-
Patent Agency Ranking
公开(公告)号：WO2014028294A1
公开(公告)日：2014-02-20
申请号：PCT/US2013/054091
申请日：2013-08-08
Applicant: UNITED TECHNOLOGIES CORPORATION
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.
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并在第一配合面和第二配合面之间周向延伸的平台， 沟槽，设置在第一配合面和第二配合面中的至少一个上。 多个冷却孔轴向设置在沟槽内。
-
公开(公告)号：WO2014003958A1
公开(公告)日：2014-01-03
申请号：PCT/US2013/043340
申请日：2013-05-30
Applicant: UNITED TECHNOLOGIES CORPORATION
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.
Abstract translation: 一种用于燃气涡轮发动机的涡轮叶片包括一个翼型件，其包括通过间隔开的压力和吸力侧连接的前缘和后缘，以提供沿径向方向延伸的外部翼面。 后缘布置在涡轮叶片的后侧。 根部支撑翼型件延伸的平台，并且冷却通道在根部内沿径向方向延伸到翼型件。 下翼设置在平台的后侧，在轴向方向上延伸，以提供具有沿圆周方向延伸的平台的U形通道。 冲击孔从U形通道延伸到冷却通道。
-
公开(公告)号：WO2015031160A1
公开(公告)日：2015-03-05
申请号：PCT/US2014/052114
申请日：2014-08-21
Applicant: UNITED TECHNOLOGIES CORPORATION
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
Abstract: Turbomachinery hardware, used in a rotor assembly and a stator assembly, including an airfoil portion including a leading edge, a trailing edge, a pressure side, and a suction side, and a platform on which the airfoil portion is disposed. The platform including a platform axis, a pressure side mateface located adjacent to the pressure side of the airfoil portion and a suction side mateface located adjacent to the suction side airfoil portion, wherein a portion of a pressure side mateface includes a first geometry, and a portion of a suction side mateface includes a second geometry. The first geometry is selected from a group consisting of: oblique to a platform axis, and a first curved portion. The second geometry is selected from a group consisting of: oblique to the platform axis and a second curved portion.
Abstract translation: 用于转子组件和定子组件的涡轮机械硬件，包括包括前缘，后缘，压力侧和吸力侧的翼型部分，以及设置翼型部分的平台。 所述平台包括平台轴线，位于所述翼型部分的压力侧附近的压力侧配合件和邻近所述吸入侧翼型部分的吸力侧面板，其中压力侧面部分包括第一几何形状，以及 抽吸侧面的一部分包括第二几何形状。 第一几何形状选自由以下部分组成的组：倾斜于平台轴线和第一弯曲部分。 第二几何形状选自：倾斜于平台轴线和第二弯曲部分的组。
-
4.发明申请
公开(公告)号：WO2014028138A1
公开(公告)日：2014-02-20
申请号：PCT/US2013/049553
申请日：2013-07-08
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： LEWIS, Scott, D. , ZESS, Gary, A.
CPC classification number: F01D5/18 , F01D5/187 , F01D5/288 , F05D2230/90 , F05D2240/127 , F05D2240/304 , F05D2260/2212 , F05D2260/22141 , Y02T50/676 , Y10T29/49341
Abstract: An airfoil for a gas turbine engine includes pressure and suction surfaces provided by pressure and suction walls that extend in a radial direction and are joined at a leading edge and a trailing edge. A cooling passage is arranged between the pressure and suction walls and extends to the trailing edge. Elongated pedestals are arranged in the cooling passage and interconnect the pressure and suction walls. The elongated pedestals are spaced apart from one another in the radial direction and extend from a plane to the trailing edge. A metering pedestal includes at least a portion that is arranged between the plane and the trailing edge. The portion is provided between adjacent elongated pedestals in the radial direction.
Abstract translation: 用于燃气涡轮发动机的翼型包括由压力和吸力壁提供的压力和吸力表面，其在径向方向上延伸并且在前缘和后缘处接合。 冷却通道设置在压力壁和吸力壁之间并延伸到后缘。 细长的基座布置在冷却通道中并互连压力和吸力壁。 细长基座在径向上彼此间隔开并且从平面延伸到后缘。 计量基座包括布置在平面和后缘之间的至少一部分。 该部分在径向方向上设置在相邻的细长基座之间。
-
公开(公告)号：WO2013122906A1
公开(公告)日：2013-08-22
申请号：PCT/US2013/025686
申请日：2013-02-12
Applicant: UNITED TECHNOLOGIES CORPORATION
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
Abstract: A gas turbine engine component includes first and second wall surfaces, an inlet located at the first wall surface, an outlet located at the second wall surface and a diffusing section positioned between the inlet and the outlet. The diffusing section includes a first lobe, a second lobe adjacent the first lobe and a third lobe adjacent the second lobe. The first lobe and the second lobe meet at a first ridge and the second lobe and the third lobe meet at a second ridge.
Abstract translation: 燃气涡轮发动机部件包括第一和第二壁表面，位于第一壁表面处的入口，位于第二壁表面处的出口和位于入口和出口之间的扩散部分。 扩散部分包括第一凸角，与第一凸角相邻的第二凸角和与第二凸角相邻的第三凸角。 第一个小叶和第二个小叶在第一个山脊相交，第二个叶和第三个叶在第二个山脊相遇。
-
-
-
-
Search Results
5
records
(took 0.009 seconds)
