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公开(公告)号：US08257032B2
公开(公告)日：2012-09-04
申请号：US12009314
申请日：2008-01-17
申请人： Alexander R. Beeck , Katharina Bergander , Georg Bostanjoglo , Tobias Buchal , Winfried Eβer , Dirk Goldschmidt , Torsten Koch , Rudolf Küperkoch , Thorsten Mattheis , Jan Münzer , Ralf Müsgen , Matthias Oechsner , Ursula Pickert , Volker Vosberg
发明人： Alexander R. Beeck , Katharina Bergander , Georg Bostanjoglo , Tobias Buchal , Winfried Eβer , Dirk Goldschmidt , Torsten Koch , Rudolf Küperkoch , Thorsten Mattheis , Jan Münzer , Ralf Müsgen , Matthias Oechsner , Ursula Pickert , Volker Vosberg
IPC分类号： F04D29/54
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。
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公开(公告)号：US08092175B2
公开(公告)日：2012-01-10
申请号：US12226537
申请日：2007-02-13
CPC分类号： F01D5/145 , F01D5/186 , F01D5/187 , F01D5/189 , F01D9/065 , F02C3/16 , F02K3/08 , F05D2240/122 , F05D2240/124 , F05D2250/25 , F05D2260/204
摘要： The invention relates to a turbine blade comprising a profiled vane around which working gas flows. The working gas cross-flows a front edge of the vane and flows away on a rear edge of the vane. The vane has a first and a second channel system for guiding two media separated from the turbine blade. Combustion taking place inside is reduced in a safe manner to maintain the service life of the turbine blade and to prevent damage in the gas turbine, such that a first outlet connected to the first channel system is arranged in the region of the rear edge for blowing out the first media into the working gas and a second outlet connected to the second channel system is arranged in the region of the rear edge for blowing out the second medium.
摘要翻译： 本发明涉及一种涡轮叶片，其包括工作气体围绕其流动的异型叶片。 工作气体交叉流动叶片的前边缘并在叶片的后边缘上流走。 叶片具有用于引导从涡轮叶片分离的两种介质的第一和第二通道系统。 在内部进行的燃烧以安全的方式被减少以维持涡轮机叶片的使用寿命并且防止燃气轮机中的损坏，使得连接到第一通道系统的第一出口布置在用于吹送的后边缘的区域中 将第一介质排出到工作气体中，并且连接到第二通道系统的第二出口布置在后边缘的区域中以吹出第二介质。
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公开(公告)号：US20110142650A1
公开(公告)日：2011-06-16
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： F01D5/22
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。
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公开(公告)号：US20100196139A1
公开(公告)日：2010-08-05
申请号：US12363892
申请日：2009-02-02
IPC分类号： F04D29/08
CPC分类号： F04D29/102 , F04D25/16
摘要： A sealing system is applied to the interface between a stator and a rotor in a turbine engine to minimize fluid leakage across the interface. One interface can be defined between portions of neighboring rotor disks and a stator. The sealing system includes one or more rows of flow guides, such as airfoils, provided on the rotor disk near the upstream end of the interface. These flow guides can impart tangential velocity on the leakage flow. One or more undulating seal structures can be connected to the stator downstream of the flow guides. These undulating seals can have a periodic waveform conformation. The undulating seals can create unsteadiness in the flow and recirculation of the leakage flow, which causes losses. The sealing system can also include other types of seals, such as labyrinth seals and brush seals, to further create a tortuous path for any leakage flow.
