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公开(公告)号：US10689983B2
公开(公告)日：2020-06-23
申请号：US15793654
申请日：2017-10-25
Applicant: MTU Aero Engines AG
Inventor： Markus Schlemmer , Andreas Hartung , Gerhard-Heinz Roesele , Martin Pernleitner , Manfred Schill , Manfred Feldmann , Adrian Ehrenberg
Abstract: An impulse body module a turbine stage of a gas turbine includes a holder component of one-piece construction, with a base and surrounding side walls arranged at the base, wherein the side walls and the base define a holding chamber; an insert component, of one-piece construction, which is inserted into the holding chamber of the holder component, wherein the holder component and the insert component accommodated therein define a number of mutually separated cavities, and wherein an impulse body, in particular a sphere, is accommodated in each cavity; and a closure component of one-piece construction, which is joined to the holder component in a material-bonded manner where the holding chamber is closed and the insert component is surrounded by the holder component and the closure component. The holder component has at least one base projection in the region of its base, which extends away from the holding chamber.
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公开(公告)号：US10047618B2
公开(公告)日：2018-08-14
申请号：US14494011
申请日：2014-09-23
Applicant: MTU Aero Engines AG
Inventor： Thomas Hess , Manfred Feldmann
Abstract: A component system of a turbine engine including a first component segment and a second component segment configurable in a ring segment shape, so that at least one abutment surface of the first component segment and an abutment surface of the second component segment abut against each other; together, the first component segment and the second component segment including at least three overlapping elements for sealing a gap between the abutment surfaces. In the case of mutually abutting abutment surfaces, each overlapping element overlapping radially with the respective other component segment. At least two of the overlapping elements are configured on the first component segment, while at least one of the overlapping elements is configured on the second component segment. In the case of mutually abutting abutment surfaces, the overlapping element of the second component segment is axially configured between the overlapping elements of the first component segment.
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公开(公告)号：US09951631B2
公开(公告)日：2018-04-24
申请号：US14316035
申请日：2014-06-26
Applicant: MTU Aero Engines AG
Inventor： Krzysztof Skura , Marcin Kozdras , Lukasz Sosnowka , Manfred Feldmann , Manfred Schill
CPC classification number: F01D5/3007 , F05D2250/292 , F05D2250/38 , F05D2250/712
Abstract: A rotor blade for a turbomachine, including an airfoil (1) for flow deflection, a blade root (2) for attachment to a rotor of the turbomachine, an inner platform (3) between the airfoil and the blade root, and at least one pocket (4, 5) defined by two axially spaced walls (4.1, 4.2; 5.1, 5.2) extending from the side of the platform opposite the airfoil toward the blade root. A first (4.1, 5.1) of these walls has an outer side (4.1A, 5.1A) that faces away from the pocket and, in at least one cross section perpendicular to a radial longitudinal axis of the rotor blade, slopes outwardly.
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公开(公告)号：US20180030856A1
公开(公告)日：2018-02-01
申请号：US15653707
申请日：2017-07-19
Applicant: MTU Aero Engines AG
Inventor： Alexander Kloetzer , Manfred Feldmann
CPC classification number: F01D25/246 , B21D22/20 , F01D25/243 , F05D2220/32 , F05D2230/20 , F05D2230/642 , F05D2240/14 , F05D2260/231 , F05D2260/30 , F05D2260/31 , F05D2260/941 , F05D2300/10 , F05D2300/603
Abstract: A liner element (10), in particular a heat shield element or casing element, of a turbomachine, in particular a gas turbine, including a fastening portion (12) having at least one bore (14-1, 14-2) through which a connection unit (42) having, in particular a pin-type or bolt-type form, is introducible along a bore axis (BA); a liner portion (16) that adjoins the fastening portion (12); the fastening portion (12) and the liner portion (16) being formed in one piece, and having an annular or ring segment shape. The bore (14-1, 14-2) is provided in a depression (24-1, 24-2) formed in the fastening portion (12), the depression (24-1, 24-2) being essentially formed concentrically about the bore (14-1, 14-2).
