CN117514519A - Novel rocket engine injector sweating panel and manufacturing method - Google Patents
Novel rocket engine injector sweating panel and manufacturing method Download PDFInfo
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- CN117514519A CN117514519A CN202311490622.2A CN202311490622A CN117514519A CN 117514519 A CN117514519 A CN 117514519A CN 202311490622 A CN202311490622 A CN 202311490622A CN 117514519 A CN117514519 A CN 117514519A
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- throttle plate
- sweat
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- 230000035900 sweating Effects 0.000 title claims abstract description 74
- 238000004519 manufacturing process Methods 0.000 title claims abstract description 13
- 239000002826 coolant Substances 0.000 claims abstract description 24
- 210000004243 sweat Anatomy 0.000 claims description 44
- 238000001816 cooling Methods 0.000 claims description 21
- 238000009792 diffusion process Methods 0.000 claims description 17
- 238000007747 plating Methods 0.000 claims description 8
- 238000003466 welding Methods 0.000 claims description 6
- 238000004140 cleaning Methods 0.000 claims description 3
- 238000004321 preservation Methods 0.000 claims description 3
- 238000001514 detection method Methods 0.000 claims description 2
- 230000035699 permeability Effects 0.000 abstract description 25
- 239000001257 hydrogen Substances 0.000 abstract description 16
- 229910052739 hydrogen Inorganic materials 0.000 abstract description 16
- 239000007788 liquid Substances 0.000 abstract description 15
- UFHFLCQGNIYNRP-UHFFFAOYSA-N Hydrogen Chemical compound [H][H] UFHFLCQGNIYNRP-UHFFFAOYSA-N 0.000 abstract description 14
- 238000007796 conventional method Methods 0.000 abstract description 4
- 230000006872 improvement Effects 0.000 abstract description 4
- 230000000694 effects Effects 0.000 description 13
- 239000000463 material Substances 0.000 description 11
- 238000002485 combustion reaction Methods 0.000 description 8
- 238000000034 method Methods 0.000 description 6
- MYMOFIZGZYHOMD-UHFFFAOYSA-N Dioxygen Chemical compound O=O MYMOFIZGZYHOMD-UHFFFAOYSA-N 0.000 description 5
- 230000001166 anti-perspirative effect Effects 0.000 description 5
- 239000003213 antiperspirant Substances 0.000 description 5
- 230000008901 benefit Effects 0.000 description 5
- 238000009826 distribution Methods 0.000 description 5
- 239000011248 coating agent Substances 0.000 description 4
- 238000000576 coating method Methods 0.000 description 4
- 239000011148 porous material Substances 0.000 description 4
- 239000000446 fuel Substances 0.000 description 3
- 230000008569 process Effects 0.000 description 3
- 230000002040 relaxant effect Effects 0.000 description 3
- 238000012360 testing method Methods 0.000 description 3
- PXHVJJICTQNCMI-UHFFFAOYSA-N Nickel Chemical compound [Ni] PXHVJJICTQNCMI-UHFFFAOYSA-N 0.000 description 2
- 230000008859 change Effects 0.000 description 2
- 150000002431 hydrogen Chemical class 0.000 description 2
- 230000004048 modification Effects 0.000 description 2
- 238000012986 modification Methods 0.000 description 2
- 238000012545 processing Methods 0.000 description 2
- 229910000601 superalloy Inorganic materials 0.000 description 2
- 238000009834 vaporization Methods 0.000 description 2
- 230000008016 vaporization Effects 0.000 description 2
- OAICVXFJPJFONN-UHFFFAOYSA-N Phosphorus Chemical compound [P] OAICVXFJPJFONN-UHFFFAOYSA-N 0.000 description 1
- 238000002679 ablation Methods 0.000 description 1
- 230000009471 action Effects 0.000 description 1
- 230000015572 biosynthetic process Effects 0.000 description 1
- 238000005219 brazing Methods 0.000 description 1
- 238000000354 decomposition reaction Methods 0.000 description 1
- 230000007547 defect Effects 0.000 description 1
- 238000013461 design Methods 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 239000007789 gas Substances 0.000 description 1
- 238000010438 heat treatment Methods 0.000 description 1
- 238000005304 joining Methods 0.000 description 1
- 239000007791 liquid phase Substances 0.000 description 1
- 238000002156 mixing Methods 0.000 description 1
- 229910052759 nickel Inorganic materials 0.000 description 1
- 230000003647 oxidation Effects 0.000 description 1
- 238000007254 oxidation reaction Methods 0.000 description 1
- 230000000149 penetrating effect Effects 0.000 description 1
- 229910052698 phosphorus Inorganic materials 0.000 description 1
- 239000011574 phosphorus Substances 0.000 description 1
- 238000005096 rolling process Methods 0.000 description 1
