Abstract: A method of repairing a gas turbine knife edge seal assembly in which assembly is included a used honeycomb ring seal and a knife edge. The method includes removing the used honeycomb ring seal, removing material from the knife edge to a first knife edge radial height, installing a replacement honeycomb ring seal with a stock radial thickness, and removing material from the replacement honeycomb ring seal to a finished radial thickness for sealable engagement with the knife edge. The finished radial thickness of the replacement honeycomb ring seal establishes a first radial gap between an inner annular surface of the replacement honeycomb ring seal and the knife edge before the knife edge seal assembly begins rotating in the gas turbine.

Abstract: A knife edge seal assembly includes at least one knife edge and at least one honeycomb ring seal. The at least one knife edge has material removed to a first knife edge radial height and the least one honeycomb ring seal has material removed to a finished radial thickness for sealable engagement with the at least one knife edge. The finished radial thickness of the replacement honeycomb ring seal establishes a first radial gap between an inner annular surface of the replacement honeycomb ring seal and the knife edge before the knife edge seal assembly begins rotating in the gas turbine.

Abstract: A rotor blade assembly includes a slot for mounting a rotor blade that extends partially through a rotor disk and a continuous uninterrupted hoop seal that extends about the circumference of the rotor disk. The rotor disk includes an integrally formed seal that includes at least one knife edge disposed concentrically about the rotor disk. The slot receives a root portion of a rotor blade but does not extend through the seal. As the seal remains an uninterrupted full hoop about the circumference of the rotor disk, additional rigidity and strength are realized. The increased rigidity and strength provided by the full hoop structure provides for the reduction in material and physical dimensions without compromising desired performance of the seal.

Abstract: A material having a plurality of impurity collection spaces has an outer face facing into a cooling air flow stream for a gas turbine engine component. Impurities such as sand or dirt will collect in the plurality of spaces. In a disclosed embodiment, a honeycombed material is utilized. The material may have a surface that will sit with at least a component parallel to an axial centerline of a gas turbine engine that is to receive the collection material. The material surface may also have a component which is generally perpendicular to the axial centerline. The material may be placed in a gas turbine engine upstream of the turbine section, and downstream of the combustion section. Moreover, the collection material may be placed such that there is cleaner air flow radially inwardly of the collection material, and heavier dirt-laden air passing along the collection material such that impurities can be collected.

Abstract: A method of repairing a gas turbine knife edge seal assembly in which assembly is included a used honeycomb ring seal and a knife edge. The method includes removing the used honeycomb ring seal, removing material from the knife edge to a first knife edge radial height, installing a replacement honeycomb ring seal with a stock radial thickness, and removing material from the replacement honeycomb ring seal to a finished radial thickness for sealable engagement with the knife edge. The finished radial thickness of the replacement honeycomb ring seal establishes a first radial gap between an inner annular surface of the replacement honeycomb ring seal and the knife edge before the knife edge seal assembly begins rotating in the gas turbine.

Abstract: A turbine engine component, such as a turbine blade, has an airfoil portion, a plurality of cooling passages within the airfoil portion with each of the cooling passages having an inlet for a cooling fluid. Each inlet has a flared bellmouth inlet portion. The turbine engine component may further have a dirt funnel at the tip of the airfoil portion, a platform with at least one beveled edge, and an undercut trailing edge slot.

Abstract: An optical device has a waveguide structure comprising a thin strip (12) having finite width and thickness of material having a relatively high free charge carrier density supported by a membrane (14) having a predetermined thickness of material that has a relatively low free charge carrier density. The dimensions of the width and thickness of the strip and the thickness of the supporting membrane are such that, when the waveguide structure is surrounded at least partially by an environment (E) having a low free charge carrier density, optical radiation having a wavelength in a predetermined range couples to the waveguide structure and propagates along the length thereof as a plasmon-polariton wave that permeates at least part of the environment (E).

Abstract: The present invention provides a turbine blade having a revised under-platform structure including a unique coating combination that reduces mechanical stress factors within the turbine blade. The turbine blade includes a platform with an airfoil extending upwardly from the airfoil and a root portion extending downwardly from the platform. Two suction side tabs extend a first distance outward from a suction side of the root potion. Two pressure side tabs extend outward from a pressure side of the root portion. One of the two pressure side tabs extends outward a distance similar to the first distance, however, the other of the two pressure side tabs extends outward a distance much smaller than the first distance, which reduces stresses acting on the turbine blade. In addition, a plurality of coatings are systematically applied to the turbine blade to further reduce mechanical stress factors and improve cooling.

Abstract: The present invention provides an improved cooling circuit for a trailing edge of a turbine blade. The cooling circuit includes an inlet passage that receives a airflow and distributes the airflow through a feed passage. The feed passage primarily includes trip strips, at least one barrier including cross-over holes, teardrop shaped protrusions, and pockets disposed along a trailing edge. The geometry and positioning of both the cross-over holes and teardrop shaped protrusions downstream of the cross-over holes have been optimized to maximize cooling efficiency and reduce airflow. An improved transition between the inlet passage and the feed passage is also provided, which is arcuate and allows the airflow to maintain attachment and flow unimpeded from the inlet passage to the feed passage. The geometry of the pockets disposed along the trailing edge is optimized to improve cooling.

Abstract: A gas sensor for hydrogen or other gases, especially flammable or explosive gases, has a plasmon-polariton waveguide comprising a metal strip on a membrane supported by a substrate in an environment in which the gas is to be introduced, and coupling means for coupling optical radiation into and out of the plasmon-polariton waveguide such that the optical radiation propagates therealong as a plasmon-polariton wave. The metal strip comprises by a chemical transducer (e.g. Pd or PdNi), the arrangement being such that exposure of the metal strip or coating to the gas to be monitored causes a change in the propagation characteristics of the plasmon-polariton wave and hence the optical radiation coupled out of the plasmon-polariton waveguide.

