2020 |
| Grant date | May 10, 2022 |
| Priority date | — |
| Expiry date | Apr 12, 2040 |
Classification
- Technology area (CPC Y)Emerging Cross-Sectional Technologies
- CPC primaryY02T50/60
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
A combustor panel arrangement for a gas turbine engine. The combustor panel arrangement includes a first combustor panel that has a first edge. A second combustor panel has a second edge facing the first edge. A first plurality of effusion holes extend through the first edge towards the second edge along a corresponding one of a first plurality of flow paths. A second plurality of effusion holes extend through the second edge along a corresponding one of a second plurality flow paths towards the first edge. The first plurality of flow paths and the second plurality of flow paths are non-intersecting.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.