Abstract: A nozzle for a gas turbine engine is provided which includes an outer casing, a convergent section, a divergent section, an external fairing, and apparatus for sealing between the external fairing and the divergent section. The convergent section communicates with the augmentor on one end and with the divergent section on the opposite end. The end of the divergent section opposite that attached to the convergent section is pivotly attached to the external fairing. The divergent section includes a plurality of divergent flaps and divergent flap seals circumferentially spaced. The apparatus for sealing between the external fairing and the divergent section attaches to the divergent flaps and divergent flap seals and mates with the external fairing.

Abstract: A blade outer air seal for a turbine engine rotor assembly is provided. The rotor assembly includes a plurality of rotor blades extending out from a rotor disk, each blade having an outer radial tip with an axial length. The blade outer air seal includes a hoop-shaped body and apparatus for suspending the body in close proximity to the outer radial tips of the rotor blades. The body includes an inner radial surface and an outer radial surface. According to a first embodiment, the body inner radial surface includes a first slot, a second slot, and a central portion positioned between the first and second slots. The central portion has an axial length equal to or less than the axial length of the rotor blade outer radial tips. According to a second embodiment, the body inner radial surface includes a raised central portion having an axial length equal to or less than the axial length of the rotor blade outer radial tips.

Abstract: A stator vane assembly for a gas turbine engine is provided which includes a plurality of stator vane segments and a seal ring. Each stator vane segment has an outer platform, an inner platform, and an airfoil extending between the platforms. The stator vane segments collectively form an annular structure. The seal ring includes an abradable bearing pad which extends out from an axial surface of the body of the seal ring. The seal ring is attached to a non-rotating member within the engine, positioned in close proximity to the stator vane segments. Contact, and consequent friction, between the individual stator vane segments and the abradable bearing pad causes the abradable bearing pad to abrade, thereby creating a sealing surface reflective of the opposing stator vane segments in contact with the abradable bearing pad.

Abstract: A liner apparatus is provided which includes an inner wall, a plurality of fasteners extending out from the inner wall, an impingement sheet attached to the inner wall by the fasteners, apparatus for spacing the inner wall and the impingement sheet a distance apart, and apparatus for sealing between the inner wall and the impingement sheet along an edge of the liner.

Abstract: A bypass air valve is provided comprising a liner, a strap, and apparatus for selectively actuating the valve. The liner includes an inner surface, an outer surface, a plurality of first regions, and a plurality of second regions. Each first region includes a plurality of first apertures. The strap includes a plurality of openings and a plurality of third regions. The third regions include a plurality of second apertures. The valve may be selectively actuated into an open position where the first regions are in communication with the openings, and the third regions are in communication with the second regions. The valve may be selectively actuated into a closed position where the first regions are in communication with the third regions, and the second regions are in communication with the openings.

Abstract: A valve for controlling the flow of fuel within a gas turbine engine is provided. The fuel flow control valve includes a valve block disposed within a sleeve, and apparatus for displacing one of the sleeve or valve block relative to the other. The sleeve includes an inlet port and an exit port. The valve block includes an inlet gate and an exit gate. One of the sleeve or the valve block may be displaced relative to the other from a closed position where the gates close the ports and thereby prevent fluid flow through the valve via the ports, to a plurality of open positions where the gates less than completely close the ports, and thereby allow fluid flow through the valve via the ports.

Abstract: A combustor for a gas turbine engine is provided which includes a plurality of liner segments and a support shell. Each liner segment includes a panel, a forward wall, a trailing wall, a pair of side walls, and a plurality of mounting studs. The panel includes a face surface and a back surface. The forward wall is positioned along a forward edge of the panel and the trailing wall is positioned along a trailing edge of the panel. The side walls connect the forward and trailing walls. The forward, trailing, and side walls extend out from said back surface a particular distance. The plurality of mounting studs extend out from the back surface, and each includes liner segment attachment apparatus.

Abstract: A method for replacing a rotor blade on an integrally bladed rotor having a disk is provided, comprising the steps of: (a) removing a damaged rotor blade, leaving a stub portion of the rotor blade extending out from the disk, the stub portion of the rotor blade having a suction side and a pressure side; (b) providing a die, having a pressure side and a suction side, wherein each side includes a platform trough; (c) fastening the die to the rotor blade stub, with the pressure side of the die positioned on the pressure side of the stub, and the suction side of the die positioned on the suction side of the stub; (d) extruding a portion of the rotor blade stub into the platform troughs, thereby creating a platform; and (e) attaching a rotor blade to the platform.

