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1. 发明申请

US20110188999A1 Axial turbine for a gas turbine with limited play between blades and housing 审中-公开
标题翻译：用于燃气轮机的轴向涡轮机，叶片和壳体之间的间隙有限
公开(公告)号：US20110188999A1
公开(公告)日：2011-08-04
申请号：US13054162
申请日：2009-07-08
申请人： Stefan Braun , Christian Cornelius , Annika Emde , Andreas Heilos , Olaf Hein , Thomas Hofbauer , Christian Lerner , Silvio-Ulrich Martin , Thorsten Mattheis , Ralf Müsgen , Eckart Schumann , Rostislav Teteruk , Adam Zimmermann
发明人： Stefan Braun , Christian Cornelius , Annika Emde , Andreas Heilos , Olaf Hein , Thomas Hofbauer , Christian Lerner , Silvio-Ulrich Martin , Thorsten Mattheis , Ralf Müsgen , Eckart Schumann , Rostislav Teteruk , Adam Zimmermann
IPC分类号： F01D11/00
CPC分类号： F01D5/20 , F01D5/141 , F01D5/143
摘要： An axial turbine for a gas turbine including a rotor blade cascade is provided. The rotor blade cascade is formed from rotor blades each including, a front edge, a blade tip, and an annular space wall that surrounds the rotor blade cascade and includes an annular space inner side, enabling the annular space wall to be arranged directly adjacent to the blade tip forming a radial gap between the covering of the blade tip and the annual space inner side. When the turbine is in operation, the area of the blade tip with the highest pressure load is disposed in the region of the front edges, and the rotor blades in the region of their front edges include a radial projection and the annular space wall includes on the annular space inner side, a peripheral radial recess that interacts with the radial projections such that a minimum is established in the direction of the main through-flow of the turbine.
摘要翻译：提供了一种用于包括转子叶片级联的燃气轮机的轴向涡轮机。转子叶片级联由转子叶片形成，每个转子叶片包括前缘，叶片尖端和围绕转子叶片级联的环形空间壁，并且包括环形空间内侧，使得环形空间壁能够直接邻近叶片尖端在叶片尖端的覆盖物和年度空间内侧之间形成径向间隙。当涡轮机运行时，具有最高压力负载的叶片尖端的区域设置在前边缘的区域中，并且其前边缘区域中的转子叶片包括径向突起，并且环形空间壁包括在环形空间内侧，与径向突起相互作用的周向径向凹部，使得在涡轮机的主通流方向上建立最小值。

2. 发明授权

US08721273B2 Ring diffuser for an axial turbomachine 有权
标题翻译：用于轴向涡轮机的环形扩散器
公开(公告)号：US08721273B2
公开(公告)日：2014-05-13
申请号：US13351475
申请日：2012-01-17
申请人： Christian Cornelius , Bernhard Küsters , Ulrich Waltke
发明人： Christian Cornelius , Bernhard Küsters , Ulrich Waltke
IPC分类号： F01D9/04 , F04D29/54
CPC分类号： F01D5/143 , F01D5/145 , F05D2250/184 , Y02T50/673
摘要： An arrangement with a ring diffuser for an axial turbomachine, for example for a gas turbine, is provided. The ring diffuser includes an outer wall and with an inner wall coaxial thereto, between which a diffuser duct extends in ring form along an axial extent so as to diverge from an inflow-side end to an outflow-side end, the inner wall and the outer wall in each case including a wall surface delimiting the diffuser duct. In order to specify a diffuser duct which is adapted to an inflow uneven along the circumference and by means of which a specially efficient conversion of kinetic energy into static energy is possible, the wall surface which delimits the diffuser duct on the inlet side is rotationally asymmetrical.
摘要翻译：提供了一种用于轴向涡轮机的环形扩散器的装置，例如用于燃气轮机。环形扩散器包括外壁和与其同轴的内壁，扩散管之间沿轴向延伸成环形，从而从流入侧端部流出到流出侧端部，内壁和在每种情况下的外壁包括限定扩散管的壁面。为了指定适于沿着圆周不均匀的流入物的扩散器管道，并且通过该扩散管道将动能特别有效地转换成静态能量，限定入口侧的扩散管道的壁面是旋转不对称的。

