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1.发明公开
公开(公告)号：EP3502563A2
公开(公告)日：2019-06-26
申请号：EP18214255.4
申请日：2018-12-19
发明人： MOURA, Dennis M. , CLUM, Carey
CPC分类号： F23R3/002 , F01D5/189 , F01D9/065 , F05D2240/35 , F05D2260/201 , F05D2260/202 , F05D2260/205 , F05D2260/607 , F23M5/08 , F23R3/005 , F23R3/06 , F23R2900/00004 , F23R2900/03042 , F23R2900/03043 , F23R2900/03044
摘要： A gas turbine engine component assembly is provided. The gas turbine engine component assembly (100), comprising: a first component (600) having a first surface (610), a second surface (620) opposite the first surface, and a cooling hole (307) extending from the second surface to the first surface through the first component; a second component (400) having a first surface (410) and a second surface (420), the first surface of the first component and the second surface of the second component defining a cooling channel (390) therebetween in fluid communication with the cooling hole for cooling the second surface of the second component; and a particulate capture device (500, 800) attached to at least one of the first component and the second component, the particulate capture device configured to aerodynamically separate the airflow (590) from the particulate (592).
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2.发明公开
公开(公告)号：EP3421733A1
公开(公告)日：2019-01-02
申请号：EP17179199.9
申请日：2017-06-30
CPC分类号： F01D11/24 , F01D25/246 , F05D2240/14 , F05D2260/205
摘要： Vane carrier for a gas turbine plant extending along a longitudinal axis (A) and comprising at least one clearance control cavity (29) which extends transversally with respect to the longitudinal axis (A).
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公开(公告)号：EP2900961B1
公开(公告)日：2018-11-21
申请号：EP13840873.7
申请日：2013-09-24
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.
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公开(公告)号：EP2295728B1
公开(公告)日：2018-10-03
申请号：EP10171849.2
申请日：2010-08-04
发明人： Inomata, Asako , Yamashita, Katsuya , Saito, Kazuhiro , Inukai, Takao , Wada, Kunihiko , Ikeda, Kazutaka , Suga, Takeo
CPC分类号： F01D25/12 , F01D25/26 , F05D2220/31 , F05D2260/205 , F05D2260/2322
摘要： A steam turbine (10) is provided with a double-structure comprising an inner casing (20) and an outer casing (21). A turbine rotor (22), in which plural stages of moving blades (24) are circumferentially implanted, is operatively disposed in inner casing (20). A diaphragm outer ring (25) and a diaphragm inner ring are disposed along the circumferential direction in inner casing (20). Stationary blades (27) are circumferentially provided between diaphragm outer ring (25) and the diaphragm inner ring, so that diaphragm outer ring (25), the diaphragm inner ring and stationary blades (27) form a stage of stationary blades. The stages of the stationary blades are arranged alternately with the stages of moving blades (24) in the axial direction of turbine rotor (22). A cooling medium passage (40) for passing a cooling medium CM which is supplied through a supply pipe (45) is formed between inner casing (20) and diaphragm outer ring (25).
