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1.发明申请
公开(公告)号：WO2014138320A1
公开(公告)日：2014-09-12
申请号：PCT/US2014/020956
申请日：2014-03-06
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： BOEKE, Mark A. , RAJCHEL, Kevin , SALZILLO, Richard M. , DEGRAY, Jeffrey J. , MAINELLI, Allison
CPC classification number: F01D11/005 , F01D9/041 , F05D2240/11 , F05D2240/57
Abstract: A component for a gas turbine engine according to an exemplary aspect of the present disclosure includes, among other things, a mate face and a feather seal slot axially extending along the mate face, the feather seal slot having a variable width along a portion of its axial length.
Abstract translation: 根据本公开的示例性方面的用于燃气涡轮发动机的部件尤其包括沿着配合面轴向延伸的配合面和羽毛密封槽，所述羽毛密封槽沿其一部分具有可变的宽度 轴向长度。
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公开(公告)号：WO2014105236A2
公开(公告)日：2014-07-03
申请号：PCT/US2013/061857
申请日：2013-09-26
Applicant: UNITED TECHNOLOGIES CORPORATION , RILEY, Sarah , BOEKE, Mark A. , DEGRAY, Jeffrey J. , GREGG, Shawn J.
Inventor： RILEY, Sarah , BOEKE, Mark A. , DEGRAY, Jeffrey J. , GREGG, Shawn J.
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组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。 人字形跳闸条从表面延伸到沿着长度的跳闸条高度处的冷却通路。 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部和外部平台。 内部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提供，所述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。 一对翼型从相同的内部平台径向延伸。 跳闸条从表面沿着长度以跳闸条高度从表面延伸到圆周通道中。 跳闸高度沿长度变化。
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公开(公告)号：WO2014052538A1
公开(公告)日：2014-04-03
申请号：PCT/US2013/061840
申请日：2013-09-26
Applicant: UNITED TECHNOLOGIES CORPORATION , BOEKE, Mark A. , GREGG, Shawn J. , RILEY, Sarah , DEGRAY, Jeffrey J. , SALZILLO, Richard M.
Inventor： BOEKE, Mark A. , GREGG, Shawn J. , RILEY, Sarah , DEGRAY, Jeffrey J. , SALZILLO, Richard M.
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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4.发明申请
公开(公告)号：WO2014042735A2
公开(公告)日：2014-03-20
申请号：PCT/US2013/046733
申请日：2013-06-20
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： BOEKE, Mark A. , OTERO, Edwin , DEGRAY, Jeffrey J. , PROPHETER-HINCKLEY, Tracy A. , FERNANDEZ, Guillermo J. , RILEY, Sarah
CPC classification number: F01D5/187 , F01D9/065 , F05D2240/121 , F05D2240/122 , F05D2240/303 , F05D2240/304 , F05D2240/81 , F05D2250/14
Abstract: A component for a gas turbine engine according to an exemplary aspect of the present disclosure includes, among other things, an body portion that extends between a leading edge and a trailing edge. At least one of the leading edge and the trailing edge includes at least one discharge slot having a first portion that includes an oval geometry.
Abstract translation: 根据本公开的示例性方面的用于燃气涡轮发动机的部件尤其包括在前缘和后缘之间延伸的主体部分。 前缘和后缘中的至少一个包括至少一个排出槽，该排出槽具有包括椭圆形几何形状的第一部分。
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公开(公告)号：EP2900962B1
公开(公告)日：2018-12-05
申请号：EP13841073.3
申请日：2013-09-26
Applicant: United Technologies Corporation , Boeke, Mark A. , Gregg, Shawn J. , Riley, Sarah , Degray, Jeffrey J. , Salzillo, Richard M.
Inventor： BOEKE, Mark A. , GREGG, Shawn J. , RILEY, Sarah , DEGRAY, Jeffrey J. , SALZILLO, Richard M.
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.
