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    11.
    发明专利
    未知

    公开(公告)号：NO20045512L

    公开(公告)日：2005-06-20

    申请号：NO20045512

    申请日：2004-12-17

    Applicant: UNITED TECHNOLOGIES CORP

    Inventor： GREGG SHAWN J ,  MONGILLO DOMINIC J

    IPC: F01D5/16 ,  F01D5/18 ,  F02C7/18

    Abstract: A rotor blade (14) for a rotor assembly (10) is provided that includes a root (180, an airfoil (20), and a damper (24). The airfoil (20) includes a base (28), a tip (30), a pressure side wall (36), a suction side wall (38), and a cavity (40) disposed therebetween. The cavity (40) extends substantially between the base (28) and the tip (30), and includes a first cavity portion (44), a second cavity portion (46), and a channel (42) disposed between the first cavity portion (44) and the second cavity portion (46). A plurality of first pedestals (48) are disposed within the first cavity portion (44) adjacent the channel (42), and a plurality of second pedestals (48) are disposed within the second cavity portion (46) adjacent the channel (42). The damper (24) is selectively received within the channel (42).

    IMPROVED COOLING FOR A TURBINE AIRFOIL TRAILING EDGE
    14.
    发明公开
    IMPROVED COOLING FOR A TURBINE AIRFOIL TRAILING EDGE 审中-公开
    改进的涡轮螺栓固定器的冷却

    公开(公告)号：EP2877705A4

    公开(公告)日：2015-11-11

    申请号：EP13813721

    申请日：2013-03-28

    Applicant: UNITED TECHNOLOGIES CORP

    Inventor： LEVINE JEFFREY R ,  MONGILLO DOMINIC J ,  DONNELL BRANDON S

    IPC: F01D5/18 ,  F01D5/14 ,  F01D9/06 ,  F02C7/12

    CPC classification number: F01D5/187 ,  F01D5/145 ,  F01D5/186 ,  F01D9/041 ,  F01D9/065 ,  F05D2240/122 ,  F05D2240/304 ,  F05D2250/12 ,  F05D2260/202

    Abstract: An assembly for a gas turbine engine includes a first platform and an airfoil extending from the first platform. The airfoil includes a first fillet, pressure side biased discharge openings, and a first center cooling discharge opening. A pressure side wall of the airfoil and the first platform form an acute angle at the trailing edge. The first fillet is formed around a perimeter of the airfoil where the airfoil extends from the first platform. The pressure side biased cooling discharge openings are along the trailing edge outside of the first fillet. Each pressure side biased cooling discharge opening extends from the trailing edge along the pressure side wall. The first center cooling discharge opening extends along the trailing edge into the first fillet and is centrally located between the pressure side wall and the suction side wall.

    SELF-COOLED ORIFICE STRUCTURE
    15.
    发明授权
    SELF-COOLED ORIFICE STRUCTURE 有权
    SELBSTKÜHLENDEÖFFNUNGSSTRUKTUR

    公开(公告)号：EP2963346B1

    公开(公告)日：2017-05-03

    申请号：EP15175344

    申请日：2015-07-03

    Applicant: UNITED TECHNOLOGIES CORP

    Inventor： PROPHETER-HINCKLEY TRACY A ,  MONGILLO DOMINIC J ,  WAGNER JOEL H ,  ZELESKY MARK F ,  KOSTKA STANISLAV ,  SNYDER TIMOTHY S

    IPC: F23R3/00 ,  F23R3/06

    CPC classification number: F23R3/06 ,  F23R3/002 ,  F23R3/005 ,  F23R2900/00019 ,  F23R2900/03042 ,  F23R2900/03044 ,  Y02T50/675

    Abstract: A self-cooled orifice structure, for example a dilution hole structure for a combustor of a gas turbine engine, includes a cold side panel spaced from a hot side panel, and a continuous inner wall extending between the hot and cold side panels and defining an orifice communicating through the hot and cold side panels. A plurality of end walls of the structure are in a cooling cavity that is defined in-part by the hot and cold side panels and the inner wall. Each end wall extends between and are engaged to the hot and cold side panels and are circumferentially spaced from the next adjacent end wall. A plurality of inlet apertures extend through the cold side panel, in fluid communication with the cavity, and proximate to a first side of the end walls. A plurality of outlet apertures extend through the hot side panel, in fluid communication with the cavity, and associated with an opposite second side of the end walls.

    Abstract translation: 自冷却孔口结构（例如用于燃气涡轮发动机的燃烧器的稀释孔结构）包括与热侧面板间隔开的冷侧面板以及在热侧面板和冷侧面板之间延伸的连续内壁， 小孔通过冷热侧板连通。 该结构的多个端壁处于由冷热侧板和内壁部分地限定的冷却腔中。 每个端壁在热侧板和冷侧板之间延伸并与其接合，并与下一个相邻端壁周向间隔开。 多个入口孔延伸穿过冷侧板，与腔体流体连通并靠近端壁的第一侧。 多个出口孔延伸穿过热侧板，与腔体流体连通并且与端壁的相对的第二侧相关联。

    COOLING HOLE FOR A GAS TURBINE ENGINE COMPONENT
    19.
    发明公开
    COOLING HOLE FOR A GAS TURBINE ENGINE COMPONENT 审中-公开
    燃气轮机发动机部件的冷却孔

    公开(公告)号：EP2956646A4

    公开(公告)日：2016-10-12

    申请号：EP14752111

    申请日：2014-02-07

    Applicant: UNITED TECHNOLOGIES CORP

    Inventor： SPANGLER BRANDON W ,  MONGILLO DOMINIC J

    IPC: F01D5/18 ,  F01D5/28 ,  F01D9/06

    CPC classification number: F01D9/023 ,  F01D5/186 ,  F01D5/288 ,  F01D9/065 ,  F01D11/20 ,  F05D2240/11 ,  F05D2240/81 ,  F05D2250/12 ,  F05D2260/202 ,  F23R3/002 ,  F23R2900/03042

    Abstract: A component for a gas turbine engine according to an exemplary aspect of the present disclosure includes, among other things, a wall having an internal surface and an outer skin, a cooling hole having an inlet extending from the internal surface and merging into a metering section, and a diffusion section downstream of the metering section that extends to an outlet located at the outer skin. The diffusion section of the cooling hole includes a first side diffusion angle, a second side diffusion angle and a downstream diffusion angle at a downstream surface of the diffusion section, the downstream diffusion angle being less than the first side diffusion angle and the second side diffusion angle.

    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具有内表面和外表皮的壁，冷却孔，其具有从内表面延伸并且汇合到计量部分 ，以及在计量部分下游延伸到位于外皮的出口的扩散部分。 冷却孔的扩散部分包括在扩散部分的下游表面处的第一侧扩散角，第二侧扩散角和下游扩散角，下游扩散角小于第一侧扩散角和第二侧扩散 角度。

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