Reverse flow ceramic matrix composite combustor
US8745989B2 · kind B2 · utility
12Cited by
31References
9Claims
0Family size
Assignee
Inventors
Key dates
| Filing date | Apr 9, 2009 |
| Grant date | Jun 10, 2014 |
| Priority date | — |
| Expiry date | Sep 4, 2031 |
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.