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1. 发明授权

EP2956623B1 TAPERED THERMAL BARRIER COATING ON CONVEX AND CONCAVE TRAILING EDGE SURFACES 有权转让
公开(公告)号：EP2956623B1
公开(公告)日：2018-12-05
申请号：EP13877747.9
申请日：2013-12-30
申请人： United Technologies Corporation
发明人： LEVINE, Jeffrey R
IPC分类号： F01D5/14 , F01D5/18 , F02C7/18
CPC分类号： F01D5/288 , F01D5/185 , F01D5/187 , F01D9/02 , F01D25/12 , F05D2220/30 , F05D2230/312 , F05D2230/313 , F05D2230/90 , F05D2260/231 , F05D2300/21 , Y10T29/49343
摘要： A turbine engine component has an airfoil portion having a pressure side, a suction side, and a trailing edge. The trailing edge has a center discharge cooling circuit, which center discharge cooling circuit has an exit defined by a concave surface on the pressure side of the airfoil portion and a convex surface on the suction side of the airfoil portion. The airfoil portion has a thermal barrier coating on the pressure side and the suction side. The thermal barrier coating on the convex surface tapers to zero in thickness at a point spaced from the trailing edge so as to leave an uncoated portion on the convex surface.

2. 发明公开

EP3279435A2 COMPONENT WITH INTEGRAL WALL PASSAGE 有权转让
标题翻译：与积分墙通道的组件
公开(公告)号：EP3279435A2
公开(公告)日：2018-02-07
申请号：EP17184335.2
申请日：2017-08-01
申请人： United Technologies Corporation
发明人： JOHNSON, Javier N. , BATES, Chris , BEACH, Eric , FARAH, Jorge I.
IPC分类号： F01D5/18 , F02K3/10 , F23R3/20
CPC分类号： F23R3/20 , B33Y10/00 , B33Y80/00 , F01D5/185 , F01D9/041 , F01D9/06 , F02K3/10 , F05D2220/32 , F05D2230/12 , F05D2230/20 , F05D2230/22 , F05D2230/31 , F05D2230/53 , F05D2240/12 , F05D2260/20 , F05D2260/232 , F05D2300/17 , F23R3/286
摘要： An aerospace component (102) includes a wall (122) with an integral longitudinal wall passage (120) formed therein, the integral longitudinal wall passage (120) including at least one entrance aperture (126) and at least one exit aperture (132), the exit aperture (132) transverse to the integral longitudinal wall passage (120). The aerospace component (102) may be additively manufactured.
摘要翻译：一种航空航天部件（102）包括具有形成在其中的整体纵向壁通道（120）的壁（122），所述整体纵向壁通道（120）包括至少一个入口孔（126）和至少一个出口孔（132），横向于整体纵向壁通道（120）的出口孔（132）。航空航天部件（102）可以附加地制造。

3. 发明公开

EP3176372A1 A COOLED COMPONENT OF GAS TURBINE ENGINE 审中-公开
标题翻译：燃气涡轮发动机的冷却组件
公开(公告)号：EP3176372A1
公开(公告)日：2017-06-07
申请号：EP16196583.5
申请日：2016-10-31
申请人： Rolls-Royce plc
发明人： Harding, Adrian
IPC分类号： F01D5/18 , F01D25/10 , F01D25/12
CPC分类号： F02C7/12 , F01D5/185 , F01D5/186 , F01D5/187 , F01D9/04 , F01D25/10 , F01D25/12 , F02C7/24 , F05D2220/32 , F05D2230/22 , F05D2230/31 , F05D2240/35 , F05D2240/36 , F05D2260/20 , F05D2260/202 , F05D2260/204 , F23R3/005 , F23R3/06 , F23R2900/03042 , F23R2900/03043 , F23R2900/03044
摘要： A cooled gas turbine engine component comprises a wall (40) having a plurality of effusion cooling apertures (50) extending there-through from a first surface (41) to a second surface (43). Each aperture (50) has an inlet (52) in the first surface (41) and an outlet (54) in the second surface (43). Each aperture (50) comprises an inlet portion (56), a collection chamber (58), a metering portion (60), a U-shaped bend portion (62) and a diffusing portion (64) arranged in flow series from the inlet (52) to the outlet (54). The inlet portion (56) of each aperture (50) is arranged substantially perpendicularly to a surface of the collection chamber (58). The metering portion (60) of each aperture (50) is arranged to extend longitudinally from a first lateral side of the collection chamber (58) and the diffusing portion (64) of each aperture (50) is arranged at an angle to the second surface (43). Each outlet (54) has a quadrilateral shape in the second surface of the wall (40) and each outlet (54) is displaced laterally from the metering portion (60).
摘要翻译：冷却的燃气涡轮发动机部件包括具有多个从第一表面（41）延伸到第二表面（43）的喷射冷却孔（50）的壁（40）。每个孔（50）在第一表面（41）中具有入口（52）并且在第二表面（43）中具有出口（54）。每个孔50包括从入口流动串联布置的入口部分56，收集腔室58，计量部分60，U形弯曲部分62和扩散部分64，（52）至出口（54）。每个孔（50）的入口部分（56）基本垂直于收集室（58）的表面设置。每个孔（50）的计量部分（60）被布置为从收集腔室（58）的第一侧面纵向延伸，并且每个孔（50）的扩散部分（64）与第二孔表面（43）。每个出口（54）在壁（40）的第二表面中具有四边形形状，并且每个出口（54）从计量部分（60）横向移位。

