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公开(公告)号：WO2014031275A1
公开(公告)日：2014-02-27
申请号：PCT/US2013/051796
申请日：2013-07-24
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： NADEAU, Daniel C. , LEVINE, Jeffrey R. , MONGILLO JR., Dominic J.
CPC classification number: F01D5/186 , F01D5/187 , F05D2240/127 , F05D2240/305 , F05D2240/306 , F05D2250/185 , F05D2260/202 , F05D2260/2212 , F05D2260/22141 , Y02T50/676
Abstract: An airfoil for a gas turbine engine includes spaced apart pressure and suction walls joined at leading and trailing edges to provide an airfoil. Intermediate walls interconnect the pressure and suction walls to provide cooling passageways. The cooing passageways have interior pressure and suction surfaces that are respectively provided on the pressure and suction walls. Trip strips include a chevron-shaped trip strip that is provided on at least one of the interior pressure and suction surfaces.
Abstract translation: 用于燃气涡轮发动机的翼型件包括在前缘和后缘处连接的间隔开的压力和抽吸壁，以提供翼型件。 中间壁互连压力和吸力壁，以提供冷却通道。 冷却通道具有分别设置在压力和吸力壁上的内部压力和吸力表面。 跳闸条包括设置在内部压力和吸力表面中的至少一个上的人字形状的跳闸条。
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公开(公告)号：WO2015126488A2
公开(公告)日：2015-08-27
申请号：PCT/US2014/066495
申请日：2014-11-20
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： TAFFET, Steven , DONNELL, Brandon S. , NADEAU, Daniel C. , DEIBEL, Russell , QUACH, San
CPC classification number: F01D5/187 , B22C7/02 , B22C9/04 , B22C9/10 , B22C9/24 , F01D9/041 , F01D25/12 , F05D2220/323 , F05D2230/21 , F05D2230/211 , F05D2240/121 , F05D2240/122 , F05D2240/303 , F05D2240/304 , F05D2260/202 , Y02T50/676
Abstract: A lost core mold component comprises a first leg and a second leg with a plurality of crossover members connecting the first and second legs. The plurality of crossover members includes outermost crossover members spaced from each other. Adjacent ends of each of the first and second legs, and second crossover members are spaced closer to each other than are the outermost crossover members. Central crossover members extend between the first and second leg and between the second crossover members. The outermost crossover members extend for a first cross-sectional area. The second crossover members extend for a second cross-sectional area and the central crossover members extend for a third cross-sectional area. The first cross-sectional area is greater than the second cross-sectional area. The second cross-sectional area is greater than the third cross-sectional area. A gas turbine engine and component are also disclosed.
Abstract translation: 失去的芯模组件包括第一腿部和第二腿部，其具有连接第一和第二腿部的多个交叉构件。 多个交叉构件包括彼此间隔开的最外侧交叉构件。 第一和第二腿部和第二交叉构件中的每一个的相邻端部比最外面的交叉构件彼此更靠近地间隔开。 中央交叉构件在第一和第二腿之间以及第二交叉构件之间延伸。 最外面的交叉构件延伸到第一横截面积。 第二交叉构件延伸到第二横截面积，并且中心交叉构件延伸第三横截面积。 第一截面积大于第二横截面积。 第二横截面积大于第三横截面积。 还公开了一种燃气涡轮发动机和部件。
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3.发明公开TRAILING EDGE COOLING PEDESTAL CONFIGURATION FOR A GAS TURBINE ENGINE AIRFOIL 审中-公开奥地利KETENKÜHLSOCKELKONFIGURATIONFÜREINE GASTURBINENMOTORSCHAUFEL
公开(公告)号：EP3099901A1
公开(公告)日：2016-12-07
申请号：EP14881024.5
申请日：2014-12-26
Applicant: United Technologies Corporation
Inventor： DOWNEY, James B. Jr. , ZHANG, Brenda , LEMIEUX, Steven G. , KAUFMAN, Eleanor D. , FUKUDA, Takao , NADEAU, Daniel C.
CPC classification number: F01D5/18 , F01D5/187 , F01D9/02 , F01D25/12 , F05D2220/32 , F05D2240/304 , F05D2260/221 , F05D2260/2212 , F05D2260/2214 , Y02T50/676 , Y02T50/6765
Abstract: An airfoil for a gas turbine engine includes pressure and suction surfaces that are provided by pressure and suction walls extending in a radial direction and joined at a leading edge and a trailing edge. A cooling passage is arranged between the pressure and suction walls and extending to the trailing edge. The cooling passage terminates in a trailing edge exit that is arranged in the trailing edge. Multiple rows of pedestals include a first row of pedestals that join the pressure and suction walls. The first row of pedestals is arranged closest to the trailing edge but interiorly from the trailing edge thereby leaving the trailing edge exit unobstructed.
Abstract translation: 用于燃气涡轮发动机的翼型包括压力和吸力表面，其由在径向方向上延伸并在前缘和后缘连接的压力和吸力壁提供。 冷却通道设置在压力和吸力壁之间并延伸到后缘。 冷却通道终止于设置在后缘的后缘出口。 多排基座包括连接压力和吸力壁的第一排基座。 基座的第一排布置成最靠近后缘，但是位于后缘的内部，从而使后缘不受阻碍地排出。
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公开(公告)号：EP3219919A1
公开(公告)日：2017-09-20
申请号：EP17160960.5
申请日：2017-03-14
Applicant: United Technologies Corporation
Inventor： LEON, Jeffrey , NADEAU, Daniel C. , LEVINE, Jeffrey R. , KAUFMAN, Eleanor D. , ALLEN, Richard N. , MOLONY, Evan P. , ANSELMI, Gregory
Abstract: An airfoil (200), comprising an airfoil body and an internal cavity (210) within the airfoil body. The internal cavity (210) may comprise an outer edge (212) comprising a first outer scallop (213) and a second outer scallop (213), an inner edge (211) opposite the outer edge (212), the inner edge (211) comprising a first inner scallop (213) and a second inner scallop (213), a leading edge (208) spanning between the outer edge (212) and the inner edge (211), and a trailing edge (209) spanning between the outer edge (212) and the inner edge (211) and opposite the leading edge (208). Between the outer edge (212), the inner edge (211), the leading edge (208), and the trailing edge (209), the internal cavity may comprise eight columns of pedestals (221...228) disposed axially relative to one another and axially between the leading edge (208) and the trailing edge (209).