- 229910052709 silver Inorganic materials 0.000 description 1
- 239000004332 silver Substances 0.000 description 1
- 238000005245 sintering Methods 0.000 description 1
- 230000001052 transient effect Effects 0.000 description 1
- 230000007704 transition Effects 0.000 description 1
- 230000003313 weakening effect Effects 0.000 description 1
Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02K—JET-PROPULSION PLANTS
- F02K9/00—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof
- F02K9/42—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof using liquid or gaseous propellants
- F02K9/44—Feeding propellants
- F02K9/52—Injectors
Landscapes
- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Devices For Medical Bathing And Washing (AREA)
Abstract
The invention provides a novel rocket engine injector sweating panel and a manufacturing method thereof, and belongs to the technical field of rocket engines. The novel rocket engine injector sweating panel comprises a porous sweating panel and a throttle plate, wherein the throttle plate is arranged on one side face of the porous sweating panel, which faces to a cooling medium, or is embedded in the porous sweating panel, a plurality of through holes which are arranged at intervals are formed in the throttle plate, the throttle plate is configured to limit the flow of cooling medium flowing to a high-temperature face of the porous sweating panel, the overall permeability of the porous sweating panel is indirectly reduced, and the structure is used for realizing that the tolerance zone width of the permeability of the porous sweating panel is widened by more than one time. The permeability of the porous panel with liquid hydrogen as cooling medium can be controlled by the conventional method (0.13-0.16) g/cm 2 S is relaxed to (0.13-0.32) g/cm 2 S, even larger, realizing the improvement of the yield of the porous sweating panel and reducing the production cost of the porous sweating panel.
Description
Technical Field
The invention relates to the technical field of rocket engines, in particular to a novel rocket engine injector sweating panel and a manufacturing method thereof.
Background
The porous sweat cooling panel is characterized in that gas or liquid sweat is discharged from the porous holes under the action of pressure, and a heat-insulating and completely continuous air film (or called a boundary layer) is formed on the surface through decomposition and vaporization of the porous sweat cooling panel, so that a large amount of heat is absorbed, and the surface temperature of the component is reduced.
Sweating cooling is first to absorb heat as the antiperspirant passes through the porous wall, lowering the temperature of the material (heat exchange takes place in the porous wall in the opposite direction to the flow of the antiperspirant in the wall); then when the antiperspirant reaches the outer surface of the porous wall, it quickly diffuses and evaporates to absorb heat, and forms a gaseous heat-absorbing insulating layer with high heat capacity and low heat conductivity. The heat insulating layer is thickened by adjusting the perspiration amount, and the temperature gradient of the heat insulating layer is reduced, so that the heat conductivity of heat flowing to the porous wall is reduced, and the material is ensured to work at the expected temperature.
Porous perspiration material is used as a panel for manufacturing liquid rocket engine injectors. Is not only a heat-proof material, but also a structural material, and belongs to a forced sweat-proof heat-proof structural material.
The results of using the sweating panel show that when the temperature of the combustion chamber is 3500 ℃, the temperature of the hot surfaces of the liquid hydrogen and liquid oxygen rocket engine is only 80-200 ℃, the temperature difference of the two surfaces of the panel is greatly reduced, and the ablation and deformation of the panel are avoided. The combustion efficiency of the engine is improved due to moderate and uniform permeability of the panel, and the reliability of the engine is improved.
The specific impulse of the engine 1s can be improved every 4% of the hydrogen flow rate is reduced. The payload can be increased by 20kg. Compared with the ratio of the hydrogen consumption for sweating and cooling to the total hydrogen consumption, the hydrogen consumption can reach 3 percent in China, the RL-10-3 in the United states is 10 percent, the J-2 engine is 3 to 4 percent, and the main engine of the spaceflight aircraft is 5 percent.
