Cooled cooling air to blade outer air seal passing through a static vane
US10711640B2 · kind B2 · utility
Assignee
Inventors
Key dates
| Filing date | Apr 11, 2017 |
| Grant date | Jul 14, 2020 |
| Priority date | — |
| Expiry date | Dec 6, 2037 |
Classification
- Technology area (CPC Y)Emerging Cross-Sectional Technologies
- CPC primaryY02T50/60
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
A gas turbine engine comprises a compressor section, a combustor, and a turbine section. The turbine section includes a high pressure turbine first stage blade having an outer tip, and a blade outer air seal positioned radially outwardly of the outer tip. A tap taps air having been compressed by the compressor, the tapped air being passed through a heat exchanger. A vane section has vanes downstream of the combustor, but upstream of the first stage blade, and the air downstream of the heat exchanger passes radially inwardly of the combustor, along an axial length of the combustor, and then radially outwardly through a hollow chamber in the vanes, and then across the blade outer air seal, to cool the blade outer air seal.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.