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1. 发明申请

US20120328446A1 TURBINE AIRFOIL OF COMPOSITE MATERIAL AND METHOD OF MANUFACTURING THEREOF 审中-公开
标题翻译：复合材料的涡轮机空气及其制造方法
公开(公告)号：US20120328446A1
公开(公告)日：2012-12-27
申请号：US13525149
申请日：2012-06-15
申请人： Rolf Hunziker , Said Havakechian
发明人： Rolf Hunziker , Said Havakechian
IPC分类号： F01D5/14 , B23P15/04
CPC分类号： F01D5/282 , F01D5/147 , F01D5/286 , F01D5/288 , F05D2230/23 , F05D2230/60 , F05D2230/90 , F05D2240/301 , F05D2260/95 , Y02T50/672 , Y02T50/673 , Y10T29/49337
摘要： A turbine blade having a root and a tip and an airfoil with a core section made of composite material and a protective sheath or layer joined to the composite core at a location or locations exposed to erosion is described with the composite core of the airfoil being continuous from a location in vicinity of the root to a location in vicinity of the tip of the blade and including a section which widens with distance from the rotational axis along the length of the airfoil and which ends at the location in vicinity of the tip of the blade. The protective sheath or layer is secured by interference fit with widening section of the core.
摘要翻译：具有根部和尖端的涡轮机叶片和具有由复合材料制成的芯部的翼型以及在暴露于侵蚀的位置或位置处接合到复合芯的保护性护套或层被描述，翼型的复合芯线是连续的从根部附近的位置到叶片尖端附近的位置，并且包括沿着翼型件的长度与旋转轴线的距离变宽的部分，并且在该端部附近的位置处终止刀。保护套或层通过与芯的加宽部分的过盈配合来固定。

2. 发明申请

US20070207032A1 Turbine 失效
标题翻译：涡轮
公开(公告)号：US20070207032A1
公开(公告)日：2007-09-06
申请号：US11743211
申请日：2007-05-02
申请人： Ralf Greim , Said Havakechian
发明人： Ralf Greim , Said Havakechian
IPC分类号： F01D1/02
CPC分类号： F01D1/06 , F01D1/04 , F01D5/28 , F05D2220/31 , Y10T29/4932
摘要： A turbine (100) of a turbine installation, especially a steam turbine of a steam turbine installation, includes at least one radial or diagonal turbine stage (120) with radial or diagonal inflow and axial outflow, and also at least one axial turbine stage (121-125) with axial inflow and axial outflow. The at least one radial or diagonal turbine stage (120) forms the first stage of the turbine (100) and the at least one axial turbine stage (121-125) is arranged downstream of the radial or diagonal turbine stage (121) as an additional stage of the turbine. The at least one radial or diagonal turbine stage (120) has a higher temperature resistance than the at least one axial turbine stage (121-125). The turbine (100) makes it possible to significantly increase the process temperature of the steam turbine installation, wherein measures for increasing the temperature resistance need only to be adopted for components of the radial or diagonal turbine stage (120).
摘要翻译：涡轮机设备的涡轮（100），特别是蒸汽涡轮机设备的蒸汽涡轮机，包括具有径向或对角线流入和轴向流出的至少一个径向或对角涡轮机台（120），并且还包括至少一个轴向涡轮机台 121 - 125）轴向流入和轴向流出。至少一个径向或对角涡轮机台（120）形成涡轮机（100）的第一级，并且至少一个轴向涡轮机台（121-125）布置在径向或对角涡轮机台（121）的下游，作为涡轮机的附加阶段。所述至少一个径向或对角涡轮机台（120）具有比所述至少一个轴向涡轮机台（121-125）更高的耐温性。涡轮（100）使得可以显着增加蒸汽轮机设备的过程温度，其中仅用于径向或对角涡轮机台（120）的部件的增加耐温性的措施。