At the same time, the hydrogen permeation quantity of the final material is ensured to be (0.13-0.16) g/cm 2 ·s。
Disadvantages of conventional sweating panels: the permeability requirement range is narrow, the yield is low, the cost is high, the permeability of the porous panel is usually required to be controlled within a certain range for different cooling media, such as the porous panel of a rocket engine using liquid hydrogen as fuel, and the hydrogen permeability of the final material is ensured to be (0.13-0.16) g/cm 2 S. The cooling effect can not meet the requirement due to the too small permeability, and the panel can be ablated; the excessive permeability can lead to excessive quantity of flowing liquid hydrogen, change the mixing ratio of the rocket engine combustion chamber and change the performance of the engine.
Therefore, the porous panel manufactured by the superalloy wire has a low yield due to a narrow required permeability range, and the cost of the porous panel manufactured by the superalloy wire is usually 20000 to 45000 yuan/kg depending on the size, which results in a problem of high manufacturing cost.
Disclosure of Invention
The invention aims to provide a novel rocket engine injector sweating panel, which realizes that the tolerance zone width for relaxing the permeability of a porous sweating panel is more than one time. The permeability of the porous panel with liquid hydrogen as cooling medium can be controlled by the conventional method (0.13-0.16) g/cm 2 S is relaxed to (0.13-0.32) g/cm 2 S, even larger, realizing the improvement of the yield of the porous sweating panel and reducing the production cost of the porous sweating panel.
In order to achieve the purpose of the invention, the invention adopts the following technical scheme:
according to one aspect of the invention, a novel rocket engine injector perspiration panel is provided, comprising a porous perspiration panel and a throttle plate, wherein the throttle plate is arranged on one side surface of the porous perspiration panel facing a cooling medium, or is embedded in the porous perspiration panel, the throttle plate is provided with a plurality of through holes which are arranged at intervals, and the throttle plate is configured to limit the flow rate of cooling medium flowing to a high-temperature surface of the porous perspiration panel.
According to an embodiment of the present invention, the plurality of through holes are arranged in any one of a honeycomb shape, a polygonal shape, and a concentric circle.
According to an embodiment of the present invention, the through holes are uniformly arranged at intervals.
According to an embodiment of the present invention, the through holes are unevenly spaced.
According to one embodiment of the invention, the hole spacing of the through holes is 1.5-2.5 times the hole diameter.
According to one embodiment of the invention, the throttle plate is mounted on the porous sweating panel in a fitting manner, and the throttle plate is attached to the porous sweating panel.
According to one embodiment of the invention, a throttle plate is diffusion-connected to the porous sweat panel.
According to one embodiment of the invention, the throttle plate is embedded between two layers of the porous sweat panels.
According to an embodiment of the invention, the porous sweat panel is a silk screen porous sweat panel.
The second aspect of the embodiment of the present invention also provides a method for manufacturing the novel rocket engine injector perspiration panel, which includes:
a through hole with the aperture of 0.3-0.5mm is formed on the throttle plate;
deburring and surface cleaning treatment are carried out on the through hole;
the throttle plate is detachably assembled and connected with the porous sweating panel;
or the throttle plate is in diffusion connection with the porous sweating panel;
when the diffusion connection mode is adopted, the surface of the throttle plate is subjected to plating treatment, and the plating treatment is not performed within the range of 0.2mm around the through hole; then, during diffusion connection, the welding pressure is controlled to be 0.1-0.5 MPa, the temperature is 920-1050 ℃, the vacuum degree is not lower than 0.02Pa, and the heat preservation and pressure maintaining time is 10-30 minutes;
and performing performance detection after the throttle plate is connected with the porous sweating panel.
One embodiment of the present invention has the following advantages or benefits:
according to the novel rocket engine injector sweating panel disclosed by the embodiment of the invention, the throttle plate is arranged at the cooling medium inlet end of the porous sweating panel to reduce the flow of the cooling medium, so that the overall permeability of the sweating panel is indirectly reduced, and the tolerance zone width for relaxing the permeability of the porous sweating panel is realized by more than one time through the structure. The permeability of the porous panel with liquid hydrogen as cooling medium can be controlled by the conventional method (0.13-0.16) g/cm 2 S is relaxed to (0.13-0.32) g/cm 2 S, even larger, realizing the improvement of the yield of the porous sweating panel and reducing the production cost of the porous sweating panel.
