Abstract: A high modulus component, such as an aircraft engine turbine blade, is formed from a base metal that has a high modulus crystallographic orientation that is aligned with the primary, i.e. radial, direction of the turbine blade. The base metal is Ni, Fe, Ti, Co, Al, Nb, or Mo based alloy. Alignment of a high modulus direction of the base metal with the primary direction provides enhanced high cycle fatigue life.

Abstract: A high modulus component, such as an aircraft engine turbine blade, is formed from a base metal that has a high modulus crystallographic orientation that is aligned with the primary, i.e. radial, direction of the turbine blade. The base metal is Ni, Fe, Ti, Co, Al, Nb, or Mo based alloy. Alignment of a high modulus direction of the base metal with the primary direction provides enhanced high cycle fatigue life.

Abstract: A device for sealing between and damping of adjacent rotor blade platforms is provided which includes a forward seal member, a compliant center seal member, an aft seal member, a first damper, and a second damper. The first damper is disposed between the forward and compliant center seal members, and the second damper is disposed between the compliant center and aft seal members. The compliant center seal member is disposed between the first and second dampers. The compliant center seal member accommodates misalignment between adjacent rotor blade platforms by deflecting in response to centrifugal forces acting on the dampers.

Abstract: The internal blade damper is an elongated member with a damping surface of discrete width in contact with the interior blade surfaces. Contact is continuous throughout a substantial length. The damper extends between 2.degree. and 30.degree. from the radial direction, producing a direction of contact having some radial component. Centrifugal force loads the damping surface.