Fabricated hybrid turbine blade

Abstract

A blade for a turbine includes: a support structure of high strength material as a central portion of the blade, the support structure including a root and a body extending to a tip, the body providing a leading edge, a trailing edge and mounting section; and a honeycomb skin attached to the mounting section for providing a lightweight airfoil portion of the blade. A method and a turbine are included.

1 . A blade for a turbine, the blade comprising:
 a support structure of high strength material, as a central portion of the blade, the support structure comprising a root and a body extending to a tip, the body providing a leading edge, a trailing edge and a mounting section; and   a honeycomb skin attached to the mounting section for providing a lightweight airfoil portion of the blade.   
   
   
       2 . The blade as in  claim 1 , wherein the support structure comprises one to many perforations. 
   
   
       3 . The blade as in  claim 1 , wherein the support structure comprises at least one gripping feature. 
   
   
       4 . The blade as in  claim 1 , wherein the support structure comprises a material that is at least one of a superalloy, a cobalt based alloy, a hardened alloy, a carbide based alloy, a nickel based alloy, a undirectionally solidified alloy, a iron based alloy, a wrought austenitic stainless steel, a martensitic stainless steel, a ferritic stainless steel, a carbon steel, a common titanium alloy and an inter-metallic titanium alloy. 
   
   
       5 . The blade as in  claim 1 , wherein the honeycomb skin comprises a material that is at least one of a superalloy, a cobalt based alloy, a hardened alloy, a carbide based alloy, a nickel based alloy, a undirectionally solidified alloy, a iron based alloy, a wrought austenitic stainless steel, a martensitic stainless steel, a ferritic stainless steel, a carbon steel, a common titanium alloy and an inter-metallic titanium alloy. 
   
   
       6 . The blade as in  claim 1 , comprising an overlap of honeycomb skin on at least one of the leading edge and the trailing edge. 
   
   
       7 . The blade as in  claim 1 , wherein an interface between the mounting section and the honeycomb skin comprises at least one of a brazed, a bonded and a welded interface. 
   
   
       8 . The blade as in  claim 1 , wherein the honeycomb skin further comprises an inner surface. 
   
   
       9 . The blade as in  claim 1 , wherein an angle between a wall of the honeycomb skin and a plane that is normal to a face of the mounting section is between about minus sixty degrees to about plus sixty degrees. 
   
   
       10 . The blade as in  claim 1 , wherein an angle for a vertex of a cell of the honeycomb skin is between about twenty degrees to about seventy degrees. 
   
   
       11 . The blade as in  claim 1 , wherein an aspect ratio for cells of the honeycomb skin ranges between about 0.5 to about 6. 
   
   
       12 . A method for fabricating a blade for a turbine, the method comprising:
 using a high strength material, forming a central portion of the blade, the central portion comprising a root and a body extending to a tip, the body providing a leading edge, a trailing edge and mounting section; and   attaching a honeycomb skin to a surface of the central portion to provide an airfoil of the blade.   
   
   
       13 . The method as in  claim 12 , wherein attaching comprises at least one of brazing, bonding, welding and fusing the honeycomb skin to the central portion. 
   
   
       14 . The method as in  claim 12 , further comprising attaching an overlap to at least one of the trailing edge and the leading edge. 
   
   
       15 . The method as in  claim 12 , further comprising designing the support structure to include dimensions for installation into one of a compressor of a gas turbine, a low pressure turbine, and a steam turbine. 
   
   
       16 . The method as in  claim 12 , wherein forming comprises at least one of casting, forging, welding, brazing, sanding, polishing and etching. 
   
   
       17 . A turbine comprising:
 at least one blade comprising a support structure of high strength material, the support structure comprising a root and a body extending to a tip, the body providing a leading edge, a trailing edge and a mounting section; and   a honeycomb skin attached to the mounting section for providing a lightweight airfoil portion of the blade.   
   
   
       18 . The turbine of  claim 17 , wherein at least one blade is comprised within one of a compressor of a gas turbine, a low pressure turbine, and a steam turbine. 
   
   
       19 . The turbine of  claim 17 , comprising one of an aircraft gas turbine and a power generation gas turbine.