Drawings
The above and other features and advantages of the present invention will become more apparent by describing in detail exemplary embodiments thereof with reference to the attached drawings.
FIG. 1 is a cross-sectional view of a novel rocket engine injector perspiration panel according to one exemplary embodiment.
FIG. 2 is a front view of a throttle plate of a new rocket engine injector perspiration panel according to an exemplary embodiment.
FIG. 3 is another cross-sectional view of a new rocket engine injector perspiration panel according to one exemplary embodiment.
FIG. 4 is another front view of a throttle plate of a new rocket engine injector perspiration panel according to an exemplary embodiment.
FIG. 5 is a schematic illustration of a new rocket engine injector sweat panel throttle plate with excessive through hole spacing, according to an exemplary embodiment.
FIG. 6 is a schematic diagram illustrating a through-hole spacing ideal for a throttle plate of a novel rocket engine injector sweat panel, according to an exemplary embodiment.
FIG. 7 is a partial cross-sectional view of a rocket engine injector according to an exemplary embodiment.
FIG. 8 is a cross-sectional view of a new rocket engine injector perspiration panel with a throttle plate embedded between two layers of porous perspiration panels according to an exemplary embodiment.
Wherein reference numerals are as follows:
1. a porous sweating panel; 2. a throttle plate; 21. a through hole; 3. a cooling medium; 4. a combustion chamber housing; 5. a high temperature region of the combustion chamber; 6. a nozzle; 7. liquid oxygen.
Detailed Description
Example embodiments will now be described more fully with reference to the accompanying drawings. However, the exemplary embodiments can be embodied in many forms and should not be construed as limited to the embodiments set forth herein; rather, these embodiments are provided so that this disclosure will be thorough and complete, and will fully convey the concept of the example embodiments to those skilled in the art. The same reference numerals in the drawings denote the same or similar structures, and thus detailed descriptions thereof will be omitted.
The terms "a," "an," "the," and "said" are used to indicate the presence of one or more elements/components/etc.; the terms "comprising" and "having" are intended to be inclusive and mean that there may be additional elements/components/etc. in addition to the listed elements/components/etc.
As shown in fig. 1-8, a novel rocket engine injector perspiration panel according to embodiments of the present invention includes a porous perspiration panel 1 and a throttle plate 2.
The inside of the porous sweating panel 1 is of a mutually communicated porous structure, and the cooling medium 3 can transversely flow in the porous sweating panel, so that the cooling medium 3 is homogenized, and finally, a heat-insulating completely continuous air film is formed on the surface of the porous sweating panel 1 (the side surface facing the high-temperature area 5 of the combustion chamber) for uniformly sweating, vaporization and surface formation so as to reduce the temperature of the surface during combustion.
When the cooling medium is liquid hydrogen, the porous sweat panel 1 preferably has a liquid hydrogen permeability of 0.16 to 0.32g/cm 2 ·s。
The throttle plate 2 is arranged on one side surface of the porous sweating panel 1 facing the cooling medium 3, or as shown in fig. 8, the throttle plate 2 is embedded in the porous sweating panel 1, and the shape and the size of the throttle plate 2 are matched with those of the porous sweating panel 1.
The throttle plate 2 is provided with a plurality of through holes 21 which are arranged at intervals, and the throttle plate 2 is configured to limit the flow rate of the cooling medium 3 flowing to the high-temperature surface of the porous sweating panel 1.
According to the novel rocket engine injector perspiration panel disclosed by the embodiment of the invention, the flow of cooling medium is reduced by arranging the throttle plate 2 at the cooling medium inlet end of the existing porous perspiration panel 1 or in the porous perspiration panel 1, the overall permeability of the novel rocket engine injector perspiration panel is indirectly reduced, and the width of a tolerance zone for relaxing the permeability of the porous perspiration panel 1 is more than doubled through the structure. The permeability of the porous panel with liquid hydrogen as cooling medium can be controlled by the conventional method (0.13-0.16) g/cm 2 S is widened to (0.13 to 0).32）g/cm 2 S, even larger, realizing an increase in the yield of the porous sweat panel 1, reducing the production cost of the porous sweat panel 1.
