CN101245745A - Laminated board sweat cooling structure by strong endothermic reaction - Google Patents
Laminated board sweat cooling structure by strong endothermic reaction Download PDFInfo
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- CN101245745A CN101245745A CNA2008100563542A CN200810056354A CN101245745A CN 101245745 A CN101245745 A CN 101245745A CN A2008100563542 A CNA2008100563542 A CN A2008100563542A CN 200810056354 A CN200810056354 A CN 200810056354A CN 101245745 A CN101245745 A CN 101245745A
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Abstract
The invention provides a plywood sweatcooling structure utilizing high heat absorption reforming reaction, which is piled by a plurality of annular sheets along the thickness direction of the structure; a plurality of dividing strips are arranged between the sheets and integrally formed on the surfaces of the sheets. Nickel base activator films are formed on the surfaces of the sheets; a cooling fluid is the mixed gas of methane and vapor. The cooling fluid enters into a cooling channel from the outer annular surface of the plywood sweatcooling structure and generates the high heat absorption reforming reaction. The cooling fluid after reaction is radiated from the inner annular surface of the plywood sweatcooling structure to carry out sweatcooling on the inner annular surface of the plywood sweatcooling structure. The cooling channel between the sheets can also be filled with porous medium material. The surface of the porous medium material is covered by the activator film. The invention provides a plywood sweatcooling structure suitable for a thrust chamber of a rocket engine with high thrust of the next generation.
Description
Technical field
The present invention relates to relate to a kind of cooling unit, particularly a kind of laminate sweating cooling structure that utilizes strong endothermic reaction.
Background technique
High temperature in the thrust chamber, high pressure, gas flow have at a high speed applied great heating hot-fluid to engine inner wall, especially near the wall the throat is under the great density of heat flow rate, if do not take suitable, effective cooling method, wall surface material is inevitable owing to persistently overheating, causes being burnt at last.Thereby cooling technology is a rocket motor always, particularly the key technology in the high thrust liquid propellant rocket engine R﹠D process.For satisfying the needs of lunar exploration coming years engineering and other space researches, China has planned to develop high thrust nontoxic pollution-free carrier rocket of new generation about 2010, and this must need the further improvement of cooling technology.
Laminate sweating cooling technology is the sweating cooling technology that has been successfully applied to the liquid propellant rocket engine thrust chamber, veneer structure has some etchings the sheet metal of fluid passage to stack by predetermined structural type, form overall structure by diffusion welding then, cooling fluid cools off layer half hitch structure by the fluid passage between the laminate, disperse outflow at last, further the outlet wall is carried out the sweating cooling.Though veneer structure has effectively been brought into play the plurality of advantages of sweating cooling, but it still belongs to the simple convection heat exchange type of cooling, thereby not only its cooling capacity is subjected to the restriction of the convection heat exchange ability of flow field and temperature field coupling, and its highest cooling limit is also retrained by the sensible heat (perhaps a part of latent heat) as the working medium of freezing mixture.Because rocket requires the weight of its additional facilities can not surpass certain limit, obviously, the flow that constantly increases freezing mixture in order to improve cooling capacity is unpractical, must need a kind of cooling capacity stronger, can break through the cooling technology of simple convection heat exchange restriction.
It is a kind of effective way of strengthening convection heat exchange that cooling fluid on the high temperature surface strong endothermic chemical reaction takes place.Compare with traditional convection heat exchange, this method can reduce the temperature on high temperature surface effectively, plays the effect on protection high temperature surface.The water vapour catforming reaction of methane is wherein a kind of very important strong endothermic reaction.
Chinese patent CN1246183C proposes to utilize water and hydrocarbon fuel under supercritical state endothermic chemical reaction to take place, but the document only discloses hydrocarbon fuels such as the bigger normal heptane of molecular chain, isooctane, hexahydrotoluene, this reaction must be carried out under supercritical state, the hydrogen content that generates only about 13%, and the document does not disclose the concrete structure of realizing above-mentioned heat absorption reaction.U.S. Pat 6357217B1 proposes to utilize the heat absorption reforming reaction of methane that gas turbine blades inside is cooled off, but the document has only disclosed the cooling system that is used for gas turbine blades, do not disclose concrete cooling structure, and the catalyzer that reacts required advances to cover the relatively large water passage surface of yardstick, and the conversion ratio of reaction is lower.
