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1. 发明申请

US20130216359A1 COMPRESSOR 审中-公开
标题翻译：压缩机
公开(公告)号：US20130216359A1
公开(公告)日：2013-08-22
申请号：US13808117
申请日：2011-07-07
申请人： Thomas Brandenburg , Daniel Ecke , Markus Hofmann , Torsten Matthias , Bernward Mertens , Frank Mildner , Markus Paus , Achim Schirrmacher , Vadim Shevchenko , Uwe Sieber , Hubertus Michael Wigger
发明人： Thomas Brandenburg , Daniel Ecke , Markus Hofmann , Torsten Matthias , Bernward Mertens , Frank Mildner , Markus Paus , Achim Schirrmacher , Vadim Shevchenko , Uwe Sieber , Hubertus Michael Wigger
IPC分类号： F01D9/04
CPC分类号： F01D9/041 , F01D17/162 , F04D29/563
摘要： An axial compressor is provided. The compressor has an annular flow channel, in which adjustable blades of a blade ring that extend through the flow channel are rotatably mounted. Each blade has a lug on the rotor-side of the vane for mounting an inner ring. In order to provide a wear-free, self-centering inner ring, the ring is designed as a split ring with two opposing ends and a spring element for spreading the split ring.
摘要翻译：提供轴流式压缩机。压缩机具有环形流动通道，其中延伸穿过流动通道的叶片环的可调叶片可旋转地安装。每个叶片在叶片的转子侧具有用于安装内圈的凸耳。为了提供无磨损，自定心的内圈，环被设计为具有两个相对端的开口环和用于扩展开口环的弹簧元件。

2. 发明申请

US20140234111A1 BLADE ARRANGEMENT 有权
标题翻译：刀片布置
公开(公告)号：US20140234111A1
公开(公告)日：2014-08-21
申请号：US14239138
申请日：2012-08-14
申请人： Sascha Dungs , Elliot Griffin , Markus Paus , Stefan Reichling , Uwe Sieber , Hubertus Michael Wigger , Dirk Wistuba
发明人： Sascha Dungs , Elliot Griffin , Markus Paus , Stefan Reichling , Uwe Sieber , Hubertus Michael Wigger , Dirk Wistuba
IPC分类号： F01D5/32
CPC分类号： F01D5/323 , F01D5/3038 , F01D5/32 , F01D5/326 , F04D29/322
摘要： A blade arrangement is provided having a blade carrier and a retaining groove arranged therein, which retaining groove has projections extending along side walls thereof forming undercuts and into which a number of blades are inserted forming a blade ring of a turbomachine. Each blade has a blade root which engages into the undercuts, and each blade is pressed against the projections by an element arranged between a blade root underside and a groove base of the retaining groove. It is further provided that each element is of plate-like form and has, in the projection of the blade airfoil in the direction of the groove base, at least one bead, arranged beneath the blade airfoil, for imparting a pressing action, and in the longitudinal direction of the retaining groove, only part of the blade root which the element presses against is covered.
摘要翻译：叶片装置设置有叶片载体和布置在其中的保持槽，该保持槽具有沿其侧壁延伸的突起形成底切，并且多个叶片插入该叶片中形成涡轮机的叶片环。每个叶片具有啮合到底切部分中的叶片根部，并且每个叶片通过设置在保持槽的叶片根部下侧和凹槽基部之间的元件压靠在突起部上。进一步地，每个元件都是板状的，并且在叶片翼型件沿凹槽底座的方向的突起中具有布置在叶片翼型之下的至少一个珠，用于施加压力，并且在保持槽的纵向方向仅覆盖元件压靠的叶片根部的一部分。

3. 发明授权

US09708919B2 Blade arrangement 有权
公开(公告)号：US09708919B2
公开(公告)日：2017-07-18
申请号：US14239138
申请日：2012-08-14
申请人： Sascha Dungs , Elliot Griffin , Markus Paus , Stefan Reichling , Uwe Sieber , Hubertus Michael Wigger , Dirk Wistuba
发明人： Sascha Dungs , Elliot Griffin , Markus Paus , Stefan Reichling , Uwe Sieber , Hubertus Michael Wigger , Dirk Wistuba
IPC分类号： F01D5/32 , F01D5/30 , F04D29/32
CPC分类号： F01D5/323 , F01D5/3038 , F01D5/32 , F01D5/326 , F04D29/322
摘要： A blade arrangement is provided having a blade carrier and a retaining groove arranged therein, which retaining groove has projections extending along side walls thereof forming undercuts and into which a number of blades are inserted forming a blade ring of a turbomachine. Each blade has a blade root which engages into the undercuts, and each blade is pressed against the projections by an element arranged between a blade root underside and a groove base of the retaining groove. It is further provided that each element is of plate-like form and has, in the projection of the blade airfoil in the direction of the groove base, at least one bead, arranged beneath the blade airfoil, for imparting a pressing action, and in the longitudinal direction of the retaining groove, only part of the blade root which the element presses against is covered.

