公开(公告)号：US09903209B2

公开(公告)日：2018-02-27

申请号：US14574897

申请日：2014-12-18

Applicant: ALSTOM Technology Ltd

Inventor： Joerg Krueckels ,  Marc Widmer

IPC: F01D5/18 ,  F01D9/02

CPC classification number: F01D5/187 ,  F01D9/02 ,  F05D2250/292 ,  F05D2260/2212 ,  F05D2260/22141

Abstract: The invention refers to a rotor blade or guide vane airfoil for a gas turbine engine having a longitudinal axis and a source of cooling fluid. The airfoil has a pressure wall, a suction wall, a leading edge, a trailing edge and at least one cooling fluid flow passage. The cooling fluid flow passage is in fluid communication with the source of cooling fluid. Means for directing cooling fluid at least to the trailing edge are provided, whereas the cooling fluid flow passage including: a plurality of axially extending walls, each of the walls extending laterally between the pressure wall and suction wall. The plurality of walls are radially spaced within the cooling fluid flow passage such that adjacent pairs of walls define a channel. The axial spacing between the adjacent walls include in radial direction of the airfoil a pins and a ribs structure, wherein the pins holistic or approximately cover the axial height of the channel. The ribs have a deeper level with respect to the pins and the ribs establish a bridge-like connection between each of adjacent ribs.

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：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：US20150267549A1

公开(公告)日：2015-09-24

申请号：US14662319

申请日：2015-03-19

Applicant: ALSTOM Technology Ltd.

Inventor： Emanuele FACCHINETTI ,  Guillaume Wagner ,  Marc Henze ,  Joerg Krueckels ,  Marc Widmer

IPC: F01D9/06 ,  F01D9/02 ,  F01D25/12

CPC classification number: F01D9/065 ,  F01D5/188 ,  F01D5/189 ,  F01D9/02 ,  F01D9/041 ,  F05D2220/32 ,  F05D2240/81 ,  F05D2260/201 ,  F05D2260/205

Abstract: The disclosure pertains to a vane comprising a platform and airfoil extending form said platform and connected to the platform by a fillet. An impingement tube is inserted into said airfoil delimiting a cooling channel between the impingement tube and the side walls. The vane further comprises a baffle structure positioned adjacent the fillet and which follows the inside contour of the fillet; delimiting a first cooling passage between the fillet and the baffle structure. A first obstruction is arranged on the inside of the airfoil at the connection of the fillet to the side walls for separating the first cooling passage from the cooling channel in the airfoil and to guide the cooling gas from the first cooling passage into the impingement tube. The disclosure further refers to a method for cooling such a vane.

Abstract translation: 本公开涉及一种叶片，其包括从所述平台延伸并且通过圆角连接到平台的平台和翼型件。 冲击管被插入到限定冲击管和侧壁之间的冷却通道的所述翼型件中。 所述叶片还包括邻近所述圆角定位并且跟随所述圆角的内部轮廓的挡板结构; 限定圆角和挡板结构之间的第一冷却通道。 在翼片与侧壁的连接处，在翼型件的内部设置第一障碍物，用于将第一冷却通道与翼型中的冷却通道分离，并将冷却气体从第一冷却通道引导到冲击管中。 本发明还涉及冷却这种叶片的方法。