Inner turbine shell support configuration and methods
원문보기
IPC분류정보
국가/구분 |
United States(US) Patent
등록
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국제특허분류(IPC7판) |
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출원번호 |
US-0049665
(2008-03-17)
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등록번호 |
US-8182207
(2012-05-22)
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발명자
/ 주소 |
- Ballard, Jr., Henry G.
- Ellis, Scott E.
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출원인 / 주소 |
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대리인 / 주소 |
Sutherland Asbill & Brennan LLP
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인용정보 |
피인용 횟수 :
4 인용 특허 :
10 |
초록
▼
Embodiments of the present disclosure relate to a turbine which includes an outer shell, an inner shell connected to and surrounded by the outer shell in generally concentric relation therewith, at least one turbine rotor housed within the inner shell, a plurality of nozzles and shrouds carried by t
Embodiments of the present disclosure relate to a turbine which includes an outer shell, an inner shell connected to and surrounded by the outer shell in generally concentric relation therewith, at least one turbine rotor housed within the inner shell, a plurality of nozzles and shrouds carried by the inner shell, a plurality of connecting elements engaging between the inner and outer shells aligning the inner shell about the rotor, and at least one compliant support. Embodiments of the present disclosure also relates a method of configuring the securing arrangement between the inner shell and the outer shell of a turbine.
대표청구항
▼
1. A turbine comprising: an outer shell;an inner shell connected to and surrounded by the outer shell in generally concentric relation therewith;at least one turbine rotor housed within the inner shell;a plurality of nozzles and shrouds carried by the inner shell;a plurality of connecting elements e
1. A turbine comprising: an outer shell;an inner shell connected to and surrounded by the outer shell in generally concentric relation therewith;at least one turbine rotor housed within the inner shell;a plurality of nozzles and shrouds carried by the inner shell;a plurality of connecting elements engaging the inner and outer shells and aligning the inner shell about the rotor, at least two of the connecting elements lying along a horizontal split line of the inner shell;a plurality of recesses spaced circumferentially about the inner shell receiving portions of the connecting elements;a first circumferential clearance between each recess and connecting element in the direction of the applied torque loading generated by the nozzles;a second circumferential clearance between each recess and connecting element in the direction of the counteracting torque loading; andat least one compliant support disposed between at least one of the connecting elements and the recess being exposed to gravitational and counteracting torque loadings in opposite directions such that the sum of the first circumferential clearance and second first circumferential clearance is greater than about 0 mils. 2. The turbine of claim 1, further comprising: at least two radial outward projections protruding in opposite directions from the inner shell along a horizontal split line of the inner shell, andat least two brackets on the outer shell along the horizontal split line of the inner shell for receiving the portions of the at least two radial outward projections from the inner shell. 3. The turbine of claim 2, further comprising a first circumferential clearance between each bracket and radial outward projection in the direction of the applied torque loading generated by the nozzles and a second circumferential clearance between each bracket and radial outward projection in the direction of the counteracting torque loading. 4. The turbine of claim 3, wherein the compliant support is disposed between the radial outward projection and bracket being exposed to gravitational and counteracting torque loadings in opposite directions such that the sum of the first circumferential clearance and second circumferential clearance is greater than about 0 mils. 5. The turbine of claim 4, wherein the first circumferential clearance is about 13 mils. 6. The turbine of claim 5, wherein the second circumferential clearance is about 0 mils. 7. The turbine of claim 1, wherein the first circumferential clearance is about 13 mils. 8. The turbine of claim 7, wherein the second circumferential clearance is about 0 mils. 9. The turbine of claim 1, wherein the compliant support comprises a spring, bellows, crest spring, wave spring, or biasing device. 10. The turbine of claim 9, wherein the spring is comprised of a material selected from the group consisting of ferrous and nonferrous alloys. 11. The turbine of claim 1, wherein the connecting elements have circumferentially facing arcuate sides for engaging the inner shell. 12. The turbine of claim 11, wherein the arcuate sides contact the inner shell along surfaces whose planer faces are directed radially to a centerline of the rotor. 