CN103672966B - Thermal protection method for scramjet engine fuel injection supporting plate by utilization of transpiration cooling - Google Patents
Thermal protection method for scramjet engine fuel injection supporting plate by utilization of transpiration cooling Download PDFInfo
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- CN103672966B CN103672966B CN201310561911.7A CN201310561911A CN103672966B CN 103672966 B CN103672966 B CN 103672966B CN 201310561911 A CN201310561911 A CN 201310561911A CN 103672966 B CN103672966 B CN 103672966B
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Abstract
The invention relates to a thermal protection method for a scramjet engine fuel injection supporting plate by the utilization of transpiration cooling. The method includes the following steps that (1), high temperature resistant material is used for manufacturing the injection supporting plate of a multi-tiny-hole structure, and a fuel pipe of a scramjet engine is communicated with the injection supporting plate; (2), by the utilization of the process that fuel leaks through holes of the injection supporting plate of the multi-tiny-hole structure, and heat convection is performed forcibly, so that the heat on the surface of the injection supporting plate is taken away; (3), it is utilized that the fuel leaks through the surface of the injection supporting plate to form a thin layer, so that main flows are prevented from performing heat transfer on the injection supporting plate. The multi-tiny-hole structure is manufactured on the injection supporting plate material, the concept of transpiration cooling is used, the fuel serves as a cooling agent, so that strong heat convection happens between the fuel and the injection supporting plate in the process that the fuel flows through the injection supporting plate, meanwhile, the fuel forms the thin layer on the surface of the injection supporting plate, heat transfer between the high temperature main flows and the surface of the injection supporting plate is obstructed, thermal protection on the injection supporting plate and particularly the front edge part of the injection supporting plate is achieved, and the injection supporting plate is prevented from being ablated and damaged. The thermal protection method can be widely applied to thermal protection performed on various ramjet injection supporting plate structures.
Description
Technical field
The present invention relates to a kind of high-temperature wall surface thermal protection method, particularly about a kind of Sweat coolling that utilizes in high-temperature high-speed airflow to the thermal protection method of super burn engine fuel spray support plate.
Background technology
The representatively aeronautical and space technology in development of modern scientific technology forward position, due to the significance that it utilizes in national defence and space resources, obtains the input energetically of many countries in the world, and has driven the prosperity and development of related industry.For meeting higher, the requirement faster that fly, the efficient engine technology of development of new also becomes the inevitable development of following aerospace flight vehicle.As shown in Figure 1, punching engine is the complex leaf structure that a class does not have High Rotation Speed, is realized the engine of high speed incoming air deceleration compression by air intake duct.For realizing in endoatmosphere hypersonic (Ma>5, Ma is Mach number) cruising flight, carry out under the main flow flowing of engine inner combustion chamber needs to remain on hypersonic speed with burning, first the high speed main flow of High Mach number flowing produces oblique shock wave deceleration compression through aircraft leading edge and inducer, then the weak shock string through distance piece enters combustion chamber again, and eventually passes through nozzle section after the fuel mix of spray, igniting, burning and sprays and provide power.But the holdup time of fuel in combustion chamber only has several millisecond, need effective device to provide the spray of fuel, to realize the blending between fuel and high speed main flow.
It is a kind ofly in combustion chamber common realize the device that fuel and high speed main flow carry out effective blending that plate structure is propped up in spray, and fuel, from the nozzle opening ejection spray support plate, mix with high speed main flow, overcomes the shortcoming that wall incidence penetration range is short.But high speed main flow produces serious Aerodynamic Heating in spray support plate surface stagnation, and spray support plate especially leading edge portion very easily ablative degradation occurs simultaneously, effective active cooling must be adopted to reduce spray support plate surface temperature.
Summary of the invention
For the problems referred to above, the object of this invention is to provide a kind of Sweat coolling that utilizes in high-temperature high-speed airflow to the thermal protection method of super burn engine fuel spray support plate.
For achieving the above object, the present invention takes following technical scheme: a kind of Sweat coolling that utilizes is to the thermal protection method of super burn engine fuel spray support plate, it comprises following content: the spray support plate 1) producing multi-cellular structure with exotic material, and is communicated with spray support plate by the cartridge of super burn engine; 2) utilize fuel to ooze out the process of multi-cellular structure spray support plate hole, force to carry out heat convection, take away the heat on spray support plate surface; 3) utilize fuel to ooze out and form thin layer on spray support plate surface, intercept main flow to the heat transfer of spray support plate.
Be provided with the ribs of high temperature resistant solid material in the cavity of described spray support plate, and be communicated with a cartridge respectively in each cavity separated by described ribs.
