公开(公告)号：US09920636B2

公开(公告)日：2018-03-20

申请号：US14499386

申请日：2014-09-29

Applicant: ALSTOM Technology Ltd

Inventor： Herbert Brandl

IPC: F01D5/22 ,  F01D5/14 ,  F01D5/30 ,  F01D5/32 ,  F01D11/00

CPC classification number: F01D5/22 ,  F01D5/147 ,  F01D5/3007 ,  F01D5/326 ,  F01D11/008 ,  F05B2240/57 ,  F05D2230/50 ,  F05D2230/51 ,  F05D2240/55 ,  F05D2240/57 ,  F05D2240/80 ,  F05D2260/30 ,  F05D2260/31 ,  F05D2260/36 ,  F05D2260/96

Abstract: The invention relates to a turbine blade, including a blade having a front edge and a rear edge, which blade transitions by means of a shaft into a blade root designed for fastening the turbine blade, and including a platform, which is arranged at the lower end of the blade in order to bound a flow channel. The platform is designed as a separate component and can be connected to the blade in a form-fit manner. Flexible application is achieved in that the platform is composed of several individual platform elements, which enclose the blade in the assembled state.

公开(公告)号：US08967972B2

公开(公告)日：2015-03-03

申请号：US13668136

申请日：2012-11-02

Applicant: ALSTOM Technology Ltd

Inventor： Herbert Brandl ,  Igor Tsypkakyin ,  Philipp Indlekofer

IPC: F01D5/08 ,  F01D5/02 ,  B23P15/02 ,  F01D5/22 ,  F01D5/18

CPC classification number: F01D5/225 ,  F01D5/187 ,  Y10T29/49341

Abstract: A turbine blade is provided and includes a tip end carrying a shroud and at least one fin, which extends radially away from the shroud. The fin includes a first sidewall and a second sidewall, which are spaced apart, arranged parallel to each other, and are connected to the shroud, and a cutting edge, which is connected to the first and second sidewalls. The cutting edge thereby creates a hollow space between the sidewalls, the shroud, and the cutting edge, and further extends radially away from the first and second sidewalls. Also provided is a method of manufacturing the blade by casting the blade as single piece with the hollow fin or by forging the blade; and machining the fin to create the first and second sidewalls and cutting edge thereby opening the hollow space between said sidewalls and the cutting edge.

Abstract translation: 涡轮机叶片被设置并且包括承载护罩的末端和至少一个翅片，其从护罩径向延伸。 翅片包括第一侧壁和第二侧壁，第一侧壁和第二侧壁间隔开，彼此平行设置并且连接到护罩，以及连接到第一和第二侧壁的切割边缘。 因此，切割边缘在侧壁，护罩和切割边缘之间形成中空空间，并进一步从第一和第二侧壁径向延伸。 还提供了通过将叶片与中空翅片一体铸造或通过锻造叶片来制造叶片的方法; 并且加工翅片以产生第一和第二侧壁和切割刃，从而打开所述侧壁和切割边缘之间的中空空间。

公开(公告)号：US09890646B2

公开(公告)日：2018-02-13

申请号：US14625734

申请日：2015-02-19

Applicant: ALSTOM Technology Ltd

Inventor： Joerg Krueckels ,  Brian Kenneth Wardle ,  Herbert Brandl ,  Marc Widmer

IPC: F01D5/18 ,  F01D9/02 ,  B22C9/24

CPC classification number: F01D5/189 ,  B22C9/24 ,  F01D5/186 ,  F01D9/02 ,  F05D2260/201 ,  F05D2260/202

Abstract: An internally cooled airfoil for a rotary machine, for example, a gas turbine engine includes a suction and pressure side wall each extending in an axial direction, i.e. from a leading to a trailing edge of the airfoil. A suction wall sided cooling channel and a pressure wall sided cooling channel extend in the axial direction. A feed chamber is defined between a first and second inner wall for feeding the suction wall and pressure wall sided cooling channel each by at least one through hole inside of the first and second inner wall. The suction wall sided cooling channel and the pressure wall sided cooling channel extend into the trailing edge region separately. The suction wall sided cooling channel and the pressure wall sided cooling channel join before discharging at the trailing edge.

公开(公告)号：US09822654B2

公开(公告)日：2017-11-21

申请号：US14505588

申请日：2014-10-03

Applicant: ALSTOM Technology Ltd

Inventor： Herbert Brandl ,  Andrey Anatolievich Sedlov ,  Artem Ivanov

IPC: F01D9/06 ,  F01D25/14 ,  F01D11/08

CPC classification number: F01D9/065 ,  F01D9/06 ,  F01D11/08 ,  F01D25/14 ,  F05D2240/11 ,  F05D2240/15

Abstract: A cooled wall segment in the hot gas path of a gas turbine. The wall segment includes a first surface, exposed to a medium of relatively high temperature, a second surface, exposed to a medium of relatively low temperature, and side surfaces connecting the first and second surface and defining a height of the wall segment. At least one cooling channel for a flow-through of a fluid cooling medium extends through the wall segment. Each cooling channel is provided with an inlet and an outlet for the cooling medium. The at least one cooling channel includes at least two heat transfer sections, a first heat transfer section extending essentially parallel to the first surface at a first distance from the first surface and a second heat transfer section extending essentially parallel to the first surface at a second distance, whereby the second distance is less than the first distance.