3. 发明授权

US08951008B2 Compressor blade and production and use of a compressor blade 有权
标题翻译：压缩机叶片和压缩机叶片的生产和使用
公开(公告)号：US08951008B2
公开(公告)日：2015-02-10
申请号：US11659551
申请日：2005-06-20
申请人： Christian Cornelius , Bernhard Küsters , Stephan Mais , Andreas Peters , Achim Schirrmacher , Lutz Stephan , Bernd van den Toorn
发明人： Christian Cornelius , Bernhard Küsters , Stephan Mais , Andreas Peters , Achim Schirrmacher , Lutz Stephan , Bernd van den Toorn
IPC分类号： F01D5/20 , B23P15/04 , F01D11/08 , F01D5/12 , F04D29/16 , F04D29/32
CPC分类号： F04D29/164 , F01D5/20 , F04D29/324 , Y10T29/49321 , Y10T29/49336
摘要： The invention relates to a compressor blade of a compressor which, along a main axis, comprises a blade base, a platform area and an adjacent blade profile having a profile tip. The blade profile is configured by a convex wall at the suction end and a concave wall at the pressure end opposite the wall at the suction end. These surfaces extend, with respect to a flow medium, from a leading edge to a trailing edge, a profile center line extending in the center between the two. A front face is arranged on the profile tip at an angle to the main axis, a sealing lip at least partially extending from the leading edge to the trailing edge and the blade profile including the sealing lip having a blade profile height extending in the direction of the main axis. In order to allow for an inexpensive compressor blade having improved aerodynamic properties and a modified sealing lip while having the same sealing properties, the height of the sealing lip is less than 2 percent of the height of the blade profile.
摘要翻译：本发明涉及一种压缩机的压缩机叶片，其沿着主轴线包括叶片基座，平台区域和具有轮廓顶端的相邻叶片轮廓。叶片轮廓由吸入端处的凸壁和在吸力端处与壁相对的压力端处的凹壁构成。这些表面相对于流动介质从前缘延伸到后缘，在两者之间的中心延伸的轮廓中心线。一个前表面以与主轴成一定角度布置在轮廓尖端上，密封唇缘从前缘至后缘至少部分地延伸，并且包括密封唇的刀片轮廓具有沿着主轴线方向延伸的刀片轮廓高度主轴。为了允许具有改善的空气动力特性的廉价的压缩机叶片和改进的密封唇，同时具有相同的密封性能，密封唇的高度小于叶片轮廓的高度的2％。

4. 发明申请

US20120230834A1 COMPRESSOR BLADE FOR AN AXIAL COMPRESSOR 有权
标题翻译：压缩机叶片压缩机
公开(公告)号：US20120230834A1
公开(公告)日：2012-09-13
申请号：US13393264
申请日：2010-08-10
申请人： Christian Cornelius , Georg Kröger , Eberhard Nicke
发明人： Christian Cornelius , Georg Kröger , Eberhard Nicke
IPC分类号： F01D5/14
CPC分类号： F04D29/324 , F01D5/141 , F05D2250/711 , F05D2250/712 , Y10S416/02 , Y10S416/05
摘要： A compressor blade for an axially permeated compressor, preferably of a stationary gas turbine is provided. The camber line of the blade tip side profile of the blade of the compressor blade includes at least two inflection points for reducing radial gap losses. By means of two inflection points, there is a concavely designed suction side contour segment in a segment from 35% to 50% for the suction side contour, and a convexly implemented pressure side contour segment for the pressure side contour. It is possible by means of the geometry to generate low-loss gap vortices, in order to increase the overall efficiency of an axial compressor including the compressor blades.
摘要翻译：提供了用于轴向渗透的压缩机的压缩机叶片，优选地为固定式燃气轮机。压缩机叶片的叶片的叶片侧面轮廓的弯度线包括用于减小径向间隙损失的至少两个拐点。通过两个拐点，对于吸力侧轮廓，在凹部设计的吸力侧轮廓段中具有35％至50％的段，以及用于压力侧轮廓的凸形实施的压力侧轮廓段。为了提高包括压缩机叶片在内的轴向压缩机的整体效率，可以通过几何形状产生低损耗间隙涡流。