3. 发明授权

US08221065B2 Turbomachine blade with variable chord length 有权
标题翻译：具有可变弦长度的涡轮机叶片
公开(公告)号：US08221065B2
公开(公告)日：2012-07-17
申请号：US12078965
申请日：2008-04-08
申请人： Ralf Greim , Said Havakechian , Ivan McBean , Simon-Pierre Monette
发明人： Ralf Greim , Said Havakechian , Ivan McBean , Simon-Pierre Monette
IPC分类号： F01D5/14 , F01D1/02 , F01D5/02
CPC分类号： F01D5/141 , F05D2220/31 , F05D2240/12 , F05D2240/301 , Y10S416/02 , Y10S416/05
摘要： A blade of a turbomachine, especially of a steam turbine, is characterized in that the chord length (sm) in the middle region of the blade airfoil is shorter than the chord lengths (s0, S1) in the tip-side region or root-side region of the blade airfoil. As a result of this, a distribution of a Zweifel parameter over the longitudinal extent of the blade airfoil is achieved which minimizes the losses of a blade cascade of the blades.
摘要翻译：涡轮机的叶片，特别是蒸汽轮机的特征在于，叶片翼型的中间区域中的弦长（sm）比尖端侧区域或根部的翼弦长度（s0，S1）短，叶片翼型的侧面区域。作为其结果，实现了在叶片翼型的纵向范围上的Zweifel参数的分布，其使叶片的叶片级联的损耗最小化。

4. 发明申请

US20110164970A1 Stator blade for a turbomachine, especially a stream turbine 审中-公开
标题翻译：用于涡轮机的定子叶片，特别是流轮机
公开(公告)号：US20110164970A1
公开(公告)日：2011-07-07
申请号：US12929047
申请日：2010-12-23
申请人： Ralf Greim , Said Havakechian , Mourad Lakehel , Carsten Mumm
发明人： Ralf Greim , Said Havakechian , Mourad Lakehel , Carsten Mumm
IPC分类号： F01D9/02
CPC分类号： F01D5/141 , F01D9/041 , F05D2220/72 , F05D2240/301 , F05D2250/20 , F05D2250/71
摘要： The invention relates to a stator blade (4) of a turbomachine, especially of a steam turbine, which has the following geometric features. A lean curvature, a swept curvature, a twist in the radial direction of the respective blade (4), a hub-side circumferential step (14) which in the direction of flow (15) falls away inwards and radially to the rotational axis (8) of the turbomachine, a chord length (s) of the blade which varies over the radial extent of the stator blade (4), and also a cross-sectional profile of the blade (4) which varies over the radial extent of the stator blade (4).
摘要翻译：本发明涉及一种具有以下几何特征的涡轮机的特别是汽轮机的定子叶片（4）。倾斜曲率，扫掠曲率，在相应叶片（4）的径向方向上的扭转;沿着流动方向（15）的轮毂侧圆周台阶（14）向内并径向向旋转轴线该涡轮机的一个或多个弦长在定子叶片（4）的径向范围内变化，以及叶片（4）的横截面轮廓，其在径向范围内变化定子叶片（4）。

5. 发明申请

US20110064560A1 AXIAL TURBINE AND METHOD FOR DISCHARGING A FLOW FROM AN AXIAL TURBINE 有权
标题翻译：轴流涡轮机和从轴向涡轮机排放流量的方法
公开(公告)号：US20110064560A1
公开(公告)日：2011-03-17
申请号：US12880240
申请日：2010-09-13
申请人： Said Havakechian , Thomas Mokulys , Vishal Borikar , Patrick Vu
发明人： Said Havakechian , Thomas Mokulys , Vishal Borikar , Patrick Vu
IPC分类号： F04D27/02 , F04D25/16
CPC分类号： F01D25/30 , F01D9/04 , F05D2220/31
摘要： An axial turbine (1) has a plurality of expansion stages (2) each defined by stator blades (13) and rotor blades. The expansion stages (2) are followed by an exhaust diffuser (4) for collecting the flow passing through the expansion stages (2) and discharging it to the outside. The expansion stages (2) and/or the diffuser (4) have at least a non-axial symmetric portion. The stator blades (13) define different openings (17) along the circumference of the turbine.
摘要翻译：轴流式涡轮机（1）具有多个由定子叶片（13）和转子叶片限定的膨胀级（2）。膨胀级（2）之后是排气扩散器（4），用于收集通过膨胀级（2）的流量并将其排出到外部。膨胀级（2）和/或扩散器（4）至少具有非轴对称部分。定子叶片（13）沿涡轮的圆周限定不同的开口（17）。

