Abstract: A thermophotovoltaic (TPV) system, comprises a substrate, an emitter material adhered to the substrate, and a thermophotovoltaic (TPV) cell. The emitter material is a typically a metal oxide doped nickel oxide sol-gel material, in which the metal is magnesium or zirconium, and in which the sol-gel material comprises 97-99 mol % metal oxide, and about 1-3 mol % nickel oxide dopant. Providing an emitter material as a sol-gel allows the material to be coated on to surfaces providing better adherence to the surface, and also provides excellent heat stability. A sol-gel material is also described.

Abstract: A work boot has a midsole connected between an upper and a sob, the midsole having a plurality of layers of puncture resistant material lining an inner surface and side walls thereof. The side walls extend upwardly from a periphery of the inner surface of the midsole. Additional layers of puncture resistant material cover a bottom of the upper. An arch of the midsole also has a plurality of layers of puncture resistant fabric thereon. The midsole has a series of spaced apart cross members and a shank extending substantially perpendicular to the cross members to provide stability and to prevent reverse flexing of the work boot.

Abstract: A method for fabricating a rotor blade is provided. The method includes providing a rotor blade that includes a tip shroud having a portion of increased cross-sectional thickness relative to adjacent portions of the tip shroud. The increased cross-sectional thickness section extends across substantially an entire circumferential width of the tip shroud. The increased cross-sectional thickness section defines a pair of opposite interlock surfaces that each form a portion of a respective side of the pair of opposite tip shroud sides used for interlocking the tip shrouds of two adjacent rotor blades on the rotor. The method also includes removing a portion of the increased cross-sectional thickness section between the pair of opposite tip shroud sides to facilitate enhancing the efficiency of the rotor blade.

Abstract: A method for fabricating a rotor blade is provided. The method includes providing a rotor blade that includes a tip shroud having a portion of increased cross-sectional thickness relative to adjacent portions of the tip shroud. The increased cross-sectional thickness section extends across substantially an entire circumferential width of the tip shroud. The increased cross-sectional thickness section defines a pair of opposite interlock surfaces that each form a portion of a respective side of the pair of opposite tip shroud sides used for interlocking the tip shrouds of two adjacent rotor blades on the rotor. The method also includes removing a portion of the increased cross-sectional thickness section between the pair of opposite tip shroud sides to facilitate enhancing the efficiency of the rotor blade.

Abstract: A method of forming an air-tight scal between two pieces of glass is described. It comprises the steps of: (a) introducing a layer of indium or indium alloy between opposing surfaces of the glass pieces; and (b) heating the indium or indium alloy layers and the glass pieces, preferably under vacuum, to a temperature, generally around or below 220° C., to melt the layers to form the seal between the pieces. The method is suitable to form a relatively small air-type seal between two glass panes or sheets, and is particularly suitable for the formation of evacuated double glazing units. Optionally, an additional metal layer is located between the indium or indium alloy layers.

Abstract: A gas turbine engine rotor blade includes an airfoil, platform, shank, and dovetail integrally joined together. A dust escape hole extends through the platform adjacent a fillet bridging the platform and shank to bleed dust therefrom during operation.

Abstract: A method for repairing a stationary turbine nozzle segment having at least one vane disposed between outer and inner structural bands includes providing an engine-run turbine nozzle segment having at least one vane disposed between outer and inner bands, wherein the outer band and the vanes are previously replaced components of the segment and the inner band is an original component of the segment; separating the inner band from the nozzle segment; repairing damage in the outer band and/or the vane; and joining the outer band and the vane to a newly manufactured replacement inner band segment. The replacement inner band segment includes: a structural inner band; and an integral structural collar adapted to receive an inner end of the at least one vane.

Abstract: A method for repairing a stationary turbine nozzle segment having at least one vane disposed between outer and inner structural bands includes providing an engine-run turbine nozzle segment having at least one vane disposed between outer and inner bands, wherein the outer band and the vanes are previously replaced components of the segment and the inner band is an original component of the segment; separating the inner band from the nozzle segment; repairing damage in the outer band and/or the vane; and joining the outer band and the vane to a newly manufactured replacement inner band segment. The replacement inner band segment includes: a structural inner band; and an integral structural collar adapted to receive an inner end of the at least one vane.

Abstract: A turbine blade includes an airfoil, platform, shank, and dovetail. The platform includes a first side disposed along the pressure side of the airfoil, and an opposite second side disposed along the airfoil suction side. The platform second side includes an integral damper keeper disposed below the midchord of the airfoil, and is locally thinner at the forward and aft ends of the platform second side for reducing blade weight.

Abstract: A turbine blade includes an airfoil, platform, shank, and dovetail. The shank includes opposite forward and aft faces corresponding with leading and trailing edges of the airfoil, and opposite first and second sides corresponding with pressure and suction sides of the airfoil. The shank further includes lugs extending outwardly from the two sides, with a first lug having an inverted skirt extending outwardly toward the platform to join the shank aft face. The skirt cooperates with a seal body when mounted in the engine for reducing inter-blade leakage.

Abstract: A turbine blade includes an airfoil having an internal cooling circuit with a first flow passage disposed directly behind the leading edge followed by a second flow passage separated therefrom by a corresponding bridge. The bridge includes a row of impingement apertures for cooling the leading edge. The suction sidewall of the airfoil includes a row of diffusion film cooling first holes extending in flow communication with the first passage. The first holes have a compound inclination angle, with a quadrilateral cross section forming a generally teardrop shaped outlet in the convex contour of the suction sidewall.

Abstract: A rotor blade for a rotor of a gas turbine engine having an axis of rotation including a root portion, a platform portion connected to the root portion and having a damper pocket formed therein, an airfoil portion connected to the platform portion, a generally bar-shaped damping member loosely arranged in the damper pocket having at least one scrubbing surface, and at least one retainer pin for retaining the bar-shaped damping member in the damper pocket. The bar-shaped damping member is slidably displaceable and rotatable within the damper pocket during rotation of the rotor. The damper pocket in the platform portion has a rear surface with an upper portion and a lower portion at an angle to the upper portion, a pair of spaced side surfaces, and a pair of spaced lower surfaces extending from the rear surface lower portion which are substantially coplanar.