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公开(公告)号：US12025058B2
公开(公告)日：2024-07-02
申请号：US18270301
申请日：2022-01-27
CPC分类号： F02C7/28 , F01D9/023 , F01D11/005 , F01D25/12 , F02C7/12 , F23R3/42 , F23R2900/00012
摘要： A sealing member that forms a combustion gas flow path of a gas turbine includes a first body portion having a cooling passage. The first body portion includes a first end portion forming one end portion in a circumferential direction, a second end portion forming the other end portion on an opposite side in the circumferential direction, and an intermediate portion formed between the first and second end portions. The cooling passage includes an intermediate portion cooling passage inclined at a first angle with respect to an axial direction, a first end portion cooling passage provided in the first end portion and inclined at a second angle with respect to the axial direction, and a second end portion cooling passage provided in the second end portion and inclined at a third angle with respect to the axial direction, and the second and third angles are smaller than the first angle.
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2.发明授权Combustor connection structure, combustor transition piece, designing method of combustor transition piece and gas turbine 有权燃烧器连接结构，燃烧器过渡件，燃烧器过渡件和燃气轮机的设计方法公开(公告)号：US08955222B2
公开(公告)日：2015-02-17
申请号：US13874883
申请日：2013-05-01
发明人： Sosuke Nakamura , Satoshi Takiguchi , Norihiko Motoyama , Taiki Kinoshita , Yoshikazu Matsumura
CPC分类号： F01D9/023 , F05D2250/50 , F23R3/46 , F23R3/60 , F23R2900/00017 , F23R2900/00018 , Y02E20/16 , Y10T29/49229 , Y10T29/49348
摘要： A cross-sectional area (Dout) of a transition piece outlet is set within a range of 0.79£DoutDin£0.9, relative to a cross-sectional area (Din) of a transition piece inlet of a combustor, and in a first stage turbine nozzle of a turbine connected to the transition piece outlet, a size (Hin) in a radial direction between upstream ends of the inner shroud and the outer shroud has a same dimension as a size (a) in a radial direction of the transition piece outlet. In a combustor transition piece that is included in the combustor having a center line (S) arranged with an angle to an axial center (R) of a rotor of a gas turbine and that guides combustion gas to the turbine, a cross-sectional area is monotonously reduced from the transition piece inlet in which the combustion gas flows to the transition piece outlet from which the combustion gas flows out.
摘要翻译： 过渡件出口的横截面面积（Dout）相对于燃烧器的过渡件入口的横截面面积（Din）设定在0.79£DoutDin£0.9的范围内，在第一级涡轮机 连接到过渡件出口的涡轮的喷嘴，在内护罩的上游端和外护罩之间的径向尺寸（Hin）具有与过渡件出口的径向尺寸（a）相同的尺寸 。 在包括在具有与燃气轮机的转子的轴向中心（R）成一角度的中心线（S））并且将燃烧气体引导到涡轮机的燃烧器中的燃烧器过渡件中，横截面积 从燃烧气体流过到燃烧气体流出的过渡件出口的过渡件入口单调地减少。
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公开(公告)号：US11891957B2
公开(公告)日：2024-02-06
申请号：US17790315
申请日：2021-02-08
CPC分类号： F02C7/28 , F01D25/243 , F23R3/42 , F05D2220/32 , F05D2240/55
摘要： This exit seal is for connecting an exit flange of a combustor and a shroud in a stator blade of a turbine. The exit seal is equipped with: a seal body that extends in a circumferential direction; and a lid member disposed at a circumferential end of the seal body. The seal body comprises one or more recessed sections that are recessed in a radial direction or in an axial direction and extend in the circumferential direction. At a position of the circumferential end of at least one recessed section among the one or more recessed sections, the lid member is disposed so as to overlap, in the axial direction and the radial direction, with a recessed space formed by the one recessed section.
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公开(公告)号：US20240027069A1
公开(公告)日：2024-01-25
申请号：US17914694
申请日：2021-03-31
发明人： Shinichi Fukuba , Satoshi Takiguchi , Taiki Kinoshita , Kenta Taniguchi , Sosuke Nakamura , Yoshikazu Matsumura
摘要： A combustor for a gas turbine, includes: a first fuel nozzle group and a second fuel nozzle group each of which includes a fuel nozzle capable of supplying a fuel and has an independently controllable fuel supply system; a cylinder inside which a combustion region allowing a combustion gas produced by combustion of the fuel to flow is formed; and a first contraction portion extending partially along a circumferential direction so as to correspond to one of the first fuel nozzle group or the second fuel nozzle group and protruding radially inward from an inner peripheral surface of the cylinder.
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公开(公告)号：US11852343B2
公开(公告)日：2023-12-26
申请号：US17774642
申请日：2020-12-21
发明人： Shinji Akamatsu , Kenji Sato , Naoki Abe , Taiki Kinoshita , Hiroki Shibata , Norihiko Motoyama
CPC分类号： F23R3/002 , F23M20/005 , F01N1/023 , F05D2260/963 , F23D2210/00 , F23R3/44 , F23R2900/00014
摘要： A combustor component of a combustor for combusting fuel to produce a combustion gas includes a combustion cylinder forming a passage for the combustion gas, a first acoustic device which internally includes a first cavity communicating with the passage via a first through hole formed in the combustion cylinder, a second acoustic device which is located on a radially outer side of the first acoustic device so as to cover the first acoustic device, and internally includes a second cavity communicating with the passage via a second through hole formed in the combustion cylinder, and a first communication passage causing the first cavity and an outer space of the combustion cylinder to communicate with each other without via the first through hole and the second cavity.
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