Gas turbine engine combustor with integrated combustor vane having swirler
US9482432B2 · kind B2 · utility
9Cited by
52References
17Claims
0Family size
Assignee
Inventors
Key dates
| Filing date | Sep 26, 2012 |
| Grant date | Nov 1, 2016 |
| Priority date | — |
| Expiry date | Aug 7, 2035 |
Classification
- Technology area (CPC Y)Emerging Cross-Sectional Technologies
- CPC primaryY02T50/60
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
A combustor section is provided for a gas turbine engine. The combustor section may include an outer liner panel, an inner liner panel and a bulkhead, which is arranged with the outer and the inner liner panels to form an annular combustion chamber. The combustor section may also include a swirler assembly and a combustor vane. The swirler assembly may be configured with the bulkhead. The combustor vane may extend at least partially into said combustion chamber, wherein the combustor vane is circumferentially aligned with the swirler assembly.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.