Summary of the invention
The present invention is conceived to solve cooling capacity defect of insufficient in the existing laminate sweating cooling, and there is the problem of the limit in the existing cooling capacity of the type of cooling that relies on convection heat exchange merely, aims to provide a kind of laminate sweating cooling structure that is applicable to high thrust carrier rocket thrust chamber of future generation.
At the prior art above shortcomings, the technical problem to be solved in the present invention is: propose a kind of laminate sweating cooling structure of strong endothermic reaction that utilizes and make it astrovehicle firing chamber, nozzle throat heated wall surface are effectively cooled off; Further improve heated wall surface cooling effectiveness, make the cooling effectiveness of heated wall surface even be better than the sweating cooling of simple layer plate structure; Under the prerequisite that has than high cooling efficiency, do not increase peripheral hardware, avoid increasing aircraft weight, strengthen system complexity.
For solving the problems of the technologies described above, the present invention takes following technological scheme:
A kind of laminate sweating cooling structure, thin plate by the multi-disc annular is stacked into laminate sweating cooling structure cylindraceous along its thickness direction, each sheet thin plate forms a plurality of along the circumferential equally distributed dividing strip of thin plate before assembling on the surface of this thin plate by laser beam machining or mechanical milling, thereby limit the cooling channel that certain interval constitutes the cooling fluid circulation between thin plate, the axial height of this cooling channel is 100～2000 μ m; Each sheet gauge of sheet is 100～300 μ m, form one deck nickel-base catalyst film on the annular surface of thin plate, the thickness of this catalyst film is 10～100 μ m, cooling fluid is the mixed gas of methane and water vapour, cooling fluid enters the cooling channel from the outer ring surface of this laminate sweating cooling structure, and because strong heat absorption reforming reaction takes place in the existence of above-mentioned catalyst film, thereby this laminate sweating cooling structure is cooled off, reacted cooling fluid exhales from the inner ring surface of this laminate sweating cooling structure, inner ring surface to this laminate sweating cooling structure further carries out the sweating cooling, and at the inner ring surface that changes laminate sweating cooling structure, the inner wall surface that is thrust chamber forms one deck cooling fluid film, can shield the heating of high temperature fluid to laminate sweating cooling structure inner ring surface.
Because the cooling channel between the thin plate is a Micro Channel Architecture, therefore, as the methane of cooling fluid and water vapour the time by the cooling channel, owing to reforming reaction takes place to absorb heat by force in the existence of catalyst film, the conversion ratio of its reaction is greater than general large scale runner, and laminate sweating cooling structure is cooled off.
In order further to improve the conversion ratio of heat absorption reforming reaction, thereby improve cooling effect, the filling porous dielectric material in cooling channel between the thin plate, this porous media material is connected with heat conduction with thin plate, and it is the thick catalyst films of 5～30 μ m that the surface coverage of this porous media material has thickness; Because strong heat absorption reforming reaction when flowing through the space of this porous media material, takes place in the existence of this catalyst film, described cooling fluid.
Preferably; this porous media material is sintered metal particle or wire mesh structure; the particle diameter of this sintered metal particle is 20～300 μ m; the aperture of this wire gaze is that this porous media material of 50-250 μ m and thin plate interconnect by welding, thereby guarantees integrally-built heat-conductive characteristic.
Described thin plate is Refractoloy or zirconium copper; Described catalyst film is a loaded catalyst, for example Ni/ZrO2 or Ni/Al2O3, adopt sol-gel process, hot spray process or electroless plating method to be formed on the surface of thin plate, this catalyst film is formed on the one side or the two sides of thin plate, thereby surface for two thin plates of each coolant flow channel correspondence, only have one of them to have catalyst film, perhaps the surface of two thin plates all has catalyst film.
Described dividing strip is straight rectangular shape or waveform, the length direction of this dividing strip (or bearing of trend) is consistent or angled with the radial direction of this laminate sweating cooling structure, thereby the cooling channel between the adjacent sheet is separated into a plurality of sector regions.Because the existence of the dividing strip of this form in the cooling channel that cooling fluid forms between by thin plate, can be avoided because too big temperature gradient causes the thermal stress of material to surpass its permitted value effectively in circumferential uniform distribution.
