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1. 发明授权

US06431830B1 Nozzle ring for a gas turbine 失效
标题翻译：用于燃气轮机的喷嘴环
公开(公告)号：US06431830B1
公开(公告)日：2002-08-13
申请号：US09643066
申请日：2000-08-21
申请人： Karl-Hermann Richter , Josef Reischl , Hans Juergen Schmuhl , Klaus Breitschwerdt , Ulrich Knott , Siegfried Boettcher , Karlheinz Manier , Werner Humhauser
发明人： Karl-Hermann Richter , Josef Reischl , Hans Juergen Schmuhl , Klaus Breitschwerdt , Ulrich Knott , Siegfried Boettcher , Karlheinz Manier , Werner Humhauser
IPC分类号： F01D900
CPC分类号： F01D9/042 , Y02T50/673 , Y10T29/49321 , Y10T29/49323
摘要： A worked nozzle ring for a gas turbine, in particular an aircraft engine, having at least one shroud and at least one blade sheet arranged thereon, whereby, in order to create a worked nozzle ring that is easy to manufacture, the blade sheet comprises, at the frontal side, at least one two-dimensionally profiled connecting space region that is placed in a profiled opening formed in the shroud by beam cutting and is connected therewith.
摘要翻译：一种用于燃气涡轮机，特别是飞机发动机的加工喷嘴环，其具有至少一个护罩和布置在其上的至少一个叶片，由此，为了形成易于制造的加工喷嘴环，在前侧，至少一个二维轮廓的连接空间区域，其通过光束切割放置在形成在罩中的成型开口中并与其连接。

2. 发明授权

US08764390B2 Assembly mechanism comprising a tension anchor and corresponding method for a rotor system of an axial turbo engine 有权
标题翻译：包括用于轴向涡轮发动机的转子系统的张力锚和相应方法的组装机构
公开(公告)号：US08764390B2
公开(公告)日：2014-07-01
申请号：US13130730
申请日：2009-12-02
申请人： Werner Humhauser
发明人： Werner Humhauser
IPC分类号： B64C11/04
CPC分类号： F01D5/066 , F05D2230/60 , F05D2230/64 , F05D2260/30 , Y10T29/49316 , Y10T29/49321 , Y10T29/53
摘要： The invention relates to a device (1) and to a method associated with an assembly mechanism for a rotor system of an axial turbo engine having a central tension anchor, as is particularly known from engine technology. To this end, the invention provides a tensioning tool that pre-tensions or biases the tension anchor prior to and during the insertion of the anchor into the compound rotor assembly. After inserting the biased tension anchor in the compound rotor assembly, the tension anchor is relaxed, whereby the anchor exercises a compressive force on the compound rotor assembly. According to a preferred embodiment, the compound rotor assembly is also biased (compressed) and relaxed after assembling the tension anchor, so that a desired nominal bias Sigmanominal can be particularly easily achieved. The use of a shaft locking nut is no longer necessary in the device according to the invention, thus avoiding the difficulties that are associated with the use of this nut, such as complexity and safety problems. The invention also relates to a method for assembling a tension anchor (2) for a rotor system (6) employing the assembly mechanism according to the invention.
摘要翻译：本发明涉及一种与发动机技术特别公知的具有中心张力锚的轴向涡轮发动机的转子系统的组装机构相关联的装置（1）。为此，本发明提供了一种张紧工具，其在锚固件插入复合转子组件之前和之中预紧张或偏压张力锚。在将偏置的张力锚固件插入复合转子组件之后，张力锚固件被松弛，由此锚固件对复合转子组件施加压缩力。根据优选实施例，复合转子组件在组装拉力锚之后也被偏压（压缩）和松弛，使得可以特别容易地实现期望的标称偏差Sigmanominal。在根据本发明的装置中不再需要使用轴锁定螺母，因此避免了与使用该螺母有关的困难，例如复杂性和安全性问题。本发明还涉及一种用于组装采用根据本发明的组装机构的转子系统（6）的张力锚（2）的方法。

