Method for forming a composite part of a gas turbine engine
US11002148B2 · kind B2 · utility
Assignee
Inventors
Key dates
| Filing date | Jun 14, 2019 |
| Grant date | May 11, 2021 |
| Priority date | — |
| Expiry date | Nov 12, 2039 |
Classification
- Technology area (CPC Y)Emerging Cross-Sectional Technologies
- CPC primaryY02T50/60
- WIPO fieldOther special machines
- WIPO sectorMechanical engineering
Abstract
A method for forming a composite part of a gas turbine engine. The method includes assembling the composite part of a first composite material and a second composite material. The second composite material defines an outer surface of the composite part, and is selected to be curable at a cure temperature generated by heat from operation of the engine. The first composite material is selected to have an operating temperature limit less than the cure temperature. The method includes placing the composite part within the engine so that, in use, the second composite material is cured by exposure to the heat generated from operation of the engine. The second composite material thermally shields the first composite material from the heat generated from operation of the engine. The method includes operating the engine to cure the second composite material.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.