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    Shroud for rotating blades of a turbo machine, and turbo machine
    1.
    发明授权
    Shroud for rotating blades of a turbo machine, and turbo machine 有权
    用于涡轮机的旋转叶片的涡卷机和涡轮机

    公开(公告)号：US08573939B2

    公开(公告)日：2013-11-05

    申请号：US12991627

    申请日：2009-04-30

    申请人： Hans-Peter Borufka ,  Hernan Victor Arrieta ,  Klemens Hain

    发明人： Hans-Peter Borufka ,  Hernan Victor Arrieta ,  Klemens Hain

    IPC分类号： F01D5/10 ,  F01D5/26

    CPC分类号： F01D5/225 ,  F05D2250/183 ,  F05D2260/96

    摘要： A shroud for the rotating blades of a turbo machine, particularly a gas turbine, in which shroud is arranged along the circumference of a row of several rotating blades disposed on a rotor and has at least one separation gap along its circumference. The separation gap is formed in zigzag shape and has at least three damping gaps that are distanced from one another and extend at an angle relative to an axis of rotation of the rotor, and adjacent to these, has connection gaps each connecting damping gaps or extending the latter in the direction of shroud edges, wherein, when the rotor rotates, the gap width of damping gaps is reduced until the gap walls forming the damping gaps come to rest against each other.

    摘要翻译： 用于涡轮机的旋转叶片的护罩，特别是燃气轮机，其中护罩沿着设置在转子上的若干旋转刀片的一排的圆周布置，并且沿其圆周具有至少一个间隔。 分离间隙以Z字形形成，并且具有至少三个相互间隔并且相对于转子的旋转轴线成一定角度并且与其相邻的阻尼间隙，具有各自连接阻尼间隙或延伸的连接间隙 后者在护罩边缘的方向上，其中，当转子旋转时，阻尼间隙的间隙宽度减小，直到形成阻尼间隙的间隙壁相互抵靠为止。

    SHROUD FOR ROTATING BLADES OF A TURBO MACHINE, AND TURBO MACHINE
    2.
    发明申请
    SHROUD FOR ROTATING BLADES OF A TURBO MACHINE, AND TURBO MACHINE 有权
    涡轮机旋转叶片，涡轮机

    公开(公告)号：US20110103956A1

    公开(公告)日：2011-05-05

    申请号：US12991627

    申请日：2009-04-30

    申请人： Hans-Peter Borufka ,  Hernan Victor Arrieta ,  Klemens Hain

    发明人： Hans-Peter Borufka ,  Hernan Victor Arrieta ,  Klemens Hain

    IPC分类号： F01D5/22

    CPC分类号： F01D5/225 ,  F05D2250/183 ,  F05D2260/96

    摘要： The invention relates to a shroud for rotating blades of a turbo machine, in particular a gas turbine. Said shroud (10) is arranged along the circumference of a row of several rotating blades (14, 50) disposed on a rotor (12) and has at least one separation gap (16, 16′, 16″) along the circumference. The separation gap (16, 16′, 16″) is serrated and has at least three damping gaps (20, 22, 24, 26, 28) that are located at a distance from one another and extend at an angle from the axis of rotation (18) of the rotor (12), and adjacent connection gaps (30, 32, 34, 36, 38, 40) which connect the damping gaps (20, 22, 24, 26, 28) or extend the same in the direction of the shroud edges (46, 48). When the rotor (12) rotates, the width of the damping gaps (20, 22, 24, 26, 28) is reduced to the point where the gap walls (42, 44) forming the damping gaps (20, 22, 24, 26, 28) rest against each other. The invention further relates to a turbo machine, in particular a gas turbine, comprising at least one rotor (12) that has at least one row of several rotating blades (14, 50). A shroud (12) according to the invention is arranged along the circumference of the row of rotating blades.

    摘要翻译： 本发明涉及一种用于旋转涡轮机的叶片的护罩，特别是燃气轮机。 所述护罩（10）沿着设置在转子（12）上的若干旋转叶片（14,50）的一排的圆周布置，并且沿圆周具有至少一个分隔间隙（16,16'，16“）。 分离间隙（16,16'，16“）是锯齿形的，并且具有至少三个阻尼间隙（20,22,24,26,28），它们彼此间隔一定距离并且以 转子（12）的旋转（18）以及连接阻尼间隙（20,22,24,26,28）的相邻的连接间隙（30,32,34,36,38,40）或将其延伸到 护罩边缘（46,48）的方向。 当转子（12）旋转时，阻尼间隙（20,22,24,26,28）的宽度减小到形成阻尼间隙（20,22,24,26,28）的间隙壁（42,44） 26,28）彼此休息。 本发明还涉及一种涡轮机，特别是一种燃气轮机，包括至少一个具有至少一排数个旋转叶片（14,50）的转子（12）。 根据本发明的护罩（12）沿着旋转叶片排的圆周布置。

