Blades
AssigneeSmiths Aerospace, Inc.
InventorsGraham Hill, Paul Methven
Life of this patent
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Abstract
Compressor fan blades have an isotropic core and composite fiber layers in an epoxy matrix. The fibers on opposite broad surfaces of the blade extend at an angle of between 25° and 35° to the blade length. The fibers on opposites sides of the blade are inclined in opposite senses such that extension force applied to the blade as it rotates produces opposing forces in the composite layers that resist untwisting of the blade. The thickness of the fiber layers varies from the leading edge to the trailing edge, being thicker towards the leading edge.
Claims16
A blade for turbomachinery, said blade having a length, being twisted along its length and comprising:
- a leading edge extending along the length of the blade;
- a trailing edge extending along the length of the blade;
- two opposed broad surfaces extending along the length of the blade and separated from one another by said leading and trailing edges;
- and composite fiber layers adjacent respective ones of said opposed surfaces, wherein said layers on said opposed surfaces are arranged such that extension forces applied to said blade along its length produce opposing forces in said composite layers resisting untwisting of said blade.
A blade for turbomachinery, said blade having a length, being twisted along its length and comprising:
- a leading edge extending along the length of said blade;
- a trailing edge extending along the length of said blade;
- two opposed broad surfaces extending along the length of said blade and separated from one another by said leading and trailing edges;
- and composite fiber layers adjacent respective ones of said opposed surfaces, wherein fibers in said layers on opposed surfaces are inclined with respect to one another such that extension forces applied to said blade along its length produce oppositely-directed shear forces in said two composite layers resisting untwisting of said blade.
Turbomachinery including a plurality of blades arranged for rotation about an axis, said blades each having a length extending radially of said axis, being twisted along its length and comprising:
- a leading edge extending along the length of said blade;
- a trailing edge extending along the length of said blade;
- two opposed broad surfaces extending along the length of said blade and separated from one another by said leading and trailing edges;
- and composite fiber layers adjacent respective ones of said opposed surfaces, wherein said layers on said opposed surfaces are arranged such that extension forces applied to said blades along their length produce opposing forces in said composite layers resisting untwisting of said blades.
A gas-turbine engine including a plurality of compressor fan blades arranged for rotation about an axis, said blades each having a length extending radially of said axis and comprising:
- a leading edge extending along the length of said blade;
- a trailing edge extending along the length of said blade;
- two opposed broad surfaces extending along the length of said blade and separated from one another by said leading and trailing edges;
- and composite fiber layers adjacent respective ones of said opposed surfaces, wherein said layers on said opposed surfaces are arranged such that extension forces applied to said blades along their length produce opposing forces in said composite layers resisting untwisting of said blades.
Dependencies are inferred from the claim text.