公开(公告)号：US09771804B2

公开(公告)日：2017-09-26

申请号：US14235060

申请日：2012-07-13

申请人： Liang Guo ,  John David Maltson ,  Yuying Yan

发明人： Liang Guo ,  John David Maltson ,  Yuying Yan

IPC分类号： F01D5/18 ,  F01D5/14 ,  F01D9/04

CPC分类号： F01D5/147 ,  F01D5/145 ,  F01D5/186 ,  F01D9/041 ,  F05D2240/12 ,  F05D2260/202

摘要： The present invention relates to a turbine assembly having an aerofoil and/or an end wall each having an outer surface with a structure for directing a flow of a cooling medium at the outer surface. The structure at the outer surface has at least a first groove and a second groove extending in the outer surface from a leading to a trailing edge and being oriented in at least two different directions with a deflection angle (α) towards each other, with the deflection angle (α) having a component in a span wise direction of the aerofoil. The structure at the outer surface of the end wall has at least a first groove and a second groove extending in an axial direction of the turbine assembly, matching an outer profile of the aerofoil and oriented in at least two different directions with a deflection angle (α) towards each other.

公开(公告)号：US20140255200A1

公开(公告)日：2014-09-11

申请号：US14235060

申请日：2012-07-13

申请人： Liang Guo ,  John David Maltson ,  Yuying Yan

发明人： Liang Guo ,  John David Maltson ,  Yuying Yan

IPC分类号： F01D5/18 ,  F01D5/14

CPC分类号： F01D5/147 ,  F01D5/145 ,  F01D5/186 ,  F01D9/041 ,  F05D2240/12 ,  F05D2260/202

摘要： The present invention relates to a turbine assembly having an aerofoil and/or an end wall each having an outer surface with a structure for directing a flow of a cooling medium at the outer surface. The structure at the outer surface has at least a first groove and a second groove extending in the outer surface from a leading to a trailing edge and being oriented in at least two different directions with a deflection angle (α) towards each other, with the deflection angle (α) having a component in a span wise direction of the aerofoil. The structure at the outer surface of the end wall has at least a first groove and a second groove extending in an axial direction of the turbine assembly, matching an outer profile of the aerofoil and oriented in at least two different directions with a deflection angle (α) towards each other.

摘要翻译： 本发明涉及一种具有机翼和/或端壁的涡轮组件，每个翼片和/或端壁都具有外表面，该外表面具有用于引导冷却介质在外表面的流动的结构。 外表面上的结构具有至少第一凹槽和第二凹槽，该第二凹槽和第二凹槽在外表面中从引导向后缘延伸，并且在至少两个不同的方向上以相对于彼此的偏转角（α）定向， 偏转角（α）在机翼的跨度方向上具有分量。 在端壁的外表面处的结构具有至少第一凹槽和在涡轮组件的轴向方向上延伸的第二凹槽，其匹配翼型的外轮廓并且在至少两个不同方向上以偏转角（ α）朝向彼此。

公开(公告)号：US08402769B2

公开(公告)日：2013-03-26

申请号：US12524766

申请日：2008-01-25

申请人： John David Maltson

发明人： John David Maltson

IPC分类号： F02C7/20 ,  F03B1/00 ,  F03D5/00

CPC分类号： F01D25/162 ,  F01D9/041 ,  F05D2240/127 ,  F23R3/04 ,  F23R3/60

摘要： A section of a gas turbine engine including a radial spoke is provided. The spoke includes an aerodynamic shape with a leading side and a trailing side and, extending from the leading side to the trailing side, a first side and a second side, opposite the first side. The spoke also includes at least one flow guiding element arranged on at least the first side.

摘要翻译： 提供了包括径向辐条的燃气涡轮发动机的一部分。 辐条包括具有前侧和后侧并且从前侧延伸到后侧的空气动力学形状，与第一侧相对的第一侧和第二侧。 辐条还包括至少一个布置在至少第一侧上的流动引导元件。

公开(公告)号：US08002521B2

公开(公告)日：2011-08-23

申请号：US11922666

申请日：2006-06-22

申请人： John David Maltson

发明人： John David Maltson

IPC分类号： F01D9/04

CPC分类号： F01D9/041 ,  F05D2240/81 ,  F05D2260/201

摘要： A flow machine is described having a first space adapted to contain a hot fluid and delimited by a wall. The wall having a first wall surface facing the first space and a second wall surface turned away from the first space. Cooling is provided for a region of the wall by supplying a relatively cool fluid onto the second wall surface. The cooling means includes a supply chamber containing the second fluid, a cavity adjacent the second wall surface, at least one duct, which has an inlet opening at the supply chamber and an outlet opening at the cavity for conveying the cool fluid to the cavity, and a deflection surface facing the cavity.

