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US 2026/0022641 A1Published application
Gas turbine engine component formed by cmcs and having a compressed insert with tapered ends
AssigneeRtx Corporation
InventorsChristian X. Campbell, Kathryn S. Read
Life of this patent
Estimating the term…
Abstract
A component includes fabric layers of ceramic matrix composite (“CMC”) fabric. The fabric has layers separated by an insert formed of the CMC fabric. The insert has at least one tapered end. The tapered end has a thickness which is less than a central thickness of the insert. A method is also disclosed.
Claims20
A component comprising:
- fabric layers of ceramic matrix composite (“CMC”) fabric, the fabric having layers separated by an insert formed of the CMC fabric, and the insert having at least one tapered end, the tapered end having a thickness which is less than a central thickness of the insert.
A gas turbine engine comprising:
- a turbine section and a compressor section;
- and
- a component in the turbine section having fabric layers of ceramic matrix composite (“CMC”) fabric, the fabric having layers separated by an insert formed of the CMC fabric, and the insert having at least one tapered end, the tapered end having a thickness which is less than a central thickness of the insert.
Dependencies are inferred from the claim text.