Gas turbine engine flowpath component including vectored cooling flow holes
US11415020B2 · kind B2 · utility
0Cited by
6References
20Claims
0Family size
Assignee
Inventors
Key dates
| Filing date | Dec 4, 2019 |
| Grant date | Aug 16, 2022 |
| Priority date | — |
| Expiry date | Jun 2, 2040 |
Classification
- Technology area (CPC F)Mechanical Engineering; Lighting; Heating
- CPC primaryF05D2260/202
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
A gas turbine engine includes a primary flowpath connecting a compressor section, a combustor section and a turbine section. The turbine section includes a stage vane having a radially outward platform and a vane extending into the primary flowpath. The platform includes a cooling plenum. At least one retaining feature extends radially outward from the platform. At least one vectored cooling hole is disposed in the retaining feature and is configured to direct cooling air from the plenum to an adjacent gaspath component.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.