US 20070119827 A1
A plasma jet system includes a housing with a single opening. A plasma generator is coupled to ionize a fluid in the housing. An electromagnetic accelerator is coupled to generate an electric field that accelerates ionized fluid in the housing toward the opening. A controller can modulate the frequency of the electric field to cause the ionized fluid to form a plasma vortex flow through the opening. A magnetic field is applied normal to the direction of the plasma vortex flow to mitigate the momentum of the electrons. The electrons slowed by the magnetic field can be collected and conducted to a location where they are re-inserted into the plasma vortex flow to maintain charge neutrality.
1. A plasma jet system, comprising:
a housing including a single opening, wherein a partially ionized fluid is drawn into the opening;
an electromagnetic accelerator configured to generate an electric field that accelerates the ionized fluid in the housing toward the opening in the housing, and to generate a magnetic field transverse to the electric field; and
a controller coupled to modulate the electromagnetic accelerator, thereby causing the ionized fluid to form a pulsed plasma flow through the opening in the housing.
2. The plasma jet system of
3. The plasma jet system of
4. The plasma jet system of
5. The plasma jet system of
a nozzle, wherein the housing is configured in the nozzle so that the plasma flow varies an effective throat area of the nozzle.
6. The plasma jet system of
a nozzle, wherein the housing is configured in the nozzle so that the plasma flow vectors the direction of thrust exiting the nozzle.
7. The plasma jet system of
an aerodynamic structure, wherein the housing is configured in the aerodynamic structure so that the plasma flow changes at least a portion of the effective shape of the aerodynamic structure.
8. The plasma jet system of
an aerodynamic structure, wherein the housing is configured in the aerodynamic structure so that the plasma flow affects the pressure on the aerodynamic surface by accelerating or decelerating the plasma flow.
9. The plasma jet system of
an aerodynamic structure, wherein the housing is configured in the aerodynamic structure so that the plasma flow creates forces and moments on the aerodynamic structure in reaction to the acceleration or deceleration of the plasma flow.
10. The plasma jet system of
11. The plasma jet system of
12. The plasma jet system of
13. A method comprising:
accelerating an ionized fluid through an electric field in a housing, wherein the housing includes a single opening and the electric field is oriented to accelerate the ionized fluid in the direction of the opening, thereby forming a plasma flow;
generating a magnetic field transverse to the electric field, wherein the magnetic field decelerates electrons in the housing;
collecting decelerated electrons; and
transporting collected electrons to a location where the collected electrons are reinserted into the plasma flow.
14. The method of
pulsing the electric field at a predetermined frequency, thereby forming vortex rings of the plasma flow as the plasma flow exits the housing.
15. The method of
injecting electron beams into the housing to generate the plasma.
16. The method of
injecting the plasma flow into a primary flow to alter the direction of the primary flow.
17. The method of
using the plasma flow to perform at least one of the group consisting of:
altering the aerodynamic characteristics of a surface;
controlling aerodynamic forces and moments acting on a device in which the housing is installed;
mixing fuel and air in a device in which the housing is installed; and
controlling aerodynamic forces and moments acting on a device in which the housing is installed.
18. An apparatus comprising:
an enclosure including a single opening;
an electric field generator operable to generate an electric field in the enclosure;
a magnetic field generator operable to generate a magnetic field transverse to the electric field; and
an ionized fluid source configured to provide ionized fluid in the enclosure, wherein the electric field is oriented to accelerate the ionized fluid toward the opening to generate a plasma jet.
19. The apparatus of
a controller operable to control at least one of the group consisting of:
the electric field generator to provide a pulsed electric field;
the strength of the electric field generated by the electric field generator;
the ionized fluid source;
sequentially activate and deactivate a series of pairs of electrodes of opposite polarity; and
the strength of the electric field generated by the electric field generator.
20. The apparatus of
a conductor configured to transport the electrons to a location where electrons collected in the enclosure are reinserted into the plasma flow.
