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    HEAT EXCHANGER SUPPLY PLENUM
    1.
    发明申请
    HEAT EXCHANGER SUPPLY PLENUM 有权

    公开(公告)号：US20210207564A1

    公开(公告)日：2021-07-08

    申请号：US16736342

    申请日：2020-01-07

    Applicant: UNITED TECHNOLOGIES CORPORATION

    Inventor： Curtis C. Cowan ,  Rebecca R. Dunnigan ,  Gary D. Roberge

    IPC: F02M35/10

    Abstract: A cooling system for a gas turbine engine may comprise a plenum extending circumferentially around an outer engine case structure. The plenum may comprise a supply conduit and a return conduit. The supply conduit and the return conduit may be in fluid communication with a heat exchanger. The heat exchanger may be disposed between the outer engine case structure and an inner engine case structure. The plenum may be configured to provide enhance heat transfer for the cooling system.

    Heat exchanger supply plenum
    2.
    发明授权
    Heat exchanger supply plenum 有权

    公开(公告)号：US11519368B2

    公开(公告)日：2022-12-06

    申请号：US16736342

    申请日：2020-01-07

    Applicant: UNITED TECHNOLOGIES CORPORATION

    Inventor： Curtis C. Cowan ,  Rebecca R. Dunnigan ,  Gary D. Roberge

    IPC: F02M35/10 ,  B60K13/02

    Abstract: A cooling system for a gas turbine engine may comprise a plenum extending circumferentially around an outer engine case structure. The plenum may comprise a supply conduit and a return conduit. The supply conduit and the return conduit may be in fluid communication with a heat exchanger. The heat exchanger may be disposed between the outer engine case structure and an inner engine case structure. The plenum may be configured to provide enhance heat transfer for the cooling system.

    Impingement cooled nozzle liner
    4.
    发明授权
    Impingement cooled nozzle liner 有权

    公开(公告)号：US10132181B2

    公开(公告)日：2018-11-20

    申请号：US15876602

    申请日：2018-01-22

    Applicant: United Technologies Corporation

    Inventor： Curtis C. Cowan ,  Jorge I. Farah

    IPC: F02K1/82 ,  F01D11/00 ,  F02K1/12 ,  F02C7/28 ,  F16J15/08 ,  F02K1/00 ,  F16J15/02 ,  F01D5/18

    Abstract: A method for cooling a rotatable nozzle includes rotating a curved seal about a seal land while maintaining contact therewith. Cooling air is directed through a first diffusion hole in the curved seal to cool the nozzle if the rotatable curved seal is in a first position where higher heat is encountered. Cool air is directed through a second diffusion hole in the curved seal to cool the nozzle if the rotatable curved seal is in a first position where higher heat is encountered and if in a second position where relatively lower heat is encountered.

    LIGHT WEIGHT LOW BLOCKAGE SLIDER SEAL
    5.
    发明申请
    LIGHT WEIGHT LOW BLOCKAGE SLIDER SEAL 审中-公开

    公开(公告)号：US20200240280A1

    公开(公告)日：2020-07-30

    申请号：US16260650

    申请日：2019-01-29

    Applicant: United Technologies Corporation

    Inventor： Curtis C. Cowan ,  Paul W. Duesler ,  Michael R. Thomas ,  Michael Joseph Murphy

    IPC: F01D11/00 ,  F02C7/28

    Abstract: A slider seal assembly for a gas turbine engine, comprising a housing comprising an outer surface and an inner surface, and a recessed opening between the inner surface and the outer surface, wherein the inner surface of the housing includes a flat portion configured to match a receiver on an inner wall of a casing of the gas turbine engine; a seal plate received within the recessed opening and moveable relative to the housing; and a retaining ring configured to retain the seal plate adjacent the housing, the retaining ring includes a plurality of tabs configured to retain the seal plate adjacent the housing.

    GAS TURBINE ENGINE AND BLOCKER DOOR ASSEMBLY
    7.
    发明申请
    GAS TURBINE ENGINE AND BLOCKER DOOR ASSEMBLY 有权
    气体涡轮发动机和堵头门总成

    公开(公告)号：US20160208714A1

    公开(公告)日：2016-07-21

    申请号：US14600951

    申请日：2015-01-20

    Applicant: United Technologies Corporation

    Inventor： Jorge I. Farah ,  Donald W. Peters ,  Adam Covino ,  Curtis C. Cowan ,  James R. Harders ,  Nicholas W. Kantany

    IPC: F02C9/18

    CPC classification number: F02C9/18 ,  F01D17/105 ,  F01D17/141 ,  F01D17/143 ,  F02C7/14 ,  F02K3/075 ,  F02K3/077 ,  F02K3/10 ,  F05D2250/411 ,  F05D2260/213 ,  F05D2260/50 ,  Y02T50/675

    Abstract: A blocker door assembly which may be for a cooling system that may be applied to a gas turbine engine includes a plurality of blocker doors circumferentially spaced about an engine axis. Each blocker door is constructed and arranged to move in a circumferential direction to, at least in-part, control air flow through a passage in an adjacent fixture. A sync-ring is concentrically located about the engine axis, disposed in an annular first duct in direct communication with each passage, and engaged to each one of the plurality of blocker doors for simultaneous operation. The sync-ring is aero-dynamically shaped to reduce surrounding airflow resistance.

    Abstract translation: 可用于可应用于燃气涡轮发动机的冷却系统的阻塞门组件包括围绕发动机轴线周向隔开的多个阻挡门。 每个阻塞门被构造和布置成沿圆周方向移动至少部分地控制通过相邻固定装置中的通道的气流。 同步环围绕发动机轴线同心地定位，设置在与每个通道直接连通的环形第一管道中，并且与多个阻挡门中的每一个接合以进行同时操作。 同步环是航空动态的，以减少周围的气流阻力。

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