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公开(公告)号：US10253635B2
公开(公告)日：2019-04-09
申请号：US15966049
申请日：2018-04-30
Applicant: United Technologies Corporation
Inventor： Dominic J. Mongillo, Jr. , Jeffrey R. Levine , Kyle C. Lana , Sasha M. Moore
Abstract: A turbine blade according to an example of the present disclosure includes, among other things, a platform extending from a root section, an airfoil section extending radially from the platform to an airfoil tip, a plurality of cooling passages defined in an external wall of the airfoil tip, the plurality of cooling passages extending radially between the airfoil tip and a cavity in the airfoil section bounded by the external wall, and each of the plurality of cooling passages defining an inlet port along the cavity and an exit port adjacent the airfoil tip, and at least one internal feature within each of the plurality of cooling passages that meter flow to the respective exit port.
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公开(公告)号：US20170198601A1
公开(公告)日：2017-07-13
申请号：US14993140
申请日：2016-01-12
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Michael N. Task , Mark A. Boeke , Jeffrey R. Levine , Russell J. Bergman
CPC classification number: F01D25/005 , C22C19/05 , C22C19/056 , C22C19/057 , C23C14/083 , C23C14/16 , C23C14/30 , C23C14/35 , C23C28/321 , C23C28/3215 , C23C28/3455 , F01D9/041 , F05D2220/32 , F05D2230/21 , F05D2230/312 , F05D2230/313 , F05D2230/90 , F05D2240/128 , F05D2260/231 , F05D2300/17 , F05D2300/175 , F05D2300/182 , F05D2300/2118 , F05D2300/611
Abstract: A gas turbine engine component comprising a nozzle segment, the nozzle segment comprising at least one substrate having a surface. A metallic bondcoat is coupled to the surface of the substrate. An yttria-stabilized zirconia thermal barrier coating is coupled to the metallic bondcoat opposite the surface.
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3.发明申请公开(公告)号：US20150118064A1
公开(公告)日：2015-04-30
申请号：US14390496
申请日：2013-03-12
Applicant: United Technologies Corporation
Inventor： Jeffrey R. Levine , Jeffrey S. Beattie , Malcolm C. Staddon
IPC: F01D5/18
CPC classification number: F01D5/188 , B22C9/103 , B22C9/108 , F01D5/187 , F05D2200/33 , F05D2230/211 , F05D2260/22141 , F05D2260/607 , F05D2300/13 , Y02E10/721
Abstract: An airfoil has a body that includes leading and trailing edges that adjoin pressure and suction sides to provide an exterior airfoil surface. A cooling passage extends in a radial direction from a root to a tip. A trailing edge cooling passage interconnects the cooling passage to the trailing edge. The trailing edge cooling passage includes first and second pedestals of different sizes that are arranged in a repeating pattern with respect to pedestals of the same size and with respect to pedestals of different sizes.
Abstract translation: 机翼具有主体，其包括邻接压力侧和吸力侧的前缘和后缘，以提供外部翼型表面。 冷却通道在径向方向上从根部延伸到尖端。 后缘冷却通道将冷却通道与后缘相互连接。 后缘冷却通道包括不同尺寸的第一和第二基座，其相对于具有相同尺寸的基座并且相对于不同尺寸的基座以重复图案布置。
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公开(公告)号：US20180163551A1
公开(公告)日：2018-06-14
申请号：US15375827
申请日：2016-12-12
Applicant: United Technologies Corporation
Inventor： John David Forbes , Gregory Anselmi , Christina E. Botnick , Eleanor D. Kaufman , Jeffrey Leon , Jeffrey R. Levine , Gerald M. Mace , Daniel C. Nadeau , Tania Bhatia Kashyap , Richard N. Allen
IPC: F01D9/04
CPC classification number: F01D9/041 , F01D9/065 , F05D2240/80 , F05D2240/81 , F05D2250/74 , F05D2260/202
Abstract: A turbine vane includes an inner platform and an outer platform joined together by an airfoil. The airfoil has a leading edge and a trailing edge joined together by a pressure side and a suction side disposed opposite the pressure side. The inner platform defines a plurality of first inner cooling holes and a plurality of second inner cooling holes that are fluidly connected to an inner cooling passage. The plurality of first inner cooling holes are disposed proximate the leading edge and extend towards the suction side and the plurality of second inner cooling holes are disposed proximate the trailing edge and the suction side and extend towards the leading edge.
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公开(公告)号：US20160017733A1
公开(公告)日：2016-01-21
申请号：US14770189
申请日：2014-03-11
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Sarah Riley , Jeffrey R. Levine , Mark A. Boeke
CPC classification number: F01D9/041 , C23C4/01 , C23C4/02 , C23C4/11 , C23C4/12 , C23C4/134 , C23C14/04 , C23C14/22 , C23C14/30 , F01D5/288 , F01D9/044 , F05D2220/32 , F05D2230/90 , F05D2240/12 , F05D2250/62 , F05D2250/63 , F05D2300/20 , F05D2300/605 , F05D2300/606
Abstract: An article includes a body that has a coating thereon. The coating has a first portion disposed on a first section of the body and a second portion disposed on a second, different section of the body. The first portion has a first microstructure and the second portion has a second, different microstructure.
