Blade row, blade and turbomachine

Abstract

A blade row for a turbomachine is disclosed. The blade row has an inner lateral wall and an outer lateral wall for bordering a hot gas channel in the turbomachine through which hot gas passes. At least one of the lateral walls has a rounded lateral wall front edge, which is provided with a circumferentially asymmetrical edge contouring that is elliptical or is comprised of one or more segments of a circle.

What is claimed is: 
     
         1 . A blade row of a turbomachine, comprising:
 an inner lateral wall;   an outer lateral wall;   wherein the inner lateral wall and the outer lateral wall border a hot gas channel of the turbomachine through which hot gas flows; and   a plurality of turbine blades disposed between the inner lateral wall and the outer lateral wall;   wherein at least one of the inner lateral wall and the outer lateral wall has a rounded lateral wall front edge which includes a circumferentially asymmetrical edge contouring;   and wherein the edge contouring is elliptical or is comprised of one or more segments of a circle.   
     
     
         2 . The blade row according to  claim 1 , wherein the edge contouring is wave-shaped in a circumferential direction. 
     
     
         3 . The blade row according to  claim 1 , wherein respective root fillets of the plurality of turbine blades are disposed in the edge contouring. 
     
     
         4 . The blade row according to  claim 1 , wherein the edge contouring is integrated into a lateral wall contouring of the at least one of the inner lateral wall and the outer lateral wall. 
     
     
         5 . The blade row according to  claim 1 , wherein the at least one of the inner lateral wall and the outer lateral wall is free of a contour and the edge contouring tapers into the at least one of the inner lateral wall and the outer lateral wall. 
     
     
         6 . The blade row according to  claim 1 , wherein a lateral wall rear edge of the at least one of the inner lateral wall and the outer lateral wall is free of a contour. 
     
     
         7 . The blade row according to  claim 1 , wherein a front lateral wall overhang of the at least one of the inner lateral wall and the outer lateral wall is free of a contour. 
     
     
         8 . The blade row according to  claim 1 , wherein a rear lateral wall overhang of the at least one of the inner lateral wall and the outer lateral wall is free of a contour. 
     
     
         9 . A turbomachine having a blade row according to  claim 1 .