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    STATIONARY NON-ROTATING BRUSH SEALS
    2.
    发明申请
    STATIONARY NON-ROTATING BRUSH SEALS 有权
    静止不旋转的刷子密封

    公开(公告)号：US20160032750A1

    公开(公告)日：2016-02-04

    申请号：US14882244

    申请日：2015-10-13

    Applicant: UNITED TECHNOLOGIES CORPORATION

    Inventor： Gary A. Schirtzinger ,  George J. Kramer

    IPC: F01D11/00

    CPC classification number: F01D11/005 ,  F01D11/001 ,  F01D11/08 ,  F05D2220/32 ,  F05D2240/56 ,  F16J15/3288

    Abstract: The present disclosure relates to an aircraft brush seal comprising a first brush seal member and a second brush seal member comprising a channel that receives a plurality of interwoven brush fibers. The interwoven brush fibers may be coupled to the first brush seal member and/or may extend into the second brush seal member. The interwoven brush fibers may not couple to the second brush seal member and/or may form an air seal. The air seal may be formed between a first air compartment and a second air compartment.

    Abstract translation: 本公开涉及一种包括第一刷密封构件和第二刷密封构件的飞行器刷密封件，该第二刷密封构件包括容纳多个交织毛刷纤维的通道。 交织毛刷纤维可以联接到第一刷密封构件和/或可以延伸到第二刷密封构件中。 交织毛刷纤维可能不耦合到第二刷密封件和/或可形成空气密封。 空气密封件可以形成在第一空气室和第二空气室之间。

    SEAL ASSEMBLY FOR LINERS OF EXHAUST NOZZLE
    5.
    发明申请
    SEAL ASSEMBLY FOR LINERS OF EXHAUST NOZZLE 有权
    用于排气喷嘴的密封组件

    公开(公告)号：US20140102108A1

    公开(公告)日：2014-04-17

    申请号：US13653590

    申请日：2012-10-17

    Applicant: UNITED TECHNOLOGIES CORPORATION

    Inventor： George J. Kramer

    IPC: F02K1/82

    CPC classification number: F02K1/82 ,  F02C7/28

    Abstract: An exhaust nozzle liner assembly of a gas turbine engine includes a first liner, a second liner spaced from the first liner by a gap, a seal assembly located at least partially within the gap to provide a continuous surface defined by the first liner, the seal assembly and the second liner, and a seal retainer to retain the seal assembly

    Abstract translation: 燃气涡轮发动机的排气喷嘴衬套组件包括第一衬套，通过间隙与第一衬套间隔开的第二衬套，至少部分地位于间隙内的密封组件，以提供由第一衬套限定的连续表面，密封件 组件和第二衬垫，以及用于保持密封组件的密封保持器

    LINER HANGER WITH SPHERICAL WASHERS
    6.
    发明申请
    LINER HANGER WITH SPHERICAL WASHERS 审中-公开

    公开(公告)号：US20160146055A1

    公开(公告)日：2016-05-26

    申请号：US15014131

    申请日：2016-02-03

    Applicant: United Technologies Corporation

    Inventor： George J. Kramer ,  Jeffrey S. Smith

    IPC: F01D25/30 ,  F16M13/00

    CPC classification number: F01D25/30 ,  F04B39/0005 ,  F05D2220/32 ,  F05D2230/60 ,  F05D2260/30 ,  F16M13/00

    Abstract: A liner assembly for a gas turbine engine includes a liner defining an inner surface exposed to exhaust gases and a duct spaced radially outward of the liner. A hanger assembly supports the liner relative to the duct. The hanger assembly includes a body segment attached to the liner and first and second washers defining a gap therebetween that receives a portion of the body segment. The gap between the washers and the body segment provides for relative movement caused by differences in thermal growth within the liner. An attachment member extending between the body section and the duct includes spherical ends that are seated on the first and second washers to accommodate misalignments during assembly.

