Patent ID: 7258525
Filing Date: 2007-08-21
Classification: F01D,Y02T

Abstract:
1. An arrangement for fixing a guide blade segment that forms part of a transition channel between the housing and the bearing pedestal of a turbine housing of a high-pressure turbine and a low-pressure turbine with aircraft gas turbines having different diameters, the transition channel transitioning from a smaller diameter of the high-pressure turbine to a larger diameter of the lower pressure turbine, wherein the guide blade segment comprises an outer platform and an inner platform tensioning the guide blades, wherein the outer and inner platforms, for axial positioning and sealing of the guide blade segment, comprise bars, wherein each of the bars enables a straight surface contact with bearing surfaces of the bearing pedestal and the turbine housing, wherein the guide blade segment, by way of an upstream groove-hook-type connection assigned to the outer platform, is held radially on the turbine housing and secured against rotation by way of a substantially radially extending pin that engages in a slot defined in a hook of the hook-groove-type connection, and wherein a groove of the groove-hook-type connection is assigned to one of the bearing surfaces of the turbine housing and the hook of the groove-hook-type connection is assigned to the outer platform of the guide blade segment.