[특허]Blade tip clearance control apparatus using shroud segment annular support ring thermal expansion

Blade tip clearance control apparatus using shroud segment annular support ring thermal expansion 원문보기

IPC분류정보
국가/구분	United States(US) Patent 등록
국제특허분류(IPC7판)	F01D-005/20
출원번호	US-0630651 (1990-12-20)
발명자 / 주소	Ciokajlo John J. (Cincinnati OH)
출원인 / 주소	General Electric Company (Cincinnati OH 02)
인용정보	피인용 횟수 : 41 인용 특허 : 0

초록 ▼

An apparatus for controlling clearance between rotor blade tips and shroud segments of a turbine engine casing includes an annular channel extending about the blade tips and having an annular opening located outwardly of and adjacent the blade tips, and separate shroud segments composing the shroud and disposed across the channel opening in circumferential spaced relation. Inlet and outlet tubular members mounted to the casing have inner portions projecting radially inwardly into the annular channel. An annular hollow ring disposed in the annular channel mounts the shroud segments across the channel opening and are mounted to the tubular member inner portions for undergoing movement radially outwardly and inwardly relative to the inner portions in response to thermal expansion and contract of the annular ring. Tubular inlet members introduce a cooling gas into the annular channel from the exterior and tubular outlet members exhausts the cooling gas from the annular channel to the exterior. Hollow manifolds disposed within the annular channel in the annular ring are connected with the inner portions of the tubular inlet members for receiving cooling air. Each manifold has jet-like apertures permitting impingement of cooling air upon the annular ring. After such impingement, the cooling air can flow from the annular ring through the tubular outlet members to the exterior.

대표청구항 ▼

In a gas turbine engine including a rotatable rotor having a central axis and a row of blades with outer tips and a stationary casing with a shroud disposed in concentric relation with said rotor, said rotor blade tips and casing shroud having a clearance therebetween, an apparatus for controlling the clearance between said rotor blade tips and casing shroud, said apparatus comprising: (a) structural means on said casing disposed radially outwardly of said rotor blade tips for defining an annular channel extending in circumferential relation to said rotor central axis about said rotor blade tips and having an annular opening located outwardly of and adjacent to said rotor blade tips; (b) at least one shroud segment disposed across said opening of said annular channel; (c) means mounted on said casing for introducing a cooling gas flow into said annular channel from the exterior thereof and means mounted on said casing for exhausting the cooling gas flow from said annular channel to the exterior thereof; (d) an annular hollow ring disposed in said annular channel and extending in circumferential relation to said rotor central axis, said annular ring mounting said shroud segment across said opening of said channel and, in turn, being mounted to and in communication with said introducing means and exhausting means for undergoing movement radially outwardly and inwardly relative the rotor blade tips and to said introducing means and exhausting means in response to thermal expansion and contraction of said annular ring; and (e) at least one manifold having an elongated hollow body disposed within said annular hollow ring in said annular channel and being connected at the interior of said hollow body of said manifold in communication with only said introducing means for receiving the cooling gas flow into the interior of said hollow body of said manifold so as to prevent introduction of the cooling gas flow into said annular ring about the exterior of said hollow body directly from said gas introducing means without first passing through said interior of said hollow body, said hollow body of said manifold having a plurality of jet-like apertures defined through said hollow body for permitting communication of the cooling gas flow from the interior to the exterior of said hollow body and impingement of the cooling gas flow upon portions of said annular ring adjacent to said apertures and the exterior of said hollow body such that after such impingement the cooling gas can flow directly from said annular ring through said exhausting means to the exterior of said annular channel without again passing through said interior of said hollow body of said manifold.

이 특허를 인용한 특허 (41)

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Casavant, Matthew Stephen; Black, Kenneth Damon; Johnson, David Martin; Danescu, Radu Ioan, Gas turbine thermal control and related method.
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Little, David A.; Johnson, Clifford E., Impingement cooling arrangement having a snap-in plate.
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Dong,Zhifeng; Epstein,Michael J.; Royal,Glen William; Albers,Robert J., Methods and apparatus for maintaining rotor assembly tip clearances.
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Powell, Brad, Movable air seal for gas turbine engine.
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Wilson, Jr.,Jack W., Passive clearance control.
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Campbell, Christian X.; Keller, Douglas A.; Gonzalez, Malberto F., Pin-loaded mounting apparatus for a refractory component in a combustion turbine engine.
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Zhang, Hua; Erickson, Dean; Michalski, Michael; Seale, Jason; Childers, Priscilla, Predictive model based control system for heavy duty gas 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 and bucket tip clearance control.
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Sexton Brendan F. (Clifton Park NY) Knuijt Hans M. (Niskayuna NY) Eldrid Sacheverel Q. (Saratoga Springs NY) Myers Albert (Amsterdam NY) Coneybeer Kyle E. (Schenectady NY) Johnson David Martin (Balls, Removable inner turbine shell with bucket tip clearance control.
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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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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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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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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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Lewis, Leo V.; Bacic, Marko, Rotor blade tip clearance control.
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Gregory Alan White ; Ching-Pang Lee, Shroud cooling segment and assembly.
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Steven Sebastian Burdgick, Side wall cooling for nozzle segments for a gas turbine.
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O'Leary, Mark, Turbine blade tip clearance apparatus and method.
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Chehab, Abdullatif M., Turbine blade tip clearance control.
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O'Leary, Mark, Turbine blade tip clearance system.
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Erickson, Dean Matthew; Zhang, Hua; Seale, Jason, Turbine case impingement cooling for heavy duty gas turbines.
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Cunha Francisco J. ; DeAngelis David A. ; Brown Theresa A. ; Chopra Sanjay ; Correia Victor H. S. ; Predmore Daniel R., Turbine stator vane segments having combined air and steam cooling circuits.
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Blade tip clearance control apparatus using shroud segment annular support ring thermal expansion 원문보기

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Blade tip clearance control apparatus using shroud segment annular support ring thermal expansion 원문보기

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