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    MANUFACTURE OF HOLLOW AEROFOIL
    2.
    发明申请
    MANUFACTURE OF HOLLOW AEROFOIL 有权
    HOLLOW AEROFOIL制造

    公开(公告)号：US20150252675A1

    公开(公告)日：2015-09-10

    申请号：US14473425

    申请日：2014-08-29

    Applicant: ROLLS-ROYCE PLC

    Inventor： Steven Aleksy RADOMSKI

    IPC: F01D5/18 ,  B23K20/00 ,  B23K20/16 ,  F01D5/14 ,  B23K20/02

    CPC classification number: F01D5/18 ,  B23K13/01 ,  B23K20/002 ,  B23K20/02 ,  B23K20/16 ,  B23K2101/001 ,  B23P15/04 ,  F01D5/147 ,  F05D2220/32 ,  F05D2230/10 ,  F05D2230/236 ,  F05D2230/51 ,  F05D2230/60 ,  F05D2230/90 ,  Y02T50/672 ,  Y02T50/673 ,  Y02T50/676 ,  Y10T29/49337

    Abstract: A method of manufacturing a hollow aerofoil component (100) for a gas turbine engine (10) comprises using a capping panel (200) to cover a pocket (310) in a pocketed aerofoil body (300). During manufacture, a mandrel (400) is provided to support the capping panel (200) in the correct position. This ensures that the outer surface of the capping panel (200) is located as accurately as possible. This means that the capping panel (200) can be made to be as thin as possible, which in turn reduces weight and material wastage. Remotely detectable elements (700) may be provided to the mandrel (400) to enable the location of the pocket (310) to be accurately determined from outside the aerofoil (100).

    Abstract translation: 一种制造用于燃气涡轮发动机（10）的空心机翼部件（100）的方法包括使用盖板（200）来覆盖袋装机翼（300）中的口袋（310）。 在制造期间，提供心轴（400）以将盖板（200）支撑在正确的位置。 这确保了封盖板（200）的外表面尽可能准确地定位。 这意味着封盖板（200）可以制成尽可能薄，这反过来减轻了重量和材料浪费。 可以将远程可检测元件（700）提供到心轴（400），以使得能够从机翼（100）的外部精确地确定口袋（310）的位置。

    MANUFACTURE OF HOLLOW AEROFOIL
    3.
    发明申请
    MANUFACTURE OF HOLLOW AEROFOIL 有权
    HOLLOW AEROFOIL制造

    公开(公告)号：US20140271227A1

    公开(公告)日：2014-09-18

    申请号：US14158014

    申请日：2014-01-17

    Applicant: ROLLS-ROYCE PLC

    Inventor： Steven Aleksy RADOMSKI ,  Clive GRAFTON-REED ,  Ian CROWSTON ,  Andrea Lelio MAURIZIO

    IPC: F01D5/18

    CPC classification number: F01D5/18 ,  B23P15/04 ,  F01D5/147 ,  Y02T50/672 ,  Y10T29/49339

    Abstract: A method of manufacturing a hollow aerofoil component for a gas turbine engine includes using a capping panel to cover a pocket in a pocketed aerofoil body. During manufacture, the outer surface of the capping panel is located relative to the pocketed aerofoil body. This ensures that the outer surface of the capping panel is located as accurately as possible. This means that the capping panel can be made to be as thin as possible, which in turn reduces weight and material wastage. Once the capping panel has been located in position, it may be welded to the aerofoil body in order to produce the hollow aerofoil component.

