The Diffusion Bonded Boron/Aluminum Spar-Shell Fan Blade Program consisted of a design and a process development tasks intended to demonstrate composite blade application in large high-bypass ratio turbofan engines. The design task included selection of a representative airfoil model; a preliminary design effort, which included parametric studies of component materials and geometries, selection of two candidate designs for detail designing; and a detail design effort on two designs which would ...
Design and process development tasks intended to demonstrate composite blade application in large high by-pass ratio turbofan engines are described. Studies in a 3.0 aspect radio space and shell construction fan blade indicate a potential weight savings for a first stage fan rotor of 39% when a hollow titanium spar is employed. An alternate design which featured substantial blade internal volume filled with titanium honeycomb inserts achieved a 14% potential ...
The Diffusion Bonded Boron/Aluminum Spar-Shell Fan Blade Program consisted of a design and a process development tasks intended to demonstrate composite blade application in large high-bypass ratio turbofan engines. The design task included selection of a representative airfoil model; a preliminary design effort, which included parametric studies of component materials and geometries, leading to the selection of two candidate designs, subject to NASA Project Manager approval, for detail designing; and ...
The design and process development tasks of the Diffusion Bonded Boron/Aluminum Spar-Shell Fan Blade Program were performed. These tasks were intended to demonstrate composite blade application in large high-bypass ratio turbo fan engines. The design task included selection of a representative airfoil model and a preliminary design effort leading to the selection of two candidate designs subject to NASA Project Manger approval for detail designing. The process development task consisted ...
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