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31. 发明授权

US09670785B2 Cooling assembly for a gas turbine system 有权
公开(公告)号：US09670785B2
公开(公告)日：2017-06-06
申请号：US13451053
申请日：2012-04-19
申请人： David Richard Johns , Kevin Richard Kirtley
发明人： David Richard Johns , Kevin Richard Kirtley
IPC分类号： F01D5/18
CPC分类号： F01D5/188 , F01D5/18 , F01D5/181 , F01D5/186 , F05D2240/81 , F05D2250/185 , F05D2260/201
摘要： A cooling assembly for a gas turbine system includes a turbine nozzle having at least one channel comprising a channel inlet configured to receive a cooling flow from a cooling source, wherein the at least one channel directs the cooling flow through the turbine nozzle in a radial direction at a first pressure to a channel outlet. Also included is an exit cavity for fluidly connecting the channel outlet to a region of a turbine component, wherein the region of the turbine component is at a second pressure, wherein the first pressure is greater than the second pressure.

32. 发明申请

US20170145922A1 TURBINE COMPONENT INCLUDING MIXED COOLING NUB FEATURE 审中-公开
公开(公告)号：US20170145922A1
公开(公告)日：2017-05-25
申请号：US14945939
申请日：2015-11-19
申请人： United Technologies Corporation
发明人： Christine F. McGinnis , Karl A. Mentz , James Tisley Auxier
IPC分类号： F02C7/18
CPC分类号： F02C7/18 , F01D5/187 , F02C7/12 , F05D2240/81 , F05D2250/18 , F05D2250/28 , F05D2260/2214 , Y02T50/676
摘要： A component for a gas turbine engine includes at least one cooled surface configured to contact a cooling flow, the at least one cooled surface has a base surface and a plurality of cooling nubs disposed about the base surface. The plurality of cooling nubs are distributed about the base surface in a mixed pattern.

33. 发明授权

US09657575B2 Gas turbine engine 有权
公开(公告)号：US09657575B2
公开(公告)日：2017-05-23
申请号：US14077460
申请日：2013-11-12
申请人： Yoji Okita
发明人： Yoji Okita
IPC分类号： F01D5/08 , F01D5/18 , F01D9/04 , F01D5/14
CPC分类号： F01D5/08 , F01D5/143 , F01D5/145 , F01D5/186 , F01D9/041 , F05D2240/121 , F05D2240/81 , F05D2250/611 , F05D2260/202 , Y02T50/673 , Y02T50/676
摘要： The gas turbine engine (S1) includes: turbine blades (7b); and a cooling air supply unit (11) to supply cooling air to the turbine blades (7b). A flow path surface (31) is formed so as to be positioned in an upstream side of the turbine blades (7b) and so as to be connected to a base surface (32) in which the turbine blades (7b) are provided. The flow path surface (31) includes: depression portions (31a) depressed relative to the base surface (32), each depression portion (31a) including at least an area overlapping with a front end (7b1) of each turbine blade (7b), when viewed from a direction of the turbine axis (L); and protrusion portions (31b) protruding relative to the base surface (32), each protrusion portion (31b) being at least part of each area positioned between front ends (7b1) of the turbine blades (7b), when viewed from the above direction.

34. 发明申请

US20170114646A1 COOLING PASSAGES IN A TURBINE COMPONENT 审中-公开
公开(公告)号：US20170114646A1
公开(公告)日：2017-04-27
申请号：US14923660
申请日：2015-10-27
申请人： PRATT & WHITNEY CANADA CORP.
发明人： Sri SREEKANTH , Si-Man LAO , Michael Leslie Clyde PAPPLE
IPC分类号： F01D5/18 , F01D9/06
CPC分类号： F01D5/186 , F01D9/065 , F05D2240/11 , F05D2240/81 , F05D2260/202 , F05D2260/204 , F23R3/002 , F23R3/005 , F23R3/06 , F23R2900/03041 , F23R2900/03042 , Y02T50/676
摘要： A turbine component has a plurality of cooling passages each extending through a body of a structure between opposite hot and cold surfaces of the structure. According to one embodiment, at least one of the cooling passages includes a plurality of upstream paths defining respective inlet openings on the cold surface and merging into a number of downstream paths defining respective outlet openings on the hot surface.

35. 发明授权

US09630277B2 Airfoil having built-up surface with embedded cooling passage 有权
公开(公告)号：US09630277B2
公开(公告)日：2017-04-25
申请号：US12723880
申请日：2010-03-15
申请人： Ching-Pang Lee , Mrinal Munshi , Gm S. Azad , Jae Y. Um
发明人： Ching-Pang Lee , Mrinal Munshi , Gm S. Azad , Jae Y. Um
IPC分类号： F02C7/12 , B23P6/00 , F01D5/00 , F01D5/14 , F01D5/18
CPC分类号： B23P6/007 , F01D5/005 , F01D5/145 , F01D5/186 , F05D2230/30 , F05D2230/80 , F05D2240/81 , Y10T29/49318
摘要： A component in a gas turbine engine includes an airfoil extending radially outwardly from a platform associated with the airfoil. The airfoil includes opposed pressure and suction sidewalls, which converge at a first location defined at a leading edge of the airfoil and at a second location defined at a trailing edge of the airfoil opposed from the leading edge. The component includes a built-up surface adjacent to the leading edge at an intersection between the pressure sidewall and the platform, and at least one cooling passage at least partially within the built-up surface at the intersection between the pressure sidewall and the platform. The at least one cooling passage is in fluid communication with a main cooling channel within the airfoil and has an outlet at the platform for providing cooling fluid directly from the main cooling channel to the platform.

