IPC분류정보
국가/구분 |
United States(US) Patent
등록
|
국제특허분류(IPC7판) |
|
출원번호 |
US-0495495
(2006-07-28)
|
등록번호 |
US-8220245
(2012-07-17)
|
발명자
/ 주소 |
|
출원인 / 주소 |
- Candent Technologies, Inc.
|
대리인 / 주소 |
Edwards Wildman Palmer LLP
|
인용정보 |
피인용 횟수 :
18 인용 특허 :
10 |
초록
▼
A gas turbine engine is provided, including an air inlet in fluid communication with a compressor, a combustor, a compressor turbine, and a power turbine. The compressor and compressor turbine may be mounted on a first drive shaft, and the power turbine may be mounted on a second shaft. The engine f
A gas turbine engine is provided, including an air inlet in fluid communication with a compressor, a combustor, a compressor turbine, and a power turbine. The compressor and compressor turbine may be mounted on a first drive shaft, and the power turbine may be mounted on a second shaft. The engine further includes an engagement mechanism adapted to selectively engage the first drive shaft to the second drive shaft, wherein the first drive shaft and second drive shaft rotate at substantially the same speed when the engagement mechanism is engaged. The disclosed multi-spool gas turbine engine provides improved part power fuel consumption at reduced output shaft speeds. The proposed invention can relate to turbines with two or more gas generator spools.
대표청구항
▼
1. A gas turbine engine, comprising: a) an air inlet;b) a low pressure compressor downstream from and in fluid communication with the air inlet for compressing air traversing the air inlet;c) a combustor downstream from and in fluid communication with the low pressure compressor for combusting a fue
1. A gas turbine engine, comprising: a) an air inlet;b) a low pressure compressor downstream from and in fluid communication with the air inlet for compressing air traversing the air inlet;c) a combustor downstream from and in fluid communication with the low pressure compressor for combusting a fuel mixture;d) a low pressure turbine downstream from and in fluid communication with the combustor, the low pressure turbine operably connected to the low pressure compressor by a first drive shaft, the low pressure turbine being adapted to generate power from a combusted fuel mixture passing therethrough to power the low pressure compressor;e) a power turbine downstream from and in fluid communication with the combustor and the low pressure turbine, the power turbine being adapted to generate power to power a load external to the engine, the power turbine mounted on a second drive shaft;f) an engagement mechanism adapted to selectively engage the first drive shaft to the second drive shaft, wherein the first drive shaft and second drive shaft rotate at substantially the same speed when the engagement mechanism is engaged, wherein the low pressure turbine and power turbine have an aerodynamic design speed such that the power turbine produces power at substantially a same speed as the low pressure turbine, thereby allowing the low pressure turbine to provide power to the output shaft when the low pressure and power turbines are selectively coupled by the engagement mechanism;g) a high pressure compressor downstream from and in fluid communication with the low pressure compressor; andh) a high pressure turbine downstream from and in fluid communication with the combustor, the high pressure turbine operably connected to the high pressure compressor by a third drive shaft, the high pressure turbine being adapted to generate power from a combusted fuel mixture passing therethrough to power the high pressure compressor. 2. The gas turbine engine of claim 1, wherein the engagement mechanism is a clutch. 3. The gas turbine engine of claim 2, wherein the clutch includes: a) a first engagement dog including a first plurality of splines affixed to the first drive shaft; andb) a second engagement dog including a second plurality of splines affixed to the second drive shaft, wherein the first plurality of splines and second plurality of splines intermesh when the clutch is in an engaged condition. 4. The gas turbine engine of claim 2, wherein the clutch includes at least one clutch plate adapted and configured to engage at least one pressure plate to couple the first drive shaft to the second drive shaft. 5. The gas turbine engine of claim 2, wherein the clutch is a hydraulic clutch. 6. The gas turbine engine of claim 1, wherein the engagement mechanism allows a controlled amount of slippage between the first drive shaft and the second drive shaft when the engagement mechanism is engaged. 7. The gas turbine engine of claim 1, wherein the first drive shaft and second drive shaft rotate about substantially the same axis of rotation. 8. The gas turbine engine of claim 7, wherein the first drive shaft, second drive shaft and third drive shaft all rotate about substantially the same axis of rotation. 9. The gas turbine engine of claim 7, wherein the first drive shaft and second drive shaft rotate about a first axis of rotation and the third drive shaft rotates about a second axis of rotation different from the first axis of rotation. 10. The gas turbine engine of claim 9, wherein the second axis of rotation is substantially parallel to the first axis of rotation. 11. The gas turbine engine of claim 9, wherein the second axis of rotation is substantially perpendicular to the first axis of rotation. 12. The gas turbine engine of claim 1, further comprising a control system adapted to control fuel flowing to the combustor in relation to the demand of an operator, the control system being further adapted to control the engine in response to at least one of: i) at least one signal representative of the speed of the first drive shaft and second drive shaft; andii) the temperature of gases flowing through the engine. 13. The gas turbine engine of claim 12, wherein the control system includes a machine readable program tangibly embodied on a computer readable medium, the program containing instructions for controlling the engagement and disengagement of the engagement mechanism based on the operating condition of the engine. 14. The gas turbine engine of claim 12, wherein the control system is adapted to operate the engine in a first operating mode wherein the engagement mechanism is disengaged, and a second operating mode wherein the engagement mechanism is engaged. 15. The gas turbine engine of claim 14, wherein the operator can manually specify when the engine changes between the first operating mode and the second operating mode. 16. The gas turbine engine of claim 1, further comprising a heat exchanger disposed between and in fluid communication with the low pressure compressor and the high pressure compressor, the heat exchanger being adapted to remove heat from fluid passing from the low pressure compressor to the high pressure compressor. 17. The gas turbine engine of claim 1, further comprising a heat exchanger adapted to direct heat from the exhaust of the engine to fluid leaving the high pressure compressor.
※ AI-Helper는 부적절한 답변을 할 수 있습니다.