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 sec
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 (72) the third turbine (26) and the heat exchanger (18) to reduce the power of the gas turbine engine (10).
대표청구항▼
The invention claimed is: 1. A gas turbine engine comprising at least one compressor, a combustor and at least one turbine arranged in flow series, the at least one turbine being arranged to drive the at least one compressor, means to inject cooling liquid into the gas turbine engine while the gas
The invention claimed is: 1. A gas turbine engine comprising at least one compressor, a combustor and at least one turbine arranged in flow series, the at least one turbine being arranged to drive the at least one compressor, means to inject cooling liquid into the gas turbine engine while the gas turbine engine is decelerating, the means to inject cooling liquid being arranged to inject cooling liquid within the combustor, between the combustor and the at least one turbine or within the at least one turbine wherein the gas turbine engine also comprises a heat exchanger, the means to inject cooling liquid being arranged to inject cooling liquid within the heat exchanger. 2. A gas turbine engine comprising at least one compressor, a combustor and at least one turbine arranged in flow series, the at least one turbine being arranged to drive the at least one compressor, means to inject cooling liquid into the gas turbine engine while the gas turbine engine is decelerating, the means to inject cooling liquid being arranged to inject cooling liquid within the combustor, between the combustor and the at least one turbine wherein the gas turbine engine further comprises a heat exchanger and the at least one compressor comprising a first compressor and a second compressor being arranged upstream of the first compressor, the at least one turbine comprising a first turbine and a second turbine arranged downstream of the first turbine, the first turbine being arranged to drive the first compressor and the second turbine being arranged to drive the second compressor. 3. A gas turbine engine as claimed in claim 2 wherein the at least one turbine comprises a third turbine arranged downstream of the second turbine. 4. A gas turbine engine as claimed in claim 3 wherein the third turbine is arranged to drive an output shaft. 5. A gas turbine engine as claimed in claim 1 wherein the at least one turbine comprises a second turbine arranged downstream of the first turbine. 6. A gas turbine engine as claimed in claim 5 wherein the second turbine is arranged to drive the output shaft. 7. A gas turbine engine as claimed in claim 2 wherein the means to inject cooling liquid is arranged to inject cooling liquid between the combustor and the first turbine, within the first turbine or between the first turbine and the heat exchanger while the gas turbine engine is decelerating. 8. A gas turbine engine as claimed in claim 2 wherein the means to inject cooling liquid is arranged to inject cooling liquid between the first turbine and the second turbine, within the second turbine, within the first turbine or between the second turbine and the heat exchanger while the gas turbine engine is decelerating. 9. A gas turbine engine as claimed in claim 2 wherein the means to inject cooling liquid is arranged to inject cooling liquid upstream of the first compressor, within the first compressor or between the first compressor and the heat exchanger while the gas turbine engine is accelerating. 10. A gas turbine engine as claimed in claim 2 wherein the means to inject cooling liquid is arranged to inject cooling liquid at one of within the first compressor, within the second compressor, upstream of the second compressor, and between the first compressor and the second compressor while the gas turbine engine is accelerating. 11. A gas turbine engine as claimed in claim 3 wherein the means to inject cooling liquid is arranged to inject cooling liquid between the second turbine and the third turbine, within the third turbine or between the third turbine and the heat exchanger while the gas turbine engine is decelerating. 12. A gas turbine engine as claimed in claim 1 wherein the cooling liquid is water.
연구과제 타임라인
LOADING...
LOADING...
LOADING...
LOADING...
LOADING...
이 특허에 인용된 특허 (3)
Kidd Harry A. (Shinglehouse PA), Constant NOxcontrol for gas turbine.
※ AI-Helper는 부적절한 답변을 할 수 있습니다.