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公开(公告)号：WO2014105236A3
公开(公告)日：2014-08-21
申请号：PCT/US2013061857
申请日：2013-09-26
Applicant: UNITED TECHNOLOGIES CORP , 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。 一个人字形的跳闸条从一个表面延伸到冷却通道中，沿一个长度的跳闸条高度。 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提供，所述第一和第二径向延伸的腿部彼此周向地间隔开并且通过周向通道彼此连接。 一对翼型件从相同的内平台径向延伸。 跳闸带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。 跳闸条高度沿长度变化。
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2.发明申请
公开(公告)号：WO2014042735A3
公开(公告)日：2014-05-22
申请号：PCT/US2013046733
申请日：2013-06-20
Applicant: UNITED TECHNOLOGIES CORP
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具有包括椭圆形几何形状的第一部分的至少一个排出槽。
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公开(公告)号：WO2015012918A3
公开(公告)日：2015-04-02
申请号：PCT/US2014035419
申请日：2014-04-25
Applicant: UNITED TECHNOLOGIES CORP
Inventor： RILEY SARAH , MOORE SASHA M , LEVINE JEFFREY R
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。 一个冷却孔从外部翼型壁延伸穿过吸入侧的供给通道到外表面。
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Patent Agency Ranking4.发明公开GAS TURBINE ENGINE AIRFOIL TRAILING EDGE SUCTION SIDE COOLING 审中-公开ABSTRÖMKANTENANSAUGSEITENKÜHLUNG燃气涡轮发动机叶片
公开(公告)号：EP3004558A4
公开(公告)日：2016-06-08
申请号：EP14830146
申请日：2014-04-25
Applicant: UNITED TECHNOLOGIES CORP
Inventor： RILEY SARAH , MOORE SASHA M , LEVINE JEFFREY R
IPC: F01D5/18
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
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公开(公告)号：EP2971689A4
公开(公告)日：2016-11-02
申请号：EP14768998
申请日：2014-03-11
Applicant: UNITED TECHNOLOGIES CORP
Inventor： RILEY SARAH , LEVINE JEFFREY R , BOEKE MARK A
IPC: C23C4/01 , C23C4/02 , C23C4/11 , C23C4/134 , C23C14/04 , C23C14/22 , C23C14/30 , F01D5/28 , F01D9/04
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.
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公开(公告)号：EP2900967A4
公开(公告)日：2015-09-16
申请号：EP13866792
申请日：2013-09-26
Applicant: UNITED TECHNOLOGIES CORP , 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.
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公开(公告)号：EP2900962A4
公开(公告)日：2015-09-30
申请号：EP13841073
申请日：2013-09-26
Applicant: UNITED TECHNOLOGIES CORP , 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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8.发明公开
公开(公告)号：EP2867479A4
公开(公告)日：2015-05-06
申请号：EP13836277
申请日：2013-06-20
Applicant: UNITED TECHNOLOGIES CORP
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.
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