36. 发明申请

US20170051613A1 CUPPED CONTOUR FOR GAS TURBINE ENGINE BLADE ASSEMBLY 审中-公开
标题翻译：用于气体涡轮发动机叶片组件的双面轮廓
公开(公告)号：US20170051613A1
公开(公告)日：2017-02-23
申请号：US14828063
申请日：2015-08-17
申请人： United Technologies Corporation
发明人： Dipanjan Saha , Brooks E. Snyder , Thomas N. Slavens
IPC分类号： F01D5/18 , F01D25/12 , F01D9/04
CPC分类号： F01D5/187 , B22F3/1055 , B22F5/04 , B22F7/08 , B23K26/34 , B23K2101/001 , B33Y10/00 , B33Y80/00 , F01D9/041 , F01D25/12 , F05D2220/32 , F05D2230/21 , F05D2230/30 , F05D2240/81 , F05D2260/204 , Y02P10/295 , Y02T50/676
摘要： An exemplary method of forming an endwall with a contour includes casting an endwall with at least one cooling channel having an opening from the endwall, and covering the opening with a cupped contour formed on the endwall. An exemplary gas turbine engine blade assembly includes an endwall with a plurality of cooling channels, an airfoil extending radially from the endwall to a tip, and a cupped contour formed on the endwall to provide a cooling chamber between the cupped contour and a radially facing surface of the endwall.
摘要翻译：形成具有轮廓的端壁的示例性方法包括用至少一个具有来自端壁的开口的冷却通道浇铸端壁，并且以形成在端壁上的杯状轮廓覆盖开口。示例性的燃气涡轮发动机叶片组件包括具有多个冷却通道的端壁，从端壁径向延伸到尖端的翼型，以及形成在端壁上的杯形轮廓，以在杯形轮廓和径向对置的表面之间提供冷却室的端壁。

37. 发明申请

US20170016339A1 COOLING STRUCTURE FOR STATIONARY BLADE 有权
标题翻译：固定式叶片冷却结构
公开(公告)号：US20170016339A1
公开(公告)日：2017-01-19
申请号：US14801412
申请日：2015-07-16
申请人： General Electric Company
发明人： Aaron Gregory Winn , George Andrew Gergely , Mary Virginia Holloway , Paul Kendall Smith
IPC分类号： F01D9/04 , F01D25/12
CPC分类号： F01D9/041 , F01D5/187 , F01D9/02 , F01D25/12 , F05D2220/30 , F05D2240/122 , F05D2240/128 , F05D2240/81 , F05D2260/2214
摘要： Embodiments of the present disclosure provide a cooling structure for a stationary blade, including: an endwall coupled to a radial end of an airfoil; a chamber positioned within the endwall and radially displaced from a radially outer end of the trailing edge of the airfoil, wherein the chamber includes a pair of opposing chamber walls, one of the pair of opposing chamber walls being positioned proximal to the pressure side surface of the airfoil and the other of the pair of opposing chamber walls being positioned proximal to the suction side surface and the trailing edge of the airfoil, and wherein the cooling fluid in the chamber is in thermal communication with least a portion of the endwall positioned proximal to the pressure side surface and the trailing edge of the airfoil; and a plurality of thermally conductive fixtures positioned within the chamber.
摘要翻译：本公开的实施例提供了一种用于固定叶片的冷却结构，包括：连接到翼型件的径向端的端壁; 定位在端壁内并且从翼型的后缘的径向外端径向偏移的腔室，其中腔室包括一对相对的腔室壁，一对相对的腔室壁中的一个位于靠近压力侧面的所述翼型件和所述一对相对的室壁中的另一个位于所述翼型件的吸入侧表面和所述后缘附近，并且其中所述腔室中的冷却流体与所述端壁的至少一部分位于翼面的压力侧表面和后缘; 以及多个位于腔室内的导热固定件。

