公开(公告)号：US20120007317A1

公开(公告)日：2012-01-12

申请号：US12832140

申请日：2010-07-08

申请人： Alexander R. Beeck

发明人： Alexander R. Beeck

IPC分类号： F02F11/00 ,  F16J15/44

CPC分类号： F16J15/3292 ,  F01D11/02 ,  F05D2240/57 ,  F05D2250/292 ,  F05D2250/314

摘要： A seal member for effecting a seal preventing fluid flow in an axial direction through an annular space formed between a rotatable shaft and a stator structure. The seal member includes a plurality of flexible seal strips extending radially through the annular space and having a radially outer end supported to the stator structure and a radially inner end defining a tip portion extending widthwise in the axial direction for engaging in sliding contact with a peripheral surface of the rotatable shaft. The seal strips are mounted to the stator structure with the tip portions of the seal strips at an angle to the axial direction. Each of the tip portions are formed with a curvature in a radially extending plane between a leading edge and a trailing edge of each seal strip.

摘要翻译： 一种用于实现密封的密封构件，其防止流体在轴向方向上流过形成在可旋转轴和定子结构之间的环形空间。 密封构件包括多个柔性密封条，其径向延伸穿过环形空间并且具有支撑到定子结构的径向外端，以及限定在轴向方向上沿宽度方向延伸的尖端部分的径向内端，用于与周边滑动接触 可旋转轴的表面。 密封条以与轴向方向成一定角度的方式安装到定子结构上。 每个尖端部分在每个密封条的前缘和后缘之间沿径向延伸的平面形成曲率。

公开(公告)号：US08047001B2

公开(公告)日：2011-11-01

申请号：US12226534

申请日：2007-03-09

申请人： Alexander R. Beeck ,  Stefan Hoffmann

发明人： Alexander R. Beeck ,  Stefan Hoffmann

IPC分类号： F02C3/16 ,  F02K3/08 ,  F01D9/06 ,  F23R3/28

CPC分类号： F23R3/14 ,  F01D5/18 ,  F01D9/065 ,  F02C3/16 ,  F02K3/08 ,  F02K3/10 ,  F23C2900/07001 ,  F23R3/286

摘要： The invention relates to a blade for a turbine comprising a blade wall, a first channel for guiding a first medium and a second channel for guiding a second medium that can be supplied to the turbine blade separately from the first medium. In order to combine both media, which are supplied separately, into one mixture, a turbine blade has least one chamber which is arranged in the interior or in the blade wall and said chamber is connected to said channels via a respective connection line. In order to provide a particularly simple component that is economical to produce, the chamber and/or the outlet conduit are a least partially delimited and/or formed by an insert accommodated in the wall.

摘要翻译： 本发明涉及一种用于涡轮机的叶片，其包括叶片壁，用于引导第一介质的第一通道和用于引导可与第一介质分开供应到涡轮叶片的第二介质的第二通道。 为了将分别供应的两种介质组合成一种混合物，涡轮机叶片具有布置在内部或叶片壁中的至少一个室，并且所述室经由相应的连接线连接到所述通道。 为了提供生产经济的特别简单的部件，腔室和/或出口导管由容纳在壁中的插入件至少部分地界定和/或形成。

公开(公告)号：US20110020113A1

公开(公告)日：2011-01-27

申请号：US12507203

申请日：2009-07-22

申请人： Alexander R. Beeck

发明人： Alexander R. Beeck

IPC分类号： F01D11/12

CPC分类号： F01D25/246 ,  F01D11/005 ,  F05D2240/57 ,  F05D2300/506

摘要： A seal structure is provided for preventing leakage of gases across a gap between first and second components in a turbine engine. The seal structure is adapted to be received in first and second adjacent slots provided in the first and second components. The seal structure may comprise: a wear resistant layer; and a deformable layer defined by a material having one of a varying density and a varying porosity.