Abstract: A rotor blade assembly includes a slot for mounting a rotor blade that extends partially through a rotor disk and a continuous uninterrupted hoop seal that extends about the circumference of the rotor disk. The rotor disk includes an integrally formed seal that includes at least one knife edge disposed concentrically about the rotor disk. The slot receives a root portion of a rotor blade but does not extend through the seal. As the seal remains an uninterrupted full hoop about the circumference of the rotor disk, additional rigidity and strength are realized. The increased rigidity and strength provided by the full hoop structure provides for the reduction in material and physical dimensions without compromising desired performance of the seal.

Abstract: An improved electro-magnetic field generating device, or field generator, which employs a high speed rotor, powered by compressed air, to generate a localized electro-magnetic field of high intensity. The field generator includes a hub that spins about a hub axis, and a charging ring that mounts to the hub that is centered on the hub axis. The charging ring receives an airstream from the hub. The airstream routes through the charging ring and back out into the hub. A housing formed from a metal material, encases the charging ring. A rotor mounts to the hub. The rotor is centered on the hub axis and receives the airstream from the hub. The airstream routes through the rotor to a pair of nozzles on the rotor am. The nozzles are oriented to exhaust the airstream at a tangent to the nozzle rotation, creating a rotational thrust to spin the charging ring.

Abstract: A material having a plurality of impurity collection spaces has an outer face facing into a cooling air flow stream for a gas turbine engine component. Impurities such as sand or dirt will collect in the plurality of spaces. In a disclosed embodiment, a honeycombed material is utilized.

Abstract: A turbine engine component, such as a turbine blade, has an airfoil portion, a plurality of cooling passages within the airfoil portion with each of the cooling passages having an inlet for a cooling fluid. Each inlet has a flared bellmouth inlet portion. The turbine engine component may further have a dirt funnel at the tip of the airfoil portion, a platform with at least one beveled edge, and an undercut trailing edge slot.

Abstract: The present invention provides a turbine blade having a revised under-platform structure including a unique coating combination that reduces mechanical stress factors within the turbine blade. The turbine blade includes a platform with an airfoil extending upwardly from the airfoil and a root portion extending downwardly from the platform. Two suction side tabs extend a first distance outward from a suction side of the root potion. Two pressure side tabs extend outward from a pressure side of the root portion. One of the two pressure side tabs extends outward a distance similar to the first distance, however, the other of the two pressure side tabs extends outward a distance much smaller than the first distance, which reduces stresses acting on the turbine blade. In addition, a plurality of coatings are systematically applied to the turbine blade to further reduce mechanical stress factors and improve cooling.

Abstract: The present invention provides an improved cooling circuit for a trailing edge of a turbine blade. The cooling circuit includes an inlet passage that receives a airflow and distributes the airflow through a feed passage. The feed passage primarily includes trip strips, at least one barrier including cross-over holes, teardrop shaped protrusions, and pockets disposed along a trailing edge. The geometry and positioning of both the cross-over holes and teardrop shaped protrusions downstream of the cross-over holes have been optimized to maximize cooling efficiency and reduce airflow. An improved transition between the inlet passage and the feed passage is also provided, which is arcuate and allows the airflow to maintain attachment and flow unimpeded from the inlet passage to the feed passage. The geometry of the pockets disposed along the trailing edge is optimized to improve cooling.

Abstract: When the temperature of pyroelectric film is increased from low to high near its phase transition temperature its ability to hold electrical charge on its surfaces diminishes, and the charge can be drawn as current through an external load resistor. Once the film temperature reaches a steady temperature, no more power can be drawn. However, if the film temperature is lowered again, it will restore charge on the film surfaces and the pyroelectric conversion process can be repeated. Because pyroelectric conversion depends on the degree of temperature change and the repetition rate of the process, the faster the cycling the more power it can generate by converting heat to electric power. An improved apparatus and method is disclosed for converting heat to electrical energy with a multi-layer stack of thin pyroelectric films. The pyroelectric film surface is cycled between higher and lower temperatures by the displacement of higher and lower temperature fluid over the film surface.

Abstract: The system for converting organic waste reservoirs into anaerobic digester comprises an inflatable roof structure adapted to be installed on a variety of reservoirs to seal it from the atmosphere. The roof structure includes an inner gas-impermeable membrane which is adapted to raise and lower with the level of organic waste contained in the reservoir. A peripheral fold is defined in the gas-impermeable membrane adjacent the inner surface of the surrounding wall of the reservoir to form a downwardly depending skirt which acts as a gas barrier to prevent gas leakage along the inner surface of the reservoir. A gas removal unit is also provided for removing biogas trapped beneath the gas-impermeable membrane from the reservoir.

Abstract: The system for converting organic waste reservoirs into anaerobic digester comprises an inflatable roof structure adapted to be installed on a variety of reservoirs to seal it from the atmosphere. The roof structure includes an inner gas-impermeable membrane which is adapted to raise and lower with the level of organic waste contained in the reservoir. A peripheral fold is defined in the gas-impermeable membrane adjacent the inner surface of the surrounding wall of the reservoir to form a downwardly depending skirt which acts as a gas barrier to prevent gas leakage along the inner surface of the reservoir. A gas removal unit is also provided for removing biogas trapped beneath the gas-impermeable membrane from the reservoir.