General Electric Company

Lockheed Martin Corporation

Nuovo Pignone Tecnologie Srl

Lumination LLC

Ge Lighting Solutions LLC

Matthew Patrick Boespflug

Seyed Gholamali Saddoughi

Grover Andrew Bennett, Jr

Anurag Gupta

Grover Andrew Bennett

Narendra Digamber Joshi

Stephen Bertram Johnson

Peggy Lynn Baehmann

Dmytro Floriyovych Opaits

Dennis Steenburgh

Mehmet Arik

Daniel Jason Erno

Geoffrey David Myers

Todd Garrett Wetzel

Adam Rasheed

James Thomas Petroski

Fulton Jose Lopez

Nicholas William Rathay

Michael Solomon Idelchik

Robert Michael Zirin

Hasan Ul Karim

Fengfeng Tao

Robert Carl Murray

Richard Jon Chevrette

Bruce J Badding

John Thomas Herbon

Ahmed Mostafa ELKady

George Horner Kirby, Iii

Philippe Giguere

Pierre Francois Pinard

Dmitry Opaits

Seyed Gholami Saddoughi

Seyed Gholani Saddoughi

Uyigue Omoma Idahosa

Katherine Anne Essenhigh

Tak Kwong Woo

Scott Donnelly

Jr Bennett Grover Andrew

Grover Andrew Bennett Jr

Jr Grover Andrew Bennett

Bruce John Badding

Seyed Gholamall Saddoughi

Dmytro Flonyovych Opaits

A flow control actuator includes at least one side wall, an upstream wall coupled to an upstream end of the side wall, a downstream cap coupled to a downstream end of the side wall, the downstream cap comprising at least one orifice disposed therein, at least one fuel injector disposed in at least one of the upstream wall, and the sidewall, the fuel injector dispersing fuel into the interior of the flow control actuator, and at least one oxidizer inlet disposed in at least one of the upstream wall and the sidewall, the at least one oxidizer inlet introducing an oxidizer into the interior of the flow control actuator. The flow control actuator includes at least one external fuel injector disposed adjacent to the side wall. The fuel from the fuel injector and oxidizer from the oxidizer inlet ignite in the interior of the flow control actuator.

Combustion-powered flow control actuator with external fuel injector

A synthetic jet pump and a method of pumping fluid using such a synthetic jet pump are disclosed. The synthetic jet pump includes a plurality of first stacks disposed in a series arrangement relative to each other, and a plurality of first valves. A first stack of the plurality of first stacks includes a plurality of first connector pairs coupled to a first support structure and a plurality of first bimorph pairs. The first connector pairs and the first bimorph pairs are disposed in a parallel arrangement relative to each other respectively. A bimorph of one of the first bimorph pairs is coupled to a corresponding first connector pair. The plurality of first valves is disposed at an upstream end of the plurality of first stacks. A valve of the plurality of first valves is movably coupled to a corresponding connector of the plurality of the first connector pairs.

Synthetic jet pump and an associated method thereof

A compressor includes a plurality of synthetic jet assemblies. Each synthetic jet assembly of the plurality of synthetic jet assemblies is in fluid communication with at least one other synthetic jet assembly of the plurality of synthetic jet assemblies. Each synthetic jet assembly of the plurality of synthetic jet assemblies includes a first side plate and a second side plate. The first side plate includes a first bimorph piezoelectric structure. The second side plate includes a second bimorph piezoelectric structure. The first side plate and the second side plate define a first fluid cavity extending between the first side plate and the second side plate.

Compressor with dual bimorph synthetic jet assemblies

A virtual aerodynamic component for a wind turbine including at least one rotor blade connected to a hub. The at least one rotor blade defines an inner portion and a profiled outer portion. The virtual aerodynamic component includes one or more air-blowing units configured to provide a flow of air substantially opposed to an incoming wind. The flow of air defines the virtual aerodynamic component in front of the inner portion of the at least one rotor blade and provides for redirection of the incoming wind toward the profiled outer portion of the at least one rotor blade in an operational state and allows the incoming wind to flow toward the inner portion of the at least one rotor blade in a non-operational state. Further described is a wind turbine including the above-described virtual aerodynamic component and method for aerodynamic performance enhancement of an existing wind turbine.

