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WO2008136698A1 - Procédé et appareil pour une régulation de débit électrohydrodynamique efficace d'un gaz - Google Patents

Procédé et appareil pour une régulation de débit électrohydrodynamique efficace d'un gaz Download PDF

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Publication number
WO2008136698A1
WO2008136698A1 PCT/RU2007/000225 RU2007000225W WO2008136698A1 WO 2008136698 A1 WO2008136698 A1 WO 2008136698A1 RU 2007000225 W RU2007000225 W RU 2007000225W WO 2008136698 A1 WO2008136698 A1 WO 2008136698A1
Authority
WO
WIPO (PCT)
Prior art keywords
discharge
gas discharge
voltage
electrode
gas
Prior art date
Application number
PCT/RU2007/000225
Other languages
English (en)
Inventor
Thomas Hammer
Andrey Mikhailovich Bartenev
Original Assignee
Siemens Aktiengesellschaft
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by Siemens Aktiengesellschaft filed Critical Siemens Aktiengesellschaft
Priority to PCT/RU2007/000225 priority Critical patent/WO2008136698A1/fr
Publication of WO2008136698A1 publication Critical patent/WO2008136698A1/fr

Links

Classifications

    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C23/00—Influencing air flow over aircraft surfaces, not otherwise provided for
    • B64C23/005—Influencing air flow over aircraft surfaces, not otherwise provided for by other means not covered by groups B64C23/02 - B64C23/08, e.g. by electric charges, magnetic panels, piezoelectric elements, static charges or ultrasounds
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/12—Blades
    • F01D5/14—Form or construction
    • F01D5/141—Shape, i.e. outer, aerodynamic form
    • F01D5/145—Means for influencing boundary layers or secondary circulations
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/12—Blades
    • F01D5/14—Form or construction
    • F01D5/147—Construction, i.e. structural features, e.g. of weight-saving hollow blades
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F15—FLUID-PRESSURE ACTUATORS; HYDRAULICS OR PNEUMATICS IN GENERAL
    • F15D—FLUID DYNAMICS, i.e. METHODS OR MEANS FOR INFLUENCING THE FLOW OF GASES OR LIQUIDS
    • F15D1/00—Influencing flow of fluids
    • F15D1/10—Influencing flow of fluids around bodies of solid material
    • F15D1/12—Influencing flow of fluids around bodies of solid material by influencing the boundary layer
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2270/00—Control
    • F05D2270/01—Purpose of the control system
    • F05D2270/17—Purpose of the control system to control boundary layer
    • F05D2270/172—Purpose of the control system to control boundary layer by a plasma generator, e.g. control of ignition
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
    • Y02T50/00—Aeronautics or air transport
    • Y02T50/60—Efficient propulsion technologies, e.g. for aircraft

