Abstract: An ultrasonic welding system that includes a rotary sonotrode, having a body that includes a first horizontal side having a first antinode; a second horizontal side having a second antinode; a first vertical side having a first node; a second vertical side having a second node; and a middle region, an upper region, and a lower region, wherein the length of the middle region is greater than the length of the upper region and greater than the length of the lower region; at least one ultrasonic transducer that is transversely aligned with the rotary sonotrode; and at least one input tool disposed between the rotary sonotrode and the transducer that includes a node and is an integral part of the transducer or is a component separate from the transducer, wherein the input tool is connected to the rotary sonotrode at the middle region thereof on either the first vertical side or the second vertical side, and wherein the connection point between the input tool and the sonotrode is located a predetermined distance aw

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 replaceable leading edge insert for an: integrally bladed rotor disk in which the insert includes an enlarged base portion that can be inserted into a dovetail shaped slot formed in the rotor disk to secure the insert to the rotor disk against centrifugal loads during the operation of the blade. The blade on the rotor disk is formed without a leading edge and the leading edge insert includes an aft edge of similar shape to the fore edge n the blade such that the insert can be bonded or fastened to the blade along the entire length of the insert from the blade root to the tip. The rotor disk and the insert include a an annular groove formed on the front side in which a retaining ring is inserted to lock the inserts to the rotor disk. The inserts can be made of a different material from the rotor disk and can be formed with a sweep to form a more :aerodynamic and efficient blade.

Abstract: The airfoil of fan/compressor and turbine rotors is constructed to include a leading edge that is detachable. The leading edge includes an airfoil section and an attachment that is adapted to fit into a complementary groove formed in the rotor disk. The detachable leading edge is efficacious in integrated bladed rotor (IBR or BLISK) designs because damage to the leading edge can be fixed by either removing the leading edge and repairing it or replacing it without having to disturb the remaining portion of the IBR.

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: Aspects according to the invention relate to a locking spacer assembly for a slotted turbine engine component. In one embodiment, aspects of the invention can be used in connection with the assembly and disassembly of a disc hosting a row of airfoils as can be found in the compressor or turbine section of a turbine engine. The spacer according to the invention is a multi-part assembly. In one embodiment, the spacer includes at least three sub-components: first and second end supports and a filler. The inner and outer faces of each of these components can have various features to facilitate engagement of the assembly and distribution of centrifugal loads in operation. These parts can be held together by a retainer, which can be received in a cutout provided in the end supports and the filler.

Abstract: Aspects according to the invention relate to a locking spacer assembly for a slotted turbine engine component. In one embodiment, aspects of the invention can be used in connection with the assembly and disassembly of a disc hosting a row of airfoils as can be found in the compressor or turbine section of a turbine engine. The spacer according to the invention is a multi-part assembly. In one embodiment, the spacer includes at least three sub-components: first and second end supports and a filler. The inner and outer faces of each of these components can have various features to facilitate engagement of the assembly and distribution of centrifugal loads in operation. These parts can be held together by a retainer, which can be received in a cutout provided in the end supports and the filler.

Abstract: The airfoil of fan/compressor and turbine rotors is constructed to include a leading edge that is detachable. The leading edge includes an airfoil section and an attachment that is adapted to fit into a complementary groove formed in the rotor disk. The detachable leading edge is efficacious in integrated bladed rotor (IBR or BLISK) designs because damage to the leading edge can be fixed by either removing the leading edge and repairing it or replacing it without having to disturb the remaining portion of the IBR.

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: An apparatus for controlling vibrations in a rotor stage rotating through core gas flow is provided. The apparatus includes a source of high-pressure gas and a plurality of ports for dispensing high-pressure gas. The rotor stage rotates through core gas flow having a plurality of circumferentially distributed first and second regions. Core gas flow within each first and second region travels at a first and a second velocity, respectively. The first velocity is substantially higher than the second velocity. The ports dispensing the high-pressure gas are selectively positioned upstream of the rotor blades, and aligned with the second regions such that high-pressure gas exiting the ports enters the second regions. The velocity of core gas flow in the second regions consequently increases, and substantially decreases the difference in core gas flow velocity between the first and second regions.

Abstract: An apparatus for controlling vibrations in a rotor stage rotating through core gas flow is provided. The apparatus includes a source of high-pressure gas and a plurality of ports for dispensing high-pressure gas. The rotor stage rotates through core gas flow having a plurality of circumferentially distributed first and second regions. Core gas flow within each first and second region travels at a first and a second velocity, respectively. The first velocity is substantially higher than the second velocity. The ports dispensing the high-pressure gas are selectively positioned upstream of the rotor blades, and aligned with the second regions such that high-pressure gas exiting the ports enters the second regions. The velocity of core gas flow in the second regions consequently increases, and substantially decreases the difference in core gas flow velocity between the first and second regions.

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.

Abstract: A method and apparatus are disclosed for fabrication of hollow articles by hot consolidation of metal alloy powder between a hollow core and a fluid pressure resistant outer shell. The hollow core is formed, a disposable layer is applied to define the object contour, a fluid pressure resistant metallic layer is formed over the disposable layer, which is then melted, removed and replaced by the metal alloy powder, and this assembly is hot isostatically pressed. The powder and core materials are preferably selected to be metallurgically compatible, so the core becomes an integral part of the finished article. The hollow article is inflated in a form die to establish the finished article contour.

Abstract: A golf stance viewer having a lens for looking at the positioning of one's feet and golf ball, said lens having stance indicating lines associated therewith for indicating foot and golf ball placement; a leveling device being provided to place said viewer in a desired plane and a reflecting device, such as a mirror, to aim the viewer in a specific direction. A support being provided to place the viewing device at the same desired position in relation to the golfer time after time. To determine a proper stance, a golf club swing marking device indicates the arcuate path of a golf club which has been swung, and a golf ball impact recording device indicates the point of impact where a club face hits a golf ball.

Abstract: A laser nozzle, optical cavity walls, and combustion manifold system is formed having a plurality of laser nozzle members formed having two elongated projections on each side thereof, a forward projection and a rearward projection, and when said members are placed together, the rear projections meet to form a solid wall while said forward projections are spaced to form an elongated nozzle. Side plates enclose the ends of the nozzle members and end plates cover the ends of the side plates and exposed surface of the end nozzle members. The cavity formed between the two projections is fed a lasing gas through openings in the side plates from a manifold system. The laser nozzle members can be internally cooled along with associated combustion distribution manifolds.