    Abstract translation: 一种用于燃气涡轮发动机的空心翼型零件的制造方法包括使用盖板覆盖袋装机翼中的口袋。 在制造过程中，封盖板的外表面相对于袋装机翼本体定位。 这确保了封盖板的外表面尽可能准确地定位。 这意味着封盖板可以制成尽可能薄，这又减轻了重量和材料浪费。 一旦盖板已经定位就位，它可以被焊接到机翼主体上，以便产生中空翼型部件。

    MANUFACTURE OF FILLED AEROFOIL
    4.
    发明申请
    MANUFACTURE OF FILLED AEROFOIL 有权
    填充的AEROFOIL的制造

    公开(公告)号：US20150125308A1

    公开(公告)日：2015-05-07

    申请号：US14474944

    申请日：2014-09-02

    Applicant: ROLLS-ROYCE PLC

    Inventor： Steven Aleksy RADOMSKI

    IPC: B23P15/04 ,  F01D5/14

    CPC classification number: B23P15/04 ,  F01D5/147 ,  F01D5/18 ,  F05D2230/232 ,  F05D2230/60 ,  Y02T50/672 ,  Y02T50/673 ,  Y02T50/676 ,  Y10T29/49336

    Abstract: A method of manufacturing a filled aerofoil component (100) for a gas turbine engine (10) comprises using a capping panel (200) to cover a pocket (310) in a pocketed aerofoil body (300). During manufacture, a pre-formed filler insert (400) is provided to support the capping panel (200) in the correct position. This ensures that the outer surface of the capping panel (200) is located as accurately as possible. This means that the capping panel (200) can be made to be as thin as possible, which in turn reduces weight and material wastage. The pre-formed filler insert (400) provides a lightweight core for the finished aerofoil component in use.

    Abstract translation: 制造用于燃气涡轮发动机（10）的填充的机翼部件（100）的方法包括使用盖板（200）来覆盖袋装机翼（300）中的口袋（310）。 在制造期间，提供预成型的填料插入件（400）以将盖板（200）支撑在正确的位置。 这确保了封盖板（200）的外表面尽可能准确地定位。 这意味着封盖板（200）可以制成尽可能薄，这反过来减轻了重量和材料浪费。 预成形的填料插入件（400）为使用中的成品机翼部件提供了轻质的芯。

    FAN CASING ARRANGEMENT FOR A GAS TURBINE ENGINE AND RELATED METHOD
    5.
    发明申请
    FAN CASING ARRANGEMENT FOR A GAS TURBINE ENGINE AND RELATED METHOD 有权
    一种气体涡轮发动机风扇装置及相关方法

    公开(公告)号：US20150104306A1

    公开(公告)日：2015-04-16

    申请号：US14505956

    申请日：2014-10-03

    Applicant: ROLLS-ROYCE PLC

    Inventor： Steven Aleksy RADOMSKI ,  Simon READ

    IPC: F04D29/64 ,  F04D19/00 ,  F04D29/02

    CPC classification number: F01D25/24 ,  F01D11/122 ,  F01D21/045 ,  F02C7/04 ,  F04D19/002 ,  F04D29/023 ,  F05D2220/36 ,  F05D2250/25 ,  F05D2300/522 ,  F05D2300/615 ,  Y10T29/49245

    Abstract: A fan casing arrangement for a gas turbine engine having a propulsive fan, the arrangement having a fan case and a fan track liner and being configured to circumscribe the fan, wherein the fan track liner is provided around the inside of fan case so as to adopt a radial position between the fan and the fan case. The fan track liner includes an elongate member which is helically-wound against the inside of the fan case in a plurality of turns. A method of installing a fan track liner in a fan casing arrangement for a gas turbine engine having a propulsive fan, the method involving: providing a fan case to circumscribe the fan, providing a flexible and elongate liner member, and helically winding the liner member against the inside of the fan case in a plurality of turns to define at least part of the fan track liner.

    Abstract translation: 一种用于具有推进风扇的燃气涡轮发动机的风扇壳体装置，该装置具有风扇壳体和风扇轨道衬套，并且构造成围绕风扇，其中，风扇履带衬套围绕风扇壳体的内部设置，以便采用 风扇和风扇外壳之间的径向位置。 风扇履带板包括细长构件，其以多个匝螺旋缠绕在风扇壳体的内部。 一种在具有推进风扇的燃气涡轮发动机的风扇壳体装置中安装风扇轨道衬套的方法，所述方法包括：提供风扇壳体以包围风扇，提供柔性和细长的衬垫构件，以及螺旋地卷绕衬套构件 以多个匝相对于风扇壳体的内部限定至少一部分风扇轨道衬套。

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