Bypass air injection method and apparatus for gas turbines
US6449956B1 · kind B1 · utility
11Cited by
5References
8Claims
0Family size
Assignee
Inventors
Key dates
| Filing date | Apr 9, 2001 |
| Grant date | Sep 17, 2002 |
| Priority date | — |
| Expiry date | Apr 9, 2021 |
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.