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    Gas turbine engine, and holding method of member to engine casing structure
    1.
    发明专利
    Gas turbine engine, and holding method of member to engine casing structure 有权
    气体涡轮发动机，以及发动机结构件的保持方法

    公开(公告)号：JP2013124667A

    公开(公告)日：2013-06-24

    申请号：JP2012272057

    申请日：2012-12-13

    Applicant: United Technologies Corp ,  ユナイテッド テクノロジーズ コーポレイションUnited Technologies Corporation

    Inventor： CHUONG CONWAY ,  WERNER KURT P ,  DUELM SHELTON O

    IPC: F01D9/04 ,  F01D25/00 ,  F01D25/28 ,  F02C7/00 ,  F02C7/20

    CPC classification number: F01D25/243 ,  F01D9/042 ,  F05D2230/64

    Abstract: PROBLEM TO BE SOLVED: To hold a vane (40) in an engine casing structure (49) so that it appropriately functions during the operation of a gas turbine engine.SOLUTION: The gas turbine engine includes the engine casing structure (49) and a holding block assembly (58). The engine casing structure (49) includes a pocket (60) housing the holding block assembly (58). The holding block assembly (58) includes a stopper block (62), and a pin (64) holding the stopper block (62) in the pocket (60). The stopper block (62) is loosely mounted with respect to the pin (64).

    Abstract translation: 要解决的问题：将发动机壳体结构（49）中的叶片（40）保持在燃气涡轮发动机的操作期间适当地起作用。 解决方案：燃气涡轮发动机包括发动机壳体结构（49）和保持块组件（58）。 发动机壳体结构（49）包括容纳保持块组件（58）的凹部（60）。 保持块组件（58）包括止动块（62）和将止动块（62）保持在口袋（60）中的销（64）。 止动块（62）相对于销（64）松动地安装。 版权所有（C）2013，JPO＆INPIT

    COMPOSITE AIRFOIL WITH INTEGRAL PLATFORM
    2.
    发明申请
    COMPOSITE AIRFOIL WITH INTEGRAL PLATFORM 审中-公开
    具有整体平台的复合式翼型

    公开(公告)号：WO2014046764A3

    公开(公告)日：2014-05-22

    申请号：PCT/US2013049070

    申请日：2013-07-02

    Applicant: UNITED TECHNOLOGIES CORP

    Inventor： DUELM SHELTON O ,  PREVOST ERICA L ,  CHUONG CONWAY

    IPC: B64C1/06 ,  B64F5/00

    CPC classification number: F01D5/147 ,  B29C70/30 ,  B29D99/0025 ,  B29L2031/082 ,  F01D5/14 ,  F01D5/28 ,  F01D5/282 ,  Y02T50/433 ,  Y10T29/49332

    Abstract: A method of forming an airfoil with an integrated platform includes: a) providing an airfoil core; b) wrapping a first overwrap ply around the airfoil core; c) darting a first end of the first overwrap ply to allow the overwrap ply to extend perpendicular to the airfoil core to form a first platform; d) filling the darted parts filler plies; e) wrapping a second overwrap ply around the first overwrap ply; f) darting a first end of the second overwrap ply to allow the second overwrap ply to extend adjacent to the first overwrap ply to form the first platform; g) filling the darted parts of the second overwrap ply with one or more filler plies; and h) placing a cap ply in the shape of the platform adjacent to at least one of the first and second overwrap plies. An airfoil with an integrated platform is also disclosed.

    Abstract translation: 一种形成具有集成平台的翼型的方法包括：a）提供翼型芯; b）围绕翼型芯包裹第一外包装层; c）将第一外包裹层的第一端戳穿以允许外包裹层垂直于翼型芯延伸以形成第一平台; d）填充飞镖部件填充层; e）将第二外包装层包裹在第一外包装层上; f）将第二外包装层的第一端分开以允许第二外包装层与第一外包装层相邻地延伸以形成第一平台; g）用一个或多个填充层填充第二外包装层的带刺部分; 以及h）将帽层放置成邻近第一外包装层和第二外包装层中的至少一个的平台形状。 还公开了具有集成平台的翼型。

    SEALS FOR A CIRCUMFERENTIAL STOP RING IN A TURBINE EXHAUST CASE
    4.
    发明申请
    SEALS FOR A CIRCUMFERENTIAL STOP RING IN A TURBINE EXHAUST CASE 审中-公开
    汽轮机排气管中的环形密封圈密封

    公开(公告)号：WO2014143317A3

    公开(公告)日：2014-12-24

    申请号：PCT/US2013076758

    申请日：2013-12-19

    Applicant: UNITED TECHNOLOGIES CORP

    Inventor： BUDNICK MATTHEW ,  CHUONG CONWAY ,  SCOTT JONATHAN A

    IPC: F01D11/00 ,  F01D9/04 ,  F02C7/28

    CPC classification number: F01D11/005 ,  F01D25/162 ,  F01D25/246

    Abstract: A turbine seal system comprises an annular structural frame, a circumferential ring, a fairing and a seal. The circumferential ring is joined to the annular structural frame. The fairing is disposed within the annular structural frame and is engaged with the circumferential ring to limit circumferential rotation of the fairing with respect to the annular structural frame. The seal extends between the fairing and the circumferential ring. In one embodiment, the structural component comprises a ring-strut-ring turbine exhaust case.

