CN113738536B - Integrated force-bearing flow-equalizing top cover device - Google Patents
Integrated force-bearing flow-equalizing top cover device Download PDFInfo
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- CN113738536B CN113738536B CN202110997421.6A CN202110997421A CN113738536B CN 113738536 B CN113738536 B CN 113738536B CN 202110997421 A CN202110997421 A CN 202110997421A CN 113738536 B CN113738536 B CN 113738536B
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- top cover
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- butt flange
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- 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
- F02K9/60—Constructional parts; Details not otherwise provided for
- F02K9/62—Combustion or thrust chambers
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- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Magnetic Bearings And Hydrostatic Bearings (AREA)
Abstract
An integrated force-bearing and flow-equalizing top cover device comprises a butt flange, an inlet section, a top cover, a force-bearing device, a rectifying device and support ribs; the port of the butt flange is a propellant inlet, the butt flange is connected with the top cover through an inlet section, radial support ribs are arranged around the inlet section, and the support ribs are respectively connected with the butt flange, the inlet section and the top cover; the upper end of the top cover is connected with a force bearing device for transmitting thrust; the lower end of the top cover is connected with a rectifying device for ensuring that the propellant entering each nozzle is uniformly distributed; the cross section of the top cover is bimodal, and the central concave cavity is a circular table-shaped platform with a central hole and is used for connecting and mounting an igniter; the top cover is provided with a radial window for operating and installing an igniter or leading out an igniter cable; the top cover is also provided with a hoisting hole for hoisting. The integrated force-bearing flow-equalizing top cover device can bear internal pressure, can transmit thrust, has high pressure and flow distribution uniformity, and is integrally formed without welding.
Description
Technical Field
The invention relates to an integrated force-bearing flow-equalizing top cover device which can be used in the technical fields of aerospace, heat energy engineering and combustion.
Background
The liquid rocket engine thrust chamber works under the high-temperature, high-pressure and complex vibration environment, the head of the thrust chamber mainly comprises a bearing seat, a top cover, an injector, a collector and other structures, and the head of the thrust chamber is used as a part with the largest number of parts, the most complex structure and the largest welding/connecting number on the engine thrust chamber, and the structural reliability of the thrust chamber is directly related to the working reliability of the thrust chamber.
The thrust chamber converts the chemical energy of the fuel into heat energy, and the heat energy is sprayed out through the spray pipe to generate thrust. The thrust is transmitted to the gimbal through the bearing seat at the head part of the thrust chamber, and almost all the thrust is transmitted to the arrow body through the gimbal. The bearing seat is connected with the top cover, and the general structural form of the top cover has three types: 1) A spherical top cover; 2) A three-core top cover; 3) A conical top cover. The first two structural forms mainly bear the pressure of the propellant and do not transmit thrust; the conical top cover bears and transmits thrust except for bearing the pressure of liquid in the cavity. The unreasonable easy structural deformation that causes of top cap structural design destroys scheduling problem even.
The injector has the main function of uniformly injecting the propellant into the combustion chamber under the specified pressure drop and flow rate of the injector, ensuring the designed mixing ratio distribution and mass distribution and rapidly completing the atomization and mixing processes. The distribution condition of the flow field pressure inside the cavity formed by the top cover and the like influences the flow distribution uniformity of each nozzle entering the injector, the working performance such as the combustion efficiency, the stability and the like of the thrust chamber is directly related, and even when the flow distribution is uneven, the local mixing ratio of the nozzles is higher, so that the nozzles are ablated.
Disclosure of Invention
The technical problem to be solved by the invention is as follows: the integrated bearing flow equalizing top cover device overcomes the defects of the prior art, can bear internal pressure, can transmit thrust, is high in pressure and flow distribution uniformity, and is free of welding.
The technical solution of the invention is as follows:
an integrated force-bearing and flow-equalizing top cover device comprises a butt flange, an inlet section, a top cover, a force-bearing device, a rectifying device and support ribs;
the port of the butt flange is a propellant inlet, the butt flange is connected with the top cover through an inlet section, radial support ribs are arranged around the inlet section, and the support ribs are respectively connected with the butt flange, the inlet section and the top cover; the upper end of the top cover is connected with a force bearing device for transmitting thrust; the lower end of the top cover is connected with a rectifying device for ensuring that the propellant entering each nozzle is uniformly distributed; the cross section of the top cover is bimodal, and the central concave cavity is a circular table-shaped platform with a central hole and is used for connecting and mounting an igniter; the top cover is provided with a radial window for operating and installing an igniter or leading out an igniter cable; the top cover is also provided with a hoisting hole for hoisting.
Furthermore, the inlet section is gradually transited from a circular section to a long circular section, the joint with the butt flange is a circular section, and the section penetrating the top cover is a long circular section; and the intersection of the inlet section and the top cover is provided with a fillet, and the diameter of the fillet is 1-1.5 times of the wall thickness of the top cover.
