Cooled cooling air for blade air seal through outer chamber
US10577964B2 · kind B2 · utility
Assignee
Inventors
Key dates
| Filing date | Mar 31, 2017 |
| Grant date | Mar 3, 2020 |
| Priority date | — |
| Expiry date | Apr 28, 2038 |
Classification
- Technology area (CPC Y)Emerging Cross-Sectional Technologies
- CPC primaryY02T50/60
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
A gas turbine engine according to an example of the present disclosure include a compressor section, a combustor, and a turbine section. The combustor has a radially outer surface that defines a diffuser chamber radially outwardly of the combustor. The turbine section has a high pressure turbine first stage blade that has an outer tip, and a blade outer air seal positioned radially outwardly of the outer tip. A tap for tapping air has been compressed by the compressor and is passed through a heat exchanger. The air downstream of the heat exchanger passes through at least one pipe and into a manifold radially outward of the blade outer air seal, and then passes across the blade outer air seal to cool the blade outer air seal.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.