6. 发明申请

US20100303627A1 TURBINE STAGE 审中-公开
标题翻译：涡轮舞台
公开(公告)号：US20100303627A1
公开(公告)日：2010-12-02
申请号：US12792352
申请日：2010-06-02
申请人： Benjamin MEGERLE , Thomas MOKULYS , Said HAVAKECHIAN
发明人： Benjamin MEGERLE , Thomas MOKULYS , Said HAVAKECHIAN
IPC分类号： F01D5/22 , F04D29/54
CPC分类号： F01D5/143 , F01D5/145 , F05D2250/611 , F05D2250/71
摘要： A turbine stage includes a circumferentially distributed row of adjacent airfoils between which there is a flow passage. The passage has a surface, which in its unmodified form, defines a datum plane. A channel, located in the passage, extends in the direction of an airfoil pressure face from a point towards a leading edge line to a point towards a trailing edge line. The channel includes two channel walls angled relative to the datum plane. Relative to the datum plane, the channel has a low point, two high points, and a channel height, which is measured between the low point and the highest one of the high points. The channel provides a means to reduce secondary flow losses.
摘要翻译：涡轮级包括相邻翼型件的周向分布的行，在其之间具有流动通道。通道具有表面，其以未修改的形式定义基准平面。位于通道中的通道沿翼型压力面的方向从一个点朝向前缘线延伸到一个朝向后缘线的点。通道包括相对于基准面成角度的两个通道壁。相对于基准平面，通道具有低点，两个高点和通道高度，其在低点和最高点之一之间测量。该通道提供减少二次流量损失的方法。

7. 发明授权

US07320574B2 Turbomachine 有权
标题翻译：涡轮机
公开(公告)号：US07320574B2
公开(公告)日：2008-01-22
申请号：US10936582
申请日：2004-09-09
申请人： Ralf Greim , Said Havakechian , Axel Pfau
发明人： Ralf Greim , Said Havakechian , Axel Pfau
IPC分类号： F01D11/08
CPC分类号： F01D11/02 , F01D5/225 , F01D11/08 , F05D2240/11 , F05D2250/183 , F05D2250/184 , F05D2250/611 , F05D2250/70
摘要： A turbomachine has, on its inner casing (5) and on its shaft, recesses into which shrouds of rotor blades and/or of guide vanes (2a) protrude. The recesses are configured with wave-shaped contouring arrangements (10), which extend over their periphery. The contouring (10) extends over axially extending regions of the recess and consists of periodic elevations and depressions (14, 15) in the radial direction. They can also be effected on the radially extending regions of the recess and on the shrouds. The undulation-shaped contouring arrangements are used to counteract existing pressure fields and to reduce performance losses due to mixing processes between the leakage flow and the main flow.
摘要翻译：涡轮机在其内壳体（5）上及其轴上具有凹口，转子叶片和/或导向叶片（2a）的护罩突出到其中。所述凹部配置有在其周边上延伸的波形轮廓布置（10）。轮廓（10）在凹部的轴向延伸区域上延伸，并且包括在径向方向上的周期性高度和凹陷（14,15）。它们也可以在凹部的径向延伸区域和护罩上进行。波浪形轮廓布置用于抵消现有的压力场并且减少由于泄漏流和主流之间的混合过程引起的性能损失。