5. 发明授权

US09771803B2 Method for profiling a replacement blade as a replacement part for an old blade for an axial-flow turbomachine 有权
公开(公告)号：US09771803B2
公开(公告)日：2017-09-26
申请号：US14241485
申请日：2012-08-14
申请人： Christian Cornelius , Torsten Matthias
发明人： Christian Cornelius , Torsten Matthias
IPC分类号： F01D5/14 , F01D5/12 , B23P6/00 , F01D9/02
CPC分类号： F01D5/12 , B23P6/005 , F01D5/141 , F01D5/147 , F01D9/02 , F05D2230/80 , Y10T29/4932
摘要： A method for profiling a replacement blade for an axial turbomachine is provided. The method includes: measuring hub contour geometry and housing contour geometry of the flow channel of the old blade and the axial position of the centre of gravity of the blade aerofoil of the old blade; laying out geometry of the blade aerofoil of the replacement blade, the blade aerofoil having a rearward sweep on its leading edge; defining a region of the blade aerofoil near the mounting and in which positive influence of the rearward sweep on the degree of stage efficiency is rated as low; and axially displacing the replacement blade aerofoil section arranged outside this region in the upstream direction, until the axial position of the centre of gravity of the blade aerofoil of the replacement blade coincides with the old blade. In the region from the mounting-side section to the displaced blade aerofoil section of the replacement blade, the leading edge is inclined downstream towards the mounting such that the blade aerofoil has a transition sweep in this region.

6. 发明申请

US20140212282A1 METHOD FOR PROFILING A REPLACEMENT BLADE AS A REPLACEMENT PART FOR AN OLD BLADE FOR AN AXIAL-FLOW TURBOMACHINE 有权
标题翻译：将替代叶片分类为用于轴流式涡轮机的旧叶片的替换部件的方法
公开(公告)号：US20140212282A1
公开(公告)日：2014-07-31
申请号：US14241485
申请日：2012-08-14
申请人： Christian Cornelius , Torsten Matthias
发明人： Christian Cornelius , Torsten Matthias
IPC分类号： F01D5/12 , B23P6/00 , F01D9/02
CPC分类号： F01D5/12 , B23P6/005 , F01D5/141 , F01D5/147 , F01D9/02 , F05D2230/80 , Y10T29/4932
摘要： A method for profiling a replacement blade for an axial turbomachine is provided. The method includes: measuring hub contour geometry and housing contour geometry of the flow channel of the old blade and the axial position of the centre of gravity of the blade aerofoil of the old blade; laying out geometry of the blade aerofoil of the replacement blade, the blade aerofoil having a rearward sweep on its leading edge; defining a region of the blade aerofoil near the mounting and in which positive influence of the rearward sweep on the degree of stage efficiency is rated as low; and axially displacing the replacement blade aerofoil section arranged outside this region in the upstream direction, until the axial position of the centre of gravity of the blade aerofoil of the replacement blade coincides with the old blade. In the region from the mounting-side section to the displaced blade aerofoil section of the replacement blade, the leading edge is inclined downstream towards the mounting such that the blade aerofoil has a transition sweep in this region.
摘要翻译：提供了一种用于对用于轴向涡轮机的替换叶片进行成形的方法。该方法包括：测量轮毂轮廓几何形状和壳体轮廓几何形状的旧叶片的流道和叶片叶片的叶片重心的轴向位置; 布置替换叶片的叶片机翼的几何形状，叶片机翼在其前缘具有向后扫掠; 在安装附近限定叶片机翼的区域，其中向后扫掠的积极影响对于阶段效率的程度被评定为低; 并且沿上游方向轴向移动设置在该区域外的替换叶片翼型部分，直到替换叶片的叶片翼面的重心的轴向位置与旧叶片重合。在从安装侧部分到替换叶片的移动叶片翼型部分的区域中，前缘朝向安装件向下倾斜，使得叶片翼型件在该区域中具有过渡扫掠。

