公开(公告)号：US20140197601A1

公开(公告)日：2014-07-17

申请号：US14154487

申请日：2014-01-14

Applicant: ALSTOM Technology Ltd

Inventor： Paul MARLOW ,  Selma Zahirovic ,  Robert Marmilic ,  Marc Widmer ,  Joerg Krückels

IPC: F01D11/04

CPC classification number: F01D11/04 ,  F01D11/005 ,  F01D11/02 ,  F01D25/12 ,  F05D2240/121 ,  F05D2240/127 ,  F16J15/40 ,  F16J15/44 ,  F16J15/443

Abstract: The invention refers to an arrangement for sealing an open cavity against hot gas entrainment. The open cavity is arranged between two axially adjacent stationary components limiting radially a hot gas path of a rotary flow machine, of which at least the downstream component carries at least one airfoil extending radially into said hot gas path. A multitude of air jets is directed into the open cavity such that hot gas flowing over the open cavity is prevented from penetrating into the open cavity completely. The invention has an arrangement of supply conduits for air jets which are directed into the open cavity with a jet momentum such that hot gas is induced not to enter the open cavity and forming at least one hot gas vortex close to the hot gas path within the open cavity and preventing hot gas from penetrating into the open cavity beyond the extension of the hot gas vortex.

Abstract translation: 本发明涉及一种用于密封开放空腔以抵抗热气体夹带的装置。 敞开的空腔布置在两个轴向相邻的固定部件之间径向限制旋转流动机器的热气体通道，其中至少下游部件承载至少一个径向延伸到所述热气体通道中的翼型件。 多个空气射流被引导到开放空腔中，使得流过开放空腔的热气体被完全渗透到开口腔中。 本发明具有用于空气射流的供应管道的布置，其以射流动量被引导到开放空腔中，使得热气体被引入不进入开放空腔并且形成靠近该热气体路径内的至少一个热气体涡流 开放的腔体，防止热气体渗入热空气涡流延伸的开放空腔内。

公开(公告)号：US20130055717A1

公开(公告)日：2013-03-07

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: F02C1/00

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。