Airfoil shape for arrays of airfoils

Details Airfoil shape for arrays of airfoils Airfoil shape for arrays of airfoils

F - Mech Eng,Light,Heat,Weapons

01

D

170/81

F01D 5/12 (2006.01)

Patent

CA 1170575

Abstract A flow directing assembly 14 having an airfoil section or shape 28 of the type adapted for use in an axial flow gas turbine engine is disclosed. The cambered meanline MCL of the airfoil shape is formed of a front circular arc FA and a rear circular arc RA. A thickness distribution TD is applied to the meanline to form the convex suction surface 20 and the concave pressure surface 22. The airfoil section exhibits good aerodynamic performance as compared with an equivalent circular arc airfoil in a transonic flow field. A method for making the airfoil shape is disclosed. The method includes the steps of: forming a cambered mean- line of two circular arcs; forming a thickness distri- bution about the conical chord line Bt; and applying thickness distribution to the cambered meanline such that a portion of the suction surface is stretched and a portion of the pressure surface is compressed.

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