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51. 发明申请

US20150260102A1 HEAT EXCHANGER FOR A TURBO ENGINE 有权
标题翻译：涡轮发动机换热器
公开(公告)号：US20150260102A1
公开(公告)日：2015-09-17
申请号：US14577097
申请日：2014-12-19
申请人： SNECMA
发明人： Imane GHAZLANE , Gabriela Philippart
IPC分类号： F02C7/18
CPC分类号： F02C7/185 , F01D25/12 , F02C7/14 , F05D2200/20 , F05D2210/12 , F05D2250/16 , F05D2250/38 , F05D2260/205 , F05D2260/213 , F05D2260/221 , F05D2260/2214 , F05D2260/22141 , F05D2260/98 , F28D1/0233 , F28D2021/0021 , F28D2021/0049 , F28F3/048 , F28F3/12 , F28F2215/00 , Y02T50/671 , Y02T50/675
摘要： The invention relates to a heat exchanger of an air circulation channel of a turbomachine, the heat exchanger being configured so as to have fluid to be cooled passing through it and including a plurality of fins protruding from a support surface, the heat exchanger being characterized in that each fin includes a base and a preferably continuous leading face which extends axially from the base in the air circulation direction while tapering from upstream to downstream along an axis parallel with the support surface.
摘要翻译：本发明涉及一种涡轮机的空气循环通道的热交换器，该热交换器被配置为具有通过该冷却器的待冷却流体并且包括从支撑表面突出的多个翅片，该热交换器的特征在于每个翅片包括基部和优选地连续的前导面，其从空气循环方向上的基部轴向延伸，同时沿着平行于支撑表面的轴线从上游到下游逐渐变细。

52. 发明申请

US20150251376A1 LAYERED ARRANGEMENT, HOT-GAS PATH COMPONENT, AND PROCESS OF PRODUCING A LAYERED ARRANGEMENT 有权
标题翻译：层状布置，热气道组件和生产层状布置的过程
公开(公告)号：US20150251376A1
公开(公告)日：2015-09-10
申请号：US13630708
申请日：2012-09-28
申请人： General Electric Company
发明人： Xiuzhang James ZHANG , Haiping WANG
IPC分类号： B32B3/26 , B32B15/04 , F01D9/02 , B32B37/00
CPC分类号： B32B3/263 , B32B3/12 , B32B3/26 , B32B3/30 , B32B9/005 , B32B9/04 , B32B15/04 , B32B37/0084 , B32B37/12 , B32B37/144 , B32B37/146 , B32B37/16 , B32B2250/03 , B32B2262/105 , B32B2262/106 , B32B2307/304 , B32B2311/00 , B32B2315/02 , B32B2603/00 , B32B2605/18 , C04B35/01 , C04B35/117 , C04B35/185 , C04B35/48 , C04B35/5156 , C04B35/584 , C04B37/003 , C04B37/025 , C04B37/04 , C04B2237/068 , C04B2237/34 , C04B2237/341 , C04B2237/343 , C04B2237/36 , C04B2237/363 , C04B2237/365 , C04B2237/368 , C04B2237/38 , C04B2237/403 , C04B2237/405 , C04B2237/406 , C04B2237/597 , C04B2237/704 , C04B2237/706 , C04B2237/72 , F01D5/187 , F01D9/02 , F01D11/24 , F05D2240/11 , F05D2240/12 , F05D2240/126 , F05D2240/15 , F05D2240/24 , F05D2240/303 , F05D2240/81 , F05D2250/232 , F05D2250/241 , F05D2250/28 , F05D2250/291 , F05D2260/20 , F05D2260/204 , F05D2260/22141 , F05D2300/175 , F05D2300/20 , F05D2300/6033 , Y10T428/24562 , Y10T428/24612 , Y10T428/24942 , Y10T428/24967
摘要： A layered arrangement, a hot-gas path component, and a process of producing a layered arrangement are disclosed. The layered arrangement includes a substrate layer, a ceramic matrix composite layer, and a non-metal spacer between the substrate layer and the ceramic matrix composite layer configured to define one or more pockets. The hot-gas-path component includes a nickel-based superalloy layer, a ceramic matrix composite layer, and a ceramic spacer between the nickel-based superalloy layer and the ceramic matrix composite layer. The ceramic spacer is mechanically secured to one or both of the substrate layer and the ceramic matrix composite layer, and the ceramic spacer is bonded to the substrate layer or the ceramic matrix composite layer. The process includes securing a non-metal spacer between a substrate layer and a ceramic matrix composite layer of the layered arrangement.
摘要翻译：公开了一种分层布置，热气路径部件和制造分层布置的工艺。分层布置包括基底层，陶瓷基质复合层和在衬底层和陶瓷基质复合层之间的非金属间隔物，其被配置为限定一个或多个口袋。热气路部件包括镍基超合金层，陶瓷基复合层和镍基超合金层与陶瓷基复合层之间的陶瓷间隔物。将陶瓷间隔件机械地固定到基底层和陶瓷基复合层中的一个或两个，陶瓷间隔物结合到基底层或陶瓷基复合层。该方法包括在分层布置的基底层和陶瓷基体复合层之间固定非金属间隔物。

