CN106640214B - A kind of part Sweat coolling inhibits the supersonic speed air film cooling device and its means of defence of shock wave - Google Patents
A kind of part Sweat coolling inhibits the supersonic speed air film cooling device and its means of defence of shock wave Download PDFInfo
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- CN106640214B CN106640214B CN201611107411.6A CN201611107411A CN106640214B CN 106640214 B CN106640214 B CN 106640214B CN 201611107411 A CN201611107411 A CN 201611107411A CN 106640214 B CN106640214 B CN 106640214B
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- pressure
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- fluid
- shock wave
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- 210000004243 sweat Anatomy 0.000 title claims abstract description 64
- 230000035939 shock Effects 0.000 title claims abstract description 63
- 238000001816 cooling Methods 0.000 title claims abstract description 47
- 239000012530 fluid Substances 0.000 claims abstract description 48
- 239000000112 cooling gas Substances 0.000 claims abstract description 9
- 230000003044 adaptive effect Effects 0.000 claims abstract description 5
- 238000012544 monitoring process Methods 0.000 claims description 40
- 239000007789 gas Substances 0.000 claims description 20
- 239000012809 cooling fluid Substances 0.000 claims description 16
- 230000000694 effects Effects 0.000 claims description 11
- 230000006378 damage Effects 0.000 claims description 8
- 238000000034 method Methods 0.000 claims description 4
- 238000001514 detection method Methods 0.000 claims description 3
- 230000035900 sweating Effects 0.000 claims description 3
- 230000008034 disappearance Effects 0.000 claims description 2
- 239000007921 spray Substances 0.000 claims description 2
- 238000013461 design Methods 0.000 abstract description 4
- 230000002401 inhibitory effect Effects 0.000 abstract description 3
- 230000008859 change Effects 0.000 description 4
- 230000004888 barrier function Effects 0.000 description 2
- 230000002708 enhancing effect Effects 0.000 description 2
- 230000002633 protecting effect Effects 0.000 description 2
- 230000009471 action Effects 0.000 description 1
- 230000006978 adaptation Effects 0.000 description 1
- 230000003139 buffering effect Effects 0.000 description 1
- 238000002485 combustion reaction Methods 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 238000010304 firing Methods 0.000 description 1
- 230000006872 improvement Effects 0.000 description 1
- 238000005457 optimization Methods 0.000 description 1
- 230000008569 process Effects 0.000 description 1
- 238000011160 research Methods 0.000 description 1
- 238000012827 research and development Methods 0.000 description 1
- 239000000126 substance Substances 0.000 description 1
- 238000002604 ultrasonography Methods 0.000 description 1
Classifications
-
- 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
- F01D5/18—Hollow blades, i.e. blades with cooling or heating channels or cavities; Heating, heat-insulating or cooling means on blades
- F01D5/186—Film cooling
-
- 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
-
- 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
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
- F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
- F23R2900/00—Special features of, or arrangements for continuous combustion chambers; Combustion processes therefor
- F23R2900/03042—Film cooled combustion chamber walls or domes
Landscapes
- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Thermotherapy And Cooling Therapy Devices (AREA)
Abstract
A kind of hypersonic vehicle high temperature component that can be used for of present invention offer is when there is Shock Wave, local Sweat coolling structure can be opened according to the appearance of shock wave, adaptive strengthens cooling method to realize the supersonic speed air film cooling structure and its cooling means of the execution for inhibiting shock wave by local Sweat coolling.The present invention can efficiently reduce the consumption of cooling gas.Involved component is the component of mechanical structure, and the principle applied is essentially the characteristic of machinery, fluid itself, is not related to the equipment such as Electronic control, electronic signal, therefore design scheme of the present invention has good dependable with function.
Description
Technical field
The present invention relates to a kind of temperature barriers and means of defence of hypersonic vehicle high-temperature component, especially with regard to one kind
There are the temperature barriers and means of defence of wall surface supersonic speed gaseous film control when shock incidence in high temperature ultrasonic speed air-flow.
Background technology
The basic principle of gaseous film control refers to injecting cooling gas along wall surface tangential direction or with certain incidence angle, is formed
One layer of buffering close to protected wall surface cools down air film, wall surface to be isolated with environment of high temperature gas, to be carried out to wall surface
Effectively thermal protection and chemical protection.The cooling provision for having become many occasion high-temperature components at present, such as high-temperature turbine blade, combustion
Burn room etc..
