Abstract: A method for actively manipulating a primary fluid flow over a surface using an active flow control system including an active fluid flow device to provide lift enhancement and lift destruction. The method including the disposing of an active fluid flow device in the surface. The active fluid flow device is then operated to generate at least one of a steady blowing secondary fluid flow, a pulsed secondary fluid flow or an oscillating secondary fluid flow. While flowing the primary fluid over the surface to create a primary flow field, a secondary fluid flow is injected in an upstream direction and substantially opposed to the incoming primary fluid flow. The injecting of the secondary fluid flow in this manner provides for influencing of the primary flow field by manipulating a momentum of the secondary fluid flow to influence the incoming primary fluid flow and resultant lift.

Abstract: Systems, apparatus, and program product and methods for controlling boundary layer flow across an aerodynamic structure which can produce separate regions of flow structures at different strengths by means of dielectric-barrier-discharge (DBD) type plasmas, are provided. An example of such apparatus provides plasma regions that are capable of being individually controlled by voltage and/or frequency, and modulated for the purposes of flow control. The apparatus includes an electrode assembly fitted with electrodes on either side of a dielectric such that different electrode geometries and arrangements create isolated regions of plasmas which results in separate regions of flow structures. These regions may be further controlled and modulated by the use of electronic-switching to produce irregularly shaped flow structures and strengths including those having a primarily vertical component.

Abstract: A fuel nozzle assembly for use with a turbine engine includes at least one fuel conduit coupled to at least one fuel source. The fuel nozzle assembly also includes at least one swirler that includes at least one wall having a porous portion. The at least one wall is coupled to the at least one fuel conduit. The porous portion is formed from a material having a porosity that facilitates fuel flow therethrough. At least one fuel flow path is thereby defined through the porous portion of the at least one wall.

Abstract: Systems and methods for controlling fluid flow utilizing a synthetic jet actuator, are provided. An example of a synthetic jet actuator system includes a synthetic jet actuator including a dual bimorph subsystem to provide low, medium, and high synthetic jet velocities and/or fine flow control response, and an arc-forming subsystem to provide enhanced pressure, velocity, and mass flow performance, enhanced flow control response, and/or heating of the fluid within the bimorph chamber to extend the performance or operating margin of the dual bimorph subsystem of the synthetic jet actuator. The arc-forming subsystem includes a pair of electrodes interfaced with inner surface walls of the dual bimorph subsystem. Various configurations of power supplies can be utilized to provide simultaneous function to both the subsystem and the arc-forming subsystem to allow selective activation.

Abstract: A system and a method of generating energy in a power plant using a turbine are provided. The system includes an air separation unit providing an oxygen output; a plasma generator that is capable of generating plasma; and a combustor configured to receive oxygen and to combust a fuel stream in the presence of the plasma, so as to maintain a stable flame, generating an exhaust gas. The system can further include a water condensation system, fluidly-coupled to the combustor, that is capable of producing a high-content carbon dioxide stream that is substantially free of oxygen. The method of generating energy in a power plant includes the steps of operating an air separation unit to separate oxygen from air, combusting a fuel stream in a combustor in the presence of oxygen, and generating an exhaust gas from the combustion. The exhaust gas can be used in a turbine to generate electricity. A plasma is generated inside the combustor, and a stable flame is maintained in the combustor.

Abstract: Systems, apparatus, and program product and methods for controlling boundary layer flow across an aerodynamic structure which can produce separate regions of flow structures at different strengths by means of dielectric-barrier-discharge (DBD) type plasmas, are provided. An example of such apparatus provides plasma regions that are capable of being individually controlled by voltage and/or frequency, and modulated for the purposes of flow control. The apparatus includes an electrode assembly fitted with electrodes on either side of a dielectric such that different electrode geometries and arrangements create isolated regions of plasmas which results in separate regions of flow structures. These regions may be further controlled and modulated by the use of electronic-switching to produce irregularly shaped flow structures and strengths including those having a primarily vertical component.

Abstract: In an embodiment, there is provided a method for the reduction of flow break in Single Radio Voice Call Continuity SRVCC mobility for a User Equipment UE, SRVCC mobility including Hand-Over HO execution procedure and Voice Call Continuity VCC procedure, said method comprising a step of: delaying HO execution at the UE, to coordinate HO execution procedure and VCC procedure.

Abstract: Pulse detonation/deflagration apparatus for providing enhanced pressure wave operating frequency and/or magnitude, and methods of increasing the frequency or the magnitude of deflagration to detonation waves, are provided. A pulse detonation/deflagration apparatus can include a main/outer pulse detonation/deflagration actuator/engine (PDA/E) with multiple smaller internal combustion chambers or tubes positioned inside the cavity of the main/outer PDA/E with each performing the function of individual PDA/Es. The output pressure waves created by the internal PDA/Es can be utilized for propulsion or for controlling large scale flows, where needed.

Abstract: A gas turbine combustion system passive air-fuel mixing prechamber includes one or more fuel passages. Each fuel passage includes at least one downstream fuel injection orifice. One or more fluid conduits connect an upstream portion of at least one fuel passage with one or more air passages such that pressure drops across each fuel injection orifice substantially self-equalize in a passive manner with corresponding air passage pressure drops over a broad range of fuel lower heating value (LHV) from about 150 Btu/scf to about 900 Btu/scf of fuel passing through the fuel passage while mixing with air passing through one or more connected fluid conduits. The effective area of each fluid conduit relative to the corresponding fuel and air passages is dependent upon the desired fuel LHV operating range.

