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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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公开(公告)号：US20160208627A1
公开(公告)日：2016-07-21
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.
IPC: F01D9/02
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.
Abstract translation: 翼型平台包括具有限定中心线轴线的弓形基部的平台本体。 轨道从弓形底座的一侧沿径向外侧延伸。 进料口至少部分地限定在轨道中。 进料孔的轴向面向的开口的内径边缘在弧形底座的外径表面的径向外侧间隔开。 一种用于制造翼型平台的方法包括提供翼型平台本体并通过导轨形成进料口。 通过导轨形成进料孔包括在弓形底座的外径表面径向地形成进料孔并且间隔开。
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公开(公告)号：US20160003152A1
公开(公告)日：2016-01-07
申请号：US14769224
申请日：2014-03-12
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Sarah Riley , Mark A. Boeke , Shawn J. Gregg
Abstract: A stator for a gas turbine engine has a platform supporting multiple vanes that includes first and second vanes respectively. First and second regions are arranged at the same location on the first and second vanes. The first and second regions respectively include first and second cooling hole configurations that are different than one another.
Abstract translation: 用于燃气涡轮发动机的定子具有分别支撑包括第一和第二叶片的多个叶片的平台。 第一和第二区域布置在第一和第二叶片上的相同位置。 第一和第二区域分别包括彼此不同的第一和第二冷却孔构造。
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公开(公告)号：US09080452B2
公开(公告)日：2015-07-14
申请号：US13630419
申请日：2012-09-28
Applicant: United Technologies Corporation
Inventor： Mark A. Boeke , Shawn J. Gregg , Sarah Riley , Jeffrey J. DeGray , Richard M. Salzillo
CPC classification number: F01D5/186 , F01D5/187 , F01D9/02 , F01D25/12 , F01D25/246 , F05D2240/12 , F05D2240/81 , F05D2260/204 , Y02T50/672 , Y02T50/676
Abstract: A stator vane for a gas turbine engine includes an airfoil extending in a radial direction and supported by a platform having a gas flowpath surface. A cooling passage is arranged in the platform and includes a circumferential passage that is fluidly connected to an inlet passage extending through and edge of the platform, and film cooling holes extending from the gas flowpath surface to the circumferential passage, radial extending passage through the edge of the platform. A void is interconnected to at least one of the radially extending passage and the inlet passage.
Abstract translation: 用于燃气涡轮发动机的定子叶片包括沿径向延伸并由具有气体流路表面的平台支撑的翼型件。 冷却通道布置在平台中，并且包括流体连接到延伸通过平台的边缘的入口通道的圆周通道，以及从气体流路表面延伸到周向通道的膜冷却孔，通过边缘的径向延伸通道 的平台。 空隙与径向延伸通道和入口通道中的至少一个相互连接。
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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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Patent Agency Ranking
公开(公告)号：US20160090846A1
公开(公告)日：2016-03-31
申请号：US14892713
申请日：2014-04-25
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Sarah Riley , Sasha M. Moore , Jeffrey R. Levine
CPC classification number: F01D5/186 , F01D5/189 , F01D9/041 , F01D25/12 , F05D2220/32 , F05D2240/12 , F05D2240/122 , F05D2240/124 , F05D2240/30 , F05D2260/201 , F05D2260/202 , Y02T50/672 , Y02T50/676
Abstract: An airfoil for a gas turbine engine includes an outer airfoil wall that provides an exterior surface and multiple radially extending cooling passages. The exterior surface provides pressure and suctions sides joined by leading and trailing edges. The cooling passages include a supply passage arranged upstream from and in fluid communication with a trailing edge passage. A cooling hole extends through the outer airfoil wall from the supply passage to the exterior surface on the suction side.
