公开(公告)号：US20150176412A1

公开(公告)日：2015-06-25

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.

Abstract translation: 本发明涉及一种用于燃气涡轮发动机的转子叶片或导叶翼型件，其具有纵向轴线和冷却流体源。 翼型件具有压力壁，吸力壁，前缘，后缘和至少一个冷却流体流动通道。 冷却流体流动通道与冷却流体源流体连通。 提供了用于将冷却流体引导至后缘的装置，而冷却流体流动通道包括：多个轴向延伸的壁，每个壁在压力壁和抽吸壁之间横向延伸。 多个壁在冷却流体流动通道内径向间隔开，使得相邻的壁对形成通道。 相邻壁之间的轴向间隔在翼型件的径向方向上包括销和肋结构，其中销整体地或近似地覆盖通道的轴向高度。 这些肋相对于销具有更深的水平，并且肋在每个相邻的肋之间建立桥状连接。

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。