4. 发明公开

EP2947274A1 TURBULATING COOLING STRUCTURES 无效转让
标题翻译：涡轮冷却结构
公开(公告)号：EP2947274A1
公开(公告)日：2015-11-25
申请号：EP15168472.7
申请日：2015-05-20
申请人： United Technologies Corporation
发明人： MONGILLO, Dominic J. , PROPHETER-HINCKLEY, Tracy A. , XU, JinQuan
IPC分类号： F01D5/18
CPC分类号： B22F3/1055 , B22F1/0003 , B22F5/009 , B22F5/04 , B22F5/10 , B22F7/06 , B23K15/0086 , B23K15/0093 , B23K26/0006 , B23K26/342 , B23K2203/26 , B23K2203/50 , B23K2203/52 , B23K2203/54 , B33Y10/00 , B33Y80/00 , C04B35/622 , C04B2235/6026 , C04B2235/665 , C04B2235/94 , C04B2235/963 , F01D5/185 , F01D5/187 , F01D9/065 , F05D2230/31 , F05D2240/31 , F05D2260/2212 , F05D2260/22141 , F05D2300/516 , Y02P10/295
摘要： In a first embodiment, a hollow gas turbine engine workpiece (12;12a;12b) comprises first and second walls (102a,104a) formed via additive manufacturing, and a cooling passage (108a,108b) defined between the first and second walls (102a,104a) by a surface of the first and second walls (102a,104a) having arithmetic average surface roughness (ε) of at least 100 µin (0.0025mm).
In a second embodiment, a method of manufacture of a gas turbine engine component (12;12a;12b) comprises depositing successive layers (L) of pulverant material (20) via additive manufacturing to form first and second walls (102a,104a) defining a cooling passage (108a;108b) therebetween, and loading a grain size (G) of the pulverant material (20) to produce lattice convective cooling design networks of various size and proportions with each having a range of relative roughness values, 0.10
摘要翻译：在第一实施例中，中空燃气涡轮发动机工件（12; 12a; 12b）包括经由增材制造形成的第一和第二壁（102a，104a）以及限定在第一和第二壁（108a，108b）之间的冷却通道 102a，104a）的表面具有至少100μin（0.0025mm）的算术平均表面粗糙度（ε）的第一和第二壁（102a，104a）的表面。在第二实施例中，一种制造燃气涡轮发动机部件（12; 12a; 12b）的方法包括通过增材制造沉积粉末状材料（20）的连续层（L）以形成第一和第二壁（102a，104a）（108a; 108b），并加载粉状材料（20）的晶粒尺寸（G）以产生各种尺寸和比例的晶格对流冷却设计网络，每个网络具有一定范围的相对粗糙度值，0.10 <ε /Dh<0.50以沿着冷却通道（108a; 108b）实现最佳的热冷却性能。

