Abstract: The present invention is directed to a turbomachinery blade and a method of fabricating the turbomachinery blade. The turbomachinery blade comprises a plurality of blade segments, and the plurality of the blade segments are separate from one another at least partially in an axial direction forming radial seams between adjacent blade segments. The method comprises forming a plurality of blade segments which are separate from one another at least partially in an axial direction; and forming radial seams between adjacent blade segments.

Abstract: The present invention is directed to a turbomachinery blade and a method of fabricating the turbomachinery blade. The turbomachinery blade comprises a plurality of blade segments, and the plurality of the blade segments are separate from one another at least partially in an axial direction forming radial seams between adjacent blade segments. The method comprises forming a plurality of blade segments which are separate from one another at least partially in an axial direction; and forming radial seams between adjacent blade segments.

Abstract: A mounting system includes a rotatable machine, a frame circumscribing the rotatable machine, and a plurality of mounting elements. Each mounting element of the plurality of mounting elements includes a pin member and a joint member. The joint member includes a rotatable joint capable of three degrees of freedom of rotation, and the joint member is slidably coupled to the pin member, such that each mounting element is capable of four degrees of freedom of motion. The plurality of mounting elements are further coupled between the frame and the rotatable machine and spaced circumferentially about the rotatable machine, such that the rotatable machine is able to expand and contract radially within the frame. The mounting system provides a uniform stiffness in any radial direction from the engine centerline within the lateral-vertical engine plane.

Abstract: A mounting system includes a rotatable machine, a frame circumscribing the rotatable machine, and a plurality of mounting elements. Each mounting element of the plurality of mounting elements includes a pin member and a joint member. The joint member includes a rotatable joint capable of three degrees of freedom of rotation, and the joint member is slidably coupled to the pin member, such that each mounting element is capable of four degrees of freedom of motion. The plurality of mounting elements are further coupled between the frame and the rotatable machine and spaced circumferentially about the rotatable machine, such that the rotatable machine is able to expand and contract radially within the frame. The mounting system provides a uniform stiffness in any radial direction from the engine centerline within the lateral-vertical engine plane.