4. 发明申请

US20130101422A1 FASTENING ASSEMBLY FOR BLADES OF TURBOMACHINES HAVING AXIAL FLOW AND METHOD FOR PRODUCING SUCH AN ASSEMBLY 审中-公开
标题翻译：具有轴向流动的涡轮机叶片的紧固件组件和用于生产这种组件的方法
公开(公告)号：US20130101422A1
公开(公告)日：2013-04-25
申请号：US13696618
申请日：2011-05-11
申请人： Patrick Bullinger , Marco Link , Nicolas Savilius , Uwe Sieber , Hubertus Michael Wigger
发明人： Patrick Bullinger , Marco Link , Nicolas Savilius , Uwe Sieber , Hubertus Michael Wigger
IPC分类号： F01D5/30
CPC分类号： F01D5/30 , F01D5/3007 , F01D5/3053 , F01D5/323 , F01D9/042 , F04D29/322 , F05B2240/94 , F05D2230/60 , F05D2230/64 , F05D2230/70 , F05D2240/91 , Y10T29/49321
摘要： A fastening assembly for blades of turbomachines through which axial flow can take place, preferably compressors, includes a blade carrier having a lateral face, in which retaining groves are distributed along the circumference, with blades being inserted in the grooves, wherein a resilient tensioning element is provided between each groove base and the underside of the respective blade foot, the underside being located opposite of the groove base. The tensioning element is supported on the respective underside and on the respective groove base in a pretensioning manner, wherein a channel is provided both in the groove base and in the underside, with the tensioning element resting in the channels.
摘要翻译：一种用于涡轮机叶片的紧固组件，通过其可以发生轴向流动，优选地，压缩机包括具有侧面的叶片载体，其中保持槽沿着圆周分布，其中叶片插入槽中，其中弹性张紧元件设置在每个凹槽底部和相应的叶片脚的下侧之间，下侧位于凹槽底部的相对侧。张紧元件以预张紧的方式支撑在相应的下侧和相应的槽底部上，其中在槽底部和下侧都设有通道，张紧元件位于通道中。

5. 发明申请

US20110286851A1 Guide blade arrangement for an axial turbo-machine 审中-公开
标题翻译：用于轴向涡轮机的导向叶片装置
公开(公告)号：US20110286851A1
公开(公告)日：2011-11-24
申请号：US13132339
申请日：2009-11-02
申请人： Francois Benkler , Raoul Costamagna , Bernward Mertens , Uwe Sieber
发明人： Francois Benkler , Raoul Costamagna , Bernward Mertens , Uwe Sieber
IPC分类号： F01D5/14
CPC分类号： F01D9/042
摘要： A guide blade arrangement for an axial turbo-machine is provided. The guide blade arrangement includes at least one annular guide blade carrier and an inner ring arranged concentrically with respect to the guide blade carrier, between which guide blade carrier and inner ring a number of guide blades are arranged in a radial configuration. To obtain a low-wear and particularly durable fastening of the guide blade, which is supported by the guide blade carrier, to the inner ring, it is proposed that the guide blades are fastened resiliently to the inner ring. Here, the fastening is provided by means of a spring element. By means of the spring element, it is possible to ensure a uniform contact pressure of the guide blade head against the inner ring or if appropriate against a further spring element, such that occurring stresses and wear can be reduced.
摘要翻译：提供了一种用于轴向涡轮机的导向叶片装置。导向叶片装置包括至少一个环形引导叶片载体和相对于导向叶片载体同心布置的内环，引导叶片载体和内环之间以多个引导叶片布置成径向构型。为了获得由导向叶片载体支撑的导向叶片的低磨损且特别耐用的紧固件到内圈，建议将引导片弹性地紧固到内圈。这里，通过弹簧元件提供紧固件。通过弹簧元件，可以确保导向叶片头部相对于内环的接触压力均匀，或者适当地抵靠另一个弹簧元件，从而可以减少发生的应力和磨损。

