Method and apparatus for compressing gaseous fuel in a turbine engine
US6381944B2 · kind B2 · utility
13Cited by
5References
10Claims
0Family size
Assignee
Inventor
Key dates
| Filing date | Jan 29, 2001 |
| Grant date | May 7, 2002 |
| Priority date | — |
| Expiry date | Jan 29, 2021 |
Classification
- Technology area (CPC F)Mechanical Engineering; Lighting; Heating
- CPC primaryF02C3/22
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
A gas turbine engine includes a rotatable impeller having a plurality of vanes with inlet and outlet ends. A plurality of diffuser channels are spaced apart radially beyond the outlet ends. A movable source of gaseous fuel is positioned adjacent the inlet ends of the vanes. The movable source of gaseous fuel is movable as a function of the rotational speed of the impeller, whereby the flow of gaseous fuel injected from the movable source is ejected from the outlet ends of the vanes into a selected one of the plurality of diffuser channels to facilitate combustion.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.