Active flow control involves modification of the turbulent structure of eddies in most complex flows with the intent to improve aerodynamic performance of air vehicle flight control and propulsion systems. Such capability can increase range and maneuverability, reduce acoustic loads, signature, weight, and cost. In some systems, a relatively small amount of high-momentum secondary fluid is used to enhance the naturally occurring instabilities of the main flow. For example, it is known to use active flow control in applications such as favorably influencing the flow over an aerodynamic surface, heating/cooling components, vectoring a primary fluid flow, and mixing fluids.
One type of device that can be used for active flow control in subsonic systems is referred to as a zero-net-mass jet. A typical zero-net-mass jet actuator comprises a housing defining an internal chamber. An orifice is present in a wall of the housing. The actuator further includes a mechanism in or about the housing for periodically changing the volume within the internal chamber so that a series of fluid vortices are generated and projected in an external environment out from the orifice of the housing. Various volume changing mechanisms are known, for example a piston positioned in the jet housing to move so that fluid is moved in and out of the orifice during reciprocation of the piston, or a flexible diaphragm as a wall of the housing. The flexible diaphragm is typically actuated by a piezoelectric actuator or other appropriate means.
Typically, a control system is utilized to create time-harmonic motion of the diaphragm. As the diaphragm moves into the chamber, decreasing the chamber volume, fluid is intermittently ejected from the chamber through the orifice. As a quantity of fluid passes through the orifice, the flow separates at the sharp edges of the orifice and creates a shear layer, which rolls up into a vortex sheet or ring. As each intermittent quantity of fluid is emitted, a separate vortical structure is generated creating a train of vortices moving away from the orifice. These vortices move away from the edges of the orifice under their own self-induced velocity. As the diaphragm moves outward with respect to the chamber, increasing the chamber volume, ambient fluid is drawn from all directions around the orifice into the chamber. Since the vortices are already removed from the edges of the orifice, they are not affected by the ambient fluid being entrained into the chamber. As the vortices travel away from the orifice, they synthesize a jet of fluid, a “zero-net-mass jet,” through entrainment of the ambient fluid.
However, piezoelectric diaphragms used to form zero-net-mass jets are generally unreliable due to moving parts and cause vibration in devices in which they are installed. Further, the amplitude, temperature, and frequency at which the diaphragms can operate is limited, with the result that piezoelectrically-driven zero-net-mass jets generate limited jet velocity and have little practical application in flows above approximately Mach 0.3.
In physics and chemistry, plasma (also called an ionized gas) is an energetic state of matter in which some or all of the electrons in the outer atomic orbital rings have become separated from the atom. Excitation of a plasma requires partial ionization of neutral atoms and/or molecules of a medium. There are several ways to cause ionization including collisions of energetic particles, strong electric fields, and ionizing radiation. The energy for ionization may come from the heat of chemical or nuclear reactions of the medium, as in flames, for instance. Alternatively, already released charged particles may be accelerated by electric fields, generated electromagnetically or by radiation fields.
There are two broad categories of plasma, hot plasmas and cold plasmas. In a hot plasma, full ionization takes place, and the ions and the electrons are in thermal equilibrium. A cold plasma (also known as a weakly ionized plasma) is one where only a small fraction of the atoms in a gas are ionized, and the electrons reach a very high temperature, whereas the ions remain at the ambient temperature. These plasmas can be created by using a high electric field, or through electron bombardment from an electron gun, and other means . . .
In some embodiments, a plasma jet system is disclosed that includes a housing with an opening. A plasma generator is coupled to ionize a fluid in the housing. An electromagnetic accelerator is coupled to generate an electric field that accelerates ionized fluid in the housing toward the opening. A controller can modulate the frequency of the electric field to cause the ionized fluid to form a plasma vortex flow through the opening. A magnetic field is applied normal to the direction of the plasma vortex flow to mitigate the momentum of the electrons. The electrons slowed by the magnetic field can be collected and conducted to a location where they are re-inserted into the plasma vortex flow to maintain charge neutrality. The plasma jet system has no moving parts and no change in mass flow volume is required to create the plasma flow.
