Gas turbine engine component having an airfoil with internal cross-ribs
US12196095B2 · kind B2 · utility
Assignee
Inventors
Key dates
| Filing date | Nov 29, 2022 |
| Grant date | Jan 14, 2025 |
| Priority date | — |
| Expiry date | Nov 29, 2042 |
Classification
- Technology area (CPC F)Mechanical Engineering; Lighting; Heating
- CPC primaryF05D2300/6033
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
A gas turbine engine component includes an airfoil body extending between a leading edge and a trailing edge and having a suction wall and a pressure wall. An outer surface of the airfoil body is formed by an outer coat defining around the pressure and suction sides, a leading edge and a trailing edge. An internal cross-rib is formed within a cavity in the airfoil body. The internal cross-rib extends to be secured to the outer coat adjacent the leading edge and the trailing edge, and extending across the internal cavity to form a junction such that the cross-rib is x-shaped. The outer coat and the cross-rib are formed of ceramic matrix composites. A gas turbine engine is also disclosed.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.