A structural composite airfoil includes a primary structural element, and a secondary structural element defining a trailing edge of the structural composite airfoil. The primary structural element includes an upper skin panel extending from an upper leading edge end to an upper trailing edge end, a lower skin panel extending from a lower leading edge end to a lower trailing edge end, and a bracket coupled to the lower skin panel. The leading edge region of the primary structural element has a bullnose shape defined by the lower skin panel. The upper skin panel includes an integrally formed front C-channel spar having a lower flange coupled to the lower skin panel. The lower flange is adjacent the upper leading edge end, and the integrally formed front C-channel spar is coupled to the bracket, thereby further coupling the lower skin panel to the integrally formed front C-channel spar.
STRUCTURAL COMPOSITE AIRFOILS WITH AN IMPROVED LEADING EDGE, AND RELATED METHODS
2021-11-25
Patent
Electronic Resource
English
Structural composite airfoils with an improved leading edge, and related methods
European Patent Office | 2022
|STRUCTURAL COMPOSITE AIRFOILS WITH AN IMPROVED LEADING EDGE, AND RELATED METHODS
European Patent Office | 2021
|STRUCTURAL COMPOSITE AIRFOILS WITH AN IMPROVED LEADING EDGE, AND RELATED METHODS
European Patent Office | 2021
|STRUCTURAL COMPOSITE AIRFOILS WITH AN IMPROVED LEADING EDGE, AND RELATED METHODS
European Patent Office | 2021
|