5. 发明公开

EP2540970A1 Liquid metal cooled blade 审中-公开
标题翻译： MitflüssigemMetallgekühlteSchaufel
公开(公告)号：EP2540970A1
公开(公告)日：2013-01-02
申请号：EP11172402.7
申请日：2011-07-01
申请人： SIEMENS AKTIENGESELLSCHAFT
发明人： Bahador, Mehdi
IPC分类号： F01D5/18
CPC分类号： F01D5/181 , F01D5/185 , F05D2260/207 , F05D2300/121 , F05D2300/1616
摘要： A blade (1) for a turbomachine is presented. The blade includes a leading edge (4) and a trailing edge (5), and a cavity (20) located at the leading edge (4) characterized in that the cavity (20) is at least partly filled by a material (19) which is liquid at operating temperature of the turbomachine.
摘要翻译：提出了一种用于涡轮机的叶片（1）。叶片包括前缘（4）和后缘（5），以及位于前缘（4）处的空腔（20），其特征在于，空腔（20）至少部分地由材料（19）填充，其在涡轮机的工作温度下为液体。

6. 发明授权

EP3604770B1 GAS TURBINE 有权
公开(公告)号：EP3604770B1
公开(公告)日：2024-08-28
申请号：EP18776659.7
申请日：2018-03-20
IPC分类号： F02C7/16 , B01D53/94 , F01D5/18 , F01D9/02 , F01D25/12 , F02C3/22 , F02C3/30 , F02C3/34 , F02C7/22 , F01D9/04 , F02C3/24
CPC分类号： F02C7/16 , F01D9/041 , F01D5/185 , F01D5/186 , F02C3/24 , F05D2260/20520130101 , F05D2260/23220130101 , F02C3/34 , B01D53/8631 , B01D53/90 , B01D2251/1120130101 , B01D2251/206220130101 , B01D2258/028320130101

7. 发明公开

EP3203027A1 TURBINE ENGINE AIRFOIL WITH COOLING 审中-公开
标题翻译：涡轮发动机机翼与冷却
公开(公告)号：EP3203027A1
公开(公告)日：2017-08-09
申请号：EP17154677.3
申请日：2017-02-03
申请人： General Electric Company
发明人： LESSARD, Bridget Lucy , REDDY, Bhanu Mahasamudram , ZHU, Gaoqiu , LEE, Michael J.
IPC分类号： F01D5/18
CPC分类号： F01D5/181 , F01D5/185 , F01D5/186 , F01D5/187 , F05D2260/20 , F05D2260/202 , F05D2260/203 , F05D2260/204 , Y02T50/676
摘要： An apparatus and method of cooling an airfoil (78) for a gas turbine engine (10) includes a tip (80) for the radially outer end of the airfoil (78) with internal ribs (108) defining cooling circuits (110) within an interior (96) of the airfoil (78). The ribs (108) can be full-length (120), extending between a root (82) and tip (80) of the airfoil (78). A gap (122) can be formed in the full-length ribs (120) near the tip (80) to form a thermal stress reduction structure (122) for the full-length rib (120).
摘要翻译：一种用于冷却用于燃气涡轮发动机（10）的翼型件（78）的设备和方法包括用于翼型件（78）的径向外端的尖端（80），其具有限定冷却回路（110）的内部肋（108）翼型件（78）的内部（96）。肋（108）可以是全长（120），在翼型件（78）的根部（82）和尖端（80）之间延伸。可在靠近尖端（80）的全长肋（120）中形成间隙（122）以形成全长肋（120）的热应力降低结构（122）。

8. 发明公开

EP2956623A4 TAPERED THERMAL BARRIER COATING ON CONVEX AND CONCAVE TRAILING EDGE SURFACES 有权转让
标题翻译：康奈尔·肯尼亚·肯尼亚·弗朗西斯科
公开(公告)号：EP2956623A4
公开(公告)日：2016-03-16
申请号：EP13877747
申请日：2013-12-30
申请人： UNITED TECHNOLOGIES CORP
发明人： LEVINE JEFFREY R
IPC分类号： F01D5/14 , F01D5/18 , F02C7/18
CPC分类号： F01D5/288 , F01D5/185 , F01D9/02 , F01D25/12 , F05D2220/30 , F05D2230/312 , F05D2230/313 , F05D2260/231 , F05D2300/21 , Y10T29/49343
摘要： A turbine engine component has an airfoil portion having a pressure side, a suction side, and a trailing edge. The trailing edge has a center discharge cooling circuit, which center discharge cooling circuit has an exit defined by a concave surface on the pressure side of the airfoil portion and a convex surface on the suction side of the airfoil portion. The airfoil portion has a thermal barrier coating on the pressure side and the suction side. The thermal barrier coating on the convex surface tapers to zero in thickness at a point spaced from the trailing edge so as to leave an uncoated portion on the convex surface.
摘要翻译：涡轮发动机部件具有具有压力侧，吸力侧和后缘的翼型部。后缘具有中心排出冷却回路，其中心排出冷却回路具有由翼型部的压力侧的凹面界定的出口和翼型部的吸入侧的凸面。翼型部分在压力侧和吸力侧具有热障涂层。凸表面上的隔热涂层在与后缘间隔开的位置处的厚度变薄到零，以便在凸面上留下未涂覆的部分。

