Vane comprising a transition zone

Abstract

A vane of a guide vane or impeller blade of a turbo machine, particularly a gas turbine. The profile of the vane includes at least one thickening that is advantageous for flow purposes in a radially inward final region and/or a radially outward final region of the vane. The thickening is cut in the area of a forward edge of the vane so as to form a mirror surface or a basal plane.

1 - 14 . (canceled)  
   
   
       15 . A blade of a guide vane or of a rotor blade of a fluid flow machine comprising: 
 at least one thickened portion of the blade profile beneficial from a standpoint of fluid mechanics on a radially inside end region and/or on a radially outside end region of the blade,    the thickened portion having a cut in an area of a leading edge of the blade forming a mirror surface or a basal plane.    
   
   
       16 . The blade as recited in  claim 15  wherein the cut is a straight or plane cut.  
   
   
       17 . The blade as recited in  claim 16  wherein the cut in such a way that a cut direction of the cut extends circumferentially or transversely to an axial direction of the fluid flow machine.  
   
   
       18 . The blade as recited in  claim 15  wherein the cut is a circular segment-shaped or cylindrical segment-shaped cut.  
   
   
       19 . The blade as recited in  claim 18  wherein cut has a tangent line at a frontmost portion extending circumferentially or transversely to the axial direction of the fluid flow machine.  
   
   
       20 . The blade as recited in  claim 15  wherein the blade is a blade of a guide vane, the thickened portion being formed in each case at a radially inside, hub-side end region and at a radially outside, housing-side end region of the blade.  
   
   
       21 . The blade as recited in  claim 15  wherein the blade is a rotor blade, the thickened portion being formed at a radially inside, hub-side end region.  
   
   
       22 . The blade as recited in  claim 15  wherein the at least one thickened portion is formed by a large radius of curvature at the radially inside end region and/or at the radially outside end region of the blade, a ratio of the radius of curvature to a chord length of the blade being between 2% and 10%.  
   
   
       23 . The blade as recited in  claim 22 , wherein the ratio of the radius of curvature to the chord length of the blade is between 4% and 8%.  
   
   
       24 . The blade as recited in  claim 23 , wherein the ratio of the radius of curvature to the chord length of the blade is between 5% and 7%.  
   
   
       25 . The blade as recited in  claim 22  wherein the radius of curvature is designed to be variable to diminish from the leading edge toward a trailing edge of the blade profile.  
   
   
       26 . The blade as recited in  claim 15  wherein the at least one thickened portion is formed by increasing at least one profile parameter of a leading-edge nose radius and/or a leading-edge wedge angle and/or a trailing-edge wedge angle and/or an absolute profile thickness, as compared to a contour of a reference profile section.  
   
   
       27 . A gas turbine comprising a blade as recited in  claim 15 .  
   
   
       28 . A fluid flow machine comprising: 
 at least one guide vane ring having a plurality of guide vanes and at least one rotor blade ring having a plurality of rotor blades, the guide vanes and the rotor blades each having blades that extend in the radial direction of a flow channel, and, at a radially inside end region and/or at a radially outside end region of the blade, the blades exhibiting a thickened portion of the blade profile that is beneficial from a standpoint of fluid mechanics,    the thickened portion having a cut in an area of a leading edge of the blade forming a mirror surface or a basal plane.    
   
   
       29 . The fluid flow machine as recited in  claim 28  wherein the fluid flow machine is a gas turbine.  
   
   
       30 . The fluid flow machine as recited in  claim 28  wherein the cut is a straight or plane cut.  
   
   
       31 . The fluid flow machine as recited in  claim 28  wherein the cut is a circular segment-shaped or cylindrical segment-shaped cut.  
   
   
       32 . The fluid flow machine as recited in  claim 28  wherein the at least one thickened portion is formed by a large radius of curvature at the radially inside end region and/or at the radially outside end region of the blade, a ratio of the radius of curvature to a chord length of the blade being between 2% and 10%.  
   
   
       33 . The fluid flow machine as recited in  claim 28  wherein the at least one thickened portion is formed by increasing at least one profile parameter of a leading-edge nose radius and/or a leading-edge wedge angle and/or a trailing-edge wedge angle and/or an absolute profile thickness, as compared to a contour of a reference profile section.  
   
   
       34 . The fluid flow machine as recited in  claim 28  wherein the blade is a blade of a guide vane, the thickened portion being formed in each case at a radially inside, hub-side end region and at a radially outside, housing-side end region of the blade.  
   
   
       35 . The fluid flow machine as recited in  claim 28  wherein the blade is a rotor blade, the thickened portion being formed at a radially inside, hub-side end region.