公开(公告)号：US09777577B2

公开(公告)日：2017-10-03

申请号：US14445346

申请日：2014-07-29

Applicant: ALSTOM Technology Ltd

Inventor： Herbert Brandl ,  Joerg Krueckels ,  Felix Reinert

IPC: F01D5/18 ,  F01D5/08 ,  F01D25/12

CPC classification number: F01D5/081 ,  F01D5/085 ,  F01D5/186 ,  F01D5/187 ,  F01D25/12 ,  F05D2230/10 ,  F05D2240/81 ,  F05D2260/20 ,  F05D2260/208

Abstract: The invention relates to a component for a thermal machine, in particular a gas turbine, which includes a corner and/or edge subjected to a thermally high load. The cooling of the component is improved in a manner such that at least one cooling channel is countersunk into the surface of the component in the immediate vicinity of the corner and/or edge in order to cool the corner and/or edge.

公开(公告)号：US09494039B2

公开(公告)日：2016-11-15

申请号：US13950344

申请日：2013-07-25

Applicant: ALSTOM Technology Ltd

Inventor： Beat Von Arx ,  Herbert Brandl

IPC: F01D5/00 ,  F01D9/04

CPC classification number: F01D5/005 ,  F01D9/042 ,  Y10T29/49229

Abstract: The invention refers to a stationary gas turbine arrangement with at least one turbine stage that includes at least a first row of vanes being mounted at a stationary component arranged radially outside of the first row of vanes and extending radially into an annular entrance opening of the turbine stage facing a downstream end of a combustor. Further a method for performing maintenance work on a stationary gas turbine is described. The invention is characterized in that the stationary component provides for each vane a radially orientated through-hole designed and arranged for a radial insertion and removal of the vane, and each of said vanes comprises an airfoil having at its one end directed radially outwards a contour being adapted to close the through-hole airtight by a detachable fixation means.

Abstract translation: 本发明涉及一种具有至少一个涡轮级的固定式燃气轮机装置，该至少一个涡轮级包括至少第一排叶片，其安装在设置在第一排叶片的径向外侧的固定部件处并径向延伸到涡轮机的环形入口 面向燃烧器的下游端。 另外，对固定式燃气轮机进行维修工作的方法进行说明。 本发明的特征在于，固定部件为每个叶片提供设计和布置用于径向插入和移除叶片的径向取向的通孔，并且每个叶片包括翼型件，其翼端在其一端径向向外指向轮廓 适于通过可拆卸的固定装置密封通孔。

公开(公告)号：US09702262B2

公开(公告)日：2017-07-11

申请号：US14335203

申请日：2014-07-18

Applicant: ALSTOM Technology Ltd

Inventor： Herbert Brandl ,  Hans-Peter Bossmann

IPC: F01D11/18 ,  F01D9/04 ,  F01D11/08 ,  F01D25/24 ,  F01D11/12

CPC classification number: F01D11/18 ,  F01D9/04 ,  F01D11/08 ,  F01D11/122 ,  F01D25/246 ,  F05D2240/11 ,  F05D2240/55 ,  F05D2260/30 ,  F05D2300/20 ,  F05D2300/21 ,  F05D2300/2112 ,  F05D2300/2118 ,  F05D2300/50212

Abstract: A stator component of a turbomachine includes at least one axially extending outer ring which serves as a frame of an inner ring composed of partial segments. The partial segments are arranged on one another such that, on the rotor side, to form a coherent circular circumferential surface in relation to the rotational movement of rotor blades. The individual partial segment is composed of a material of uniform construction or, at least in a radial direction, of multiple partial bodies constructed from different materials, such as for example ceramic, wherein a partial segment thus formed exhibits predetermined stress and/or expansion behavior as a function of the load ranges of the turbomachine.

公开(公告)号：US09174275B2

公开(公告)日：2015-11-03

申请号：US14189377

申请日：2014-02-25

Applicant: ALSTOM Technology Ltd

Inventor： Herbert Brandl ,  Hans-Peter Bossmann

IPC: B22D19/00 ,  B22D19/04 ,  B22D19/08 ,  C04B37/02 ,  C23C6/00 ,  B32B15/04

CPC classification number: B22D19/00 ,  B22D19/04 ,  B22D19/08 ,  B32B15/043 ,  C04B37/026 ,  C23C6/00 ,  Y10T428/12396

Abstract: A method for manufacturing a metal-ceramic composite structure for high temperature exposure is provided, whereby the composite structure includes a base metal structure or component, which is on at least one side covered and permanently joined with one or more ceramic tiles. The method may include the steps of: manufacturing green bodies with cavities and sintering the green bodies to receive ceramic tiles into cavities; arranging the ceramic tiles in a cast mould; pouring liquid metal into the cast mould to substantially fill the cavities; creating an intermediate metal layer; and solidifying the liquid metal to permanently join the ceramic tiles and the intermediate metal layer.

