-
1.发明申请GAS TURBINE ENGINE COMPONENT WITH COMBINED MATE FACE AND PLATFORM COOLING 审中-公开燃气涡轮发动机组件与组合的油面和平台冷却
公开(公告)号：WO2014186005A3
公开(公告)日：2015-02-26
申请号：PCT/US2014015194
申请日：2014-02-07
Applicant: UNITED TECHNOLOGIES CORP
Inventor： LEWIS SCOTT D , RAPP BRANDON M , BEATTIE JEFFREY S , HOUGH MATTHEW ANDREW , TELLER BRET M , JACQUES JEFFREY MICHAEL , ASTERLIN MAX
CPC classification number: F01D5/186 , F01D9/023 , F05D2240/81 , F05D2260/202 , F23R3/02
Abstract: A component for a gas turbine engine according to an exemplary aspect of the present disclosure includes, among other things, a platform that axially extends between a leading edge and a trailing edge, circumferentially extends between a first mate face and a second mate face, and includes a gas path surface and a non-gas path surface. The component defines at least one cavity that extends at least partially inside of the component. A first plurality of cooling holes extends from the at least one cavity to at least one of the first mate face and the second mate face and a second plurality of cooling holes extends from either the at least one cavity or the non-gas path surface to the gas path surface.
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轴向延伸的平台，其周向地在第一配合面和第二配合面之间延伸，以及 包括气体通道表面和非气体通道表面。 该部件限定至少一个至少部分地在部件内部延伸的空腔。 第一多个冷却孔从所述至少一个空腔延伸到所述第一配合面和所述第二配合面中的至少一个，并且第二多个冷却孔从所述至少一个空腔或所述非气体通道表面延伸到 气路面。
-
公开(公告)号：WO2015088699A1
公开(公告)日：2015-06-18
申请号：PCT/US2014065430
申请日：2014-11-13
Applicant: UNITED TECHNOLOGIES CORP
Inventor： LEWIS SCOTT D , KOHLI ATUL , PRAISNER THOMAS J
CPC classification number: F01D11/08 , F01D5/12 , F01D5/143 , F01D9/02 , F01D11/006 , F05D2220/32 , F05D2240/11 , F05D2240/80 , F05D2250/192 , F05D2250/231
Abstract: An array of components in a gas turbine engine includes first and second structures respectively including first and second surfaces that are arranged adjacent to one another to provide a gap. The first and second surfaces respectively have first and second rounded edges at the gap that are arranged in staggered relationship relative to one another.
Abstract translation: 燃气涡轮发动机中的部件阵列包括第一和第二结构，第一和第二结构分别包括彼此相邻布置以提供间隙的第一和第二表面。 第一和第二表面分别在间隙处具有第一和第二圆形边缘，这些边缘相对于彼此以交错关系布置。
-
公开(公告)号：EP2815098A4
公开(公告)日：2016-02-24
申请号：EP13749073
申请日：2013-02-12
Applicant: UNITED TECHNOLOGIES CORP
Inventor： ZELESKY MARK F , KOHLI ATUL , LEWIS SCOTT D
CPC classification number: F23R3/06 , F01D5/186 , F01D9/065 , F05D2240/81 , F05D2260/202 , F23R2900/03041 , F23R2900/03042 , Y02T50/673 , Y02T50/676
-
公开(公告)号：EP2867501A4
公开(公告)日：2015-07-08
申请号：EP13810147
申请日：2013-05-30
Applicant: UNITED TECHNOLOGIES CORP
Inventor： ZELESKY MARK F , TRINDADE RICARDO , TELLER BRET M , LEWIS SCOTT D , BEATTIE JEFFREY S , JACQUES JEFFREY MICHAEL , RAPP BRANDON M
CPC classification number: F01D5/085 , F01D5/081 , F01D5/18 , F05D2240/81 , Y02T50/676
Abstract: A turbine blade for a gas turbine engine includes an airfoil including leading and trailing edges joined by spaced apart pressure and suction sides to provide an exterior airfoil surface extending in a radial direction. The trailing edge is arranged on an aft side of the turbine blade. A root supports a platform from which the airfoil extends and a cooling passage extends within the root in the radial direction to the airfoil. A lower wing is arranged beneath the platform on the aft side and extends in an axial direction to provide a U-shaped channel with the platform that extends in a circumferential direction. An impingement hole extends from the U-channel to the cooling passage.