Preferably, axially can further distribute in order to make cooling fluid, described thin plate is provided with a plurality of through holes, and the diameter of this through hole is 300～1000 μ m, thereby the cooling channel of these thin plate both sides is interconnected.Especially, the edge of described through hole is formed with protruding part at the downstream area of cooling fluid, for example can be fish scale shape projection, and this projection can guide cooling fluid to enter adjacent coolant flow channel.The thin plate that offers through hole can be alternately stacked with the thin plate of not offering through hole, thereby form this laminate sweating cooling structure, has the thin plate that a slice or multi-disc (for example two to five) are offered through hole between for example per two thin plates of not offering through hole.The cooling channel of cooling fluid between axially freely distributed, and the axial distribution of cooling fluid can be limited in certain scope.
Because the present invention has adopted above-mentioned technological scheme, with respect to traditional laminate cooling structure, can greatly improve cooling capacity, and catalyst film is set simultaneously, can avoid heat absorption reaction only to take place under supercritical state; Simultaneously, the coolant flow channel of this micro passage form, and further fill the porous media material that is coated with catalyst film, can greatly increase the conversion ratio of heat absorption reaction.The laminate sweating cooling structure that utilizes strong endothermic reaction that the present invention proposes can satisfy the cooling needs of following thrust-augmented rocket.
Description of drawings
Fig. 1 is the three-dimensional view of laminate sweating cooling structure of the present invention.
Fig. 2 is the axial plane view of laminate sweating cooling structure of the present invention.
Fig. 3 is the thin-slab structure schematic representation of laminate sweating cooling structure of the present invention.
Fig. 4 is the circumferential sectional view of laminate sweating cooling structure of the present invention.
Fig. 5 is the straight dividing strip identical with radial direction.
Fig. 6 is the straight dividing strip angled with radial direction.
Fig. 7 is the layout plan of waveform dividing strip.
Fig. 8 is the through hole that is provided with the thin plate of through hole and has jut.
Symbol description among the figure:
1, thin plate; 2, control runner; 3, assignment of traffic district; 4, thrust chamber; 5, catalyst film; 6, coolant flow channel; 7, dividing strip; 8, outer ring surface; 9, inner ring surface; 10, through hole; 11, protruding part.
Embodiment
Figure 1 shows that the three-dimensional view of laminate sweating cooling structure of the present invention, Figure 2 shows that the axial plane view of laminate sweating cooling structure of the present invention.Thin plate 1 by the multi-disc annular is stacked into laminate sweating cooling structure cylindraceous along its thickness direction, this stacked direction constitutes the axial direction A of laminate sweating cooling structure of the present invention, and this laminate sweating cooling structure forms an outer ring surface 8 and an inner ring surface 9, this outer ring surface 8 is provided with and is used to introduce cooling fluid, and cooling fluid enters this laminate sweating cooling structure from opening; The tubular space that this inner ring surface 9 is limited promptly constitutes the thrust chamber 4 of rocket motor.
Form a plurality of along thin plate 1 circumferential equally distributed dividing strip 7 on the surface of each sheet thin plate 1 by laser beam machining or mechanical milling, thereby after multi-disc thin plate 1 its thickness direction is stacked into laminate sweating cooling structure cylindraceous, because dividing strip separates the surface of two adjacent thin plates, thereby limit the cooling channel that certain interval constitutes the cooling fluid circulation between adjacent sheet, the axial height of this cooling channel is 100～2000 μ m; Each sheet gauge of sheet is 100～300 μ m, forms one deck nickel-base catalyst film on the annular surface of thin plate, and the thickness of this catalyst film is 10～100 μ m.This dividing strip 7 can only be formed on a surface of thin plate 1, and in the process of piling up, all thin plates 1 are formed with one of dividing strip 7 and face same direction, to guarantee all have dividing strip 7 between the adjacent thin plate, to form cooling channel 6, at this moment, under the situation of not considering catalyst film thickness, the height of dividing strip 7 is the axial height of cooling channel 6.Correspondingly, dividing strip 7 can be formed on the two sides of each thin plate 1 simultaneously, thereby under the situation of not considering catalyst film thickness, the height sum of the dividing strip 7 of adjacent two thin plates of formation cooling channel 6 is the axial height of cooling channel.Similarly, also can have the thin plate of a dividing strip and the thin plate hybrid stack-ups that the two sides has dividing strip, perhaps have the thin plate of dividing strip and do not have the thin plate hybrid stack-ups of dividing strip, as long as all guarantee to have dividing strip between the thin plate.This dividing strip 7 can obtain by mechanical milling, laser beam machining or electric discharge machining, directly thin slice processed, and the cut-out material, thus form dividing strip 7 on the surface of thin plate 1 integratedly.Understand easily ground, if do not consider manufacture process ground complexity, this dividing strip also can form independently, is placed between the adjacent sheet 1 thereby pile up in the ground process at thin plate 1.