In a preferred embodiment of the present invention, as shown in fig. 1 and 2, when the same permeability is required for different areas of the sweat panel of the novel rocket engine injector, the through holes 21 on the throttle plate 2 are uniformly arranged at intervals so as to meet the requirement of uniform cooling effect of the injector.
In a preferred embodiment of the present invention, as shown in fig. 3 and 4, when different permeability is required for different areas of the sweat panel of the novel rocket engine injector, the through holes 21 on the throttle plate 2 are unevenly arranged at intervals, so as to realize different permeability in different areas. The existing porous panel adopts the same silk screen, has the same permeability after the same rolling, sintering and other technological processes, and can not meet the requirements of different cooling effects required by different areas and different temperatures of the injector panel in the actual working process of the liquid rocket engine.
When the novel rocket engine injector sweating panel is applied to an injector of a liquid rocket engine, due to the characteristics of different working temperatures of different areas and different cooling requirements of different positions of the liquid rocket engine during operation, the through holes 21 of the throttle plate 2 are formed into corresponding uneven interval arrangement, so that different areas of the overall novel rocket engine injector sweating panel have different permeability, and further different cooling effects on the different areas of the injector are realized.
The non-uniform arrangement of the through holes 21 is used for throttling and adjusting the flow distribution state, such as improving the cooling effect of a specific area, such as the vicinity of the ignition nose of the injector, further protecting the ignition area panel, preventing the local high temperature from damaging the panel at the moment of ignition of the rocket engine, and the like.
If the actual temperature is high, it is desirable to have a lower temperature, i.e. more perspiration is needed to cool, and the pitch is reduced with the same pore size; the pore diameter is increased with the same pitch.
When the porous panel 1 needs different areas to have different cooling effects, the thickness of the silk screen porous panel 1 should be controlled within a certain range, otherwise, the uneven cooling effect of the cooling medium directionally distributed by the throttle plate 2 is destroyed under the transverse flow equalization effect in the thicker mesh porous panel 1, therefore, the thickness of the mesh porous panel 1 should not exceed 3-5 mm, and the uneven cooling effect is optimal within the range.
As shown in fig. 2 and 4, in a preferred embodiment of the present invention, the plurality of through holes 21 are arranged in any of a honeycomb shape, a polygonal shape, and a concentric circle.
As shown in fig. 1 and 2, in a preferred embodiment of the present invention, the through holes 21 are uniformly spaced, and the through holes radially distributed in the throttle plate 2 are uniformly spaced.
As shown in fig. 3 and 4, in the case where the through holes 21 are unevenly spaced, the through holes of the throttle plate 2 are unevenly spaced in radial direction.
The non-uniform arrangement of the through holes 21 at intervals is not limited to the radial non-uniform arrangement, but may be circumferentially non-uniform arrangement, and a person skilled in the art may select a non-uniform arrangement mode according to different cooling portions.
In a preferred embodiment of the present invention, the hole spacing of the through holes 21 is 1.5-2.5 times the hole diameter.
As shown in fig. 5, the through holes 21 have a large pitch L1 and sweat generation is uneven.
The pore spacing is too large, and the space cannot be too large because after the antiperspirant flows through the pores, the expansion range in the porous perspiration panel 1 is limited, no antiperspirant flows out in the region outside the expansion range, and the cooling effect is poor.
As shown in fig. 6, the through holes 21 are small in pitch L2 and ideal in pitch, and sweat is generated uniformly.
Under the condition of the same total flow, too small hole spacing can cause more holes, so that the hole diameter is smaller, the processing difficulty of the holes is increased, the technical problem is avoided, and only the processing difficulty and the cost are solved; too large a hole spacing has technical defects, which can cause uneven sweating.
When the hole spacing of the through holes 21 of the throttle plate 2 is too large or the thickness H of the porous sweating panel 1 is too thin, the flow equalization of the cooling medium in the porous sweating panel 1 is insufficient, and the sweat cooling of the high temperature surface of the porous panel is uneven, so the hole spacing of the through holes 21 should not be more than half the thickness of the porous sweating panel 1.