3. 发明授权

US6119339A Nozzle ring for a gas turbine and method of manufacture thereof 有权
标题翻译：一种用于燃气轮机的喷嘴环及其制造方法
公开(公告)号：US6119339A
公开(公告)日：2000-09-19
申请号：US281987
申请日：1999-03-29
申请人： Karl-Hermann Richter , Josef Reischl , Hans Juergen Schmuhl , Klaus Breitschwerdt , Ulrich Knott , Siegfried Boettcher , Karlheinz Manier , Werner Humhauser
发明人： Karl-Hermann Richter , Josef Reischl , Hans Juergen Schmuhl , Klaus Breitschwerdt , Ulrich Knott , Siegfried Boettcher , Karlheinz Manier , Werner Humhauser
IPC分类号： F01D9/02 , F01D9/04 , B21D53/78
CPC分类号： F01D9/042 , Y02T50/673 , Y10T29/49321 , Y10T29/49323
摘要： A worked nozzle ring for a gas turbine, in particular an aircraft engine, having at least one shroud and at least one blade sheet arranged thereon, whereby in order to create a worked nozzle ring that is easy to manufacture, the blade sheet comprises, at the frontal side, at least one two-dimensionally profiled connecting space region that is placed in a profiled opening formed in the shroud by means of beam cutting and is connected therewith.
摘要翻译：一种用于燃气涡轮机，特别是飞机发动机的加工喷嘴环，其具有至少一个护罩和布置在其上的至少一个刀片，由此为了形成易于制造的加工喷嘴环，刀片包括在前侧，至少一个二维轮廓的连接空间区域，其通过光束切割放置在形成在护罩中的成型开口中并与其连接。

4. 发明授权

US09617866B2 Blade outer air seal for a gas turbine engine 有权
公开(公告)号：US09617866B2
公开(公告)日：2017-04-11
申请号：US13559901
申请日：2012-07-27
申请人： Nicholas R. Leslie , Fadi S. Maalouf , Georg Zotz , Werner Humhauser
发明人： Nicholas R. Leslie , Fadi S. Maalouf , Georg Zotz , Werner Humhauser
IPC分类号： F01D11/12
CPC分类号： F01D11/122 , F01D11/125 , F01D11/127 , F05D2230/312
摘要： A blade outer air seal (BOAS) for a gas turbine engine according to an exemplary aspect of the present disclosure includes, among other things, a seal body having a radially inner face and a radially outer face that axially extend between a leading edge portion and a trailing edge portion. The BOAS includes a trough disposed on the radially inner face and an abradable seal received within the trough. The trough is open to expose a leading edge of the abradable seal to a core flow path of the gas turbine engine.

5. 发明授权

US08061965B2 Ring structure of metal construction having a run-in lining 失效
标题翻译：金属结构的环形结构具有磨合衬里
公开(公告)号：US08061965B2
公开(公告)日：2011-11-22
申请号：US11578862
申请日：2005-02-28
申请人： Manfred A. Daeubler , Horst Mueller-Wittek, legal representative , Renate Mendritzki, legal representative , Ulrike Hain , Werner Humhauser
发明人： Manfred A. Daeubler , Ulrike Hain , Werner Humhauser
IPC分类号： F01D11/08
CPC分类号： F01D11/122 , F01D11/127 , F05D2230/236 , F05D2230/237 , F05D2230/238 , F05D2250/283 , F05D2300/601
摘要： A ring structure with a metal design for a moving blade of axially flowed through compressor and turbine stages, particularly in gas turbine engines is provided. The ring structure includes a circular ring-shaped outer wall, a circular ring-shaped inner wall, which is located at a short radial distance from the moving blade tips, and includes a joining structure provided in the form of hollow chamber structure between the outer wall and the inner wall. The outer wall is provided in the form of a closed, mechanically stable housing wall of the compressor or turbine stage, and the joining structure provided in the form of hollow chamber structure is joined in a fixed manner to the outer wall and to the inner wall, for example, by soldering, diffusion welding or other joining techniques. The inner wall is provided in the form of a closed, mechanically stable structure, which serves as a run-in lining for the moving blade tips and which is made of a metal woven fabric and/or of a metal felt.
摘要翻译：提供了一种具有金属设计的环形结构，用于轴向流过压缩机和涡轮级的动叶片，特别是在燃气涡轮发动机中。环形结构包括圆形环形外壁，圆形环形内壁，其位于距活动叶片尖端短的径向距离处，并且包括以中空室结构的形式设置在外部的外部的接合结构墙壁和内壁。外壁以压缩机或涡轮机台的封闭的，机械稳定的壳体壁的形式提供，并且以中空室结构的形式提供的接合结构以固定的方式连接到外壁和内壁例如，通过焊接，扩散焊接或其它接合技术。内壁以闭合的，机械稳定的结构的形式提供，其用作活动叶片尖端的延伸衬里，其由金属织物和/或金属毡制成。