摘要翻译： 提供密封结构，用于防止气体穿过涡轮发动机中的第一和第二部件之间的间隙泄漏。 密封结构适于容纳在设置在第一和第二部件中的第一和第二相邻槽中。 密封结构可以包括：耐磨层; 以及由具有不同密度和不同孔隙度之一的材料限定的可变形层。

公开(公告)号：US20080267771A1

公开(公告)日：2008-10-30

申请号：US12009314

申请日：2008-01-17

申请人： Alexander R. Beeck ,  Katharina Bergander ,  Georg Bostanjoglo ,  Tobias Buchal ,  Winfried Esser ,  Dirk Goldschmidt ,  Torsten Koch ,  Rudolf Kuperkoch ,  Thorsten Mattheis ,  Jan Munzer ,  Ralf Musgen ,  Matthias Oechsner ,  Ursula Pickert ,  Volker Vosberg

发明人： Alexander R. Beeck ,  Katharina Bergander ,  Georg Bostanjoglo ,  Tobias Buchal ,  Winfried Esser ,  Dirk Goldschmidt ,  Torsten Koch ,  Rudolf Kuperkoch ,  Thorsten Mattheis ,  Jan Munzer ,  Ralf Musgen ,  Matthias Oechsner ,  Ursula Pickert ,  Volker Vosberg

IPC分类号： F01D1/02

CPC分类号： F01D9/00 ,  F01D5/146 ,  F05D2240/301 ,  Y02T50/673

摘要： A guide vane for a gas turbine with a vane base body which is of single-piece design and comprises a profiled vane blade extending between a vane root and a cover plate and also the vane root formed integrally with the vane blade and the cover plate formed integrally with the vane blade, is intended, in a relatively simple way to be able to be matched to the individual conditions of use with especially little outlay on apparatus and logistics. For this purpose, according to the invention, a flow-routing body with an advance guide blade that is connected upstream of the vane blade as seen in the direction of flow of the working medium of the gas turbine is joined to the vane base body.

摘要翻译： 一种具有叶片基体的燃气轮机的导向叶片，其具有单件式设计，并且包括在叶片根部和盖板之间延伸的异型叶片叶片，以及与叶片和盖板一体形成的叶片根部 与叶片一体地，以相对简单的方式旨在能够与单独的使用条件匹配，特别是在设备和物流方面的特别少的费用。 为此，根据本发明，在叶片叶片的工作介质的流动方向上观察到连接在叶片叶片的上游的具有前进导向叶片的流动路线体与叶片基体接合。

公开(公告)号：US08961135B2

公开(公告)日：2015-02-24

申请号：US13171691

申请日：2011-06-29

申请人： Alexander R. Beeck ,  Shantanu P. Mhetras

发明人： Alexander R. Beeck ,  Shantanu P. Mhetras

IPC分类号： F01D5/22 ,  F01D11/00 ,  F01D5/14

CPC分类号： F01D5/143 ,  F01D5/22 ,  F01D11/003

摘要： In a gas turbine engine, adjoining pairs of airfoil structures include airfoils mounted to respective platforms. The platforms have side edges defining matefaces that form a mateface gap extending from an upstream edge of the platforms to a downstream edge of the platforms. A flow field of working gas adjacent to endwalls of the platform comprises streamlines extending generally transverse to the axial direction from a first airfoil toward an adjacent second airfoil. To achieve improved aerodynamic performance, the mateface gap has portions oriented transverse to the streamlines and oriented aligned with the streamlines. A step in elevation of the side edges at the transverse portion can include injected cooling flow in a direction that enhances attachment of the flow at a downstream side.