摘要翻译： 将密封系统应用于涡轮发动机中的定子和转子之间的界面，以最小化穿过界面的流体泄漏。 一个接口可以在相邻的转子盘和定子的部分之间限定。 密封系统包括设置在接近上游端的转子盘上的一排或多排流动引导件，例如翼型件。 这些流动导向器可以在泄漏流上产生切向速度。 一个或多个起伏密封结构可以连接到导流器下游的定子。 这些起伏密封件可以具有周期性的波形构型。 起伏密封件可能导致泄漏流量的流动和再循环不稳定，从而导致损耗。 密封系统还可以包括其它类型的密封件，例如迷宫式密封件和刷子密封件，以进一步产生用于任何泄漏流动的曲折路径。
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15.发明授权公开(公告)号：US07722326B2
公开(公告)日：2010-05-25
申请号：US11717238
申请日：2007-03-13
申请人： Alexander R. Beeck , Sanjay Chopra
发明人： Alexander R. Beeck , Sanjay Chopra
IPC分类号： F01D5/18
CPC分类号： F01D5/187 , F05D2220/3215 , F05D2250/32 , F05D2260/201
摘要： A cooling system designed to cool the trailing edge of a turbine blade usable in rear stages of a turbine engine. The turbine blade may have a leading edge cooling cavity and a trailing edge cooling cavity separated by an impingement rib. The cooling system may exhaust cooling fluids through the tip of the turbine blade rather than through the trailing edge of the turbine blade to prevent premature failure at the trailing edge of the turbine blade.
摘要翻译： 一种设计用于冷却可用于涡轮发动机后级的涡轮叶片的后缘的冷却系统。 涡轮叶片可以具有前缘冷却腔和由冲击肋分开的后缘冷却腔。 冷却系统可以将冷却流体排出通过涡轮叶片的尖端，而不是通过涡轮机叶片的后缘排出，以防止在涡轮叶片的后缘处的过早失效。
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公开(公告)号：US20090081048A1
公开(公告)日：2009-03-26
申请号：US12226534
申请日：2007-03-09
IPC分类号： F01D5/18
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。
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17.发明申请公开(公告)号：US20080226461A1
公开(公告)日：2008-09-18
申请号：US11717238
申请日：2007-03-13
申请人： Alexander R. Beeck , Sanjay Chopra
发明人： Alexander R. Beeck , Sanjay Chopra
IPC分类号： F01D5/18
CPC分类号： F01D5/187 , F05D2220/3215 , F05D2250/32 , F05D2260/201
摘要： A cooling system designed to cool the trailing edge of a turbine blade usable in rear stages of a turbine engine. The turbine blade may have a leading edge cooling cavity and a trailing edge cooling cavity separated by an impingement rib. The cooling system may exhaust cooling fluids through the tip of the turbine blade rather than through the trailing edge of the turbine blade to prevent premature failure at the trailing edge of the turbine blade.
摘要翻译： 一种设计用于冷却可用于涡轮发动机后级的涡轮叶片的后缘的冷却系统。 涡轮叶片可以具有前缘冷却腔和由冲击肋分开的后缘冷却腔。 冷却系统可以将冷却流体排出通过涡轮叶片的尖端，而不是通过涡轮机叶片的后缘排出，以防止在涡轮叶片的后缘处的过早失效。
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18.发明授权公开(公告)号：US09528706B2
公开(公告)日：2016-12-27
申请号：US14105313
申请日：2013-12-13
申请人： Matthew D. Montgomery , Richard C. Charron , Jose L. Rodriguez , Bernhard W. Küsters , Jay A. Morrison , Alexander R. Beeck
发明人： Matthew D. Montgomery , Richard C. Charron , Jose L. Rodriguez , Bernhard W. Küsters , Jay A. Morrison , Alexander R. Beeck
CPC分类号： F23R3/46 , F04D29/542 , F04D29/545 , F04D29/547 , F23R3/02 , F23R3/04 , F23R3/425
摘要： A gas turbine engine can-annular combustion arrangement (10), including: an axial compressor (82) operable to rotate in a rotation direction (60); a diffuser (100, 110) configured to receive compressed air (16) from the axial compressor; a plenum (22) configured to receive the compressed air from the diffuser; a plurality of combustor cans (12) each having a combustor inlet (38) in fluid communication with the plenum, wherein each combustor can is tangentially oriented so that a respective combustor inlet is circumferentially offset from a respective combustor outlet in a direction opposite the rotation direction; and an airflow guiding arrangement (80) configured to impart circumferential motion to the compressed air in the plenum in the direction opposite the rotation direction.