Gaseous film control is divided into subsonic speed gaseous film control and supersonic speed gaseous film control.Wherein, supersonic speed gaseous film control is due to it
The features such as simple in structure, good cooling results, it is cold to be included into cooling, the following hypersonic aircraft hot-end component of rocket high-temperature component
But the considerations of range.
However, in supersonic flow field, it is frequently accompanied by the appearance of shock wave, shock incidence air film boundary layer is often to ultrasound
Fast gaseous film control impacts.Studying influence of the Shock Wave to cooling effect can not at supersonic speed air film Study on Cooling one
The component part lacked.Have for supersonic speed gaseous film control be excited wave action research shows that shock incidence to weaken air film cold
But protecting effect.
Influence is made its practical implementation by the destruction due to shock wave to supersonic speed gaseous film control.Thus research and
Development effectively inhibits the method and apparatus of blast damage supersonic speed gaseous film control to be answered for the engineering of supersonic speed gaseous film control is practical
With having great importance.
For the thermal protection of high-speed aircraft high-temperature component, its good cooling results energy guard block is on the one hand wished,
The cooling fluid usage amount that still further aspect is desirably used for thermal protection again is few as possible.And in supersonic flow field, the appearance of shock wave is very
When more and mainstream flows the change of flow parameter, the variation of structure, office in the uneven mismatch of Fluid pressure, channel with cooling
The closely related of factors such as fire in portion flow field, therefore shock wave may not be to occur and occur always.If one can be developed
Kind can monitor the appearance of shock wave in real time, adaptively by the local enhancement type of cooling come resist shock wave incident structure and
Device is of great significance for the use cooling fluid of optimization.
The present invention proposes a kind of supersonic speed air film cooling structure for taking local Sweat coolling auxiliary, passes through adaptive monitoring
Pressure change caused by shock wave, opening local Sweat coolling reduces effect of the shock wave to supersonic speed gaseous film control.
Invention content
The object of the present invention is to provide a kind of hypersonic vehicle high temperature components that can be used for when there is Shock Wave, according to
There is the local Sweat coolling of adaptive opening to realize the supersonic speed gaseous film control knot for the execution for inhibiting shock wave in shock wave
Structure.
In order to realize that the purpose of thermal protection, supersonic speed air film cooling structure pass through parallel from wall cooling flow nozzle
Cooling fluid is sprayed with supersonic speed to be covered on protected wall surface, wall surface and high temperature mainstream are separated in high temperature mainstream.However,
In supersonic flow field, when the change of flow parameter in the uneven mismatch of mainstream and cooling stream Fluid pressure, channel, structure
Variation when firing in local flow field, will cause the generation of shock wave, shock wave by incident cooling gas boundary layer, to gaseous film control into
Row destroys, and the supersonic speed air film cooling structure of original design at this time will cannot resist the execution of shock wave, protected wall surface
Temperature will increase, until local damage is failed.
To inhibit this destruction of the shock wave to supersonic speed gaseous film control, technical scheme of the present invention provides one kind can be with
The appearance of monitoring shock wave in real time adaptively opens local Sweat coolling structure, passes through the enhancing cooling side of local Sweat coolling
Formula reaches the execution for inhibiting shock wave.
It is a kind of that shock wave is inhibited to realize according to the local Sweat coolling of the opening of the appearance of the shock wave of incident wall surface adaptively
The supersonic speed air film cooling device of execution, including：Pressure monitoring pipeline, pressure opening/shutting valve, the supply of Sweat coolling fluid
Channel, Sweat coolling gas storage chamber, be arranged protected wall pressure detection zone wall surface Sweat coolling porous media and
Supersonic speed air film cooling duct, the pressure monitoring pipeline are metallic conduit structure, and one end is arranged in the prison of protected wall surface
At measuring point, the other end is arranged on pressure opening/shutting valve, and the protected wall surface monitoring point setting is porous in wall surface Sweat coolling
In medium, Sweat coolling fluid feed channel is connect with Sweat coolling gas storage chamber, is pacified on Sweat coolling fluid feed channel
Pressure opening/shutting valve is filled, Sweat coolling gas storage chamber is set as in outside around protected wall surface monitoring point, pressure monitoring pipeline
It is arranged at protected wall surface monitoring point after the Sweat coolling gas storage chamber；Pass through the Fluid pressure in pressure monitoring pipeline
Realize valve opening and closing, after the intensity of shock wave is more than certain value, thus caused by pressure can work as shock dampening with open-top valve
Or when disappearing, the insufficient pressure of fluid is closed with open-top valve, valve in pressure monitoring pipeline, and valve is opened and closed by the pressure
Door controls Sweat coolling fluid feed channel, and when the valve is opened, cooling fluid will pass through valve inflow Sweat coolling
Gas storage chamber will cut off the supply of Sweat coolling fluid when the valve is closed.
