[특허]Self-cooling joint connection for abutting segments in a gas turbine engine

Self-cooling joint connection for abutting segments in a gas turbine engine 원문보기

IPC분류정보
국가/구분	United States(US) Patent 등록
국제특허분류(IPC7판)	F01D-009/04
출원번호	US-0866094 (1992-04-06)
발명자 / 주소	Starkweather John H. (Cincinnati OH)
출원인 / 주소	General Electric Company (Cincinnati OH 02)
인용정보	피인용 횟수 : 43 인용 특허 : 0

초록 ▼

A joint connection for abutting, circumferentially extending segments in a gas turbine engine, such as turbine nozzle segments, includes a sealing member which is insertable between longitudinally extending slots formed in the abutting side edges of two adjacent segments. The segments are each formed with a number of grooves which are longitudinally spaced along the length of the slots therein, and which extend beneath the sealing member carried within the slots. A cooling air flow path is thus formed extending from one side of the sealing member, into the longitudinal slot of each segment and then through the grooves to the opposite side of the sealing member so that the entire joint connection or seal region between the abutting side edges of the segments is cooled.

대표청구항 ▼

In a gas turbine engine including at least one section comprising a plurality of circumferentially adjacent segments, each of said segments having inner and outer surfaces in communication with gas flows and passages for providing cooling air from one surface to the other, and a pair of opposed side edges, each side edge having a face extending between said inner and outer surfaces, abutting the side edges of adjacent segments, a joint connection between said abutting side edges of said circumferentially adjacent segments comprising: a first slot having an axis extending in a first direction and formed in one side edge of a first segment, said first slot extending from the face of said one side edge of the first segment toward the opposite side edge thereof, said first slot defining an imperforate inner wall, an imperforate outer wall and an imperforate interior side wall extending between said inner and outer walls, one of said inner and outer walls being formed with grooves having axes extending transverse to said first direction, each extending in said one of said inner and outer walls between said interior side wall of said first slot and the face of said one side edge of the first segment; a second slot having an axis extending in a first direction and formed in one side edge of a second segment, said second slot extending from the face of said one side edge of the second segment toward the opposite side edge thereof, said second slot defining an imperforate inner wall, an imperforate outer wall and an imperforate interior side wall extending between said inner and outer walls, one of said inner and outer walls being formed with grooves having axes extending transverse to said first direction, each extending in said one of said inner and outer walls between said interior side wall of said second slot and the face of said one side edge of the second segment; and a symmetrical sealing member extending between said first slot in the first segment and said second slot in the second segment, said sealing member having a first side overlying said grooves in each of the first and second segments and a second side opposite said grooves, whereby an air flow path is formed between the abutting side edges of the first and second segments in which a flow of cooling air is first directed onto said second side of said sealing member, into said first slot in the first segment and the second slot in the second segment and then through said grooves of said first and second slots to said first side of said sealing member. The method of cooling abutting side edges of circumferentially extending segments in a gas turbine engine, the segments including holes for providing cooling air through the segments, the method of cooling abutting side edges comprising: directing cooling air onto a first side of a symmetrical sealing member carried within a longitudinally extending slot formed in the side edge of a first segment and within a longitudinally extending slot formed in the side edge of an abutting, second segment; directing the cooling air from said first side of said sealing member into the imperforate interior of each said longitudinally extending slots; directing the cooling air into grooves formed in each of the first and second segments within said interior of said longitudinally extending slots therein, the opposite, second side of the sealing member overlying said grooves within said slots so that the cooling air flows from said first side of said sealing member into said grooves and then to said opposite, second side of the sealing member.

이 특허를 인용한 특허 (43)

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Predmore Daniel Ross ; Kellock Iain Robertson ; Correia Victor Hugo ; Starkweather John Howard ; Lenahan Dean Thomas, Cooling joint connection for abutting segments in a gas turbine engine.
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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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Kreis,Erhard; Oehl,Markus; Rathmann,Ulrich, Seal arrangement for reducing the seal gaps within a rotary flow machine.
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Nichols,Glenn H.; Tressler,Judd Dodge, Thermal barrier coating wrap for turbine airfoil.
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Robert P. Czachor ; Michael L. Barron, Thermal control passages for horizontal split-line flanges of gas turbine engine casings.
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Allen, David B., Thermally sprayed conformal seal.
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Spangler, Brandon W.; Paauwe, Corneil S.; Lehane, Christopher J.; Tracy, Anita L.; Wiedemer, John D.; Hjelm, Scott D., Turbine airfoil with platform cooling.
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Zagar Thomas W. ; Schiavo Anthony L., Turbine blade platform seal.
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Self-cooling joint connection for abutting segments in a gas turbine engine 원문보기

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Self-cooling joint connection for abutting segments in a gas turbine engine 원문보기

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