CN114872904B - Method and device for controlling shock wave induced separation in air inlet channel for local particle delivery - Google Patents
Method and device for controlling shock wave induced separation in air inlet channel for local particle delivery Download PDFInfo
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- CN114872904B CN114872904B CN202210538518.5A CN202210538518A CN114872904B CN 114872904 B CN114872904 B CN 114872904B CN 202210538518 A CN202210538518 A CN 202210538518A CN 114872904 B CN114872904 B CN 114872904B
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- particle
- air inlet
- inlet channel
- shock wave
- solid particles
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- 239000002245 particle Substances 0.000 title claims abstract description 123
- 238000000926 separation method Methods 0.000 title claims abstract description 41
- 230000035939 shock Effects 0.000 title claims abstract description 37
- 238000000034 method Methods 0.000 title claims abstract description 22
- 239000007787 solid Substances 0.000 claims abstract description 30
- 230000000694 effects Effects 0.000 claims abstract description 13
- 238000011144 upstream manufacturing Methods 0.000 claims abstract description 11
- 230000006835 compression Effects 0.000 claims description 16
- 238000007906 compression Methods 0.000 claims description 16
- 238000002347 injection Methods 0.000 claims description 3
- 239000007924 injection Substances 0.000 claims description 3
- ZOXJGFHDIHLPTG-UHFFFAOYSA-N Boron Chemical compound [B] ZOXJGFHDIHLPTG-UHFFFAOYSA-N 0.000 claims description 2
- XAGFODPZIPBFFR-UHFFFAOYSA-N aluminium Chemical compound [Al] XAGFODPZIPBFFR-UHFFFAOYSA-N 0.000 claims description 2
- 229910052782 aluminium Inorganic materials 0.000 claims description 2
- 229910052796 boron Inorganic materials 0.000 claims description 2
- 238000004891 communication Methods 0.000 claims description 2
- 238000007789 sealing Methods 0.000 claims description 2
- 239000004449 solid propellant Substances 0.000 claims description 2
- 239000000463 material Substances 0.000 claims 1
- 239000012530 fluid Substances 0.000 abstract description 12
- 238000004088 simulation Methods 0.000 description 4
- 239000002243 precursor Substances 0.000 description 3
- 238000010586 diagram Methods 0.000 description 2
- 230000001133 acceleration Effects 0.000 description 1
- 238000013459 approach Methods 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 238000007796 conventional method Methods 0.000 description 1
- 238000001816 cooling Methods 0.000 description 1
- 230000003247 decreasing effect Effects 0.000 description 1
- 230000003071 parasitic effect Effects 0.000 description 1
- 238000011084 recovery Methods 0.000 description 1
- 238000012546 transfer Methods 0.000 description 1
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D33/00—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for
- B64D33/02—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for of combustion air intakes
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D33/00—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for
- B64D33/02—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for of combustion air intakes
- B64D2033/0246—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for of combustion air intakes comprising particle separators
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D33/00—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for
- B64D33/02—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for of combustion air intakes
- B64D2033/0253—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for of combustion air intakes specially adapted for particular type of aircraft
- B64D2033/026—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for of combustion air intakes specially adapted for particular type of aircraft for supersonic or hypersonic aircraft
-
- 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
- Y02T50/10—Drag reduction
Landscapes
- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Aviation & Aerospace Engineering (AREA)
- Combined Means For Separation Of Solids (AREA)
Abstract
The invention discloses a method and a device for controlling shock wave induced separation in an air inlet channel of local particle delivery. By injecting solid particles into the boundary layer facing the upstream wall of the shock wave/boundary layer interference area, the solid particles are accelerated to the same speed as the fluid along with the flow, and momentum is injected into the low-speed fluid after the shock wave by using the relaxation effect of the solid particles after passing through the shock wave so as to control separation. When the flight Mach number is higher, the injected low-temperature particles can cool the fluid near the wall surface, so that the thermal protection effect is realized. The invention controls the flow separation in the air inlet channel by injecting solid particles, avoids the heat protection problem caused by the boundary layer air release control method, does not lose the capture flow, and provides a novel flow control method for the air inlet channel working at high Mach number.
Description
Technical Field
The invention belongs to the field of supersonic/hypersonic air inlet channel flow control, and particularly relates to a control method and a device for controlling shock wave/boundary layer interference induced flow separation.
Background
The supersonic/hypersonic air inlet channel is an important part of the air suction type high-speed aircraft, is positioned at the forefront end of the high-speed air suction type propulsion system, has multiple functions of capturing and adjusting air flow, converting and utilizing incoming flow energy, adjusting flow speed and uniformity, isolating upstream and downstream disturbance and the like, and has direct influence on the working efficiency and envelope of the propulsion system. As the ramjet engine of the hypersonic aircraft ideal power device, more than 50% of the total thrust is derived from a complex air inlet and exhaust system.