Definitions

  • the invention is related to a method for an efficient Electrohydrodynamic flow control of gases and an apparatus therefore.
  • the invention is used in known turbo-machines or other devices .
  • Turbo-machines such as compressors or turbines are optimized for certain operation conditions characterized by thermal and transport properties of the gas mixture applied (density, specific heat, viscosity, heat conductivity) , temperature, and mass flow. If turbo-machines are operated at other than the optimum operation conditions, the efficiency decreases, and even under optimized operation conditions some inherent losses cannot be avoided: Mixing losses occur due to mixing of the flow fields at the trailing edge of a turbine blade caused by the velocity difference between pressure side and suction side of the turbine blade profile. The shear stresses in the boundary layers generate boundary layer losses. In the worst case boundary layer separation may occur. Other losses are clearance gap losses at rotating blades and end-wall losses, which may also occur at the stator. Further due to interactions between rows of blades (wake formation) cascade losses are generated.
  • turbo-machinery Another problem related to turbo-machinery is heat transfer, especially at the vanes and blades of gas turbines exposed to high temperature gas flows.
  • film cooling is utilized in order to protect the surface from overheating, which again is optimized for a certain range of operation conditions.
  • Turbo-machines for industrial application such as electric power plants are characterized by high mass-flow densities and high energy densities and therefore often operate at atmospheric pressure and above.
  • Electro-hydrodynamic flow control is based on momentum transfer of charged particles accelerated in an electric field to the surrounding neutral gas, which e.g. under certain conditions forms the so-called ionic wind.
  • the actuators suggested in this application are either based on dielectric barrier discharges (DBD) known from ozonizers or on DC-Corona discharges (DC-CD) known from electrostatic precipitators .
  • DBD dielectric barrier discharges
  • DC-CD DC-Corona discharges
  • the electric field at the dielectric barrier needs to be below the dielectric breakdown field, and thus the charge transferred per half cycle of the applied AC-voltage (or per pulse in the case of a pulsed DBD) is limited to:
  • Q E bmax x d b x C b (1)
  • Ebmax is a maximum electric field below the breakdown limit of the barrier material
  • d b is the thickness of the barrier material
  • C b is the capacity of the dielectric barrier.
  • the barrier capacity is given by: with the relative permittivity of the barrier material ⁇ b , the vacuum permittivity ⁇ 0 , the surface area of the barrier Ab.
  • the maximum charge transferred per half cycle cannot be influenced by the thickness of the barrier material .
  • the DC-CD can be operated at large reduced discharge gaps of some 100 mm x bar, however, the power density which can be achieved without sparking is much lower than that of a DBD .
  • the invention is defined by a method with the steps of claim 1.
  • An apparatus is defined in claim 11. Further realisations of the inventive method and the related apparatus are given by the dependent claims .
  • Finally claim 21 to 25 give preferred uses of the inventive method and apparatus in a turbine and other devices .
  • Object of the invention is the electrohydrodynamic actuation of a gas flow by means of EHD-actuator, which other than the DC-CD or the DBD-actuator makes use of separately controlled ion formation in an electrical gas discharge and momentum transfer to the gas flow in an ion drift zone.
  • EHD-actuator transfers momentum and energy much more efficiently to the gas flow than a DBD- or a DC-CD-actuator.
  • the basic idea of the invention is that in a first step in a limited volume being substantially smaller than the volume of interest for EHD-actuation large electron-ion pair densities are generated efficiently by means of a very short gas discharge pulse, which is characterized by an electric field exceeding the gas discharge breakdown value substantially.
  • a second step following charge generation an electric field is generated by means of an electrode structure consisting of at least one anode and one cathode in the complete volume of interest for EHD-actuation, whereby the electric field is large enough to separate the electron-ion pairs and to force the electrons to drift to the anode (s) and the ions to drift to the cathode (s) of the electric field generating electrode structure without causing spark-formation between the electrodes.
  • the electric field in the second step is kept below the gas discharge breakdown limit of the electrode structure.
  • the second step can be considered as a non self-sustained gas discharge.
  • the current invention combines the advantage of a short time, small volume gas discharge plasma, that charges can be generated very efficiently at a high density, with the advantage of a DC-corona or a non self-sustained gas discharge, that charges can be transported over a large distance.
  • the invention allows to build turbines and heat exchangers more compact, because the improved properties of the boundary layer, e.g. at the surface of a turbine blade, allow to reduce the number of stages of a gas turbine or of an axial compressor. More advantages and details of the invention are given in the description of preferred embodiments in respect to the drawings. There is shown schematically:
  • Figure 1 the method performed in a set-up for direct electrical gas discharge generation between two electrode tips and a third wire electrode for charge separation and momentum transfer
  • Figure 2 the method performed in a set-up for direct electrical gas discharge generation between parallel wire electrodes and a third wire electrode for charge separation and momentum transfer
  • Figure 3 the method performed in a set-up for dielectric barrier discharge generation between two electrode tips and a third wire electrode for charge separation and momentum transfer, and an enlarged view of the electrode set-up for DBD-generation in figure 3A,
  • Figure 4 the method performed in a set-up for dielectric barrier discharge generation between two parallel wire electrodes and a third wire electrode for charge separation and momentum transfer