Abstract translation: 一种制品包括其上具有涂层的主体。 涂层具有设置在主体的第一部分上的第一部分和设置在主体的第二不同部分上的第二部分。 第一部分具有第一微结构，第二部分具有第二不同的微结构。
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Patent Agency Ranking
公开(公告)号：US10428666B2
公开(公告)日：2019-10-01
申请号：US15375827
申请日：2016-12-12
Applicant: United Technologies Corporation
Inventor： John David Forbes , Gregory Anselmi , Christina E. Botnick , Eleanor D. Kaufman , Jeffrey Leon , Jeffrey R. Levine , Gerald M. Mace , Daniel C. Nadeau , Tania Bhatia Kashyap , Richard N. Allen
Abstract: A turbine vane includes an inner platform and an outer platform joined together by an airfoil. The airfoil has a leading edge and a trailing edge joined together by a pressure side and a suction side disposed opposite the pressure side. The inner platform defines a plurality of first inner cooling holes and a plurality of second inner cooling holes that are fluidly connected to an inner cooling passage. The plurality of first inner cooling holes are disposed proximate the leading edge and extend towards the suction side and the plurality of second inner cooling holes are disposed proximate the trailing edge and the suction side and extend towards the leading edge.
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公开(公告)号：US20180245470A1
公开(公告)日：2018-08-30
申请号：US15966049
申请日：2018-04-30
Applicant: United Technologies Corporation
Inventor： Dominic J. Mongillo, JR. , Jeffrey R. Levine , Kyle C. Lana , Sasha M. Moore
CPC classification number: F01D5/186 , F01D5/187 , F01D5/20 , F05D2240/307 , F05D2260/2214 , F05D2260/22141 , Y02T50/673 , Y02T50/676
Abstract: A turbine blade according to an example of the present disclosure includes, among other things, a platform extending from a root section, an airfoil section extending radially from the platform to an airfoil tip, a plurality of cooling passages defined in an external wall of the airfoil tip, the plurality of cooling passages extending radially between the airfoil tip and a cavity in the airfoil section bounded by the external wall, and each of the plurality of cooling passages defining an inlet port along the cavity and an exit port adjacent the airfoil tip, and at least one internal feature within each of the plurality of cooling passages that meter flow to the respective exit port.
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公开(公告)号：US09982560B2
公开(公告)日：2018-05-29
申请号：US14599075
申请日：2015-01-16
Applicant: United Technologies Corporation
Inventor： Mark A. Boeke , Kristopher K. Anderson , Jeffrey J. De Gray , Jeffrey R. Levine , Sarah Riley , Richard M. Salzillo, Jr.
CPC classification number: F01D25/12 , F01D9/023 , F01D9/04 , F01D9/06 , F05D2240/81 , Y02T50/676
Abstract: An airfoil platform includes a platform body having an arcuate base defining a centerline axis. A rail extends radially outboard from a side of the arcuate base. A feed orifice is defined at least partially in the rail. The inner diameter edge of an axially facing opening of the feed orifice is spaced apart radially outboard of an outer diameter surface of the arcuate base. A method for manufacturing an airfoil platform includes providing an airfoil platform body and forming the feed orifice through the rail. Forming the feed orifice through the rail includes forming the feed orifice radially outboard of and spaced apart from the outer diameter surface of the arcuate base.
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公开(公告)号：US20170260864A1
公开(公告)日：2017-09-14
申请号：US15069738
申请日：2016-03-14
Applicant: United Technologies Corporation
Inventor： Jeffrey Leon , Daniel C. Nadeau , Jeffrey R. Levine , Eleanor D. Kaufman , Richard N. Allen , Evan P. Molony , Gregory Anselmi
CPC classification number: F01D5/187 , B22C9/10 , F02C7/18 , F05D2220/32 , F05D2260/20 , F05D2260/2212 , F05D2260/22141 , Y02T50/676
Abstract: An airfoil is disclosed, comprising an airfoil body and an internal cavity within the airfoil body. The internal cavity may comprise an outer edge comprising a first outer scallop and a second outer scallop, an inner edge opposite the outer edge, the inner edge comprising a first inner scallop and a second inner scallop, a leading edge spanning between the outer edge and the inner edge, and a trailing edge spanning between the outer edge and the inner edge and opposite the leading edge. Between the outer edge, the inner edge, the leading edge, and the trailing edge, the internal cavity may comprise eight columns of pedestals disposed axially relative to one another and axially between the leading edge and the trailing edge.
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公开(公告)号：US20160230564A1
公开(公告)日：2016-08-11
申请号：US14619343
申请日：2015-02-11
Applicant: United Technologies Corporation
Inventor： Dominic J. Mongillo, JR. , Jeffrey R. Levine , Kyle C. Lana , Sasha M. Moore
CPC classification number: F01D5/186 , F01D5/187 , F01D5/20 , F05D2240/307 , F05D2260/2214 , F05D2260/22141 , Y02T50/673 , Y02T50/676
Abstract: A turbine blade according to an example of the present disclosure includes, among other things, a platform, an airfoil tip, and an airfoil section between the platform and the airfoil tip. The airfoil section has a cavity spaced radially from the airfoil tip and a plurality of cooling passages radially between the cavity and the airfoil tip. Each of the plurality of cooling passages defines an exit port adjacent the airfoil tip. An internal feature within each of the plurality of cooling passages is configured to meter flow to the exit port.
Abstract translation: 根据本公开的示例的涡轮叶片包括平台，翼型末端以及平台和翼型顶端之间的翼型部分。 机翼部分具有与翼型件末端径向间隔开的空腔和在空腔和翼型端之间径向放置的多个冷却通道。 多个冷却通道中的每一个限定了与翼型件末端相邻的出口。 多个冷却通道内的每个内部特征被配置成计量到出口的流量。
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