-
5.发明公开GAS TURBINE ENGINE COMPONENT WITH COMBINED MATE FACE AND PLATFORM COOLING 有权GASTURBINENMOTORKOMPONENTE MIT KOMBINIERTERANPASSUNGSFLÄCHEUND PLATTFORMKHHUNG
公开(公告)号：EP2956627A4
公开(公告)日：2016-09-28
申请号：EP14797049
申请日：2014-02-07
Applicant: UNITED TECHNOLOGIES CORP
Inventor： LEWIS SCOTT D , RAPP BRANDON M , BEATTIE JEFFREY S , HOUGH MATTHEW ANDREW , TELLER BRET M , JACQUES JEFFREY MICHAEL , ASTERLIN MAX
CPC classification number: F01D5/186 , F01D9/023 , F05D2240/81 , F05D2260/202 , F23R3/02
Abstract: A component for a gas turbine engine according to an exemplary aspect of the present disclosure includes, among other things, a platform that axially extends between a leading edge and a trailing edge, circumferentially extends between a first mate face and a second mate face, and includes a gas path surface and a non-gas path surface. The component defines at least one cavity that extends at least partially inside of the component. A first plurality of cooling holes extends from the at least one cavity to at least one of the first mate face and the second mate face and a second plurality of cooling holes extends from either the at least one cavity or the non-gas path surface to the gas path surface.
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轴向延伸的平台，其周向地在第一配合面和第二配合面之间延伸，以及 包括气体路径表面和非气体通道表面。 该部件限定至少一个至少部分地在部件内部延伸的空腔。 第一多个冷却孔从所述至少一个空腔延伸到所述第一配合面和所述第二配合面中的至少一个，并且第二多个冷却孔从所述至少一个空腔或非气体通道表面延伸到 气路面。
-
Patent Agency Ranking
公开(公告)号：EP2885520A4
公开(公告)日：2015-08-12
申请号：EP13829663
申请日：2013-08-08
Applicant: UNITED TECHNOLOGIES CORP
Inventor： TELLER BRET M , ZELESKY MARK F , LEWIS SCOTT D , SPANGLER BRANDON W , TRINDADE RICARDO
CPC classification number: F01D5/187 , F01D11/24 , F05D2240/11 , F05D2240/81 , F05D2260/201 , Y02T50/676
Abstract: A component for a gas turbine engine according to an exemplary aspect of the present disclosure includes, among other things, a platform that axially extends between a leading edge and a trailing edge and circumferentially extends between a first mate face and a second mate face and a trench disposed on at least one of the first mate face and the second mate face. A plurality of cooling holes are axially disposed within the trench.
-
公开(公告)号：EP3090143A4
公开(公告)日：2017-12-06
申请号：EP14869239
申请日：2014-11-13
Applicant: UNITED TECHNOLOGIES CORP
Inventor： LEWIS SCOTT D , KOHLI ATUL , PRAISNER THOMAS J
CPC classification number: F01D11/08 , F01D5/12 , F01D5/143 , F01D9/02 , F01D11/006 , F05D2220/32 , F05D2240/11 , F05D2240/80 , F05D2250/192 , F05D2250/231
Abstract: An array of components in a gas turbine engine includes first and second structures respectively including first and second surfaces that are arranged adjacent to one another to provide a gap. The first and second surfaces respectively have first and second rounded edges at the gap that are arranged in staggered relationship relative to one another.
