Abstract: A method of manufacturing a cooled gas turbine component includes forming a core with an outer surface. The outer surface includes a core feature. The method also includes casting an outer wall of an airfoil about the core. The outer wall has an exterior surface and an interior surface. The interior surface includes a shaped inlet portion that corresponds to the core feature. Moreover, the method includes forming an outlet portion through the outer wall to fluidly connect the outlet portion to the shaped inlet portion. The shaped inlet portion and the outlet portion cooperatively define a cooling aperture through the outer wall.

Abstract: A method of manufacturing a cooled gas turbine component includes forming a core with an outer surface. The outer surface includes a core feature. The method also includes casting an outer wall of an airfoil about the core. The outer wall has an exterior surface and an interior surface. The interior surface includes a shaped inlet portion that corresponds to the core feature. Moreover, the method includes forming an outlet portion through the outer wall to fluidly connect the outlet portion to the shaped inlet portion. The shaped inlet portion and the outlet portion cooperatively define a cooling aperture through the outer wall.

Abstract: A method of manufacturing a cooled gas turbine component includes forming a core with an outer surface. The outer surface includes a core feature. The method also includes casting an outer wall of an airfoil about the core. The outer wall has an exterior surface and an interior surface. The interior surface includes a shaped inlet portion that corresponds to the core feature. Moreover, the method includes forming an outlet portion through the outer wall to fluidly connect the outlet portion to the shaped inlet portion. The shaped inlet portion and the outlet portion cooperatively define a cooling aperture through the outer wall.

Abstract: A method of manufacturing a cooled gas turbine component includes forming a core with an outer surface. The outer surface includes a core feature. The method also includes casting an outer wall of an airfoil about the core. The outer wall has an exterior surface and an interior surface. The interior surface includes a shaped inlet portion that corresponds to the core feature. Moreover, the method includes forming an outlet portion through the outer wall to fluidly connect the outlet portion to the shaped inlet portion. The shaped inlet portion and the outlet portion cooperatively define a cooling aperture through the outer wall.

Abstract: Vane impingement tubes having blockage deterrent features are provided, as turbine nozzles containing blockage-resistant vane impingement tubes. In an embodiment, the turbine nozzle includes inner and outer annular endwalls, and turbine nozzle vanes arranged in an annular array between the outer and inner annular endwalls. Vane impingement tubes are inserted into the turbine nozzle vanes. The vane impingement tubes each includes a tube body, an impingement outlet formed in the tube body and configured to discharge airflow for impingement against one of the turbine nozzle vanes, a first flow-turning feature located in the tube body, and an inlet formed in the tube body and configured receive cooling airflow in a substantially radial direction. The first flow-turning feature is shaped and positioned to turn the airflow received through the inlet in a substantially axial direction, which is perpendicular to the radial direction, prior to discharge through the impingement outlet.

Abstract: A method of manufacturing a cooled gas turbine component includes forming a core with an outer surface. The outer surface includes a core feature. The method also includes casting an outer wall of an airfoil about the core. The outer wall has an exterior surface and an interior surface. The interior surface includes a shaped inlet portion that corresponds to the core feature. Moreover, the method includes forming an outlet portion through the outer wall to fluidly connect the outlet portion to the shaped inlet portion. The shaped inlet portion and the outlet portion cooperatively define a cooling aperture through the outer wall.

Abstract: Vane impingement tubes having blockage deterrent features are provided, as turbine nozzles containing blockage-resistant vane impingement tubes. In an embodiment, the turbine nozzle includes inner and outer annular endwalls, and turbine nozzle vanes arranged in an annular array between the outer and inner annular endwalls. Vane impingement tubes are inserted into the turbine nozzle vanes. The vane impingement tubes each includes a tube body, an impingement outlet formed in the tube body and configured to discharge airflow for impingement against one of the turbine nozzle vanes, a first flow-turning feature located in the tube body, and an inlet formed in the tube body and configured receive cooling airflow in a substantially radial direction. The first flow-turning feature is shaped and positioned to turn the airflow received through the inlet in a substantially axial direction, which is perpendicular to the radial direction, prior to discharge through the impingement outlet.

Abstract: A method of manufacturing a cooled gas turbine component includes forming a core with an outer surface. The outer surface includes a core feature. The method also includes casting an outer wall of an airfoil about the core. The outer wall has an exterior surface and an interior surface. The interior surface includes a shaped inlet portion that corresponds to the core feature. Moreover, the method includes forming an outlet portion through the outer wall to fluidly connect the outlet portion to the shaped inlet portion. The shaped inlet portion and the outlet portion cooperatively define a cooling aperture through the outer wall.

Abstract: An inlet particle separator system for an engine includes a hub section, a shroud section, a splitter, and a plasma flow control actuator. The shroud section surrounds at least a portion of the hub section and is spaced apart therefrom to define a passageway having an air inlet. The splitter is disposed downstream of the air inlet and extends into the passageway to divide the passageway into a scavenge flow path and an engine flow path. The plasma flow control actuator is coupled to the hub section and is disposed between the air inlet and the splitter.

Abstract: An inlet particle separator system for an engine includes an inner flowpath section, an outer flowpath section, a splitter, a first electrostatic discharge device, and a second electrostatic discharge device. The outer flowpath section surrounds at least a portion of the inner flowpath section and is spaced apart therefrom to define a passageway having an air inlet. The splitter is disposed downstream of the air inlet and extends into the passageway to divide the passageway into a scavenge flow path and an engine flow path. The first electrostatic charge device is disposed between the air inlet and the splitter and is electrostatically charged to a first polarity. The second electrostatic charge device is disposed downstream of the first electrostatic charge device and is electrostatically charged to a second polarity that is opposite to the first polarity.

