Machinable coating for CMC and metal interface in a turbine section
US12012870B1 · kind B1 · utility
Assignee
Inventors
Key dates
| Filing date | Nov 29, 2022 |
| Grant date | Jun 18, 2024 |
| Priority date | — |
| Expiry date | Nov 29, 2042 |
Classification
- Technology area (CPC F)Mechanical Engineering; Lighting; Heating
- CPC primaryF05D2300/611
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
A gas turbine engine turbine blade includes a turbine blade body including an inner platform. An airfoil extends radially outwardly of the inner platform. The airfoil has a leading edge and a trailing edge, and a suction wall and a pressure wall. The turbine blade body has mount structure including at least one circumferentially outwardly extending mount portion on a suction wall side and a pressure wall side each having a radially outer face. The turbine blade body is formed of one of a polymer, metal or ceramic matrix composite. There is a protective coating on the radially outer faces of the at least one enlarged mount portions. A gas turbine engine is also disclosed.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.