Abstract: Presented is a system and method for providing electrical isolation in vehicle power systems. The method comprises placing linear optimized isolation transformers in structures of a vehicle at positions that minimize the propagation of energy spikes into internal electronic systems, for example in the wing root of an aircraft where electrical cables from a generator associated with an engine enter the fuselage. The system includes a linear optimized isolation transformer with a core that has primary side winding isolated from a secondary side winding by an isolation dielectric. The isolation dielectric maintains a high value isolation independent of pressure differences due to operation at different altitudes.

Abstract: A turbine rotor blade with a four-pass aft flowing serpentine flow cooling circuit with a first leg located along the leading edge and the fourth leg located along the trailing edge region, and with two exit slots connected to the fourth leg with one exit slot opening on the trailing edge just above the platform and the second exit slot opening just below the platform.

Abstract: A film cooling hole for a turbine airfoil, the film hole having a metering inlet section followed by a diffusion section that has two sidewalls with a sinusoidal shape and with the upstream and downstream walls forming zero diffusion so that a thin slot is formed on the film hole opening. The film hole can be straight or curved in a direction of the film injection.

Abstract: A turbine rotor blade with a three-pass serpentine flow cooling circuit for a mid-chord region and a triple metering and impingement cooling circuit for a trailing edge region of the blade. The triple rows of metering holes each includes regular sized metering holes in an upper span and a lower span section of the row, and a middle span metering holes having a larger flow area in order to pass more cooling air to the middle span section of the trailing edge region of the blade. The three rows of metering holes are separated by an upper continuous cooling channel and a lower continuous cooling channel.

Abstract: A turbine rotor blade with a squealer tip having an enclosed pocket channel formed below the squealer floor and having an inlet end opening adjacent to a leading edge region of the blade tip to receive cooler hot gas stream and direct the cooler gas toward the trailing edge region, and with film cooling holes along the aft section of the blade tip that discharge the cooler hot gas flow passing through the pocket channel onto the tip rail surface to produce both cooling and sealing. A similar pocket channel with film cooling holes can be used on the pressure and the suction sides of the blade tip.

Abstract: A turbine stator vane with an airfoil extending between an inner endwall and an outer endwall, and with a fillet formed between the airfoil and each of the endwalls, and a row of metering impingement and diffusion slots extending around the leading edge region and along the pressure side and suction side of the airfoil just below the fillet that discharges a layer of film cooling air onto the surface of the endwall. A showerhead arrangement of film cooling holes in the leading edge region of the airfoil also discharges a layer of film cooling air toward the leading edge fillet in order to form a double layer of film cooling air from the leading edge region of the endwall.

Abstract: A turbine airfoil, such as a rotor blade or a stator vane, in which a trailing edge region is cooled by a series of modules that extend along the airfoil in the trailing edge region and form a plurality of serpentine flow channels to cool the trailing edge. Each module is separated by partition ribs so that each module can be varied in flow to control metal temperature. The modules are supplied with cooling air from a radial extending cooling supply channel located adjacent to the trailing edge region.

Abstract: A stator vane with endwalls having film cooling diffusion slots that open onto the hot gas surface. Each diffusion slot is formed as a row of one or more separated diffusion slots each having a serpentine flow channel and one or more metering inlet holes to supply spent cooling air from an impingement chamber to the diffusion slots. The metering inlet holes meter the flow of cooling air into the serpentine channels, the serpentine channels provide convection cooling for the endwalls, and the diffusion slots diffuse the cooling air into a layer of film cooling air onto the hot gas surface of the endwalls.

Abstract: An air cooled turbine airfoil with a leading edge region having rows of diffusion slots opening onto the airfoil surface. Each diffusion slot is connected to a plurality of metering and diffusion holes that meter the cooling air flow and provide for a first diffusion of the cooling air. The metering holes and diffusion holes are angled in order to improve the cooling effectiveness of the passages. The metering and diffusion holes and diffusion slots are formed from a metal printing process that can produce features that cannot be formed from an investment casting process that uses a ceramic core.

Abstract: A turbine stator vane with cooling air cavities each having an impingement cooling insert secured therein, and an impingement cooling insert secured within each cavity. A leading edge impingement insert and a mid-chord impingement insert have a section on the pressure side wall with impingement holes forming a parallel flow of impingement cooling air and a section on the suction side wall with a sinusoidal shaped piece that forms a series of impingement cooling holes that produces impingement cooling on cooler surfaces of the airfoil but with less cooling air flow.