Abstract translation: 用于燃气涡轮发动机的翼型件包括提供外表面和多个径向延伸的冷却通道的外翼型壁。 外表面提供由前缘和后缘连接的压力和吸力面。 冷却通道包括设置在后缘通道上游并与后缘通道流体连通的供给通道。 冷却孔从供气通道的外侧翼面壁延伸到吸入侧的外表面。
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公开(公告)号：US20140093361A1
公开(公告)日：2014-04-03
申请号：US13630107
申请日：2012-09-28
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Sarah Riley , Mark A. Boeke , Jeffrey J. DeGray , Shawn J. Gregg
CPC classification number: F01D25/12 , F01D5/187 , F01D9/02 , F05D2240/12 , F05D2240/126 , F05D2240/127 , F05D2240/81 , F05D2250/183 , F05D2260/2212 , F05D2260/22141 , Y02T50/672 , Y02T50/676
Abstract: An airfoil component for a gas turbine engine includes an airfoil extending from a platform. At least one of the airfoil and the platform includes a cooling passage defined by a surface. A chevron-shaped trip strip extends from the surface into the cooling passage at a trip strip height along a length. The trip strip height varies along the length. A turbine vane for a gas turbine engine includes inner and outer platforms. A cooling passage is provided in the inner platform. The cooling passage is provided by first and second radially extending legs spaced circumferentially apart from one another and joined to one another by a circumferential passage. A pair of airfoils extend radially from the same inner platform. A trip strip extends from the surface into the circumferential passage at a trip strip height along a length. The trip strip height varying along the length.
Abstract translation: 用于燃气涡轮发动机的翼型件包括从平台延伸的翼型件。 翼型件和平台中的至少一个包括由表面限定的冷却通道。 一个V形形状的跳闸条从一个长度的跳闸带高度从表面延伸到冷却通道中。 跳闸条高度沿长度变化。 用于燃气涡轮发动机的涡轮叶片包括内平台和外平台。 在内平台上设有冷却通道。 冷却通道由第一和第二径向延伸的腿部彼此周向间隔开并且通过周向通道彼此连接而设置。 一对翼型件从相同的内平台径向延伸。 跳闸条沿着一段长度以一个跳闸带高度从表面延伸到圆周通道中。 行程长度沿长度变化。
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公开(公告)号：US20190218916A1
公开(公告)日：2019-07-18
申请号：US16365943
申请日：2019-03-27
Applicant: United Technologies Corporation
Inventor： Sarah Riley , Sasha M. Moore , Jeffrey R. Levine
CPC classification number: F01D5/186 , F01D5/189 , F01D9/041 , F01D25/12 , F05D2220/32 , F05D2240/12 , F05D2240/122 , F05D2240/124 , F05D2240/30 , F05D2260/201 , F05D2260/202 , Y02T50/672 , Y02T50/676
Abstract: An airfoil for a gas turbine engine includes an outer airfoil wall that provides an exterior surface and multiple radially extending cooling passages. The exterior surface provides pressure and suctions sides joined by leading and trailing edges. The cooling passages include a supply passage arranged upstream from and in fluid communication with a trailing edge passage. A cooling hole extends through the outer airfoil wall from the supply passage to the exterior surface on the suction side.
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公开(公告)号：US10294806B2
公开(公告)日：2019-05-21
申请号：US14770189
申请日：2014-03-11
Applicant: United Technologies Corporation
Inventor： Sarah Riley , Jeffrey R. Levine , Mark A. Boeke
IPC: F01D9/04 , C23C14/04 , C23C4/02 , C23C4/11 , C23C4/01 , C23C4/12 , C23C14/22 , C23C4/134 , F01D5/28 , C23C14/30
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.
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公开(公告)号：US10253634B2
公开(公告)日：2019-04-09
申请号：US14892713
申请日：2014-04-25
Applicant: United Technologies Corporation
Inventor： Sarah Riley , Sasha M. Moore , Jeffrey R. Levine
Abstract: An airfoil for a gas turbine engine includes an outer airfoil wall that provides an exterior surface and multiple radially extending cooling passages. The exterior surface provides pressure and suctions sides joined by leading and trailing edges. The cooling passages include a supply passage arranged upstream from and in fluid communication with a trailing edge passage. A cooling hole extends through the outer airfoil wall from the supply passage to the exterior surface on the suction side.
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