摘要翻译： 流动机被描述为具有适于容纳热流体并由壁限定的第一空间。 所述壁具有面向所述第一空间的第一壁表面和远离所述第一空间的第二壁表面。 通过将相对较冷的流体供应到第二壁表面上来为壁的区域提供冷却。 冷却装置包括一个容纳第二流体的供应室，邻近第二壁表面的空腔，至少一个管道，其在供应室处具有入口开口，在空腔处具有用于将冷却流体输送到空腔的出口， 以及面向空腔的偏转表面。

公开(公告)号：US08628292B2

公开(公告)日：2014-01-14

申请号：US12532503

申请日：2008-03-27

申请人： John David Maltson

发明人： John David Maltson

IPC分类号： F03B11/00

CPC分类号： F01D5/186 ,  F01D5/188 ,  F05D2250/232 ,  F05D2250/29 ,  F05D2260/201 ,  F05D2260/202 ,  F05D2260/221 ,  F05D2260/607 ,  F23R3/002 ,  F23R2900/03042 ,  F23R2900/03044 ,  Y02T50/676

摘要： A flow channel with a branch channel perpendicular to a main channel including an edge defining an inlet opening of the branch channel is provided. A chamfer is disposed at the upstream edge of the inlet opening and a straight edge is disposed at the downstream edge of the inlet opening, perpendicular to the main channel.

摘要翻译： 提供具有垂直于主通道的分支通道的流动通道，该主通道包括限定分支通道的入口的边缘。 倒角设置在入口开口的上游边缘处，并且直线边缘设置在入口开口的下游边缘处，垂直于主通道。

公开(公告)号：US20100031673A1

公开(公告)日：2010-02-11

申请号：US12524766

申请日：2008-01-25

申请人： John David Maltson

发明人： John David Maltson

IPC分类号： F02C7/12 ,  F02C7/20

CPC分类号： F01D25/162 ,  F01D9/041 ,  F05D2240/127 ,  F23R3/04 ,  F23R3/60

摘要： A section of a gas turbine engine including a radial spoke is provided. The spoke includes an aerodynamic shape with a leading side and a trailing side and, extending from the leading side to the trailing side, a first side and a second side, opposite the first side. The spoke also includes at least one flow guiding element arranged on at least the first side.

摘要翻译： 提供了包括径向辐条的燃气涡轮发动机的一部分。 辐条包括具有前侧和后侧并且从前侧延伸到后侧的空气动力学形状，与第一侧相对的第一侧和第二侧。 辐条还包括至少一个布置在至少第一侧上的流动引导元件。

公开(公告)号：US08550774B2

公开(公告)日：2013-10-08

申请号：US12664742

申请日：2008-06-18

申请人： John David Maltson

发明人： John David Maltson

IPC分类号： F01D25/12

CPC分类号： F01D5/225 ,  F01D11/10 ,  F01D25/12 ,  F05D2240/11 ,  F05D2250/323 ,  F05D2250/324

摘要： A turbine arrangement with a rotor and a stator surrounding the rotor forming a flow path for hot and pressurized combustion gases between the rotor and the stator is provided. The rotor defines a radial direction and a circumferential direction and includes turbine blades extending in the radial direction through the flow path towards the stator. The turbine blades have shrouds located at their tips and the stator includes a wall section along which the shrouds move when the rotor is turning. A supersonic nozzle is located in the wall section and is connected to a cooling fluid provider. The supersonic nozzle provides a supersonic cooling fluid flow towards the shroud. The supersonic nozzle is angled with respect to the radial direction towards the circumferential direction in such an orientation that the supersonic cooling fluid flow has a flow component parallel to the moving direction of the shroud.

