[특허]Rotor with cooling passage

Rolls-Royce Corporation

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특허 상세정보

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Rotor with cooling passage

특허상세정보
국가/구분	United States(US) Patent 등록
국제특허분류(IPC7판)	F01D-005/08
출원번호	US-0335708 (2011-12-22)
등록번호	US-9091172 (2015-07-28)
발명자 / 주소	Wolfgram, Christopher Otero, David A. Smith, Daniel G. Westphal, Bill
출원인 / 주소	Rolls-Royce Corporation
대리인 / 주소	Krieg DeVault LLP
인용정보	피인용 횟수 : 0 인용 특허 : 21

초록

A gas turbine engine is disclosed having a cooling passage that rotates with a turbine and is capable of providing cooling flow to the turbine. In one embodiment the cooling passage can receive cooling flow from an interior of a shaft of the gas turbine engine and increase the pressure of the cooling flow before delivering it to a location near a blade of the turbine. In one form the cooling passage can have an inducer section. In one form the cooling passage can have internal vanes useful in increasing the pressure of the cooling flow.

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1. An apparatus comprising: a gas turbine engine having a compressor rotatably coupled to a turbine with a spool shaft;a flow path formed internal to the spool shaft structured to provide a working fluid to the turbine;a cooling flow path coupled to a turbine rotor and rotatable therewith, the cooling flow path having an inlet for receiving the working fluid from the flow path internal to the spool shaft and an outlet for delivering the working fluid to suppress temperatures of the turbine rotor;wherein the cooling flow path radially extends from an inner portion of the turbine rotor and is bounded by an axially forward cooling flow path portion and an axially aft cooling flow path portion, the axially forward cooling flow path portion and axially aft cooling flow path portion being separate components from one another, and the axially forward cooling flow path portion and the axially aft cooling flow path portion separate from the turbine rotor and located on a common side of the turbine rotor; andwherein the cooling flow path is coupled to an axially aft portion of the turbine rotor. 2. The apparatus of claim 1, wherein the cooling flow path is structured to increase the pressure of the working fluid between the inlet and the outlet. 3. The apparatus of claim 2, which further includes an inducer that receives working fluid from the flow path internal to the spool shaft, the inducer structured to rotate with the cooling flow path. 4. The apparatus of claim 1, wherein the outlet of the cooling flow path provides the working fluid to a rim of the turbine rotor. 5. The apparatus of claim 1, wherein the working fluid provided to the flow path formed internal to the spool shaft is taken from a flow stream downstream of a rotatable turbomachinery component. 6. The apparatus of claim 1, wherein the turbine rotor is made from one of titanium, nickel, an alloy of titanium, and an alloy of nickel. 7. The apparatus of claim 1, which further includes a passageway cover coupled to a radially outer portion of the turbine rotor and structured to close a passageway that is fed with cooling air from the cooling flow path and the extends from an axially aft portion of the turbine rotor to an axially forward portion of the turbine rotor, the passageway cover located on an opposite side of the turbine rotor from the cooling passageway. 8. The apparatus of claim 1, wherein the flow path includes a flow path turn structured to change direction of the flow path from a radial direction to an axial direction, and wherein the a flow path turn is at the same radial height as the outlet. 9. An apparatus comprising: a gas turbine engine having a turbine rotor that includes a plurality of blades disposed in a flow path of the gas turbine engine operable to extract work from a working fluid traversing the flow path, the turbine rotor having a first passageway from an axial forward side to an axial aft side of the turbine rotor;a cooling flow path that rotates with the turbine rotor and receives cooling fluid from the first passageway and delivers it to a location radially outward of the passageway at a delivery radial station;wherein the cooling flow path radially extends from an inner portion of the turbine rotor and is bounded by an axially forward cooling flow path portion and an axially aft cooling flow path portion, the axially forward cooling flow path portion and the axially aft cooling flow path portion located on an aft side of the turbine rotor, the axially forward cooling flow path portion and the axially aft cooling flow path portion offset from the turbine rotor;wherein the cooling flow path turns the flow from a radial direction to an axial direction prior to delivering the cooling fluid to the location, the flow path turned at the delivery radial station of the location; andwherein the axially forward cooling flow path portion and axially aft cooling flow path portion are separate components that have been fastened to one another. 10. The apparatus of claim 9, wherein the plurality of blades have a different coefficient of thermal expansion than the turbine rotor, and the turbine rotor is made from a titanium alloy. 11. The apparatus of claim 9, wherein the cooling flow path includes components made from a titanium alloy, nickel alloy, or both. 12. The apparatus of claim 9, wherein the cooling flow path is mechanically fastened to the turbine rotor. 13. The apparatus of claim 12, wherein the cooling flow path is structured to increase the pressure of the cooling fluid delivered to the location of the turbine rotor. 14. The apparatus of claim 13, wherein the cooling fluid is delivered to the cooling flow path via a spool shaft having an open interior, the spool shaft rotatably connecting the turbine rotor to a compressor. 15. The apparatus of claim 14, wherein the first passageway of the turbine rotor is connected to the spool shaft. 16. The apparatus of claim 9, wherein the turbine rotor is cantilevered from a bearing disposed axially forward of the turbine rotor. 17. The apparatus of claim 9, which further includes a passageway cover coupled to a radially outer portion of the turbine rotor and structured to close a second passageway that extends from an axially aft portion of the turbine rotor to an axially forward portion of the turbine rotor, the passageway cover located on an opposite side of the turbine rotor from the cooling flow path. 18. A method comprising: operating a gas turbine engine to provide a flow of working fluid;conveying a cooling fluid internally within a rotatable shaft connected to a turbine of the gas turbine engine, the cooling fluid traversing from an upstream side of a rotor to a downstream side of a rotor during the conveying; andafter the conveying, flowing the cooling fluid through an annular flow path having an axially forward portion coupled to an axially aft portion which are both located on the downstream side and offset from a rotor, the flowing proceeding to a location radially outward of the rotatable shaft where it is turned to flow axially before encountering a blade of the turbine. 19. The method of claim 18, which further includes extracting a portion of the working fluid from a flow downstream of a compressor, the extraction forming the cooling fluid. 20. The method of claim 18, which further includes directing the cooling fluid to flow internally within a blade connected to the rotor, the flowing including delivering the cooling fluid near a rim of the rotor. 21. The method of claim 18, which further includes pressurizing the cooling fluid as a result of the flowing. 22. The method of claim 18, which further includes turning the cooling fluid from an axially aft direction to a radially outward direction, the turning occurring axially aft of the rotor. 23. The method of claim 22, wherein the turning occurs with the rotation of the turbine. 24. The apparatus of claim 18, which further includes covering a radially outer portion of the rotor such that the cover closes a passageway that is fed with cooling air from the annular flow path, the covering located on an opposite side of the rotor from the annular flow path.

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Rotor with cooling passage

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Rotor with cooling passage

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