General Electric Company

Lockheed Martin Corporation

Lumination LLC

Ge Lighting Solutions LLC

Seyed Gholamali Saddoughi

Matthew Patrick Boespflug

Anurag Gupta

Fengfeng Tao

Grover Andrew Bennett, Jr

Robert Carl Murray

Abdelkrim Younsi

Aspi Rustom Wadia

John Thomas Herbon

Grover Andrew Bennett

Dmytro Floriyovych Opaits

Clark Leonard Applegate

Stephen Bertram Johnson

Peggy Lynn Baehmann

Steven Martens

Philippe Giguere

Frank Jakob John Mueller

Narendra Digamber Joshi

Mehmet Arik

Daniel Jason Erno

Anthony John Dean

Geoffrey David Myers

John Stanley Glaser

Stefan Herr

Todd Garrett Wetzel

Karim Younsi

Adam Rasheed

James Thomas Petroski

Fulton Jose Lopez

Michael Kent Cueman

Michael Solomon Idelchik

Robert Michael Zirin

Lawrence Butler

Hasan Ul Karim

Bruce J Badding

Brian R Smith

Florian Peter Pintgen

Ahmed Mostafa ELKady

Joseph Taher Mossoba

Pierre Francois Pinard

Ivett Alejandra Leyva

Dmitry Opaits

Dennis Steenburgh

Kevin Sean Early

Uyigue Omoma Idahosa

Scott Donnelly

Bernard Francois Robic

Jr Bennett Grover Andrew

Grover Andrew Bennett Jr

Jr Grover Andrew Bennett

Bruce John Badding

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 plasma actuator system includes a first electrode having a first slit formed in a first peripheral section of the first electrode. The first slit directs flow of a gaseous medium along a radial direction of the first electrode. Further, the plasma actuator system includes a second electrode coupled to the first electrode and is disposed concentrically around the first electrode. The second electrode includes a second slit formed in a second peripheral section for directing flow of the gaseous medium along the radial direction. Further, the system includes a power source coupled to the first and second electrode for supplying electric power to the electrodes for ionizing gaseous medium to generate plasma.

System and method for controlling plasma induced flow

Active Circulation Control (ACC) of aerodynamic structures, such as a turbine blade, uses unsteady or oscillatory flow from either synthetic jets or pulsed jets to modify a velocity profile of the blade. The blade includes an opening disposed in a surface of the blade at a location proximate to a trailing edge, a leading edge, or both the trailing edge and the leading edge of the blade. An active flow control device in fluid communication with the opening produces a wall-jet of pulsed fluid that flows over the trailing edge, the leading edge, or both the trailing and leading edges of the blade and modify the velocity profile of the blade.

Active circulation control of aerodynamic structures

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 gate drive circuit includes an insulated gate semiconductor switch. A controlled current source is connected to the semiconductor switch gate terminal to provide a gate drive circuit that is responsive to recycled gate charge corresponding to an internal gate capacitance of the insulated gate semiconductor switch.

High speed low loss gate drive circuit

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 heat resistant piezo bimorph synthetic jet apparatus comprises a working fluid chamber partially defined by a plate, a working fluid port that provides fluid flow communication between the working fluid chamber and a working fluid mass, and a bimorph piezoelectric structure included in the plate. The bimorph piezoelectric structure alternately increases and decreases chamber volume by alternately expanding convexly and concavely in response to application of voltage of alternating polarity to alternately draw working fluid into and expel working fluid from the working fluid chamber through the working fluid port. A thermal insulating layer is disposed between the working fluid chamber and the bimorph piezoelectric structure to protect a ceramic layer within the first bimorph piezoelectric structure from high temperature working fluid.

Heat resistant piezo bimorph 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

A power generator includes one or more full bridge inverter modules coupled to a semiconductor opening switch (SOS) through an inductive resonant branch. Each module includes a plurality of switches that are switched in a fashion causing the one or more full bridge inverter modules to drive the semiconductor opening switch SOS through the resonant circuit to generate pulses to a load connected in parallel with the SOS.

Solid state pulsed power generator

An instability mitigation system is disclosed, comprising a rotor having a row of blades arranged around a centerline axis, and a mitigation system comprising at least one plasma actuator mounted on a blade that facilitates the improvement of the stability of the rotor, and a control system for controlling the operation of the mitigation system. An instability mitigation system further comprising a detection system for detecting an onset of an instability in a rotor and a control system for controlling the detection system and the mitigation system are disclosed.

Instability mitigation system using rotor plasma actuators

An instability mitigation system is disclosed, comprising a detection system for detecting an onset of an instability in a rotor during the operation of the rotor, a mitigation system that facilitates the improvement of the stability of the rotor when the onset of instability is detected by the detection system, a control system for controlling the detection system and the mitigation system.

Instability mitigation system

Growing community of inventors

Clifton Park, NY, United States of America

Seyed Gholamali Saddoughi