Apparatus and method for aerodynamic performance enhancement of a wind turbine

A deployable aerodynamic component configured to be mounted to a wind turbine. The wind turbine includes at least one rotor blade. The deployable aerodynamic component configured to be positioned in front of an inner portion of the at least one rotor blade, and is structurally configured to cover a substantial portion of the inner portion of the at least one rotor blade in a wind direction during deployment of the deployable aerodynamic component and to allow the passage therethrough of an incoming wind when non-deployed. Further described is a wind turbine including the above-described deployable aerodynamic component and method for aerodynamic performance enhancement of an existing wind turbine, wherein the method includes mounting the above-described deployable aerodynamic component to a wind turbine.

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.

Method of using an active flow control system for lift enhancement or destruction in a wind turbine blade

A gas turbine engine augmentor includes at least one fluid based augmentor initiator defining a chamber in flow communication with a source of air and a source of fuel. The chamber includes a plurality of ejection openings in flow communication with an exhaust flowpath. The at least one fluid based augmentor initiator is devoid of any exhaust flowpath protrusions thereby minimizing any pressure drops and loss of thrust during dry work phase of operation. The source of fuel is operable for injecting fuel into the chamber such that at least a portion of the fuel flow is ignited at the plurality of ejection openings to produce a plurality of fuel-rich hot jets radially into the exhaust flowpath.

Side-initiated augmentor for engine applications

A synthetic jet apparatus including a series of generally parallel spaced-apart bimorph piezoelectric plates defining first and second sets of fluid chambers. The chambers of the second set of fluid chambers are interleaved with the chambers of the first set of fluid chambers. The first and second sets of fluid chambers are in fluid communication with sources of first and second fluids, respectively, the source of the first fluid being separate from the source of the second fluid. The bimorph plates are operable to alternately draw the first fluid from its source into the first set of fluid chambers while expelling the second fluid from the second set of fluid chambers, and then expel the first fluid from the first set of fluid chambers back into its source while drawing the second fluid from its source into the second set of fluid chambers.

Synthetic jet apparatus

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.

Systems and methods for power generation using oxy-fuel combustion

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.

System, apparatus, program product, and related methods for providing boundary layer flow control

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.

Pulse detonation/deflagration apparatus and related methods for enhancing DDT wave production

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.

System and method of deicing and prevention or delay of flow separation over wind turbine blades

A system and method for actively manipulating fluid flow over a surface using synthetic pulsators. Synthetic pulsators produce pulsed jet operable to manipulate the primary fluid flow proximate to the synthetic pulsator. The synthetic pulsator includes a dual diaphragm synthetic jet coupled to high performance dual actuator solenoids, wherein the synthetic jet is operable to produce an oscillatory flow. The oscillatory flow of the synthetic jet(s) produces the pulsed jet operable to manipulate the primary fluid flow. These synthetic pulsators may then be actively manipulated to control the flow behavior of the ducted fluid flow, influence the inception point and trajectory of flow field vortices within the fluid flow, and reduce flow separation within the primary fluid flow.

High performance synthetic valve/pulsator

The present invention provides a system and method for actively manipulating fluid flow over a surface using synthetic pulsators. Synthetic pulsators produce pulsed jet operable to manipulate the primary fluid flow proximate to the synthetic pulsator. The synthetic pulsator includes a synthetic jet actuator(s) operable to produce an oscillatory flow, and fluidic jet(s) operable to provide a continuous fluid flow. The oscillatory flow of the synthetic jet(s) and the continuous fluid flow of the fluidic jet(s) combine or mix to produce the pulsed jet operable to manipulate the primary fluid flow. These synthetic pulsators may then be actively manipulated to control the flow behavior of the ducted fluid flow, influence the inception point and trajectory of flow field vortices within the fluid flow, and reduce flow separation within the primary fluid flow.

Dual bimorph synthetic pulsator

Growing community of inventors

Clifton Park, NY, United States of America

Matthew Patrick Boespflug