7. 发明申请

US20110189020A1 Axial turbo engine with low gap losses 有权
标题翻译：具有低间隙损失的轴流涡轮发动机
公开(公告)号：US20110189020A1
公开(公告)日：2011-08-04
申请号：US13054190
申请日：2009-07-08
申请人： Marcel Aulich , Christian Cornelius , Georg Kröger
发明人： Marcel Aulich , Christian Cornelius , Georg Kröger
IPC分类号： F01D5/22
CPC分类号： F01D5/20 , F01D5/143 , F01D5/145 , F01D11/08 , F05D2250/71 , Y02T50/671 , Y02T50/673
摘要： An axial turbomachine including a rotor blade cascade is provided. The rotor blade cascade includes rotor blades each including front edge, a radially outer free blade tip and an annular enclosure enclosing the rotor blade cascade with an annulus inner side by means of which the annular enclosure is arranged directly adjacent to the blade tips to give a radial gap between the enveloping ends of the blade tips and the annulus inner side. The rotor blades include a radial projection in the region of the front edge on the blade tip and the annular enclosure has an annular radial recess in the annulus inner side, arranged at a radial distance from the ends of the blade tips, such that in the main flow direction of the axial turbomachine the line of the radial projections on the side facing the radial gap matches the line of the radial recess.
摘要翻译：提供了包括转子叶片级联的轴向涡轮机。转子叶片级联包括转子叶片，每个转子叶片包括前边缘，径向外部自由叶片尖端和围绕转子叶片的环形壳体，其具有环形内侧，环形外壳直接布置在叶片尖端附近，以产生叶片尖端和环形内侧的包络端之间的径向间隙。转子叶片包括位于叶片尖端上的前边缘区域中的径向突出部分，并且环形壳体在环形内侧具有环形径向凹部，该叶片内侧面布置成距离叶片尖端端部的径向距离，使得在轴向涡轮机的主流动方向在面向径向间隙的一侧上的径向突起的线匹配径向凹槽的线。

8. 发明申请

US20110044800A1 Compressor Blade and Production and Use of a Compressor Blade 有权
标题翻译：压缩机叶片和压缩机叶片的生产和使用
公开(公告)号：US20110044800A1
公开(公告)日：2011-02-24
申请号：US11659551
申请日：2005-06-20
申请人： Christian Cornelius , Bernhard Küsters , Stephan Mais , Andreas Peters , Achim Schirrmacher , Lutz Stephan , Bernd van den Toorn
发明人： Christian Cornelius , Bernhard Küsters , Stephan Mais , Andreas Peters , Achim Schirrmacher , Lutz Stephan , Bernd van den Toorn
IPC分类号： F01D5/20 , F01D5/12 , B23P15/04 , F01D11/08
CPC分类号： F04D29/164 , F01D5/20 , F04D29/324 , Y10T29/49321 , Y10T29/49336
摘要： The invention relates to a compressor blade of a compressor which, along a main axis, comprises a blade base, a platform area and an adjacent blade profile having a profile tip. The blade profile is configured by a convex wall at the suction end and a concave wall at the pressure end opposite the wall at the suction end. These surfaces extend, with respect to a flow medium, from a leading edge to a trailing edge, a profile center line extending in the center between the two. A front face is arranged on the profile tip at an angle to the main axis, a sealing lip at least partially extending from the leading edge to the trailing edge and the blade profile including the sealing lip having a blade profile height extending in the direction of the main axis. In order to allow for an inexpensive compressor blade having improved aerodynamic properties and a modified sealing lip while having the same sealing properties, the height of the sealing lip is less than 2 percent of the height of the blade profile.
摘要翻译：本发明涉及一种压缩机的压缩机叶片，其沿着主轴线包括叶片基座，平台区域和具有轮廓顶端的相邻叶片轮廓。叶片轮廓由吸入端处的凸壁和在吸力端处与壁相对的压力端处的凹壁构成。这些表面相对于流动介质从前缘延伸到后缘，在两者之间的中心延伸的轮廓中心线。一个前表面以与主轴成一定角度布置在轮廓尖端上，密封唇缘从前缘至后缘至少部分地延伸，并且包括密封唇的刀片轮廓具有沿着主轴线方向延伸的刀片轮廓高度主轴。为了允许具有改善的空气动力特性的廉价的压缩机叶片和改进的密封唇，同时具有相同的密封性能，密封唇的高度小于叶片轮廓的高度的2％。

