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    MISCHVORRICHTUNG UND TURBOFANTRIEBWERK MIT EINER DERARTIGEN MISCHVORRICHTUNG
    1.
    发明申请
    MISCHVORRICHTUNG UND TURBOFANTRIEBWERK MIT EINER DERARTIGEN MISCHVORRICHTUNG 有权
    麻醉药物TURBOFANTRIEBWERK MIT EINER DERARTIGEN MISCHVORRICHTUNG

    公开(公告)号：US20140298772A1

    公开(公告)日：2014-10-09

    申请号：US14244050

    申请日：2014-04-03

    Applicant: MTU Aero Engines AG

    Inventor： Hermann Klingels ,  Stephan Klaen ,  Christian Scherer ,  Uwe Vogel

    IPC: F02K3/075

    CPC classification number: F02K3/075 ,  F02K1/06 ,  F02K1/386 ,  F02K1/46 ,  F02K1/48 ,  F05D2250/61

    Abstract: The invention relates to a mixing device and a turbofan engine having such a mixing device 30 for mixing a first gas flow 40 with a second gas flow 50 in a turbofan engine 20, having an actuating device 95 and walls 60, which bound a channel 65 for the first gas flow 40 and a channel 70 lying radially outside for the second gas flow 50, the actuating device 95 comprising a coupling element 110 that is coupled to the walls (60), the actuating device 95 being designed to pivot the walls 60 between a first position and a second position disposed radially outside relative to the first position, the actuating device 95 comprising an adjusting ring 105 that can be rotated between a first rotating position and a second rotating position in the peripheral direction and that is joined to the coupling element 110.

    Abstract translation: 本发明涉及一种混合装置和涡轮风扇发动机，其具有这样的混合装置30，用于将第一气流40与涡扇发动机20中的第二气流50混合，具有致动装置95和壁60，其结合通道65 对于第一气流40和位于第二气流50的径向外侧的通道70，致动装置95包括联接到壁（60）的联接元件110，致动装置95被设计成枢转壁60 在第一位置和第二位置之间，相对于第一位置径向设置在外侧，致动装置95包括调节环105，调节环105能够在周向方向上在第一旋转位置和第二旋转位置之间旋转，并且连接到 耦合元件110。

    Seal support of titanium aluminide for a turbomachine
    2.
    发明授权
    Seal support of titanium aluminide for a turbomachine 有权

    公开(公告)号：US10287989B2

    公开(公告)日：2019-05-14

    申请号：US14166167

    申请日：2014-01-28

    Applicant: MTU Aero Engines AG

    Inventor： Frank Stiehler ,  Stephan Klaen ,  Stefan Busam ,  Bernhard Theis

    IPC: F02C7/28 ,  F01D11/00

    Abstract: Disclosed is a turbomachine having an annular flow duct and a housing structure surrounding the flow duct and a multiplicity of guide vanes and rotor blades which are arranged in the flow duct. The rotor blades are rotatably accommodated in the housing structure whereas the guide vanes are fixed in the housing structure, a plurality of guide vanes forming an annular guide vane ring. The housing structure has a seal in the region of the radially inner flow duct boundary in order to prevent hot gas escaping from the flow duct, which seal is arranged on guide vane roots of the guide vanes of the guide vane ring via a seal support and forms a seal against a rotatable seal surface, the seal support being formed from an intermetallic material, in particular a TiAl material.

    Restraint Mechanism for Rotor Blades of a Turbo Engine, an Assembly Method and a Turbo Engine
    4.
    发明申请
    Restraint Mechanism for Rotor Blades of a Turbo Engine, an Assembly Method and a Turbo Engine 审中-公开
    涡轮发动机转子叶片的限制机构，装配方法和涡轮发动机

    公开(公告)号：US20140044550A1

    公开(公告)日：2014-02-13

    申请号：US13962319

    申请日：2013-08-08

    Applicant: MTU Aero Engines AG

    Inventor： Felix KERN ,  Frank Stiehler ,  Stephan Klaen

    IPC: F01D5/30

    CPC classification number: F01D5/3038 ,  F01D5/30 ,  F01D5/32 ,  Y10T29/49321

    Abstract: A restraint mechanism for rotor blades of a turbo engine on a rotor disk having blade root receptacles for radial guidance of the rotor blades is disclosed. The restraint mechanism has a plurality of axial securing elements, each having at least one web for positioning in a blade root receptacle, such that each web has a retaining section at one end for establishing a form-fitting design to a mating brace of another axial securing element. A method for axially securing rotor blades on a rotor disk and a turbo engine are also disclosed.