The high-temperature fuel gas that rocket motor produces in axial direction A flows through thrust chamber 4, and cooling fluid is introduced into the assignment of traffic district 3 of annular, enters the outer ring surface 8 of laminate sweating cooling structure then by control runner 2.These control runner 2 operated by rotary motion have flow control device, and valve for example is in order in the circumferentially distribution of control cooling fluid.
Because the existence of above-mentioned catalyst film, strong heat absorption reforming reaction takes place in cooling fluid, thereby this laminate sweating cooling structure is cooled off, reacted cooling fluid exhales from the inner ring surface 9 of this laminate sweating cooling structure, to the inner ring surface 9 of this laminate sweating cooling structure, be that the wall of thrust chamber 4 carries out the sweating cooling.
Catalytic reforming reaction takes place during by the micro passage between the veneer structure in the cooling fluid that methane and water vapour are formed under high temperature, high pressure effect, both effectively reduced the veneer structure surface temperature, has strengthened cooling effect, and it generates CO, the H that contains in product
2The little molecular product good etc. combustion performance can enter the firing chamber and burn, and improved energy utilization ratio.
The methane of utilization of the present invention, its main reaction of steam reforming reaction have three:
CH
4+H
2O＝CO+3H
2-206.1kJ/mol (1)
CO+H
2O＝CO
2+H
2+41kJ/mol (2)
CH
4+2H
2O＝CO
2+4H
2-164kJ/mol (3)
As can be seen, the catalytic reforming reaction of methane, water vapour is a strong endothermic reaction, and the ratio of the hydrogen that generates will be higher than the reformation of the hydrocarbon fuel of practical macromolecular chain.
Figure 3 shows that the thin-slab structure schematic representation of laminate sweating cooling structure of the present invention, thin plate 1 is a loop configuration, its surface is provided with catalyst film 5, and catalyst film 5 can only be arranged on the one side of thin plate, also can all be provided with catalyst film on the two sides of thin plate.
Figure 4 shows that the circumferential sectional view of laminate sweating cooling structure of the present invention, be formed with the coolant flow channel 6 of cooling fluid circulation between the adjacent thin plate 1, have a plurality of dividing strips 7 between two thin plates 1,7 of this dividing strips are formed on one of them annular surface of thin plate.Dividing strip 7 is used for supporting and separating coolant flow channel 6, and the two sides of each sheet thin plate 1 has catalyst film, thereby makes cooling fluid by in the process of coolant flow channel 6, can fully contact with catalyzer.Because coolant flow channel 6 of the present invention is the less Micro Channel Architecture of size, therefore, one side or two sides that the thin plate 1 that contacts with runner can be set according to the actual needs are provided with catalyst film 5.