摘要翻译： 在燃气涡轮发动机中，相邻的翼型结构对包括安装到相应平台的翼型件。 平台具有侧边缘，其限定了形成从平台的上游边缘延伸到平台的下游边缘的面对间隙的面。 与平台的端壁相邻的工作气体的流场包括从第一翼面朝向相邻的第二翼面大致横向于轴向方向延伸的流线。 为了实现改进的空气动力学性能，配合间隙具有横向于流线并且与流线对准的部分。 在横向部分处的侧边缘的升高台阶可以包括在增强下游侧的流动的附着方向的注入的冷却流。

公开(公告)号：US08961134B2

公开(公告)日：2015-02-24

申请号：US13171678

申请日：2011-06-29

申请人： Alexander R. Beeck

发明人： Alexander R. Beeck

IPC分类号： F01D5/14 ,  F01D5/18

CPC分类号： F01D5/18 ,  F01D5/143 ,  F01D5/145 ,  F01D5/147 ,  F05D2240/80

摘要： A turbine engine airfoil structure including an airfoil adapted to be supported to extend across a gas passage for a hot working gas in a turbine engine. The airfoil structure further includes a platform structure located at one end of the airfoil and positioned at a location forming a boundary of the gas passage. The platform structure includes a platform member including a gas side surface extending generally perpendicular from the airfoil at a junction with the airfoil, and providing a structural connection to the airfoil. The platform structure further includes a separately formed platform cover attached to the platform member at the gas side surface. The platform cover extends from a location adjacent to one of the sidewalls of the airfoil, and includes an outer surface located for contact with the hot working gas passing through the gas path.

摘要翻译： 一种涡轮发动机翼型结构，其包括适于被支撑以延伸穿过涡轮发动机中的热工作气体的气体通道的翼型件。 翼型结构还包括位于翼型件的一端处并定位在形成气体通道的边界的位置处的平台结构。 平台结构包括平台构件，该平台构件包括在与翼型的连接处大体上垂直于翼型延伸的气体侧表面，并且提供与翼型的结构连接。 平台结构还包括在气体侧表面处附接到平台构件的单独形成的平台盖。 平台盖从与翼型件的一个侧壁相邻的位置延伸，并且包括位于与通过气体路径的热作业气体接触的外表面。

公开(公告)号：US08690158B2

公开(公告)日：2014-04-08

申请号：US12832140

申请日：2010-07-08

申请人： Alexander R. Beeck

发明人： Alexander R. Beeck

IPC分类号： F01D11/02 ,  F16J15/00

CPC分类号： F16J15/3292 ,  F01D11/02 ,  F05D2240/57 ,  F05D2250/292 ,  F05D2250/314

摘要： A seal member for effecting a seal preventing fluid flow in an axial direction through an annular space formed between a rotatable shaft and a stator structure. The seal member includes a plurality of flexible seal strips extending radially through the annular space and having a radially outer end supported to the stator structure and a radially inner end defining a tip portion extending widthwise in the axial direction for engaging in sliding contact with a peripheral surface of the rotatable shaft. The seal strips are mounted to the stator structure with the tip portions of the seal strips at an angle to the axial direction. Each of the tip portions are formed with a curvature in a radially extending plane between a leading edge and a trailing edge of each seal strip.

摘要翻译： 一种用于实现密封的密封构件，其防止流体在轴向方向上流过形成在可旋转轴和定子结构之间的环形空间。 密封构件包括多个柔性密封条，其径向延伸穿过环形空间并且具有支撑到定子结构的径向外端，以及限定在轴向方向上沿宽度方向延伸的尖端部分的径向内端，用于与周边滑动接触 可旋转轴的表面。 密封条以与轴向方向成一定角度的方式安装到定子结构上。 每个尖端部分在每个密封条的前缘和后缘之间沿径向延伸的平面形成曲率。

公开(公告)号：US20140060001A1

公开(公告)日：2014-03-06

申请号：US13602480

申请日：2012-09-04

申请人： Alexander R. Beeck

发明人： Alexander R. Beeck

IPC分类号： F02C3/14

CPC分类号： F02C3/14 ,  F01D9/023 ,  Y02T50/671

摘要： An industrial gas turbine engine (10) rated for at least 75 MW maximum output, including: a can annular combustion assembly (80); and a single rotor shaft (114); wherein a combustion section length (112) between a trailing edge (28) of a last row of compressor airfoils (20, 22) and a leading edge (54) of first row of turbine blades (56) is less than 20% of an engine length (154) between a leading edge (26) of a first row of compressor airfoils and a trailing edge (66) of a last row of turbine airfoils (60, 62).

