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    Gas turbine engine ramped rapid response clearance control system
    31.
    发明授权
    Gas turbine engine ramped rapid response clearance control system 有权

    公开(公告)号：US10316685B2

    公开(公告)日：2019-06-11

    申请号：US15024686

    申请日：2014-08-01

    Applicant: United Technologies Corporation

    Inventor： Timothy M. Davis ,  Brian Duguay

    IPC: F01D11/22

    Abstract: An active clearance control system of a gas turbine engine includes a multiple of blade outer air seal assemblies and a multiple of rotary ramps. Each of the multiple of rotary ramps is associated with one of the multiple of blade outer air seal assemblies. A method of active blade tip clearance control for a gas turbine engine is provided. The method includes rotating a multiple of rotary ramps to control a continuously adjustable radial position for each of a respective multiple of blade outer air seal assemblies.

    GAS TURBINE ENGINE RAPID RESPONSE CLEARANCE CONTROL SYSTEM
    35.
    发明申请
    GAS TURBINE ENGINE RAPID RESPONSE CLEARANCE CONTROL SYSTEM 审中-公开
    气体涡轮发动机快速响应间隙控制系统

    公开(公告)号：US20160356170A1

    公开(公告)日：2016-12-08

    申请号：US14913785

    申请日：2014-07-23

    Applicant: UNITED TECHNOLOGIES CORPORATION

    Inventor： Timothy M. Davis ,  Brian Duguay

    IPC: F01D11/22 ,  F04D29/16

    CPC classification number: F01D11/22 ,  F01D11/08 ,  F01D11/14 ,  F04D29/164 ,  F05D2220/32 ,  F05D2260/50 ,  F05D2270/60

    Abstract: An active clearance control system of a gas turbine engine includes a multiple of blade outer air seal assemblies and a sync ring with a multiple of graduation sets. Each of the graduation sets is associated with one of the multiple of blade outer air seal assemblies. An active clearance control system of a gas turbine engine includes a sync ring with a multiple of graduation sets. Each of the graduation sets includes a multiple of graduations to define an associated radial position for each of a respective multiple of blade outer air seal assemblies.

    Abstract translation: 燃气涡轮发动机的主动间隙控制系统包括多个叶片外部空气密封组件和具有多个分级组的同步环。 每个分级组与多个叶片外部空气密封组件中的一个相关联。 燃气涡轮发动机的主动间隙控制系统包括具有多个分级组的同步环。 每个分级组包括多个刻度以确定相应的多个叶片外部空气密封组件中的每一个的相关的径向位置。

    TURBINE ENGINE TIP CLEARANCE CONTROL SYSTEM WITH LATER TRANSLATABLE SLIDE BLOCK
    36.
    发明申请
    TURBINE ENGINE TIP CLEARANCE CONTROL SYSTEM WITH LATER TRANSLATABLE SLIDE BLOCK 有权
    涡轮发动机提升间隙控制系统，具有可翻转的滑块

    公开(公告)号：US20160356168A1

    公开(公告)日：2016-12-08

    申请号：US14731155

    申请日：2015-06-04

    Applicant: United Technologies Corporation

    Inventor： Brian Duguay ,  Timothy M. Davis

    IPC: F01D11/14 ,  F01D25/24

    CPC classification number: F01D11/14 ,  F01D11/22 ,  F01D25/24

    Abstract: An assembly is provided for a turbine engine with an axial centerline. This turbine engine assembly may include a blade outer air seal segment, a linkage and an actuation device. The linkage may include a shaft and a head, where the shaft is connected to the blade outer air seal segment and extends radially outward to the head. The actuation device may include a sloped slide block located radially within and engaged with the head. The actuation device may be configured to laterally translate the sloped slide block and thereby radially move the blade outer air seal segment.

    Abstract translation: 为具有轴向中心线的涡轮发动机提供组件。 该涡轮发动机组件可以包括叶片外部空气密封段，连杆机构和致动装置。 连杆可以包括轴和头部，其中轴连接到叶片外部空气密封部分并且径向向外延伸到头部。 致动装置可以包括位于径向位于头部并与头部接合的倾斜滑块。 致动装置可以构造成横向平移倾斜的滑块，从而径向移动叶片外部空气密封段。

    ACTUATOR FOR GAS TURBINE ENGINE BLADE OUTER AIR SEAL
    37.
    发明申请
    ACTUATOR FOR GAS TURBINE ENGINE BLADE OUTER AIR SEAL 审中-公开
    气动涡轮发动机叶片外空气密封件执行器

    公开(公告)号：US20160017743A1

    公开(公告)日：2016-01-21

    申请号：US14773861

    申请日：2014-02-18

    Applicant: UNITED TECHNOLOGIES CORPORATION

    Inventor： Brian Duguay

    IPC: F01D11/20

    CPC classification number: F01D11/20 ,  F01D11/08 ,  F01D11/22 ,  F05D2220/32 ,  F05D2240/11 ,  F05D2240/12 ,  F05D2240/30 ,  F05D2240/55 ,  F05D2260/57

    Abstract: A blade outer air seal (BOAS) actuator assembly, according to an exemplary aspect of the present disclosure includes, among other things, an actuator member; and a retractor configured to move with the actuator member to move a BOAS segment from a first position to a second position that is radially outside the first position, the BOAS segment seated against a support structure when in the first position and spaced from the support structure when in the second position.

    Abstract translation: 根据本公开的示例性方面的叶片外部空气密封（BOAS）致动器组件尤其包括致动器构件; 以及牵开器，其构造成与所述致动器构件一起移动以将BOAS段从第一位置移动到径向位于所述第一位置的第二位置，所述BOAS段在处于所述第一位置时抵靠支撑结构抵靠并与所述支撑结构间隔开 当在第二个位置。

    BLADE OUTER AIR SEAL
    39.
    发明申请
    BLADE OUTER AIR SEAL 审中-公开
    叶片外密封

    公开(公告)号：US20140127006A1

    公开(公告)日：2014-05-08

    申请号：US13668398

    申请日：2012-11-05

    Applicant: UNITED TECHNOLOGIES CORPORATION

    Inventor： Dmitriy A. Romanov ,  Brian Duguay ,  Russell E. Keene

    IPC: F01D11/08

    CPC classification number: F01D25/246 ,  F01D9/04 ,  F01D11/08 ,  F05D2240/11 ,  F05D2260/201 ,  F05D2260/221 ,  Y02T50/676 ,  Y02T50/6765

    Abstract: A blade outer air seal for a gas turbine engine includes a first side surface, a second side surface, and a wall. The wall extends between the first side surface and the second side surface and has one or more holes formed therein. The holes are spaced from the first side surface and/or the second side surface and have areas between about 0.005% and 0.450% of a surface area of the blade outer air seal.

    Abstract translation: 用于燃气涡轮发动机的叶片外部空气密封件包括第一侧表面，第二侧表面和壁。 该壁在第一侧表面和第二侧表面之间延伸并且在其中形成有一个或多个孔。 孔与第一侧表面和/或第二侧表面间隔开并且具有在叶片外部空气密封件的表面积的约0.005％至0.450％之间的面积。

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