The conversion ratio that the heat absorption reforming reaction takes place in coolant flow channel 6 cooling fluid has directly determined the cooling effect of laminate sweating cooling structure of the present invention, therefore, in order further to improve the conversion ratio of heat absorption reforming reaction, thereby improve cooling effect, as an alternative embodiment of the invention, cooling channel 6 filling porous dielectric materials between the thin plate 1, this porous media material is connected with heat conduction with thin plate 1, and it is the thick catalyst film of 5-30 μ m that the surface coverage of this porous media material has thickness; Because strong heat absorption reforming reaction when flowing through the space of this porous media material, takes place in the existence of this catalyst film, described cooling fluid.Preferably, this porous media material is sintered metal particle, wire mesh structure or foam metal, the particle diameter of this sintered metal particle is 20-300 μ m, the aperture of this wire gaze is that this porous media material of 50-250 μ m and thin plate interconnect by welding, thereby guarantees integrally-built heat-conductive characteristic.Because porous media material has very big specific surface area, therefore, cooling fluid is when passing through coolant flow channel 6, can contact with catalyzer more fully, thereby improve the conversion ratio of its heat absorption reforming reaction, and because porous media material can further improve the sweating cooling effect to the further distribution of cooling fluid.
As shown in Figure 8, axially can further distribute in order to make cooling fluid, described thin plate is provided with a plurality of through holes 10, and the diameter of this through hole is 300-1000 μ m, thereby the cooling channel of these thin plate both sides is interconnected.Especially, the edge of described through hole is formed with protruding part 11 at the downstream area of cooling fluid, for example can be fish scale shape projection, and this protruding part 11 can guide cooling fluid to enter adjacent coolant flow channel.In coolant flow channel 6, the flow direction of cooling fluid is the radial direction B of laminate sweating cooling structure, the protruding part 11 that downstream area at through hole 10 edges forms can make the component velocity of cooling fluid acquisition axial direction A, thereby cooling fluid can be by through hole 10 further flow rate distribution on the axial direction of laminate sweating cooling structure.
Claims (9)
1. laminate sweating cooling structure, thin plate by the multi-disc annular is stacked into laminate sweating cooling structure cylindraceous along its thickness direction, form a plurality of along the circumferential equally distributed dividing strip of thin plate on the surface of each sheet thin plate by laser beam machining or mechanical milling, thereby limit the cooling channel that certain interval constitutes the cooling fluid circulation between thin plate, the axial height of this cooling channel is 100～2000 μ m; It is characterized in that: each sheet gauge of sheet is 100～300 μ m, form one deck nickel-base catalyst film on the annular surface of thin plate, the thickness of this catalyst film is 10～100 μ m, cooling fluid is the mixed gas of methane and water vapour, cooling fluid enters the cooling channel from the outer ring surface of this laminate sweating cooling structure, and because strong heat absorption reforming reaction takes place in the existence of above-mentioned catalyst film, thereby this laminate sweating cooling structure is cooled off, reacted cooling fluid exhales from the inner ring surface of this laminate sweating cooling structure, and the inner ring surface of this laminate sweating cooling structure is further carried out the sweating cooling.
2, laminate sweating cooling structure according to claim 1, it is characterized in that: the filling porous dielectric material in the cooling channel between the thin plate, this porous media material is connected with heat conduction with thin plate, and it is the thick catalyst film of 5-30 μ m that the surface coverage of this porous media material has thickness; Because strong heat absorption reforming reaction when flowing through the space of this porous media material, takes place in the existence of this catalyst film, described cooling fluid.
3, laminate sweating cooling structure according to claim 2; it is characterized in that: this porous media material is sintered metal particle or wire mesh structure; this porous media material and thin plate interconnect by welding; the particle diameter of this sintered metal particle is 20-300 μ m, and the aperture of this wire gaze is 50-250 μ m.
4, laminate sweating cooling structure according to claim 1 and 2 is characterized in that: described thin plate is Refractoloy or zirconium copper; Described catalyst film is a loaded catalyst, adopts sol-gel process, hot spray process or electroless plating method to be formed on the surface of thin plate.
5, laminate sweating cooling structure according to claim 4, it is characterized in that: described supported catalyst agent film is Ni/ZrO
2Or Ni/Al
2O
3, this catalyst film is formed on the one side or the two sides of thin plate.
6, laminate sweating cooling structure according to claim 1 and 2, it is characterized in that: described dividing strip is straight rectangular shape, the length direction of this dividing strip is consistent or angled with the radial direction of this laminate sweating cooling structure, thereby the cooling channel between the adjacent sheet is separated into a plurality of sector regions.
