公开(公告)号：US20120076653A1

公开(公告)日：2012-03-29

申请号：US12892515

申请日：2010-09-28

申请人： Alexander R. Beeck ,  Glenn E. Brown

发明人： Alexander R. Beeck ,  Glenn E. Brown

IPC分类号： F01D5/08

CPC分类号： F01D5/20 ,  F01D5/187 ,  F05D2210/33 ,  F05D2240/127 ,  F05D2250/21 ,  F05D2260/2212

摘要： A turbine blade for a turbine engine having a tip with one or more vortex generators for reducing tip leakage during operation of the turbine engine. The vortex generators may extend radially outward from the radially outer surface of the tip wall. The vortex generator may be positioned between a rib extending radially outward from the radially outer surface of the tip wall and an intersection between the outer surface of the tip wall and an outer surface on the pressure side. The vortex generators may include a base and three sides forming a triangular point with a first side having a larger surface are than second and third sides. One or more film cooling holes may be formed in the tip wall to provide cooling air to the tip. In one embodiment, film cooling holes may be positioned in one or more vortex generators.

摘要翻译： 一种用于涡轮发动机的涡轮叶片，其具有具有一个或多个涡流发生器的尖端，用于在涡轮发动机的运行期间减少尖端泄漏。 涡流发生器可以从尖端壁的径向外表面径向向外延伸。 涡流发生器可以位于从尖端壁的径向外表面径向向外延伸的肋与尖端壁的外表面与压力侧的外表面之间的交叉点之间。 涡流发生器可以包括基部，并且形成具有比第二和第三侧更大表面的第一侧的三角形点的三个边。 可以在尖端壁中形成一个或多个薄膜冷却孔，以向尖端提供冷却空气。 在一个实施例中，膜冷却孔可以定位在一个或多个涡流发生器中。

公开(公告)号：US08690536B2

公开(公告)日：2014-04-08

申请号：US12892515

申请日：2010-09-28

申请人： Alexander R. Beeck ,  Glenn E. Brown

发明人： Alexander R. Beeck ,  Glenn E. Brown

IPC分类号： F01D5/20 ,  F01D5/08

CPC分类号： F01D5/20 ,  F01D5/187 ,  F05D2210/33 ,  F05D2240/127 ,  F05D2250/21 ,  F05D2260/2212

摘要： A turbine blade for a turbine engine having a tip with one or more vortex generators for reducing tip leakage during operation of the turbine engine. The vortex generators may extend radially outward from the radially outer surface of the tip wall. The vortex generator may be positioned between a rib extending radially outward from the radially outer surface of the tip wall and an intersection between the outer surface of the tip wall and an outer surface on the pressure side. The vortex generators may include a base and three sides forming a triangular point with a first side having a larger surface are than second and third sides. One or more film cooling holes may be formed in the tip wall to provide cooling air to the tip. In one embodiment, film cooling holes may be positioned in one or more vortex generators.

摘要翻译： 一种用于涡轮发动机的涡轮叶片，其具有具有一个或多个涡流发生器的尖端，用于在涡轮发动机的运行期间减少尖端泄漏。 涡流发生器可以从尖端壁的径向外表面径向向外延伸。 涡流发生器可以位于从尖端壁的径向外表面径向向外延伸的肋与尖端壁的外表面与压力侧的外表面之间的交叉点之间。 涡流发生器可以包括基部，并且形成具有比第二和第三侧更大表面的第一侧的三角形点的三个边。 可以在尖端壁中形成一个或多个薄膜冷却孔，以向尖端提供冷却空气。 在一个实施例中，膜冷却孔可以定位在一个或多个涡流发生器中。

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

IPC分类号： F23R3/46 ,  F04D29/54 ,  F23R3/02 ,  F23R3/04 ,  F23R3/42

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。

公开(公告)号：US20130004331A1

公开(公告)日：2013-01-03

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： F01D5/18 ,  F01D5/14

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：US08313286B2

公开(公告)日：2012-11-20

申请号：US12393555

申请日：2009-02-26

申请人： Alexander R. Beeck

发明人： Alexander R. Beeck

IPC分类号： F03D11/00 ,  F04D29/44 ,  F04D29/54 ,  F03B1/00 ,  F03B11/02

CPC分类号： F01D5/143 ,  F01D5/145 ,  F01D25/30

摘要： A diffuser apparatus in a turbomachine is provided comprising a diffuser structure and stabilizing structure. The diffuser structure includes inner and outer walls defining a flow passageway through which gases flow and diffuse such that kinetic energy is reduced and pressure is increased in the gases as they move through the passageway. The stabilizing structure stabilizes a separated gas recirculation zone.

