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Patent Agency Ranking
公开(公告)号：US20160201469A1
公开(公告)日：2016-07-14
申请号：US14914762
申请日：2014-08-21
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Scott D. Lewis , John W. Magowan
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。
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公开(公告)号：US10577936B2
公开(公告)日：2020-03-03
申请号：US14914762
申请日：2014-08-21
Applicant: United Technologies Corporation
Inventor： Scott D. Lewis , John W. Magowan
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.
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公开(公告)号：US10125694B2
公开(公告)日：2018-11-13
申请号：US14950095
申请日：2015-11-24
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： John W. Magowan
Abstract: A gas turbine engine has a fan section including a fan hub supporting a plurality of fan blades for rotation relative to a fan case. A shaft is rotatable relative to the fan case about an engine center axis. A geared architecture is driven by the shaft and provides driving output to rotate the fan hub. A compressor is driven by the shaft and is positioned forward of the geared architecture. The compressor includes at least first and second stages with the first stage being positioned forward of the plurality of fan blades and the second stage being positioned aft of the plurality of fan blades. The compressor includes at least one set of vanes that rotate in a first direction about the engine center axis and at least one set of compressor blades that rotate in a second direction about the engine center axis. The second direction is opposite of the first direction.
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公开(公告)号：US20160305324A1
公开(公告)日：2016-10-20
申请号：US15101178
申请日：2014-11-19
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： John W. Magowan
CPC classification number: F02C7/143 , F02C3/107 , F02C7/08 , F02C7/10 , F02C7/185 , F02K3/077 , F05D2220/32 , F05D2250/30 , F05D2250/311 , F05D2260/211 , Y02T50/675
Abstract: A gas turbine engine includes a first stage compressor, an intercooler in fluid communication with the first stage compressor, and a second stage compressor in fluid communication with the intercooler. The engine also includes a combustor in fluid communication with the second stage compressor and a turbine in fluid communication with the combustor. The intercooler cools an air inflow from the first stage compressor and the recuperator heats the airflow traveling from the second stage compressor to the turbine exhaust. The intercooler and recuperator are arranged radially outward of the combustor.
Abstract translation: 燃气涡轮发动机包括第一级压缩机，与第一级压缩机流体连通的中间冷却器和与中间冷却器流体连通的第二级压缩机。 发动机还包括与第二级压缩机流体连通的燃烧器和与燃烧器流体连通的涡轮机。 中间冷却器冷却来自第一级压缩机的空气流入，并且换热器将从第二级压缩机行进的气流加热到涡轮机排气。 中间冷却器和换热器布置在燃烧器的径向外侧。
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公开(公告)号：US20160076459A1
公开(公告)日：2016-03-17
申请号：US14950095
申请日：2015-11-24
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： John W. Magowan
CPC classification number: F02C7/36 , F02C3/067 , F02C3/107 , F02K3/06 , F05D2260/40311
Abstract: A gas turbine engine has a fan section including a fan hub supporting a plurality of fan blades for rotation relative to a fan case. A shaft is rotatable relative to the fan case about an engine center axis. A geared architecture is driven by the shaft and provides driving output to rotate the fan hub. A compressor is driven by the shaft and is positioned forward of the geared architecture. The compressor includes at least first and second stages with the first stage being positioned forward of the plurality of fan blades and the second stage being positioned aft of the plurality of fan blades. The compressor includes at least one set of vanes that rotate in a first direction about the engine center axis and at least one set of compressor blades that rotate in a second direction about the engine center axis. The second direction is opposite of the first direction.
Abstract translation: 燃气涡轮发动机具有风扇部分，风扇部分包括支撑相对于风扇壳体旋转的多个风扇叶片的风扇轮毂。 轴可相对于发动机中心轴线相对于风扇壳体旋转。 齿轮架构由轴驱动，并提供驱动输出以旋转风扇轮毂。 压缩机由轴驱动并位于齿轮架构的前方。 压缩机包括至少第一和第二级，其中第一级位于多个风扇叶片的前方，第二级定位在多个风扇叶片的后方。 压缩机包括至少一组围绕发动机中心轴线在第一方向上旋转的叶片以及围绕发动机中心轴线沿第二方向旋转的至少一组压缩机叶片。 第二方向与第一方向相反。
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