Blade component

Abstract

A blade component has a longitudinal axis and extends between a root end and a tip end. The component comprises a composite laminate structure, the laminate structure comprising a plurality of plies of fibres in a matrix, wherein all the plies are arranged such that the fibres in respective plies are oriented symmetrically relative to the component axis at respective layup angles, the layup angles being in the range of 19° to 25° and −19° to −25° respectively relative to the component axis.

1 . A blade component having a longitudinal axis and extending between a root end and a tip end, the component comprising a composite laminate structure, the laminate structure comprising a plurality of plies of fibres in a matrix, wherein all the plies are arranged such that the fibres in respective plies are oriented symmetrically relative to the component axis at respective layup angles, the layup angles being in the range of 19° to 25° and −19° to −25° respectively relative to the component axis. 
     
     
         2 . A blade component as claimed in  claim 1 , wherein the plurality of plies comprises one or more first plies each comprising fibres aligned at a layup angle α relative to the component axis and one or more second plies each comprising fibres aligned at a layup angle of −α relative to the component axis. 
     
     
         3 . A blade component as claimed in  claim 2  wherein the plurality of plies further comprises one or more third plies comprising fibres aligned at a layup angle of β relative to the component axis and one or more fourth plies comprising fibres aligned at a layup angle of −β relative to the component axis and wherein β is different from α, wherein α and β are both in the range of 19° to 25° and −19° to −25° 
     
     
         4 . A blade component as claimed in  claim 1 , wherein alternating plies are arranged symmetrically relative to the component axis. 
     
     
         5 . A blade component as claimed in  claim 1 , wherein the layup angle is in the range ±20° to 23°. 
     
     
         6 . A method of manufacturing a blade component having a longitudinal axis and extending between a root end and a tip end, the method comprising:
 laying a plurality of plies of fibres on a core, all the plies being arranged such that the fibres in the plies are oriented symmetrically relative to the component axis at respective layup angles, the layup angles being in the range of 19° to 25° and −19° to −25° respectively relative to the component axis; and   curing the component with the plies to form a laminated structure on the core.   
     
     
         7 . A method of manufacturing a blade component as claimed in  claim 6 , wherein the plurality of plies comprises one or more first plies each comprising fibres aligned at a layup angle a relative to the component axis and one or more second plies each comprising fibres aligned at a layup angle of −α relative to the component axis. 
     
     
         8 . A method of manufacturing a blade component as claimed in  claim 7 , wherein the plurality of plies further comprises one or more third plies comprising fibres aligned at a layup angle of β relative to the component axis and one or more fourth plies comprising fibres aligned at a layup angle of −β relative to the component axis. 
     
     
         9 . A method of manufacturing a blade component as claimed in  claim 6 , wherein alternating plies are oriented symmetrically relative to the component axis. 
     
     
         10 . A method of manufacturing a blade component as claimed in  claim 6 , wherein the layup angle is in the range ±20° to 23° 
     
     
         11 . A blade component or method as claimed in  claim 6 , wherein the plies are formed from sheets or tapes of fibre material. 
     
     
         12 . A method as claimed in  claim 11 , wherein the plies are pre-impregnated with a resin or wherein a resin is applied to the plies for curing. 
     
     
         13 . A method of manufacturing a blade component as claimed in  claim 6 , wherein the blade component is a propeller blade component or a fan blade component. 
     
     
         14 . A method of manufacturing a blade component as claimed in  claim 6 , wherein the blade component is a blade spar. 
     
     
         15 . A blade component as claimed in  claim 1 , wherein the blade component is a propeller blade component or a fan blade component. 
     
     
         16 . A blade component as claimed in  claim 1 , wherein the blade component is a blade spar. 
     
     
         17 . A blade component as claimed in  claim 14 , wherein the laminate structure is provided on a core of the spar.