Cooling features for a component of a gas turbine engine
US12359620B2 · kind B2 · utility
Assignee
Inventors
Key dates
| Filing date | Oct 13, 2023 |
| Grant date | Jul 15, 2025 |
| Priority date | — |
| Expiry date | Oct 13, 2043 |
Classification
- Technology area (CPC F)Mechanical Engineering; Lighting; Heating
- CPC primaryF05D2260/232
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
A component for a gas turbine engine, including: at least one internal cavity extending through the component, the internal cavity having at least one inlet opening and at least one outlet opening each being in fluid communication with the at least one internal cavity; a plurality of cooling features extending from a surface of the at least one internal cavity, the plurality of cooling features are formed in accordance with at least one of the following groups: i) a plurality of airfoil shaped features that extend upwardly from the surface of the at least one internal cavity and a plurality of wedge shaped features each having a triangular base that has an upstream portion and a downstream portion, the upstream portion extending further from the surface than the downstream portion; ii) a plurality features having a curved or “J” shaped base that extends upwardly from the surface, a plurality features having a double curved or symmetrically “J” shaped base that extends upwardly from the surface, and a plurality features having a base that extends upwardly from the surface with a curved portion that defines an opening therethrough; iii) a first plurality of pins with a plurality of g…
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.