Abstract: A thermal spray apparatus for depositing a coating on to a substrate is provided which includes a plasma generator for selectively changing gas from a gaseous state to a plasma, and apparatus for filtering plasma. Powder particles entrained in the plasma change from a solid state to a molten state. The apparatus for filtering the plasma permits only a high intensity region of the plasma to pass through to the substrate.

Abstract: A method for cooling a stator vane is provided, comprising the steps of: (a) providing a hollow stator vane having a high pressure and a standard pressure chamber disposed within the hollow stator vane, adjacent the leading edge of the airfoil, and a supply chamber, disposed within the hollow stator vane, aft of the high and standard pressure chambers, and forward of the trailing edge; the stator vane further includes first and second inlet apertures, and first and second exit apertures; the first inlet apertures extend between the high pressure chamber and the supply chamber, and the second inlet apertures extend between the standard pressure chamber and the supply chamber; the first exit apertures extend between the high pressure chamber and the exterior of the stator vane, and the second exit apertures extend between the standard pressure chamber and the exterior of the stator vane; (b) determining the magnitudes of the gas flow pressure gradient facing the stator vane, and the position of the gradient rel

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 bowed airfoil is provided which includes a plurality of passages disposed between a pressure side wall and a suction side wall. The pressure and suction side walls extend widthwise between a leading edge and a trailing edge, and spanwise between inner and outer platforms. Passages extend spanwise between the inner and outer platforms. Ribs, each having a rib end, separate adjacent passages. Passage turns, each having an end wall, connect the passages. The end wall of each passage turn acutely converges with one of the side walls, and a first fillet extends between the acutely converging side wall and end wall. According to one embodiment, each rib end acutely converges with the other of the side walls, and a second fillet extends between the acutely converging side wall and rib end.

Abstract: A feather seal is provided having a first element and a second element. The first element includes a pair of protrusions and the second element includes a slot for receiving the first element. The first element is slidably received within the slot of the second element, and the protrusions limit the travel of the first and second element relative to one another.

Abstract: A serviceable liner is provided comprising an outer wall, an inner wall, a plurality of standoffs disposed between the walls, and a plurality of attachment assemblies for attaching the walls to one another. The outer wall includes a plurality of first apertures. The inner wall includes a plurality of sections, each section having at least one second aperture. Each attachment assembly includes a fastener and an insert. An insert is received within each first aperture and a fastener is received within each insert.

Abstract: A liner for a gas turbine engine is provided which includes an outer wall, an inner wall, a plurality of standoffs, a plurality of attachment assemblies, and a plurality of tapered ribs. The inner wall sections each have a first edge and a second edge. The standoffs are attached to the inner wall sections, and separate the inner and outer walls. The attachment assemblies fix at least one standoff, per inner wall section, to the outer wall section. Each tapered rib has a pair of surfaces tapering from a greater end to a lesser end. The tapered ribs are attached to the outer wall, with the lesser end is in contact with the outer wall and the tapered surfaces disposed between, and in contact with, adjacent inner wall sections.

Abstract: A bypass air valve is provided which includes a liner, a strap, apparatus for biasing the strap into contact with the liner, a selective actuator, and apparatus for passage of bypass air. To open and close the valve, the selective actuator unwraps a segment of the strap from the liner before the strap is translated a distance around the circumference of the liner. The biasing apparatus biases the strap back into contact with the liner.

Abstract: A method for distributing fuel within a gas turbine engine is provided. An augmentor is provided which includes a plurality of vanes. Each vane includes a pair of side walls, an aft wall, and a plurality of fuel apertures and pressurized gas apertures extending through the side walls. At least one of the pressurized gas apertures is positioned adjacent and forward of all fuel apertures at a particular position. At least one fuel distributor is provided in each vane. Fuel admitted into the fuel distributors flows into the core gas path in a direction substantially perpendicular to the core gas path. Gas admitted into the vanes at a pressure higher than that of the core gas flow, flows a distance into the core gas path in a direction substantially perpendicular to the core gas path. Fuel is selectively admitted into the fuel distributors when the augmentor is enabled. Pressurized gas entering the core gas path forward of the fuel creates a low velocity wake that enables the fuel to distribute circumferentially.

Abstract: A divergent flap seal for a gas turbine engine exhaust nozzle having a longitudinal axis is provided, having a body, a spine member, and a flap position guide. The flap position guide separates adjacent divergent flaps regardless of the angle the flaps are skewed relative to the longitudinal axis of the nozzle, thereby more evenly distributing the flaps about the circumference of the nozzle.

Abstract: According to the present invention, a method and apparatus for electrochemically machining a workpiece is provided.