[특허]System and method for supporting a turbine shroud

General Electric Company

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특허 상세정보

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내보내기 페이스북 공유 트위터 공유 카카오톡 공유

System and method for supporting a turbine shroud

특허상세정보
국가/구분	United States(US) Patent 등록
국제특허분류(IPC7판)	F01D-011/16 F01D-011/22 F01D-005/12 F01D-009/04
출원번호	US-0825201 (2015-08-13)
등록번호	US-10132186 (2018-11-20)
발명자 / 주소	Shapiro, Jason David
출원인 / 주소	General Electric Company
대리인 / 주소	General Electric Company
인용정보	피인용 횟수 : 0 인용 특허 : 9

초록
▼

In one aspect the present subject matter is directed to a system for supporting a turbine shroud. The system includes a shroud support at least partially defining a first piston sleeve and a piston assembly having a first piston head disposed within the first piston sleeve and a second piston head coupled to the first piston head. The first piston head is slideably engaged with an inner surface of the first piston sleeve. The second piston head is slideably engaged with an inner surface of a second piston sleeve. The system also includes a turbine shroud that is fixedly connected to the piston assembly and that extends radially inwardly from the shroud support. The piston assembly provides for radially inward and radially outward movement of the turbine shroud in response to a change in a radial force applied to a hot side surface of the turbine shroud.

