Airfoil and corresponding guide vane, blade, gas turbine and turbomachine

Abstract

An airfoil suitable for being arranged in a compressor section of the gas turbine includes a platform, a pressure surface and a suction surface, and a tip region. The tip region is located between the pressure and the suction surface opposite to the platform in respect of the pressure and the suction surfaces, being a distant end of the airfoil in direction along the first direction perpendicular to the platform. The tip region includes a first surface with a first distance to the platform along the first direction, and a second surface with a second distance to the platform along the first direction. The first distance is greater than the second distance and the first surface and the second surface together build a profiled surface. The profiled surface is a ribbed surface. The material of the first surface is deformable to bend away from the rotation direction of the airfoil.

1 - 10 . (canceled) 
     
     
         11 . An airfoil of a gas turbine, the airfoil suitable for being arranged in a compressor section of the gas turbine, the airfoil comprising:
 a platform;   a pressure surface and a suction surface, extending substantially perpendicular to the platform along a first direction, the first direction being defined as a direction substantially perpendicular to the platform and progressing with a distance to the platform;   a tip region between the pressure and the suction surface opposite to the platform, the tip region being a distant end of the airfoil in direction along the first direction and being configured such that the tip region comprises:
 a first surface with a first surface expanse less than a cross sectional plane of the airfoil perpendicular to the first direction and with a first distance to the platform along the first direction, 
 a second surface with a second surface expanse and with a second distance to the platform along the first direction, 
   wherein the first distance is greater than the second distance, and   wherein the first surface and the second surface together build a profiled surface, the profiled surface being a ribbed surface, and   wherein the material of the first surface is deformable such that the material of the first surface bends away from a direction of rotation of the airfoil during operation.   
     
     
         12 . The airfoil according to  claim 11 , wherein the first surface includes a plurality of elevated areas of the profiled surface and the second surface includes a plurality of recessed areas of the profiled surface. 
     
     
         13 . The airfoil according to  claim 12 , wherein the plurality of elevated areas of the profiled surface and the plurality of recessed areas of the profiled surface are arranged alternating. 
     
     
         14 . The airfoil according to  claim 11 , the elevated areas and the recessed areas are arranged as ribs between the suction surface and the pressure surface. 
     
     
         15 . The airfoil according to  claim 11 , the elevated areas and the recessed areas are arranged as ribs substantially parallel to the suction surface or to the pressure surface. 
     
     
         16 . The airfoil according to  claim 11 , the elevated areas and the recessed areas are arranged in a grid pattern. 
     
     
         17 . The airfoil according to  claim 16 , wherein the grid pattern has a shape of a first plurality of ribs intersected with a second plurality of ribs, the first plurality of ribs being diagonal in direction of a trailing edge of the airfoil and the second plurality of ribs being diagonal in direction of a leading edge of the airfoil. 
     
     
         18 . The airfoil according to  claim 16 , wherein the grid pattern having a shape of an inverse profile of a first plurality of ribs intersected with a second plurality of ribs, the first plurality of ribs being diagonal in direction of a trailing edge of the airfoil and the second plurality of ribs being diagonal in direction of a leading edge of the airfoil. 
     
     
         19 . The airfoil according to  claim 11 , wherein the tip region is coated with an abrasive coating for abrading an opposing surface. 
     
     
         20 . The airfoil according to  claim 11 , wherein the tip region is coated with an abradable coating. 
     
     
         21 . A component of a gas turbine, comprising an airfoil according to  claim 11 . 
     
     
         22 . The component according to  claim 21 , wherein the component is a variable guide vane. 
     
     
         23 . The component according to  claim 21 , wherein the component is a blade. 
     
     
         24 . A gas turbine, comprising:
 at least one of a compressor section or a turbine section, the compressor section or the turbine section comprising at least one airfoil configured according to  claim 11 .