Abstract translation: 提供了一种用于制造用于高温暴露的金属 - 陶瓷复合结构体的方法，由此该复合结构包括在与一个或多个陶瓷砖覆盖并永久连接的至少一个侧面上的基底金属结构或部件。 该方法可以包括以下步骤：制造具有空腔的生坯，并烧结生坯以将陶瓷砖接收到空腔中; 将陶瓷砖布置在铸模中; 将液态金属浇注到铸模中以基本上填充空腔; 形成中间金属层; 并固化液态金属以永久地连接瓷砖和中间金属层。

公开(公告)号：US20150159490A1

公开(公告)日：2015-06-11

申请号：US14625734

申请日：2015-02-19

Applicant: ALSTOM Technology Ltd

Inventor： Joerg KRUECKELS ,  Brian Kenneth Wardle ,  Herbert Brandl ,  Marc Widmer

IPC: F01D5/18 ,  F01D9/02

CPC classification number: F01D5/189 ,  B22C9/24 ,  F01D5/186 ,  F01D9/02 ,  F05D2260/201 ,  F05D2260/202

Abstract: The invention refers to an internally cooled casted airfoil for a rotary machine, preferably a gas turbine engine comprising a suction and a pressure side wall each extending in an axial direction, i.e. from a leading to a trailing edge region of said airfoil. At least one suction wall sided cooling channel extends in axial direction confined by the suction side wall and a first inner wall. At least one pressure wall sided cooling channel extends in axial direction confined by the pressure side wall and a second inner wall. At least one feed chamber is defined between the first and second inner wall for feeding said at least one suction and pressure sided cooling channel each by at least one through hole inside of the first and second inner wall. At least one suction wall sided cooling channel and the at least one pressure wall sided cooling channel extend into the trailing edge region separately. At least one suction wall sided cooling channel and at least one pressure wall sided cooling channel join before discharging at the trailing edge.

Abstract translation: 本发明涉及一种用于旋转机器的内部冷却铸造翼型件，优选地是包括抽吸和压力侧壁的燃气涡轮发动机，其各自在轴向方向上延伸，即从所述翼型的导向到后缘区域延伸。 至少一个抽吸壁侧冷却通道在被吸入侧壁和第一内壁限制的轴向方向上延伸。 至少一个压力壁侧冷却通道在受压侧壁和第二内壁限制的轴向方向上延伸。 至少一个进料室限定在第一和第二内壁之间，用于将第一和第二内壁内的至少一个通孔各自供给至少一个吸入和压力侧冷却通道。 至少一个抽吸壁侧冷却通道和至少一个压力壁侧冷却通道分别延伸到后缘区域。 至少一个抽吸壁侧冷却通道和至少一个压力壁侧冷却通道在后缘排放之前连接。

公开(公告)号：US20140030077A1

公开(公告)日：2014-01-30

申请号：US13950344

申请日：2013-07-25

Applicant: ALSTOM Technology Ltd

Inventor： Beat Von Arx ,  Herbert Brandl

IPC: F01D5/00

CPC classification number: F01D5/005 ,  F01D9/042 ,  Y10T29/49229

Abstract: The invention refers to a stationary gas turbine arrangement with at least one turbine stage that includes at least a first row of vanes being mounted at a stationary component arranged radially outside of the first row of vanes and extending radially into an annular entrance opening of the turbine stage facing a downstream end of a combustor. Further a method for performing maintenance work on a stationary gas turbine is described. The invention is characterized in that the stationary component provides for each vane a radially orientated through-hole designed and arranged for a radial insertion and removal of the vane, and each of said vanes comprises an airfoil having at its one end directed radially outwards a contour being adapted to close the through-hole airtight by a detachable fixation means.

Abstract translation: 本发明涉及一种具有至少一个涡轮级的固定式燃气轮机装置，该至少一个涡轮级包括至少第一排叶片，其安装在设置在第一排叶片的径向外侧的固定部件处并径向延伸到涡轮机的环形入口 面向燃烧器的下游端。 另外，对固定式燃气轮机进行维修工作的方法进行说明。 本发明的特征在于，固定部件为每个叶片提供设计和布置用于径向插入和移除叶片的径向取向的通孔，并且每个叶片包括翼型件，其翼端在其一端径向向外指向轮廓 适于通过可拆卸的固定装置密封通孔。