CN110823495A - High-speed wind tunnel dynamic wing type plasma flow control test protection device - Google Patents
High-speed wind tunnel dynamic wing type plasma flow control test protection device Download PDFInfo
- Publication number
- CN110823495A CN110823495A CN201911012281.1A CN201911012281A CN110823495A CN 110823495 A CN110823495 A CN 110823495A CN 201911012281 A CN201911012281 A CN 201911012281A CN 110823495 A CN110823495 A CN 110823495A
- Authority
- CN
- China
- Prior art keywords
- exciter
- voltage
- model
- insulation
- airfoil
- Prior art date
- Legal status (The legal status 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 status listed.)
- Pending
Links
Images
Classifications
-
- G—PHYSICS
- G01—MEASURING; TESTING
- G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
- G01M9/00—Aerodynamic testing; Arrangements in or on wind tunnels
- G01M9/02—Wind tunnels
- G01M9/04—Details
Abstract
The invention discloses a high-speed wind tunnel dynamic wing-shaped plasma flow control test protection device, which consists of a wing-shaped model, an exciter, a vibration shaft, an insulation rotating window and a sensor, wherein the exciter is arranged on the wing-shaped model; lugs at two ends of the airfoil model are fastened with the oscillating shaft through bolts, and the side end of the oscillating shaft in the downstream direction is connected with the motor shaft to drive the airfoil model to oscillate in pitch. The vibration shaft passes through the insulation rotating window, the upper electrode and the lower electrode of the plasma exciter are connected with high-voltage wires, and the positive electrode high-voltage wire and the negative electrode high-voltage wire are led out of the insulation rotating window through high-voltage wire lead grooves at the vibration shaft end. The surface of the wing is covered by a high-voltage-resistant insulating tape, so that the insulation of the surface of the wing is ensured when the plasma exciter discharges; a high-voltage-resistant insulating adhesive tape is stuck on the contact surface of the oscillating shaft and the wing-shaped lug, so that the insulation between the model and the side wall rotating window and the oscillating shaft is ensured; the sensor insulation bushing is adopted to effectively reduce the electromagnetic interference signals collected by the sensor, so that a test instrument is protected; the protection device is suitable for a high-speed wind tunnel dynamic test.
Description
Technical Field
The invention relates to the field of safety and protection of plasma flow control experiment technology in a high-speed wind tunnel, in particular to a dynamic wing-shaped plasma flow control experiment protection device for the high-speed wind tunnel.
Background
Dynamic stall is an unsteady flow separation phenomenon. Dynamic stall caused by high attack angle can appear on the backward moving blade of the rotor, dynamic stall caused by separation before shock wave induction can also appear on the forward moving blade, the dynamic stall of the helicopter rotor can cause lift force reduction, rotor shaft torque increase, consumed power increase, operation load increase, blade pitching moment change causes vibration of a torque conversion pull rod and blade flutter, and helicopter performance is reduced. Therefore, improving dynamic stall performance is critical to heavy-duty rotor systems to increase forward flight speed. In recent years, the plasma flow control technology has become a new research direction of the active flow control technology due to the advantages of short response time, no need of moving parts, wide excitation frequency band, small thickness of an exciter, small influence on the aerodynamic performance of an airfoil and the like. The technology successfully achieves the purposes of delaying separation, increasing lift force, reducing resistance and the like in a steady-state airfoil test at present, so that a plasma flow control method aiming at the problem of dynamic stall has great engineering application value.