The foregoing has outlined rather broadly the features and technical advantages of embodiments of the present invention so that those skilled in the art may better understand the detailed description of embodiments of the invention that follows.
Embodiments disclosed herein may be better understood, and their numerous objects, features, and advantages made apparent to those skilled in the art by referencing the accompanying drawings. The use of the same reference symbols in different drawings indicates similar or identical items.
What is desired is a fixed-volume zero-net-mass jet actuator with sufficient momentum and control authority that can be used to actively control high velocity flows in a variety of applications, such as engines, aerodynamic surfaces, mixing, and heating and cooling. Embodiments disclosed herein provide a plasma flow accelerated through an electric field to create a high speed, steady and/or high frequency pulsed plasma jet. The plasma jet can be configured to control flow without diverting a portion of the primary flow or requiring an auxiliary flow source.
The magnetic field B is applied normal to the direction of the plasma jet and creates a large force on the electrons. The force of magnetic field B mitigates the momentum of the electrons, which aids collection of the electrons by positive electrical terminal 114, such as a cathode. Positive terminal 114 can be coupled to a conductive element 116 and configured to transport the electrons to a location downstream of plasma vortex flow 112. A negative terminal 118 such as an anode can be coupled to the other end of conductive element 116 at a downstream location, where the electrons can be re-inserted into plasma vortex flow 112 to help neutralize the charge of flow 112. A switch 120 can be coupled between conductive element 118 and controller 102. Controller 102 can be configured to receive information from one or more sensor(s) 122 regarding the characteristics of flow 112 at some downstream location, and control operation of plasma generator 104 and electromagnetic accelerator 106.
Controller 102 can operate electromagnetic accelerator 106 to provide a steady or a pulsed electric field. When a pulsed electric field is applied, a series of plasma vortices issue from an opening in cavity 110, shown as plasma vortex flow 112. The strength and/or the pulse frequency of the electric field can be varied, depending on the force required from plasma vortex flow 112.
Controller 102 is typically implemented with a processing system that can be embodied in any suitable computing device(s) using any suitable combination of firmware, software, and/or hardware, such as microprocessors, Field Programmable Gate Arrays (FPGAs), Application Specific Integrated Circuit (ASICs), or other suitable devices. Controller 102 can be coupled to a power supply (not shown) to control power supplied to plasma generator 104 and electromagnetic accelerator 106. Sensor(s) 122 can also provide information regarding the velocity, pressure, temperature, and other characteristics of flow 112 to controller 102 to operate electromagnetic accelerator 106 and plasma generator 104.
Any suitable component or combination of components can be used for controller 102, plasma generator 104, electromagnetic accelerator 106, positive terminal 114, negative terminal 118, conductor 116, and sensor(s) 122. For example, plasma generator 104 can be implemented by strong electric fields, electron beams, microwaves, and other phenomena and/or components capable of generating plasma. Electromagnetic accelerator 106 can be implemented with one or more suitable device(s) capable of generating an electrical field transverse to a magnetic field.
Housing 209 can be configured with one or more magnet devices 212 that can be operated by controller 102 to create a transverse magnetic field normal to the direction of the electric field. Electrodes 204 and magnet devices 212 together perform at least some of the functions of electromagnetic field generator 106 (
Housing 209 is open at both ends to allow flow 206 to enter one end and plasma jet 202 to exit the other end. Flow 206 can be any suitable liquid, gaseous, and/or solid substance(s) supplied from any suitable source (s). For example, flow 206 can be supplied from a secondary or auxiliary source such as a tank of compressed gas or fluid (not shown). Flow 206 can also be supplied by diverting a portion of a primary flow in addition to, or instead of, being supplied from a secondary source. Electron beams 208 can increase the ionization of flow 206, which can be supplied as a non-ionized, partially ionized, or fully ionized substance, as required.
