Abstract: According to the present invention, a brush seal is provided having a side plate, a back plate, and a bristle pack disposed between the side plate and the back plate. The side plate is in contact with an upstream surface of the bristle pack. The back plate is in contact with a downstream surface of the bristle pack. The back plate includes a plurality of apertures positioned to provide a gas path through the back plate for gas exiting the bristle pack. In some embodiments, the back plate further includes an exit channel disposed in the back plate surface contiguous with the bristle pack, aligned with the apertures. In some embodiments, the radial length of the side plate in contact with the bristle pack is less than the radial length of the back plate in contact with the bristle pack.

Abstract: A method for inhibiting radial transfer of core gas flow away from a center radial region and toward the inner and outer radial boundaries of a core gas flow path within a gas turbine engine is provided that includes the steps of: (1) providing a flow directing structure that includes an airfoil that abuts a wall surface, said airfoil having a leading edge, a pressure side, and a suction side; and (2) increasing the velocity of the core gas flow in the area where the leading edge of the airfoil abuts the wall. Increasing the velocity of the core gas flow in the area where the leading edge of the airfoil abuts the wall impedes the formation of a pressure gradient along the surface of the airfoil that forces core gas from the center region of the core gas toward the wall. The apparatus includes apparatus for diverting core gas flow away from the area where the airfoil abuts the wall.

Abstract: A method for repairing an airfoil is provided that includes the steps of: (a) determining repair regions of the airfoil that are likely to be damaged during a period of operation; (b) creating a stress profile for the airfoil that considers dynamic, steady-state, and residual stresses; (c) selecting a replacement section patch line using the stress profile and the determination of those regions likely to be damaged during operation; (d) providing an airfoil replacement section with a predetermined shape having a bond surface that substantially mates with the patch line; (e) removing a portion of the airfoil up to the patch line; (f) bonding the airfoil replacement section to the airfoil along the patch line; and (g) shaping the patched airfoil.

Abstract: An apparatus and method for cooling a wall for use in a gas turbine engine is provided that includes a cooling air passage having a plurality of segments connected in series by one or more chambers, an inlet aperture, and an exit aperture. The inlet aperture connects the cooling air passage to one side of the wall. The exit aperture connects the cooling air passage to the opposite side of the wall. Cooling air on the inlet aperture side of the wall enters the cooling air passage through the inlet aperture and exits through the exit aperture.

Abstract: According to the present invention, a method and an apparatus for cooling a wall within a gas turbine engine is provided. The apparatus includes and the method provides for a cooling circuit disposed within a wall having utility within a gas turbine engine. The cooling circuit includes a forward end, an aft end. The pedestals extend between first and second portions of the wall. The characteristics and array of the pedestals within the cooling circuit are chosen to provide a heat transfer cooling profile within the cooling circuit that substantially offsets the profile of the thermal load applied to the wall portion containing the cooling circuit. At least one inlet aperture provides a cooling airflow path into the forward portion of the cooling circuit from the cavity. A plurality of exit apertures provide a cooling airflow path out of the aft portion of the cooling circuit and into the core gas path outside the wall.

Abstract: A method and apparatus for cooling a wall within a gas turbine engine is provided which comprises the steps of: (1) providing a wall having an internal surface and an external surface; (2) providing a cooling microcircuit within the wall that has a passage for cooling air that extends between the internal surface and the external surface; and (3) increasing heat transfer from the wall to a fluid flow within the passage by increasing the average heat transfer coefficient per unit flow within the microcircuit. According to one aspect, the present invention method and apparatus can be tuned to substantially match the thermal profile of the wall at hand.

Abstract: An apparatus for applying material by cathodic arc vapor deposition to a substrate is provided which includes a vessel, a disk-shaped cathode, a platter for supporting the substrate, apparatus for maintaining a vacuum in the vessel, and apparatus for selectively sustaining an arc of electrical energy between the cathode and an anode. The disk-shaped cathode has a first end surface, a second end surface, and an evaporative surface extending between the first and second end surfaces, and the cathode is mounted on a pedestal positioned inside the vessel. The platter has a slot for receiving the pedestal, thereby enabling the platter to be movable into and out of the vessel.

Abstract: A hollow airfoil is provided which includes a body, a trench, and a plurality of cooling apertures disposed within the trench. The body extends chordwise between a leading edge and a trailing edge, and spanwise between an outer radial surface and an inner radial surface, and includes an external wall surrounding a cavity. The trench is disposed in the external wall along the leading edge, extends in a spanwise direction, and is aligned with a stagnation line extending along the leading edge.

Abstract: A hollow airfoil is provided which includes a body having an external wall and an internal cavity. The external wall includes a suction side portion and a pressure side portion. The portions extend chordwise between a leading edge and a trailing edge and spanwise between an inner radial surface and an outer radial surface. A stagnation line extends along the leading edge. A plurality of cooling apertures, disposed spanwise along the leading edge. According to one aspect of the present invention, the apertures extend through the external wall along a helical path. According to another aspect of the present invention, the apertures are alternately directed towards the suction side portion and the pressure side portions of the airfoil.

