[특허]Turbine vane assembly with integrally cast cooling fluid nozzle

Turbine vane assembly with integrally cast cooling fluid nozzle 원문보기

IPC분류정보
국가/구분	United States(US) Patent 등록
국제특허분류(IPC7판)	F04D-029/58
출원번호	US-0949968 (1992-09-24)
발명자 / 주소	Rup Jr. John J. (Willington CT) Nikkanen John P. (West Hartford CT)
출원인 / 주소	United Technologies Corporation (Hartford CT 02)
인용정보	피인용 횟수 : 30 인용 특허 : 0

초록 ▼

A gas turbine engine having a turbine vane assembly including an integrally cast cooling fluid nozzle is disclosed. Various construction details are developed which disclose a cooling fluid nozzle including a flow passage having an exit and a wall. In one embodiment, the wall includes an angled leading edge which mates with a circumferentially adjacent trailing edge of an adjacent wall. The leading edge is tapered such that in a most open position of the turbine vane assembly the leading edge and the trailing edge circumferentially align. In a most closed position of the turbine vane assembly, the angled leading edge aligns with the trailing edge such that a step down is created in the circumferentially directed flow of the sealed cavity. The plurality of wall thereby produce a waterfall arrangement within the sealed cavity to reduce the windage losses.

대표청구항 ▼

A gas turbine engine disposed about a longitudinal axis and including an axially extending flow path, a turbine section, and means to conduct cooling fluid into the turbine section, the turbine section including a rotor assembly disposed circumferentially about the axis, sealing means disposed axially downstream of the rotor assembly, the rotor assembly and sealing means adapted to rotate about the axis in an operational condition, and a turbine vane assembly disposed axially downstream of the rotor assembly and radially outward of the sealing means, wherein an annular seal cavity is defined in part by the separation between the rotor assembly, the turbine vane assembly and the sealing means, the turbine vane assembly including a plurality of vanes, and a sealing shroud adapted to engage the sealing means to block the passage of fluid from the cavity, wherein each vane has a pitch angle ggg1 wherein g1 is the most open pitch angle, each vane including an airfoil portion, a platform, and an integrally cast nozzle, the airfoil portion being hollow and in fluid communication with the means to conduct cooling fluid, the nozzle including wall means having a flow surface facing the cavity, and a smooth, continuous flow passage in fluid communication with the airfoil portion and adapted to direct cooling fluid into the cavity, the wall means extending circumferentially between adjacent wall means and extending radially inward from the platform, each wall means having a trailing edge and a leading edge, the leading edge adapted to circumferentially align with the trailing edge of an adjacent wall means with gg1, and the leading edge adapted to form a step down relative to the direction of flow within the cavity with gg1.

이 특허를 인용한 특허 (30)

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Matwey, Mark; Jan, David K., Flow discouraging systems and gas turbine engines.
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Laurello, Vincent P.; Tham, Kok-Mun, Gas turbine engine with improved cooling between turbine rotor disk elements.
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Lee, Ching-Pang; Estill, Eric Alan; Laflen, James Harvey; Jones, Daniel Verner, Methods and system for cooling integral turbine nozzle and shroud assemblies.
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Lee, Ching-Pang; Estill, Eric Alan; Laflen, James Harvey; Andersen, Katherine Jaynetorrence, Methods and system for recuperated cooling of integral turbine nozzle and shroud assemblies.
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Lee, Ching-Pang; Estill, Eric Alan; Laflen, James Harvey; Jones, Daniel Vern, Methods and system for shielding cooling air to facilitate cooling integral turbine nozzle and shroud assemblies.
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Durocher, Eric; Paquet, Rene; Lefebvre, Guy, Rim seal for a gas turbine engine.
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Snyder, Daniel A.; Corcoran, Christopher, Rotor heat shield.
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Cunha, Francisco J.; Chiu, R. Paul, Steam and air cooling for stator stage of a turbine.
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McCaffrey, Michael G., Systems and methods involving aerodynamic struts.
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Liang, George, Turbine airfoil cooling system with platform edge cooling channels.
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Rodriguez, Jose L.; Golsen, Matthew J., Turbine airfoil with an internal cooling system having trip strips with reduced pressure drop.
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Rieck ; Jr. Harold P. ; Kress Jeffrey A., Turbine nozzle having purge air circuit.
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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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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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Turbine vane assembly with integrally cast cooling fluid nozzle 원문보기

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Turbine vane assembly with integrally cast cooling fluid nozzle 원문보기

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연구과제 타임라인

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이 특허를 인용한 특허 (30)

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