38. 发明申请

US20170016338A1 COOLING STRUCTURE FOR STATIONARY BLADE 有权
标题翻译：固定式叶片冷却结构
公开(公告)号：US20170016338A1
公开(公告)日：2017-01-19
申请号：US14801197
申请日：2015-07-16
申请人： General Electric Company
发明人： Christopher Donald Porter , Christopher Lee Golden
IPC分类号： F01D9/04 , F01D25/12
CPC分类号： F01D9/041 , F01D5/187 , F01D25/12 , F05D2240/12 , F05D2240/81 , F05D2260/2214 , F05D2260/22141
摘要： Embodiments of the present disclosure provide a cooling structure for a stationary blade. The cooling structure can include: an airfoil having a cooling circuit therein; an endwall coupled to a radial end of the airfoil; a chamber positioned within the endwall for receiving a cooling fluid from the cooling circuit, wherein the cooling fluid absorbs heat from the endwall, and a temperature of the cooling fluid in an upstream region is lower than a temperature of the cooling fluid in a downstream region; a first passage within the endwall fluidly connecting the upstream region of the chamber to a wheel space positioned between the endwall and the turbine wheel; and a second passage within the endwall fluidly connecting the downstream region of the chamber to the wheel space.
摘要翻译：本公开的实施例提供了一种用于固定叶片的冷却结构。冷却结构可以包括：其中具有冷却回路的翼型件; 连接到所述翼型件的径向端部的端壁; 位于端壁内的室，用于从冷却回路接收冷却流体，其中冷却流体从端壁吸收热量，并且上游区域中的冷却流体的温度低于下游区域中的冷却流体的温度 ; 所述端壁内的第一通道将所述腔室的上游区域流体连接到位于所述端壁与所述涡轮机叶轮之间的车轮空间; 以及端壁内的第二通道，其将腔室的下游区域流体连接到车轮空间。

39. 发明授权

US09540947B2 Cooling system of ring segment and gas turbine 有权
标题翻译：环段和燃气轮机的冷却系统
公开(公告)号：US09540947B2
公开(公告)日：2017-01-10
申请号：US14264552
申请日：2014-04-29
申请人： MITSUBISHI HEAVY INDUSTRIES, LTD.
发明人： Hidemichi Koyabu , Satoshi Hada
IPC分类号： F01D25/12 , F01D11/08
CPC分类号： F01D25/12 , F01D11/08 , F01D11/24 , F05D2240/81 , F05D2260/201
摘要： A cooling system of ring segment is provided with: a collision plate that has a plurality of small holes; a cooling space that is enclosed by the collision plate and a main body of the segment body; a first cavity that arranged is the upstream end portion of the segment body in the flow direction of the combustion gas so as to be perpendicular to the axial direction of a rotating shaft; a first cooling passage that communicates from the cooling space to the first cavity; and a second cooling passage that communicates from the first cavity to a fire combustion gas d gas space in the downstream end portion of the segment body in the flow direction of the combustion gas.
摘要翻译：环段的冷却系统设有：具有多个小孔的碰撞板; 由所述碰撞板和所述节段主体的主体包围的冷却空间; 在燃烧气体的流动方向上，分段主体的上游端部与旋转轴的轴向垂直地配置的第一空腔; 第一冷却通道，其从所述冷却空间与所述第一空腔连通; 以及第二冷却通道，其在所述燃烧气体的流动方向上从所述第一空腔与所述段主体的下游端部中的燃烧气体d气体空间连通。

40. 发明申请

US20160348515A1 MONOLITHIC CERAMIC RODS TO ENABLE COOLING HOLES IN CMC 有权
标题翻译：在CMC中启用冷却孔的单晶陶瓷棒
公开(公告)号：US20160348515A1
公开(公告)日：2016-12-01
申请号：US14722093
申请日：2015-05-26
申请人： Rolls-Royce Corporation , Rolls-Royce North American Technologies, Inc.
发明人： Bruce Edward Varney , Ted Joseph Freeman
IPC分类号： F01D5/28 , B23H7/00 , C04B41/45 , B23K26/402 , C04B41/51 , B23B37/00 , B23K26/382
CPC分类号： F01D5/284 , B23B35/00 , B23B37/00 , B23B2226/18 , B23B2226/27 , B23K26/0093 , B23K26/389 , B23K26/402 , B23K2103/172 , B23K2103/52 , B32B3/266 , C04B35/00 , F01D5/186 , F01D5/282 , F01D9/065 , F05D2230/10 , F05D2230/12 , F05D2230/13 , F05D2230/61 , F05D2240/11 , F05D2240/81 , F05D2260/202 , F05D2300/6033
摘要： A method to form a hole in a ceramic matrix composite component may be provided. A monolithic rod may be inserted into a porous ceramic preform. The ceramic preform may be formed into a ceramic matrix composite body that includes the monolithic rod. A portion of the monolithic rod may be removed, leaving a remaining portion in the ceramic matrix composite body. The remaining portion may include walls that define the opening in the ceramic matrix composite body. Alternatively or in addition, a ceramic matrix composite component may be provided. The ceramic matrix composite component may comprise a ceramic matrix composite body that includes a portion of a monolithic rod. The portion of the monolithic rod forms a lining around a hole passing partly or entirely through a length of the monolithic rod.
摘要翻译：可以提供在陶瓷基复合部件中形成孔的方法。单块棒可以插入多孔陶瓷预制件中。陶瓷预制件可以形成为包括整体棒的陶瓷基体复合体。可以去除整块棒的一部分，在陶瓷基体复合体中留下剩余部分。剩余部分可以包括限定陶瓷基体复合体中的开口的壁。或者或另外，可以提供陶瓷基复合部件。陶瓷基复合材料组件可以包括陶瓷基体复合体，其包括整体棒的一部分。单块杆的一部分在通过部分或完全穿过整体杆的长度的孔周围形成衬里。

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