公开(公告)号：US09097119B2

公开(公告)日：2015-08-04

申请号：US13668274

申请日：2012-11-04

Applicant: ALSTOM Technology Ltd

Inventor： Thomas Heinz-Schwarzmaier ,  Marc Widmer ,  Selma Zahirovic ,  Paul Marlow

IPC: F01D9/00 ,  F01D9/02 ,  F01D11/00 ,  F02C6/00

CPC classification number: F01D9/023 ,  F01D11/005 ,  F02C6/003 ,  F05D2240/127

Abstract: A gas turbine is provided having a secondary combustion chamber and a first guide vane row of a low-pressure turbine, the row being arranged directly downstream of the chamber. The radially outer boundary of the secondary combustion chamber is formed by at least one outer wall segment, which is secured on at least one support element arranged radially outwardly. The flow path of the hot gases is bounded radially outwardly, in the region of the guide vane row, by an outer platform which is secured at least indirectly on at least one guide vane support. A substantially radially extending gap-shaped cavity having a width in the range of 1-25 mm in the axial direction in the inlet region is arranged between the wall segment and the outer platform. At least one step element, which reduces the width by at least 10% in at least one step, extending substantially perpendicularly to the direction of flow of the hot gas in the cavity, is arranged in the inlet region.

Abstract translation: 提供一种燃气轮机，其具有二次燃烧室和低压涡轮机的第一导向叶片排，该排直接设置在室的下游。 二次燃烧室的径向外边界由至少一个外壁段形成，该外壁段固定在径向向外布置的至少一个支撑元件上。 热气体的流动路径在导向叶片排的区域中径向向外限定外部平台，该外部平台至少间接地固定在至少一个导向叶片支撑件上。 在壁部段和外部平台之间布置有在入口区域中在轴向方向上具有1-25mm范围内的宽度的大致径向延伸的间隙形腔。 在入口区域中布置有至少一个步进元件，其在基本垂直于空腔中的热气体的流动方向的至少一个步骤中将至少10％的宽度减小。

公开(公告)号：US20150001815A1

公开(公告)日：2015-01-01

申请号：US14489630

申请日：2014-09-18

Applicant: ALSTOM Technology Ltd

Inventor： Ulrich Robert Steiger ,  Thomas Heinz-Schwarzmaier

IPC: F01D11/00

CPC classification number: F01D11/005 ,  F05B2240/572 ,  F05B2250/184 ,  F05D2240/55 ,  F16J15/0887

Abstract: A strip seal and method of configuration thereof for sealing portions of components of a gas turbine exposed to pressure pulsations. The strip seal has a sealing face that is configured to follow the contours of first portions of the components. The strip seal further has a pressure face that has a sinusoidal curvilinear shape with respect to the sealing face. The pressure face is configured to prevent localized movement of strip seal by configuring pressure face on its first side to contact sealing face at a plurality of points, on its second side to contact second portions of the components at a plurality of points.

Abstract translation: 一种带状密封件及其构造方法，用于密封暴露于压力脉动的燃气涡轮机部件的部分。 带状密封件具有密封面，其被构造成遵循部件的第一部分的轮廓。 带状密封件还具有相对于密封面具有正弦曲线形状的压力面。 压力面被构造成通过在其第一侧上配置压力面以在多个点处在其第二侧上接触密封面以防止在多个点处接触部件的第二部分的带状密封件的局部移动。

公开(公告)号：US09267385B2

公开(公告)日：2016-02-23

申请号：US14489630

申请日：2014-09-18

Applicant: ALSTOM Technology Ltd

Inventor： Ulrich Robert Steiger ,  Thomas Heinz-Schwarzmaier

IPC: F16J15/02 ,  F01D11/00 ,  F16J15/08

CPC classification number: F01D11/005 ,  F05B2240/572 ,  F05B2250/184 ,  F05D2240/55 ,  F16J15/0887

Abstract: A strip seal and method of configuration thereof for sealing portions of components of a gas turbine exposed to pressure pulsations. The strip seal has a sealing face that is configured to follow the contours of first portions of the components. The strip seal further has a pressure face that has a sinusoidal curvilinear shape with respect to the sealing face. The pressure face is configured to prevent localized movement of strip seal by configuring pressure face on its first side to contact sealing face at a plurality of points, on its second side to contact second portions of the components at a plurality of points.

Abstract translation: 一种带状密封件及其构造方法，用于密封暴露于压力脉动的燃气涡轮机部件的部分。 带状密封件具有密封面，其被构造成遵循部件的第一部分的轮廓。 带状密封件还具有相对于密封面具有正弦曲线形状的压力面。 压力面被构造成通过在其第一侧上配置压力面以在多个点处在其第二侧上接触密封面以防止在多个点处接触部件的第二部分的带状密封件的局部移动。