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    NOSECAP
    13.
    发明公开
    NOSECAP 审中-公开
    NASENSCHUTZ

    公开(公告)号：EP3063391A1

    公开(公告)日：2016-09-07

    申请号：EP14859281.9

    申请日：2014-10-15

    Applicant: United Technologies Corporation

    Inventor： KLING, Colin J. ,  BROWN, Charles W.

    IPC: F02C7/20 ,  F01D25/28

    CPC classification number: F02C7/04 ,  B29C45/00 ,  B64C11/14 ,  F05D2230/72 ,  F05D2250/73 ,  F05D2300/43 ,  F05D2300/433 ,  F05D2300/436

    Abstract: The present disclosure relates generally to a nosecap for a gas turbine engine. The nosecap may be injection molded in an embodiment. The nosecap may have bolt holes surrounded by bolt pockets that are asymmetric about a plane passing through a geometric center of the nosecap and passing through and dividing the bolt hole in an embodiment.

    Abstract translation: 本公开总体上涉及燃气涡轮发动机的喷嘴。 在一个实施方案中，可以注射成型。 螺栓孔可以具有螺栓孔，所述螺栓孔围绕穿过螺栓孔的几何中心的平面不对称，并且在一个实施例中通过并分隔螺栓孔。

    SPINNER AFT-EXTENDED FORWARD RETURN FLANGE
    15.
    发明公开
    SPINNER AFT-EXTENDED FORWARD RETURN FLANGE 审中-公开
    HINTENVERLÄNGERTERVORWÄRTS-RÜCKHOLFLANSCHEINES SCHLEUDERRADS

    公开(公告)号：EP2980385A1

    公开(公告)日：2016-02-03

    申请号：EP15179032.6

    申请日：2015-07-30

    Applicant: United Technologies Corporation

    Inventor： KLING, Colin J. ,  LUSSIER, Darin X.

    IPC: F02C7/04 ,  B64C11/14

    CPC classification number: F02C7/04 ,  B29C43/021 ,  B29C2043/026 ,  B29K2101/00 ,  B29L2031/7504 ,  B64C11/14 ,  F02C3/04 ,  F05D2220/32 ,  F05D2230/30 ,  F05D2240/20 ,  F05D2240/35 ,  F05D2300/43 ,  Y02T50/671

    Abstract: A spinner (15) for a fan assembly (11) of a gas turbine engine (10), a method of fabricating a spinner for a fan assembly (11) of a gas turbine engine (10), and a gas turbine engine (10) are disclosed. The fan section (11) may include a nosecap (25). The spinner (15) may include a forward end (17), an aft end (18), and a return flange (30) associated with the forward end (17). The return flange (30) may include a forward flange (34) extending forward towards the nosecap (25) and an aft flange (32) extending aft towards the aft end (18).

    Abstract translation: 一种用于燃气涡轮发动机（10）的风扇组件（11）的旋转器（15），制造用于燃气涡轮发动机（10）的风扇组件（11）的旋转器的方法，以及燃气涡轮发动机（10） ）。 风扇部分（11）可以包括诺塞（25）。 旋转器（15）可以包括前端（17），后端（18）和与前端（17）相关联的返回凸缘（30）。 返回凸缘（30）可以包括向前朝向顶点（25）向前延伸的前凸缘（34）和向后端部（18）向后延伸的后凸缘（32）。

    GAS TURBINE ENGINE COMPONENT WITH INTEGRALLY FORMED STIFFENERS
    17.
    发明公开
    GAS TURBINE ENGINE COMPONENT WITH INTEGRALLY FORMED STIFFENERS 审中-公开

    公开(公告)号：EP3511528A1

    公开(公告)日：2019-07-17

    申请号：EP19151453.8

    申请日：2019-01-11

    Applicant: United Technologies Corporation

    Inventor： KLING, Colin J.

    IPC: F01D21/04 ,  B29C70/22 ,  B29D99/00

    Abstract: A gas turbine engine component includes a tubular body section (66) including a plurality of fiber wraps encompassed within a matrix composition and one or more integrally-formed stiffeners (84) extending from an outer surface (86) of the body section and in a component circumferential direction around the body section. The stiffener includes one or more fiber wraps extending radially outwardly from the body section over a form and to the body section from the form.

    BLADE LOCK RETAINER AND CORRESPNDING FAN ASSEMBLY
    18.
    发明公开
    BLADE LOCK RETAINER AND CORRESPNDING FAN ASSEMBLY 审中-公开
    ZUGEHÖRIGEBLÄSERANORDNUNG的FIXIERVORRICHTUNGFÜRSCHAUFELHALTER

    公开(公告)号：EP3081758A1

    公开(公告)日：2016-10-19

    申请号：EP16164962.9

    申请日：2016-04-12

    Applicant: United Technologies Corporation

    Inventor： KLING, Colin J. ,  ROBERTSON, Thomas J. ,  ANDERSON, Carney R. ,  McPHAIL, James J.

    IPC: F01D5/30 ,  F01D5/32 ,  F02K7/06

    CPC classification number: F01D5/326 ,  F01D5/282 ,  F01D5/3015 ,  F01D5/3076 ,  F02K7/06 ,  F05D2220/36 ,  F05D2230/54 ,  F05D2300/121 ,  F05D2300/133 ,  F05D2300/173 ,  F05D2300/174 ,  F05D2300/175 ,  F05D2300/603 ,  Y02T50/672

    Abstract: The present disclosure provides devices related to aircraft engine fan assemblies (300) and blade lock retainers (210). In various embodiments, a blade lock retainer (210) is formed from sheet metal and comprises an annular ring portion (211), an outer retainer tab portion (212), and an inner tab portion (213). In various embodiments, the outer retainer tab portion (212) is disposed on an outer circumference of the annular ring portion (211), oriented substantially perpendicular to the annular ring portion (211), and extends in an aft direction from the annular ring portion (211). In various embodiments, the inner retainer tab portion (213) is disposed on an inner circumference of the annular ring portion (211) and radially aligned with the outer retainer tab portion (212), oriented substantially perpendicular to the annular ring portion (211), and extends in a forward direction from the annular ring portion (211).

    Abstract translation: 本公开提供了与飞机发动机风扇组件（300）和叶片锁定保持器（210）相关的装置。 在各种实施例中，刀片锁定保持器（210）由金属板形成并且包括环形环部分（211），外部保持器突出部分（212）和内部突出部分（213）。 在各种实施例中，外保持器突片部分（212）设置在环形环部分（211）的外圆周上，其基本上垂直于环形环部分（211）定向，并且在后方向上从环形环部分 （211）。 在各种实施例中，内部保持器突出部分（213）设置在环形环部分（211）的内圆周上，并且与外部保持器突出部分（212）径向对准，其基本上垂直于环形环部分（211）定向， 并且从环形环部分（211）沿向前方向延伸。

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