The research on the wing-type dynamic stall plasma flow control technology at home and abroad is gradually made in recent years, the current large logarithm of wind tunnel test research mainly aims at low-speed flow with inflow less than 0.3Ma, and the wing-type aerodynamic magnitude is small under the low-speed flow condition and the requirement on the structural strength is low, so that a wing-type model made of an insulating material is generally adopted in the low-speed wing-type dynamic stall plasma flow control test, the discharge of a wing-type surface plasma exciter is easily realized, the aerodynamic force is changed violently when the wing-type has a dynamic stall phenomenon under the high-speed inflow condition, the structural strength requirement on the wing-type model is high and cannot be met by the traditional insulating material, and the high-speed wind tunnels are all-steel tunnels generally, tens of thousands of volts of high voltage needs to be applied to the wing-type exciter when the plasma discharges, and test data acquisition equipment is adopted, The test model and the wind tunnel body have larger influence, so how to realize the insulation of the wing-shaped model, the wind tunnel body and the experimental instrument when the plasma exciter discharges becomes a key problem for realizing the high-speed wind tunnel type dynamic stall plasma flow control test.
The Chinese invention patent 201410108550.5 provides a supporting and protecting device for a high-speed wind tunnel plasma flow control experiment, which solves the supporting and electromagnetic shielding problems of the plasma flow control experiment in the high-speed wind tunnel and effectively protects a test instrument; however, the device can only be applied to steady-state tests and cannot be applied to high-speed wind tunnel dynamic test devices.
Disclosure of Invention
In order to avoid the defects in the prior art, the invention provides a dynamic airfoil plasma flow control test protection device for a high-speed wind tunnel.
The technical scheme adopted by the invention for solving the technical problems is that the device comprises an exciter upper electrode, an exciter lower electrode, an airfoil model, an oscillating shaft, a positive electrode high-voltage wire, a negative electrode high-voltage wire, an insulation rotating window, a high-voltage wire lead groove, an upper electrode insulation layer, a lower electrode insulation layer and a sensor insulation bush, and is characterized in that lugs are arranged at two ends of the airfoil model, the lugs at two ends of the airfoil model are respectively matched with a middle cavity hole on the end surface of the oscillating shaft and are tightly pressed and fixed through bolts, the side end of the downstream direction of the oscillating shaft is connected with a motor output shaft through a coupler to drive the airfoil model to oscillate in a pitching manner, the oscillating shaft penetrates through the insulation rotating window, and a gap between the oscillating shaft and the insulation rotating window is smaller than 0.8mm so as to ensure;
the distance between the upper electrode of the exciter and the lower electrode of the exciter on the airfoil model along the chord length direction of the airfoil model is 1mm, a polyimide insulating tape is coated and pressed between the upper electrode of the exciter and the lower electrode of the exciter for insulation, the upper electrode of the exciter and the lower electrode of the exciter are respectively connected with an anode high-voltage lead and a cathode high-voltage lead, and the anode high-voltage lead and the cathode high-voltage lead are respectively led out of the insulating rotary window through high-voltage lead grooves on the end part of the oscillating shaft;
the lower electrode insulating layer is adhered to the surface of the airfoil model and used for insulating a lower electrode of an exciter from the airfoil model, the lower electrode of the exciter is adhered to the upper surface of the lower electrode insulating layer, the upper electrode insulating layer is adhered to the upper parts of the lower electrode insulating layer and the lower electrode of the exciter and used as a dielectric layer for plasma excitation, the upper electrode of the exciter is adhered to the upper part of the upper electrode insulating layer, the sensor insulating bush penetrates through the surface of the airfoil model and is communicated with the model cavity, and the sensor insulating bush is used for mounting a high-frequency dynamic sensor.
The upper electrode and the lower electrode of the exciter are made of copper foil insulating tapes with the thickness of 0.2mm, and the widths of the upper electrode and the lower electrode of the exciter are both 4 mm.
The high-voltage lead wire comprises a positive electrode high-voltage lead wire, a negative electrode high-voltage lead wire, a multilayer shielding high-voltage lead wire, a high-voltage-resistant lead wire, a 75 omega base band coaxial cable, a common copper net, a plastic hose and a metal snake skin hose.
The insulating rotating window structure is processed by adopting an epoxy resin material; the surface insulating layer of the airfoil model is a high-voltage-resistant insulating tape which completely covers the surface of the airfoil and the contact surface of the airfoil model and the supporting mechanism.