대표
청구항
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1. A system for supporting a turbine shroud, the system comprising: a shroud support, the shroud support at least partially defining a first piston sleeve therein;a piston assembly having a first piston head disposed within the first piston sleeve and a second piston head coupled to the first piston head, wherein the first piston head is slideably engaged with an inner surface of the first piston sleeve, wherein the second piston head is slideably engaged with an inner surface of a second piston sleeve; anda turbine shroud fixedly connected to the piston assembly and extending radially inwardly from the shroud support, wherein the piston assembly provides for radially inward and radially outward movement of the turbine shroud in response to a radially outward force applied to a hot side surface of the turbine shroud;wherein a first pressure chamber is at least partially defined within the shroud support between the first piston head and the second piston head, wherein the first pressure chamber is pressurized at a first pressure to provide a first radially inward force on a backside surface of the first piston head; andwherein a second end of the second piston sleeve is open and in fluid communication with a pressurized medium supply, wherein the pressurized medium supply is pressurized at a second pressure to provide a second radially inward force on the second piston head. 2. The system as in claim 1, wherein a sum of the first radial force and the second radial force is equal to the radial force applied to the hot side surface of the turbine shroud when the radially outward force is provided by combustion gases flowing across the hot side surface of the turbine shroud. 3. The system as in claim 1, wherein a sum of the first radial force and the second radial force is less than the radial force applied to the hot side surface of the turbine shroud when the radially outward force is provided by turbine rotor blade tips. 4. The system as in claim 1, wherein the second piston sleeve extends through a radially outer wall portion of the shroud support, wherein the second piston sleeve is in fluid communication with a pressurized medium supply. 5. The system as in claim 1, wherein the second piston sleeve extends radially through an outer casing that surrounds the shroud support, wherein the second piston sleeve is in fluid communication with a pressurized medium supply. 6. The system as in claim 1, wherein a radial pressure delta across the second piston head is the same as a radial pressure delta across the turbine shroud. 7. A system for supporting a turbine shroud, the system comprising: a shroud support, the shroud support at least partially defining a first piston sleeve therein;a piston assembly having a first piston head disposed within the first piston sleeve and a second piston head coupled to the first piston head, wherein the first piston head is slideably engaged with an inner surface of the first piston sleeve, wherein the second piston head is slideably engaged with an inner surface of a second piston sleeve; anda turbine shroud fixedly connected to the piston assembly and extending radially inwardly from the shroud support, wherein the piston assembly provides for radially inward and radially outward movement of the turbine shroud in response to a radially outward force applied to a hot side surface of the turbine shroud;wherein the first piston head includes at least one aperture, wherein the aperture provides for fluid flow through the first piston head towards a back side surface of the turbine shroud. 8. A system for supporting a turbine shroud, the system comprising: a shroud support, the shroud support at least partially defining a first piston sleeve therein;a piston assembly having a first piston head disposed within the first piston sleeve and a second piston head coupled to the first piston head, wherein the first piston head is slideably engaged with an inner surface of the first piston sleeve, wherein the second piston head is slideably engaged with an inner surface of a second piston sleeve; anda turbine shroud fixedly connected to the piston assembly and extending radially inwardly from the shroud support, wherein the piston assembly provides for radially inward and radially outward movement of the turbine shroud in response to a radially outward force applied to a hot side surface of the turbine shroud;wherein the shroud support defines a first pressure chamber between the first piston head and an intermediate wall portion of the shroud support and a second pressure chamber defined between the intermediate wall and a radially outer wall portion of the shroud support, wherein the second piston sleeve extends radially through the intermediate wall and is open to the second pressure chamber. 9. A system for supporting a turbine shroud, the system comprising: a shroud support;a piston assembly having a first piston head fixedly connected to an inner surface of the shroud support and a second piston head coupled to the first piston head, wherein the second piston head is slideably engaged with an inner surface of a piston sleeve that extends through an outer casing; anda turbine shroud fixedly connected to the piston assembly and extending radially inwardly from the shroud support, wherein the piston assembly provides for movement of the turbine shroud in response to a change in a radially outward force applied to a hot side surface of the turbine shroud;wherein a first pressure chamber is at least partially defined within the shroud support between the first piston head and the second piston head, wherein the first pressure chamber is pressurized at a first pressure to provide a first radially inward force on a backside surface of the first piston head; andwherein one end of the piston sleeve is open and in fluid communication with a pressurized medium supply, wherein the pressurized medium supply is pressurized at a second pressure to provide a second radially inward force on the second piston head. 10. The system as in claim 9, wherein a radial pressure delta across the second piston head is substantially the same as a radial pressure delta across the turbine shroud. 11. The system as in claim 9, wherein a sum of the first radial force and the second radial force is equal to the radial force applied to the hot side surface of the turbine shroud when the radially outward force is provided by combustion gases flowing across the hot side surface of the turbine shroud. 12. The system as in claim 9, wherein a sum of the first radial force and the second radial force is less than the radial force applied to the hot side surface of the turbine shroud when the radially outward force is provided by turbine rotor blade tips. 13. A system for supporting a turbine shroud, the system comprising: a shroud support, the shroud support at least partially defining a first piston sleeve therein;a piston assembly having a first piston head disposed within the first piston sleeve and a second piston head coupled to the first piston head, wherein the first piston head is slideably engaged with an inner surface of the first piston sleeve, wherein the second piston head is slideably engaged with an inner surface of a second piston sleeve; anda turbine shroud fixedly connected to the piston assembly and extending radially inwardly from the shroud support, wherein the piston assembly provides for radially inward and radially outward movement of the turbine shroud in response to a radially outward force applied to a hot side surface of the turbine shroud;wherein the first piston head includes at least one aperture, wherein the aperture provides for fluid flow through the first piston head towards a back side surface of the turbine shroud. 14. A method for supporting a turbine shroud, wherein the turbine shroud is fixedly connected to a piston assembly, wherein the piston assembly includes a first piston head connected to the turbine shroud and disposed within a first pressure chamber and a second piston head linked to the first piston head and disposed between the first pressure chamber and a second pressure chamber, wherein a hot side surface of the turbine shroud is directed towards a hot gas path of a turbine, the method comprising: pressurizing the first pressure chamber with a first pressurized medium so as to provide a first radial force against a backside to the first piston head;pressurizing the second pressure chamber with a second pressurized medium so as to provide a second radial force against the second piston head;wherein the turbine shroud is held in a first position by the piston assembly when a sum of the first radial force and the second radial force is substantially equal to a radially outward force applied to the hot side surface of the turbine shroud; andwherein the turbine shroud moves to second position when the sum of first radial force and the second radial force is less than the radially outward force applied to the hot side surface of the turbine shroud. 15. The method as in claim 14, further comprising adjusting pressure in at least one of the first pressure chamber and the second pressure chamber to maintain equilibrium between the sum of the first radial force and the second radial force and the radially outward force applied to the hot side of the turbine shroud by combustion gases. 16. The method as in claim 14, further comprising adjusting the pressure in at least one of the first pressure chamber and the second chamber to increase, decrease or to maintain a radial gap between the turbine rotor blade tip and the hot side of the turbine shroud.

이 특허에 인용된 특허 (9)

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특허 상세정보

System and method for supporting a turbine shroud

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System and method for supporting a turbine shroud

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이 특허에 인용된 특허 (9)

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