6. 发明申请

US20090290974A1 Annular Flow Duct for a Turbomachine Through which a Main Flow can Flow in the Axial Direction 有权
标题翻译：一个涡轮机的环形流道，主流通过该流道可以在轴向流动
公开(公告)号：US20090290974A1
公开(公告)日：2009-11-26
申请号：US12227928
申请日：2007-05-29
申请人： Romain Bayere , Malte Blomeyer , Christian Cornelius , Torsten Matthias , Uwe Sieber
发明人： Romain Bayere , Malte Blomeyer , Christian Cornelius , Torsten Matthias , Uwe Sieber
IPC分类号： F04D27/02 , F04D29/68
CPC分类号： F01D5/145 , F01D5/143 , F04D29/526 , F04D29/685
摘要： Disclosed is an annular flow duct for a turbomachine, the flow duct arranged concentrically about a machine axis running in the axial direction and defined by a boundary wall of circular cross section for directing a main flow, wherein the boundary wall has a plurality of return flow passages distributed over its circumference and through which in each case a partial flow is detached from the main flow at a bleed position and returned to the main flow at a feed position situated upstream of the bleed position, and having aerofoils, arranged radically in the flow duct, of a blade ring, the aerofoil tips of which lie opposite the boundary wall, with a gap formed in each case, wherein the aerofoils are movable in a predetermined rotation direction along the circumference of the boundary wall. Furthermore, a compressor which is insensitive to pumping and flow separations, as viewed in rotation direction, the bleed position of each return flow passage lies upstream of the corresponding feed position.
摘要翻译：公开了一种用于涡轮机的环形流动管道，该流动管道围绕沿着轴向运动的机器轴线同心地布置并且由用于引导主流量的圆形横截面的边界壁限定，其中边界壁具有多个回流分布在其圆周上的通道，并且在每种情况下，部分流动在出口位置处与主流体分离，并且在位于排放位置上游的进给位置处返回到主流体，并且具有从根本上排列在流体中的机翼一个叶片环的管道，其机翼尖头与边界壁相对，在每种情况下形成间隙，其中翼型件可沿着边界壁的圆周沿预定的旋转方向移动。此外，从旋转方向观察对泵送和流动分离不敏感的压缩机，每个返回流动通道的排放位置位于相应进给位置的上游。

7. 发明授权

US08066471B2 Annular flow duct for a turbomachine through which a main flow can flow in the axial direction 有权
标题翻译：用于涡轮机的环形流道，主流通过该流道可沿轴向流动
公开(公告)号：US08066471B2
公开(公告)日：2011-11-29
申请号：US12227928
申请日：2007-05-29
申请人： Romain Bayere , Malte Blomeyer , Christian Cornelius , Torsten Matthias , Uwe Sieber
发明人： Romain Bayere , Malte Blomeyer , Christian Cornelius , Torsten Matthias , Uwe Sieber
IPC分类号： F04D27/02
CPC分类号： F01D5/145 , F01D5/143 , F04D29/526 , F04D29/685
摘要： Disclosed is an annular flow duct for a turbomachine, the flow duct arranged concentrically about a machine axis running in the axial direction and defined by a boundary wall of circular cross section for directing a main flow, wherein the boundary wall has a plurality of return flow passages distributed over its circumference and through which in each case a partial flow is detached from the main flow at a bleed position and returned to the main flow at a feed position situated upstream of the bleed position, and having aerofoils, arranged radically in the flow duct, of a blade ring, the aerofoil tips of which lie opposite the boundary wall, with a gap formed in each case, wherein the aerofoils are movable in a predetermined rotation direction along the circumference of the boundary wall. Furthermore, a compressor which is insensitive to pumping and flow separations, as viewed in rotation direction, the bleed position of each return flow passage lies upstream of the corresponding feed position.
摘要翻译：公开了一种用于涡轮机的环形流动管道，该流动管道围绕沿着轴向运动的机器轴线同心地布置并且由用于引导主流量的圆形横截面的边界壁限定，其中边界壁具有多个回流分布在其圆周上的通道，并且在每种情况下，部分流动在出口位置处与主流体分离，并且在位于排放位置上游的进给位置处返回到主流体，并且具有从根本上排列在流体中的机翼一个叶片环的管道，其机翼尖头与边界壁相对，在每种情况下形成间隙，其中翼型件可沿着边界壁的圆周沿预定的旋转方向移动。此外，从旋转方向观察对泵送和流动分离不敏感的压缩机，每个返回流动通道的排放位置位于相应进给位置的上游。