The inner diameter of the sensor insulation bushing is 2.33mm, the outer diameter of the sensor insulation bushing is 3.5mm, the length of the sensor insulation bushing is 8mm, and the sensor insulation bushing is used for fixing the dynamic sensor and insulating the dynamic sensor from the surface of the airfoil; the sensor lead shielding layer is a copper foil adhesive tape with 0.05mm thick and is embossed, and the copper foil adhesive tape is used for shielding electromagnetic interference on the sensor lead during plasma discharge; the grounding copper foil adopts a copper foil broadband with the width of 10cm and the thickness of 0.05mm and is used for guiding induced voltage generated by plasma discharge on a model into the ground.
Advantageous effects
The invention provides a high-speed wind tunnel dynamic wing-shaped plasma flow control test protection device which comprises a wing-shaped model, an exciter, a vibration shaft, an insulation rotating window and a sensor, wherein the exciter is arranged on the wing-shaped model; lugs at two ends of the airfoil model are fastened with the oscillating shaft through bolts, and the side end of the oscillating shaft in the downstream direction is connected with the motor transmission shaft to drive the airfoil model to oscillate in pitch. The oscillation shaft passes through the insulation rotating window, the upper electrode and the lower electrode of the plasma exciter are connected with high-voltage wires, and the positive electrode high-voltage wire and the negative electrode high-voltage wire are led out of the insulation rotating window through a high-voltage wire lead groove at the end of the oscillation shaft. Covering the surface of the wing profile by adopting a high-voltage-resistant insulating adhesive tape so as to ensure the insulation of the surface of the wing profile when the plasma exciter discharges; the insulation of the wind tunnel body is realized by adopting an insulation rotating window made of epoxy resin material; the high-voltage-resistant insulating adhesive tape is pasted on the contact surface of the oscillating shaft and the lug at the airfoil end, and the polytetrafluoroethylene lining and the gasket are assembled on the fixing screw, so that the insulation between the airfoil model and the insulating rotating window and the oscillating shaft and the insulation between the fixing screw and the lug are ensured. The induced electromagnetic field is attenuated layer by adopting a multi-layer shielding high-voltage wire, so that the requirements of safety, pressure resistance and electromagnetic shielding of a measurement and control instrument are met; the copper foil is grounded in a broadband mode, so that the induced voltage caused by the radiation of an electromagnetic field of a transmission lead is greatly reduced; the installation reliability of the sensor is ensured by adopting the dynamic sensor bush, and the insulation between the sensor and the airfoil model is also ensured; the adoption of the sensor wire shielding layer can effectively reduce the electromagnetic interference signals collected by the sensor. The protection device ensures the insulation effect between the model and the hole body and protects the test instrument; the protection device is suitable for a high-speed wind tunnel dynamic test.
Drawings
The invention further describes the high-speed wind tunnel dynamic airfoil plasma flow control test protection device in detail with reference to the accompanying drawings and the implementation mode.
FIG. 1 is a schematic view of a high-speed wind tunnel dynamic airfoil plasma flow control test protection device.
FIG. 2 is a schematic view of the installation of a model of the test guard of the present invention.
FIG. 3 is a schematic view of the leading edge of an airfoil model.
FIG. 4 is a schematic view of the oscillation axis.
FIG. 5 is a schematic view of a sensor insulator bushing.
In the drawings
1. Exciter upper electrode 2, exciter lower electrode 3, airfoil model 4, oscillating shaft 5, positive electrode high-voltage wire 6, negative electrode high-voltage wire 7, insulation rotating window 8, high-voltage wire lead groove 9, upper electrode insulation layer 10, lower electrode insulation layer 11 and sensor insulation bush
Detailed Description
The embodiment is a high-speed wind tunnel dynamic airfoil plasma flow control test protection device.