In a preferred embodiment of the present invention, the throttle plate 2 is mounted to the porous sweat panel 1 by fitting, and the throttle plate 2 is closely fitted to the porous sweat panel 1. For example, the throttle plate 2 is limited to the throttle plate 2 by an annular clip (this annular clip can be realized with a nozzle structure in the injector structure, since there are few tens, many hundreds of such nozzles per injector), and the throttle plate 2 is located between the annular clip and the porous sweat panel 1 and is in close abutment with the annular clip and the porous sweat panel 1.
Of course, the assembly method of the throttle plate 2 is not limited to the above embodiment, and the throttle plate 2 and the porous sweat panel 1 may be fixed by bolts, and a person skilled in the art may select a method of attaching the throttle plate 2 and the porous sweat panel 1 according to actual needs.
In a preferred embodiment of the invention, the throttle plate 2 is diffusion-connected to the porous sweating panel 1. For example, diffusion brazing, which is a process of forming a "mirror" effect on the joining surfaces of two separate pieces to ensure adequate contact between the end surfaces, and then heating to high temperatures to effect welding by interatomic diffusion. Diffusion welding is characterized in that the base material is not melted, but the welded surface of the work must be processed with high precision, and in order to prevent high-temperature oxidation of the work, it is generally necessary to perform the work in vacuum.
When the through holes 21 are unevenly arranged at intervals, namely, sweat panels with different permeability are realized for different areas, the throttle plate 2 and the porous sweat panel 1 are in a diffusion connection mode, the close combination of the throttle plate 2 and the porous sweat panel 1 is ensured, the redistribution of the flow of the medium after the cooling medium flows through the throttle plate 2 is prevented, and the flow distribution effect of the porous panel is prevented from weakening or eliminating.
In a preferred embodiment of the present invention, as shown in fig. 8, the throttle plate 2 is embedded in the porous sweat panel 1, and the throttle plate 2 is located between the two porous sweat panels 1, and both side surfaces of the throttle plate 2 are diffusion-connected with the two porous sweat panels 1, respectively.
The scheme that the throttle plate 2 is inlayed between two-layer porous sweating panel 1 mainly used changes the scene of the distribution of sweating flow, and the inhomogeneous sweating cooling scene of through-hole 21 uneven distribution promptly, and the main reason lies in:
1. the inside of the porous sweating panel 1 is provided with micropores, and the porous sweating panel 1 has a certain thickness (usually more than 3 mm), so that a cooling medium can transversely flow in the inside of the porous sweating panel 1, and when the thickness of the porous sweating panel 1 is thicker, uneven sweating which is redistributed through the uneven distribution through holes 21 can be damaged;
2. in order to prevent the uneven sweating effect from being damaged, the thickness of the porous sweating panel 1 is usually required to be not more than 3-4mm, and when the design structure of the rocket engine requires that the thickness of the porous sweating panel is thicker, the throttle plate 2 can be inlaid in the two layers of porous sweating panels, and the thickness of the porous sweating panel 1 behind the throttle plate 2 is ensured to be not more than 3-4mm.
In diffusion bonding, it is desirable to control the amount of deformation, relatively high temperature, low pressure, small amounts of deformation, or near no deformation.
The thickness of the transient liquid phase diffusion welding plating layer is less than 0.01mm, preferably 0.005 mm.
Figures 1, 3 and 7 are all partial cross-sectional views of the injector. Wherein FIG. 1 is a uniform cooling injector state without a nozzle shown; FIG. 3 is a non-uniformly cooled injector state without a nozzle shown; fig. 7 shows only 1 nozzle, and an actual injector has hundreds of nozzles uniformly distributed, due to the partial cross-sectional view.
As shown in fig. 7, the throttle plate 2 is positioned in the combustion chamber shell 4 of the injector, 7 is liquid oxygen, 3 is fuel, the throttle plate 2 and the porous sweating panel 1 are both provided with mounting holes for the nozzle 6 to pass through, the nozzle 6 is arranged in the mounting holes in a penetrating way, the liquid oxygen 7 is sprayed out through the inner hole of the nozzle 6, and the fuel 3 is sprayed out through the circumferential seam of the nozzle 6.
