Abstract: 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.

Abstract: 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.

Abstract: 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.

Abstract: 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) located within an ambient pressure chamber, wherein the synthetic jet actuator 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.

Abstract: 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) located within an ambient pressure chamber, wherein the synthetic jet actuator 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.

Abstract: An aircraft engine is provided with at least one pulse detonation device connected to an engine exhaust nozzle portion with a plurality of supersonic injectors. The flow from the pulse detonation device is passed through the supersonic injectors into the primary engine flow path. The injector flow is injected at a velocity such that the injected flow penetrates into the primary flow path. This injected flow creates a virtual obstacle for the primary flow, and their interaction creates a virtual surface or an aero-lobe, thus controlling the nozzle exit area to reduce engine noise.

Abstract: 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.

Abstract: The present invention provides a pulse detonation insert that induces flow obstructions within the pulse detonation chambers, wherein the flow obstructions are operable to induce turbulence within a primary fluid flow passing over the obstructions. This turbulence may take the form of vortices that enhance the mixing of the oxidizer and fuel within the primary flow. Additionally, supports couple to the pulse detonation chamber walls and flow obstructions to hold the flow obstructions in place within the pulse detonation chamber. The combustion/Detonation of the mixed oxidizing fuel results in an increased velocity of the primary flow exiting the pulse detonation chamber and reduced the amount of unburnt fuel within the exhaust.

Abstract: An aircraft engine is provided with at least one pulse detonation device connected to an engine exhaust nozzle portion with a plurality of supersonic injectors. The flow from the pulse detonation device is passed through the supersonic injectors into the primary engine flow path. The injector flow is injected at a velocity such that the injected flow penetrates into the primary flow path. This injected flow creates a virtual obstacle for the primary flow, and their interaction creates a virtual surface or an aero-lobe, thus controlling the nozzle exit area to reduce engine noise.

Abstract: A system and method for control of a fluid flow. The system includes an array of interdependent fluidic actuators, each including a chamber, a flow control port, and opposite side walls configured to expand apart and contract together to flow a control fluid through the flow control port in response to an input, wherein adjacent actuators in the array of interdependent fluidic actuators are integrally coupled together via a common side wall of the opposite side walls.

Abstract: 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.

Abstract: The present invention provides a pulse detonation insert that induces flow obstructions within the pulse detonation chambers, wherein the flow obstructions are operable to induce turbulence within a primary fluid flow passing over the obstructions. This turbulence may take the form of vortices that enhance the mixing of the oxidizer and fuel within the primary flow. Additionally, supports couple to the pulse detonation chamber walls and flow obstructions to hold the flow obstructions in place within the pulse detonation chamber. The combustion/Detonation of the mixed oxidizing fuel results in an increased velocity of the primary flow exiting the pulse detonation chamber and reduced the amount of unburnt fuel within the exhaust.

Abstract: A wind turbine blade is situated on a wind turbine and includes a side and a tip. The blade is configured to rotate about an axis upon an impact of a wind flow on the blade. An active flow modification device is disposed on the blade. The active flow modification device is configured to receive active flow instructions and to modify the wind flow proximate to the blade. The resulting wind turbine blade uses these active flow modifications to achieve reduced loads, reduced aerodynamic losses, reduced noise, enhanced energy capture, or combinations thereof.

Abstract: An apparatus comprising: an aerodynamic surface adapted for producing an adverse pressure gradient in a fluid flow; and a first pulse detonation actuator disposed adjacent the aerodynamic surface and adapted for impulsively detonating a fuel/air mixture to produce a pressure rise and velocity increase of combustion products therein, the aerodynamic surface having a plurality of separation control holes adapted for communicating combustion product flows from the first pulse detonation actuator to the aerodynamic surface for modulating separation of the fluid flow from the aerodynamic surface.

Abstract: A gas cooking system having a gas cooking burner that includes a gas line, a first gas port coupled to the gas line, and a second gas port disposed downstream from the first gas port, wherein at least one of the first and second gas ports comprises a non-circular geometry adapted to increase air entrainment, the second gas port further being non-rectangular if the first gas port has a circular geometry.