53. 发明授权

US09115590B2 Gas turbine engine airfoil cooling circuit 有权
标题翻译：燃气涡轮发动机翼型冷却回路
公开(公告)号：US09115590B2
公开(公告)日：2015-08-25
申请号：US13627072
申请日：2012-09-26
申请人： United Technologies Corporation
发明人： Brandon W. Spangler , Mark F. Zelesky , Edwin Otero
IPC分类号： F01D5/18
CPC分类号： F01D5/18 , F01D5/187 , F05D2260/202 , F05D2260/205 , F05D2260/22141 , Y02T50/676
摘要： A component for a gas turbine engine according to an exemplary aspect of the present disclosure includes, among other things, an airfoil that extends between a leading edge, a trailing edge, a pressure side wall and a suction side wall. A cooling circuit is disposed inside of the airfoil. The cooling circuit includes a first core cavity that radially extends inside of the airfoil. A first axial skin core is in fluid communication with the first core cavity at a first location of the first axial skin core and a second core cavity is in fluid communication with the first axial skin core at a second location of the first axial skin core.
摘要翻译：根据本公开的示例性方面的用于燃气涡轮发动机的部件尤其包括在前缘，后缘，压力侧壁和吸力侧壁之间延伸的翼型件。冷却回路设置在翼型的内部。冷却回路包括在翼型件内径向延伸的第一芯腔。第一轴向皮肤芯在第一轴向皮肤芯的第一位置处与第一芯腔流体连通，并且第二芯腔在第一轴向皮肤芯的第二位置处与第一轴向皮肤芯流体连通。

54. 发明申请

US20150198063A1 COOLED STATOR HEAT SHIELD 审中-公开
标题翻译：冷却式定温器
公开(公告)号：US20150198063A1
公开(公告)日：2015-07-16
申请号：US14592127
申请日：2015-01-08
申请人： ALSTOM Technology Ltd
发明人： Petr Vitalievich LALETIN , Andrey Anatolievich Sedlov , Anton Titov , Maxim Plodistyy
IPC分类号： F01D25/12 , F01D9/02
CPC分类号： F01D25/12 , F01D9/04 , F01D11/10 , F05D2240/11 , F05D2240/15 , F05D2250/15 , F05D2260/201 , F05D2260/202 , F05D2260/22141
摘要： The present invention provides a stator heat shield for a gas turbine. The gas turbine includes a rotor defining an axis of rotation. The stator heat shield includes a plurality of cooling units disposed in array along the axis of rotation. Each of the cooling units includes an outside part facing hot gas path of the gas turbine, and an inside plate positioned on the outside part and exposed to cooling air, wherein the inside plate comprises a plurality of inlet openings formed through the inside plate to introduce the cooling air into the outside part and thereby impingement cooling of the hot gas washed wall of the outside part. The outside part includes a cooling air channel formed therein with a first central portion to receive the cooling air, and a second spiral portion around the first central portion to convey the cooling air outward to a cooling air outlet of the second spiral portion. Initial investigation of the proposed cooling scheme in the present invention shows that the cooling air saving of 40% is expected compared to the common design.
摘要翻译：本发明提供一种用于燃气轮机的定子隔热罩。燃气涡轮机包括限定旋转轴线的转子。定子隔热罩包括沿着旋转轴设置成阵列的多个冷却单元。每个冷却单元包括面对燃气轮机的热气路的外部部分和位于外部部分并暴露于冷却空气的内侧板，其中内侧板包括通过内侧板形成的多个入口，以引入冷却空气进入外部部分，从而冲击外部部分的热气体洗涤壁的冷却。外部部分包括形成有第一中心部分以接收冷却空气的冷却空气通道，以及围绕第一中心部分的第二螺旋部分，以将冷却空气向外输送到第二螺旋部分的冷却空气出口。本发明所提出的冷却方案的初步调查表明，与普通设计相比，预计节约了40％的冷却空气。

