Moving blade and turbomachine

Abstract

A moving blade for a turbomachine, in particular an aircraft engine, is disclosed, having an inner shroud which has a front elongation for forming an axial overlap with an upstream guide blade, and on which at least one flow guide element for deflecting a leakage flow of a cooling air flow in the peripheral direction is situated. The at least one flow guide element is guided beyond a leading edge of the elongation. A turbomachine having a plurality of these types of moving blades is also disclosed.

What is claimed is: 
     
         1 . A moving blade for a turbomachine comprising:
 an inner shroud having a front elongation for forming an axial overlap with an upstream guide blade;   at least one flow guide element for deflecting a leakage flow of a cooling air flow being situated in a peripheral direction, the at least one flow guide element extending in an axial direction beyond a leading edge of the elongation.   
     
     
         2 . The moving blade as recited in  claim 1  wherein the flow guide element terminates in flush alignment with a hot gas side and with a cooling air side of the elongation. 
     
     
         3 . The moving blade as recited in  claim 1  wherein the flow guide element protrudes beyond a hot gas side and a cooling air side of the elongation in the radial direction. 
     
     
         4 . The moving blade as recited in  claim 1  wherein the flow guide element has a hot gas side section on a hot gas side of the elongation. 
     
     
         5 . The moving blade as recited in  claim 4  wherein the hot gas side is located over an entirety of an axial extension of the elongation. 
     
     
         6 . The moving blade as recited in  claim 4  wherein the hot gas side section has a constant height. 
     
     
         7 . The moving blade as recited in  claim 1  wherein the flow guide element has a cooling air side section on a cooling air side of the elongation. 
     
     
         8 . The moving blade as recited in  claim 7  wherein the cooling gas side is located over an entirety of an axial extension of the elongation. 
     
     
         9 . The moving blade as recited in  claim 7  wherein the cooling gas side section has a constant height. 
     
     
         10 . The moving blade as recited in  claim 1  wherein the flow guide element has a hot gas side section on the hot gas side of the elongation, and a cooling air side section on a cooling air side of the elongation. 
     
     
         11 . The moving blade as recited in  claim 6  the hot gas side section and the cooling air side section are oriented oppositely with respect to one another, viewed in a direction of rotation. 
     
     
         12 . The moving blade as recited in  claim 10  wherein the hot gas side and/or the cooling air section is located over an entirety of an axial extension of the elongation. 
     
     
         13 . The moving blade as recited in  claim 10  wherein the hot gas side section and/or the cooling air side section has a constant height. 
     
     
         14 . The moving blade as recited in  claim 1  wherein the at least one flow guide element includes a plurality of flow guide elements. 
     
     
         11 . A turbomachine comprising:
 a moving blade row having a plurality of moving blades as recited in  claim 1 .   
     
     
         12 . An aircraft engine comprising the turbomachine as recited in  claim 11 .