Since the supersonic/hypersonic air inlet is mainly used for realizing the deceleration and pressurization of the captured gas by means of a laser system, the flow dominated by the shock wave is one of core flow phenomena in the air inlet, in particular to the shock wave/boundary layer interference phenomenon. The shock wave/boundary layer interference in the air inlet channel can reduce the total pressure recovery of the air inlet channel and enhance the flow field distortion. When shock wave/boundary layer interference induces separation, the circulation capacity of the air inlet channel is reduced, and when serious, the air inlet channel is not started or even the engine is flameout, so that the control of flow separation is very important.
Increasing the fluid momentum within the boundary layer or decreasing the back pressure gradient can inhibit separation. The traditional control method comprises a slope type vortex generator, a plasma synthetic jet, a wall bulge control method, boundary layer deflation and the like. Although these conventional methods have some control effects, they have obvious drawbacks. The vortex generator can generate parasitic resistance and is easy to damage under the impact of high-speed airflow, the practicability of the plasma synthetic jet is limited by the size of an exciter and the electromagnetic compatibility of other airborne equipment, the control effect of the bulge control method is weak under the working condition of a wide speed range, and the boundary layer deflation can lose capture flow, generate deflation resistance and cause unavoidable heat protection problems under the high Mach number.
Disclosure of Invention
The invention aims to: the invention discloses a control method and a control device for shock wave induced separation in an air inlet channel for local particle delivery. The effect of suppressing separation can be achieved by injecting solid particles into the boundary layer. This new flow control approach avoids the thermal protection problem of boundary layer bleed air without losing trapped flow.
The invention also provides an air inlet channel using the shock wave induced separation control device in the air inlet channel.
The technical scheme is as follows:
The control device for shock wave induced separation in the air inlet channel for local particle delivery provided by the invention can adopt the following technical scheme.
The device comprises an air inlet channel compression surface and a particle throwing device positioned in the air inlet channel compression surface; the particle throwing device comprises a plurality of tubular particle containers preset with solid particles, a piston positioned in the tubular particle containers, and a switch for opening and closing the tubular particle containers; the compression surface of the air inlet channel is provided with a plurality of particle throwing openings which are in one-to-one correspondence with the tubular particle containers, the switch controls the communication or closure of the particle throwing openings and the interiors of the tubular particle containers, and when the particle throwing openings are communicated with the interiors of the tubular particle containers, the piston pushes solid particles of the tubular particle containers to be discharged outwards through the particle throwing openings.
Further, the switch comprises a plate body and a driver for controlling the movement of the plate body, and the driver is arranged in the compression surface of the air inlet channel; the plate body is located between the tubular particle container outlet and the particle throwing port, a plurality of middle channels are arranged on the plate body, when the plate body moves to the position that the middle channels are located between the particle throwing port and the tubular particle container outlet, the particle throwing port is communicated with the tubular particle container outlet through the middle channels, and when the plate body moves to the position that the plate body sealing part is located between the particle throwing port and the tubular particle container outlet, the particle throwing port is sealed with the tubular particle container outlet.
Further, a screw motor for driving the piston is further arranged in the compression surface of the air inlet channel, and the piston is connected with the screw motor through a push rod.
Further, the solid particles have a diameter in the range of 100nm to 20. Mu.m.
The beneficial effects are that: compared with the prior art, when the shock wave/boundary layer interference phenomenon of the air inlet channel is serious and large separation is induced, the shock wave induced separation control device in the air inlet channel provided by the invention can input solid particles into a flow field (particularly in a boundary layer) at a lower speed from a wall surface at a far position upstream of an interference region. The size of the solid particles is small, the solid particles can be accelerated to the same speed as the fluid within a certain distance, and then momentum is injected into the fluid by utilizing the relaxation effect of the solid particles when the fluid is decelerated, so that separation is inhibited. Meanwhile, the solid particles are low in temperature, can be used for cooling the fluid near the wall surface, and plays a role in local heat protection.
The invention also provides a technical scheme of the air inlet channel comprising the air inlet channel internal shock wave induced separation control device, which comprises the following steps: the injection position of the solid particles is at the upstream wall surface of the shock wave/boundary layer interference of the air inlet channel, and the injected particles are positioned inside the boundary layer.
The invention also provides a technical scheme of a control method of the shock wave induced separation control device in the air inlet channel, which comprises the following steps: and injecting solid particles into the air inlet channel of the high Mach number aircraft at the upstream of the shock wave/boundary layer interference area, and injecting momentum into the air flow by utilizing a relaxation effect when the boundary layer air flow is decelerated after the injected solid particles accelerate along with the flow, so as to inhibit separation.
