CN106523159B - The adaptive supersonic speed air film cooling device and application method for resisting shock wave - Google Patents
The adaptive supersonic speed air film cooling device and application method for resisting shock wave Download PDFInfo
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- CN106523159B CN106523159B CN201611113428.2A CN201611113428A CN106523159B CN 106523159 B CN106523159 B CN 106523159B CN 201611113428 A CN201611113428 A CN 201611113428A CN 106523159 B CN106523159 B CN 106523159B
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- pressure
- electrode
- shock wave
- pressure switch
- supersonic speed
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Classifications
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
- F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
- F02C7/12—Cooling of plants
- F02C7/14—Cooling of plants of fluids in the plant, e.g. lubricant or fuel
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
- F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
- F02C7/12—Cooling of plants
- F02C7/14—Cooling of plants of fluids in the plant, e.g. lubricant or fuel
- F02C7/141—Cooling of plants of fluids in the plant, e.g. lubricant or fuel of working fluid
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
- F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
- F02C7/12—Cooling of plants
- F02C7/16—Cooling of plants characterised by cooling medium
- F02C7/18—Cooling of plants characterised by cooling medium the medium being gaseous, e.g. air
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
- F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
- F02C7/12—Cooling of plants
- F02C7/16—Cooling of plants characterised by cooling medium
- F02C7/18—Cooling of plants characterised by cooling medium the medium being gaseous, e.g. air
- F02C7/185—Cooling means for reducing the temperature of the cooling air or gas
-
- 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
- F05D2260/00—Function
- F05D2260/20—Heat transfer, e.g. cooling
- F05D2260/202—Heat transfer, e.g. cooling by film cooling
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- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Plasma Technology (AREA)
Abstract
The present invention provides a kind of adaptive supersonic speed air film cooling device and application method for resisting shock wave, it is when Shock Wave is occurring in hypersonic vehicle high temperature part, according to the appearance of shock wave and the plasma injected in Shock Wave region with shock strength corresponding amount of intensity size adaptation, the supersonic speed air film cooling structure of the execution that suppresses shock wave can be realized.The device includes：Supersonic speed air film cooling flow passage, nozzle, protected wall, pressure monitoring pipeline, pressure switch group, power supply, dielectric, electrode A, electrode B and connection circuit.Fluid pressure rise caused by shock wave is guided to combination pressure switch by pressure monitoring pipeline, according to corresponding different circuits in different shock strength connection combination pressure switch, so that magnitude of voltage corresponding to electric power starting and output, plasma is produced between electrode A and electrode B, weakens destruction of the shock wave to supersonic speed gaseous film control.
Description
Technical field
The present invention relates to a kind of temperature barrier and method of hypersonic vehicle high-temperature component, especially with regard to one kind
The temperature barrier and method of wall supersonic speed gaseous film control when intense shock wave incidence be present in high temperature ultrasonic speed air-flow.
Background technology
Gaseous film control is since the seventies in last century is initially as a kind of cooling means use of aero-gas turbine, at present
The main cooling provision of modern gas turbines high-temperature component is become.In other field, gaseous film control is as a kind of effective
Active cooling method is also widely used.Due to the features such as gaseous film control is simple in construction, good cooling results, cooling gas is tangentially sprayed
Enter to play a part of to reduce wall friction, gaseous film control is also included into the cooling of rocket high-temperature component, hypersonic aircraft
The limit of consideration of hot-end component cooling.
There is difference in supersonic speed gaseous film control, reason essentially consists on the one hand ultrasound with the gaseous film control in the case of subsonic speed
The compressible influence of gas shows more obvious in the case of speed；On the other hand in supersonic flow field, it is frequently accompanied by shock wave
Appearance, shock incidence air film boundary layer often impacts to supersonic speed gaseous film control.
There are some researches show under the condition of incidence of intense shock wave, shock wave will cause gaseous film control boundary layer separation, cooling stream
Body and main flow blending enhancing, so as to destroy supersonic speed gas film cooling efficiency, there are some researches show after intense shock wave incidence, due to border
Supersonic speed gaseous film control no longer works after the separation of layer causes shock incidence point.
