[특허]Low-pressure turbine heat shield

General Electric Company (Cincinnati OH 02)

Low-pressure turbine heat shield

국가/구분	United States(US) Patent 등록
국제특허분류(IPC7판)	B63H-001/14
출원번호	US-0799799 (1991-11-29)
발명자 / 주소	Sweeney Derek J. (Dublin IEX)
출원인 / 주소	General Electric Company (Cincinnati OH 02)
인용정보	피인용 횟수 : 45 인용 특허 : 0

초록 ▼

A turbine for an axial flow gas turbine engine has a heat shield arranged in an annular space between the outer casing and an array of butted nozzle segments. The heat shield is made of a material which expands when subjected to the high temperatures generated inside said turbine during operation. A mechanism is provided for blocking rotation about the axial axis and axial displacement in an aft direction of the heat shield, while not blocking radial expansion of the heat shield. The outer casing and heat shield are dimensioned and configured so that after thermal expansion the heat shield and outer casing contact to form a gastight chamber therebetween, whereas prior to thermal expansion the heat shield and outer casing do not form a gastight chamber therebetween. The heat shield is a sheet metal ring.

대표청구항 ▼

A heat shield for incorporation in a turbine of a gas turbine engine comprising: a sheet metal ring having four sections connected in series as follows: a rearmost substantially cylindrical first section having a predetermined diameter, a substantially conical second section connected to said first section, a substantially cylindrical third section having a diameter less than the predetermined diameter of said first section and connected to said second section, and a folded-back fourth section connected to and radially outside of said third section. a plurality of axial recesses circumferentially distributed along and extending from a rearward edge of said first section, wherein each of said axial recesses terminates along a corresponding arc of a circle, and a plurality of axial stops joined to said sheet metal ring, said axial stops being respectively arranged with a portion thereof disposed inside a corresponding axial recess, and each of said axial stops having rearwardly facing abutment surface which lies substantially in a radial plane. A turbine for a gas turbine engine having an inlet, an outlet and an annular passageway for gas flow from said inlet to said outlet, comprising: an outer casing surrounding said annular passageway and having an annular cavity situated between first and second annular projections, said first annular projection being located at a first axial position and said second annular projection being located at a second axial position downstream of said first axial position; a plurality of nozzle segments circumferentially arranged end to end inside said outer casing to form a stator stage, each of said nozzle segments comprising an outer platform having a first portion which forms a part of said annular passageway, a second portion which is operatively supported by said outer casing at a point upstream of said cavity and a third portion which is operatively supported by said outer casing at a point downstream of said cavity, said outer platform and said outer casing defining a space therebetween that comprises said annular cavity; and an annular heat shield arranged inside said space, said heat shield being dimensioned and disposed so that after thermal expansion due to the heat from hot gases flowing through said turbine, a first portion of said heat shield abuts said first annular projection substantially contiguously along a circumference and a second portion of said heat shield abuts said second annular projection substantially contiguously along a circumference for forming a gas tight chamber between said shield and said outer casing.

이 특허를 인용한 특허 (45)

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Mickelsen, Justin C.; Baker, Martin C., Fireproof systems with local heat shields for aircraft engines.
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Chuong, Conway; Werner, Kurt P.; Duelm, Shelton O., Gas turbine engine part retention.
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Pizzi Antonio,CAX ; Crone James Christopher,CAX, Gas turbine engine shroud seals.
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Munshi, Mrinal; Finneran, John W.; Shteyman, Yevgeniy; Graber, Daryl J.; Porter, Matthew R.; Leagon, Jonathan M., Gas turbine outer case active ambient cooling including air exhaust into sub-ambient cavity.
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Kreiselmaier, Erich; McFeat, Jose Anguisola; Nagler, Christoph; Riazantsev, Sergei; Wardle, Brian Kenneth, Guide vane for a gas turbine.
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Tsypkaykin, Igor; Von Arx, Beat; Nagler, Christoph, Guide vane having hooked fastener for a gas turbine.
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Marc Roger Marchi FR; Jean-Pierre Louis Mareix FR; Patrice Rosset FR, Leaf seal.
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Durocher,Eric; Pietrobon,John Walter, Lightweight annular interturbine duct.
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Harper, Cedric B; Creagh, Michael; Humphries, Neil; Martindale, Ian G, Liner for a gas turbine engine casing.
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Rosset, Patrice Jean-Marie; Guerard, Coralie; Condat, Helene; Prestel, Sebatien, Locking of blade-supporting components.
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Taylor,Steven Mitchell; Spencer,Christina Marie; Licu,Dragos Nicolae, Methods and apparatus for controlling gas turbine engine rotor tip clearances.
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Frederick J. Zegarski ; John S. Carpenter, Methods and apparatus for minimizing thermal gradients within turbine shrouds.
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Steplewski, Marek; Gupta, Bhupendra K., Methods for replacing portions of turbine shroud supports.
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Housley, Christopher George; Enzweiler, Donald Franklin, Nozzle lock for gas turbine engines.
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Harper,Cedric Brett; Martindale,Ian Graham, Rotor blade containment assembly for a gas turbine engine.
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Lawer, Steven D; Halliwell, Mark A, Seal segment for a turbine.
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Feldmann, Manfred; Schinko, Norbert; Kaltenbach, Sebastian; Lorenz, Joachim, Sealing of the flow channel of a turbomachine.
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Gekht, Eugene; Di Paola, Franco, Sheet metal turbine or compressor static shroud.
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Sluyter, Gregory Kent; Sener, Alexander Martin; Dziech, Aaron Michael, Shroud retention system with keyed retention clips.
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Sener, Alexander Martin, Shroud retention system with retention springs.
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Sutcu, Muzaffer; Fox, Timothy A.; Ryan, William R., Stepped inlet ring for a transition downstream from combustor basket in a combustion turbine engine.
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Belmonte, Olivier; Beaujard, Antoine Jean-Philippe, Turbine engine stator wheel and a turbine or a compressor including such a stator wheel.
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Stine,Frederick J.; Tucker,James W.; Szpunar,Stephen J., Turbine shroud assembly with enhanced blade containment capabilities.
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Tanaka, Agamu, Turbine shroud segment.
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Breugnot, Thierry Michel; Durand, Didier Noel; Leutard, Florence Irene Noelle, Turbo machine with a device for preventing a segment of nozzle guide vanes assembly from rotating in a casing; rotation-proofing peg.
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Ramm, Guenter, Turbomachine.
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Arnould, Julien, Turbomachine distributor comprising a thermal protection sheet with a radial stop, and associated thermal protection sheet.
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Low-pressure turbine heat shield

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Low-pressure turbine heat shield

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