  • Figure 5 a view onto a wall including four electrodes for generating the discharge region and a drift region respectively
  • Figure 6 the cross section of the set-up of Figure 5
  • Figure 7 - a first graph presenting the voltages over time applied to the electrodes of the electrical gas discharge and to the ion extracting cathode, respectively
  • Figure 8 - a second graph presenting the voltages over time applied to the electrodes of the electrical gas discharge and to the ion extracting cathode, respectively
  • Figure 9, 10 the use of the embodiments of one of the figures 1 to 8 to the blade of an axial compressor or of a turbine,
  • Figure 11 the use of printed electrodes on an insulating film of an conductive body
  • FIG 12, 13 the use of the embodiments of one of the figures 1 to 8 to a heat exchanger.
  • figure 1 there are two electrodes, a first electrode 1 and a second electrode 2 which are supplied by a high voltage source 11 with a time dependent voltage Ui (t) .
  • the voltage amplitude Ui 0 is set such that between the electrode tips a self-sustained electrical gas discharge plasma is generated. If d g is the gap between the electrode tips and n gas is the number density of the gas molecules filling the discharge gap, then preferred values of the reduced electric field being approximated by
  • Eav/n gas U 10 / (n g as x d g ) (4.1) are in the range of IxIO "19 Vm 2 to 5xlO '19 Vm 2 .
  • the region 5 between the electrodes 1 and 2 is called “discharge region” .
  • electrode 3 In a certain distance da r to the opposed electrode tips there is a third, linearly extended electrode 3 supplied by a voltage source 12 with another time dependent voltage U 2 (t) normally having a negative polarity.
  • electrode 3 normally is a cathode.
  • the voltage amplitude U 2O is set such that it causes separation of the charges generated in the discharge region 5, and drift of the positive ions with an electrical current 7 to the cathode without generating a self-sustained gas discharge.
  • the region 6 between the electrodes 1/2 and the electrode 3 is called “drift region" .
  • Preferred values of the reduced electric field in the drift region 6 being approximated by E av /n gas U 20 / (n gas x d dr ) (4.2) are in the range of IxIO "20 Vm 2 to IxIO "19 Vm 2 .
  • the discharge region 5 and the drift region 5 being in direct contact to the discharge region 5 are well defined by the placement of the electrodes 1, 2 and 3, and that the gas discharge generation in the discharge region 5 and the momentum transfer to the gas flow by means of ion drift in the drift region 6 are controlled separately with respect to reduced electric field and time by different voltages Ui (t) an U 2 (t) .
  • the shape of the electrode tips 1, 2 may be arbitrary. They may be rounded or sharp edged and can simply be formed by cut wires or thin rods mounted with insulating clamps, by pasting thin conductive foils pasted on an insulating surface, or by conductive layers printed on an insulating surface using conductive ink.
  • the electrical gas discharge plasma generating means of figure 1 are changed in that way that the first and the second electrode 21 and 22 are parallel wires, strips, or rods extending over a certain length being substantially larger than the discharge gap between the electrodes.
  • the discharge region 5 located between the electrodes 21 and 22 is a linear source of ions supplied to the drift region 6.
  • this set-up is advantageous if a gas flow needs to be controlled near to a wide surface such as a wing of an airplane or a turbine blade .
  • FIG 3 the electrical gas discharge plasma generating means of figure 1 are changed in that way that a dielectric barrier discharge (DBD) is generated in the discharge region 5.
  • Electrode 31 has a coating 34 of a dielectric material acting as a dielectric barrier, whereas electrode 32 is uncoated. Details of the DBD-electrode setup are shown in the enlarged view of figure 3A. Electrode 32 is connected to ground and for the charge separation thus acts as the anode, the cathode 33 being connected to the voltage supply 12 is the same as in figure 1.
  • the advantage of this set-up compared to that shown in figure 1 is that more intense electrical gas discharge plasmas can be formed without the risk of sparking. Thus larger ion currents can be supplied to the drift region, resulting in a larger momentum transfer.
  • Electrode 41 has a coating 44, whereas electrode 42 is uncoated. Again electrode 42 and cathode 43 define the drift region 10 being much wider than that generated by the set-up given in figure 3. Compared to the set-up in figure 2 more intense gas discharge plasmas can be formed without the risk of sparking. Thus larger ion currents can be supplied to the drift region, resulting in a larger momentum transfer.
  • FIG 5A and figure 5B a device with four electrodes applied to a surface is shown.
  • a wall 50 of electrically insulating material acting as a dielectric barrier into which flat, stripe-shaped gas discharge electrodes 51 and 52 are embedded.
  • the electrodes 51 and 52 are connected to the voltage-source 11 supplying U x (t).
  • the voltage-source 12 supplying U 2 (t) is connected to the electrodes 53 and 54.
  • the electrodes are placed such that the discharge region 5 and the drift region 6 overlap with the discharge region being near to the anode (53) side of the drift region.
  • the time interval between two high-voltage pulses or wave packages usually is long compared to the duration of the high-voltage pulses or wave packages .
  • Preferred values for the duration of the high-voltage pulses are in the range of 1 ns to 10 ⁇ s, whereas the duration of wave packages has preferred values ranging from 10 ns to 100 ⁇ s .
  • Preferred values for the intervals between pulses or wave packages range from 10 ⁇ s to 10 ms .
  • the described method and apparatuses can be used in gas turbines, whereby gas flow induced losses at turbine blades are reduced or also in steam turbines, whereby gas flow induced losses at turbine blades are reduced.
  • Another use is in an axial compressor, whereby gas flow induced losses at compressor blades are reduced. Also in wings boundary layer separation is suppressed.