    Turbine vane of a gas turbine
    3.
    发明授权
    Turbine vane of a gas turbine 有权
    燃气轮机的涡轮叶片

    公开(公告)号：US08172520B2

    公开(公告)日：2012-05-08

    申请号：US12445439

    申请日：2007-10-06

    申请人： Hernan Victor Arrieta ,  Rolf Kleinstueck ,  Paul Storm ,  Peter Wiedemann

    发明人： Hernan Victor Arrieta ,  Rolf Kleinstueck ,  Paul Storm ,  Peter Wiedemann

    IPC分类号： F01D25/08 ,  F04D29/58

    CPC分类号： F01D5/18 ,  F01D5/288 ,  F01D9/041 ,  F05D2260/94 ,  F05D2260/941 ,  Y02T50/67 ,  Y02T50/673 ,  Y02T50/676

    摘要： A turbine vane of a gas turbine, especially a gas turbine aircraft engine, is disclosed. The turbine vane includes a vane base body with an outer surface forming a suction side and a pressure side, the outer surface of the vane base body being at least partially coated with a thermal barrier coating. The thermal barrier coating extends continuously or uninterruptedly at least largely over the suction side and largely over the pressure side of the surface of the vane base body, with the layer thickness of the thermal barrier coating being variable or adjustable.

    摘要翻译： 公开了一种燃气轮机的涡轮叶片，特别是燃气涡轮机飞机发动机。 涡轮叶片包括具有形成吸入侧和压力侧的外表面的叶片基体，叶片基体的外表面至少部分地涂覆有热障涂层。 热障涂层至少在吸力侧连续或不间断延伸，并大大超过叶片基体表面的压力侧，而热障涂层的层厚度是可变的或可调节的。

    DEVICE AND METHOD FOR SERVICE-LIFE MONITORING
    6.
    发明申请
    DEVICE AND METHOD FOR SERVICE-LIFE MONITORING 审中-公开
    用于维修生命监控的设备和方法

    公开(公告)号：US20110166798A1

    公开(公告)日：2011-07-07

    申请号：US12998054

    申请日：2009-09-09

    申请人： Eberhard Knodel ,  Hans-Peter Borufka ,  Hernan Victor Arrieta

    发明人： Eberhard Knodel ,  Hans-Peter Borufka ,  Hernan Victor Arrieta

    IPC分类号： G06F19/00

    CPC分类号： F01D21/003 ,  F05D2270/11 ,  G05B23/0283 ,  Y02T50/671

    摘要： In the case of a device and a method for monitoring the service life of an engine or of a turbine having a compressor blisk and/or a turbine blisk, momentary stresses of blisk substructures, such as the blade (1), the disk (2), and the join region (3) between the blade (1) and the disk (2), are calculated on the basis of operating parameters that are measured in the course of engine or turbine operation; and accumulated damage to the individual substructures, that was caused by the momentary stresses, is estimated.

    摘要翻译： 在用于监测发动机或具有压缩机叶片和/或涡轮叶片的涡轮机的使用寿命的装置和方法的情况下，叶片子结构（例如叶片（1）），盘（2）的瞬时应力 ）和叶片（1）和盘（2）之间的连接区域（3）基于在发动机或涡轮机操作过程中测量的操作参数来计算; 并估计了由瞬时压力造成的各个子结构的累积损失。

    Apparatus and method for attaching a rotor blade to a rotor
    7.
    发明授权
    Apparatus and method for attaching a rotor blade to a rotor 失效
    用于将转子叶片附接到转子的装置和方法

    公开(公告)号：US07503751B2

    公开(公告)日：2009-03-17

    申请号：US10544754

    申请日：2005-03-16

    申请人： Hernan Victor Arrieta

    发明人： Hernan Victor Arrieta

    IPC分类号： F01D5/30

    CPC分类号： F01D5/3007 ,  Y02T50/671 ,  Y10T29/49321

    摘要： An apparatus and method for attaching a rotor blade to a rotor, particularly for a gas turbine, is disclosed. The rotor blade has a blade vane and a blade root, such that the blade vane can be attached to or anchored in the rotor by the blade root. The blade root is configured asymmetrically, such that the front region of the blade root as seen in the direction of rotation of the rotor blade is provided with more anchoring teeth than a rear region of the blade root as seen in the direction of rotation of the rotor blade.

    摘要翻译： 公开了一种用于将转子叶片附接到转子，特别是用于燃气轮机的装置和方法。 转子叶片具有叶片叶片和叶片根部，使得叶片叶片可以通过叶片根部附接或固定在转子中。 叶片根部被不对称地构造，使得如在转子叶片的旋转方向上看到的叶片根部的前部区域具有比叶片根部的后部区域更多的锚固齿， 转子叶片。