9. 发明公开

EP2956623A2 TAPERED THERMAL BARRIER COATING ON CONVEX AND CONCAVE TRAILING EDGE SURFACES 有权转让
标题翻译：锥形热层ON凹凸REAR边缘的区域
公开(公告)号：EP2956623A2
公开(公告)日：2015-12-23
申请号：EP13877747.9
申请日：2013-12-30
申请人： United Technologies Corporation
发明人： LEVINE, Jeffrey R
IPC分类号： F01D5/14 , F01D5/18 , F02C7/18
CPC分类号： F01D5/288 , F01D5/185 , F01D5/187 , F01D9/02 , F01D25/12 , F05D2220/30 , F05D2230/312 , F05D2230/313 , F05D2230/90 , F05D2260/231 , F05D2300/21 , Y10T29/49343
摘要： A turbine engine component has an airfoil portion having a pressure side, a suction side, and a trailing edge. The trailing edge has a center discharge cooling circuit, which center discharge cooling circuit has an exit defined by a concave surface on the pressure side of the airfoil portion and a convex surface on the suction side of the airfoil portion. The airfoil portion has a thermal barrier coating on the pressure side and the suction side. The thermal barrier coating on the convex surface tapers to zero in thickness at a point spaced from the trailing edge so as to leave an uncoated portion on the convex surface.

10. 发明公开

EP2946078A2 AN APPARATUS AND CORRESPONDING METHOD 审中-公开
标题翻译： VORRICHTUNG UNDZUGEHÖRIGESVERFAHREN
公开(公告)号：EP2946078A2
公开(公告)日：2015-11-25
申请号：EP13870387.1
申请日：2013-12-23
申请人： Rolls-Royce North American Technologies, Inc.
发明人： USKERT Richard C. , FREEMAN Ted J. , THOMAS David J.
IPC分类号： F01D5/14 , F01D5/28 , F23R3/00 , F01D25/08
CPC分类号： F01D25/12 , F01D5/147 , F01D5/185 , F01D5/282 , F01D9/02 , F01D25/08 , F05D2240/35 , F05D2260/203 , F05D2300/514 , F05D2300/603 , F05D2300/6033 , F05D2300/612 , F23R3/002 , F23R3/007 , F23R2900/03041 , F23R2900/03042 , F23R2900/03043 , Y02T50/672 , Y02T50/676 , Y10T29/49316
摘要： In one embodiment, a gas turbine engine component includes a foam based core and a composite skin member. Both the foam based core and the composite skin member can be used to structurally support the gas turbine engine component. The composite skin member can be a CMC material and is used to partially encapsulate the foam core. The gas turbine engine component can take the form of an airfoil member such as a blade or a vane, a combustor liner, etc. A first portion of the composite skin member includes a first surface extending past an edge of the component creating a step approximate an edge section. In another embodiment, composite skin members can be used to form a continuous shape for the edge section such that the foam core forms part of a gas path surface.
摘要翻译：在一个实施例中，燃气涡轮发动机部件包括基于泡沫的芯和复合表皮构件。泡沫基芯和复合蒙皮构件都可用于结构地支撑燃气涡轮发动机部件。复合表皮构件可以是CMC材料，并且用于部分地包封泡沫芯。燃气涡轮发动机部件可以采取诸如叶片或叶片的翼型件的形式，燃烧器衬套等。复合表皮部件的第一部分包括延伸穿过部件的边缘的第一表面，形成步骤近似边缘部分。在另一个实施例中，可以使用复合表皮构件来形成用于边缘部分的连续形状，使得泡沫芯形成气体路径表面的一部分。

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