摘要翻译： 一种工业燃气涡轮发动机（10），其额定功率为至少75MW最大输出，包括：罐式环形燃烧组件（80）; 和单个转子轴（114）; 其中在最后一排压缩机翼片（20,22）的后缘（28）和第一排涡轮叶片（56）的前缘（54）之间的燃烧部分长度（112）小于第一排涡轮叶片 第一排压缩机翼型件的前缘（26）和最后一排涡轮翼型件（60,62）的后缘（66）之间的发动机长度（154）。

公开(公告)号：US08616848B2

公开(公告)日：2013-12-31

申请号：US12637066

申请日：2009-12-14

申请人： Alexander R. Beeck

发明人： Alexander R. Beeck

IPC分类号： F01D5/16

CPC分类号： F01D5/22 ,  F04D29/324 ,  F04D29/668 ,  F05D2250/712 ,  F05D2260/96

摘要： A damping structure for a turbomachine rotor. The damping structure includes an elongated snubber element including a first snubber end rigidly attached to a first blade and extending toward an adjacent second blade, and an opposite second snubber end defining a first engagement surface positioned adjacent to a second engagement surface associated with the second blade. The snubber element has a centerline extending radially inwardly in a direction from the first blade toward the second blade along at least a portion of the snubber element between the first and second snubber ends. Rotational movement of the rotor effects relative movement between the first engagement surface and the second engagement surface to position the first engagement surface in frictional engagement with the second engagement surface with a predetermined damping force determined by a centrifugal force on the snubber element.

摘要翻译： 涡轮机转子的阻尼结构。 阻尼结构包括细长的缓冲元件，其包括刚性地连接到第一叶片并朝向相邻的第二叶片延伸的第一缓冲端，以及相对的第二缓冲端，限定了邻近与第二叶片相关联的第二接合表面定位的第一接合表面 。 缓冲元件具有沿第一和第二缓冲器端部之间的缓冲元件的至少一部分沿着从第一刀片朝向第二刀片的方向径向向内延伸的中心线。 转子的旋转运动影响第一接合表面和第二接合表面之间的相对运动，以使第一接合表面与第二接合表面摩擦接合，并以由缓冲件上的离心力确定的预定阻尼力。

公开(公告)号：US20130121806A1

公开(公告)日：2013-05-16

申请号：US13811943

申请日：2011-07-18

申请人： Alexander R. Beeck ,  Bonnie D. Marini

发明人： Alexander R. Beeck ,  Bonnie D. Marini

IPC分类号： F01D25/30

CPC分类号： F01D25/30 ,  F05D2220/32 ,  F05D2250/232 ,  F05D2270/17 ,  F05D2270/301

摘要： An exhaust diffuser assembly is provided, particularly for a stationary gas turbine. The exhaust diffuser assembly includes a longitudinal axis, a diffuser inlet for receiving a turbine mainflow gas, a diffuser outlet, and a diverging diffuser wall having an adjustable geometry and forming a conduit for flow of the gas therethrough from the diffuser inlet to the diffuser outlet. The diffuser wall has a divergence angle ‘α’ with respect to the longitudinal axis. The diffuser assembly also has a diffuser geometry control device for controlling a recovery of pressure from the gas between the diffuser inlet and the diffuser outlet by adjusting the divergence angle ‘α’ of the diffuser wall to cause a resultant flow field of the gas that is attached to the diffuser wall.

摘要翻译： 提供排气扩散器组件，特别是用于固定式燃气轮机。 排气扩散器组件包括纵向轴线，用于接收涡轮机主流气体的扩散器入口，扩散器出口和具有可调节几何形状的发散扩散壁，并形成用于气体从扩散器入口到扩散器出口流动的导管 。 扩散壁相对于纵向轴线具有发散角α'。 扩散器组件还具有扩散器几何控制装置，用于通过调节扩散壁的发散角“α”来控制从扩散器入口和扩散器出口之间的气体的压力恢复，从而导致气体的合成流场 附着在扩散壁上。