Note that various embodiments of plasma jet systems 100 (
The ability to manipulate and control fluid flows with plasma jet systems has tremendous potential for improving system performance in diverse technological applications, including: mixing and combustion processes, boundary layer flow of aerodynamic surfaces, pressure shock stabilization, engine inlet boundary layer diversion, inlet duct secondary flow control, and thrust management, among others. Shear flow is typically receptive to small disturbances within a limited frequency band and, as a result, these disturbances are rapidly amplified and lead to substantial modification of the primary flow and the performance of the system in which it is employed.
Another embodiment of a plasma jet system 600 is shown in
In the embodiment shown, inner nozzle 604 is positioned in convergent portion 608 of shroud 606. Plasma vortex flow 614 forms a primary flow that mixes with a secondary fluid in nozzle portion 610. The efficiency of the mixing is affected by several variables such as the pulsing frequency and amplitude of plasma vortex flow 614, and the length and cross-sectional geometry of nozzle portion 610. In some embodiments, the length of nozzle portion 610 can be based on a harmonic of the frequency of plasma vortex flow 614.
Plasma jet system 600 can be used in a variety of industrial applications such as a smokestack, where it may be desirable to direct a plume of a smokestack with ejectors to drive the smoke and exhaust in a certain direction. Plasma jet system 600 can be used to pump additional mass flow in an engine, or in the ventilation or environmental control system of a machine or vehicle. In some embodiments, plasma jet system 600 can boost pumping capacity by 100% or more over a steady-state ejector, essentially doubling the pumped mass flow. Plasma jet system 600 can also be used to cool electronic equipment, as well as other devices.
In other embodiments, a series of nested plasma jet systems 600 can be included to form two or more stages of mixing. In still further embodiments, multiple plasma jet systems 600 can be included in the same stage to increase the amount of fluids that are mixed in the stage. Note that inner nozzle 604 can be configured with an open housing 202 (
Engine 700 creates thrust related to the velocity of the mass and density of the air of flow 710 over a given time period. Typically, in a jet engine, flow 710 is a subsonic flow of air until it reaches throat 704. Nozzle 708 cooperates with exit 706 to accept flow 710 from exhaust chamber 728 and to accelerate exhaust flow 710 to higher velocities, typically supersonic velocities. To achieve optimum acceleration of the exhaust flow, nozzle 708 converges the flow at throat 704, which is the point or section in nozzle 708 having the smallest cross sectional area, the constriction of throat 704 typically accelerating flow 710 to a sonic velocity, and a supersonic velocity after throat 704. Constriction of flow 710 at throat 270 operationally translates energy in flow 710 from pressure and temperature into velocity, thus creating thrust opposite to the vector of flow 710 as flow 710 exits nozzle 708. Although nozzle 708 is depicted as a fixed geometry nozzle, it should be understood that variable geometry nozzles could be incorporated in engine 700 to enhance control of the exhaust flow.
Note that pulsed plasma jets 702 are shown as zero net mass flow jets with a cavity closed at one end, similar to housing 302 shown in
In alternative embodiments, duct 752 can collect air from bypass section 714, combustion chamber 722 or any other portion of engine 750 having high-pressure air. In an alternative embodiment, a separate compressor (not shown) can provide high-pressure fluid to duct 752. Controller 102 controls operation of plasma jets 754, and the flow pressurized fluid in duct 752. One or more ducts 752 can be included to provide compressed air to two or more opposing jets 754 located in nozzle 708 and/or other portions of engine 750.
In both engines 700 and 750, plasma jets 702, 754 can be located at different positions to affect different performance parameters of engines 700, 750. Additionally, the pulse frequency and amplitude of plasma jets 702, 754 can be varied to optimize performance. For instance, referring to
When engines 700, 750 are operated at varying power settings, the energy level of flow 710 is varied by, for instance, fluctuation of the amount of fuel in combustion chamber 722. A greater energy level added to flow 710 increases the pressure and temperature in exhaust chamber 728. Typically, jet engines 700, 750 increase the cross sectional area of the nozzle when afterburner is selected. At high flow energy levels, controller 102 can direct plasma jets 802 to provide a secondary flow with decreased blockage of throat 704 to reduce pressure in exhaust chamber 728. When the energy level of flow 710 is maximized by providing fuel into exhaust chamber 728 with afterburner 730, the exhaust flow in exhaust chamber 728 can create an over-pressure which can cause a backflow through turbine section 718 and, in extreme situations, bypass chamber 714. To minimize the effects of the backpressure created in exhaust chamber 728 by initiation of afterburner 730, controller 102 can direct plasma jets 802 to provide no or just minimal blockage of throat 704, thus effectively increasing the cross sectional area of throat 704.
