Gas turbine engine combustor having a ceramic matrix composite liner and dome
US12372238B1 · kind B1 · utility
0Cited by
14References
18Claims
0Family size
Assignee
Inventors
Key dates
| Filing date | Mar 14, 2024 |
| Grant date | Jul 29, 2025 |
| Priority date | — |
| Expiry date | Mar 14, 2044 |
Classification
- Technology area (CPC F)Mechanical Engineering; Lighting; Heating
- CPC primaryF23R2900/00012
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
A combustor for a gas turbine engine includes a ceramic matrix composite (CMC) dome structure, a CMC outer liner, a CMC inner liner, and a cowl structure, that are connected together via at least one outer connection and at least one inner connection. An outer seal member is arranged to seal an outer gap between an outer liner connecting flange and an outer dome connecting flange, and an inner seal member is arranged to seal an inner gap between an inner liner connecting flange and an inner dome connecting flange.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.