Rotor blade for a compressor of a turbomachine, compressor, and turbomachine

Abstract

A rotor blade for a compressor of a turbomachine is disclosed, the rotor blade having an airfoil having a leading edge, a trailing edge, an airfoil tip, as well as a pressure side and a suction side extending therebetween, provision being made for a profile variation on the pressure side, the profile variation extending into the trailing edge and into the airfoil tip. Also disclosed are a compressor and a turbomachine.

1 - 11 . (canceled) 
     
     
         12 . A rotor blade for a compressor of a turbomachine, comprising:
 an airfoil having a leading edge, a trailing edge, and an airfoil tip ( 12 ), the airfoil having a pressure side and a suction side extending therebetween, and a profile variation on the pressure side, the profile variation extending into the trailing edge and into the airfoil tip.   
     
     
         13 . The rotor blade as recited in  claim 12  wherein the profile variation forms a recess open toward the airfoil tip and toward the trailing edge. 
     
     
         14 . The rotor blade as recited in  claim 13  wherein the profile variation begins in the region of a maximum pressure gradient. 
     
     
         15 . The rotor blade as recited in  claim 12  wherein the profile variation forms an undulating profile. 
     
     
         16 . The rotor blade as recited in  claim 15  wherein the undulating profile is oriented transversely to the direction of flow of the airfoil. 
     
     
         17 . A compressor comprising at least one blade row including a plurality of rotor blades as recited in  claim 12 . 
     
     
         18 . The compressor as recited in  claim 17  further comprising a side wall radially opposite the rotor blades, the profile variations on the pressure sides being enlarged toward the suction sides and each merging into a set-back extending through the airfoil tips in the direction of rotation, and a plurality of counter-contours are formed in the side wall. 
     
     
         19 . The compressor as recited in  claim 18  wherein the set-backs and the counter-contours are symmetrical to each other. 
     
     
         20 . The compressor as recited in  claim 18  wherein the set-backs and the counter-contours form rectangular enlargements of an annular gap between the side wall and the rotor blades. 
     
     
         21 . The compressor as recited in  claim 18  wherein the set-backs and the counter-contours form funnel-shaped enlargements of an annular gap between the side wall and the rotor blades. 
     
     
         22 . A turbomachine comprising the compressor as recited in  claim 17 .