Plasma jets 702, 754 can be incorporated into various nozzle designs, including an axisymmetric, rectangular (2-D), elliptical, diamond, triangular shapes, and low observable RADAR and IR configurations. Plasma jets 802 can be formed as one or more slots that encompass all or portion(s) of the periphery of the nozzle 708 to provide a uniform flow along the entire slot from a single duct, or can include a number of smaller injection components within each slot that cooperate to provide a uniform flow or a flow that varies along the slot(s).
Referring now to
In some embodiments, exit area 706 is a two-dimensional rectangular nozzle configuration. The thrust-vectoring control moments are proportional to the thrust vector deflection angle and the force exerted by the vectored primary fluid flow 710.
Plasma jets 802 can generate pitch, roll, and yaw control moments by deflecting the primary flow 710 vertically and horizontally. For single nozzle configurations, vertical deflections cause pitching moments, and horizontal deflections cause yawing moments. Multiple nozzles 708 can be positioned at desired locations relative to the axes of the vehicle so that vertical deflections cause pitching moments, differential vertical deflections cause rolling moments, and horizontal deflections cause yawing moments. In some embodiments, plasma jets 802 are disposed on opposing sidewalls. In other embodiments, one or more plasma jets 802 can be formed in only one sidewall. Plasma jets 802 can be arranged in rows having the same or a different number of plasma jets 802 in each row. Groups of plasma jets 802 can be arranged in nozzle 708 to meet the requirements for a particular use.
While plasma jets 802 can be positioned at various locations on sidewalls of nozzle 708, the greatest amount of thrust vectoring is typically achieved by positioning plasma jets 802 as close to the free stream edge of exit area 706 as possible. The force exerted by plasma jets 802 is also dependent on the diameter and the pressure of plasma vortex flow from plasma jets 802. Plasma jets 802 with larger diameters and lower pressure can achieve the same overall fluid mass flow as smaller diameters with higher pressure secondary fluid flow. Any combination of number, size, and location of plasma jets 802, and rate of secondary fluid flow, can be configured to provide the desired thrust vectoring capability.
Note that plasma jets 802 can be provided in any number of sidewalls to provide maneuvering control in the desired directions. Further, secondary flow can be injected simultaneously in two or more sidewalls to effect maneuvering control in two or more directions. It should also be noted that the position of one or more of nozzles 708 on a vehicle can be selected with respect to the vehicle's center of gravity to increase or decrease the pitch, roll, and yaw moments that can be achieved with a given amount of thrust vectoring force.
The systems depicted in
Plasma jets 802 can also be used in a wide variety of other applications, including modifying the shape of aerodynamic surfaces, such as airfoils.
In operation, airfoil 1102 creates a pressure difference from a suction surface on one side of airfoil 1102 to a pressure surface on an opposite side by imposing on the fluid flow a greater curvature on the suction surface than on the pressure surface. A reduction of the efficacy of airfoil results 1102, however, when the fluid flow boundary layer separates from the suction surface. One strategy for reducing the tendency toward boundary layer separation is to inject fluid into the boundary layer through jets in the suction surface. Typically, the effectiveness of this strategy increases as the velocity of the injected fluid approaches the velocity of the bulk fluid flow.