8. 发明申请

US20140193241A1 INTERNALLY COOLABLE COMPONENT FOR A GAS TURBINE WITH AT LEAST ONE COOLING DUCT 有权
标题翻译：用于具有至少一个冷却导管的气体涡轮机的内部可冷却部件
公开(公告)号：US20140193241A1
公开(公告)日：2014-07-10
申请号：US14237871
申请日：2012-08-02
申请人： Marcel Eifel , Daniel Gloss , Andreas Heselhaus , Stephan Klumpp , Marco Link , Uwe Sieber , Stefan Volker , Michael Wagner
发明人： Marcel Eifel , Daniel Gloss , Andreas Heselhaus , Stephan Klumpp , Marco Link , Uwe Sieber , Stefan Volker , Michael Wagner
IPC分类号： F02C7/12
CPC分类号： F01D5/187 , F02C7/12 , F05D2260/22141
摘要： An internally coolable component for a gas turbine with at least one cooling duct, on the inner surface of which swirl elements are arranged in the form of turbulators which extend transversely with respect to the main flow direction of a coolant is provided. In order to reduce pressure losses for the coolant in the cooling duct, pins with different heights are set up between the turbulators.
摘要翻译：提供了一种用于具有至少一个冷却管道的燃气轮机的内部可冷却部件，其内表面上设置有相对于冷却剂的主流动方向横向延伸的涡流体形式的涡流元件。为了减少冷却管道中的冷却剂的压力损失，在湍流器之间建立具有不同高度的销。

9. 发明申请

US20110052397A1 Stator Blade for a Turbomachine which is Exposable to Axial Throughflow, and also Stator Blade Arrangement for It 失效
标题翻译：可用于轴向通流的涡轮机的定子叶片，以及它的定子叶片布置
公开(公告)号：US20110052397A1
公开(公告)日：2011-03-03
申请号：US12868946
申请日：2010-08-26
申请人： Bernhard Kusters , Marc Mittelbach , Uwe Sieber , Ulrich Waltke , Dirk Wistuba
发明人： Bernhard Kusters , Marc Mittelbach , Uwe Sieber , Ulrich Waltke , Dirk Wistuba
IPC分类号： B64C11/06
CPC分类号： F01D5/3038 , F01D5/32 , F01D9/042 , F04D29/542 , F04D29/644
摘要： A stator blade and a stator blade arrangement for a turbomachine which is exposable to axial throughflow is provided. Each stator blade is retained via a fixed clamping in a circumferential groove. For the fixed clamping, provision is made on one side of the blade root for a shaped piece with a threaded hole into which a tensioning screw, which is supported on the bottom of the circumferential groove, may be screwed.
摘要翻译：提供了可暴露于轴向通流的涡轮机的定子叶片和定子叶片装置。每个定子叶片通过固定的夹紧保持在圆周槽中。对于固定夹紧，在叶片根部的一侧设置具有螺纹孔的成形件，支撑在周向槽的底部上的张紧螺钉可被拧入到该螺纹孔中。

10. 发明授权

US09574449B2 Internally coolable component for a gas turbine with at least one cooling duct 有权
标题翻译：具有至少一个冷却管道的燃气轮机的内部可冷却部件
公开(公告)号：US09574449B2
公开(公告)日：2017-02-21
申请号：US14237871
申请日：2012-08-02
申请人： Marcel Eifel , Daniel Gloss , Andreas Heselhaus , Stephan Klumpp , Marco Link , Uwe Sieber , Stefan Volker , Michael Wagner
发明人： Marcel Eifel , Daniel Gloss , Andreas Heselhaus , Stephan Klumpp , Marco Link , Uwe Sieber , Stefan Volker , Michael Wagner
IPC分类号： F01D5/18 , F02C7/12
CPC分类号： F01D5/187 , F02C7/12 , F05D2260/22141
摘要： An internally coolable component for a gas turbine with at least one cooling duct, on the inner surface of which swirl elements are arranged in the form of turbulators which extend transversely with respect to the main flow direction of a coolant is provided. In order to reduce pressure losses for the coolant in the cooling duct, pins with different heights are set up between the turbulators.
摘要翻译：提供了一种用于具有至少一个冷却管道的燃气轮机的内部可冷却部件，其内表面上设置有相对于冷却剂的主流动方向横向延伸的涡流体形式的涡流元件。为了减少冷却管道中的冷却剂的压力损失，在湍流器之间建立具有不同高度的销。

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