In the case where shock incidence occurs, by changing wall structure or flow field structure etc., weaken shock wave to ultrasound
The destruction of fast gaseous film control is significant for the practical application of supersonic speed gaseous film control.Therefore, develop and develop
Go out can in Adaptive Suppression flow field blast damage supersonic speed air film cooling structure it is significant for its practicality.
The content of the invention
Can be used for heat shield member in hypersonic vehicle it is an object of the invention to provide one kind, can when there is Shock Wave
Injected with the generation plasma of the appearance according to shock wave and the Self-adaptive strength of shock wave in gaseous film control boundary layer, so as to
Effectively resist supersonic speed air film cooling structure and its application method of the shock wave for supersonic speed gaseous film control border damage layer.
In supersonic flow field, when the change of local flow-parameters or structure may induce generation shock wave, for using super
For the wall of velocity of sound gaseous film control, if intense shock wave is incided on gaseous film control boundary layer, the now supersonic speed of original design
Gaseous film control structure is possible to completely inhibit the execution of shock wave, and cooling effect, which will reduce, even to fail.To suppress
This destruction of shock wave, technical scheme provide it is a kind of can be according to the big of the appearance of shock wave and shock strength
It is small, a certain amount of plasma adaptively is injected to Shock Wave region air film boundary layer, reaches the execution for suppressing shock wave.
A kind of supersonic speed air film cooling device of the adaptive Shock Wave of plasma excitation, including supersonic speed gaseous film control
Circulation road, nozzle, protected wall, pressure monitoring pipeline, pressure switch group, power supply, dielectric, electrode A, electrode B and company
Connect circuit.
The device includes：Supersonic speed air film cooling flow passage, nozzle, protected wall, pressure monitoring pipeline, pressure switch
Group, power supply, dielectric, electrode A, electrode B and connection circuit；Supersonic speed air film cooling flow passage is located at the inflow of high temperature main flow
Side-lower, the end set of supersonic speed air film cooling flow passage have nozzle, and nozzle is used to spray into cooling gas to protected wall
Thermal protection is carried out, is vulnerable to region setting dielectric and the electrode B that the shock wave of induction influences, dielectric setting in protected wall
In protected wall, under electrode B implantation dielectric, electrode A is arranged on electrode B side, and is attached to close to nozzle, electrode A
On protected wall, electrode A is connected with electrode B with power supply, and pressure monitoring pipeline forms for metallic conduit, and its one end is arranged in
At protected wall monitoring point, the other end is arranged in pressure switch group, and pressure switch group includes multiple pressure switches, each pressure
Power switch is all connected with power supply, according to different shock strengths, can connect different circuits, different circuits corresponds to different
Magnitude of voltage, so as to produce different amounts of plasma, the voltage output value of power supply is multi gear, according to the connection of pressure switch group not
With magnitude of voltage corresponding to circuit output.
Cooling gas supersonic speed air film cooling flow passage and nozzle are used for the thermic load for maintaining nominal situation, in actual motion
During, cooling fluid is covered in and protected by being sprayed into after supersonic speed air film cooling flow passage through nozzle parallel to high temperature main flow
On retaining wall face, so as to carry out effective thermal protection to protected wall.
Pressure monitoring pipeline is formed for metallic conduit, and suitable pipe diameter, its one end arrangement are selected according to practical structures
At protected wall monitoring point, the other end is arranged in pressure switch.Its function by directly being contacted with protected wall,
When part is acted on by shock wave, Fluid pressure rise, the high pressure of shock wave can be transferred to by pressure by pressure monitoring pipeline
At power switch, so as to have the function that to open pressure switch.
Pressure switch group is by suitably calculating and designing, and in the case of there is shock wave in flow field, is swashed according to different
Intensity of wave, different circuits can be connected, different circuits corresponds to different magnitudes of voltage, different amounts of so as to finally produce
Plasma.
