Bypass air injection method and apparatus for gas turbines
US6568188B2 · kind B2 · utility
11Cited by
8References
9Claims
0Family size
Assignee
Inventors
Key dates
| Filing date | Jul 26, 2002 |
| Grant date | May 27, 2003 |
| Priority date | — |
| Expiry date | Jul 26, 2022 |
Classification
- Technology area (CPC F)Mechanical Engineering; Lighting; Heating
- CPC primaryF23R3/40
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
A bypass air injection scheme for a combustor of a gas turbine. Combustor includes a body with an inner liner and a casing enclosing the body with a passageway defined therebetween. A predetermined amount of the compressor discharge air passing through the passageway is extracted through a manifold. A conduit feeds the extracted air into an injection manifold having a plurality of injection tubes for injecting the extracted air into the combustor bypassing the reactor. The injection tubes and the injection manifold are disposed in a substantially common axial plane.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.