55. 发明申请

US20150184524A1 TURBINE AIRFOIL WITH AN INTERNAL COOLING SYSTEM HAVING TRIP STRIPS WITH REDUCED PRESSURE DROP 有权
标题翻译：具有减少压力下降的牵引带的内部冷却系统的涡轮机
公开(公告)号：US20150184524A1
公开(公告)日：2015-07-02
申请号：US14140589
申请日：2013-12-26
申请人： Jose L. Rodriguez , Matthew J. Golsen
发明人： Jose L. Rodriguez , Matthew J. Golsen
IPC分类号： F01D5/18 , F01D9/02
CPC分类号： F01D5/188 , F01D5/187 , F01D9/02 , F05D2240/127 , F05D2250/711 , F05D2250/712 , F05D2260/2212 , F05D2260/22141
摘要： A turbine airfoil usable in a turbine engine and having at least one cooling system with an efficient trip strip is disclosed At least a portion of the cooling system may include one or more cooling channels having one or more trip strips protruding from an inner surface forming the cooling channel. The trip strip may have improved operating characteristics including enhanced heat transfer capabilities and a substantial reduction in pressure drop typically associated with conventional trip strips In at least one embodiment, the trip strip may have a cross-sectional area with a first section of an upstream surface of the trip strip being positioned nonparallel and nonorthogonal to a surface forming the cooling system channel extending upstream from the at least one trip strip and a concave shaped downstream surface of the at least one trip strip that enables separated flow to reattach to the cooling fluid flow.
摘要翻译：公开了一种可用于涡轮发动机并且具有至少一个具有有效跳闸带的冷却系统的涡轮机翼型。冷却系统的至少一部分可包括一个或多个冷却通道，该冷却通道具有从内表面突出的一个或多个跳闸条，冷却通道。脱扣带可以具有改进的操作特性，包括增强的热传递能力和通常与常规跳闸带相关联的压差的显着降低。在至少一个实施例中，跳闸带可具有横截面积，其具有上游表面的第一部分所述跳闸条与所述至少一个跳闸带的上游延伸的所述冷却系统通道的表面非平行且非正交地定位，并且所述至少一个跳闸带的凹形下游表面使得能够分离的流重新连接到所述冷却流体流。

56. 发明申请

US20150176412A1 ROTOR BLADE AND GUIDE VANE AIRFOIL FOR A GAS TURBINE ENGINE 有权
标题翻译：用于气体涡轮发动机的转子叶片和导向空气涡轮机
公开(公告)号：US20150176412A1
公开(公告)日：2015-06-25
申请号：US14574897
申请日：2014-12-18
申请人： ALSTOM Technology Ltd
发明人： Joerg KRUECKELS , Marc WIDMER
IPC分类号： F01D5/18 , F01D9/02
CPC分类号： F01D5/187 , F01D9/02 , F05D2250/292 , F05D2260/2212 , F05D2260/22141
摘要： The invention refers to a rotor blade or guide vane airfoil for a gas turbine engine having a longitudinal axis and a source of cooling fluid. The airfoil has a pressure wall, a suction wall, a leading edge, a trailing edge and at least one cooling fluid flow passage. The cooling fluid flow passage is in fluid communication with the source of cooling fluid. Means for directing cooling fluid at least to the trailing edge are provided, whereas the cooling fluid flow passage including: a plurality of axially extending walls, each of the walls extending laterally between the pressure wall and suction wall. The plurality of walls are radially spaced within the cooling fluid flow passage such that adjacent pairs of walls define a channel. The axial spacing between the adjacent walls include in radial direction of the airfoil a pins and a ribs structure, wherein the pins holistic or approximately cover the axial height of the channel. The ribs have a deeper level with respect to the pins and the ribs establish a bridge-like connection between each of adjacent ribs.
摘要翻译：本发明涉及一种用于燃气涡轮发动机的转子叶片或导叶翼型件，其具有纵向轴线和冷却流体源。翼型件具有压力壁，吸力壁，前缘，后缘和至少一个冷却流体流动通道。冷却流体流动通道与冷却流体源流体连通。提供了用于将冷却流体引导至后缘的装置，而冷却流体流动通道包括：多个轴向延伸的壁，每个壁在压力壁和抽吸壁之间横向延伸。多个壁在冷却流体流动通道内径向间隔开，使得相邻的壁对形成通道。相邻壁之间的轴向间隔在翼型件的径向方向上包括销和肋结构，其中销整体地或近似地覆盖通道的轴向高度。这些肋相对于销具有更深的水平，并且肋在每个相邻的肋之间建立桥状连接。

57. 发明授权

US09051943B2 Gas turbine engine heat exchanger fins with periodic gaps 有权
标题翻译：具有周期性间隙的燃气涡轮发动机换热器翅片
公开(公告)号：US09051943B2
公开(公告)日：2015-06-09
申请号：US12939252
申请日：2010-11-04
申请人： James S. Elder
发明人： James S. Elder
IPC分类号： F01D25/12 , F04D29/58 , F02K3/115 , F02C7/14 , F02K3/06 , F02C7/143 , F02C7/141
CPC分类号： F04D29/584 , F01D25/12 , F02C7/14 , F02C7/141 , F02C7/143 , F02K3/06 , F02K3/115 , F04D29/5826 , F04D29/5853 , F05D2260/22141 , F05D2260/98 , Y02T50/675
摘要： A heat exchanger for a gas turbine engine is provided by a structure including an enclosed fluid cavity. The structure has opposing sides, and a set of fins is supported on one of the sides and arranged outside the cavity. The set of fins includes rows of discrete chevron fins separated by periodic gaps. In one application, the heat exchanger is arranged in a gas turbine engine. A core is supported relative to a fan case by structure. A fan duct is provided between a core nacelle and a fan case. The core includes a compressor section and a bleed cavity is provided within the core and is in fluid communication with the compressor section. The heat exchanger includes first and second sides opposite one another. The second side includes the set of rows of fins with the periodic gaps exposed to the bleed cavity.
摘要翻译：用于燃气涡轮发动机的热交换器由包括封闭流体腔的结构提供。该结构具有相对的侧面，并且一组翅片支撑在一个侧面上并且布置在腔的外部。翅片组包括由周期性间隙隔开的离散人字形翅片排。在一个应用中，热交换器被布置在燃气涡轮发动机中。相对于风扇的结构，支持核心。在机舱和风扇壳之间设有风扇导管。芯部包括压缩机部分，并且排出腔设置在芯部内并与压缩机部分流体连通。热交换器包括彼此相对的第一和第二侧。第二侧包括具有暴露于放气腔的周期性间隙的翅片排。

58. 发明申请

US20150139813A1 TURBINE 审中-公开
标题翻译：涡轮
公开(公告)号：US20150139813A1
公开(公告)日：2015-05-21
申请号：US14541716
申请日：2014-11-14
申请人： Samsung Techwin Co., Ltd.
发明人： Myunghwan CHO , Jaekyung SIM
IPC分类号： F01D5/18 , F01D5/22
CPC分类号： F01D5/187 , F05D2260/22141
摘要： Provided is a turbine including a rotor; a blade provided on the rotor and comprising a cooling flow path through which a cooling fluid flows; and a shroud surrounding an exterior of the blade, wherein the blade includes: at least one rib turbulator protruding into the cooling flow path; and at least one subsidiary protrusion protruding from an outer surface of the at least one rib turbulator.
摘要翻译：提供一种包括转子的涡轮机; 叶片，其设置在转子上并且包括冷却流路，冷却流体通过冷却流路流动; 以及围绕所述叶片的外部的护罩，其中所述刀片包括：突出到所述冷却流动路径中的至少一个肋状紊流器; 以及从所述至少一个肋状湍流器的外表面突出的至少一个辅助突起。