Abstract: The invention relates to a case assembly for antenna amplifying system, an antenna amplifying system and a mast antenna incorporating such a system. According to the invention, the case assembly for antenna amplifying system having a general shape elongated along a longitudinal axis (34) comprises a control module (16) and two amplifying modules (9a, 9b) aligned therewith along the longitudinal axis (34), the control module (16) and both amplifying modules (9a, 9b) each comprising two longitudinal lateral walls (11a, 11b, 11c, 12a, 12b, 12c), an upper surface (36a, 36b, 36c) and a lower surface (37a, 37b, 37c) and having a small thickness.

Abstract: A system for deicing a wind turbine blade includes an electrically powered active plasma actuator applied to a desired portion of a wind turbine blade. The activated plasma actuator energizes the air in the vicinity of the plasma actuator to increase the surface temperature of the wind turbine blade in the vicinity of the plasma actuator sufficiently to reduce or eliminate the collection of ice on a desired portion of the wind turbine blade.

Abstract: A method, user equipment and a network entity are disclosed. The method comprises the steps of: determining which of a plurality of packet bearers carry voice media components for handover between a packet-switched network and a circuit-switched network to ensure voice call continuity; and notifying an entity that will said enforce voice call continuity for which of said plurality of packet bearers carry said voice media components.

Abstract: Systems and methods for controlling fluid flow utilizing a synthetic jet actuator, are provided. An example of a synthetic jet actuator system includes a synthetic jet actuator including a dual bimorph subsystem to provide low, medium, and high synthetic jet velocities and/or fine flow control response, and an arc-forming subsystem to provide enhanced pressure, velocity, and mass flow performance, enhanced flow control response, and/or heating of the fluid within the bimorph chamber to extend the performance or operating margin of the dual bimorph subsystem of the synthetic jet actuator. The arc-forming subsystem includes a pair of electrodes interfaced with inner surface walls of the dual bimorph subsystem. Various configurations of power supplies can be utilized to provide simultaneous function to both the subsystem and the arc-forming subsystem to allow selective activation.

Abstract: A system for deicing a wind turbine blade includes an electrically powered active plasma actuator applied to a desired portion of a wind turbine blade. The activated plasma actuator energizes the air in the vicinity of the plasma actuator to increase the surface temperature of the wind turbine blade in the vicinity of the plasma actuator sufficiently to reduce or eliminate the collection of ice on a desired portion of the wind turbine blade.

Abstract: A high gain pulse generator includes a piezoelectric transformer (PT) that is driven by an input power stage to drive the PT at a desired PT resonant frequency such that at least one PT characteristic substantially matches at least one non-linear load characteristic such as, without limitation, a plasma load characteristic to deliver a desired pulse to the non-linear load.

Abstract: The invention relates to a case assembly for antenna amplifying system, an antenna amplifying system and a mast antenna incorporating such a system. According to the invention, the case assembly for antenna amplifying system having a general shape elongated along a longitudinal axis (34) comprises a control module (16) and two amplifying modules (9a, 9b) aligned therewith along the longitudinal axis (34), the control module (16) and both amplifying modules (9a, 9b) each comprising two longitudinal lateral walls (11a, 11b, 11c, 12a, 12b, 12c), an upper surface (36a, 36b, 36c) and a lower surface (37a, 37b, 37c) and having a small thickness.

Abstract: Pulse detonation/deflagration apparatus for providing enhanced pressure wave operating frequency and/or magnitude, and methods of increasing the frequency or the magnitude of deflagration to detonation waves, are provided. A pulse detonation/deflagration apparatus can include a main/outer pulse detonation/deflagration actuator/engine (PDA/E) with multiple smaller internal combustion chambers or tubes positioned inside the cavity of the main/outer PDA/E with each performing the function of individual PDA/Es. The output pressure waves created by the internal PDA/Es can be utilized for propulsion or for controlling large scale flows, where needed.

Abstract: A plasma enhanced pilot including a swirler mechanism is configured to be inserted into an existing blank (purge air) or liquid fuel (dual fuel) cartridge space within the centerbody of a lean, premixed land-based gas turbine combustor fuel nozzle.

Abstract: An end-cutting vitrectomy probe 100 is provided that includes a hollow sleeve 102 having an opening 108 at the sleeve's distal end, and a tapered annular surface 112 disposed in the interior of the sleeve's distal end. The probe further includes a cutting member 120 disposed within the sleeve 102, and having a circumferential cutting edge 122 at its end. The cutting member 120 is moveable within the sleeve 102, such that the circumferential cutting edge 122 frictionally engages the tapered annular surface 112, to thereby cut any vitreous tissue disposed therebetween. The probe 100 may further include a drive mechanism 130 for slidably displacing the cutting member 120 within the hollow sleeve 102 in a reciprocating manner, to oscillate the cutting member 120 between engagement and disengagement with the tapered annular surface 112.

Abstract: A method and system is generally directed to synchronizing the language used for applications and the language used for information provided across a network. The client language that is associated with the language used for applications on a computing device is detected along with the services language. The services language corresponds to the language used for the user interface of network materials, such as web sites and help pages. The services language is stored online so that the services language and the client language may be made to correspond to one another despite the user moving from online to offline or from one computing device to another, allowing for a consistent user experience.