Described ribs is be arranged in the middle part of described cavity.
Described ribs is that it is multiple to be disposed in described cavity.
Described spray support plate offers nozzle opening.
The outer shape of described spray support plate is carry out the rhombus that flow path direction is an angle of inclination with main flow.
When adopting metal powder porous spray support plate, first the metal dust of micron dimension and organic binder bond are evenly mixed, under heating plasticizing state, solidified forming in die cavity is injected with injection machine after granulating, then by the method for chemistry or thermal decomposition, the binding agent in shaping base is removed, and obtain final products through sintering densification.
The present invention is owing to taking above technical scheme; it has the following advantages: 1, the inventive method is according to the characteristic of porous media; prop up on plate material in spray and produce multi-pore structure; utilize the concept of Sweat coolling, not only can realize the better blending of fuel and main flow, and fuel is served as cooling agent and complete Thermal protection to spray support plate outer surface; its cooling capacity is very large; from thermo-lag angle, only need lower fuel quantity, just can meet and use needs.2, spray of the present invention props up intralamellar part owing to there is a large amount of holes, and specific area is very large, and therefore flow in fuel with spray support plate, strong heat convection occurs in the process of spray support plate, effectively can absorb the heat of solid, reduces spray and props up plate temperature.3, the present invention's speed of penetrating into main flow by the hole on spray support plate due to fuel is slower; therefore a thin layer can be formed on spray support plate surface; hinder the heat transfer on high temperature main flow and spray support plate surface; realize the protection to spray support plate especially its leading edge portion, prevent the ablative degradation of spray support plate.4, the present invention owing to increasing ribs in spray support plate chamber, shares stressed the produced tension in spray support plate both sides, therefore can increase the structural strength of spray support plate, makes up the strength reduction adopting loose porous gap medium making spray support plate to bring.5, the present invention is owing to being arranged to diamond structure by spray support plate, therefore can regulate spray support plate and the inclination angle carrying out flow path direction according to actual needs, main current flow is weakened in the stagnation effect on spray support plate surface, improve thermal protection effect further.6, according to flight demand, the present invention can also on the basis of spray support plate of the present invention, be the nozzle opening of about 0.5mm size with the prior art perforate footpath on spray support plate that coexists mutually, increasing fuel injection rate, further raising cooling effectiveness, and prior art can not be there is concrete dynamic modulus Problems existing is not set.7, the inventive method adopts the powder of stainless steel of micron dimension sintering to make mushy spray and props up plate structure, therefore can ensure spray support plate intensity while permission fuel flows through from micropore, bear certain fuel inlet pressure.The present invention can be widely used in various punching engine spray and prop up in the thermal protection of plate structure.
Accompanying drawing explanation
Fig. 1 is super burn engine operation principle schematic
Fig. 2 is the connection diagram of spray support plate in the present invention and existing equipment
Fig. 3 is spray support plate end face structure schematic diagram in Fig. 2
Fig. 4 be Fig. 3 overlook cross-sectional schematic
Fig. 5 is the structural representation that spray support plate of the present invention adds base steel ribs
Fig. 6 is rhombus spray support plate structural representation of the present invention
Fig. 7 is the cross-sectional schematic of Fig. 6
Detailed description of the invention
Below in conjunction with drawings and Examples, the present invention is described in detail.
As shown in Figure 1 and Figure 2, in super burn engine, be generally the different flight Mach number scopes according to aircraft, select aviation kerosine or liquid hydrogen as fuel, under some particular job environment, the employing fuel gas also had.Fuel is by the self-contained pump of super burn generator and the Valve controlling that is arranged on fuel channel, after arriving certain pressure, spray support plate 2 is entered by a cartridge 1, and spray according in the nozzle opening of designing requirement setting from spray support plate 2, main flow blending after-combustion with high-temperature high-speed airflow, provides power.The inventive method is structurally substantially identical with prior art; unlike the present invention to the improvement on spray support plate materials and structures; the present invention, according to the characteristic of porous media, utilizes the concept of Sweat coolling, fuel is served as cooling agent and completes Thermal protection to spray support plate outer surface.