It is anticipated that plasma jets 802 can also be used on leading and/or trailing edges of various portions of an aircraft or other device, in addition to, or instead of, conventional control surfaces, such as rudders, ailerons, flaps, elevators, among others, to control the attitude and position of the device in which plasma jets 802 are installed. For example, on an aircraft, arrays of plasma jets 802 can be positioned in both wings and operated to create higher lift on one side of the center of gravity of the aircraft than on the other. The asymmetrical lifting force will cause a rolling moment, similar to the effect of aileron deflections in a conventional aircraft. One advantage of plasma jets 802 over conventional control surfaces is the absence of hinge lines, which have a higher RADAR cross-section than plasma jets 802. Accordingly, a device that incorporates plasma jets 802 instead of conventional hinged control surfaces will be less observable with RADAR sensors.
More aft locations can also be used with plasma jets 802 pointing more directly downstream to increase lift through pressure reduction, increase L/D, delay separation and thereby increase the maximum attainable lift (CLmax), and even provide primary thrust for some applications. Differential application of plasma jets 802 can also be used to provide pitch, roll, and yaw control. Plasma jets 802 can also be used near leading and/or trailing edges to replace the conventional control surfaces.
In addition to the aerodynamic forces, acceleration or deceleration of the air flowing around an aircraft creates a direct thrust (or drag) force on the aircraft. The moment added to the air stream by plasma jets 802 can create a reaction force on the aircraft. This force can be a significant thrust on the vehicle, which can be applied symmetrically, or asymmetrically to provide additional control moments.
Referring now to
The term “pulse detonation actuator” (PDA) refers to any device or system which produces both a pressure rise and velocity increase from a series of repeating detonations or quasi-detonations within the device. A “quasi-detonation” refers to a combustion process which produces a pressure rise and velocity increase higher than the pressure rise and velocity increase produced by a deflagration wave. Typical embodiments of PDAs 1320 comprise a means of impulsively igniting a fuel/air mixture, and a detonation chamber in which pressure wave fronts initiated by the ignition process coalesce to produce a detonation wave. The geometry of the detonation chamber is such that the pressure rise of the detonation wave expels combustion products out exhaust nozzle 1350. As used herein, “impulsively detonating” refers to a process of repeating detonations or quasi-detonations wherein each detonation or quasi-detonation is initiated either by external ignition (for example, spark discharge or laser pulse) or by gas dynamic processes (for example, shock initiation or autoignition).
One way to achieve a higher exhaust velocity is to increase the speed at which the fuel is burnt. The speed is increased by introducing turbulence and enhanced mixing in PDAs 1320. Plasma jets 802 can be included in PDAs 1320 to improve the fuel-air mixture for better combustion and introduce turbulence to increase flame speed.
Lift control holes 1340 are shaped and oriented to promote attachment of the boundary layer to the surface of airfoil 1310 so that the lift force is an increasing function of the combustion product flows. In an alternative embodiment, lift control holes 1340 are shaped to promote separation of the boundary layer from the surface of airfoil 1310 so that the lift force is a decreasing function of the combustion product flows.
In some embodiments, one or more PDAs 1320 can operate out of phase with other PDAs 1320. Out of phase operation raises the frequency with which combustion product pulses are delivered to the boundary layer and, in some applications, produces a temporally more uniform boundary layer compared to operation with a single PDA 1320.
Plasma jets 802 can also be used to cool heat-producing bodies, which is a concern in many different technologies, such as integrated circuits in single- and multi-chip modules (MCMs). Additionally, either zero net mass flow plasma jets 802, and/or open cavity plasma jets 200 such as shown in
While the present disclosure describes various embodiments, these embodiments are to be understood as illustrative and do not limit the claim scope. Many variations, modifications, additions and improvements of the described embodiments are possible. For example, those having ordinary skill in the art will readily implement the processes necessary to provide the structures and methods disclosed herein. Variations and modifications of the embodiments disclosed herein may also be made while remaining within the scope of the following claims. For example, housing 109 can be formed by any suitable type of enclosure formed in independent structure as well as enclosures formed by surrounding structure(s). Additionally, any suitable component or combination of components can be used for controller 102, plasma generator 104, and electromagnetic accelerator 106 in any embodiments of plasma systems, such as systems 100 (