In a preferred embodiment of the invention, the porous sweating panel 1 is a silk screen porous sweating panel, the silk screen porous sweating panel has been successfully applied to a carrier rocket, the single-piece accumulated test run test of a liquid hydrogen and liquid oxygen engine is carried out for 3210s, the silk screen porous sweating cooling panel has an important function and the reliability of the use is verified.
Of course, the porous perspiration panel 1 is not limited to the silk screen porous perspiration panel, and those skilled in the art can select other types of porous perspiration panels according to actual needs.
The embodiment of the invention also provides a manufacturing method of the novel rocket engine injector perspiration panel, which comprises the following steps:
the throttle plate 2 is provided with a through hole 21 with the diameter of 0.3-0.5 mm;
deburring and surface cleaning the through hole 21;
the throttle plate 2 is detachably assembled and connected with the porous sweating panel 1;
or the throttle plate 2 is in diffusion connection with the porous sweating panel 1;
when the diffusion connection mode is adopted, the surface of the throttle plate is subjected to plating treatment, and the periphery of the through hole is not subjected to plating treatment within the range of 0.2 mm; then, during diffusion connection, the welding pressure is controlled to be 0.1-0.5 MPa, the temperature is 920-1050 ℃, the vacuum degree is not lower than 0.02Pa, and the heat preservation and pressure maintaining time is 10-30 minutes;
performance testing was performed after the throttle plate 2 was connected to the porous sweat panel 1.
In a preferred embodiment of the invention, the composition of the coating is 80% nickel, 15% silver, 5% phosphorus, the thickness of the coating preferably being 0.005 to 0.01mm.
The coating is used for a transition layer in diffusion connection, and has the advantages of small number of parts and simple assembly, but the diffusion connection needs coating treatment, has slightly high cost, and has to be performed when different areas need to be controlled for different sweating.
The throttle plate 2 and the porous sweat panel 1 do not need plating treatment when assembled, and the assembled mode has the advantage of low cost, but the assembled mode adopts a large number of parts and slightly complex assembly operation.
In embodiments of the present invention, the term "plurality" refers to two or more, unless explicitly defined otherwise. The terms "mounted," "connected," "secured," and the like are to be construed broadly, and may be, for example, fixedly attached, detachably attached, or integrally attached. The specific meaning of the above terms in the embodiments of the present invention will be understood by those of ordinary skill in the art according to specific circumstances.
In the description of the embodiments of the present invention, it should be understood that the directions or positional relationships indicated by the terms "upper", "lower", etc. are based on the directions or positional relationships shown in the drawings, are merely for convenience in describing the embodiments of the present invention and to simplify the description, and do not indicate or imply that the devices or units referred to must have a specific direction, be configured and operated in a specific direction, and thus should not be construed as limiting the embodiments of the present invention.
In the description of the present specification, the terms "one embodiment," "a preferred embodiment," and the like, mean that a particular feature, structure, material, or characteristic described in connection with the embodiment or example is included in at least one embodiment or example of the embodiments of the present invention. In this specification, schematic representations of the above terms do not necessarily refer to the same embodiment or example. Furthermore, the particular features, structures, materials, or characteristics described may be combined in any suitable manner in any one or more embodiments or examples.
The above is only a preferred embodiment of the present invention and is not intended to limit the embodiment of the present invention, and various modifications and variations can be made to the embodiment of the present invention by those skilled in the art. Any modification, equivalent replacement, improvement, etc. made within the spirit and principle of the embodiments of the present invention should be included in the protection scope of the embodiments of the present invention.
Claims (10)
1. A novel rocket engine injector sweat panel, comprising:
a porous sweat panel (1),
the cooling device comprises a throttle plate (2), wherein the throttle plate (2) is arranged on one side surface of the porous sweating panel (1) facing a cooling medium, or the throttle plate (2) is embedded in the porous sweating panel (1), a plurality of through holes (21) which are arranged at intervals are formed in the throttle plate (2), and the throttle plate (2) is configured to limit the flow of the cooling medium to the high-temperature surface of the porous sweating panel (1).
2. A new rocket engine injector sweat panel as claimed in claim 1, characterised in that a plurality of said through holes (21) are arranged in a honeycomb pattern.