As shown in Figure 3, Figure 4, overall structure shape and the prior art of spray support plate 2 of the present invention are similar, comprise the stripe shape cavity 22 of a front portion 21 in gradually-reducing shape, one end of cavity 22 is blind end 23, the other end to be connected super burn generator by a lower bottom base 3 upper bed-plate 4 with one is tightly connected, and to be tightly connected cartridge 1 by a sealing steel plate 5, cartridge 1 is communicated with spray support plate 2.The principal character of the inventive method is that the wall surface material of spray support plate 2 is arranged to multi-cellular structure, and namely on the wall of whole spray support plate 2, be covered with micropore, fuel can under the effect of the pressure, ooze out from micropore.The spray support plate 2 of multi-cellular structure of the present invention can adopt the various exotic material of prior art and various different processing technology to obtain, such as: the metal dust of micron dimension and organic binder bond are evenly mixed, under heating plasticizing state, solidified forming in die cavity is injected with injection machine after granulating, then by the method for chemistry or thermal decomposition, the binding agent in shaping base is removed, and obtain final products through sintering densification.The spray support plate 2 that the present invention is made by this many micropores manufacture craft, making precision is high, micropore even tissue, excellent performance.
The present invention utilizes the huge specific area of spray support plate 2 inside of multi-cellular structure, make to be filled with fuel in spray support plate 2 cavity under pressure, can ooze out from many micropores, carry out strong heat convection with spray support plate 2 surface, thus effectively take away the heat of solid spray support plate 2.Simultaneously due under the effect of main flow, fuel can be subject to resistance when oozing out many micropores of spray support plate 2, fuel flow rate is not very high, therefore the fuel oozed out can be formed to be detained on spray support plate 2 surface and cover, thicken the boundary layer of fluid, serve the heat transfer effect hindering high-temperature gas to spray support plate 2 wall.In addition, mix with the main flow of high temperature and high speed afterwards because fuel oozes out from many micropores on spray support plate 2 surface, heat, and take fire after reaching ignition point, therefore can think that fuel has been deep into main flow by microporous spray support plate 2 inner, make the fuel constantly oozed out from many micropores, better mixing effect can be realized with main flow.
In above-described embodiment, in order to overcome the flow resistance in many micropores, the fuel pressure passed in spray support plate 2 cavity is greater than extraneous main flow environmental pressure usually, and inside, spray support plate 2 both sides can produce certain tensile stress; Multi-cellular structure can produce certain strength reduction to spray support plate 2 simultaneously.As shown in Figure 5, the present invention is in order to address this problem, the ribs 6 Steel material or other high temperature resistant solid material being set and making is increased in the cavity of spray support plate 2, ribs 6 can be arranged on the near middle of spray support plate 2 cavity, spray support plate 2 is made to form former and later two cavitys 7,8, to share the tensile stress of the stressed generation in spray support plate 2 both sides, effectively increase the intensity of spray support plate 2.After taking this measure, need to be that two cavitys 7,8 arrange a cartridge 1 respectively, that is send into fuel respectively.Certain the present invention can also as required, set up more ribs 6 in the cavity of spray support plate 2 simultaneously, and arrange more cartridge 1 and connect different cavitys.
In above-described embodiment, because spray support plate 2 is usually designed to anterior 21 edge lines and main flow, to carry out flow path direction vertical, due to the stagnation effect in leading edge portion main flow, flow velocity is zero, static pressure static temperature is maximum, be unfavorable for that fuel oozes out while thermal environment is severe, therefore larger to the thermal protection difficulty of spray support plate 2.As shown in Figure 6, Figure 7, spray support plate 2, in order to address this problem, is designed to the diamond structure tilted by the present invention, makes the incline direction of spray support plate 2 leading edge and carry out flow path direction in an acute angle.Like this; under some particular job environment; as aircraft adopts fuel gas, fluid ratio thermal capacitance is little, and main flow flow velocity, Aerodynamic Heating amount are high especially; in the situations such as spray support plate 2 leading edge portion deathtrap cooling capacity is not enough; the spray support plate 2 of this diamond structure is adopted to design, can when main flow arrive leading edge portion, fluid still can flow along spray support plate 2 outer surface; thus weaken the stagnation effect of main flow, be conducive to improving the protection to spray support plate 2 leading edge hazardous part.
In above-described embodiment, in order to improve fuelcarrying charge, can also some nozzle opening (not shown)s offering about 0.5mm same as the prior art on spray support plate 2 as required, but due to the existence of multi-cellular structure of the present invention, spray support plate 2 will clearly alleviate prior art Problems existing.
The various embodiments described above are only for illustration of the present invention; wherein the manufacture craft, contour structures etc. of spray support plate all can change to some extent; every equivalents of carrying out on the basis of technical solution of the present invention and improvement, all should not get rid of outside protection scope of the present invention.
Claims (10)
1. utilize Sweat coolling to a thermal protection method for super burn engine fuel spray support plate, it comprises following content:
1) produce the spray support plate of multi-cellular structure with exotic material, and the cartridge of super burn engine is communicated with spray support plate;
2) utilize fuel to ooze out the process of multi-cellular structure spray support plate hole, force to carry out heat convection, take away the heat on spray support plate surface;
3) utilize fuel to ooze out and form thin layer on spray support plate surface, intercept main flow to the heat transfer of spray support plate.
