Blade cascade and turbomachine

Abstract

A blade cascade of a turbomachine having at least one shape variation of a blade situated on the blade side in the proximity of a side wall and extending downstream, and at least one side wall contouring of the side wall or at least one second shape variation of an adjacent blade near the side wall, as well as a turbomachine, are disclosed.

What is claimed is: 
     
         1 . A blade cascade of a turbomachine, the blade cascade comprising:
 a plurality of blade channels in a peripheral direction delimited in each case by a pressure side of a blade and by an oppositely situated suction side of an adjacent blade, and in a radial direction delimited in each case by two oppositely situated side walls,   at least one side wall of the blade channels in each case having at least one circumferentially asymmetrical side wall contouring in an area of one of the blade and the adjacent blade, the other of the blade and the adjacent blade in a pressure side or suction side area facing the side wall contouring having at least one shape variation extending downstream, at the side wall.   
     
     
         2 . The blade cascade as recited in  claim 1  wherein the shape variation is a thickened area of the pressure side, and the at least one side wall contouring is an impression on the suction side. 
     
     
         3 . The blade cascade as recited in  claim 2  wherein the shape variation extends downstream from a leading edge on the pressure side, and the side wall contouring begins upstream from a leading edge on the suction side. 
     
     
         4 . The blade cascade as recited in  claim 2  wherein a further side wall contouring in the form of a suction-side projection is situated downstream from the side wall contouring. 
     
     
         5 . The blade cascade as recited in  claim 1  wherein the shape variation is an abrasion or cutout of the suction side, and the at least one side wall contouring is a projection on the pressure side. 
     
     
         6 . The blade cascade as recited in  claim 5  wherein the shape variation begins downstream from a leading edge on the suction side, and the side wall contouring begins upstream from a leading edge on the pressure side. 
     
     
         7 . The blade cascade as recited in  claim 5  wherein a further side wall contouring in the form of a pressure-side impression is situated downstream from the side wall contouring. 
     
     
         8 . A turbomachine comprising the blade cascade as recited in  claim 1 . 
     
     
         9 . A blade cascade of a turbomachine, the blade cascade comprising:
 a plurality of blade channels in a peripheral direction delimited in each case by a pressure side of a blade and by an oppositely situated suction side of an adjacent blade, and in radial direction are in each case by two oppositely situated side walls, the pressure side and the oppositely situated suction side each having at least one shape variation extending downstream, at at least one of the side walls.   
     
     
         10 . The blade cascade as recited in  claim 9  wherein the pressure-side shape variation is a thickened area and the suction-side shape variation is an abrasion or cutout. 
     
     
         11 . A turbomachine comprising the blade cascade as recited in  claim 9 .