Pressure monitoring pipeline is metallic conduit structure, and suitable pipe diameter, one end arrangement are designed according to practical structures
At protected wall surface monitoring point, the other end is arranged on pressure opening/shutting valve.Its function is by monitoring protected wall surface
Fluid pressure, when part is acted on by shock wave, at wall surface Fluid pressure increase, can will be swashed by pressure monitoring pipeline
The high pressure of wave is transferred at pressure opening/shutting valve, to have the function that Open valve.
Pressure opening/shutting valve is by suitably calculating and designing, and in the case of there is shock wave in flow field, works as shock strength
After reaching certain value, boundary layer fluid pressure will be more than a certain value, and high pressure caused by shock wave can just be beaten under the intensity at this time
Pressure opening/shutting valve is opened, to open Sweat coolling fluid feed channel in the case, cooling fluid enters Sweat coolling storage
Gas chamber is then penetrated into above protected wall surface again by the porous media of wall surface and is cooled down, reached and resist blast damage
Effect.
Supersonic speed air film cooling duct mainly undertakes the thermic load of nominal situation.Its design conditions predominantly without shock wave or
In the case of weak shock, cooling fluid is covered in protected wall surface by the parallel ejection of nozzle of supersonic speed air film cooling duct
Upper carry out thermal protection.Local Sweat coolling structure can adaptively be opened and closed to reach according to the appearance of shock wave by being finally reached
Thermal protection effect realizes optimum use cooling fluid.
In being designed due to the present invention, involved component is the component of mechanical structure, and the principle applied is essentially
The characteristic of machinery, fluid itself is not related to the equipment such as Electronic control, electronic signal, therefore design scheme of the present invention has very
Good dependable with function.
Description of the drawings
Fig. 1 is the scheme schematic diagram of the embodiment of the present invention；
Fig. 2 is the partial enlarged view of Fig. 1；
Wherein：1- high temperature mainstreams；2- supersonic speed air films cooling duct；3- cools down flow nozzle；4- pressure monitoring pipelines；5- is pressed
Power opening/shutting valve；6- Sweat coolling fluid feed channels；7- Sweat coolling gas storage chambers；8- porous medias；The protected wall surfaces of 9-；
10- shock waves；The high-pressure areas 11-.
Specific implementation mode
With reference to the accompanying drawings and examples, the specific implementation mode of the present invention is described in further detail.Implement below
Example is not limited to the scope of the present invention for illustrating the present invention.
It is a kind of that shock wave is inhibited to realize according to the local Sweat coolling of the opening of the appearance of the shock wave of incident wall surface adaptively
The supersonic speed air film cooling device of execution, the device include：Pressure monitoring pipeline 4, pressure opening/shutting valve 5, Sweat coolling
Fluid feed channel 6, Sweat coolling gas storage chamber 7, the wall surface Sweat coolling that is arranged in protected wall pressure detection zone are more
Hole medium 8 and supersonic speed air film cooling duct 2, the pressure monitoring pipeline be metallic conduit structure, one end be arranged in by
At the monitoring point for protecting wall surface 9, the other end is arranged on pressure opening/shutting valve, and the protected wall surface monitoring point is arranged in wall surface
In Sweat coolling porous media, Sweat coolling fluid feed channel is connect with Sweat coolling gas storage chamber, in Sweat coolling fluid
Pressure opening/shutting valve is installed on feed path, Sweat coolling gas storage chamber is set as surrounding protected wall surface monitoring point in outside,
Pressure monitoring pipeline is arranged after passing through the Sweat coolling gas storage chamber at protected wall surface monitoring point；Pass through pressure monitoring pipeline
In Fluid pressure realize valve opening and closing, after the intensity of shock wave is more than certain value, thus caused by pressure can with open-top valve
Door, when shock dampening or disappearance, the insufficient pressure of fluid is closed, is passed through with open-top valve, valve in pressure monitoring pipeline
The pressure opening/shutting valve controls Sweat coolling fluid feed channel, and when the valve is opened, cooling fluid will pass through the valve
Door flows into Sweat coolling gas storage chamber, when the valve is closed, will cut off the supply of Sweat coolling fluid.