9. 发明授权

US08911215B2 Compressor blade for an axial compressor 有权
标题翻译：用于轴流式压缩机的压缩机叶片
公开(公告)号：US08911215B2
公开(公告)日：2014-12-16
申请号：US13393264
申请日：2010-08-10
申请人： Christian Cornelius , Georg Kröger , Eberhard Nicke
发明人： Christian Cornelius , Georg Kröger , Eberhard Nicke
IPC分类号： F01D5/14 , F04D29/32
CPC分类号： F04D29/324 , F01D5/141 , F05D2250/711 , F05D2250/712 , Y10S416/02 , Y10S416/05
摘要： A compressor blade for an axially permeated compressor, preferably of a stationary gas turbine is provided. The camber line of the blade tip side profile of the blade of the compressor blade includes at least two inflection points for reducing radial gap losses. By means of two inflection points, there is a concavely designed suction side contour segment in a segment from 35% to 50% for the suction side contour, and a convexly implemented pressure side contour segment for the pressure side contour. It is possible by means of the geometry to generate low-loss gap vortices, in order to increase the overall efficiency of an axial compressor including the compressor blades.
摘要翻译：提供了用于轴向渗透的压缩机的压缩机叶片，优选地为固定式燃气轮机。压缩机叶片的叶片的叶片侧面轮廓的弯度线包括用于减小径向间隙损失的至少两个拐点。通过两个拐点，对于吸力侧轮廓，在凹部设计的吸力侧轮廓段中具有35％至50％的段，以及用于压力侧轮廓的凸形实施的压力侧轮廓段。为了提高包括压缩机叶片在内的轴向压缩机的整体效率，可以通过几何形状产生低损耗间隙涡流。

10. 发明授权

US08647054B2 Axial turbo engine with low gap losses 有权
标题翻译：具有低间隙损失的轴流涡轮发动机
公开(公告)号：US08647054B2
公开(公告)日：2014-02-11
申请号：US13054190
申请日：2009-07-08
申请人： Marcel Aulich , Christian Cornelius , Georg Kröger
发明人： Marcel Aulich , Christian Cornelius , Georg Kröger
IPC分类号： F01D5/20
CPC分类号： F01D5/20 , F01D5/143 , F01D5/145 , F01D11/08 , F05D2250/71 , Y02T50/671 , Y02T50/673
摘要： An axial turbomachine including a rotor blade cascade is provided. The rotor blade cascade includes rotor blades each including front edge, a radially outer free blade tip and an annular enclosure enclosing the rotor blade cascade with an annulus inner side by means of which the annular enclosure is arranged directly adjacent to the blade tips to give a radial gap between the enveloping ends of the blade tips and the annulus inner side. The rotor blades include a radial projection in the region of the front edge on the blade tip and the annular enclosure has an annular radial recess in the annulus inner side, arranged at a radial distance from the ends of the blade tips, such that in the main flow direction of the axial turbomachine the line of the radial projections on the side facing the radial gap matches the line of the radial recess.
摘要翻译：提供了包括转子叶片级联的轴向涡轮机。转子叶片级联包括转子叶片，每个转子叶片包括前边缘，径向外部自由叶片尖端和围绕转子叶片的环形壳体，其具有环形内侧，环形外壳直接布置在叶片尖端附近，以产生叶片尖端和环形内侧的包络端之间的径向间隙。转子叶片包括位于叶片尖端上的前边缘区域中的径向突出部分，并且环形壳体在环形内侧具有环形径向凹部，该叶片内侧面布置成距离叶片尖端端部的径向距离，使得在轴向涡轮机的主流动方向在面向径向间隙的一侧上的径向突起的线匹配径向凹槽的线。

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