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    Internally cooled spoke
    21.
    发明授权
    Internally cooled spoke 有权
    内部冷却的辐条

    公开(公告)号：US09512738B2

    公开(公告)日：2016-12-06

    申请号：US13753821

    申请日：2013-01-30

    Applicant: United Technologies Corporation

    Inventor： Paul K. Sanchez ,  Kalpendu J. Parekh ,  William A. Daniels ,  John S. Tu

    IPC: F01D5/18 ,  F01D25/14 ,  F01D25/12 ,  F01D25/24 ,  F01D25/16

    CPC classification number: F02C7/20 ,  F01D25/12 ,  F01D25/14 ,  F01D25/16 ,  F01D25/162 ,  F01D25/24 ,  F01D25/246 ,  F02C7/12 ,  F02K3/04 ,  F05D2220/36 ,  F05D2260/20

    Abstract: A turbine engine includes a compressor section, a combustor section in fluid communication with the compressor section, a high pressure turbine in fluid communication with the combustor, a low pressure turbine in fluid communication with the high pressure turbine, and a mid turbine frame located axially between the high pressure turbine and the low pressure turbine. The mid turbine frame includes an outer frame case, an inner frame case, and a plurality of hollow spokes that distribute loads from the inner frame case to the outer frame case. The spokes are hollow to allow cooling airflow to be supplied through the spokes to the inner frame case.

    Abstract translation: 涡轮发动机包括压缩机部分，与压缩机部分流体连通的燃烧器部分，与燃烧器流体连通的高压涡轮机，与高压涡轮机流体连通的低压涡轮机，以及位于轴向 在高压涡轮机和低压涡轮机之间。 中间涡轮机框架包括外框架壳体，内框架壳体和多个中空轮辐，其将负载从内框架壳体分配到外框架壳体。 轮辐是中空的，以允许冷却气流通过轮辐供应到内框架壳体。

    COOLED WALL ASSEMBLY FOR A COMBUSTOR AND METHOD OF DESIGN
    22.
    发明申请
    COOLED WALL ASSEMBLY FOR A COMBUSTOR AND METHOD OF DESIGN 审中-公开
    冷却水箱组装和设计方法

    公开(公告)号：US20160169512A1

    公开(公告)日：2016-06-16

    申请号：US14939619

    申请日：2015-11-12

    Applicant: United Technologies Corporation

    Inventor： John S. Tu ,  Steven W. Burd

    IPC: F23M5/08 ,  F23R3/06 ,  F23R3/00

    Abstract: A wall assembly that may be for a combustor of a gas turbine engine includes a liner having a hot face that defines a combustion chamber, an opposite cold face, and a plurality of effusion holes. A shell of the assembly is spaced outward from the cold face and includes a plurality of impingement holes each having a centerline orientated substantially normal to the cold face. A plurality of cooling member arrays of the liner each include a first plurality of members that may be pins projecting outward from the cold face to conduct heat out of the liner. Each array is spaced between adjacent effusion holes and is symmetrically orientated about the respective centerline.

    Abstract translation: 可用于燃气涡轮发动机的燃烧器的壁组件包括具有限定燃烧室，相对冷面和多个渗出孔的热面的衬套。 组件的壳体与冷面相隔一定距离，并且包括多个冲击孔，每个冲击孔具有基本垂直于冷面的中心线。 衬套的多个冷却构件阵列各自包括第一多个构件，其可以是从冷面向外突出的销，以将热量传导出衬套。 每个阵列在相邻的渗出孔之间隔开并且围绕相应的中心线对称定向。

    Combustor panels having angled rail
    25.
    发明授权
    Combustor panels having angled rail 有权

    公开(公告)号：US10260750B2

    公开(公告)日：2019-04-16

    申请号：US14982642

    申请日：2015-12-29

    Applicant: United Technologies Corporation

    Inventor： John S. Tu ,  James B. Hoke ,  Jonathan Jeffery Eastwood ,  Kevin Joseph Low ,  Sean D. Bradshaw

    IPC: F23R3/00 ,  F23R3/26 ,  F23R3/06

    Abstract: A combustor of a gas turbine engine including a combustor shell having an interior surface defining a combustion chamber, a first panel mounted to the interior surface at a first position, the first panel having a first surface and a first rail extending from the first surface toward the combustor shell, the first rail configured at a first angle relative to the first surface, and a second panel mounted to the interior surface at a second position axially adjacent to the first panel, the second panel having a second surface and a second rail extending from the second surface toward the combustor shell, the second rail configured at a second angle relative to the second surface. The first and second rails are proximal to each other and define a circumferential gap there between and at least one of the first or second angles is an acute angle.

    Combustor panels having recessed rail
    26.
    发明授权
    Combustor panels having recessed rail 有权

    公开(公告)号：US10215411B2

    公开(公告)日：2019-02-26

    申请号：US15062440

    申请日：2016-03-07

    Applicant: United Technologies Corporation

    Inventor： John S. Tu ,  James B. Hoke ,  David Kwoka ,  Jonathan Jeffery Eastwood

    IPC: F23R3/00 ,  F23R3/06 ,  F23M5/08 ,  F23R3/04 ,  F23M5/00 ,  F23M5/04

    Abstract: A combustor of a gas turbine engine including a combustor shell having an interior surface, a first panel mounted to the interior surface at a first position and a second panel mounted to the interior surface at a second position. The first panel has a first end, a first combustion chamber surface parallel with the interior surface, a first rail extending from the first combustion chamber surface toward the interior surface of the combustor shell, and a first extension extending axially from the first rail to the end of the first panel. The second panel has a second end, a second combustion chamber surface, and a second rail extending from the second combustion chamber surface toward the interior surface of the combustor shell. The first end and the second end are proximal to each other and define a circumferentially extending gap there between.

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