Referring to fig. 1 to 5, the dynamic wing-shaped plasma flow control test protection device for the high-speed wind tunnel in the embodiment is used for a dynamic test system of an NF-6 pressurized continuous high-speed wind tunnel, the subjects of the NF-6 pressurized continuous high-speed wind tunnel and a dynamic test mechanism are all made of steel, and when a plasma flow control test is performed, the assembly and insulation problems of a wind tunnel body, a model and a supporting mechanism of the wind tunnel body and the model must be considered, so that the electromagnetic interference of high voltage on measurement and control instruments and equipment is prevented.
The high-speed wind tunnel dynamic wing-shaped plasma flow control test protection device comprises an exciter upper electrode 1, an exciter lower electrode 2, a wing-shaped model 3, a vibration shaft 4, a positive high-voltage wire 5, a negative high-voltage wire 6, an insulation rotating window 7, a high-voltage wire lead groove 8, an upper electrode insulation layer 9, a lower electrode insulation layer 10 and a sensor insulation bush 11; wherein, airfoil model 3 both ends are equipped with the lug, and 3 end lugs of airfoil model stretch into respectively and compress tightly fixedly through the bolt in the oscillating shaft cavity. The side end of the oscillating shaft 4 in the downstream direction is connected with the output shaft of the motor to drive the airfoil model 3 to perform pitching oscillation. The oscillating shaft 4 penetrates through the insulation rotating window 7, and a gap between the oscillating shaft 4 and the insulation rotating window 7 is smaller than 0.8mm, so that the oscillating shaft is prevented from being scratched with the insulation rotating window in high-frequency oscillation motion. The exciter upper electrode 1 and the exciter lower electrode 2 are positioned on the airfoil model 3, and the distance along the chord length direction of the airfoil model 3 is 1 mm. The upper electrode 1 and the lower electrode 2 of the exciter are copper foil insulating tapes with the thickness of 0.2mm, and the electrode widths are both 4 mm; the exciter upper electrode 1 and the exciter lower electrode 2 are insulated by a layer of polyimide insulating tape. The exciter upper electrode 1 and the exciter lower electrode 2 are respectively connected with the anode high-voltage wire 5 and the cathode high-voltage wire 6, and the anode high-voltage wire 5 and the cathode high-voltage wire 6 are respectively led out from the insulation rotary window 7 through a high-voltage wire lead groove 8 at the end part of the oscillating shaft. The positive electrode high-voltage lead 5 and the negative electrode high-voltage lead 6 are used for transmitting excitation voltage in a plasma flow control experiment, and the multilayer shielding high-voltage lead sequentially comprises a high-voltage-resistant lead, a 75 omega base band coaxial cable, a common copper net, a plastic hose and a metal snake skin hose from inside to outside; the multilayer shielded high voltage wire is used for transmitting an excitation voltage in a plasma flow control experiment. The lower electrode insulating layer 10 is pasted on the surface of the airfoil model and used for insulating the exciter lower electrode 2 from the airfoil model 3, and the exciter lower electrode 2 is pasted above the lower electrode insulating layer 10. An upper electrode insulating layer 9 is attached above a lower electrode insulating layer 10 and an exciter lower electrode 2 and serves as a plasma excitation dielectric layer, an exciter upper electrode 1 is attached above the upper electrode insulating layer 9, and a sensor insulating bush 11 penetrates through the surface of the airfoil and is communicated with the atmosphere and the cavity of the airfoil model 3 and used for mounting a high-frequency dynamic sensor.
In the embodiment, the insulating rotating window structure is made of epoxy resin material; the gap between the oscillating shaft 4 and the insulating rotating window 7 is smaller than 0.8mm, so that the oscillating shaft is ensured not to rub against the insulating rotating window in high-frequency oscillation motion, air tightness between the oscillating shaft and the insulating rotating window is also ensured, if large-scale air leakage occurs, binary characteristics of a wing test are influenced, and authenticity and reliability of test data are reduced. The airfoil surface insulating layer is a high-voltage-resistant insulating tape and completely covers the airfoil surface and the contact surface of the airfoil and the supporting mechanism.