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公开(公告)号：EP3186485B1
公开(公告)日：2018-07-04
申请号：EP15750321.0
申请日：2015-08-05
CPC分类号： F01D5/187 , F01D5/188 , F01D5/189 , F01D9/041 , F01D25/12 , F05D2240/12 , F05D2240/30 , F05D2240/81 , F05D2260/201 , F05D2260/205
摘要： The present invention relates to a turbine assembly (10, 10a, 10b) comprising a basically hollow aerofoil (12) having at least a main cavity (14) with at least an impingement tube (16, 16b), which is insertable inside the main cavity (14) of the hollow aerofoil (12) and is used for impingement cooling of at least an inner surface (18) of the main cavity (14), and with at least a platform (20, 20'), which is arranged at a radial end (22, 22') of the hollow aerofoil (12), and with at least a cooling chamber (24, 24') used for cooling of at least the platform (20, 20') and which is arranged relative to the hollow aerofoil (12) on an opposed site of the at least one platform (20, 20') and wherein the at least one cooling chamber (24, 24') is limited at a first radial end (26, 26') by at least one a wall segment (28, 28') of the platform (20, 20') and at an opposed radial second end (30, 30') from at least a cover plate (32, 32'), and wherein the impingement tube (16, 16b) extends in span wise direction (34) at least completely through the cooling chamber (24, 24') from the platform (20, 20') to the cover plate (32, 32'). To minimised aerofoil cooling feed temperatures and increase impingement cooling effectiveness the impingement tube (16, 16b) restricts a sub-cavity (36) of the main cavity (14) and wherein the at least one wall segment (28, 28') of the at least one platform (20, 20') comprises at least one entry aperture (38, 38'; 38a, 38a') for a cooling medium (40) to enter through the at least one entry aperture (38, 38'; 38a, 38a') from the at least one cooling chamber (24, 24') of the at least one platform (20, 20') into the sub-cavity (36) of the hollow aerofoil (12).
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公开(公告)号：EP3315724A1
公开(公告)日：2018-05-02
申请号：EP17197311.8
申请日：2017-10-19
CPC分类号： F01D5/187 , F01D5/147 , F01D9/041 , F02C3/04 , F05D2220/32 , F05D2240/122 , F05D2240/304 , F05D2240/35 , F05D2250/185 , F05D2260/202 , F05D2260/205
摘要： A trailing edge cooling system for a multi-wall blade 6, including: a set of outward legs 134 extending toward a trailing edge of the multi-wall blade and fluidly coupled to a coolant feed; a set of return legs 138 extending away from the trailing edge of the multi-wall blade and fluidly coupled to a coolant collection passage 146; and a connecting system for fluidly coupling the set of outward legs and the set of return legs; wherein the set of outward legs is radially offset from the set of return legs along a radial axis of the multi-wall blade.
摘要翻译： 一种用于多壁叶片6的后缘冷却系统，其包括：一组向外的支腿134，其向多壁叶片的后缘延伸并且流体地联接到冷却剂供给装置; 从多壁叶片的后缘延伸并且流体地联接到冷却剂收集通道146的一组返回腿138; 以及连接系统，用于流体连接所述一组向外腿和所述一组返回腿; 其中所述一组向外的腿沿着所述多壁叶片的径向轴线从所述一组返回腿径向偏移。
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公开(公告)号：EP3315723A1
公开(公告)日：2018-05-02
申请号：EP17197310.0
申请日：2017-10-19
CPC分类号： F01D5/187 , F01D5/147 , F01D9/041 , F02C3/04 , F05D2220/32 , F05D2240/122 , F05D2240/304 , F05D2240/35 , F05D2250/185 , F05D2260/202 , F05D2260/205
摘要： A trailing edge cooling system for a multi-wall blade, including: a cooling circuit 32, including: an outward leg 34 extending toward a trailing edge 14 of the multi-wall blade and fluidly coupled to a coolant feed; a return leg 38 extending away from the trailing edge of the multi-wall blade and fluidly coupled to a coolant collection passage 46; and a turn 36 for coupling the outward leg and the return leg; wherein the outward leg is radially offset from the return leg along a radial axis of the multi-wall blade.
摘要翻译： 一种用于多壁叶片的后缘冷却系统，包括：冷却回路32，其包括：朝向多壁叶片的后缘14延伸并流体联接至冷却剂进料的向外支柱34; 从多壁叶片的后缘延伸并且流体联接到冷却剂收集通道46的返回腿38; 以及用于连接外腿和返腿的转弯36; 其中所述向外的腿沿着所述多壁叶片的径向轴线从所述返回腿径向偏移。
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公开(公告)号：EP2740900A3
公开(公告)日：2018-03-14
申请号：EP13194598.2
申请日：2013-11-27
CPC分类号： F01D9/041 , F01D5/187 , F01D5/288 , F05D2260/204 , F05D2260/205
摘要： A system (60) for removing heat from a turbine (26) includes a component in the turbine (26) having a supply plenum (80) and a return plenum (82) therein. A substrate (110) that defines a shape of the component has an inner surface (112) and an outer surface (114). A coating (116) applied to the outer surface (114) of the substrate (110) has an interior surface (118) facing the outer surface (114) of the substrate (110) and an exterior surface (120) opposed to the interior surface (118). A first fluid channel is between the outer surface (114) of the substrate (110) and the exterior surface (120) of the coating (116). A first fluid path (128) is from the supply plenum (80), through the substrate (110), and into the first fluid channel, and a second fluid path (130) is from the first fluid channel, through the substrate (110), and into the return plenum (82).
摘要翻译： 用于从涡轮机（26）去除热量的系统（60）包括涡轮机（26）中的具有供应增压室（80）和返回增压室（82）的部件。 限定部件形状的基板（110）具有内表面（112）和外表面（114）。 施加到基底（110）的外表面（114）上的涂层（116）具有面向基底（110）的外表面（114）的内表面（118）和与内表面（120）相对的外表面 表面（118）。 第一流体通道位于基底（110）的外表面（114）和涂层（116）的外表面（120）之间。 第一流体路径（128）来自供应室（80），穿过基板（110）并进入第一流体通道，并且第二流体路径（130）来自第一流体通道，穿过基板（110） ），并进入回气室（82）。
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公开(公告)号：EP2946077B1
公开(公告)日：2018-03-07
申请号：EP14711497.9
申请日：2014-03-18
发明人： SZIJARTO, Janos , WANG, Lieke
CPC分类号： F01D5/081 , F01D5/187 , F01D9/023 , F05D2240/81 , F05D2260/201 , F05D2260/205
摘要： A platform cooling device (10) for directing a cooling fluid onto a root side (52) of a platform (50) of a turbomachine part (2) is presented. The platform cooling device (10) includes a first segment (20) to be positioned at a root (60) of the turbomachine part (2) and a second segment (30), at an angle to the first segment (20), to be positioned at the root side (52) of the platform (50) of the turbomachine part (2). The second segment (30 includes at least one impingement channel (32) having an inlet (34) for receiving at least a part of the cooling fluid and an outlet (36) for releasing the received cooling fluid onto the root side (52) of the platform (50). The first segment (20) and the second segment (30) define a path for the cooling fluid via the impingement channel (32). A turbomachine component (1) including the platform cooling device (10) is also presented.
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公开(公告)号：EP3284944A1
公开(公告)日：2018-02-21
申请号：EP17186506.6
申请日：2017-08-16
发明人： Geyer, Marc , Goetz, Andreas , Birck, Torben
CPC分类号： F02K9/64 , F02K9/972 , F05D2250/312 , F05D2260/205 , F05D2260/31
摘要： The disclosure relates to a combustion chamber structure (10), particularly for a rocket engine, which comprises a liner (12) surrounding a combustion chamber (14) with an outer surface (32) facing away from the combustion chamber (14) on which coolant channels (38) extending in a longitudinal direction of the liner (12) are formed. The liner (12) forms, at one longitudinal end, a coolant chamber (16, 17) extending in the circumferential direction of the liner (12) for collecting and/or distributing a coolant. The combustion chamber structure (10) further comprises a connecting structure (40, 41) that fluidly connects the coolant chamber (16, 17) to the coolant channels (38).
摘要翻译： 本发明涉及一种燃烧室结构（10），尤其是用于火箭发动机的燃烧室结构（10），其包括围绕燃烧室（14）的衬套（12），其具有背向燃烧室（14）的外表面（32），在燃烧室 形成沿着衬里（12）的纵向方向延伸的冷却剂通道（38）。 内衬（12）在一个纵向端部处形成沿内衬（12）的圆周方向延伸的冷却剂室（16,17），用于收集和/或分配冷却剂。 燃烧室结构（10）还包括将冷却剂室（16,17）流体连接到冷却剂通道（38）的连接结构（40,41）。
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