Gas turbine engine
US6968698B2 · kind B2 · utility
Assignee
Inventors
Key dates
| Filing date | May 15, 2003 |
| Grant date | Nov 29, 2005 |
| Priority date | — |
| Expiry date | Dec 26, 2023 |
Classification
- Technology area (CPC F)Mechanical Engineering; Lighting; Heating
- CPC primaryF02C7/1435
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
A gas turbine engine (10) comprises a second compressor (14), a first compressor (16), a heat exchanger (18), a combustor (20), a first turbine (22), a second turbine (24) and a third turbine (26) arranged in flow series. The first turbine (22) is arranged to drive the first compressor (16). The second turbine (24) is arranged to drive the second compressor (14). There are means to inject liquid into the gas turbine engine (10). The means to inject liquid is arranged to inject liquid upstream (46) of the second compressor (14), within (48) the second compressor (14), between (50) the second compressor (14) and the first compressor (16), within (52) the first compressor (16), between (54) the first compressor (16) and the heat exchanger (18) or within (56) the combustor (20) to boost the power of the gas turbine engine (10). The means to inject liquid is arranged to inject liquid between (70) the combustor (20) and the first turbine (22), within (68) the first turbine (22), between (66) the first turbine (22) and the second turbine (24), within (64) the second turbine (24), between (62) the second turbine (24) and the third turbine (26), within (60) the third turbine (26) or between…
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.