3. A new rocket engine injector sweat panel as claimed in claim 1, wherein the through holes (21) are uniformly spaced.
4. A new rocket engine injector sweat panel as claimed in claim 1, characterised in that the through holes (21) are unevenly spaced.
5. A new rocket engine injector sweat panel as claimed in claim 1, characterised in that the hole spacing of the through holes (21) is 1.5-2.5 times the hole diameter.
6. A new rocket engine injector perspiration panel according to claim 1 characterised in that the throttle plate (2) is mounted on the porous perspiration panel (1) by fitting and the throttle plate (2) is attached to the porous perspiration panel (1).
7. A new rocket engine injector perspiration panel according to claim 1 characterised in that the throttle plate (2) is diffusion connected with the porous perspiration panel (1).
8. A new rocket engine injector sweat panel as claimed in claim 1, characterized in that the throttle plate (2) is embedded between two layers of the porous sweat panels (1).
9. A new rocket engine injector sweat panel as claimed in any one of claims 1 to 8 wherein the porous sweat panel (1) is a wire mesh porous sweat panel.
10. A method of manufacturing a new rocket engine injector sweat panel according to any one of claims 1-9, comprising:
a through hole (21) with the aperture of 0.3-0.5mm is formed in the throttle plate (2);
deburring and surface cleaning the through hole (21);
detachably connecting the throttle plate (2) with the porous sweating panel (1);
or diffusion-connecting the throttle plate (2) with the porous sweat panel (1);
when the diffusion connection mode is adopted, the surface of the throttle plate (2) is subjected to plating treatment, and the periphery of the through hole (21) is not subjected to plating treatment within the range of 0.2 mm; then, during diffusion connection, the welding pressure is controlled to be 0.1-0.5 MPa, the temperature is 920-1050 ℃, the vacuum degree is not lower than 0.02Pa, and the heat preservation and pressure maintaining time is 10-30 minutes;
and performing performance detection after the throttle plate (2) is connected with the porous sweating panel (1).
Priority Applications (1)
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| CN202311490622.2A CN117514519A (en) | 2023-11-10 | 2023-11-10 | Novel rocket engine injector sweating panel and manufacturing method |
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Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US5161379A (en) * | 1991-12-23 | 1992-11-10 | United Technologies Corporation | Combustor injector face plate cooling scheme |
| US20030021905A1 (en) * | 2000-11-06 | 2003-01-30 | Ching-Pang Lee | Method for cooling engine components using multi-layer barrier coating |
| US20110000981A1 (en) * | 2006-06-20 | 2011-01-06 | Deutsches Zentrum Fuer Luft- Und Raumfahrt E.V. | Injection head, mixing space and power unit |
| JP2013133711A (en) * | 2011-12-26 | 2013-07-08 | Ihi Corp | Rocket injector and rocket combustor |
| CN111852691A (en) * | 2020-08-13 | 2020-10-30 | 北京星际荣耀空间科技有限公司 | Integrated double-component injector, manufacturing method thereof and aerospace equipment |
| CN112765913A (en) * | 2021-04-08 | 2021-05-07 | 中国空气动力研究与发展中心计算空气动力研究所 | Layered gradient porous material sweating cooling structure and aircraft |
-
2023
- 2023-11-10 CN CN202311490622.2A patent/CN117514519A/en active Pending
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US5161379A (en) * | 1991-12-23 | 1992-11-10 | United Technologies Corporation | Combustor injector face plate cooling scheme |
| US20030021905A1 (en) * | 2000-11-06 | 2003-01-30 | Ching-Pang Lee | Method for cooling engine components using multi-layer barrier coating |
| US20110000981A1 (en) * | 2006-06-20 | 2011-01-06 | Deutsches Zentrum Fuer Luft- Und Raumfahrt E.V. | Injection head, mixing space and power unit |
| JP2013133711A (en) * | 2011-12-26 | 2013-07-08 | Ihi Corp | Rocket injector and rocket combustor |
| CN111852691A (en) * | 2020-08-13 | 2020-10-30 | 北京星际荣耀空间科技有限公司 | Integrated double-component injector, manufacturing method thereof and aerospace equipment |
| CN112765913A (en) * | 2021-04-08 | 2021-05-07 | 中国空气动力研究与发展中心计算空气动力研究所 | Layered gradient porous material sweating cooling structure and aircraft |
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