Drawings
Fig. 1 is a schematic diagram of a flow control method according to the present invention.
FIG. 2 is a schematic diagram of the shock wave induced separation control device in the air inlet channel.
FIG. 3 is a graph showing the comparison of the separation control effects obtained by numerical simulation of the flow separation control method of the present invention.
Detailed Description
The present invention will be described in further detail with reference to the drawings and examples, which should not be construed as limiting the scope of the invention.
Referring to fig. 1 and 2, the present invention provides an in-air-inlet shock wave induced separation control device for local particle delivery, which includes an air inlet precursor 8, an air inlet compression surface 7 covering the air inlet precursor 8, and a particle delivery device located inside the air inlet compression surface. The particle delivery device comprises a plurality of tubular particle containers 10 provided with solid particles (not shown), a piston 14 positioned in the tubular particle containers 10, a switch for opening and closing the tubular particle containers 10, and a screw motor 13 for driving the piston 14. The piston 14 is connected with the screw motor 13 through a push rod 15. In this embodiment, a cavity is formed between the inlet precursor 8 and the inlet compression surface 7, and the particle delivery device is disposed in the cavity.
The inlet channel compression surface 7 is provided with a plurality of particle throwing openings 9 which are in one-to-one correspondence with the tubular particle containers 10. The switch includes a board 11 and a driver 12 (motor) that controls the movement of the board 11. The driver 12 is mounted inside the inlet compression surface 7. The plate 11 is located between the outlet of the tubular particle container 10 and the particle delivery opening 9, and a plurality of intermediate channels are arranged on the plate 11. When the plate body 11 is moved to a state where the intermediate passage is located between the particle dispensing opening 9 and the outlet of the tubular particle container 10, the particle dispensing opening 9 communicates with the outlet of the tubular particle container 10 through the intermediate passage, and in this state, the solid particles of the tubular particle container 10 can be pushed by the piston 14 to be discharged outside through the particle dispensing opening 9. When the plate body 11 is moved to a position where the plate body closing portion is located between the particle dispensing opening 9 and the outlet of the tubular particle container 10, the particle dispensing opening 9 closes the outlet of the tubular particle container 10.
In this embodiment, the diameter of the solid particles ranges from 100nm to 20 μm, and the solid particles can be made of solid fuel of a scramjet engine, such as aluminum or boron.
And referring to fig. 1, the device for controlling separation induced by shock wave in the air inlet is applied to an air inlet structure of a supersonic/hypersonic aircraft, and the injection position of solid particles in the air inlet is located at the upstream wall surface of interference of shock wave/boundary layer of the air inlet, and the injected particles are located in the boundary layer.
Referring to fig. 1, the control method of the shock wave induced separation control device in the air inlet channel comprises the following steps: and injecting solid particles into the air inlet channel of the high Mach number aircraft at the upstream of the shock wave/boundary layer interference area, and injecting momentum into the air flow by utilizing a relaxation effect when the boundary layer air flow is decelerated after the injected solid particles accelerate along with the flow, so as to inhibit separation.
As shown in fig. 1, the incoming flow 1 is supersonic or hypersonic in the application scenario of the control method. When the separation is controlled by the method of the invention, particles are thrown into the boundary layer 3 from the particle throwing area 2 upstream of the shock wave/boundary layer interference. After the particles are put into the container, they are accelerated to the same speed as the fluid by the acceleration section 4.
In the shock/boundary layer disturbance zone 5, the accelerated particles will not be decelerated immediately after passing through the shock wave 6, so the velocity will be higher than the fluid velocity, which will result in momentum transfer from the particles to the fluid, achieving the effect of suppressing separation.
In the above method, the solid particle size of the flow field fed from the particle feeding region 2 is in the order of nanometers or micrometers, and the particles can be fed from the particle feeding region 2 into the flow field at a very low speed.
In the above method, particles are put into the flow field from the particle putting region 2, and the temperature of the particles is lower than the total temperature of the air flow when the high Mach number aircraft flies. The low-temperature particles can also extract heat from the fluid near the wall surface during separation control, so that the local heat protection effect is achieved.
To further illustrate the utility of the present invention, the control effect of the above method on the compression corner induced flow separation was verified using a numerical simulation method. In numerical simulation, the Mach number of the incoming flow is 3, and particles are injected into the flow field from the upstream of the interference area at zero flow direction speed and very small normal speed. The flow near the separation zone when no control is applied is shown in figure 3 a and the flow near the separation zone after control is applied is shown in figure 3 b. Numerical simulation results show that after particles are put into the separation zone, the flow direction and the normal size of the separation zone are reduced, and the control method provided by the invention is proved to be practical and feasible.