In the embodiment, the dynamic sensor is made of metal, the requirement on the electromagnetic environment is extremely high, insulation treatment is required, the sensor bushing is made of polytetrafluoroethylene, the effect of wrapping and fastening the sensor can be achieved while insulation between the sensor bushing and the airfoil model is guaranteed, the inner diameter of the dynamic sensor insulation bushing is 2.33mm, the outer diameter of the dynamic sensor insulation bushing is 3.5mm, the length of the dynamic sensor insulation bushing is 8mm, the tolerance of the inner diameter is-0.1 mm, and the tolerance of the outer diameter is +0.1 mm; after the sensor is installed, the part of the bushing extending out of the surface of the airfoil needs to be flattened, and the bushing is ensured to be flush with the surface of the airfoil. The sensor lead shielding layer is a copper foil adhesive tape with embossing and the thickness of 0.05mm and is used for shielding electromagnetic interference to the sensor lead during plasma discharge. The grounding copper foil broadband is 10cm wide and 0.05mm thick and is used for guiding induced voltage generated by plasma discharge on the model into the ground.
Claims (5)
1. A high-speed wind tunnel dynamic wing-shaped plasma flow control test protection device comprises an exciter upper electrode, an exciter lower electrode, a wing-shaped model, a vibration shaft, a positive electrode high-voltage wire, a negative electrode high-voltage wire, an insulation rotating window, a high-voltage wire lead groove, an upper electrode insulation layer, a lower electrode insulation layer and a sensor insulation bush, and is characterized in that lugs are arranged at two ends of the wing-shaped model, the lugs at two ends of the wing-shaped model are respectively matched with a middle cavity hole in the end face of the vibration shaft and are compressed and fixed through a bolt, the side end of the downstream direction of the vibration shaft is connected with a motor output shaft through a coupler to drive the wing-shaped model to perform pitching oscillation, the vibration shaft penetrates through the insulation rotating window, and a gap between the vibration shaft and the insulation rotating window is smaller than 0.8 mm;
the distance between the upper electrode of the exciter and the lower electrode of the exciter on the airfoil model along the chord length direction of the airfoil model is 1mm, a polyimide insulating tape is coated and pressed between the upper electrode of the exciter and the lower electrode of the exciter for insulation, the upper electrode of the exciter and the lower electrode of the exciter are respectively connected with an anode high-voltage lead and a cathode high-voltage lead, and the anode high-voltage lead and the cathode high-voltage lead are respectively led out of the insulating rotary window through high-voltage lead grooves on the end part of the oscillating shaft;
the lower electrode insulating layer is adhered to the surface of the airfoil model and used for insulating a lower electrode of an exciter from the airfoil model, the lower electrode of the exciter is adhered to the upper surface of the lower electrode insulating layer, the upper electrode insulating layer is adhered to the upper parts of the lower electrode insulating layer and the lower electrode of the exciter and used as a dielectric layer for plasma excitation, the upper electrode of the exciter is adhered to the upper part of the upper electrode insulating layer, the sensor insulating bush penetrates through the surface of the airfoil model and is communicated with the model cavity, and the sensor insulating bush is used for mounting a high-frequency dynamic sensor.
2. The high-speed wind tunnel dynamic airfoil plasma flow control test protection device according to claim 1, wherein the upper electrode and the lower electrode of the exciter are copper foil insulating tapes with the thickness of 0.2mm, and the widths of the upper electrode and the lower electrode of the exciter are both 4 mm.
3. The high-speed wind tunnel dynamic wing type plasma flow control test protection device according to claim 1, wherein the positive electrode high-voltage lead and the negative electrode high-voltage lead are used for transmitting excitation voltage in a plasma flow control test, and the multilayer shielding high-voltage lead sequentially comprises a high-voltage-resistant lead, a 75 omega baseband coaxial cable, a common copper netting, a plastic hose and a metal snakeskin hose from inside to outside.
