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。