59. 发明授权

US09016065B2 Coil arrangement for air intake system for gas turbine and methods 有权
标题翻译：燃气轮机进气系统线圈布置及方法
公开(公告)号：US09016065B2
公开(公告)日：2015-04-28
申请号：US13026801
申请日：2011-02-14
申请人： Theodore Philip Bezat
发明人： Theodore Philip Bezat
IPC分类号： F02C7/08 , F02C7/143 , F02C7/047 , F02C7/055 , F28F13/14
CPC分类号： F02C7/143 , F02C7/047 , F02C7/055 , F05D2230/80 , F05D2260/208 , F05D2260/22141 , F28F13/14 , Y10T29/49238
摘要： An air intake system for a gas turbine includes one or more coils in airflow communication with an inlet arrangement. Each coil is constructed and arranged to have a respective upstream face velocity that is intended to be within 20% of the other coils. Each coil utilizes a working fluid of a predetermined temperature range conveyed there through and a plurality of spaced fins. The fins are spaced apart to permit air to flow between adjacent fins as air flows through the coil. At least one of the coils has a number of fins per inch that is different from the number of fins per inch of the other coils. Alternatively, each individual coil has at least one section with fewer or greater numbers of fins per inch that the other sections of that coil.
摘要翻译：用于燃气轮机的进气系统包括与入口装置气流连通的一个或多个线圈。每个线圈被构造和布置成具有预期在其它线圈的20％以内的各自的上游面速度。每个线圈使用通过其输送的预定温度范围的工作流体和多个间隔开的翅片。当空气流过线圈时，翅片间隔开以允许空气在相邻翅片之间流动。线圈中的至少一个具有与每英寸其他线圈的翅片数不同的每英寸数量的翅片。或者，每个单独的线圈具有至少一个具有每英寸更少或更多数量的翅片的部分，该线圈的其它部分。

60. 发明申请

US20150096305A1 METHOD AND SYSTEM FOR PROVIDING COOLING FOR TURBINE COMPONENTS 有权
标题翻译：用于提供涡轮机组件冷却的方法和系统
公开(公告)号：US20150096305A1
公开(公告)日：2015-04-09
申请号：US14046437
申请日：2013-10-04
申请人： General Electric Company
发明人： Victor John Morgan , John Wesley Harris, Jr. , Michael James Healy , Aaron Ezekiel Smith , Brian Gene Brzek , Donald Earl Floyd, II
IPC分类号： F01D5/18
CPC分类号： F01D5/18 , F01D5/183 , F01D5/186 , F01D5/187 , F01D9/065 , F05D2230/21 , F05D2230/90 , F05D2240/122 , F05D2260/202 , F05D2260/204 , F05D2260/22141 , F05D2300/612
摘要： A method and system for providing cooling of a turbine component that includes a region to be cooled is provided. A recess is defined within the region to be cooled, and includes an inner face. At least one support projection extends from the inner face. The at least one support projection includes a free end. A cover is coupled to the region to be cooled, such that an inner surface of the cover is coupled to the free end of the at least one support projection, such that at least one cooling fluid passage is defined within the region to be cooled.
摘要翻译：提供了一种用于提供包括待冷却区域的涡轮机部件的冷却的方法和系统。在待冷却的区域内限定凹部，并且包括内表面。至少一个支撑突起从内表面延伸。所述至少一个支撑突起包括自由端。盖被联接到要冷却的区域，使得盖的内表面联接到至少一个支撑突起的自由端，使得至少一个冷却流体通道限定在待冷却的区域内。

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