[특허]Shroud cooling assembly for gas turbine engine

Shroud cooling assembly for gas turbine engine 원문보기

IPC분류정보
국가/구분	United States(US) Patent 등록
국제특허분류(IPC7판)	F01D-005/18
출원번호	US-0702549 (1991-05-20)
발명자 / 주소	Proctor Robert (West Chester OH) Plemmons Larry W. (Fairfield OH) Brainch Gulcharan S. (West Chester OH) Hess John R. (West Chester OH) Albers Robert J. (Park Hills KY)
출원인 / 주소	General Electric Company (Cincinnati OH 02)
인용정보	피인용 횟수 : 70 인용 특허 : 0

초록 ▼

To cool the shroud in the high pressure turbine section of a gas turbine engine, high pressure cooling air is directed in metered flow to baffle plenums and thence through baffle perforations to impingement cool the shroud rails and back surface. Impingement cooling air then flows through elongated, convection cooling passages in the shroud and exits to flow along the shroud front surface with the main gas stream to provide film cooling. The baffle perforations and the convection cooling passages are interactively located to achieve maximum cooling benefit and highly efficient cooling air utilization.

대표청구항 ▼

A shroud cooling assembly for a gas turbine engine comprising, in combination: A. a plurality of arcuate shroud sections circumferentially arranged to surround the rotor blades of a high pressure turbine in the gas turbine engine, each said shroud section including 1) a base having a radially outer back surface, a radially inner front surface defining a portion of a radially outer boundary for the engine main gas stream flowing through the high pressure turbine, an upstream end and a downstream end, 2) a fore rail extending radially outwardly from said base adjacent said upstream end thereof, 3) an aft rail extending radially outwardly from said base adjacent said downstream end thereof, 4) a pair of spaced side rails extending radially outwardly from said base in conjoined relation with said fore and aft rails, and 5) a plurality of convection cooling passages extending through said base with inlets at said base back surface and outlets at said base front surface, said cooling passages having lengths greatly exceeding the thickness of said base between said back and front surfaces thereof, B. a plurality of arcuate hanger sections secured to the outer case of the gas turbine engine for supporting said shroud sections, each said hanger section including at least one hole therethrough for metering the flow of pressurized cooling air from a nozzle plenum, each said hanger section defining with said base back surface and said fore, aft and side rails of each said shroud section a shroud chamber; C. a pan-shaped baffle affixed to each said hanger section in position in within each said shroud chamber to define with said hanger section a baffle plenum in communication with said metering hole to receive pressurized cooling air directly from said nozzle plenum, said baffle including a plurality of perforations through which streams of cooling air are radially inwardly directed into impingement with one of said shroud sections, the positions of said perforations being such that said cooling air streams impinge only on said base back surface at locations intermediate said convection cooling passage inlets, whereby to maximize impingement cooling of said shroud sections, the impingement cooing air then flowing through said passages to convection cool said shroud sections and ultimately flowing along said shroud front surface to provide film cooling of said shroud sections; and D. wherein said passages are interactively arranged in groups, said groups including first, second and third rows, such that said passage inlets of said first row are substantially radially aligned with said passage outlets of said second row, whereby to compensate for the characteristics of decreasing convection heat transfer coefficient as cooling air flows through said passages from said inlets to said outlets.

이 특허를 인용한 특허 (70)