Power supply can be AC power or dc source, and its voltage output value can be multi gear, according to pressure switch group
Magnitude of voltage corresponding to the different circuit outputs of connection.
Electrode A is attached on protected wall, and thickness is not more than 0.2 millimeter, and electrode B is implanted under dielectric, dielectric material
Material is arranged in protected wall.
In present invention design, different amounts of plasma can be produced according to different shock strengths, it is possible to achieve to more
Kind intensity shock wave resists effect.
Brief description of the drawings
Fig. 1 is the scheme schematic diagram of the embodiment of the present invention；
Fig. 2 is schematic diagram at protected wall monitoring point in the scheme of the embodiment of the present invention；
Wherein：1- high temperature main flows；2- supersonic speed air film cooling flow passages；3- cools down flow nozzle；4- pressure monitoring pipelines；5-
Pressure switch group；6- power supplys；7- electrode As；8- electrode Bs；9- dielectrics；The protected walls of 10-；11- shock waves；12- high-pressure areas.
Embodiment
With reference to the accompanying drawings and examples, the embodiment of the present invention is described in further detail.Implement below
Example is used to illustrate the present invention, but is not limited to the scope of the present invention.
A kind of supersonic speed air film cooling device that can realize the execution for suppressing shock wave, described device is according to shock wave
There is the plasma to injecting respective amount in gaseous film control boundary layer with intensity size adaptation.
The device includes：Supersonic speed air film cooling flow passage (2), nozzle (3), protected wall (10), pressure monitoring pipe
Road (4), pressure switch group (5), power supply (6), dielectric (9), electrode A (7), electrode B (8) and connection circuit；Supersonic Gas
Film cooling flow passage (2) is located at below the inflow side of high temperature main flow (1), the end set of supersonic speed air film cooling flow passage (2)
There is nozzle (3), nozzle (3) is used to spray into cooling gas to protected wall (10) progress Thermal protection, in protected wall (10)
The region that being vulnerable to the shock wave of induction influences sets dielectric (9) and electrode B (8), dielectric (9) to be arranged on protected wall
(10) in, under electrode B (8) implantation dielectric (9), electrode A (7) is arranged on electrode B (8) side, and close to nozzle (3), electrode A
(7) it is attached on protected wall (10), electrode A (7) is connected with electrode B (8) with power supply (6), and pressure monitoring pipeline (4) is
Metallic conduit is formed, and its one end is arranged at protected wall monitoring point, and the other end is arranged in pressure switch group (5), pressure
Switches set (5) includes multiple pressure switches, and each pressure switch is connected with power supply (6), can be with according to different shock strengths
Different circuits is connected, different circuits corresponds to different magnitudes of voltage, so as to produce different amounts of plasma, power supply (6)
Voltage output value is multi gear, magnitude of voltage corresponding to the different circuit outputs connected according to pressure switch group.
In apparatus of the present invention practical application, its operation logic process following steps：
1) in supersonic flow field, under normal circumstances, after high temperature 1 flow channel of main flow, supersonic speed gaseous film control stream is passed through
Passage 2 introduces cooling fluid and sprays into cooling gas to protected wall 10 progress Thermal protection through nozzle 3；
2) due to the change of local flow-parameters or structure, the incidence of shock wave 11 is induced, causes cooling gas boundary layer
Interior pressure rise, high-pressure area 12 is formed, the incident of shock wave will destroy cooling gas boundary layer, be cooling gas boundary layer point
From so as to cause cooling effect to decline；Now, in the pressure monitoring pipeline 4 of protected wall fluid due to Shock Wave area
Domain is connected, and its Fluid pressure drastically raises；
3) after the Fluid pressure rise in pressure monitoring pipeline 4, high-pressure fluid will open certain corresponding in pressure switch group 5
One pressure switch, and then connect the circuit of the different magnitudes of voltage according to corresponding to different pressure ratings；
4) after pressure switch group 5 is opened, power supply 6 will start, and certain voltage is formed between electrode A and electrode B, different
The voltage of grade will produce different amounts of plasma；After plasma produces, in the presence of electrode A and electrode B, plasma
Ion in the body para-electric field direction in the presence of electric field is moved, and the gas molecule collision in air, and momentum is passed to
Gas molecule, accelerate air-flow, while will also trigger shock effect with effects such as transitivity changes, so as to prevent boundary layer point
From resisting destruction of the shock wave to supersonic speed gaseous film control；
5) after shock strength dies down or disappears, the now fluid pressure drop in pressure monitoring region, pressure monitoring pipe
Fluid pressure drop in road 4, be not enough to be maintained open pressure switch, now pressure switch is closed, power supply 6 stop to electrode A and
Electrode B is powered, and plasma no longer produces.