2. utilize Sweat coolling to the thermal protection method of super burn engine fuel spray support plate as claimed in claim 1, it is characterized in that: the ribs being provided with high temperature resistant solid material in the cavity of described spray support plate, and be communicated with a cartridge respectively in each cavity separated by described ribs.
3. utilize Sweat coolling to the thermal protection method of super burn engine fuel spray support plate as claimed in claim 2, it is characterized in that: described ribs is be arranged in the middle part of described cavity.
4. utilize Sweat coolling to the thermal protection method of super burn engine fuel spray support plate as claimed in claim 2, it is characterized in that: described ribs is that it is multiple to be disposed in described cavity.
5. as claimed in claim 1 or 2 or 3 or 4 utilize Sweat coolling to the thermal protection method of super burn engine fuel spray support plate, it is characterized in that: described spray support plate offers nozzle opening.
6. as claimed in claim 1 or 2 or 3 or 4 utilize Sweat coolling to the thermal protection method of super burn engine fuel spray support plate, it is characterized in that: the outer shape of described spray support plate is carry out the rhombus that flow path direction is an angle of inclination with main flow.
7. utilize Sweat coolling to the thermal protection method of super burn engine fuel spray support plate as claimed in claim 5, it is characterized in that: the outer shape of described spray support plate is carry out the rhombus that flow path direction is an angle of inclination with main flow.
8. as described in claim 1 or 2 or 3 or 4 or 7, utilize Sweat coolling to the thermal protection method of super burn engine fuel spray support plate, it is characterized in that: when adopting metal powder porous spray support plate, first by the metal dust of micron dimension and organic binder bond Homogeneous phase mixing, under heating plasticizing state, solidified forming in die cavity is injected with injection machine after granulating, then by the method for chemistry or thermal decomposition, the binding agent in shaping base is removed, and obtain final products through sintering densification.
9. utilize Sweat coolling to the thermal protection method of super burn engine fuel spray support plate as claimed in claim 5, it is characterized in that: when adopting metal powder porous spray support plate, first by the metal dust of micron dimension and organic binder bond Homogeneous phase mixing, under heating plasticizing state, solidified forming in die cavity is injected with injection machine after granulating, then by the method for chemistry or thermal decomposition, the binding agent in shaping base is removed, and obtain final products through sintering densification.
10. utilize Sweat coolling to the thermal protection method of super burn engine fuel spray support plate as claimed in claim 6, it is characterized in that: when adopting metal powder porous spray support plate, first by the metal dust of micron dimension and organic binder bond Homogeneous phase mixing, under heating plasticizing state, solidified forming in die cavity is injected with injection machine after granulating, then by the method for chemistry or thermal decomposition, the binding agent in shaping base is removed, and obtain final products through sintering densification.
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| CN201310561911.7A CN103672966B (en) | 2013-11-12 | 2013-11-12 | Thermal protection method for scramjet engine fuel injection supporting plate by utilization of transpiration cooling |
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| CN201310561911.7A CN103672966B (en) | 2013-11-12 | 2013-11-12 | Thermal protection method for scramjet engine fuel injection supporting plate by utilization of transpiration cooling |
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| CN104633709A (en) * | 2014-12-11 | 2015-05-20 | 清华大学 | Thermal protection method of porous medium jetting support plate leading edge nose cone |
| CN104859835B (en) * | 2015-04-27 | 2017-06-16 | 清华大学 | A kind of hypersonic aircraft nose cone based on Compound cooling mode |
| CN109774981B (en) * | 2019-01-28 | 2020-07-03 | 清华大学 | Thermal protection system of auxiliary rocket of hypersonic vehicle |
| CN110425572B (en) * | 2019-07-23 | 2021-02-19 | 哈尔滨工业大学 | Porous single-column fuel supply structure for supersonic aircraft ramjet engine |
| CN110529845B (en) * | 2019-07-29 | 2020-08-07 | 中国科学院广州能源研究所 | Vortex tubular flame burner for directly burning liquid fuel |
| CN110701637B (en) * | 2019-09-20 | 2021-02-12 | 清华大学 | Compound combustion chamber thermal protection wall surface structure |
| CN111824391B (en) * | 2020-07-27 | 2021-11-23 | 清华大学 | Phase-change sweating cooling heat protection structure and construction method thereof |
| CN114811651B (en) * | 2022-06-01 | 2023-03-24 | 清华大学 | Electric heating stable combustion system, method and storage medium |
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