Claims (6)
1. The utility model provides a shock wave induced separation controlling means in intake duct of local particle input, includes intake duct compression face, its characterized in that: the particle delivery device is positioned in the compression surface of the air inlet channel; the particle throwing device comprises a plurality of tubular particle containers preset with solid particles, a piston positioned in the tubular particle containers, and a switch for opening and closing the tubular particle containers; the compression surface of the air inlet channel is provided with a plurality of particle throwing openings which are in one-to-one correspondence with the tubular particle containers, the switch controls the communication or closure of the particle throwing openings and the interiors of the tubular particle containers, and when the particle throwing openings are communicated with the interiors of the tubular particle containers, the piston pushes solid particles in the tubular particle containers to be discharged outwards through the particle throwing openings.
2. The in-intake shock induced separation control device according to claim 1, wherein: the switch comprises a plate body and a driver for controlling the plate body to move, and the driver is arranged in the compression surface of the air inlet channel; the plate body is located between the tubular particle container outlet and the particle throwing port, a plurality of middle channels are arranged on the plate body, when the plate body moves to the position that the middle channels are located between the particle throwing port and the tubular particle container outlet, the particle throwing port is communicated with the tubular particle container outlet through the middle channels, and when the plate body moves to the position that the plate body sealing part is located between the particle throwing port and the tubular particle container outlet, the particle throwing port is sealed with the tubular particle container outlet.
3. The in-intake shock induced separation control apparatus according to claim 2, wherein: the inside of the compression surface of the air inlet channel is also provided with a screw motor for driving the piston, and the piston is connected with the screw motor through a push rod.
4. The in-intake shock induced separation control device according to claim 3, wherein: the diameter of the solid particles ranges from 100nm to 20 mu m, the particle temperature is lower than the total air flow temperature when the applied high Mach number aircraft flies, and the particle material is solid fuel of the scramjet engine and comprises aluminum or boron.
5. An air intake duct comprising the in-air intake duct shock wave induced separation control apparatus according to any one of claims 1 to 4, characterized in that: the injection position of the solid particles is at the upstream wall surface of the shock wave/boundary layer interference of the air inlet channel, and the injected particles are positioned inside the boundary layer.
6. A control method of the in-intake shock wave induced separation control apparatus according to any one of claims 1 to 4, characterized in that: and injecting solid particles into the air inlet channel of the high Mach number aircraft at the upstream of the shock wave/boundary layer interference area, and injecting momentum into the air flow by utilizing a relaxation effect when the boundary layer air flow is decelerated after the injected solid particles accelerate along with the flow, so as to inhibit separation.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202210538518.5A CN114872904B (en) | 2022-05-18 | 2022-05-18 | Method and device for controlling shock wave induced separation in air inlet channel for local particle delivery |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202210538518.5A CN114872904B (en) | 2022-05-18 | 2022-05-18 | Method and device for controlling shock wave induced separation in air inlet channel for local particle delivery |
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| Publication Number | Publication Date |
|---|---|
| CN114872904A CN114872904A (en) | 2022-08-09 |
| CN114872904B true CN114872904B (en) | 2024-06-07 |
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| CN202210538518.5A Active CN114872904B (en) | 2022-05-18 | 2022-05-18 | Method and device for controlling shock wave induced separation in air inlet channel for local particle delivery |
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|---|---|---|---|---|
| US3864907A (en) * | 1973-11-05 | 1975-02-11 | Us Air Force | Step cylinder combustor design |
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| US6390418B1 (en) * | 1999-02-25 | 2002-05-21 | United Technologies Corporation | Tangentially directed acoustic jet controlling boundary layer |
| CN103231796A (en) * | 2013-04-22 | 2013-08-07 | 哈尔滨工业大学 | Aircraft wing boundary layer separation inhibiting method based on plasma actuation |
| WO2015024601A1 (en) * | 2013-08-23 | 2015-02-26 | Correale Giuseppe | Boundary layer control via nanosecond dielectric/resistive barrier discharge |
| CN107091158A (en) * | 2017-06-08 | 2017-08-25 | 南京航空航天大学 | Low extrernal resistance is super/hypersonic inlet and Shock/Boundary-Layer interference control method |
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| Publication number | Priority date | Publication date | Assignee | Title |
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| US6981660B2 (en) * | 2000-09-25 | 2006-01-03 | Evit Labs | Shock wave aerosolization apparatus and method |
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2022
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| CN114872904A (en) | 2022-08-09 |
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