Furthermore, the included angle between the axis of the inlet section and the axis of the top cover is 60-90 degrees; and when the included angle between the axis of the inlet section and the axis of the top cover is 90 degrees, the height of the double peaks is the same as or slightly higher than the axial height of the long cross section which is formed by the penetration of the inlet section and the top cover.
Furthermore, the inlet section is 1, two or more, along top cap circumference evenly distributed.
Further, the propellant is gas or liquid, wherein the gas flow speed does not exceed 150m/s when the propellant reaches the cross section of the through circle between the inlet section and the top cover; the liquid flow rate does not exceed 40m/s.
Furthermore, the wall thickness of the force bearing device is 2-2.5 times of that of the top cover.
Further, fairing outer fringe and inner edge overlap joint respectively on the outer side post inner wall of top cap and center post wall, by straightway, four circular arc sections, straightway constitute, from being close to outer fringe department, straightway and outer side post inner wall overlap joint, back connection four circular arc sections, including transition circular arc, concave circular arc 1, epirelief circular arc, concave circular arc 2, link to each other with the center post wall through a straightway at last, tangent between each circular arc, and R Concave 1 ：R Convex upward ：R Lower concave 2 1, the whole rectifying device is in a wide-ring thin-plate wave type structure.
Furthermore, the number of the support ribs is 6 or a multiple of the number of the support ribs, the support ribs are positioned on the upper side of the axial section of the butting flange, and the support ribs with the total number of 1/6 of the number of the support ribs are only arranged under the butting flange.
Furthermore, the integrated force-bearing flow equalizing device is formed by 3D printing or powder metallurgy in an integrated mode.
Furthermore, the number of the hoisting holes arranged on the top cover is 2, and the hoisting holes are distributed at 180 degrees.
Compared with the prior art, the invention has the beneficial effects that:
1) The integrated bearing flow equalizing top cover device is adopted, so that welding seams between the bearing seat and the top cover are reduced, and the problem of nozzle ablation caused by uneven annular seam gaps of the injector nozzle due to the influence of welding seam heat input is solved.
2) The bimodal top cover structure can improve the rigidity and the internal pressure resistance of the top cover, prevent the deformation problem of the top cover caused under the high internal pressure condition, and further avoid a series of problems of propellant leakage, structural damage and the like.
3) The unique radial support rib structure is adopted, the support ribs are mainly located on the upper side of the axial section of the flange, and the lower side is only provided with one support rib under the support rib, so that the problem of overload damage caused by stress concentration due to over-support is prevented.
4) The inlet section adopts a variable cross-section structure with a circular cross section gradually transited into a long circular cross section, so that the flange is convenient to butt-joint and connected, the speed of fluid entering the top cover can be reduced, the flow resistance loss is reduced, and the uniformity of the flow of each nozzle entering the injector is improved.
5) The fairing of top cap low reaches installation wholly is wide ring sheet metal wavy structure, can improve the flow homogeneity that gets into the nozzle on the one hand, and on the other hand can effectively resist the impact of upper reaches incoming flow propellant to fairing, avoids taking place great displacement and causes structural damage.
Drawings
FIG. 1 is a schematic view of an integrated force-bearing flow-equalizing top cover device;
in the figure: 1-butt flange; 2-an inlet section; 3-top cover; 4-force bearing device; 5-a rectifying device; 6-support ribs; 7-radial window; and 8, hoisting holes.
FIG. 2 is a schematic view of a radial support rib;
fig. 3 is a schematic view of an oblong cross section of the inlet section.
Detailed Description
The invention provides an integrated force-bearing flow-equalizing top cover device, which comprises a butt flange 1, an inlet section 2, a top cover 3, a force-bearing device 4, a rectifying device 5 and support ribs 6, wherein the butt flange is arranged at the bottom of the inlet section;
the port of the butt flange 1 is a propellant inlet, the butt flange 1 is connected with the top cover 3 through the inlet section 2, and the periphery of the inlet section 2 is provided with radial support ribs 6 which are respectively connected with the butt flange 1, the inlet section 2 and the top cover 3 as shown in figure 2; the upper end of the top cover is connected with a force bearing device 4 for transmitting thrust; the lower end of the top cover 3 is connected with a rectifying device 5 for ensuring that the propellant entering each nozzle is uniformly distributed. The cross section of the top cover 3 is bimodal, and the central concave cavity is a circular platform with a central hole and is used for connecting and mounting external devices such as an igniter and the like. The double-peak type cross section is similar to an M shape, two peaks are arranged, a circular truncated cone-shaped concave cavity is arranged between the two peaks, and a central through hole is formed in the bottom of the concave cavity. The center part of the M-shaped structure is a central column, and two sides of the M-shaped structure are outer columns. The double-peak top cover structure adopted by the invention can improve the rigidity and the internal pressure resistance of the top cover, prevent the deformation problem of the top cover under the condition of high internal pressure, and further avoid a series of problems of propellant leakage, structural damage and the like.