Abstract: A subscriber login server is used for managing a subscriber login session. The login server is associated with a DHCP server for configuring a premise equipment device and operator-managed device. A subscriber login client at the premise equipment device securely communicates login username and password identifiers to the subscriber login server without using PPP technology. The login server retrieves matching identifiers from a RADIUS server and authorizes service with messages to the DHCP server and the CMTS. The login client can emulate a PPP login client so that a user's interface is similar to a PPPoE client. However, a layer-3 CMTS can be used instead of a layer-2 CMTS. In addition, subscriber authentication and accounting using RADIUS are preserved, positive network access control at the CMTS is maintained, and native IP traffic is routed or switched for maximum performance and QoS treatment.

Abstract: A cooling arrangement is provided for a gas turbine engine with a turbine section. The cooling arrangement includes a first conduit to receive cooling air that includes particles; a separator system coupled to the first conduit to receive the cooling air and configured to remove at least a portion of the particles to result in relatively clean cooling air and scavenge air including the portion of the particles; and a second conduit coupled to the separator system and configured to direct the relatively clean cooling air to the turbine section.

Abstract: A packet data flow processor applies a first level of Data Over Cable Service Interface Specification (DOCSIS) processing to packet flows that are not from trusted sources, and applies a second level of DOCSIS processing, simpler than the first level, to packet flows from the trusted sources.

Abstract: A cooling arrangement is provided for a gas turbine engine with a turbine section. The cooling arrangement includes a first conduit to receive cooling air that includes particles; a separator system coupled to the first conduit to receive the cooling air and configured to remove at least a portion of the particles to result in relatively clean cooling air and scavenge air including the portion of the particles; and a second conduit coupled to the separator system and configured to direct the relatively clean cooling air to the turbine section.

Abstract: An inlet particle separator system for an engine includes an inner flowpath section, an outer flowpath section, a splitter, a first electrostatic discharge device, and a second electrostatic discharge device. The outer flowpath section surrounds at least a portion of the inner flowpath section and is spaced apart therefrom to define a passageway having an air inlet. The splitter is disposed downstream of the air inlet and extends into the passageway to divide the passageway into a scavenge flow path and an engine flow path. The first electrostatic charge device is disposed between the air inlet and the splitter and is electrostatically charged to a first polarity. The second electrostatic charge device is disposed downstream of the first electrostatic charge device and is electrostatically charged to a second polarity that is opposite to the first polarity.

Abstract: An inlet particle separator system for an engine includes a hub section, a shroud section, a splitter, and a plasma flow control actuator. The shroud section surrounds at least a portion of the hub section and is spaced apart therefrom to define a passageway having an air inlet. The splitter is disposed downstream of the air inlet and extends into the passageway to divide the passageway into a scavenge flow path and an engine flow path. The plasma flow control actuator is coupled to the hub section and is disposed between the air inlet and the splitter.

Abstract: An impeller or axial stage compressor disk backface shroud for use with a gas turbine engine is disclosed. The backface shroud includes, but is not limited to, a substantially funnel shaped body having a surface. The substantially funnel shaped body is configured to be statically mounted to the gas turbine engine substantially coaxially with the impeller or axial stage compressor disk. The surface and a backface of the impeller or axial stage compressor disk form a cavity that guides an airflow portion to a turbine when the substantially funnel shaped body is mounted coaxially with the impeller or axial stage compressor disk and axially spaced apart therefrom. The airflow portion has a tangential velocity and a recessed groove in the surface of the backface shroud is oriented generally transversely to the tangential velocity to at least partially interfere with the airflow portion, thus affecting static pressure in the cavity.

Abstract: Bandwidth is assigned to subscribers of a data network by applying logic of one or more network devices to sample bits of information communicated over a network communication medium to identify if there is a network congestion condition or an extremely lightly loaded condition. The maximum bandwidth assigned to a subscriber is below a normative maximum bandwidth assigned to the subscriber if the network is congested and the logic of the one or more network devices identifies the subscriber as a heavy bandwidth user. The maximum bandwidth assigned to a subscriber is above the normative maximum bandwidth if the network is extremely lightly loaded and the subscriber is a heavy bandwidth user.

Abstract: Gas turbine engines and methods for cooling components thereof with mid-impeller bleed (MIB) cooling air having a pressure are provided. The gas turbine engine has a compressor comprising an impeller body and an impeller shroud at least partially surrounding the impeller body. The impeller shroud has a plurality of MIB openings disposed therein. At least one edge treatment is provided thereto. The edge treatment substantially preserves pressure of the cooling air during entrance into and discharge out of the MIB opening. The plurality of MIB openings may be extended MIB openings in a thickened impeller shroud. The centerline of the MIB openings may be oriented to be substantially aligned with an averaged local absolute flow velocity vector of the cooling air at the inlet section of the MIB opening in order to extract cooling air in a direction that has a vector component in a tangential, an axial, and a radial flow direction.

Abstract: A data communication system includes multiple Media Access Control (MAC) units, multiple physical layer (PHY) interface units, and logic to communicate between the MAC units and the PHY units using a single tunneling protocol over Internet Protocol (IP).