Abstract: A hybrid-material construction for string instruments may include providing an internal lattice framework structure encased in a composite material to produce a final form of a string instrument. The framework structure may provide a lightweight structural support system within a finished instrument to reduce overall weight while maintaining strength of the instrument.

Abstract: A hybrid-material construction for string instruments may include providing an internal lattice framework structure encased in a composite material to produce a final form of a string instrument. The framework structure may provide a lightweight structural support system within a finished instrument to reduce overall weight while maintaining strength of the instrument.

Abstract: A light weight fan blade for a gas turbine engine is disclosed. The disclosed fan blade has an increased chord length at a transition section between the inner edge or single tooth attachment portion of the fan blade that connects to the rotor disk and the airfoil. Increasing the chord length at the transition section substantially reduces the stress concentration when the fan blade is operated under normal operating conditions. Reducing the stress concentration enables engineers to design lighter fan blades and larger fan blades for larger gas turbine engines. By increasing the size of gas turbine engines, additional thrust can be provided without adding additional engines to the aircraft.

Abstract: A gas turbine engine rotor includes a hub having a slot. A blade includes a root received in the slot. An under-root area is provided between the root and the fan hub in the slot. A spacer includes first and second portions that cooperate with one another to provide an adjustment feature with discrete height settings. The adjustment feature provides different radial heights of the spacer. The spacer is arranged in the under-root area beneath the root.

Abstract: A method for making a metallic component includes placing a diffusion bonded airfoiled component having an initial shape into a first intermediate shaping die. The first intermediate shaping die has a cavity corresponding to a first intermediate shape different from the initial shape. The component is shaped into the first airfoil shape by applying a first elevated temperature to the first intermediate shaping die. The component is transferred into a final shaping die, which has a cavity corresponding to a target nominal shape different from the first intermediate shape and the initial shape. The component is shaped into a final nominal shape substantially equivalent to the target nominal shape by applying a final elevated temperature to the final shaping die.

Abstract: A gas turbine engine rotor includes a hub having a slot. A blade includes a root received in the slot. An under-root area is provided between the root and the fan hub in the slot. A spacer includes first and second portions that cooperate with one another to provide an adjustment feature with discrete height settings. The adjustment feature provides different radial heights of the spacer. The spacer is arranged in the under-root area beneath the root.