中科微点-全球专利检索

  1. Login
  2. Sign Up

Search Results

107 records (took 0.014 seconds)

    Interior cooling circuits in turbine blades
    72.
    发明授权
    Interior cooling circuits in turbine blades 有权

    公开(公告)号：US09765642B2

    公开(公告)日：2017-09-19

    申请号：US14143490

    申请日：2013-12-30

    Applicant: General Electric Company

    Inventor： Aaron Ezekiel Smith

    IPC: F01D5/08 ,  F01D25/12 ,  F01D5/18

    CPC classification number: F01D25/12 ,  F01D5/186 ,  F01D5/187 ,  Y02T50/676

    Abstract: A turbine blade having an airfoil defined by outer walls in which a concave shaped pressure side outer wall and a convex shaped suction side outer wall connect along leading and trailing edges and form a chamber for receiving the flow of a coolant. The turbine blade may include a rib configuration that partitions the chamber into radially extending flow passages. The rib configuration may include a rib having a wavy profile that opposes a target surface across one of the flow passages. Relative to the target surface, the wavy profile of the rib may include a ridge portion and a furrow portion. The rib may include impingement apertures formed through the ridge portion.

    COOLING STRUCTURE FOR HOT-GAS PATH COMPONENTS WITH METHODS OF FABRICATION
    76.
    发明申请
    COOLING STRUCTURE FOR HOT-GAS PATH COMPONENTS WITH METHODS OF FABRICATION 有权
    具有制造方法的热气路径组件的冷却结构

    公开(公告)号：US20170037731A1

    公开(公告)日：2017-02-09

    申请号：US14818695

    申请日：2015-08-05

    Applicant: General Electric Company

    Inventor： Victor John Morgan ,  George Andrew Gergely ,  Frederic Woodrow Roberts, JR. ,  Aaron Ezekiel Smith

    IPC: F01D5/18 ,  B23P15/02 ,  F01D9/06

    CPC classification number: F01D5/187 ,  B23P15/02 ,  F01D9/065 ,  F05D2240/81 ,  F05D2250/314 ,  F05D2250/75 ,  F05D2260/2212 ,  F05D2260/2214

    Abstract: Embodiments of the present disclosure provide components for hot gas path (HGP) components and methods of forming the same. A structure according to the present disclosure can include: an HGP component extending radially from a rotor axis of a turbomachine, the HGP component including a tapered edge; a plurality of first passages in fluid communication with a preliminary cooling zone of the HGP component, and extending through a sidewall positioned between the preliminary cooling zone and the tapered edge; and a plurality of second passages extending through at least the tapered edge, wherein each of the plurality of second passages is in fluid communication with the flow path for the operative fluid and at least one passage of the plurality of first passages, and wherein at least one of the plurality of second passages is radially displaced from each passage of the plurality of first passages.

    Abstract translation: 本公开的实施例提供了用于热气路径（HGP）部件的部件及其形成方法。 根据本公开的结构可以包括：HGP部件，其从涡轮机的转子轴线径向延伸，所述HGP部件包括锥形边缘; 多个第一通道，其与HGP部件的预冷却区域流体连通，并且延伸穿过位于预冷却区域和锥形边缘之间的侧壁; 以及多个第二通道，其至少延伸穿过所述锥形边缘，其中所述多个第二通道中的每一个与所述操作流体的流动路径和所述多个第一通道的至少一个通道流体连通，并且其中至少 多个第二通道中的一个从多个第一通道的每个通道径向移位。

    AIRFOIL AND METHOD FOR MANUFACTURING AN AIRFOIL
    77.
    发明申请
    AIRFOIL AND METHOD FOR MANUFACTURING AN AIRFOIL 审中-公开
    飞行器和制造航空器的方法

    公开(公告)号：US20160245097A1

    公开(公告)日：2016-08-25

    申请号：US15142640

    申请日：2016-04-29

    Applicant: General Electric Company

    Inventor： Mark Andrew Jones ,  Aaron Ezekiel Smith

    IPC: F01D5/18 ,  F01D25/12 ,  F01D9/04

    CPC classification number: F01D5/187 ,  F01D9/041 ,  F01D25/12 ,  F05D2220/32 ,  F05D2240/304 ,  F05D2260/202

    Abstract: An airfoil includes a pressure side, a suction side opposed to the pressure side, a cavity inside the airfoil between the pressure and suction sides, and a trailing edge downstream from the cavity between the pressure and suction sides. A first set of cooling passages through the trailing edge provide fluid communication from the cavity through the trailing edge. A first divider across each cooling passage in the first set of cooling passages extends from the pressure side to the suction side at the trailing edge.

