Reverse flow ceramic matrix composite combustor
US9423130B2 · kind B2 · utility
8Cited by
31References
12Claims
0Family size
Assignee
Inventors
Key dates
| Filing date | Apr 28, 2014 |
| Grant date | Aug 23, 2016 |
| Priority date | — |
| Expiry date | Feb 18, 2035 |
Classification
- Technology area (CPC F)Mechanical Engineering; Lighting; Heating
- CPC primaryF23R2900/00018
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
A gas turbine engine has an annular reverse-flow combustor with a combustor inner liner enclosing a combustion chamber. The inner liner having a dome portion at an upstream end of the combustor and a downstream combustor exit defined between a small exit duct portion and a large exit duct portion. At least one of the dome portion, the small exit duct portion and the large exit duct portion is made of a separately formed hemi-toroidal shell composed of a ceramic matrix composite.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.