Abstract translation: 一种翼型（200），包括翼型主体和翼型主体内的内腔（210）。 内腔210可以包括外边缘212，该外边缘212包括第一外扇贝213和第二外扇贝213，与外边缘212相对的内边缘211， ）包括第一内扇贝（213）和第二内扇贝（213），跨越外边缘（212）和内边缘（211）之间的前缘（208），以及跨越 外边缘（212）和内边缘（211）并与前缘（208）相对。 在外边缘（212），内边缘（211），前缘（208）和后缘（209）之间，内腔可以包括相对于轴向设置的八列基座（221 ... 228） 彼此并且在前缘（208）和后缘（209）之间轴向地延伸。
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公开(公告)号：EP3099901B1
公开(公告)日：2019-10-09
申请号：EP14881024.5
申请日：2014-12-26
Applicant: United Technologies Corporation
Inventor： DOWNEY, James B. Jr. , ZHANG, Brenda , LEMIEUX, Steven G. , KAUFMAN, Eleanor D. , FUKUDA, Takao , NADEAU, Daniel C.
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Patent Agency Ranking
公开(公告)号：EP3342986A1
公开(公告)日：2018-07-04
申请号：EP17206360.4
申请日：2017-12-11
Applicant: United Technologies Corporation
Inventor： FORBES, John David , ANSELMI, Gregory , BOTNICK, Christina E. , KAUFMAN, Eleanor D. , LEON, Jeffrey , LEVINE, Jeffrey R. , MACE, Gerald M. , NADEAU, Daniel C. , KASHYAP, Tania Bhatia , ALLEN, Richard N.
IPC: F01D9/06
CPC classification number: F01D9/041 , F01D9/065 , F05D2240/80 , F05D2240/81 , F05D2250/74 , F05D2260/202
Abstract: A turbine vane includes an inner platform (72) and an outer platform (74) joined together by an airfoil (70). The airfoil (70) has a leading edge (80) and a trailing edge (82) joined together by a pressure side (84) and a suction side (86) disposed opposite the pressure side (84). The inner platform (72) defines a plurality of first inner cooling holes (96) and a plurality of second inner cooling holes (98) that are fluidly connected to an inner cooling passage (94). The plurality of first inner cooling holes (96) are disposed proximate the leading edge (80) and extend towards the suction side (86) and the plurality of second inner cooling holes (98) are disposed proximate the trailing edge (82) and the suction side (86) and extend towards the leading edge (80).
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公开(公告)号：EP3636882A1
公开(公告)日：2020-04-15
申请号：EP19211067.4
申请日：2017-12-11
Applicant: United Technologies Corporation
Inventor： FORBES, John David , ANSELMI, Gregory , BOTNICK, Christina E. , KAUFMAN, Eleanor D. , LEON, Jeffrey , LEVINE, Jeffrey R. , MACE, Gerald M. , NADEAU, Daniel C. , KASHYAP, Tania Bhatia , ALLEN, Richard N.
IPC: F01D9/06
Abstract: A gas turbine engine (20) comprises a turbine section (28) disposed adjacent to a combustor section (26), the turbine section including a turbine vane (62) having an inner platform (72) and an outer platform (74) joined together by an airfoil (70) having a pressure side (84) and a suction side (86) each extending between a leading edge (80) and a trailing edge (82). The inner platform (72) defines a plurality of first inner cooling holes (96) disposed proximate the leading edge (80) and extending towards the suction side (86), a plurality of second inner cooling holes (98) disposed proximate the trailing edge (82) and the suction side (86), and a plurality of third inner cooling holes (100) disposed proximate the trailing edge (82) and the pressure side (84).
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公开(公告)号：EP2888462A1
公开(公告)日：2015-07-01
申请号：EP13830772.3
申请日：2013-07-24
Applicant: United Technologies Corporation
Inventor： NADEAU, Daniel C. , LEVINE, Jeffrey R. , MONGILLO JR., Dominic J.
CPC classification number: F01D5/186 , F01D5/187 , F05D2240/127 , F05D2240/305 , F05D2240/306 , F05D2250/185 , F05D2260/202 , F05D2260/2212 , F05D2260/22141 , Y02T50/676
Abstract: An airfoil for a gas turbine engine includes spaced apart pressure and suction walls joined at leading and trailing edges to provide an airfoil. Intermediate walls interconnect the pressure and suction walls to provide cooling passageways. The cooing passageways have interior pressure and suction surfaces that are respectively provided on the pressure and suction walls. Trip strips include a chevron-shaped trip strip that is provided on at least one of the interior pressure and suction surfaces.
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公开(公告)号：EP3219919B1
公开(公告)日：2020-09-23
申请号：EP17160960.5
申请日：2017-03-14
Applicant: United Technologies Corporation
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公开(公告)号：EP3086893B1
公开(公告)日：2019-07-24
申请号：EP14883263.7
申请日：2014-11-20
Applicant: United Technologies Corporation
Inventor： TAFFET, Steven , DONNELL, Brandon S. , NADEAU, Daniel C. , DEIBEL, Russell , QUACH, San
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