  • FIG 9 and figure 10 the gas flow around the blade of an axial compressor or of a turbine is shown. Without EHD-actuation in figure 9 mixing-losses occur, because at the trailing edge of the blade the flow velocities from the pressure- and from the suction-side of the profile are different.
  • Figure 10 shows the blade 90 of figure 9 with means for EHD-actuation. Due to momentum transfer to the boundary layer gas flow on the suction side of the profile mixing losses are avoided. In the same way boundary layer separation can also be avoided.
  • FIG 11 an example of an electrode set-up attached to a conductive body 105 is presented.
  • a first insulating layer 110 is prepared e.g. by plasma spraying of alumina in the region where the EHD-actuator shall be placed.
  • At least one discharge electrode 111 is prepared by pasting a thin metal foil or printing a conductive pattern on top of that layer 110. Then this layer 110 carrying electrode structures is covered by another insulating layer 110', on top of which two electrodes 112 and 113 are prepared in the same way as the electrode 111.
  • Electrode 112 is connected to ground and works both for discharge generation and drift activation.
  • FIG 12 there is presented a heat exchanger with tubes 120 and a structure of separation parts 130. The gas flows around the tubes 120. Because of the boundary layer separation the heat transfer may be inefficient.
  • Figure 13 shows the tubular heat exchanger with means for EHD- actuation included. There are two electrodes 121, 122 and a voltage power supply 125 for AC and a voltage power supply 125 for DC.
  • the tubes 120 of the heat exchanger are metallic, and the structure 130 carrying the tubes 130 is insulating or has an insulating surface. Due to EHD-actuation at the surface of the structure carrying the tubes re-attachment of the gas-flow to the tube-surface is achieved. Thus the heat transfer is improved, and the heat-exchanger can be built more compact.
  • the gas discharge required for generation of electron- ion pairs in a limited volume can be excited periodically by application of a pulsed DC-voltage or of a short high- frequency voltage pulse U 1 Ct) to a pair of electrodes with electrode 1 and electrode 2 generating the electric field required for gas discharge breakdown in this limited volume (e.g. "discharge region"), only.
  • pulsed DC- voltage this may either be a pulsed corona discharge or a pulsed dielectric barrier discharge.
  • the barrier discharge may be formed either as a volume discharge or as a surface discharge .
  • this may also be a dielectric barrier discharge, or it may be a capacitively coupled radio-frequency discharge, which is distinguished from the dielectric barrier discharge in that the surface charging of the barrier material is not essential for the gas discharge characteristics.
  • the dielectric breakdown of the barrier material is no longer a limiting factor to the power density.
  • DC-voltage will be controlled such that the efficiency of ion generation is maximized. If the reduced electric field is near to the value required for gas discharge breakdown, electronic loss mechanism such as vibrational and electronic excitation of molecules will prevail, and if the reduced electric field is more than five times of the gas discharge breakdown value, the efficiency of ionization as a function of the plasma input energy per pulse will saturate, however, the efficiency of the power coupling between electric power supply and electrical gas discharge will drop drastically. Thus the product of these efficiencies will maximize at a certain reduced electric field value.
  • the duration of the electrical gas discharge pulse is of importance for the efficiency of ion generation: At the beginning of each pulse the ion density in the gas discharge region will increase exponentially as a function of time because ions are generated due to electron collision ionization at a rate being proportional to the electron (or ion) number density and a rate coefficient depending on the reduced electric field. Since ion losses are caused by ion drift and diffusion to surfaces, especially to the electrodes, and by ion-electron recombination, an increase of the ion loss rate with increasing ion number density can be assumed. Thus after some time a quasi-steady state ion concentration would be achieved resulting in an increase of energy consumption without any increase in ion density if too long pulses were applied.
  • the optimum pulse duration is reached when the ion density approaches 50-70 % of its saturation value which of course depends on the reduced electric field in the discharge gap.
  • the voltage U 2 (t) driving the drift in the second step may be applied as a DC-voltage all the time, or it may be a time-dependent voltage being switched on after the gas discharge voltage of the first step has been switched off and being switched off before the gas discharge voltage is been switched on. In the case of time dependence this voltage may be bipolar, as long as by some means such as the design of the electrode arrangement or by the time- dependence of the voltage itself a predominant ion-flow direction is achieved.
  • the duration of the drift voltage pulse being only slightly smaller than the period between two gas discharge pulses should be such that most of the ions are removed from the gas discharge region. However, a small fraction of the electrons and ions may remain in the gas discharge region in order to facilitate ionization in the next gas discharge pulse. This fraction is preferably between 0.01 % and 1 % of the maximum ion density.
  • the preferred case is that of a unipolar applied voltage.
  • the drift may be along a surface, it may, however, be also a drift between electrodes placed somewhere in the volume of interest. Further the direction of the electric field causing the drift may include any angle with the direction of the electric field applied to the gas discharge.
  • the gas discharge may especially be perpendicular as shown in Figures 1 and 3 , or it may be parallel as shown in Figures 2, 4, 5, 8, 9, and 10 respectively. Normally it is not bordered exactly and can be frayed in respect to the geometry of the electrodes.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Physics & Mathematics (AREA)
  • Fluid Mechanics (AREA)
  • Architecture (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Physical Or Chemical Processes And Apparatus (AREA)