13. A turbine comprising: an outer structural shell;an inner shell connected to and surrounded by the outer structural shell in generally concentric relation therewith, wherein the inner shell has a plurality of recesses spaced circumferentially thereabout;a plurality of nozzles and shrouds carried by the inner shell;at least one turbine rotor housed within the inner shell;a plurality of pins engaging the inner and outer shells and aligning the inner shell about the rotor, wherein a portion of each pin engages each recess with a first circumferential clearance in the direction of the applied torque loading generated by the nozzles and a second circumferential clearance in the direction of the counteracting torque loading;at least two radial outward projections protruding in opposite directions from the inner shell along a horizontal split line of the inner shell and at least two brackets on the outer shell along the horizontal split line of the inner shell for receiving the portions of the at least two radial outward projections from the inner shell, each radial outward projection and bracket having a third circumferential clearance in the direction of the applied torque loading generated by the nozzles and a fourth circumferential clearance in the direction of the counteracting torque loading; andat least one spring disposed between at least one of the radial outward projections and at least one of the brackets to maintain the third circumferential clearance at greater than about 0 mils. 14. A method of configuring a turbine comprising: providing an outer shell with at least two brackets;providing an inner shell with a plurality of recesses spaced circumferentially thereabout, the inner shell connected to and surrounded by the outer shell in generally concentric relation therewith by a plurality of connecting elements;providing a plurality of nozzles and shrouds carried by the inner shell;providing at least one turbine rotor housed within the inner shell;engaging the plurality of recesses with a plurality of pins, wherein each recess receives a portion of each pin and comprises a first circumferential clearance in the direction of the applied torque loading generated by the nozzles and a second circumferential clearance in the direction of the counteracting torque loading;engaging two brackets of the outer shell with two radial outward projections of the inner shell protruding in opposite directions along a horizontal splitline of the rotor during turbine assembly, wherein each bracket receives a portion of the radial outward projection and comprises a third circumferential clearance in the direction of the applied torque loading generated by the nozzles and a fourth circumferential clearance in the direction of the counteracting torque loading; anddisposing a compliant support between at least one of the brackets and radial outward projections to maintain the third circumferential clearance at greater than about 0 mils. 15. The method of claim 14, wherein the compliant support comprises a spring, bellows, crest spring, wave spring, or biasing device. 16. The method of claim 14, wherein the connecting elements have circumferentially facing arcuate sides engaging the inner shell along line contacts whose planer faces are directed radially to a centerline of the rotor.
이 특허에 인용된 특허 (10)
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Donlan John P. (Ovideo FL), Apparatus and method for supporting a vane segment in a gas turbine.
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Leach David ; Bergendahl Peter Allen ; Waldo Stuart Forrest ; Smith Robert Leroy ; Phelps Robert Kim, Apparatus and methods for installing, removing and adjusting an inner turbine shell section relative to an outer turbine shell section.
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Beckershoff ; Wolfgang, Apparatus for positioning coaxial arranged machine parts.
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Schwarz Hans (Umiken CHX), Externally adjustable axial location for a vane carrier in a turbine.
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Remberg Axel (Mulheim DT), High pressure double flow turbine construction.
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David Leach ; Peter Allen Bergendahl, Inner shell radial pin geometry and mounting arrangement.
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Donlan John P. (Aston PA) Krauss Alfred R. (Oak Valley NJ), Locking structure for an alignment bushing of a combustion turbine engine.
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McLaurin Leroy D. (Winter Springs FL) Williams Roland E. (Altamonte Springs FL) Donlan John P. (Oviedo FL) Hultgren Kent G. (Swarthmore PA), Method and apparatus for vane segment support and alignment in combustion turbines.
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Sexton Brendan F. ; Knuijt Hans M. ; Eldrid Sacheverel Q. ; Myers Albert ; Coneybeer Kyle E. ; Johnson David Martin ; Kellock Iain R., Removable inner turbine shell with bucket tip clearance control.
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McLaurin Leroy Dixon ; Sizemore John Derek, Vane segment support and alignment device.
이 특허를 인용한 특허 (4)
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Casavant, Matthew Stephen, Assembly for aligning an inner shell of a turbine casing.
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Gerzner, Stefan; Rauch, Marc; Vogt, Ernst; Lopez, Jose-Manuel, Pullable drawer for a turbine and turbine with such a drawer.
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Niitsu, Toshihiro; Sagayama, Akira; Suzuki, Hirokazu; Matsuzaka, Osamu; Sato, Yoshinobu; Sagayama, Kota; Morioka, Nobuhide; Shibata, Yusuke, Sheet connector having a terminal protruding from a conductive pattern on a substrate to engage a terminal of another connector.
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Shapiro, Jason David, System and method for supporting a turbine shroud.
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