6. 发明授权

US5601407A Stator for turbomachines 失效
标题翻译：涡轮机定子
公开(公告)号：US5601407A
公开(公告)日：1997-02-11
申请号：US609557
申请日：1996-03-01
申请人： Werner Humhauser
发明人： Werner Humhauser
IPC分类号： F01D9/02 , F01D9/04 , F01D11/00 , F01D25/24 , F04D29/16 , F04D29/54 , F04D29/44
CPC分类号： F04D29/161 , F01D11/001 , F01D25/246 , F04D29/542
摘要： A stator construction for turbomachines includes a plurality of support segments (3) and a plurality of guide vane segment roots (2) forming an inner shroud, with an abradable seal liner (4) provided on the radially inner surface of the support segments. An interlocking connection is provided between the vane segment roots and the support segments. The vane segment roots and support segments interlock with one another via radially extending annular flanges (21, 31), and annular grooves (23, 33) provided in the side faces (22, 32) of the annular flanges mate with one another to form annular channels therebetween. To secure the interlocked connection, an annular securing wire (5) is inserted into the annular channels. Spring members (6) may be arranged in annular spaces between the support segments and the vane segment roots.
摘要翻译：用于涡轮机的定子结构包括多个支撑段（3）和形成内护罩的多个导叶段（2），在支撑段的径向内表面上设有可磨损的密封衬套（4）。在叶片段根部和支撑段之间设置有互锁连接。叶片段根部和支撑段通过径向延伸的环形凸缘（21,31）彼此互锁，并且设置在环形凸缘的侧面（22,32）中的环形槽（23,33）彼此配合以形成环形通道。为了固定互锁连接，环形固定线（5）插入到环形通道中。弹簧构件（6）可以布置在支撑段和叶片段根部之间的环形空间中。

7. 发明授权

US09297391B2 Flow device comprising a cavity cooling system 有权
标题翻译：流动装置包括空腔冷却系统
公开(公告)号：US09297391B2
公开(公告)日：2016-03-29
申请号：US13260694
申请日：2010-05-12
申请人： Peter Klaus Rued , David Koch , Werner Humhauser
发明人： Peter Klaus Rued , David Koch , Werner Humhauser
IPC分类号： F04D29/58 , F04D29/54 , F01D11/04 , F04D29/10
CPC分类号： F04D29/542 , F01D11/04 , F04D29/102 , F04D29/584 , F05D2260/205 , Y02T50/671 , Y02T50/676
摘要： A flow device having a cooling-air injection system for injecting cooling air into cavities (20, 24) between sealing elements (14a, 14b) or sealing bodies (16a, 16b), respectively, on the side of the guide vanes and on the side of the rotor is disclosed.
摘要翻译：一种流动装置，具有冷却空气注入系统，用于将冷却空气分别注入在导向叶片侧面上的密封元件（14a，14b）或密封体（16a，16b）之间的空腔（20,24）中，并且在公开了转子的侧面。

8. 发明授权

US08105016B2 Damping arrangement for guide vanes 有权
标题翻译：导叶的阻尼装置
公开(公告)号：US08105016B2
公开(公告)日：2012-01-31
申请号：US10589160
申请日：2005-02-04
申请人： Carsten Butz , Werner Humhauser , Patrick Wackers , Walter Waschka , Moritz Wirth
发明人： Carsten Butz , Werner Humhauser , Patrick Wackers , Walter Waschka , Moritz Wirth
IPC分类号： F01D5/00
CPC分类号： F01D5/26 , F01D5/22 , F01D9/042 , F01D11/001 , F05D2240/70 , F05D2240/80 , F05D2260/96
摘要： A damping arrangement for guide vanes, in particular for guide vanes of a gas turbine or an aircraft engine, is disclosed. Referring to this damping arrangement, the radially external ends of the guide vanes of a guide vane grid or a guide vane ring are mounted to a housing. The radially internal ends of the guide vanes form an inner shroud. At least one seal bearing is mounted to the inner shroud of the guide vanes. At least one spring element is installed between the inner shroud of the guide vanes and the, or each, seal bearing. The, or each, spring element is configured as a leaf spring.
摘要翻译：公开了用于导向叶片，特别是用于燃气轮机或飞机发动机的导向叶片的阻尼装置。参考这种阻尼装置，导向叶栅格或导叶环的导向叶片的径向外端安装到壳体上。导向叶片的径向内端形成内护罩。至少一个密封轴承安装在导叶的内护罩上。至少一个弹簧元件安装在导向叶片的内护罩和每个密封轴承之间。弹簧元件或每个弹簧元件被配置为板簧。

