Gas turbine with at least one multi-stage compressor unit including several compressor modules
원문보기
IPC분류정보
국가/구분 |
United States(US) Patent
등록
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국제특허분류(IPC7판) |
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출원번호 |
US-0486355
(2009-06-17)
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등록번호 |
US-8251639
(2012-08-28)
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우선권정보 |
DE-10 2008 028 883 (2008-06-18) |
발명자
/ 주소 |
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출원인 / 주소 |
- Rolls-Royce Deutchland Ltd Co KG
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대리인 / 주소 |
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인용정보 |
피인용 횟수 :
1 인용 특허 :
1 |
초록
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A gas turbine includes at least one multi-stage compressor unit 2, with the compressor unit 2 including several, independent compressor modules 3-5, which, independently of each other, are rotatably borne on a drive shaft 1 and are each engageable with the drive shaft 1 by at least one clutch unit 9
A gas turbine includes at least one multi-stage compressor unit 2, with the compressor unit 2 including several, independent compressor modules 3-5, which, independently of each other, are rotatably borne on a drive shaft 1 and are each engageable with the drive shaft 1 by at least one clutch unit 9-11.
대표청구항
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1. A gas turbine, comprising: a drive shaft having an axis about which it is rotatable;at least one multi-stage compressor unit having a plurality of independent compressor modules, which, independently of each other, are rotatably borne on the drive shaft, each independent compressor module includi
1. A gas turbine, comprising: a drive shaft having an axis about which it is rotatable;at least one multi-stage compressor unit having a plurality of independent compressor modules, which, independently of each other, are rotatably borne on the drive shaft, each independent compressor module including a compressor stage having a rotor with a plurality of rotor blades disposed circumferentially around the axis of the drive shaft;a respective clutch unit for each of the plurality of independent compressor modules by which each independent compressor module is engageable with the drive shaft such that the plurality of rotor blades of that independent compressor module is rotationally fixed to the drive shaft around the axis of the drive shaft and disengageable from the drive shaft such that the plurality of rotor blades of that independent compressor module is rotatable with respect to the drive shaft around the axis of the drive shaft. 2. The gas turbine of claim 1, wherein each independent compressor module includes a stator with a plurality of stator vanes. 3. The gas turbine of claim 2, wherein at least one of the independent compressor modules includes a plurality of compressor stages, each having a rotor with a plurality of rotor blades and a plurality of stators, each stator having a plurality of stator vanes. 4. The gas turbine of claim 3, wherein each clutch unit is independently engageable and disengageable. 5. The gas turbine of claim 4, wherein all of the independent compressor modules are independently engageable with and disengageable from the drive shaft. 6. The gas turbine of claim 5, wherein the multi-stage compressor unit is a high-pressure compressor of the gas turbine. 7. The gas turbine of claim 5, wherein the multi-stage compressor unit is a low-pressure compressor of the gas turbine. 8. The gas turbine of claim 1, wherein at least one of the independent compressor modules includes a plurality of compressor stages, each having a rotor with a plurality of rotor blades and a plurality of stators, each stator having a plurality of stator vanes. 9. The gas turbine of claim 1, wherein each clutch unit is independently engageable and disengageable. 10. The gas turbine of claim 1, wherein all of the independent compressor modules are independently engageable with and disengageable from the drive shaft. 11. The gas turbine of claim 1, wherein the multi-stage compressor unit is a high-pressure compressor of the gas turbine. 12. The gas turbine of claim 1, wherein the multi-stage compressor unit is a low-pressure compressor of the gas turbine. 13. A method for starting a gas turbine having a plurality of independent compressor modules rotatably borne on a drive shaft of the gas turbine, comprising: providing a respective clutch unit for each of the plurality of independent compressor modules by which each independent compressor module is engageable with and disengageable from the drive shaft;disengaging at least one of the plurality of independent compressor modules from the drive shaft to reduce a load on the drive shaft and allow the drive shaft to be accelerated at a faster rate;accelerating the drive shaft to a rotational speed sufficient for starting the gas turbine while the at least one of the plurality of independent compressor modules is disengaged from the drive shaft; andafter the gas turbine has been started, engaging the at least one of the plurality of independent compressor modules with the drive shaft when operating conditions require the gas turbine to operate at a higher load. 14. The method of claim 13 and further comprising engaging with the drive shaft only a minimum number of the independent compressor modules necessary to start the gas turbine while disengaging the remaining independent compressor modules from the drive shaft until after the gas turbine has started. 15. A method for operating a gas turbine having a plurality of independent compressor modules rotatably borne on a drive shaft of the gas turbine, comprising: providing a respective clutch unit for each of the plurality of independent compressor modules by which each independent compressor module is engageable with and disengageable from the drive shaft;disengaging at least one of the plurality of independent compressor modules from the drive shaft during partial load operation of the gas turbine; andengaging the at least one of the plurality of independent compressor modules with the drive shaft when operating conditions require the gas turbine to operate at a higher load. 16. The method of claim 15 wherein disengaging the at least one of the plurality of independent compressor modules from the drive shaft during partial load operation of the gas turbine causes the independent compressor modules that are engaged with the drive shaft to operate at higher stage compression ratios than if all of the independent compressor modules were engaged with the drive shaft. 17. The method of claim 16 and further comprising disengaging an increasing number of the independent compressor modules from the drive shaft as the operation load of the engine decreases.
이 특허에 인용된 특허 (1)
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Kern, John M.; De Bedout, Juan M.; Chung, Kiyoung; Waszak, Michal-Wolfgang; Shah, Manoj Ramprasad; Toot, Peter D.; Qu, Ronghai; Wu, Wei, Variable magnetic coupling of rotating machinery.
이 특허를 인용한 특허 (1)
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Ress, Jr., Robert A., Three spool gas turbine engine having a clutch and compressor bypass.
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