7, laminate sweating cooling structure according to claim 1 and 2, it is characterized in that: described dividing strip is a waveform, the bearing of trend of this dividing strip is consistent or angled with the radial direction of this laminate sweating cooling structure, thereby the cooling channel between the adjacent sheet is separated into a plurality of sector regions.
8, laminate sweating cooling structure according to claim 1 and 2, it is characterized in that: described thin plate is provided with a plurality of through holes, and the diameter of this through hole is 300-1000 μ m, thereby the cooling channel of these thin plate both sides is interconnected.
9, laminate sweating cooling structure according to claim 8, it is characterized in that: the edge of described through hole is formed with protruding part at the downstream area of cooling fluid.
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| CNB2008100563542A CN100570147C (en) | 2008-01-17 | 2008-01-17 | A kind of laminate sweating cooling structure that utilizes strong endothermic reaction |
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| CN102300628A (en) * | 2009-01-27 | 2011-12-28 | 西门子公司 | Mixing device for mixing water and water vapor in a diversion station |
| CN102483013A (en) * | 2009-07-07 | 2012-05-30 | 火星工程有限公司 | Tiered porosity flashback suppressing elements for monopropellant or pre-mixed bipropellant systems |
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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 |
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| CN112832929A (en) * | 2021-03-05 | 2021-05-25 | 中国科学院力学研究所 | Method for designing cooling structure for equal inner wall surface temperature of rocket engine |
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| DE19730674A1 (en) * | 1997-07-17 | 1999-01-21 | Deutsch Zentr Luft & Raumfahrt | Combustion chamber and method of manufacturing a combustion chamber |
| SE512942C2 (en) * | 1998-10-02 | 2000-06-12 | Volvo Aero Corp | Procedure for manufacturing rocket engine outlet nozzles |
| DE19934927A1 (en) * | 1999-07-26 | 2001-02-01 | Abb Alstom Power Ch Ag | Process for cooling guide vanes and / or moving blades in the turbine stages of a gas turbine plant and gas turbine plant for carrying out the process |
| EP1929147B1 (en) * | 2005-09-06 | 2010-08-25 | Volvo Aero Corporation | A method of producing an engine wall structure |
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| CN102300628A (en) * | 2009-01-27 | 2011-12-28 | 西门子公司 | Mixing device for mixing water and water vapor in a diversion station |
| CN102483013A (en) * | 2009-07-07 | 2012-05-30 | 火星工程有限公司 | Tiered porosity flashback suppressing elements for monopropellant or pre-mixed bipropellant systems |
| CN103672966A (en) * | 2013-11-12 | 2014-03-26 | 清华大学 | Thermal protection method for scramjet engine fuel injection supporting plate by utilization of transpiration cooling |
| CN103672966B (en) * | 2013-11-12 | 2015-06-24 | 清华大学 | Thermal protection method for scramjet engine fuel injection supporting plate by utilization of transpiration cooling |
| 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 |
| CN108187590A (en) * | 2017-12-29 | 2018-06-22 | 北京氢璞创能科技有限公司 | A kind of reforming reactor |
| CN108119260B (en) * | 2018-01-23 | 2023-12-05 | 陕西蓝箭航天技术有限公司 | Liquid engine and carrier |
| CN108119260A (en) * | 2018-01-23 | 2018-06-05 | 北京蓝箭空间科技有限公司 | Liquid engine and vehicle |
| CN110081466A (en) * | 2019-01-18 | 2019-08-02 | 西北工业大学 | A kind of burner inner liner wall structure cooling using microchannel |
| CN110594036B (en) * | 2019-08-23 | 2020-06-02 | 西北工业大学 | Active cooling double-nozzle support plate ejection rocket of rocket-based combined cycle engine |
| CN110594036A (en) * | 2019-08-23 | 2019-12-20 | 西北工业大学 | Active cooling double-nozzle support plate ejection rocket of rocket-based combined cycle engine |
| CN112832929A (en) * | 2021-03-05 | 2021-05-25 | 中国科学院力学研究所 | Method for designing cooling structure for equal inner wall surface temperature of rocket engine |
| CN113153573A (en) * | 2021-04-28 | 2021-07-23 | 西北工业大学 | Piezoelectric type sweating cooling method based on piezoelectric material |
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