Rotating turbomachine component having a tip leakage flow guide

Abstract

A rotating turbomachine component includes a base portion and an airfoil portion extending from the base portion. The airfoil portion includes a first end connected to the base portion and a tip end portion that is cantilevered from the base portion. A tip leakage flow guide is provided at the tip end portion of the airfoil portion. The tip leakage flow guide includes one or more turning vane members configured and disposed to guide a leakage flow from the tip end portion at a flow angle that substantially coincides with a flow angle of gases flowing downstream from the rotating turbomachine component.

What is claimed is: 
     
         1 . A rotating turbomachine component comprising:
 a base portion;   an airfoil portion extending from the base portion, the airfoil portion including a first end connected to the base portion and a tip end portion that is cantilevered from the base portion; and   a tip leakage flow guide provided at the tip end portion of the airfoil portion, the tip leakage flow guide including one or more turning vane members configured and disposed to guide a leakage flow from the tip end portion at a flow angle that substantially coincides with a flow angle of gases flowing downstream from the rotating turbomachine component.   
     
     
         2 . The rotating turbomachine component according to  claim 1 , further comprising: a turning vane support member positioned at the tip end portion, the turning vane support member having an upstream end, and a downstream end, each of the upstream end and the downstream end projecting beyond the tip end portion, the one or more turning vane members projecting outward from the turning vane support member. 
     
     
         3 . The rotating turbomachine component according to  claim 2 , wherein the tip leakage flow guide is arranged at the downstream end of the turning vane support member. 
     
     
         4 . The rotating turbomachine component according to  claim 1 , wherein the one or more turning vane members comprise a plurality of substantially linear vane members extending across the tip end portion, each of the plurality of substantially linear vane members including a first end and a second end, the second end being off-set relative to the first end. 
     
     
         5 . The rotating turbomachine component according to  claim 1 , wherein the one or more turning vane members comprise a plurality of curvilinear vane members extending across the tip end portion. 
     
     
         6 . The rotating turbomachine component according to  claim 1 , wherein the one or more turning vane members comprise a plurality of complex geometrical vane members extending across the tip end portion. 
     
     
         7 . The rotating turbomachine component according to  claim 6 , wherein each of the plurality of complex geometrical vane members including a first vane member having a first end section that extends to a second end section, and a second vane member having a first end portion that extends from the second end section of the first vane member to a second end portion, the second end portion being off-set relative to the first end section. 
     
     
         8 . The rotating turbomachine component according to  claim 1 , wherein the one or more turning vane members are arranged at an angle that generally corresponds to an airfoil profile of the airfoil portion. 
     
     
         9 . A method of operating a turbomachine comprising:
 passing hot gases from a combustor assembly toward a plurality of buckets;   guiding the hot gases onto the plurality of buckets;   directing the hot gases downstream relative to the plurality of buckets along a gas path at a first flow angle;   passing a portion of the hot gases over a tip end portion of the plurality of buckets at a second flow angle that is distinct from the first flow angle; and   guiding the portion of the hot gases from the tip end portion of the plurality of buckets at a third flow angle that substantially coincides with the first flow angle.   
     
     
         10 . The method of  claim 9 , wherein passing the portion of hot gases from the tip end portion includes guiding the portion of hot gases across one or more turning vane members arranged at the tip end portion. 
     
     
         11 . The method of  claim 10 , wherein guiding the portion of hot gases across one or more turning vane members includes passing the portion of hot gases over a plurality of angled vane members. 
     
     
         12 . The method of  claim 10 , wherein guiding the portion of hot gases across one or more turning vane members includes passing the portion of hot gases over a plurality of curvilinear vane members. 
     
     
         13 . The method of  claim 10 , wherein guiding the portion of hot gases across one or more turning vane members includes passing the portion of hot gases at an angle that generally corresponds to an angle of an airfoil portion of each of the plurality of buckets. 
     
     
         14 . A turbomachine comprising:
 a compressor portion;   a combustor assembly fluidly connecting the compressor portion;   a turbine portion mechanically linked to the compressor portion and fluidly connected to the combustor assembly, the turbine portion including a rotating component having a base portion and an airfoil portion extending from the base portion, the airfoil portion including a first end connected to the base portion and a tip end portion that is cantilevered from the base portion;   a tip leakage flow guide provided at the tip end portion of the airfoil portion, the tip leakage flow guide including one or more turning vane members configured and disposed to guide a leakage flow from the tip end portion at a flow angle that substantially coincides with a flow angle of gases flowing downstream from the rotating component; and   a turning vane support member positioned at the tip end portion, the turning vane support member having an upstream end and a downstream end, the one or more turning vane members projecting outward from the turning vane support member.   
     
     
         15 . The turbomachine according to  claim 14 , wherein the one or more turning vane members is arranged at an angle that generally corresponds to an airfoil profile of the airfoil portion. 
     
     
         16 . The turbomachine according to  claim 15 , wherein the angle of the one or more turning vane members is within no more than about 30° of a trailing edge angle of the airfoil profile. 
     
     
         17 . The turbomachine according to  claim 14 , wherein the one or more turning vane members comprise a plurality of substantially linear vane members extending across the tip end portion, each of the plurality of substantially linear vane members including a first end and a second end, the second end being off-set relative to the first end. 
     
     
         18 . The turbomachine according to  claim 13 , wherein the one or more turning vane members comprise a plurality of curvilinear vane members extending across the tip end portion. 
     
     
         19 . The turbomachine according to  claim 13 , wherein the one or more turning vane members comprise a plurality complex geometrical vane members extending across the tip end portion. 
     
     
         20 . The turbomachine according to  claim 19 , wherein the plurality of complex geometrical vane members include a first vane member having a first end section that extends to a second end section, and a second vane member having a first end portion that extends from the second end section of the first vane member to a second end portion, the second end portion being off-set relative to the first end section.