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Patent Agency Ranking6.发明公开
公开(公告)号：EP2964934A1
公开(公告)日：2016-01-13
申请号：EP14760315.3
申请日：2014-03-06
Applicant: United Technologies Corporation
Inventor： BOEKE, Mark A. , RAJCHEL, Kevin , SALZILLO,Richard M. , DEGRAY, Jeffrey J. , MAINELLI, Allison
CPC classification number: F01D11/005 , F01D9/041 , F05D2240/11 , F05D2240/57
Abstract: A component for a gas turbine engine according to an exemplary aspect of the present disclosure includes, among other things, a mate face and a feather seal slot axially extending along the mate face, the feather seal slot having a variable width along a portion of its axial length.
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公开(公告)号：EP2900962A1
公开(公告)日：2015-08-05
申请号：EP13841073.3
申请日：2013-09-26
Applicant: United Technologies Corporation , Boeke, Mark A. , Gregg, Shawn J. , Riley, Sarah , Degray, Jeffrey J. , Salzillo, Richard M.
Inventor： BOEKE, Mark A. , GREGG, Shawn J. , RILEY, Sarah , DEGRAY, Jeffrey J. , SALZILLO, Richard M.
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.
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公开(公告)号：EP2867479B1
公开(公告)日：2018-08-01
申请号：EP13836277.7
申请日：2013-06-20
Applicant: United Technologies Corporation
Inventor： BOEKE, Mark A. , OTERO, Edwin , DEGRAY, Jeffrey J. , PROPHETER-HINCKLEY, Tracy A. , FERNANDEZ, Guillermo J. , RILEY, Sarah
CPC classification number: F01D5/187 , F01D9/065 , F05D2240/121 , F05D2240/122 , F05D2240/303 , F05D2240/304 , F05D2240/81 , F05D2250/14 , Y02T50/676
Abstract: A component for a gas turbine engine according to an exemplary aspect of the present disclosure includes, among other things, an body portion that extends between a leading edge and a trailing edge. At least one of the leading edge and the trailing edge includes at least one discharge slot having a first portion that includes an oval geometry.
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9.发明公开GAS TURBINE ENGINE AIRFOIL AND CORRESPONDING METHOD OF FORMING 审中-公开GASTURBINENMOTOR-TRAGFLÄCHEUND ENTSPRECHENDES HERSTELLUNGSVERFAHREN
公开(公告)号：EP3061910A1
公开(公告)日：2016-08-31
申请号：EP16157737.4
申请日：2016-02-26
Applicant: United Technologies Corporation
Inventor： BOECKE, Mark A. , SALZILLO, Richard , DEGRAY, Jeffrey J. , GREGG, Shawn J.
CPC classification number: F01D5/189 , F01D5/141 , F01D5/147 , F01D9/041 , F01D9/065 , F01D25/12 , F05D2220/32 , F05D2230/20 , F05D2230/60 , F05D2240/126 , F05D2240/301 , F05D2240/81 , F05D2260/221 , Y02T50/676
Abstract: An airfoil (68) includes an airfoil wall (110, 112) including an exterior airfoil surface and at least partially defines an airfoil cavity (104). A fillet (102A, 102B) is on the exterior airfoil surface (98, 100). A recess (114) is in an interior surface of the airfoil wall (110, 112) adjacent the fillet (102A, 102B). A baffle tube (116) is located in the airfoil cavity (104) spaced from the recess (114).
Abstract translation: 翼型件（68）包括包括外部翼面表面并且至少部分地限定翼型腔（104）的翼型件壁（110,112）。 圆角（102A，102B）位于外翼面（98,100）上。 凹部114位于与圆角（102A，102B）相邻的翼型件壁110,112的内表面中。 挡板（116）位于与凹部（114）间隔开的翼型腔（104）中。
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公开(公告)号：EP2964934B1
公开(公告)日：2018-10-03
申请号：EP14760315.3
申请日：2014-03-06
Applicant: United Technologies Corporation
Inventor： BOEKE, Mark A. , RAJCHEL, Kevin , SALZILLO,Richard M. , DEGRAY, Jeffrey J. , MAINELLI, Allison
CPC classification number: F01D11/005 , F01D9/041 , F05D2240/11 , F05D2240/57
Abstract: A component for a gas turbine engine according to an exemplary aspect of the present disclosure includes, among other things, a mate face and a feather seal slot axially extending along the mate face, the feather seal slot having a variable width along a portion of its axial length.
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