It should be noted that due to the injection of plasma, added in the fluid equivalent to article on plasma injection zone
Energy, the temperature of fluid have certain rise so as to cause the wall surface temperature in the region also to have the rise of respective degrees.Cause
This is in actual applications, it is necessary to carefully calculate and design the amount of the plasma needed, to prevent what is brought because of this effect
Destruction of the temperature rise for wall.
As can be seen from the above embodiments, the embodiment of the present invention can be realized conveniently in hypersonic vehicle high-temperature component,
When there is Shock Wave, can by monitor change in fluid pressure caused by shock wave and the grade of adaptive injection respective amount from
Daughter suppresses destruction of the shock wave for supersonic speed gaseous film control.
Described above is only the preferred embodiment of the present invention, it is noted that for the ordinary skill people of the art
For member, without departing from the technical principles of the invention, some improvement and replacement can also be made, these improve and replaced
Also it should be regarded as protection scope of the present invention.
Claims (6)
1. a kind of adaptive supersonic speed air film cooling device for resisting shock wave, appearance and intensity size of the described device according to shock wave
The adaptive plasma to injecting respective amount in gaseous film control boundary layer, it is characterised in that the device includes：Supersonic Gas
Film cooling flow passage (2), nozzle (3), protected wall (10), pressure monitoring pipeline (4), pressure switch group (5), power supply (6),
Dielectric (9), electrode A (7), electrode B (8) and connection circuit；Supersonic speed air film cooling flow passage (2) is located at high temperature main flow
(1) below inflow side, the end set of supersonic speed air film cooling flow passage (2) has a nozzle (3), and nozzle (3) is used to spraying into cold
But gas carries out Thermal protection to protected wall (10), and the region for being vulnerable to the shock wave influence of induction in protected wall (10) is set
Dielectric (9) and electrode B (8) are put, dielectric (9) is arranged in protected wall (10), electrode B (8) implantation dielectric (9)
Under, electrode A (7) is arranged on electrode B (8) side, and is attached to close to nozzle (3), electrode A (7) on protected wall (10), electricity
Pole A (7) is connected with electrode B (8) with power supply (6), pressure monitoring pipeline (4) be metallic conduit composition, its one end be arranged in by
Protect at wall monitoring point, the other end is arranged in pressure switch group (5), and pressure switch group (5) includes multiple pressure switches, often
Individual pressure switch is all connected with power supply (6), according to different shock strengths, can connect different circuits, different circuits pair
Different magnitudes of voltage is answered, so as to produce different amounts of plasma, the voltage output value of power supply (6) is multi gear, is opened according to pressure
Magnitude of voltage corresponding to the different circuit outputs of pass group connection.
2. device according to claim 1, it is characterised in that：The supersonic speed air film cooling flow passage (2), nozzle (3)
For undertaking normal heat load condition.
3. device according to claim 1, it is characterised in that：Pressure is realized by the Fluid pressure in pressure monitoring pipeline
The keying of power switches set (5), the pressure according to caused by the shock wave of varying strength can be opened a certain corresponding to pressure switch group (5)
Individual pressure switch, so as to connect its corresponding circuit, when shock dampening or disappearance, the pressure of fluid in pressure monitoring pipeline
It is not enough to open pressure switch, circuit is closed.