Abstract

L'invention concerne un procédé destiné à la régulation de débit d'un gaz au moyen de l'électrohydrodynamique (EHD) actionnant le débit, l'actionnement EHD générant une petite zone de décharge discrète et une zone de dérive plus importante respectivement, qui sont toutes deux commandées indépendamment en termes de temps et en termes d'emplacements (lieux). L'invention concerne également un appareil utilisé pour ce procédé, comprenant des moyens pour une décharge à barrière diélectrique (DBD), qui présente au moins trois électrodes (1-3), une première tension (U1(t)) entre les première et deuxième électrodes (1, 2) générant une zone de décharge et une seconde tension (U2(t)) entre la deuxième et une troisième électrode (2, 3) générant une zone de dérive (10).
PCT/RU2007/000225 2007-05-04 2007-05-04 Procédé et appareil pour une régulation de débit électrohydrodynamique efficace d'un gaz WO2008136698A1 (fr)

Priority Applications (1)

Application Number Priority Date Filing Date Title
PCT/RU2007/000225 WO2008136698A1 (fr) 2007-05-04 2007-05-04 Procédé et appareil pour une régulation de débit électrohydrodynamique efficace d'un gaz

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Application Number Priority Date Filing Date Title
PCT/RU2007/000225 WO2008136698A1 (fr) 2007-05-04 2007-05-04 Procédé et appareil pour une régulation de débit électrohydrodynamique efficace d'un gaz