9. 发明申请

US20110225822A1 ASSEMBLY MECHANISM COMPRISING A TENSION ANCHOR AND CORRESPONDING METHOD FOR A ROTOR SYSTEM OF AN AXIAL TURBO ENGINE 有权
标题翻译：包括张力锚杆的组装机构和轴向涡轮发动机转子系统的相应方法
公开(公告)号：US20110225822A1
公开(公告)日：2011-09-22
申请号：US13130730
申请日：2009-12-02
申请人： Werner Humhauser
发明人： Werner Humhauser
IPC分类号： B21D53/78 , B23P19/027
CPC分类号： F01D5/066 , F05D2230/60 , F05D2230/64 , F05D2260/30 , Y10T29/49316 , Y10T29/49321 , Y10T29/53
摘要： The invention relates to a device (1) and to a method associated with an assembly mechanism for a rotor system of an axial turbo engine having a central tension anchor, as is particularly known from engine technology. To this end, the invention provides a tensioning tool that pre-tensions or biases the tension anchor prior to and during the insertion of the anchor into the compound rotor assembly. After inserting the biased tension anchor in the compound rotor assembly, the tension anchor is relaxed, whereby the anchor exercises a compressive force on the compound rotor assembly. According to a preferred embodiment, the compound rotor assembly is also biased (compressed) and relaxed after assembling the tension anchor, so that a desired nominal bias Sigmanominal can be particularly easily achieved. The use of a shaft locking nut is no longer necessary in the device according to the invention, thus avoiding the difficulties that are associated with the use of this nut, such as complexity and safety problems. The invention also relates to a method for assembling a tension anchor (2) for a rotor system (6) employing the assembly mechanism according to the invention.
摘要翻译：本发明涉及一种与发动机技术特别公知的具有中心张力锚的轴向涡轮发动机的转子系统的组装机构相关联的装置（1）。为此，本发明提供了一种张紧工具，其在锚固件插入复合转子组件之前和之中预紧张或偏压张力锚。在将偏置的张力锚固件插入复合转子组件之后，张力锚固件被松弛，由此锚固件对复合转子组件施加压缩力。根据优选实施例，复合转子组件在组装拉力锚之后也被偏压（压缩）和松弛，使得可以特别容易地实现期望的标称偏差Sigmanominal。在根据本发明的装置中不再需要使用轴锁定螺母，因此避免了与使用该螺母有关的困难，例如复杂性和安全性问题。本发明还涉及一种用于组装采用根据本发明的组装机构的转子系统（6）的张力锚（2）的方法。

10. 发明授权

US07396206B2 Arrangement for axially and radially fixing the guide vanes of a vane ring of a gas turbine 失效
标题翻译：用于轴向和径向固定燃气轮机叶片环的导向叶片的布置
公开(公告)号：US07396206B2
公开(公告)日：2008-07-08
申请号：US10515597
申请日：2003-05-15
申请人： Werner Humhauser
发明人： Werner Humhauser
IPC分类号： F01D9/02
CPC分类号： F01D25/246 , F01D9/042 , F05D2230/64 , F05D2240/11 , F05D2260/30
摘要： A gas turbine has at least one guide blade ring, whose guide vanes are axially and radially fixed via detachable locking elements. A shell ring is configured as a freely machinable component having projections bearing a stop surface and mating surfaces. A holding piece is provided for each guide vane, which engages into corresponding recesses on an upstream shell ring. The holding pieces are held in a position determined by the locking elements, via spring clips.
摘要翻译：燃气轮机具有至少一个引导叶片环，其引导叶片通过可拆卸的锁定元件轴向和径向地固定。壳环被构造为具有能够具有止动表面和配合表面的凸起的可自由加工的部件。为每个导向叶片提供保持件，该保持件接合在上游壳环上的相应凹部中。保持件通过弹簧夹保持在由锁定元件确定的位置。

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