Gas turbine engine assembly with mid-vane outer platform gap
US11181005B2 · kind B2 · utility
2Cited by
27References
20Claims
0Family size
Assignee
Inventors
Key dates
| Filing date | May 18, 2018 |
| Grant date | Nov 23, 2021 |
| Priority date | — |
| Expiry date | Oct 14, 2038 |
Classification
- Technology area (CPC Y)Emerging Cross-Sectional Technologies
- CPC primaryY02T50/60
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
An assembly for a gas turbine engine includes a vane assembly having an inner platform and an airfoil section extending from the inner platform. A first combustor panel extends at least partially along the vane from upstream of the vane, and a blade outer air seal extends at least partially along the vane from downstream of the vane. The first combustor panel and the blade outer air seal define a platform gap located between a leading edge of the airfoil section of the vane and a trailing edge of the airfoil section of the vane.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.