-
8.发明公开MATEFACE SURFACES HAVING A GEOMETRY ON TURBOMACHINERY HARDWARE 审中-公开MATEFACE-OBERFLÄCHENMIT EINER GEOMETRIE AUF EINER TURBOMASCHINEN-HARDWARE
公开(公告)号：EP3039249A4
公开(公告)日：2017-03-29
申请号：EP14840790
申请日：2014-08-21
Applicant: UNITED TECHNOLOGIES CORP
Inventor： LEWIS SCOTT D , MAGOWAN JOHN W
CPC classification number: F01D5/141 , F01D5/02 , F01D5/081 , F01D5/18 , F01D9/041 , F01D11/006 , F01D25/12 , F05D2220/32 , F05D2240/123 , F05D2240/124 , F05D2240/305 , F05D2240/306 , F05D2240/80 , F05D2240/81 , F05D2250/32 , F05D2250/71 , F05D2260/221
-
9.发明公开INTERNALLY-COOLED ENGINE PART HAVING AN IMPINGEMENT CAVITY WITH AN UNDULATING INTERNAL SURFACE, AND CORRESPONDING GAS TURBINE ENGINE 审中-公开内部水冷发动机COMPONENT IMPACT腔用波浪面积和相关的燃气涡轮发动机
公开(公告)号：EP3181822A1
公开(公告)日：2017-06-21
申请号：EP16204836
申请日：2016-12-16
Applicant: UNITED TECHNOLOGIES CORP
Inventor： LEWIS SCOTT D , LANA KYLE C
IPC: F01D5/18
CPC classification number: F01D5/187 , F01D5/145 , F01D5/147 , F01D9/041 , F01D11/08 , F01D25/12 , F05D2220/32 , F05D2240/11 , F05D2240/12 , F05D2240/24 , F05D2240/301 , F05D2240/35 , F05D2240/81 , F05D2250/611 , F05D2260/201 , F05D2260/22141 , F23R3/002 , Y02T50/676
Abstract: An airfoil (55;200) is provided. The airfoil (55;200) comprises a crossover (232) and an impingement cavity (102,106,110) in fluid communication with the crossover (232) and having an internal surface. At least a portion of the internal surface comprises an undulating internal surface (237). A plurality of trip strips (236) may be disposed on the at least a portion of the internal surface to define the undulating internal surface (237). A gas turbine engine (20) and an internally-cooled engine part (55;200,250,252) are also provided.
Abstract translation: 翼型件（55; 200）被提供。 翼型件（55; 200）包括交叉（232）和在与交叉（232）和具有内表面流体连通冲击腔（102106110）。 至少波状内表面（237）的内表面包括的部分。 脱扣条带（236）中的多个可在内部表面的至少一部分被布置以限定起伏的内表面（237）。 一种燃气涡轮发动机（20）和在内部冷却的发动机部件，所以被提供（55 200250252）。
-
公开(公告)号：EP3049640A4
公开(公告)日：2017-04-26
申请号：EP14845261
申请日：2014-08-26
Applicant: UNITED TECHNOLOGIES CORP
Inventor： LEWIS SCOTT D , MONGILLO JR DOMINIC J , ZELESKY MARK F , TELLER BRET M , DEIBEL RUSSELL , GLEINER MATTHEW S
CPC classification number: F01D9/041 , F01D5/02 , F01D11/08 , F01D11/24 , F02C3/04 , F04D29/321 , F04D29/542 , F04D29/584 , F05D2220/32 , F05D2240/11 , F05D2240/12 , F05D2240/35 , F05D2240/80 , F05D2240/81 , F05D2250/12 , F05D2260/201 , Y02T50/676
Abstract: A vane according to an exemplary aspect of the present disclosure includes, among other things, a platform extending from an edge face and between spaced apart lateral faces and an airfoil extending outwardly from the platform. The platform includes at least one ejection port in the edge face and at least one passage connected to the at least one ejection port.
Abstract translation: 除了别的以外，根据本公开的示例性方面的叶片包括从边缘面延伸并且在间隔开的侧面与从平台向外延伸的翼面之间的平台。 平台包括在边缘面中的至少一个喷射口和连接到至少一个喷射口的至少一个通道。
-
-
-
-
-
-
-
-
-
Search Results
11
records
(took 0.024 seconds)