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公开(公告)号：US09506368B2
公开(公告)日：2016-11-29
申请号：US14064844
申请日：2013-10-28
Applicant: MTU Aero Engines AG
Inventor： Manfred Feldmann , Janine Sangl , Norbert Schinko
CPC classification number: F01D11/08 , F01D9/042 , F01D11/12 , F01D11/122 , F01D25/246 , F05D2230/90 , F05D2240/11 , F05D2240/80 , F05D2260/30 , Y02T50/673
Abstract: A housing structure for a turbomachine having a stationary blade ring annularly surrounding a flow channel, and having a seal carrier ring which also annularly surrounds the flow channel, the stationary blade ring and the seal carrier ring being connected to each other, and either the stationary blade ring or the seal carrier ring having a one-sidedly open receptacle in the radial direction in relation to the flow channel and a radially projecting engagement area which corresponds to the connected seal carrier ring or stationary blade ring and which is held in a form-fitting manner in the axial direction and in the radial direction in the direction of the closed side of the receptacle but is freely movable with respect to the connected receptacle and the seal carrier ring or stationary blade ring having this receptacle in the radially opposite direction in the direction of the receptacle opening.
Abstract translation: 一种用于涡轮机的壳体结构，其具有环形环绕流动通道的固定叶片环，并且具有环形地围绕流动通道的密封载体环，固定叶片环和密封承载环彼此连接， 叶片环或密封承载环相对于流动通道在径向方向上具有单侧敞开的容器，以及对应于所连接的密封承载环或固定叶片环的径向突出的接合区域， 在容器的封闭侧的方向上在轴向方向和径向方向上的装配方式，但是可以相对于所连接的容器和具有该容器的密封承载环或固定叶片环沿着径向相反的方向自由移动 插座开口的方向。
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Patent Agency Ranking
公开(公告)号：US20160326897A1
公开(公告)日：2016-11-10
申请号：US15144974
申请日：2016-05-03
Applicant: MTU Aero Engines AG
Inventor： Manfred Feldmann , Daniel Kirchner
CPC classification number: F01D11/005 , F01D9/02 , F01D9/023 , F05D2220/32 , F05D2240/11 , F05D2240/57 , F05D2250/75 , F05D2300/501 , Y02T50/675
Abstract: A turbomachine includes a seal device for sealing a gap between two components, with a plurality of sealing elements tippable in the direction of a relative displacement of the components. The sealing elements are mounted on one of the components and bridge the gap where the device has prestressing elements, by which the tippable sealing elements are prestressed against a respective sealing edge of the components. The prestressing elements are each supported at a front support point and a back support point of the component on the mounting side, these points being distanced from one another in the axial direction and in the radial direction of the turbomachine where the front support point is disposed radially outside and the back support point is disposed radially inside with respect to the mounting.
Abstract translation: 涡轮机包括用于密封两个部件之间的间隙的密封装置，多个密封元件可在部件的相对移位的方向上倾斜。 密封元件安装在其中一个部件上并桥接设备具有预应力元件的间隙，通过该间隙，可翻转的密封元件预先抵靠部件的相应的密封边缘。 预应力元件各自支撑在安装侧的部件的前支撑点和后支撑点处，这些点在轴向方向上和在设置前支撑点的涡轮机的径向方向上彼此间隔开 径向外侧和后支撑点相对于安装件径向设置在内侧。
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公开(公告)号：US09416672B2
公开(公告)日：2016-08-16
申请号：US14052338
申请日：2013-10-11
Applicant: MTU AERO ENGINES AG
Inventor： Manfred Feldmann , Janine Sangl , Sebastian Kaltenbach , Joachim Lorenz
CPC classification number: F01D9/023 , F01D9/041 , F01D11/005 , F01D25/243 , F05D2240/15
Abstract: A housing structure for a turbo-engine, especially for a gas turbine or an aircraft engine, includes an outer housing wall and an inner housing wall, the inner and outer housing walls annularly enclosing a flow channel for the turbo-engine and being spaced apart radially from the flow channel. At least one heat shield is arranged between the inner and outer housing walls, and a bar or a fixture projects at least somewhat radially from the inner housing wall. The bar or the fixture has on at least one side a broadening element that includes a sealing face against which the heat shield is positioned in a sealing manner.