    Abstract translation: 涡轮机密封系统包括环形结构框架，周向环，整流罩和密封件。 周向环连接到环形结构框架。 整流装置设置在环形结构框架内并且与周向环接合以限制整流装置相对于环形结构框架的周向旋转。 密封件在整流罩和圆周环之间延伸。 在一个实施例中，结构部件包括环形支撑环涡轮排气箱。

    CIRCUMFERENTIALLY RETAINED FAIRING
    5.
    发明申请
    CIRCUMFERENTIALLY RETAINED FAIRING 审中-公开
    圆形保留公寓

    公开(公告)号：WO2014133647A2

    公开(公告)日：2014-09-04

    申请号：PCT/US2013075368

    申请日：2013-12-16

    Applicant: UNITED TECHNOLOGIES CORP

    Inventor： CHUONG CONWAY ,  SCOTT JONATHAN A ,  BUDNICK MATTHEW

    CPC classification number: F02C7/20 ,  F01D25/162 ,  F01D25/28 ,  F05D2250/42

    Abstract: An assembly for a gas turbine engine includes a frame, a mount, and a fairing. The mount is attached to the frame and the fairing is connected to the mount. The fairing and mount have mating anti-deflection features that engage to prevent circumferential movement of the fairing relative to the frame.

    Abstract translation: 用于燃气涡轮发动机的组件包括框架，底座和整流罩。 安装架连接到框架，整流罩连接到安装座。 整流罩和安装座具有接合防偏转特征，其接合以防止整流罩相对于框架的圆周运动。

    COMPONENT RETENTION WITH PROBE
    7.
    发明申请
    COMPONENT RETENTION WITH PROBE 审中-公开
    带探针的元件保持

    公开(公告)号：WO2014133649A2

    公开(公告)日：2014-09-04

    申请号：PCT/US2013075446

    申请日：2013-12-16

    Applicant: UNITED TECHNOLOGIES CORP

    Inventor： CHUONG CONWAY ,  BUDNICK MATTHEW

    CPC classification number: F01D9/065 ,  F01D9/041 ,  F01D17/08 ,  F01D21/003 ,  F01D25/162 ,  F01D25/28 ,  F02C7/20 ,  F05D2230/642

    Abstract: A gas turbine engine includes a casing, a probe, and a fairing. The probe extends through the casing and the fairing is disposed within the casing. The fairing is engaged by the probe to prevent circumferential movement of the fairing relative to the casing.

    Abstract translation: 燃气涡轮发动机包括壳体，探针和整流罩。 探头延伸穿过壳体并且整流罩布置在壳体内。 整流罩与探头接合以防止整流罩相对于壳体的周向运动。

    CORRUGATED MID-TURBINE FRAME THERMAL RADIATION SHIELD
    9.
    发明申请
    CORRUGATED MID-TURBINE FRAME THERMAL RADIATION SHIELD 审中-公开
    波纹中涡轮机架热辐射防护罩

    公开(公告)号：WO2014058483A2

    公开(公告)日：2014-04-17

    申请号：PCT/US2013046780

    申请日：2013-06-20

    Applicant: UNITED TECHNOLOGIES CORP

    Inventor： ZIMMERMANN ALISHA ,  LIEBEL CHRISTINA S ,  CHUONG CONWAY

    IPC: F01D25/24 ,  F01D25/00 ,  F02C7/00

    CPC classification number: F01D25/28 ,  F01D9/065 ,  F01D25/08 ,  F01D25/145 ,  F01D25/16 ,  F01D25/24 ,  F02C7/20 ,  F02K3/04 ,  F05D2260/231 ,  F28F2265/10 ,  Y02T50/675

    Abstract: A corrugated shield comprises a mounting base and a corrugated ring section. The mounting base is disposed at an aft end of the ring section for securing the shield ring section within a generally annular cavity. The generally annular cavity is defined at least in part by a hot fluid flow path boundary wall, and a radially adjacent and spaced apart cold fluid flow path boundary wall. The corrugated ring section is configured to substantially block a line of sight between the hot fluid flow path boundary wall and the cold fluid flow path boundary wall.

    Abstract translation: 波纹状防护罩包括安装底座和波纹环部分。 安装基座设置在环形部分的后端，用于将屏蔽环部分固定在大致环形的空腔内。 大致环形腔至少部分地由热流体流动路径边界壁和径向相邻且间隔开的冷流体流动路径边界壁限定。 波纹环部分构造成基本阻挡热流体流动路径边界壁与冷流体流动路径边界壁之间的视线。

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