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WO2008136698A1 true WO2008136698A1 (fr) 2008-11-13

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Cited By (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN102056392A (zh) * 2010-12-17 2011-05-11 中国科学技术大学 一种高气压放电产生冷等离子体的方法及介质阻挡放电装置
US8881527B2 (en) 2012-04-30 2014-11-11 General Electric Company Systems and methods for generating electricity
CN104185354A (zh) * 2014-04-10 2014-12-03 中国商用飞机有限责任公司北京民用飞机技术研究中心 介质阻挡放电等离子体激励器及系统
EP2963241A1 (fr) * 2014-06-30 2016-01-06 Techspace Aero S.A. Élément de guidage de flux gazeux de turbomachine
WO2020247031A1 (fr) 2019-06-07 2020-12-10 Massachusetts Institute Of Technology Dispositifs électroaérodynamiques
US20220063821A1 (en) * 2020-08-27 2022-03-03 William J. Cass Ionic propulsion system

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US3956666A (en) * 1975-01-27 1976-05-11 Ion Tech, Inc. Electron-bombardment ion sources
US4643745A (en) * 1983-12-20 1987-02-17 Nippon Soken, Inc. Air cleaner using ionic wind
EP0426110A2 (fr) * 1989-10-31 1991-05-08 Nec Corporation Propulsion ionique pour mission dans l'espace interplanétaire
WO2002081304A1 (fr) * 2001-04-06 2002-10-17 Bae Systems Plc Reduction de la trainee d'un ecoulement turbulent
US20060038087A1 (en) * 2004-07-21 2006-02-23 Minick Alan B Wing enhancement through ion entrainment of media

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US3956666A (en) * 1975-01-27 1976-05-11 Ion Tech, Inc. Electron-bombardment ion sources
US4643745A (en) * 1983-12-20 1987-02-17 Nippon Soken, Inc. Air cleaner using ionic wind
EP0426110A2 (fr) * 1989-10-31 1991-05-08 Nec Corporation Propulsion ionique pour mission dans l'espace interplanétaire
WO2002081304A1 (fr) * 2001-04-06 2002-10-17 Bae Systems Plc Reduction de la trainee d'un ecoulement turbulent
US20060038087A1 (en) * 2004-07-21 2006-02-23 Minick Alan B Wing enhancement through ion entrainment of media

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Title
J. PONS, E. MOREAU, G. TOUCHARD: "asymmetric surface dielectric barrier discharge in air at atmospheric pressure: electrical properties and induced airflow characteristics", JOURNAL OF PHYSICS D : APPLIED PHYSICS, no. 38, 16 September 2005 (2005-09-16), United Kingdom, pages 3635 - 3642, XP002473884 *

Cited By (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN102056392A (zh) * 2010-12-17 2011-05-11 中国科学技术大学 一种高气压放电产生冷等离子体的方法及介质阻挡放电装置
US8881527B2 (en) 2012-04-30 2014-11-11 General Electric Company Systems and methods for generating electricity
CN104185354A (zh) * 2014-04-10 2014-12-03 中国商用飞机有限责任公司北京民用飞机技术研究中心 介质阻挡放电等离子体激励器及系统
EP2963241A1 (fr) * 2014-06-30 2016-01-06 Techspace Aero S.A. Élément de guidage de flux gazeux de turbomachine
US10132188B2 (en) 2014-06-30 2018-11-20 Safran Aero Boosters Sa Axial turbomachine compressor inner shell
WO2020247031A1 (fr) 2019-06-07 2020-12-10 Massachusetts Institute Of Technology Dispositifs électroaérodynamiques
EP3980332A4 (fr) * 2019-06-07 2023-06-14 Massachusetts Institute of Technology Dispositifs électroaérodynamiques
US11725638B2 (en) 2019-06-07 2023-08-15 Massachusetts Institute Of Technology Electroaerodynamic devices
US20220063821A1 (en) * 2020-08-27 2022-03-03 William J. Cass Ionic propulsion system

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