    Spherical Collet for Mounting a Gas turbine Engine Liner
    7.
    发明申请
    Spherical Collet for Mounting a Gas turbine Engine Liner 有权
    用于安装燃气轮机发动机衬套的球形夹头

    公开(公告)号：US20140157782A1

    公开(公告)日：2014-06-12

    申请号：US13706404

    申请日：2012-12-06

    Applicant: UNITED TECHNOLOGIES CORPORATION

    Inventor： George J. Kramer

    IPC: F23R3/60

    CPC classification number: F23R3/60 ,  F02K1/82 ,  F23R2900/00005 ,  F23R2900/00017 ,  Y10T29/4932

    Abstract: A liner and attachment structure has an exhaust liner for use in a gas turbine engine. At least one hanger has feet secured to the liner. The hanger has an aperture extending at a central web. A flanged washer is received within the opening in the hanger. The flanged washer allows adjustment relative to the hanger. The flanged washer has a spherical recess. A collet has a plurality of part-spherical fingers separated by slots, and are received in the spherical recess of the flanged washer. A member extends into the collet to hold the part-spherical fingers radially outwardly. The member is also utilized to secure static structure, and to secure the liner to the static structure.

    Abstract translation: 衬套和附接结构具有用于燃气涡轮发动机的排气衬套。 至少一个衣架有脚固定到衬垫上。 衣架具有在中央网处延伸的孔。 凸缘垫圈被接纳在衣架的开口内。 带法兰的垫圈允许相对于衣架进行调节。 凸缘垫圈有一个球形凹槽。 夹头具有多个由槽分开的部分球形指状物，并被容纳在带凸缘的垫圈的球形凹部中。 一个构件延伸到夹头中以将部分球形的手指径向向外保持。 该构件还用于固定静态结构，并将衬垫固定到静态结构。

    Gas turbine engine mid turbine frame bearing support
    8.
    发明授权
    Gas turbine engine mid turbine frame bearing support 有权

    公开(公告)号：US10753279B2

    公开(公告)日：2020-08-25

    申请号：US14818392

    申请日：2015-08-05

    Applicant: United Technologies Corporation

    Inventor： Robert Russell Mayer ,  George J. Kramer ,  Paul W. Palmer

    IPC: F02C1/00 ,  F02C7/06 ,  F02C3/045 ,  F02C7/36 ,  F02C7/20 ,  F01D25/24 ,  F01D25/16 ,  F23R3/00 ,  F23R3/60

    Abstract: A gas turbine engine includes a fan and a compressor section that is fluidly connected to the fan. The compressor includes a high pressure compressor and a low pressure compressor. A combustor is fluidly connected to the compressor section. A turbine section is fluidly connected to the combustor. The turbine section includes a high pressure turbine coupled to the high pressure compressor via a first shaft. A low pressure turbine is coupled to the low pressure compressor via a second shaft. A geared architecture interconnects between the second shaft and the fan. The gas turbine engine is a high bypass geared aircraft engine having a bypass ratio of greater than six (6). The low pressure turbine has a pressure ratio that is greater than 5, and the geared architecture includes a gear reduction ratio of greater than 2.5:1.

    Seal assembly for liners of exhaust nozzle
    9.
    发明授权
    Seal assembly for liners of exhaust nozzle 有权

    公开(公告)号：US09771895B2

    公开(公告)日：2017-09-26

    申请号：US13653590

    申请日：2012-10-17

    Applicant: UNITED TECHNOLOGIES CORPORATION

    Inventor： George J. Kramer

    IPC: F02C7/28 ,  F02K1/82

    CPC classification number: F02K1/82 ,  F02C7/28

    Abstract: An exhaust nozzle liner assembly of a gas turbine engine includes a first liner, a second liner spaced from the first liner by a gap, a seal assembly located at least partially within the gap to provide a continuous surface defined by the first liner, the seal assembly and the second liner, and a seal retainer to retain the seal assembly.

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