The top cover 3 is provided with a radial window 7, so that devices such as an igniter and the like can be operated and installed conveniently, or a cable of the igniter and the like can be led out conveniently. The top cover 3 is provided with hoisting holes 8, the number of the hoisting holes is 2, and the hoisting holes are distributed at 180 degrees.
The invention adopts the integrated bearing flow equalizing top cover device, reduces the welding seam between the bearing seat and the top cover, and prevents the nozzle ablation problem caused by the uneven annular seam gap of the injector nozzle due to the influence of the heat input of the welding seam.
In the above three-component integrated nozzle assembly, the inlet section 2 gradually transitions from a circular cross section to an oblong cross section, as shown in fig. 3, the joint with the docking flange 1 is a circular cross section, and the cross section through the top cover 3 is an oblong cross section. The structure is convenient for flange butt joint on one hand, and on the other hand, the speed of fluid entering the top cover can be reduced, flow resistance loss is reduced, and uniformity of flow of each nozzle of the injector is improved. And the intersection of the inlet section and the top cover is provided with a fillet, and the diameter of the fillet is not less than 1-1.5 times of the wall thickness. The structure can ensure that the propellant smoothly enters the inner cavity of the top cover, and avoid forming obvious back step eddy current to cause higher local flow resistance loss.
In the three-component integrated nozzle assembly, the included angle between the axis of the inlet section 2 and the axis of the top cover 3 is 60-90 degrees; when the included angle between the axis of the inlet section 2 and the axis of the top cover is 90 degrees, the height of the double peaks is the same as or slightly higher than the axial height of the through circular cross section of the inlet section 2 and the top cover 3;
in the above three-component integrated nozzle assembly, the number of the inlet sections 2 is 1, two or more, and the inlet sections are uniformly distributed along the circumferential direction of the top cover 3;
in one of the three-component integrated nozzle assemblies described above, the propellant may be a gas or a liquid, wherein the gas flow rate does not exceed 150m/s when reaching the cross-sectional area through which the inlet section 2 and the cap 3 intersect; the liquid flow rate does not exceed 40m/s.
In the three-component integrated nozzle assembly, the wall thickness of the force bearing device 4 is about 2 to 2.5 times of that of the top cover 3;
in foretell three component integral type nozzle assembly, fairing 5 outer fringe and inner edge overlap joint respectively on top cap 3's outer side post inner wall and center post wall, by straightway + four circular arc sections + straightway, from being close to outer fringe department, straightway and outer side post inner wall overlap joint, back connection four circular arc sections, including transition circular arc, recessed circular arc 1, epirelief circular arc, recessed circular arc 2, link to each other with the center post wall through a straight line section at last, tangent between each circular arc, and R Concave 1 ：R Convex upward ：R Concave 2 1, the whole rectifying device is in a wide ring thin plate wavy structure. On the one hand, the flow uniformity of the incoming flow propellant entering the nozzle can be improved, on the other hand, the impact of the incoming flow propellant on the rectifying device at the upstream can be effectively resisted, and the structural damage caused by large displacement is avoided.
In the above-described three-component one-piece nozzle assembly, as shown in fig. 2, the number of the support ribs 6 is 6 or a multiple thereof, and the support ribs are mainly located on the upper side of the axial section of the flange, and the lower side is provided with only 1/6 of the total number of the support ribs directly below. The invention adopts a unique radial support rib structure, the support ribs are mainly positioned at the upper side of the axial section of the flange, and only one support rib is arranged right below the lower side of the axial section of the flange, so that the problem of overload damage caused by stress concentration due to over-support is prevented.
In the three-component integrated nozzle assembly, the integrated force-bearing flow equalizing device is integrally formed by 3D printing or powder metallurgy.
