Gas turbine combustor including burner having plural gaseous fuel manifolds
US9650961B2 · kind B2 · utility
3Cited by
3References
6Claims
0Family size
Assignee
Inventors
Key dates
| Filing date | Nov 15, 2013 |
| Grant date | May 16, 2017 |
| Priority date | — |
| Expiry date | Apr 28, 2035 |
Classification
- Technology area (CPC F)Mechanical Engineering; Lighting; Heating
- CPC primaryF23R2900/00018
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
A gas turbine combustor includes: multiple gaseous fuel nozzles to inject gaseous fuel; a manifold to distribute gaseous fuel to the multiple gaseous fuel nozzles; a burner flange to secure a burner to an end cover; and a burner body to connect the manifold and the burner flange. Gaseous fuel passages are provided in the end cover, the burner flange, and the burner body. The gaseous fuel passage communicates with the manifold. A second manifold is provided in the burner flange. The gaseous fuel passage is provided in the burner body to make the second manifold communicate with the first mentioned manifold.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.