Abstract: A pair of mating titanium alloy substrates for use in a gas turbine engine are provided, one of which comprises an aluminum bronze alloy wear resistant coating. The coating consists essentially of 9.0-11.0% aluminum (Al), 0.0-1.50% iron (Fe), and a remainder of copper (Cu). The wear resistant coating is disposed between the mating substrates and inhibits frictional wear between the mating substrates.

Abstract: A seal for coaxial inner and outer spools rotatable about an axis is provided which includes a flange having a catch surface. The flange is attached to the outer spool, and is disposed between the inner and outer spools such that the catch surface is in close proximity to the inner spool. The catch surface, which includes a seal end and a discharge end, is canted from the axis between the seal end and the discharge end. Liquid disposed between the inner spool and the catch surface is forced against the catch surface by centrifugal force when the spools rotate at a sufficient speed. The liquid is subsequently driven axially along the canted catch surface in the from the seal end to the discharge end, toward the bearing compartment.

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 coolable airfoil is disclosed which includes an internal cavity, an external wall, a plurality of first apertures, and a plurality of second apertures. The external wall includes a suction-side portion and a pressure-side portion. The external wall portions extend chordwise between a leading edge and a trailing edge, and spanwise between an inner radial surface and an outer radial surface. The mean camber line of the airfoil passes through the leading edge and the trailing edge along a path equidistant between the outer surfaces of the pressure-side and suction-side walls. The first apertures, which are disposed in the external wall adjacent the trailing edge, extend a distance within the suction-side wall portion and exit the external wall through the pressure-side wall portion. The second apertures extend through the pressure-side wall portion and exit the pressure-side wall portion upstream of and in close proximity to the first apertures.

Abstract: A coolable airfoil is provided which includes an internal cavity, an external wall, a plurality of first cooling apertures, and a plurality of second cooling apertures. The external wall includes a suction side portion and a pressure side portion. The wall portions extend chordwise between a leading edge and a trailing edge and spanwise between an inner radial surface and an outer radial surface. The first cooling apertures are disposed in the external wall adjacent the trailing edge, exiting the airfoil through the pressure side portion. The second cooling apertures are disposed in the external wall adjacent the trailing edge, exiting the airfoil through the suction side portion.

Abstract: A hollow airfoil is provided having a leading edge, a trailing edge, and a wall including a suction side portion and a pressure side portion. The wall, which includes an interior surface and an exterior surface, surrounds a first cavity and a second cavity, separated from one another by a rib extending between the suction side and pressure side wall portions. The first cavity is contiguous with the leading edge. The airfoil further includes a coolant flow splitter attached to the wall interior surface within the first cavity, and at least one metering orifice disposed in the rib. The metering orifice(s) are substantially aligned with the coolant flow splitter, such that cooling air passing through the metering orifice(s) encounters the flow splitter. The flow splitter splits the cooling air flow and directs it along the wall interior surface.

Abstract: A pair of mating titanium alloy substrates for use in a gas turbine engine are provided, one of which comprises an aluminum bronze alloy wear resistant coating. The coating consists essentially of 9.0-11.0% aluminum (Al), 0.0-1.50% iron (Fe), and a remainder of copper (Cu). The wear resistant coating is disposed between the mating substrates and inhibits frictional wear between the mating substrates.

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 hollow airfoil is provided which includes a body, a trench, and a plurality of cooling apertures disposed within the trench. The body extends chordwise between a leading edge and a trailing edge, and spanwise between an outer radial surface and an inner radial surface, and includes an external wall surrounding a cavity. The trench is disposed in the external wall along the leading edge, extends in a spanwise direction, and is aligned with a stagnation line extending along the leading edge.

Abstract: A gas turbine augmentor fuel manifold unit is provided which includes a plurality of fuel manifolds, each having a plurality of feed tubes, and at least one wear resistant clamp for clamping the feed tubes. The wear resistant clamp includes first and second wear sleeves, first and second clamp members, and a fastener. The wear sleeves are disposed between the clamp members and the tubes to minimize wear therebetween. The first wear sleeve, which is fixed to one of the feed tubes, includes a plurality of retaining tabs to limit the travel of the first and second clamp members.

Abstract: An apparatus for applying material by cathodic arc vapor deposition to a substrate is provided which includes a vessel, apparatus for maintaining a vacuum in the vessel, a disk-shaped cathode, apparatus for selectively sustaining an arc of electrical energy between the cathode and an anode, and apparatus for steering the arc around the cathode. The arc of electrical energy extending between the cathode and the anode liberates a portion of the cathode which is subsequently deposited on the substrate located inside the vessel.