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1.发明申请公开(公告)号：US20180100398A1
公开(公告)日：2018-04-12
申请号：US15729776
申请日：2017-10-11
发明人： Miklos GAEBLER , Sven BRUEGGMANN
摘要： A rotor blade assembly group for an engine with a ring-shaped or disc-shaped blade carrier having multiple rotor blades that are provided along a circle line about a central axis of the rotor blade assembly group, wherein the blade carrier has a carrier section that extends radially inwards in the direction of the central axis with respect to the rotor blades, the carrier section comprises a connection area, at which a stiffening structure with at least two, first and second, stiffening elements is fixedly attached, and the first stiffening element is arranged at a first face side of the blade carrier and the second stiffening element is arranged at a second face side that is facing away from the first face side. The first and second stiffening elements are connected to the connection area of the blade carrier and in addition are connected to each other.
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2.发明申请SEALING ELEMENT FOR A TURBO-MACHINE, TURBO-MACHINE COMPRISING A SEALING ELEMENT AND METHOD FOR MANUFACTURING A SEALING ELEMENT 审中-公开涡轮机的密封元件，包含密封元件的涡轮机和用于制造密封元件的方法公开(公告)号：US20170058689A1
公开(公告)日：2017-03-02
申请号：US15247247
申请日：2016-08-25
CPC分类号： F01D11/127 , F01D11/10 , F01D11/122 , F04D29/164 , F04D29/526 , F05D2220/323 , F05D2250/11 , F05D2250/121 , F05D2250/131 , F05D2250/132 , F05D2250/141 , F05D2250/283 , F16J15/444
摘要： A sealing element for a turbomachine, in particular an aircraft engine, with a housing for the at least one rotating structural component is provided. The sealing element comprises a honeycomb structure for arrangement inside the housing, wherein the honeycomb structure extends in a first direction, wherein support structures are connected to the honeycomb structure in one piece and/or in a pattern-like manner and extend at least partially into the honeycomb structure, and the support structures extend at least partially or completely in a second direction that is different from the first direction. The support structures have planar portions, which are formed by at least one partially or completely closed cell together with the honeycomb structure.
摘要翻译： 提供了一种用于涡轮机，特别是飞机发动机的密封元件，其具有用于至少一个旋转结构部件的壳体。 所述密封元件包括用于布置在所述壳体内的蜂窝结构体，其中所述蜂窝结构体沿第一方向延伸，其中支撑结构以一体式和/或图案状方式连接到所述蜂窝结构，并且至少部分地延伸到 蜂窝结构和支撑结构至少部分地或完全地在与第一方向不同的第二方向上延伸。 支撑结构具有平面部分，其由与蜂窝结构一起的至少一个部分或完全闭合的单元形成。
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公开(公告)号：US20180100402A1
公开(公告)日：2018-04-12
申请号：US15729793
申请日：2017-10-11
发明人： Miklos GAEBLER , Sven BRUEGGMANN
IPC分类号： F01D5/30
摘要： A rotor blade assembly group for an engine with at least one blade carrier having at least one rotor blade that is provided with multiple rotor blades along a circle line about a central axis of the rotor blade assembly group, wherein the blade carrier has a carrier section that extends radially inwards in the direction of the central axis with respect to the rotor blade, the carrier section comprises a connection area at which a stiffening structure with at least two, first and second, stiffening elements is fixedly attached, and the stiffening element is arranged at a first face side of the blade carrier, and the second stiffening element is arranged at a second face side that is facing away from the first face side. The blade carrier is formed in a ring-segment-shaped or disc-segment-shaped-manner.
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公开(公告)号：US20200024950A1
公开(公告)日：2020-01-23
申请号：US16376389
申请日：2019-04-05
发明人： Sven BRUEGGMANN , Miklos GAEBLER
摘要： A rotor blade assembly group for an engine includes a blade carrier with rotor blades along a circle line about a central axis of the group, wherein the blade carrier has a carrier section extending radially inwards toward a central axis, the carrier section includes a connecting area at which a stiffening structure with a stiffening element is fixedly attached, and the stiffening element is arranged at a face side of the blade carrier. The stiffening element is axially secured at the face side of the blade carrier via a barrier element, that (a) is affixed radially further inside at or to a flange section of the blade carrier, or (b) is formed in front of the blade carrier and engages around the stiffening element with at least one barrier element section.
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5.发明申请SEALING ELEMENT, SEALING SYSTEM WITH A SEALING ELEMENT, TURBOMACHINE WITH A SEALING SYSTEM AND METHOD FOR MANUFACTURING A SEALING ELEMENT 审中-公开密封元件，具有密封元件的密封系统，具有密封系统的涡轮机和用于制造密封元件的方法公开(公告)号：US20170074405A1
公开(公告)日：2017-03-16
申请号：US15263853
申请日：2016-09-13
发明人： Miklos GAEBLER , Stephan PANNIER
IPC分类号： F16J15/453 , F01D11/00 , F01D11/02 , F16J15/447
CPC分类号： F16J15/453 , F01D5/225 , F01D11/003 , F01D11/02 , F01D11/122 , F05D2220/323 , F05D2230/30 , F05D2230/31 , F05D2300/177 , F05D2300/2262 , F05D2300/2282 , F16J15/445 , F16J15/447
摘要： A sealing element for a rotating sealing system of a turbomachine is provided. The sealing element, if installed in the sealing system according to the intended use, can be rotated around a rotational axis of the turbomachine. The sealing element comprises a ring-shaped sealing lip that has a central point through which the rotational axis extends if the sealing element is installed in the sealing system according to the intended use, wherein the sealing lip has at least one recess, and at least one rubbing element that is arranged at the sealing lip, wherein the at least one rubbing element is arranged inside the at least one recess and projects at least partially beyond the outer contour of the sealing lip in the radial and/or the axial direction with respect to the rotational axis. The at least one rubbing element has a plurality of layers of a rubbing material.
摘要翻译： 提供了一种用于涡轮机的旋转密封系统的密封元件。 如果密封元件安装在根据预期用途的密封系统中，则可围绕涡轮机的旋转轴线旋转。 密封元件包括环形密封唇缘，其具有中心点，如果密封元件根据预期用途安装在密封系统中，则旋转轴线延伸穿过该中心点，其中密封唇缘具有至少一个凹部，并且至少 布置在密封唇部的一个摩擦元件，其中所述至少一个摩擦元件布置在所述至少一个凹部内部，并且在所述径向和/或轴向方向上至少部分地突出超过所述密封唇的外轮廓， 到旋转轴线。 所述至少一个摩擦元件具有多层摩擦材料。
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