Rioux, Philip Robert, Active clearance control for gas turbine engine.
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Kitamura, Tsuyoshi; Masaki, Shinichiro, Aircraft gas turbine.
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Koyabu, Hidemichi; Hada, Satoshi; Masada, Junichiro; Tsukagoshi, Keizo, Cooling system of ring segment and gas turbine.
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Shapiro,Jason David, Counterflow film cooled wall.
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Trindade,Ricardo; Pham,Dan Que; Lebel,Larry, Double impingement vane platform cooling.
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Lee, Ching-Pang; Robinson, Geoffrey Douglas; Orlando, Robert Joseph, Duplex turbine shroud.
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Craig Alan Gonyou ; Roger Lee Doughty ; Monty Lee Shelton, End rail cooling for combined high and low pressure turbine shroud.
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Scricca Joseph A. (Jupiter FL) Kelch George W. (Palm Beach Gardens FL), Enhanced film cooling slot for turbine blade outer air seals.
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Morris, Mark C.; Howe, William J.; Zurmehly, George E.; Tiltman, Alan G.; Wolfmeyer, George W.; Sciacca, John F., Gas turbine cooled shroud assembly with hot gas ingestion suppression.
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Cunha, Frank J.; Erbas-Sen, Nurhak, Gas turbine engine combustor liner assembly with convergent hyperbolic profile.
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Dierberger, James A., Gas turbine engine component with upstream-directed cooling film holes.
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Maguire Alan R,GBX ; Richards Martyn,GBX, Gas turbine engine cooling apparatus.
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Power, Bronwyn; Fulayter, Roy D.; Rivers, Jonathan M., Gas turbine engine flow path geometry.
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Liang,George, Gas turbine vane with integral cooling system.
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Khanin, Alexander; Sloutski, Edouard, Heat accumulation segment.
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Khanin, Alexander; Sloutski, Edouard, Heat accumulation segment.
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Shapiro, Jason David, Method and system for a ceramic matrix composite shroud hanger assembly.
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Kottilingam, Srikanth Chandrudu; Bucci, David Vincent; Lacy, Benjamin Paul; Morey, Kathleen Blanche; Tollison, Brian Lee; Walsh, Patrick Thomas, Method for manufacturing a hot gas path component and hot gas path turbine component.
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Nguyen, Ly D.; Cruse, Louis; Fowkes, Ivar Gene; Salas, Silvestre; North, William; Kadambi, Vadanth, Method of forming a thermally isolated gas turbine engine housing.
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Lee, Ching-Pang; Guentert, Joseph M.; Lu, Wenfeng; Iles, Mitchell E., Methods and apparatus for assembling turbine engines.
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Bosley, Blaine Charles; Keith, Sean Robert; Kress, Jeffrey Allen; Albrecht, Jr., Richard W., Methods and apparatus for operating gas turbine engines.
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Stahl Matthew ; Kane Daniel E. ; Murdock James R. ; Haddad Donald E., Mounting and sealing arrangement for a turbine shroud segment.
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Franks, Michael John; Shapiro, Jason David; Rulli, Samuel Ross; Doughty, Roger Lee, Mounting apparatus for low-ductility turbine shroud.
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Dooley,Kevin Allan, Pump and method.
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Lee Ching-Pang ; Durgin George A., Recessed turbine shroud.
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Cotten, Blake R.; Thackway, Richard L.; Polyzopoulos, Charalambos, Reverse bulk flow effusion cooling.
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Brunelli, Marco Claudio Pio; Khan, Sameer A.; Landis, Kenneth K.; Marussich, Walter H.; Martin, Nicholas F.; Suarez-Crosse, Beatriz; Pankey, William W., Ring segment with cooling fluid supply trench.
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Berrong, Eric C.; Lee, Ching-Pang; Bhatia, Akash; Yamane, Ryan S.; Tschirren, Stefan; Meyer, Leonard J., Ring segment with forked cooling passages.
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Lee, Ching-Pang; Berrong, Eric C., Ring segment with serpentine cooling passages.
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Proctor Robert (West Chester OH) Linger David R. (Cincinnati OH) Di Salle David A. (West Chester OH) Brassfield Steven R. (Cincinnati OH) Plemmons Larry W. (Fairfield OH), Sealable turbine shroud hanger.
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Gregory Alan White ; Ching-Pang Lee, Shroud cooling segment and assembly.
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Shapiro, Jason David, Shroud hanger with diffused cooling passage.
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IPC	Description
A	생활필수품
A62	인명구조; 소방(사다리 E06C)
A62B	인명구조용의 기구, 장치 또는 방법(특히 의료용에 사용되는 밸브 A61M 39/00; 특히 물에서 쓰이는 인명구조 장치 또는 방법 B63C 9/00; 잠수장비 B63C 11/00; 특히 항공기에 쓰는 것, 예. 낙하산, 투출좌석 B64D; 특히 광산에서 쓰이는 구조장치 E21F 11/00)
A62B-1/08	.. 윈치 또는 풀리에 제동기구가 있는 것

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연합인증

Shroud cooling assembly for gas turbine engine 원문보기

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Shroud cooling assembly for gas turbine engine 원문보기

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연구과제 타임라인

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이 특허를 인용한 특허 (70)

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