中科微点-全球专利检索

  1. Login
  2. Sign Up

Search Results

75 records (took 0.016 seconds)

    LOW LUMP MASS COMBUSTOR WALL WITH QUENCH APERTURE(S)
    52.
    发明申请
    LOW LUMP MASS COMBUSTOR WALL WITH QUENCH APERTURE(S) 审中-公开
    低MP MP）OR）））））））））

    公开(公告)号：US20160123594A1

    公开(公告)日：2016-05-05

    申请号：US14932556

    申请日：2015-11-04

    Applicant: United Technologies Corporation

    Inventor： Frank J. Cunha ,  Stanislav Kostka

    IPC: F23R3/06 ,  F02C7/18 ,  F23R3/00

    Abstract: An assembly is provided for a turbine engine. This turbine engine assembly includes a combustor wall including a first layer vertically connected with a second layer. A first portion of the first layer overlaps and is vertically spaced from the second layer by a cavity. A second portion of the first layer is substantially vertically inline with an adjacent portion of the second layer. The second portion of the first layer at least partially forms a quench aperture vertically through the combustor wall.

    Abstract translation: 提供了一种用于涡轮发动机的组件。 该涡轮发动机组件包括燃烧器壁，该燃烧器壁包括与第二层垂直连接的第一层。 第一层的第一部分与空腔重叠并与第二层垂直间隔开。 第一层的第二部分基本上与第二层的相邻部分垂直一致。 第一层的第二部分至少部分地通过燃烧器壁垂直地形成骤冷孔。

    GAS TURBINE ENGINE COMBUSTOR LINER PANEL
    53.
    发明申请
    GAS TURBINE ENGINE COMBUSTOR LINER PANEL 审中-公开
    燃气轮机发动机衬板

    公开(公告)号：US20160102861A1

    公开(公告)日：2016-04-14

    申请号：US14893378

    申请日：2014-05-23

    Applicant: UNITED TECHNOLOGIES CORPORATION

    Inventor： Frank J. Cunha ,  Stanislav Kostka, JR.

    IPC: F23R3/00 ,  F23R3/06

    Abstract: A liner panel for a combustor of a gas turbine engine includes a multiple of heat transfer augmentors which extend from a cold side thereof. At least one of the multiple of heat transfer augmentors includes a first heat transfer augmentation feature with a second heat transfer augmentation feature stacked thereon.

    Abstract translation: 用于燃气涡轮发动机的燃烧器的衬板包括多个从其冷侧延伸的传热增强器。 多个传热增强器中的至少一个包括具有堆叠在其上的第二传热增强特征的第一传热增强特征。

    GROMMET ASSEMBLY AND METHOD OF DESIGN
    55.
    发明申请
    GROMMET ASSEMBLY AND METHOD OF DESIGN 审中-公开
    GROMMET装配和设计方法

    公开(公告)号：US20150285498A1

    公开(公告)日：2015-10-08

    申请号：US14677520

    申请日：2015-04-02

    Applicant: United Technologies Corporation

    Inventor： Frank J. Cunha ,  Stanislav Kostka, JR. ,  Andreas Sadil

    IPC: F23R3/06 ,  F02C7/18

    Abstract: A grommet assembly and method of design to enhance the flow coefficient, thereof, includes a shell having a first side and an opposite second side, and a chamfered grommet projecting through the shell along a centerline and including an annular first end surface spaced outward from the first side and a conical face spanning axially and radially inward from the annular first end surface and axially beyond the second side. The assembly may further include a panel spaced from the shell and defining a cooling cavity therebetween with the conical surface defining at least in-part a hole in fluid communication through the shell and panel and isolated from the cooling cavity. A plurality of cooling channels in the grommet are in fluid communication with the cooling cavity and communicate through the panel. The combination of the conical face and the cooling channels improve the discharge coefficient of the grommet while enhancing grommet cooling.

    Abstract translation: 一种用于提高其流动系数的护环组件和设计方法包括具有第一侧和相对的第二侧的壳体，以及沿着中心线突出穿过壳体的倒角索环，并且包括从第二侧向外间隔开的环形第一端表面 第一侧和圆锥形表面从环形第一端表面轴向和径向向内跨过并且轴向地超过第二侧。 组件还可以包括与壳体间隔开并且在其间限定冷却腔的面板，锥形表面至少部分地限定通过壳体和面板流体连通并与冷却腔隔离的孔。 索环中的多个冷却通道与冷却腔流体连通并通过面板连通。 锥形面和冷却通道的组合提高了垫圈的排气系数，同时增强了索环冷却。

    Film cooling a combustor wall of a turbine engine
    56.
    发明授权
    Film cooling a combustor wall of a turbine engine 有权

    公开(公告)号：US11320146B2

    公开(公告)日：2022-05-03

    申请号：US16703211

    申请日：2019-12-04

    Applicant: United Technologies Corporation

    Inventor： Frank J. Cunha ,  Stanislav Kostka, Jr.

    IPC: F23R3/00 ,  F02C7/18 ,  F23R3/06 ,  F02C7/12

    Abstract: An assembly is provided for a turbine engine. This turbine engine assembly includes a combustor wall including a shell and a heat shield. The combustor wall defines first and second cavities between the shell and the heat shield. The heat shield defines a first outlet and an elongated second outlet. The first outlet is fluidly coupled with the first cavity. The second outlet is fluidly coupled with the second cavity. The combustor wall defines one of the cavities with a tapered geometry.

    Cooling a quench aperture body of a combustor wall
    58.
    发明授权
    Cooling a quench aperture body of a combustor wall 有权

    公开(公告)号：US10386068B2

    公开(公告)日：2019-08-20

    申请号：US15038774

    申请日：2014-12-03

    Applicant: United Technologies Corporation

    Inventor： Stanislav Kostka, Jr. ,  Frank J. Cunha

    IPC: F23R3/00 ,  F23R3/04 ,  F23R3/06 ,  F23R3/50

    Abstract: An assembly is provided for a turbine engine. A combustor wall of the turbine engine assembly includes a shell, a heat shield and an annular body. The annular body extends through the combustor wall. The annular body at least partially defines a quench aperture along a centerline through the combustor wall. The annular body defines a first cooling aperture fluidly coupled between a cooling cavity and the quench aperture. The cooling cavity is between the shell and the heat shield.

Patent Agency Ranking