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    COOLING PASSAGES FOR A MID-TURBINE FRAME
    2.
    发明申请
    COOLING PASSAGES FOR A MID-TURBINE FRAME 审中-公开
    冷却中间滚轮的通道

    公开(公告)号：US20160208701A1

    公开(公告)日：2016-07-21

    申请号：US14598732

    申请日：2015-01-16

    Applicant: United Technologies Corporation

    Inventor： Anthony P. Cherolis ,  Jeffrey J. Lienau ,  Robert Newman ,  Cheng-Zhang Wang

    IPC: F02C7/18

    CPC classification number: F02C7/18 ,  F01D9/065 ,  F05D2220/3213 ,  F05D2240/90 ,  Y02T50/675

    Abstract: A gas turbine engine includes a mid-turbine frame that includes an inner frame case. At least one spoke is connected to the inner frame case. At least one spoke includes a fluid passage that is in fluid communication with a channel on a radially inner end of the fluid passage. The channel is directed in a radially inward and circumferential direction. A cavity is located radially inward from the mid-turbine frame and is in fluid communication with the channel.

    Abstract translation: 燃气涡轮发动机包括中间涡轮机框架，其包括内框架壳体。 至少一个辐条与内框架连接。 至少一个辐条包括与流体通道的径向内端上的通道流体连通的流体通道。 通道被引导在径向向内和圆周方向。 空腔从中涡轮机框架径向向内定位并与通道流体连通。

    CONVECTION COOLING AT LOW EFFUSION DENSITY REGION OF COMBUSTOR PANEL
    3.
    发明申请
    CONVECTION COOLING AT LOW EFFUSION DENSITY REGION OF COMBUSTOR PANEL 有权

    公开(公告)号：US20210222879A1

    公开(公告)日：2021-07-22

    申请号：US16746432

    申请日：2020-01-17

    Applicant: United Technologies Corporation

    Inventor： Fumitaka Ichihashi ,  Jeffrey J. Lienau

    IPC: F23R3/00

    Abstract: A combustor for a gas turbine engine includes a combustion chamber defined between an inner shell and an outer shell. The combustor further includes a bulkhead extending between the inner shell and the outer shell. The combustor further includes a liner panel mounted to one of the inner shell and the outer shell aft of the bulkhead. The liner panel includes a first section including a first plurality of effusion holes. A first portion of the first plurality of effusion holes extends in a substantially circumferential direction. A second portion of the first plurality of effusion holes, disposed forward of the first portion, transitions from the substantially circumferential direction toward a substantially forward direction. A third portion of the first plurality of effusion holes, disposed aft of the first portion, transitions from the substantially circumferential direction to a substantially aft direction.

    SEAL SUPPORT STRUCTURES FOR TURBOMACHINES
    6.
    发明申请
    SEAL SUPPORT STRUCTURES FOR TURBOMACHINES 有权
    密封支持结构的涡轮机

    公开(公告)号：US20160376925A1

    公开(公告)日：2016-12-29

    申请号：US14662347

    申请日：2015-03-19

    Applicant: United Technologies Corporation

    Inventor： Seth A. Max ,  Anthony P. Cherolis ,  Steven D. Porter ,  Joshua D. Winn ,  Gregory E. Reinhardt ,  Jeffrey J. Lienau

    IPC: F01D25/28 ,  F01D25/24 ,  F01D11/00

    CPC classification number: F01D25/28 ,  F01D11/003 ,  F01D11/006 ,  F01D25/24 ,  F01D25/243 ,  F05D2220/32 ,  F05D2230/00 ,  F05D2230/60 ,  F05D2240/55 ,  F05D2240/60 ,  F05D2260/97

    Abstract: A seal support structure for a turbomachine includes a mounting portion shaped to mount to a stationary structure of a turbomachine and a cylindrical leg portion disposed on the mounting portion extending axially from the mounting portion. The cylindrical leg portion can include a radially extending flange. The flange can extend at an angle of 90 degrees from the end of the cylindrical leg portion. The flange can extend at least partially in an axial direction. The cylindrical leg portion can be formed integrally with the mounting portion. In embodiments, the cylindrical leg portion is not integral with the mounting portion, i.e., the cylindrical leg portion is a separate piece joined to the mounting portion.

    Abstract translation: 用于涡轮机的密封支撑结构包括成形为安装到涡轮机的固定结构的安装部分和设置在从安装部分轴向延伸的安装部分上的圆柱形腿部。 圆柱形腿部可以包括径向延伸的凸缘。 凸缘可以从圆柱形腿部的端部以90度的角度延伸。 凸缘可以在轴向方向上至少部分地延伸。 圆筒形腿部可以与安装部一体地形成。 在实施例中，圆柱形腿部不与安装部分成一体，即，圆柱形腿部是与安装部分接合的分离件。

    Combustor heat shield and method of cooling same
    9.
    发明授权
    Combustor heat shield and method of cooling same 有权

    公开(公告)号：US11293638B2

    公开(公告)日：2022-04-05

    申请号：US16549722

    申请日：2019-08-23

    Applicant: United Technologies Corporation

    Inventor： Fumitaka Ichihashi ,  Timothy S. Snyder ,  Jeffrey J. Lienau ,  Baris A. Sen

    IPC: F23R3/08 ,  F01D25/12 ,  F01D25/26

    Abstract: A combustor for a gas turbine engine includes an annular shell, an annular bulkhead connected to the shell, and a heat shield panel. The heat shield panel has a first surface facing a combustion chamber and a second surface opposite the first surface. The heat shield panel is mounted to the bulkhead and defines a cooling chamber between the bulkhead and the heat shield panel. The heat shield panel has a wall extending from the heat shield panel toward the bulkhead around at least a portion of a periphery of the heat shield panel. The wall includes a circumferential wall portion including at least one cooling air passage extending between the cooling chamber and a cavity defined between the circumferential wall portion and the shell. The at least one cooling air passage is configured to purge the cavity by directing a first cooling air stream from the cooling chamber into the cavity.

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