4. device according to claim 3, the power supply (6), which is stressed, switchs control, according to pressure switch connection not
The different magnitude of voltage with circuit output so that electrode A (7) produced from electrode B (8) under different magnitudes of voltage it is different amounts of etc.
Gas ions.
5. device according to claim 1, it is characterised in that：The thickness of electrode A (7) is not more than 0.2 millimeter.
6. using the device according to claim any one of 1-5 to the side of hypersonic vehicle high-temperature component thermal protection
Method, it is characterised in that including step：
1) in supersonic flow field, after high temperature main flow (1) flow channel, introduced by supersonic speed air film cooling flow passage (2) cold
But fluid sprays into cooling gas through nozzle (3) and carries out Thermal protection to protected wall (10)；
2) due to the change of local flow-parameters or structure, the incidence of shock wave (11) is induced, is caused in cooling gas boundary layer
Pressure rise, formed high-pressure area (12), the incident of shock wave will destroy cooling gas boundary layer, make cooling gas boundary layer point
From now, fluid with Shock Wave region due to being connected in the pressure monitoring pipeline (4) of protected wall (10), its fluid pressure
Power drastically raises；
3) after the Fluid pressure rise in pressure monitoring pipeline (4), high-pressure fluid will open certain corresponding in pressure switch group (5)
One pressure switch, and then connect the circuit of the different magnitudes of voltage according to corresponding to different pressure ratings；
4) after pressure switch group (5) is opened, power supply (6) will start, and certain electricity is formed between electrode A (7) and electrode B (8)
Pressure, different grades of voltage will produce different amounts of plasma；After plasma produces, in electrode A (7) and electrode B (8)
Under effect, ion in the plasma para-electric field direction in the presence of electric field moves, and the gas molecule collision in air, and
Momentum is passed into gas molecule, accelerates air-flow, while will also trigger shock effect to be acted on transitivity change, so as to prevent
Boundary layer separation, resist destruction of the shock wave to supersonic speed gaseous film control；
5) after shock strength dies down or disappears, the now fluid pressure drop in pressure monitoring region, pressure monitoring pipeline (4)
Middle fluid pressure drop, it is not enough to be maintained open pressure switch, now pressure switch is closed, and power supply (6) stops to electrode A (7)
Powered with electrode B (8), plasma no longer produces.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201611113428.2A CN106523159B (en) | 2016-12-06 | 2016-12-06 | The adaptive supersonic speed air film cooling device and application method for resisting shock wave |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201611113428.2A CN106523159B (en) | 2016-12-06 | 2016-12-06 | The adaptive supersonic speed air film cooling device and application method for resisting shock wave |
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| CN106523159A CN106523159A (en) | 2017-03-22 |
| CN106523159B true CN106523159B (en) | 2018-02-02 |
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Families Citing this family (2)
| Publication number | Priority date | Publication date | Assignee | Title |
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| US20200023942A1 (en) * | 2018-07-19 | 2020-01-23 | General Electric Company | Control system for an aircraft |
| CN110933832A (en) * | 2019-07-16 | 2020-03-27 | 中国人民解放军空军工程大学 | Single power supply driven array type plasma synthetic jet flow control device and flow control method |
Citations (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4565490A (en) * | 1981-06-17 | 1986-01-21 | Rice Ivan G | Integrated gas/steam nozzle |
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| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US7588413B2 (en) * | 2006-11-30 | 2009-09-15 | General Electric Company | Upstream plasma shielded film cooling |
| US9200522B2 (en) * | 2007-12-14 | 2015-12-01 | University Of Florida Research Foundation, Inc. | Active film cooling for turbine blades |
| US8453457B2 (en) * | 2009-08-26 | 2013-06-04 | Lockheed Martin Corporation | Nozzle plasma flow control utilizing dielectric barrier discharge plasma actuators |
| US8500404B2 (en) * | 2010-04-30 | 2013-08-06 | Siemens Energy, Inc. | Plasma actuator controlled film cooling |
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Patent Citations (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4565490A (en) * | 1981-06-17 | 1986-01-21 | Rice Ivan G | Integrated gas/steam nozzle |
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