8. 发明授权

US06270315B1 Highly loaded turbine blading 有权
标题翻译：高负荷涡轮叶片
公开(公告)号：US06270315B1
公开(公告)日：2001-08-07
申请号：US09395562
申请日：1999-09-14
申请人： Ralf Greim , Said Havakechian , Harald Romer , Peter Szincsak
发明人： Ralf Greim , Said Havakechian , Harald Romer , Peter Szincsak
IPC分类号： F01D900
CPC分类号： F01D5/06 , F01D5/00 , Y10S416/02 , Y10S416/05
摘要： To reduce the number of stages of a turbine and, associated therewith, the overall length and the costs, blading having high stage-specific enthalpy transfer is to be used. In this case, the disadvantages of conventional highly loaded blading, such as increased secondary flow losses due to blades of large chord length and comparatively small height and the design of the turbine in the complicated chamber type of construction, are to be avoided. Resulting from these requirements is a highly loaded slim blade type of construction having considerable deflection. A turbine having blading according to the invention is characterized by a loading parameter RBL, which in the HRBL blading according to the invention, in contrast to conventional types of construction, is greater than 1.
摘要翻译：为了减少涡轮机的级数，并且与其相关联的总长度和成本，将使用具有高阶段特定焓传递的叶片。在这种情况下，要避免常规高负载叶片的缺点，例如由于大弦长和较小高度的叶片所引起的二次流动损失增加，以及复杂室型结构中涡轮机的设计。由这些要求导致的是具有相当大偏转的高负载薄型结构。根据本发明的具有叶片的涡轮机的特征在于加载参数RBL，其在根据本发明的HRBL叶片中与常规类型的结构相比大于1。

9. 发明授权

US5228833A Turbomachine blade/vane for subsonic conditions 失效
标题翻译：涡轮叶片/ VANE用于子午线条件
公开(公告)号：US5228833A
公开(公告)日：1993-07-20
申请号：US902738
申请日：1992-06-23
申请人： Martin Schonenberger , Ulrich Steiger , Said Havakechian , Nils Lannefors
发明人： Martin Schonenberger , Ulrich Steiger , Said Havakechian , Nils Lannefors
IPC分类号： F01D5/14
CPC分类号： F01D5/141 , F01D5/145 , Y10S415/914
摘要： In a turbomachine blade/vane for subsonic conditions with a convex curvature profile contour in the region of the leading edge and over the major part of the suction surface (S) and with a concave curvature profile contour in the region of the pressure surface (D), the profile contour in the suction-surface trailing edge region is designed to be concave (K). The momentum loss thickness mainly responsible for the profile loss is reduced in this region.
摘要翻译：在用于亚音速条件的涡轮机叶片/叶片中，在前缘和吸力表面（S）的主要部分的区域中具有凸曲率轮廓轮廓，并且在压力表面（D）的区域中具有凹曲率轮廓轮廓），吸表面后缘区域中的轮廓轮廓被设计为凹（K）。在这个地区，主要负责轮廓损失的动量损失厚度减小。

10. 发明授权

US08506233B2 Axial turbine and method for discharging a flow from an axial turbine 有权
标题翻译：轴流式涡轮机和用于从轴向涡轮机排出流量的方法
公开(公告)号：US08506233B2
公开(公告)日：2013-08-13
申请号：US12880240
申请日：2010-09-13
申请人： Said Havakechian , Thomas Mokulys , Vishal Borikar , Patrick Vu
发明人： Said Havakechian , Thomas Mokulys , Vishal Borikar , Patrick Vu
IPC分类号： F04D27/02
CPC分类号： F01D25/30 , F01D9/04 , F05D2220/31
摘要： An axial turbine (1) has a plurality of expansion stages (2) each defined by stator blades (13) and rotor blades. The expansion stages (2) are followed by an exhaust diffuser (4) for collecting the flow passing through the expansion stages (2) and discharging it to the outside. The expansion stages (2) and/or the diffuser (4) have at least a non-axial symmetric portion. The stator blades (13) define different openings (17) along the circumference of the turbine.
摘要翻译：轴流式涡轮机（1）具有多个由定子叶片（13）和转子叶片限定的膨胀级（2）。膨胀级（2）之后是排气扩散器（4），用于收集通过膨胀级（2）的流量并将其排出到外部。膨胀级（2）和/或扩散器（4）至少具有非轴对称部分。定子叶片（13）沿涡轮的圆周限定不同的开口（17）。

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