Gas turbine

Abstract

A gas turbine stage, in particular a low-pressure compressor stage, for a gas turbine, in particular an aircraft engine gas turbine having a guide vane assembly having at least one guide vane ( 1 ) having a radially inner guide vane root ( 1.1 ), on which a sealing ring element ( 2 ) is supported by a spoke-type centering that has an inner wall ( 1.2 ) and a circumferential groove ( 2.1, 2.2 ) receiving the same, the inner wall having at least one face ( 1.4 ) facing a groove inner surface of the circumferential groove and a flank ( 1.5 ) adjacent thereto and angled therefrom; a rounded portion, in particular a radius (R) being formed between the face and the flank.

What is claimed is: 
     
         1 . A gas turbine stage for a gas turbine, the gas turbine stage comprising:
 a guide vane assembly having at least one guide vane having a radially inner guide vane root,   a sealing ring element supported on the guide vane assembly by a spoke-type centering that has an inner wall and a circumferential groove receiving the inner wall, the inner wall having at least one face facing a groove inner surface of the circumferential groove and a flank adjacent thereto and angled therefrom, wherein a rounded portion is formed between the face and the flank.   
     
     
         2 . The gas turbine stage as recited in claim I wherein the rounded portion defines a radius R. 
     
     
         3 . The gas turbine stage as recited in  claim 1  wherein the inner wall is joined to the guide vane root, and the circumferential groove is formed on the sealing ring element. 
     
     
         4 . The gas turbine stage as recited in  claim 3  wherein the inner wall is joined integrally to the guide vane root. 
     
     
         5 . The gas turbine stage as recited in  claim 1  wherein the inner wall is joined to the sealing ring element, and the circumferential groove is formed on the guide vane root. 
     
     
         6 . The gas turbine stage as recited in  claim 5  wherein the inner wall is joined integrally to the sealing ring element. 
     
     
         7 . The gas turbine stage as recited in  claim 1  wherein the at least one guide vane includes at least two interconnected guide vanes having a common inner wall or circumferential groove. 
     
     
         8 . The gas turbine stage as recited in  claim 7  wherein the two interconnected guide vanes are integrally interconnected. 
     
     
         9 . The gas turbine stage as recited in  claim 1  wherein the inner wall has a radial groove for receiving a sliding element for forming the spoke-type centering. 
     
     
         10 . The gas turbine stage as recited in  claim 2  wherein the radius is at least 25% of a width of the flank. 
     
     
         11 . The gas turbine stage as recited in  claim 10  wherein the radius is at least 30% of the width of the flank. 
     
     
         12 . The gas turbine stage as recited in  claim 2  wherein the radius is at least 0.5 mm. 
     
     
         13 . The gas turbine stage as recited in  claim 12  wherein the radius is at least 10 mm. 
     
     
         14 . The gas turbine stage as recited in  claim 13  wherein the radius is at least 15 mm. 
     
     
         15 . The gas turbine stage as recited in  claim 1  wherein the rounded portion is produced by master forming, forming, or machining, or is hardened. 
     
     
         12 . The gas turbine stage as recited in  claim 1  wherein the sealing ring element is a brush sealing ring element. 
     
     
         13 . The gas turbine stage as recited in  claim 1  wherein the rounded portion is provided at one end of the face in the circumferential direction that is positioned against the adjacent groove inner surface in response to torsion in the preferential direction for torsion of the guide vane assembly. 
     
     
         14 . A low-pressure compressor stage comprising the gas turbine stage as recited in  claim 1 . 
     
     
         15 . A gas turbine comprising at least one gas turbine stage as recited in  claim 1 . 
     
     
         16 . An aircraft engine comprising the gas turbine as recited in  claim 15 . 
     
     
         17 . A guide vane assembly for a gas turbine, the guide vane assembly comprising at least one guide vane having a radially inner guide vane root and an inner wall joined thereto that is provided to be received in a circumferential groove of a sealing ring element of the gas turbine, the inner wall having at least one face facing a groove inner surface of the circumferential groove and a flank adjacent thereto and angled therefrom, and a rounded portion being formed between the face and the flank. 
     
     
         18 . The guide vane assembly as recited in  claim 17  wherein the rounded portion defines a radius R. 
     
     
         19 . A sealing ring element for a gas turbine comprising an inner wall joined thereto that is provided to be received in a circumferential groove of a guide vane assembly of the gas turbine, the inner wall having at least one face facing a groove inner surface of the circumferential groove and a flank adjacent thereto and angled therefrom, and a rounded portion being formed between the face and the flank. 
     
     
         20 . The sealing ring element as recited in  claim 19  wherein the rounded portion defines a radius R.