摘要翻译： 一种燃气涡轮发动机罐环式燃烧装置（10），包括：轴向压缩机（82），其可操作以沿旋转方向（60）旋转; 构造成从所述轴向压缩机接收压缩空气（16）的扩散器（100,110）; 配置成从扩散器接收压缩空气的增压室（22） 多个燃烧器罐（12）各自具有与所述气室流体连通的燃烧器入口（38），其中每个燃烧室可以被切向地定向，使得相应的燃烧器入口在与旋转相反的方向上与相应的燃烧室出口周向偏移 方向; 以及气流引导装置（80），其构造成沿着与旋转方向相反的方向对所述增压室中的压缩空气施加周向运动。
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公开(公告)号：US20130101409A1
公开(公告)日：2013-04-25
申请号：US13280440
申请日：2011-10-25
申请人： ALEXANDER R. BEECK
发明人： ALEXANDER R. BEECK
CPC分类号： F01D5/141 , F01D5/145 , F05D2240/127 , F05D2250/184 , F05D2250/294
摘要： A turbine engine airfoil structure including an airfoil adapted to extend across a gas passage, and a platform structure defining an endwall located at one end of the airfoil and positioned at a location forming a boundary of the gas passage. A saddle portion is associated with at least one airfoil surface of the airfoil, the saddle portion defining a contour having a first radially outer edge located on the at least one airfoil surface and a second radially inner edge located radially inwardly from the radially outer edge. The contour includes a curvature in a plane extending generally perpendicular to the at least one airfoil surface and passing through the saddle portion, the curvature being radially spaced from the endwall and defining an apex located between the radially outer and inner edges of the saddle portion.
摘要翻译： 包括适于延伸穿过气体通道的翼型件的涡轮发动机翼型结构以及限定位于所述翼型件的一端并位于形成所述气体通道的边界的位置处的端壁的平台结构。 鞍座部分与翼型件的至少一个翼型件表面相关联，鞍形部分限定轮廓，该轮廓具有位于至少一个翼型表面上的第一径向外边缘和从径向外边缘径向向内定位的第二径向内边缘。 轮廓包括在大致垂直于至少一个翼面表面延伸并穿过鞍座部分的平面中的曲率，该曲率与端壁径向间隔开并限定位于鞍部的径向外边缘和内边缘之间的顶点。
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公开(公告)号：US08769816B2
公开(公告)日：2014-07-08
申请号：US13367750
申请日：2012-02-07
申请人： Alexander R. Beeck
发明人： Alexander R. Beeck
IPC分类号： B23P11/00
CPC分类号： F01D25/285 , F01D11/00 , F02C7/28 , F05D2230/60
摘要： A method of assembling a seal in a horizontal split plane gas turbine engine including providing a rotor assembly including a turbine blade assembly defining a forward face and a seal ring extending axially from the forward face. The rotor assembly is positioned extending through a lower compressor casing and a lower turbine casing, the positioning including tilting the rotor assembly at an angle relative to the longitudinal axis for the engine. An upper turbine casing is positioned over the tilted rotor assembly, and the upper and lower turbine casings define a circumferentially extending seal groove. The rotor assembly is moved in an axially forward direction to position the seal ring in axially overlapping relation within the seal groove. The longitudinal axis of the rotor assembly is then aligned with the longitudinal axis of the turbine engine to further position the seal ring within the seal groove.
摘要翻译： 一种在水平分裂平面燃气涡轮发动机中组装密封件的方法，包括提供转子组件，转子组件包括限定前表面的涡轮叶片组件和从前表面轴向延伸的密封环。 转子组件定位成延伸穿过下压缩机壳体和下涡轮机壳体，该定位包括使转子组件相对于发动机的纵向轴线成一定角度倾斜。 上涡轮机壳体位于倾斜的转子组件上方，并且上涡轮机壳体和下涡轮机壳体限定周向延伸的密封槽。 转子组件沿轴向向前移动以将密封环定位在密封槽内的轴向重叠关系。 然后转子组件的纵向轴线与涡轮发动机的纵向轴线对齐，以将密封环进一步定位在密封槽内。
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