In apparatus of the present invention practical application, operation logic process following steps：
1) under normal circumstances, logical by supersonic speed gaseous film control after high temperature 1 flow channel of mainstream in supersonic flow field
Road 2 introduces cooling fluid and sprays into cooling gas to the progress Thermal protection of protected wall surface 9 through cooling flow nozzle 3；
2) due to the variation of local flow-parameters or structure, the incidence of shock wave 10 is induced, cooling gas boundary layer is caused
Interior pressure rise forms high-pressure area 11, and the incident of shock wave will destroy cooling gas boundary layer, so as to cause under cooling effect
Drop；At this point, fluid with Shock Wave region due to being connected in the pressure monitoring pipeline 4 of protected wall surface, Fluid pressure is drastically
It increases；After Fluid pressure in pressure monitoring pipeline 4 increases, high-pressure fluid will open pressure opening/shutting valve 5；
3) after pressure opening/shutting valve 5 is opened, Sweat coolling feed path 6 is opened, and it is cold that cooling fluid will be introduced to sweating
But it in gas storage chamber 7, is then penetrated on upper surface by porous media 8 again, it is cold to carry out local enhancement to protected wall surface 9
But, so as to reducing the destruction of shock wave；
4) after parameter changes in supersonic flow field, shock strength dies down or disappears, at this time in high-pressure area 11
Fluid pressure drop, fluid pressure drop in pressure monitoring pipeline 4 is not enough to be maintained open pressure opening/shutting valve 5, press at this time
Power opening/shutting valve 5 is closed, and Sweat coolling fluid feed channel 6 is closed, and local Sweat coolling no longer works.Operating mode enters at this time
Nominal situation, protected wall surface 9 pass through its cooling effect of the fluid sustainable of supersonic speed air film cooling duct 2.To reach
Save the purpose of cooling stream flow.
As can be seen from the above embodiments, the embodiment of the present invention can facilitate realization in hypersonic vehicle high-temperature component,
When there is Shock Wave, caused by monitoring shock wave change in fluid pressure by open local Sweat coolling structure, from
The cooling effect of the enhancing part of adaptation, which reaches, inhibits blast damage effect.
The above is only a 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, several improvement and replacement can also be made, these improve and replace
Also it should be regarded as protection scope of the present invention.
Claims (5)
1. a kind of local Sweat coolling of the opening adaptive according to the appearance of the shock wave of incident wall surface inhibits the broken of shock wave to realize
The supersonic speed air film cooling device of bad effect, the device include：Pressure monitoring pipeline (4), pressure opening/shutting valve (5), sweating are cold
But fluid feed channel (6), Sweat coolling gas storage chamber (7), wall surface sweating in protected wall pressure detection zone is set
Cooling porous media (8) and supersonic speed air film cooling duct (2), the pressure monitoring pipeline are metallic conduit structure, one
End is arranged at protected wall surface (9) monitoring point, and the other end is arranged on pressure opening/shutting valve, the protected wall surface monitoring point
It is arranged in wall surface Sweat coolling porous media, Sweat coolling fluid feed channel is connect with Sweat coolling gas storage chamber, is being sent out
Pressure opening/shutting valve is installed, Sweat coolling gas storage chamber is set as in outside around protected wall on sweat cooling fluid feed path
Face monitoring point, pressure monitoring pipeline are arranged after passing through the Sweat coolling gas storage chamber at protected wall surface monitoring point；Pass through pressure
Fluid pressure in power monitoring pipeline realizes valve opening and closing, after the intensity of shock wave is more than certain value, thus caused by pressure
Can be with open-top valve, when shock dampening or disappearance, the insufficient pressure of fluid is with open-top valve, valve in pressure monitoring pipeline
It closes, Sweat coolling fluid feed channel is controlled by the pressure opening/shutting valve, when the valve is opened, cooling fluid will
Sweat coolling gas storage chamber is flowed by the valve, when the valve is closed, the supply of Sweat coolling fluid will be cut off, it is protected
Wall surface maintains its cooling by the fluid of supersonic speed air film cooling duct；Supersonic speed gaseous film control is by being sprayed from wall cooling stream
It is parallel to high temperature mainstream in mouth to be covered on protected wall surface with supersonic speed ejection cooling fluid, wall surface and high temperature mainstream are separated
To realize thermal protection.
2. the apparatus according to claim 1, it is characterised in that：The thermic load of base regime is held by supersonic speed gaseous film control
Load realizes thermal protection when there is the incidence of shock wave by opening the supplementary mode of local Sweat coolling.
