[특허]Turbine vane having dedicated inner platform cooling

[미국특허] Turbine vane having dedicated inner platform cooling 원문보기

IPC분류정보
국가/구분	United States(US) Patent 등록
국제특허분류(IPC7판)	F01D-005/14
출원번호	US-0008959 (1993-01-21)
발명자 / 주소	Magowan John W. (Longmeadow MA) Pawlaczyk Richard J. (Newington CT) Pighetti Annette M. (Andover CT) Schwarz Jr. Richard A. (Somers CT)
출원인 / 주소	United Technologies Corporation (Hartford CT 02)
인용정보	피인용 횟수 : 64 인용 특허 : 0

초록 ▼

A turbine vane for a gas turbine engine core adaptable to be operated in a variety of thrust regimes is disclosed. Various construction details are developed which provide cooling to an inner platform of the turbine vane. In one particular embodiment, a turbine vane includes a hollow core permitting cooling fluid to pass through the vane and an inner platform having a pocket disposed therein, the pocket being in fluid communication with the core. Heat is exchanged between the platform and the cooling fluid within the pocket. Cooling holes extend between the pocket and a flow surface of a platform to provide cooling of the flow surface.

대표청구항 ▼

A turbine vane for a gas turbine engine disposed about a longitudinal axis and having an axially oriented annular flow path therethrough, the gas turbine engine including a compressor section, a combustor section, a turbine section downstream of the combustor section, and a source of cooling fluid, the turbine section including the turbine vane, wherein the turbine vane includes: an airfoil portion extending through the flow path, the airfoil portion including a hollow core therein, the core being open at its radially outer end to define a passage for conducting cooling fluid from the source through the airfoil portion; a platform portion disposed radially inwardly of the airfoil portion and oppositely of the open end of the core, the platform having a radially outer surface defining a flow surface for working fluid within the flow path, the platform including a plurality of pockets and a plurality of cooling holes, each of the pockets having a cooling passage permitting fluid communication with the core such that cooling fluid is exchanged between the core and the pocket to thereby transfer heat from the platform to the fluid within the pocket, and the cooling holes extending between each of the pockets and the flow surface and defining means to eject cooling fluid over the flow surface of the platform.

이 특허를 인용한 특허 (64) 인용/피인용 타임라인 분석

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Liang,George, Cooling system for an airfoil vane.
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Kuwabara, Masamitsu; Tomita, Yasuoki; Shirota, Akihiko; Ito, Eisaku, Gas turbine cooled stationary blade.
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Spangler, Brandon W.; Beattie, Jeffrey S., Gas turbine engine systems involving baffle assemblies.
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Spangler, Brandon W.; Paauwe, Corneil S., Gas turbine engine systems involving turbine blade platforms with cooling holes.
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Bergman, Russell J.; Bach, Leonard A.; Spangler, Brandon W., Gas turbine engine turbine vane platform core.
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Benton, Robert, Platform cooling arrangement for the nozzle guide vane stator of a gas turbine.
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Chon, Young H.; Mongillo, Dominic J.; Propheter-Hinckley, Tracy A., Turbine vane platform leading edge cooling holes.
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A	생활필수품
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[미국특허] Turbine vane having dedicated inner platform cooling 원문보기

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