    Abstract translation: 翼型件包括压力侧，与压力侧相对的吸入侧，在压力侧和吸力侧之间的翼型内的空腔，以及在压力侧和吸力侧之间的空腔下游的后缘。 通过后缘的第一组冷却通道提供从空腔到后缘的流体连通。 第一组冷却通道中的每个冷却通道的第一分隔件从后侧的压力侧延伸到吸入侧。

    Airfoil and a method for cooling an airfoil platform
    78.
    发明授权
    Airfoil and a method for cooling an airfoil platform 有权
    翼型和翼型平台的冷却方法

    公开(公告)号：US09121292B2

    公开(公告)日：2015-09-01

    申请号：US13705804

    申请日：2012-12-05

    Applicant: General Electric Company

    Inventor： Xiuzhang James Zhang ,  Stephen Paul Wassynger ,  Aaron Ezekiel Smith ,  Anthony Louis Giglio

    IPC: F01D5/18

    CPC classification number: F01D5/187 ,  F01D5/186 ,  F05D2240/81 ,  Y02T50/673 ,  Y02T50/676

    Abstract: An airfoil includes an outer surface having a leading edge, a trailing edge downstream from the leading edge, and a convex surface between the leading and trailing edges. A cavity is inside the outer surface, and a platform is connected to the outer surface and defines a top surface around at least a portion of the outer surface. A first plurality of trenches is beneath the top surface of the platform upstream from the leading edge, wherein each trench in the first plurality of trenches is in fluid communication with the cavity inside the outer surface. A first plurality of cooling passages provide fluid communication from the first plurality of trenches through the top surface of the platform.

    Abstract translation: 翼型件包括具有前缘的外表面，在前缘下游的后缘以及前缘和后缘之间的凸面。 空腔在外表面内，并且平台连接到外表面并且围绕外表面的至少一部分限定顶表面。 第一多个沟槽位于平台的顶表面上方的前缘上游，其中第一多个沟槽中的每个沟槽与外表面内的空腔流体连通。 第一多个冷却通道提供从第一多个沟槽通过平台的顶表面的流体连通。

    METHOD AND SYSTEM FOR PROVIDING SEALING IN GAS TURBINES
    79.
    发明申请
    METHOD AND SYSTEM FOR PROVIDING SEALING IN GAS TURBINES 审中-公开
    用于在气体涡轮机中提供密封的方法和系统

    公开(公告)号：US20150118042A1

    公开(公告)日：2015-04-30

    申请号：US14063269

    申请日：2013-10-25

    Applicant: General Electric Company

    Inventor： Victor John Morgan ,  Aaron Ezekiel Smith ,  David Wayne Weber

    IPC: F01D11/00

    CPC classification number: F01D11/005 ,  F01D11/003 ,  F01D11/006 ,  F01D11/008

    Abstract: A gas turbine system is provided that includes a compressor section, a combustor assembly coupled to the compressor section, and a turbine section coupled to the compressor section. At least one of the combustor assembly and the turbine section includes a sealing sub-system for use in sealing between a first component and a second component. A first component defines a first seal member receiving region oriented between a higher-temperature gas region and a cooler-temperature gas region. A second component adjacent the first component defines a second seal member receiving region oriented adjacent the first seal member receiving region. The sealing system includes first and second end walls defined in at least one of the first and second seal member receiving regions. A seal member is oriented within the first and second seal member receiving regions, and includes at least a first layer defining at least a first resilient seal end portion that engages one of the first and second end walls.

    Abstract translation: 提供了一种燃气轮机系统，其包括压缩机部分，联接到压缩机部分的燃烧器组件和联接到压缩机部分的涡轮部分。 燃烧器组件和涡轮部分中的至少一个包括用于密封第一部件和第二部件之间的密封子系统。 第一部件限定在较高温度气体区域和较冷温度气体区域之间定向的第一密封构件接收区域。 与第一部件相邻的第二部件限定了邻近第一密封件接收区域定向的第二密封件接收区域。 密封系统包括限定在第一和第二密封构件接收区域中的至少一个中的第一和第二端壁。 密封构件定位在第一和第二密封构件接收区域内，并且包括限定至少第一弹性密封端部的至少第一层，该第一层限定第一和第二端壁中的一个。

Patent Agency Ranking