    Abstract translation: 公开了一种用于转子盘上的涡轮发动机的转子叶片的约束机构，其具有用于转子叶片的径向引导的叶片根部容器。 约束机构具有多个轴向固定元件，每个轴向固定元件具有至少一个用于定位在叶片根部容器中的腹板，使得每个腹板在一端具有保持部分，用于将形状配合设计建立到另一个轴向的配合支架 固定元件。 还公开了一种用于将转子叶片轴向固定在转子盘和涡轮发动机上的方法。

    Seal configuration for a turbo machine
    5.
    发明授权
    Seal configuration for a turbo machine 有权

    公开(公告)号：US10047619B2

    公开(公告)日：2018-08-14

    申请号：US14532822

    申请日：2014-11-04

    Applicant: MTU Aero Engines AG

    Inventor： Andre Werner ,  Stephan Klaen ,  Manuel Hertter ,  Frank Stiehler

    IPC: F01D11/00 ,  F01D25/00 ,  F01D11/02 ,  F16J15/3288

    Abstract: A seal configuration (100) for a turbo machine having a rotor (5), wherein the seal configuration (100) has a sealing element (300) to create a seal with respect to the rotor (5) in an installed position and a supporting device (200). The supporting device (200) has, in at least one section of the supporting device, a material (9) that melts when it comes into contact with the rotating rotor (5) in the installed position. A turbo machine having a seal configuration (100) is also provided.

    Guide vane arrangement and method for mounting a guide vane
    6.
    发明授权
    Guide vane arrangement and method for mounting a guide vane 有权

    公开(公告)号：US09617861B2

    公开(公告)日：2017-04-11

    申请号：US14305134

    申请日：2014-06-16

    Applicant: MTU Aero Engines AG

    Inventor： Stephan Klaen ,  Norbert Schinko

    IPC: F01D9/02 ,  F01D17/16 ,  F01D11/00

    CPC classification number: F01D9/02 ,  F01D11/001 ,  F01D17/162 ,  F05D2230/60 ,  Y10T29/49321

    Abstract: The invention relates to a guide vane arrangement and a method for mounting a guide vane. The guide vane arrangement has at least one guide vane having a radially inner journal, which engages in a borehole of a bushing. The bushing is disposed in a borehole of an inner ring segment. The journal is connected to the bushing in a rotation-resistant manner and a slide mounting is provided between the bushing and the inner ring borehole. For mounting the guide vane in an inner ring segment, the journal of the guide vane is introduced into the borehole of the bushing. Further, the journal is fastened to the bushing in a rotation-resistant manner, and the bushing is slide-mounted with the inner ring segment. The slide mounting is conducted prior to or simultaneously with or after the fastening of the journal to the bushing in a rotation-resistant manner.

    Seal configuration for a turbo machine
    7.
    发明申请
    Seal configuration for a turbo machine 审中-公开
    涡轮机的密封结构

    公开(公告)号：US20150125278A1

    公开(公告)日：2015-05-07

    申请号：US14532822

    申请日：2014-11-04

    Applicant: MTU Aero Engines AG

    Inventor： Andre WERNER ,  Stephan Klaen ,  Manuel Hertter ,  Frank Stiehler

    IPC: F01D11/00 ,  F01D25/00

    CPC classification number: F01D11/001 ,  F01D11/025 ,  F01D25/005 ,  F05D2240/56 ,  F16J15/3288

    Abstract: The present invention relates to a seal configuration (100) for a turbo machine having a rotor (5), wherein the seal configuration (100) has a sealing element (300) to create a seal with respect to the rotor (5) in an installed position and a supporting device (200). The supporting device (200) has, in at least one section of the supporting device, a material (9) that melts when it comes into contact with the rotating rotor (5) in the installed position. The present invention further relates to a turbo machine having a seal configuration (100).

    Abstract translation: 本发明涉及一种用于具有转子（5）的涡轮机的密封结构（100），其中密封构型（100）具有密封元件（300），以在一个或多个转子中相对于转子（5）产生密封 安装位置和支撑装置（200）。 支撑装置（200）在支撑装置的至少一个部分中具有在安装位置与旋转转子（5）接触时熔化的材料（9）。 本发明还涉及具有密封构造（100）的涡轮机。

    Mixing device and turbofan engine having such mixing device
    10.
    发明授权
    Mixing device and turbofan engine having such mixing device 有权

    公开(公告)号：US09771896B2

    公开(公告)日：2017-09-26

    申请号：US14244050

    申请日：2014-04-03

    Applicant: MTU Aero Engines AG

    Inventor： Hermann Klingels ,  Stephan Klaen ,  Christian Scherer ,  Uwe Vogel

    IPC: F02K3/075 ,  F02K1/38 ,  F02K1/48 ,  F02K1/46 ,  F02K1/06

    CPC classification number: F02K3/075 ,  F02K1/06 ,  F02K1/386 ,  F02K1/46 ,  F02K1/48 ,  F05D2250/61

    Abstract: The invention relates to a mixing device and a turbofan engine having such a mixing device 30 for mixing a first gas flow 40 with a second gas flow 50 in a turbofan engine 20, having an actuating device 95 and walls 60, which bound a channel 65 for the first gas flow 40 and a channel 70 lying radially outside for the second gas flow 50, the actuating device 95 comprising a coupling element 110 that is coupled to the walls (60), the actuating device 95 being designed to pivot the walls 60 between a first position and a second position disposed radially outside relative to the first position, the actuating device 95 comprising an adjusting ring 105 that can be rotated between a first rotating position and a second rotating position in the peripheral direction and that is joined to the coupling element 110.

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