Abstract translation: 用于涡轮发动机，特别是用于燃气轮机或飞机发动机的涡轮发动机的壳体结构包括外部壳体壁和内部壳体壁，内部和外部壳体壁环绕地包围涡轮发动机的流动通道并且间隔开 径流从流道。 至少一个隔热罩设置在内壳体外壳和外壳体壁之间，并且杆或固定件至少在一定程度上从内壳体壁伸出。 杆或固定装置至少在一侧具有增宽元件，该增宽元件包括密封面，隔热罩以密封方式定位在该密封面上。
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公开(公告)号：US20140119902A1
公开(公告)日：2014-05-01
申请号：US14064844
申请日：2013-10-28
Applicant: MTU Aero Engines AG
Inventor： Manfred Feldmann , Janine Sangl , Norbert Schinko
IPC: F01D11/08
CPC classification number: F01D11/08 , F01D9/042 , F01D11/12 , F01D11/122 , F01D25/246 , F05D2230/90 , F05D2240/11 , F05D2240/80 , F05D2260/30 , Y02T50/673
Abstract: A housing structure for a turbomachine having a stationary blade ring annularly surrounding a flow channel, and having a seal carrier ring which also annularly surrounds the flow channel, the stationary blade ring and the seal carrier ring being connected to each other, and either the stationary blade ring or the seal carrier ring having a one-sidedly open receptacle in the radial direction in relation to the flow channel and a radially projecting engagement area which corresponds to the connected seal carrier ring or stationary blade ring and which is held in a form-fitting manner in the axial direction and in the radial direction in the direction of the closed side of the receptacle but is freely movable with respect to the connected receptacle and the seal carrier ring or stationary blade ring having this receptacle in the radially opposite direction in the direction of the receptacle opening.
Abstract translation: 一种用于涡轮机的壳体结构，其具有环形环绕流动通道的固定叶片环，并且具有环形地围绕流动通道的密封载体环，固定叶片环和密封承载环彼此连接， 叶片环或密封承载环相对于流动通道在径向方向上具有单侧敞开的容器，以及对应于所连接的密封承载环或固定叶片环的径向突出的接合区域， 在容器的封闭侧的方向上在轴向方向和径向方向上的装配方式，但是可以相对于所连接的容器和具有该容器的密封承载环或固定叶片环沿着径向相反的方向自由移动 插座开口的方向。
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公开(公告)号：US20140044529A1
公开(公告)日：2014-02-13
申请号：US13960455
申请日：2013-08-06
Applicant: MTU Aero Engines AG
Inventor： Manfred Feldmann , Norbert Schinko , Sebastian Kaltenbach , Joachim Lorenz
IPC: F01D11/00
CPC classification number: F01D11/001 , F01D9/04 , F01D11/08 , F01D11/12 , F01D25/145 , F01D25/246 , Y02T50/675
Abstract: A turbomachine having a flow channel and a housing radially surrounding the flow channel, a plurality of stationary and moving blades being situated in the flow channel, stationary blades being situated adjacent to the moving blades in the axial direction, and the stationary blades having at least one stationary blade hook which engages with at least one housing hook for the purpose of connecting the stationary blades to the housing. A sealing and lining element is situated in the radial direction between the moving blades adjacent to the stationary blades and the housing, and has a sealing structure interacting with blade tips of the moving blades. A heat protection element is provided in the area between the sealing and lining element and the housing, and a sealing element being situated on the heat protection element for the purpose of sealing contact with the housing hook.
Abstract translation: 一种具有流动通道和径向围绕流动通道的壳体的涡轮机，多个静止和可动的叶片位于流动通道中，固定叶片沿着轴向位于活动叶片附近，并且固定叶片至少具有 一个固定叶片钩，其与至少一个壳体钩接合，用于将固定叶片连接到壳体。 密封和衬里元件位于与静止叶片和壳体相邻的活动叶片之间的径向方向上，并且具有与动叶片的叶片尖端相互作用的密封结构。 在密封和衬里元件和壳体之间的区域中设置有热保护元件，并且密封元件位于热保护元件上，用于与壳体钩紧密接触。
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公开(公告)号：US11125163B2
公开(公告)日：2021-09-21
申请号：US16454351
申请日：2019-06-27
Applicant: MTU Aero Engines AG
Inventor： Manfred Feldmann
Abstract: The present invention relates to a housing structure for a turbomachine, a turbomachine, and a method for cooling a housing portion of a housing structure of a turbomachine, wherein the housing structure has an outer housing wall, which is formed by at least one housing part, and an inner wall, wherein the inner wall is arranged in the radial direction inside of the housing wall and spaced apart from the housing wall and is designed to bound the main flow channel, at least partially, wherein the housing structure comprises a cooling air channel for cooling a housing portion to be cooled, and has an upstream end and a downstream end, wherein the cooling air channel extends, at least partially, between the housing wall and the inner wall.
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