4. The high-speed wind tunnel dynamic airfoil plasma flow control test protection device according to claim 1, wherein the insulation rotating window structure is processed by epoxy resin material; the surface insulating layer of the airfoil model is a high-voltage-resistant insulating tape which completely covers the surface of the airfoil and the contact surface of the airfoil model and the supporting mechanism.
5. The high-speed wind tunnel dynamic airfoil plasma flow control test protection device according to claim 1, wherein the sensor insulation bushing has an inner diameter of 2.33mm, an outer diameter of 3.5mm and a length of 8mm, and is used for fixing the dynamic sensor and insulating the dynamic sensor from the surface of an airfoil; the sensor lead shielding layer is a copper foil adhesive tape with 0.05mm thick and is embossed, and the copper foil adhesive tape is used for shielding electromagnetic interference on the sensor lead during plasma discharge; the grounding copper foil adopts a copper foil broadband with the width of 10cm and the thickness of 0.05mm and is used for guiding induced voltage generated by plasma discharge on a model into the ground.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201911012281.1A CN110823495A (en) | 2019-10-23 | 2019-10-23 | High-speed wind tunnel dynamic wing type plasma flow control test protection device |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201911012281.1A CN110823495A (en) | 2019-10-23 | 2019-10-23 | High-speed wind tunnel dynamic wing type plasma flow control test protection device |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN110823495A true CN110823495A (en) | 2020-02-21 |
Family
ID=69550274
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201911012281.1A Pending CN110823495A (en) | 2019-10-23 | 2019-10-23 | High-speed wind tunnel dynamic wing type plasma flow control test protection device |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN110823495A (en) |
-
2019
- 2019-10-23 CN CN201911012281.1A patent/CN110823495A/en active Pending
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| US10280896B2 (en) | Lightning protection system for a wind turbine blade | |
| US10844843B2 (en) | Wind turbine blade and wind turbine power generating apparatus, and method of producing or retrofitting wind turbine blade | |
| EP2122162B1 (en) | Wind turbine rotor blade and method of manufacturing such rotor blade | |
| US20080095624A1 (en) | Lightning protection of wind turbines | |
| EP2510229B1 (en) | Wind turbine with a lightning protection system | |
| CN101008374B (en) | Systems and methods for directing a current | |
| EP2522859B1 (en) | Voltage application device and rotation apparatus | |
| CN108266335A (en) | A kind of wind power plant blade lightning protection device | |
| CN101936264A (en) | The cross conduction lightning conductor system | |
| JP6209211B2 (en) | Wind turbine blade lightning bypass system | |
| EP3615791B1 (en) | Wind turbine blade and wind turbine power generating apparatus | |
| CN102661240A (en) | Wind wheel vane anti-lightning device for wind generating set and mounting method thereof | |
| CN106762389A (en) | Blade tip, blade of wind generating set and blade tip installation method | |
| CN207701299U (en) | A kind of breakdown prevention type wind electricity blade lightning arrester | |
| CN211042650U (en) | High-speed wind tunnel dynamic wing type plasma flow control test protection device | |
| CN110823495A (en) | High-speed wind tunnel dynamic wing type plasma flow control test protection device | |
| WO2012153717A1 (en) | Windmill | |
| US11933265B2 (en) | Wind turbine blade assembly and method for manufacturing | |
| CN107956656A (en) | A kind of wind power generation unit blade lightning protection connects sudden strain of a muscle system | |
| CN108223306B (en) | Lightning protection lightning receiving device externally covered on surface of wind turbine generator blade | |
| US11118571B2 (en) | Lightning protection arrangement | |
| US10900468B2 (en) | Wind turbine blade protection structure and method of forming the same | |
| EP3667684A1 (en) | Electrical bushing | |
| CN108223305B (en) | Electrode lightning receiving device for wind turbine generator blade | |
| KR101756748B1 (en) | Airflow generation device and wind power generation system |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination |