Abstract: The interlocking of two or more sections via the insertion of one or more out-of-plane features in one section or combination of sections through a void in one or more a complementary sections can result in a reinforced ceramic matrix composite article upon securing of the sections. The sections can be secured by friction between two tightly matched sections or by the use of a pin, hook, or clamp. The sections can be constructed from one or more CMC laminate sheets. The out-of-plane feature can be a loop or a flange and the void can be an orifice or a matched loop in the complementary sheet. The securing of the sections can result in a CMC article where the delamination between sheets is inhibited.

Abstract: The interlocking of two or more sections via the insertion of one or more out-of-plane features in one section or combination of sections through a void in one or more a complementary sections can result in a reinforced ceramic matrix composite article upon securing of the sections. The sections can be secured by friction between two tightly matched sections or by the use of a pin, hook, or clamp. The sections can be constructed from one or more CMC laminate sheets. The out-of-plane feature can be a loop or a flange and the void can be an orifice or a matched loop in the complementary sheet. The securing of the sections can result in a CMC article where the delamination between sheets is inhibited.

Abstract: A welded joint between two metal members in which the weld must support a structural load. The abutting faces of the welded members have step portions formed therein, in which the step portions extend beyond the surface of the adjoining welded members. The outer step portion of one member extends beyond an inner step portion of the adjacent member, and a weld is applied on abutting faces of the members and the step portions. The welded joint of this invention is intended to be used for two adjacent rotor discs in a gas turbine engine. But, the weld arrangement of this invention can be used for welding two pipes together, or two adjacent plate members. The weld arrangement of this invention provides for reduced stress distribution along the weld line that acts to increase part life.

Abstract: A centrifugal impeller having an inlet and a plurality of outlets the outlets including at least one outlet in a forward direction of the Impeller and at least one outlet in a rearward direction of the impeller. A flow path distance of the outlet in the forward direction can be greater than a flow path distance of the outlet in the rearward direction in order to provide a greater pressure in the outlet having the greater flow path distance. In another embodiment, the flow path volume in the forward direction can be greater than the flow path volume in the rearward direction in order to provide a greater flow volume in the forward direction In another embodiment, the number of flow paths in the forward direction can be greater than the number of flow paths in the rearward direction in order to provide a greater flow volume in the forward direction.

Abstract: A gas turbine engine includes a tip shroud ring rotatably supported on a last stage blade assembly in a turbine. The tip shroud ring is formed entirely of a fiber reinforced ceramic matrix composite material to provide a very light weight tip shroud ring, but also a very strong ring. The blades include pins extending from the tips, and the tip shroud ring includes holes in which the pins slide. Thus, the tip shroud ring is completely supported by the blade tip pins, and the centrifugal force developed by the rotation of the tip shroud ring does not add to the tensile force developed along the blades. Thus, the maximum rotational speed of the turbine rotor as defined by An2 can be increased. Also, because the blade tips are secured to the tip shroud ring in a circumferential direction, the tip shroud ring acts to dampen the bladed turbine by allowing only the middle of the blade to vibrate.

Abstract: The segments of the vanes of a stator and the blades of a rotor for a gas turbine engine are dampened by utilizing braided wire cable that is affixed to adjacent segments such that each of the wire strands forming the cable is allowed to move relative to each other to dissipate the vibratory energy inflicted on the stator or rotor. The ends of the cable are welded or heated and then tapered to facilitate fitting into a sleeve or collar which in turn is affixed to the adjacent segments by braze, weld or the like.

Abstract: A thermal turbo machine is provided for the attachment of guide vanes on its stationary housing with guide vane carriers with a guide vane platform, from which braces extend towards a band that is suspended in a recess in the stationary housing. In particular, part of the axially adjoining heat shield segments form part of the guide vane platform, and the braces are arranged in a V shape. The braces and the guide vane platform furthermore include a first material, and the band of a second material, whereby the first material has a higher coefficient of expansion than the second material. The guide vane carrier according to the invention has the advantage that the radial blade clearance for the guide vanes and at the same time the radial blade clearance for the rotating blades is minimized for different operating conditions of the turbo machine.

Abstract: A rotor blade pair for rotation around an axial centerline is provided which includes a platform, a first and a second airfoil, and a root having a first and second wall. The platform has an inner and an outer radial surface. The first and second airfoils extend out from the outer radial surface of the platform. The root walls extend out from said inner radial surface of the platform, and are integrally connected to one another, forming a hollow between the walls and the inner radial surface. The first wall is substantially aligned with the first airfoil and the second wall is substantially aligned with the second airfoil.

Abstract: A turbine engine rotor assembly disk is provided which includes a forward web, an aft web, a plurality of first stub shafts, and a plurality of second stub shafts. The first and second stub shafts have axial ends and web ends. The stub shafts are attached to the respective forward or aft web, at the web end. The first and second stub shafts are equal in number, similarly spaced around the axial centerline, and attached to one another by fasteners.