3. the apparatus according to claim 1, it is characterised in that：In the case of shock wave or weak shock, cooling fluid is logical
The parallel ejection of nozzle for crossing supersonic speed air film cooling duct, is covered on protected wall surface and carries out thermal protection.
4. device according to claim 3, the part Sweat coolling is the protected wall surface in supersonic speed gaseous film control
On, there may be the positions of Shock Wave to be processed using porous media for part, the indoor cooling stream of Sweat coolling air storing cavity
Body can be penetrated by porous media above wall surface, to carry out the protection of local enhancement cooling to the position.
5. a kind of beaten using claim 1-4 any one of them device come the appearance according to the shock wave of incident wall surface is adaptive
The method of beginning portion Sweat coolling, it is characterised in that include the following steps：1) in supersonic flow field, when high temperature mainstream flow channel
Afterwards, cooling fluid is introduced by supersonic speed air film cooling duct and sprays into cooling gas to protected through wall cooling flow nozzle (3)
Wall surface (9) carries out Thermal protection；
2) due to the variation of local flow-parameters or structure, the incidence of shock wave (10) is induced, is caused in cooling gas boundary layer
Pressure rise is formed high-pressure area (11), and the incident of shock wave will destroy cooling gas boundary layer, so as to cause under cooling effect
Drop；At this point, for fluid due to being connected with Shock Wave region, Fluid pressure is anxious in the pressure monitoring pipeline (4) of protected wall surface
Play increases；After Fluid pressure in pressure monitoring pipeline (4) increases, high-pressure fluid will open pressure opening/shutting valve (5)；
3) after pressure opening/shutting valve (5) is opened, Sweat coolling fluid feed channel (6) is opened, and cooling fluid will be introduced to hair
Sweat cools down in gas storage chamber (7), is then penetrated on upper surface by wall surface Sweat coolling porous media (8) again, to protected
Wall surface (9) carries out local enhancement cooling, so as to reduce the destruction of shock wave；
4) after parameter changes in supersonic flow field, shock strength dies down or disappears, at this time in high-pressure area (11)
Fluid pressure drop, fluid pressure drop in pressure monitoring pipeline (4), is not enough to be maintained open pressure opening/shutting valve (5), at this time
Pressure opening/shutting valve (5) is closed, and Sweat coolling fluid feed channel (6) is closed, and local Sweat coolling no longer works；Work at this time
Condition enters nominal situation, and protected wall surface (9) passes through its cooling effect of the fluid sustainable of supersonic speed air film cooling duct.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201611107411.6A CN106640214B (en) | 2016-12-06 | 2016-12-06 | A kind of part Sweat coolling inhibits the supersonic speed air film cooling device and its means of defence of shock wave |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201611107411.6A CN106640214B (en) | 2016-12-06 | 2016-12-06 | A kind of part Sweat coolling inhibits the supersonic speed air film cooling device and its means of defence of shock wave |
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| Publication Number | Publication Date |
|---|---|
| CN106640214A CN106640214A (en) | 2017-05-10 |
| CN106640214B true CN106640214B (en) | 2018-07-17 |
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| CN201611107411.6A Active CN106640214B (en) | 2016-12-06 | 2016-12-06 | A kind of part Sweat coolling inhibits the supersonic speed air film cooling device and its means of defence of shock wave |
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| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108223021A (en) * | 2017-12-28 | 2018-06-29 | 吴谦 | A kind of air air film and the method for water diverging composite blading cooling |
Citations (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US3452553A (en) * | 1967-03-17 | 1969-07-01 | Gen Dynamics Corp | Transpiration cooled window |
| US4111596A (en) * | 1977-01-10 | 1978-09-05 | The United States Of America As Represented By The Secretary Of The Navy | Turbine blade cooling system |
Family Cites Families (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20060145020A1 (en) * | 2004-12-10 | 2006-07-06 | Buehler David B | Atmospheric entry thermal protection system |
-
2016
- 2016-12-06 CN CN201611107411.6A patent/CN106640214B/en active Active
Patent Citations (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US3452553A (en) * | 1967-03-17 | 1969-07-01 | Gen Dynamics Corp | Transpiration cooled window |
| US4111596A (en) * | 1977-01-10 | 1978-09-05 | The United States Of America As Represented By The Secretary Of The Navy | Turbine blade cooling system |
Non-Patent Citations (1)
| Title |
|---|
| 超声速气膜冷却中激波抑制的研究;彭威等;《工程热物理学报》;20111015;第32卷(第10期);1732-1733页 * |
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| CN106640214A (en) | 2017-05-10 |
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