Patent ID: 11885233
Assignee: GE AVIO S.R.L.
Field: Engines, pumps, turbines (Mechanical engineering)
Classification: CPC F  Y | IPC F

Claim 0:
1. An airfoil assembly comprising:
at least two airfoils carried by a rotor and configured to rotate about a rotational axis, the at least two airfoils being circumferentially spaced from each other, with respect to the rotational axis, to define a pitch (P) therebetween, each airfoil of the at least two airfoils comprising:
an outer wall defining a pressure side and a suction side extending in a chord-wise direction between a leading edge to a trailing edge and extending in a span-wise direction between a root and a tip;
a mean camber line extending between the leading edge and the trailing edge and intersecting the leading edge to define a leading edge intersection, and intersecting the trailing edge to define a trailing edge intersection;
an inlet angle, βin, in degrees, defined by an included angle between a line parallel to the mean camber line at the leading edge intersection and the rotational axis; and
an outlet angle, βout, in degrees, defined by an included angle between a line parallel to the mean camber line at the trailing edge intersection and the rotational axis;
an axial chord length (Cax) extending between the leading edge and the trailing edge in an axial direction with respect to the rotational axis;
a blade turning (BT) of less than 100 degrees along at least 30% of a span of the airfoil, wherein the blade turning (BT) is determined by:, BT
  =
  
   
    
     ❘
     "\[LeftBracketingBar]"
    
    
     β
     out
    
    
     ❘
     "\[RightBracketingBar]"
    
   
   +
   
    
     
      β
      
       i
       ⁢
       n
      
     
     *
     
      β
      out
     
    
    
     
      ❘
      "\[LeftBracketingBar]"
     
     
      β
      out
     
     
      ❘
      "\[RightBracketingBar]"
     
    
   
  
 

 and
an airfoil solidity (Sl) of the at least two airfoils is determined by:, c
    
     a
     ⁢
     x
    
   
   
    P
     
   
  
  ;
 

wherein the airfoil solidity (Sl) is greater than or equal to 0.6 and less than or equal to 1.2 (0.6≤Sl≤1.2); and

wherein βin is constant along the span from the root to the tip, or βout is constant along the span from the root to the tip.