Abstract: A turbine rotor blade with a thin thermal skin bonded over a spar to enclose serpentine flow cooling channels that extend from a platform to a blade tip along the airfoil walls. The radial channels discharge into a collection cavity and then flow through exit holes in the trailing edge. The radial cooling channels are formed as semi-circular shaped channels to maximize surface area on the hot side wall and on the cold side wall of the spar.

Abstract: In one embodiment, a computerized method facilitates invoicing for transactions in a network-based transaction system. The method includes identifying a plurality of transactions to which a first entity is a party, identifying first and second transactions from the plurality of transactions that satisfy combinable criteria relating to combining transactions into a single invoice, and providing to the first entity an indication of the combinability of transactions of the first and second transactions into the single invoice. The method can also be implemented on a machine readable medium.

Abstract: A turbine exhaust cylinder for an industrial gas turbine engine with an external blower that delivers cooling air to a heat shield jacket surrounding an outer diameter cylinder to provide impingement cooling for the cylinder. Spent impingement cooling air is collected as passed through a space formed between a fairing and a strut to provide cooling to these parts. The cooling air then provides cooling for the inner diameter cylinder before being discharged into the turbine exhaust gas or out from the turbine exhaust cylinder.

Abstract: An industrial turbine stator vane with a aft flowing serpentine flow cooling circuit with an inner endwall turn channel having a rib extending into the first leg of the serpentine circuit, where the rib separates the turn channel from a purge air channel located along the lower end of the leading edge wall that opens into a front rim cavity to discharge purge air. The separate purge air channel minimizes pressure loss in the serpentine flow and maintains high flow velocity to cool the lower end of the leading edge wall.

Abstract: A turbine rotor blade with impingement cooling cavities for the airfoil and serpentine flow cooling channels for the platform of the blade. Two impingement cavities provide cooling for the forward section of the airfoil while another two impingement cavities provide cooling for the aft section of the airfoil. Both impingement cavity cooling circuits are connected in series to platform cooling channels that use the same cooling air to cool the platform. The spent cooling air from the platform cooling channels is discharged into a dead rim cavity as purge air for the blade. The blade with the impingement cavities and the platform serpentine flow cooling channels are all formed as a single piece from a metal printing process.

Abstract: A turbine vane for use in a gas turbine engine, the vane including an airfoil portion and an endwall in which fillets extend around the airfoil at the junction to the endwall. A row of film cooling holes that connects to a cooling air supply cavity on the outer side of the endwall and open into breakout holes that are located in the fillets discharge film cooling air into the fillet. The breakout holes extend around the leading edge in the fillet and extend along the pressure side fillet and the suction side fillet just past the leading edge region to discharge film cooling air into the fillets. The film cooling holes are straight holes and are aligned with the curvature of the fillet at the midpoint height of the fillet.

Abstract: A turbine blade having an internal cooling system with incremental serpentine cooling channels in near walls forming an outer surface of the turbine blade is disclosed. The turbine blade may be formed from an internal structural spar that is covered with a thermal skin. The incremental serpentine cooling channels may be cut into the outer surface of the spar to which the thermal skin may be attached. The incremental serpentine cooling channels may be formed from two or more serpentine cooling channels aligned along an axis that extends generally spanwise throughout the turbine blade. A row of incremental serpentine cooling channels may extend from a root to a tip of the blade, but a single incremental cooling channel does not.

Abstract: A turbine rotor blade with a tip section having a pressure side and suction side tip rail that forms a squealer pocket. A number of chordwise extending ribs formed within the squealer pocket form vortex cooling channels that extend from the leading edge region and open along the pressure side tip peripheral wall. A row of tip cooling holes opens into each of the vortex cooling channels to discharge cooling air and form a vortex flow within the channels that provides both sealing and cooling for the blade tip.

Abstract: A stator vane for an industrial turbine, the vane includes a serpentine flow cooling circuit for cooling of the airfoil, and two separate purge air channels to supply air to the rim cavities. The purge channels are formed as separate channels from the serpentine flow channels so that the purge air is not heated by the hot metal and has smooth surfaces so that pressure losses is minimal.

Abstract: A Thermal Interface Material (“TIM”) composition of matter with improved heat conductivity comprises solderable heat-conducting particles in a bondable resin matrix and at least some of the solderable heat-conducting particles comprise a solder surface. Positioning the TIM between a first surface having a solder adhesion layer and a second surface, and then heating it results in soldering some of the solderable heat-conducting particles to one another; and some to the solder-adhesion layer on the first surface as well as adhesively bonding the resin matrix to the first surface and the second surface. The first surface can comprise an electronic device, e.g., a semiconductor device and the second surface a heat sink, such as a solderable heat sink. A product comprises an article of manufacture made by the process.