Claims (6)
1. The utility model provides an integral type load top cap device that flow equalizes which characterized in that: comprises a butt flange (1), an inlet section (2), a top cover (3), a force bearing device (4), a rectifying device (5) and a support rib (6);
the port of the butt flange (1) is a propellant inlet, the butt flange (1) is connected with the top cover (3) through the inlet section (2), radial support ribs (6) are arranged around the inlet section (2), and the support ribs (6) are respectively connected with the butt flange (1), the inlet section (2) and the top cover (3); the upper end of the top cover (3) is connected with a force bearing device (4) for transmitting thrust; the lower end of the top cover (3) is connected with a rectifying device (5) for ensuring that the propellant entering each nozzle is uniformly distributed; the cross section of the top cover (3) is bimodal, and the central concave cavity is a circular truncated cone-shaped platform with a central hole and is used for connecting and mounting an igniter; the top cover (3) is provided with a radial window (7) for operating and installing an igniter or leading out an igniter cable; the top cover (3) is also provided with a hoisting hole (8) for hoisting;
the inlet section (2) is gradually transited from a circular section to a long circular section, the joint with the butt flange (1) is the circular section, and the cross section of the inlet section and the top cover (3) is the long circular section; a fillet is arranged at the intersection of the inlet section (2) and the top cover (3), and the diameter of the fillet is 1 to 1.5 times of the wall thickness of the top cover (3);
the wall thickness of the force bearing device (4) is 2 to 2.5 times of that of the top cover (3);
the outer edge and the inner edge of the rectifying device (5) are respectively lapped on the inner wall of the outer side column and the wall surface of the central column of the top cover (3) and consist of a straight line segment, four arc segments and a straight line segment, the straight line segment is lapped with the inner wall of the outer side column from the position close to the outer edge, and the four arc segments are connected afterwards and comprise a transition arc, a lower concave arc 1, an upper convex arc and a lower concave arc 2Finally, is connected with the wall surface of the central column through a straight line segment, all arcs are tangent, and R Concave 1 ：R Convex upward ：R Concave 2 1, the whole rectifying device is in a wide ring thin plate wave type structure;
the number of the support ribs (6) is 6 or multiples thereof, the support ribs are mainly positioned on the upper side of the axial section of the butt flange and are radial, and the support ribs with the total support rib number of 1/6 are only arranged under the butt flange on the lower side of the axial section of the butt flange.
2. The integrated force-bearing flow-equalizing top cover device of claim 1, wherein: the included angle between the axis of the inlet section (2) and the axis of the top cover (3) is 60-90 degrees; and when the included angle between the axis of the inlet section (2) and the axis of the top cover is 90 degrees, the height of the double peaks is the same as or slightly higher than the axial height of the through round cross section of the inlet section (2) and the top cover (3).
3. The integrated force-bearing flow equalizing top cover device according to claim 1, characterized in that: the number of the inlet sections (2) is 1, two or more, and the inlet sections are uniformly distributed along the circumferential direction of the top cover (3).
4. The integrated force-bearing flow-equalizing top cover device of claim 1, wherein: the propellant is gas or liquid, wherein the gas flow rate does not exceed 150m/s when the gas reaches the cross section of the long circle which is intersected by the inlet section (2) and the top cover (3); the liquid flow rate does not exceed 40m/s.
5. The integrated force-bearing flow equalizing top cover device according to claim 1, characterized in that: the integrated force-bearing flow equalizing device is integrally formed by 3D printing or powder metallurgy.
6. The integrated force-bearing flow-equalizing top cover device of claim 1, wherein: the hoisting holes (8) arranged on the top cover (3) are 2 in number and are distributed at 180 degrees.
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| Application Number | Priority Date | Filing Date | Title |
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| CN202110997421.6A CN113738536B (en) | 2021-08-27 | 2021-08-27 | Integrated force-bearing flow-equalizing top cover device |
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| CN202110997421.6A CN113738536B (en) | 2021-08-27 | 2021-08-27 | Integrated force-bearing flow-equalizing top cover device |
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| CN113738536B true CN113738536B (en) | 2022-10-28 |
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| CN114412663B (en) * | 2021-12-23 | 2023-08-29 | 北京航天动力研究所 | Integrated liquid rocket engine thrust chamber top cover structure |
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| Publication number | Priority date | Publication date | Assignee | Title |
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| CN113006971A (en) * | 2021-03-11 | 2021-06-22 | 北京航天动力研究所 | Oxyhydrogen igniter adopting glow plug |
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| JPS58128443A (en) * | 1982-01-28 | 1983-08-01 | Nissan Motor Co Ltd | Method for charging propellant powder in solid rocket motor of direct charge type |
| CN108194204B (en) * | 2017-12-28 | 2020-03-03 | 西安航天动力研究所 | High-reliability integral injector |
| CN108915899B (en) * | 2018-06-29 | 2020-02-14 | 北京航天动力研究所 | Four-bottom three-cavity injector |
| CN110805506A (en) * | 2019-09-29 | 2020-02-18 | 北京航天动力研究所 | Combined combustion stabilizing device |
| CN212563480U (en) * | 2020-02-25 | 2021-02-19 | 星河动力(北京)空间科技有限公司 | Light quick mounting and connecting structure of engine |
| CN112746910A (en) * | 2020-10-29 | 2021-05-04 | 北京航天动力研究所 | Injector for inhibiting high-frequency unstable combustion |
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| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113006971A (en) * | 2021-03-11 | 2021-06-22 | 北京航天动力研究所 | Oxyhydrogen igniter adopting glow plug |
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