Abstract: A gas turbine engine assembly includes a housing including an annular duct wall that at least partially defines a mainstream hot gas flow path configured to receive mainstream hot gas flow. The assembly further includes a stator assembly including a stator vane that extends into the mainstream hot gas flow path and a turbine rotor assembly downstream of the stator assembly that includes a turbine disk and a turbine blade extending from the turbine disk into the mainstream hot gas flow path. The stator assembly and turbine assembly define a turbine disk cavity, and the turbine disk cavity includes a recirculation cavity configured to recirculate gas ingested from the mainstream hot gas flow path back into the mainstream hot gas flow path.

Abstract: A gas turbine engine includes a housing with a duct wall that defines a generally annular and axially elongated hot gas flow path for passage of combustion gas. The engine further includes a contoured shroud mounted within the internal engine cavity and defining a hot gas recirculation pocket for receiving hot gas ingested from the hot gas flow path through the annular space and for recirculating the ingested hot gas back through the annular space to the hot gas flow path. The contoured shroud includes a base wall extending radially inwardly from the duct wall, an inboard wall extending from the base wall in an axial direction toward the rotor, and an end wall extending from the inboard wall in a radially outward direction. The end wall terminates in a circumferentially extending free edge disposed in proximity to the annular space. The end wall defines an opening.

Abstract: A gas turbine engine assembly has combustion gases flowing through a gas flow path. The gas turbine engine assembly includes a stator assembly comprising a stator vane that extends into the gas flow path; and a turbine rotor assembly downstream of the stator assembly and comprising a turbine platform and a turbine rotor blade extending from the turbine platform into the mainstream combustion gases flow path. The turbine rotor blade includes a pressure side and a suction side opposing the pressure side that extend from a leading edge to a trailing edge. The combustion gases form horseshoe vortices at a formation area adjacent the leading edge of the turbine rotor blade, and the turbine rotor assembly further includes a first set of holes in the turbine platform for directing first jets into the formation area of the horseshoe vortices.

Abstract: A turbine blade assembly is provided. The turbine blade assembly comprises a turbine blade comprising a cavity, and a blade platform supporting the turbine blade, the cavity extending into the blade platform. The blade platform comprises an upper surface adjacent the turbine blade and a lower surface comprising a first rib, the cavity extending into the first rib, the first rib coupled to the lower surface, tapering as it extends away from the turbine blade, and comprising a first port extending from the cavity to the upper surface.

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: A translation agent adapts DOCSIS information, primarily QoS information, for transmission over a PON. The agent places into an IP address field of a DHCP message the MAC address of an ONU associated with a CPE device attempting to register with a CMTS. The translation agent intercepts DHCP reply messages from the DHCP server using the MAC address of the ONU. The translation agent extracts information, including an IP address of the client CPE assigned by the DHCP server. The agent downloads a configuration file for the CPE device using the configuration filename and configuration file server contained in a DHCP reply message. Information contained in the configuration file is converted from content in a format used by DOCSIS, to content in a format used by PON devices. The translated content includes QoS parameters, functions related to which are controlled at the ONU by an OLT coupled to the CMTS.

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 turbine blade assembly is provided. The turbine blade assembly comprises a turbine blade comprising a cavity, and a blade platform supporting the turbine blade, the cavity extending into the blade platform. The blade platform comprises an upper surface adjacent the turbine blade and a lower surface comprising a first rib, the cavity extending into the first rib, the first rib coupled to the lower surface, tapering as it extends away from the turbine blade, and comprising a first port extending from the cavity to the upper surface.

Abstract: A gas turbine engine assembly has combustion gases flowing through a gas flow path. The gas turbine engine assembly includes a stator assembly comprising a stator vane that extends into the gas flow path; and a turbine rotor assembly downstream of the stator assembly and comprising a turbine platform and a turbine rotor blade extending from the turbine platform into the mainstream combustion gases flow path. The turbine rotor blade includes a pressure side and a suction side opposing the pressure side that extend from a leading edge to a trailing edge. The combustion gases form horseshoe vortices at a formation area adjacent the leading edge of the turbine rotor blade, and the turbine rotor assembly further includes a first set of holes in the turbine platform for directing first jets into the formation area of the horseshoe vortices.

Abstract: A gas turbine engine assembly includes a housing including an annular duct wall that at least partially defines a mainstream hot gas flow path configured to receive mainstream hot gas flow. The assembly further includes a stator assembly including a stator vane that extends into the mainstream hot gas flow path and a turbine rotor assembly downstream of the stator assembly that includes a turbine disk and a turbine blade extending from the turbine disk into the mainstream hot gas flow path. The stator assembly and turbine assembly define a turbine disk cavity, and the turbine disk cavity includes a recirculation cavity configured to recirculate gas ingested from the mainstream hot gas flow path back into the mainstream hot gas flow path.

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 gas turbine engine includes a housing with a duct wall that defines a generally annular and axially elongated hot gas flow path for passage of combustion gas. The engine further includes a contoured shroud mounted within the internal engine cavity and defining a hot gas recirculation pocket for receiving hot gas ingested from the hot gas flow path through the annular space and for recirculating the ingested hot gas back through the annular space to the hot gas flow path. The contoured shroud includes a base wall extending radially inwardly from the duct wall, an inboard wall extending from the base wall in an axial direction toward the rotor, and an end wall extending from the inboard wall in a radially outward direction. The end wall terminates in a circumferentially extending free edge disposed in proximity to the annular space. The end wall defines an opening.

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).

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: A translation agent adapts DOCSIS information, primarily QoS information, for transmission over a PON. The agent places into an IP address field of a DHCP message the MAC address of an ONU associated with a CPE device attempting to register with a CMTS. The translation agent intercepts DHCP reply messages from the DHCP server using the MAC address of the ONU. The translation agent extracts information, including an IP address of the client CPE assigned by the DHCP server. The agent downloads a configuration file for the CPE device using the configuration filename and configuration file server contained in a DHCP reply message. Information contained in the configuration file is converted from content in a format used by DOCSIS, to content in a format used by PON devices. The translated content includes QoS parameters, functions related to which are controlled at the ONU by an OLT coupled to the CMTS.