摘要翻译： 提供了具有转子和围绕转子的定子的涡轮机装置，其形成用于转子和定子之间的热和加压燃烧气体的流动路径。 转子限定径向方向和圆周方向，并且包括沿径向方向延伸通过朝向定子的流动路径的涡轮叶片。 涡轮叶片具有位于其顶端处的护罩，并且定子包括壁部分，当转子转动时，护罩沿着该壁部分移动。 超音速喷嘴位于壁部分并连接到冷却液供应商。 超音速喷嘴提供朝向护罩的超音速冷却流体流。 超音速喷嘴相对于径向朝向圆周方向成角度，使得超音速冷却流体流动具有平行于护罩移动方向的流动分量。

公开(公告)号：US20100189542A1

公开(公告)日：2010-07-29

申请号：US12664742

申请日：2008-06-18

申请人： John David Maltson

发明人： John David Maltson

IPC分类号： F01D25/12 ,  F01D11/08 ,  F01D5/22

CPC分类号： F01D5/225 ,  F01D11/10 ,  F01D25/12 ,  F05D2240/11 ,  F05D2250/323 ,  F05D2250/324

摘要： A turbine arrangement with a rotor and a stator surrounding the rotor forming a flow path for hot and pressurised combustion gases between the rotor and the stator is provided. The rotor defines a radial direction and a circumferential direction and includes turbine blades extending in the radial direction through the flow path towards the stator. The turbine blades have shrouds located at their tips and the stator includes a wall section along which the shrouds move when the rotor is turning. A supersonic nozzle is located in the wall section and is connected to a cooling fluid provider. The supersonic nozzle provides a supersonic cooling fluid flow towards the shroud. The supersonic nozzle is angled with respect to the radial direction towards the circumferential direction in such an orientation that the supersonic cooling fluid flow has a flow component parallel to the moving direction of the shroud.

摘要翻译： 提供了具有转子和围绕转子的定子的涡轮机装置，其形成用于转子和定子之间的热和加压燃烧气体的流动路径。 转子限定径向方向和圆周方向，并且包括沿径向方向延伸通过朝向定子的流动路径的涡轮叶片。 涡轮叶片具有位于其顶端处的护罩，并且定子包括壁部分，当转子转动时，护罩沿着该壁部分移动。 超音速喷嘴位于壁部分并连接到冷却液供应商。 超音速喷嘴提供朝向护罩的超音速冷却流体流。 超音速喷嘴相对于朝向圆周方向的径向方向成角度，使得超音速冷却流体流具有平行于护罩移动方向的流动分量。

公开(公告)号：US20130213056A1

公开(公告)日：2013-08-22

申请号：US13704266

申请日：2011-05-31

申请人： Ghenadie Bulat ,  John David Maltson

发明人： Ghenadie Bulat ,  John David Maltson

IPC分类号： F16F7/00

CPC分类号： F16F7/00 ,  F02C3/14 ,  F02C7/24 ,  F05D2260/96 ,  F23M20/005 ,  F23R3/04 ,  F23R3/54 ,  F23R2900/00014

摘要： A damping device for damping pressure oscillations within a combustion chamber of a turbine is provided. The damping device has a radially extending damping device body. The damping device body has a radially inner circumferential edge portion and a radially outer circumferential edge portion. A through hole is formed in the damping device body and has a tapered shape.

摘要翻译： 提供一种用于阻尼在涡轮的燃烧室内的压力振荡的阻尼装置。 阻尼装置具有径向延伸的阻尼装置主体。 阻尼装置主体具有径向内周缘部和径向外周缘部。 在阻尼装置主体中形成通孔，并具有锥形形状。

公开(公告)号：US08016555B2

公开(公告)日：2011-09-13

申请号：US12680791

申请日：2008-09-01

申请人： John David Maltson

发明人： John David Maltson

IPC分类号： F04D29/58

CPC分类号： F01D5/18 ,  F01D25/246 ,  F05D2260/2212 ,  F05D2260/22141

摘要： A turbomachine is provided. The turbomachine includes a rotor, a stator and a plurality of blade discs mounted on the rotor. The rotor includes a turbulator cylinder where a plurality of turbulators are provided on a curved surface of the turbulator cylinder and the stator includes an annular shroud extending around the turbulator cylinder. The plurality of turbulators increase a heat transfer to a coolant flowing between the adjacent opposed surfaces of the turbulator cylinder and the annular shroud.

摘要翻译： 提供涡轮机。 涡轮机包括转子，定子和安装在转子上的多个叶片盘。 该转子包括一个湍流缸，其中多个湍流器设置在湍流器气缸的曲面上，定子包括围绕湍流器气缸延伸的环形护罩。 多个湍流器增加了对在紊流器气缸的相邻相对表面和环形护罩之间流动的冷却剂的热传递。