摘要翻译： 提供了一种涡轮机中的扩散装置，其包括扩散器结构和稳定结构。 扩散器结构包括限定流动通道的内壁和外壁，气体通过该通道流动并扩散，使得动能减小，并且当气体移动通过通道时气体中的压力增加。 稳定结构稳定了分离的气体再循环区域。

公开(公告)号：US20100290897A1

公开(公告)日：2010-11-18

申请号：US12464492

申请日：2009-05-12

申请人： Alexander R. Beeck ,  Sankar Nellian

发明人： Alexander R. Beeck ,  Sankar Nellian

IPC分类号： F01D11/08 ,  F01D5/22

CPC分类号： F01D11/08 ,  F01D5/225

摘要： A turbine blade is provided comprising: an airfoil including upper and lower ends; a root coupled to the airfoil lower end; a shroud coupled to the airfoil upper end; and at least one sealing rail extending radially outwardly from an upper surface of the shroud and extending generally along a circumferential length of the shroud. The sealing rail may comprise a mid-section, opposing end sections and at least one intermediate section located between the mid-section and one of the opposing end sections. An axial thickness of the rail may vary.

摘要翻译： 提供一种涡轮叶片，其包括：包括上端和下端的翼型件; 与翼型件下端相连的根部; 联接到翼型件上端的护罩; 以及至少一个密封轨道，其从护罩的上表面径向向外延伸并且大致沿着护罩的圆周长度延伸。 密封轨道可以包括中间部分，相对的端部部分和位于中间部分和相对的端部部分之一之间的至少一个中间部分。 轨道的轴向厚度可以变化。

公开(公告)号：US20100021291A1

公开(公告)日：2010-01-28

申请号：US12393555

申请日：2009-02-26

申请人： Alexander R. Beeck

发明人： Alexander R. Beeck

IPC分类号： F01D25/24

CPC分类号： F01D5/143 ,  F01D5/145 ,  F01D25/30

摘要： A diffuser apparatus in a turbomachine is provided comprising a diffuser structure and stabilizing structure. The diffuser structure includes inner and outer walls defining a flow passageway through which gases flow and diffuse such that kinetic energy is reduced and pressure is increased in the gases as they move through the passageway. The stabilizing structure stabilizes a separated gas recirculation zone.

摘要翻译： 提供了一种涡轮机中的扩散装置，其包括扩散器结构和稳定结构。 扩散器结构包括限定流动通道的内壁和外壁，气体通过该通道流动并扩散，使得动能减小，并且当气体移动通过通道时气体中的压力增加。 稳定结构稳定了分离的气体再循环区域。

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。

公开(公告)号：US08322977B2

公开(公告)日：2012-12-04

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：US08176720B2

公开(公告)日：2012-05-15

申请号：US12564166

申请日：2009-09-22

申请人： Alexander R. Beeck

发明人： Alexander R. Beeck

IPC分类号： F02G3/00

CPC分类号： F02C7/052 ,  F01D5/08 ,  F01D9/065 ,  F05D2260/607

摘要： A centrifugal particle separator is provided for removing particles such as microscopic dirt or dust particles from the compressed cooling air prior to reaching and cooling the turbine blades or turbine vanes of a turbine engine. The centrifugal particle separator structure has a substantially cylindrical body with an inlet arranged on a periphery of the substantially cylindrical body. Cooling air enters centrifugal particle separator through the separator inlet port having a linear velocity. When the cooling air impinges the substantially cylindrical body, the linear velocity is transformed into a rotational velocity, separating microscopic particles from the cooling air. Microscopic dust particles exit the centrifugal particle separator through a conical outlet and returned to a working medium.

摘要翻译： 提供离心式颗粒分离器，用于在到达和冷却涡轮发动机的涡轮叶片或涡轮叶片之前，从压缩的冷却空气中除去诸如微小污垢或灰尘颗粒的颗粒。 离心式颗粒分离器结构具有基本上圆柱形的主体，其具有布置在基本上圆柱形主体的周边上的入口。 冷却空气通过具有线速度的分离器入口进入离心式颗粒分离器。 当冷却空气冲击基本上圆柱形的主体时，将线速度转变成旋转速度，从微型颗粒与冷却空气分离。 微观尘埃颗粒通过锥形出口离开离心颗粒分离器并返回工作介质。