阅读说明：本技术 一种一体式承力均流顶盖装置 (Integrated force-bearing flow-equalizing top cover device ) 是由 刘倩 丁兆波 潘刚 王洋洲 张亚 孔维鹏 潘亮 孙纪国 郑孟伟 谢恒� 于 2021-08-27 设计创作，主要内容包括：一种一体式承力均流顶盖装置,包括对接法兰、入口段、顶盖、承力装置、整流装置、支撑肋；对接法兰端口为推进剂入口,对接法兰通过入口段与顶盖相连,入口段周围设置辐射状支撑肋,支撑肋分别连接对接法兰、入口段和顶盖；顶盖上端连接承力装置,用于推力传递；顶盖下端连接整流装置,用于保证进入各喷嘴的推进剂均匀分布；顶盖过轴线截面呈双峰型,中心凹腔为带中心孔的圆台形平台,用于点火器的连接和安装；顶盖上设置径向窗口,用于操作安装点火器或点火器电缆引出；顶盖上还设置有用于吊装的吊装孔。该一体式承力均流顶盖装置可承内压、可传推力、压力和流量分布均匀性高、一体成型无焊接。(An integrated force-bearing 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 truncated cone-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.)

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.

2. The integrated force-bearing flow-equalizing top cover device of claim 1, wherein: 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; and the intersection of the inlet section (2) and the top cover (3) is provided with a fillet, and the diameter of the fillet is 1-1.5 times of the wall thickness of the top cover (3).

3. 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).

4. The integrated force-bearing flow-equalizing top cover device of claim 1, wherein: 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).

5. 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 40 m/s.

6. The integrated force-bearing flow-equalizing top cover device of claim 1, wherein: the wall thickness of the bearing device (4) is 2-2.5 times of that of the top cover (3).

7. The integrated force-bearing flow-equalizing top cover device of claim 1, wherein: 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 are formed by straight connectionThe four-arc-section rear connection structure comprises a line section, four arc sections and a straight line section, wherein the straight line section is lapped with the inner wall of the outer side column from the position close to the outer edge, the four arc sections are connected with the rear end and comprise a transition arc, a concave arc 1, a convex arc and a concave arc 2, the four arc sections are connected with the wall surface of the center column through a straight line section, all arcs are tangent, and R is_{Concave 1}：R_{Convex upward}：R_{Concave 2}The whole rectifying device is in a wide ring thin plate wave type structure as 1:1: 5.

8. The integrated force-bearing flow-equalizing top cover device of claim 1, wherein: the number of the support ribs (6) 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 butt flange, and the support ribs with the total support rib number of 1/6 are only arranged on the lower side of the axial section of the butt flange right below the butt flange.

9. The integrated force-bearing flow-equalizing top cover device of claim 1, wherein: the integrated force-bearing flow equalizing device is integrally formed by 3D printing or powder metallurgy.

10. 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.

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 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 is to bear and transmit thrust in addition to bearing the liquid pressure 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 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 truncated cone-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 reaching the cross section of the long circle which is intersected with the inlet section and the top cover; the liquid flow rate does not exceed 40 m/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 outside post inner wall of top cap and center post wall, by straightway, four circular arc sections, straightway are constituteed, from being close to outer fringe department, straightway and outside 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 straight line section at last, tangent between each circular arc, and R_{Concave 1}：R_{Convex upward}：R_{Concave 2}The whole rectifying device is in a wide ring thin plate wave type structure as 1:1: 5.

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 support rib number of 1/6 are only arranged on the lower side of the axial section of the butting flange right below 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 whole wide ring sheet metal wavy structure that is of fairing of top cap low reaches installation 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 inflow propellant to fairing, avoids taking place great displacement and causes the structural damage.

Drawings

FIG. 1 is a schematic structural view of an integrated force-bearing flow-equalizing top cover device;

in the figure: 1-a butt flange; 2-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 bimodal 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 conveniently operated and installed, or an igniter cable and the like can be conveniently led out. 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 circumferential seam clearance 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 changes 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 connection 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 the uniformity of flow entering 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 40 m/s.

In the three-component integrated nozzle assembly, the wall thickness of the force bearing device 4 is about 2-2.5 times of that of the top cover 3;

in one three-component integrated nozzle assembly as described above, the fairing 5 is outer and innerThe edges are respectively lapped on the inner wall of the outer side column of the top cover 3 and the wall surface of the central column and are composed of a straight line segment, four circular 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, the four circular arc segments are connected afterwards and comprise a transition circular arc, a lower concave circular arc 1, an upper convex circular arc and a lower concave circular arc 2, the transition circular arc is connected with the wall surface of the central column through a straight line segment, the circular arcs are tangent to each other, and R is connected with the wall surface of the central column_{Concave 1}：R_{Convex upward}：R_{Concave 2}The whole rectifying device is in a wide ring thin plate wave type structure as 1:1: 5. 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 one of the three-component one-piece nozzle assemblies described above, 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 cross section of the flange, and the lower side is provided with 1/6 support ribs of the total number of support ribs only right 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.