Integrated partition plate for liquid rocket, liquid rocket engine and liquid rocket

Abstract

The utility model provides an integrated partition plate for a liquid rocket, a liquid rocket engine and the liquid rocket. The integrated partition plate comprises an outer shell, an inner circumferential plate arranged in the middle of the outer shell, a radial plate arranged between the inner circumferential plate and the outer shell and an upper end face fixed to the inner circumferential plate. The upper end surface of the inner circumferential plate can be connected with an injector; the outer wall of the outer shell can be tightly matched and connected with the inner wall of the combustion chamber; a radial liquid inlet is formed in the outer wall of the outer shell; a plurality of first flow pipes which flow in the axial direction are arranged in the plate wall of the radial plate in the radial direction, a plurality of second flow pipes which flow in the axial direction are arranged in the plate wall of the inner circumferential plate in the circumferential direction, the height of the solid partition plate penetrating into a combustion chamber is indirectly increased by arranging an inner flow pipe structure to generate liquid phase jet flow, and then partition liquid drainage is utilized; and meanwhile, 3D printing integrated forming is adopted, the problem that the manufacturing process and the structure are complex can be effectively solved, and the structural reliability is enhanced.

Description

TECHNICAL FIELD

[0001] The utility model relates to liquid rocket technical field, concretely relates to a kind of integrated bulkhead for liquid rocket, liquid rocket engine and liquid rocket. BACKGROUND

[0002] Liquid rocket engine injector design has the most significant and direct influence on high-frequency unstable combustion, especially for the combustion chamber diameter of medium thrust greater than 300mm, high-frequency unstable combustion is prone to occur, so when designing the injector, some special damping devices, such as bulkhead, need to be used. The bulkhead divides the thrust chamber injector into several small areas, which increases the acoustic vibration frequency near the injection surface, destroys the energy conditions of high-frequency unstable combustion, and thus suppresses unstable combustion. The traditional bulkhead structure has ablation bulkhead and regenerative cooling bulkhead. The ablation bulkhead is usually disposable and is burned out after one use, and cannot be used multiple times. The traditional regenerative cooling bulkhead is usually composed of multiple parts such as inner circle, reinforcing ribs, outer wall and corrugated plate, and needs to be connected by brazing. On the one hand, the process is complex, and there is a risk of leakage, blockage of internal channels and poor reliability. Moreover, due to the high temperature in the combustion chamber, the distance of the bulkhead extending out of the injector end surface is limited, and the effect of suppressing unstable combustion is also discounted.

[0003] In summary, the existing technology has the following problems: the liquid rocket engine injector has the problem of unstable combustion. INVENTION CONTENTS

[0004] The utility model provides a kind of integrated bulkhead for liquid rocket, liquid rocket engine and liquid rocket, and the technical problems solved are how to suppress the problem of unstable combustion of liquid rocket engine injector.

[0005] To achieve the above-mentioned purpose, on the one hand, the utility model provides an integrated bulkhead for liquid rocket, comprising:

[0006] an outer shell, an inner circumferential plate arranged in the outer shell, a radial plate arranged between the outer shell and the inner circumferential plate, and an upper end face fixed to the inner circumferential plate;

[0007] The radial plate extends along the radial direction of the outer shell and is arranged in intervals along the circumferential direction of the outer shell. One end of the radial plate is connected to the outer circumference of the inner circumferential plate, and the other end of the radial plate is connected to the inner wall of the outer shell. A radial through cavity is formed in one end of the plate wall of the radial plate close to the upper end face. The radial through cavity is arranged along the radial direction of the radial plate in the outer shell. A plurality of first flow tubes flowing in the axial direction are formed in the plate wall of the radial plate along the radial direction of the outer shell. The radial through cavity is connected to and communicates with the upper end of the first flow tube. The radial liquid inlet corresponds to and communicates with the radial through cavity.

[0008] A plurality of second flow tubes flowing in the axial direction are arranged in the plate wall of the inner circumferential plate in the circumferential direction, and an annular liquid collecting cavity is arranged in the plate wall of the inner circumferential plate, which is connected with and communicated with the upper ends of the second flow tubes; the annular liquid collecting cavity is communicated with the radial through cavity. The first flow tubes on the inner circumferential plate and the second flow tubes on the radial plate realize partitioned liquid discharge of the propellant into the combustion chamber, indirectly extend the height of the solid partition plate into the combustion chamber through liquid jet, and have a stronger inhibition effect on unstable combustion.

[0009] Specifically, the radial plate is provided with six radial plates which are uniformly distributed along the radial direction of the outer shell. The combustion chamber is divided into seven small areas, and reasonable partitioned liquid discharge is realized.

[0010] Specifically, a plurality of circumferential liquid inlets are arranged on the upper end face, and the circumferential liquid inlets are communicated with the second flow tubes.

[0011] Specifically, the circumferential liquid inlets are uniformly distributed on the upper end face.

[0012] Specifically, the upper end of the annular liquid collecting cavity is communicated with the circumferential liquid inlets, and the lower end of the annular liquid collecting cavity is communicated with the second flow tubes. This is beneficial to improve the uniformity of the fluid entering the flow tubes of the partition plate.

[0013] Specifically, the height of the radial plate and the height of the inner circumferential plate are both 90mm to 110mm, which is beneficial to improve the strength of the partition plate and reduce the weight. The plate wall of the radial plate is wave-shaped, and the plate wall of the inner circumferential plate is also wave-shaped. This is beneficial to heat exchange between the liquid in the flow tubes and the combustion gas in the combustion chamber, so as to better cool the partition plate.

[0014] Specifically, the diameter of the outer shell is 350mm to 420mm; the wall thickness of the plate wall of the radial plate is 1mm to 1.5mm; and the wall thickness of the plate wall of the inner circumferential plate is 1mm to 1.5mm. In this way, the strength of the integrated partition plate is well maintained, the reasonable weight of the integrated partition plate is ensured, and the risk of ablation of the outer surface is avoided.

[0015] Specifically, the radial liquid inlet and the circumferential liquid inlet are both communicated with the cavity between the inner wall and the outer wall of the combustion chamber.

[0016] On the other hand, the utility model provides a liquid rocket engine which is installed with the integrated partition plate for liquid rocket, the upper end face of the partition plate is used for being connected with the injector, the outer wall of the outer shell of the partition plate is used for being connected with the inner wall of the combustion chamber, and the outer wall of the outer shell is provided with a radial liquid inlet.

[0017] In still another aspect, the utility model provides a liquid rocket, which is installed with the liquid rocket engine.

[0018] The beneficial technical effects of the above technical scheme are that the utility model adds the structure of rowing, which extends the height of the baffle in a disguised way, makes up for the insufficient height of the original baffle extending from the injection surface, reduces the risk of ablation due to the baffle extending too high from the injection surface, and has better effect of inhibiting unstable combustion, and meets the needs of high-efficiency, reliable and stable combustion of the open cycle and closed cycle liquid oxygen kerosene rocket engine. BRIEF DESCRIPTION OF DRAWINGS

[0019] Figure 1 It is an isometric side partial sectional view structure schematic diagram of the integrated baffle for the liquid rocket according to the utility model embodiment;

[0020] Figure 2 It is a longitudinal sectional structure schematic diagram of the integrated baffle for the liquid rocket according to the utility model embodiment;

[0021] Figure 3 It is Figure 2 It is a structure diagram viewed from A direction;

[0022] Figure 4 It is a fluid flow schematic diagram in the liquid collecting cavity according to the utility model embodiment.

[0023] BRIEF DESCRIPTION OF DRAWINGS

[0024] 1, upper end face;2, radial plate;3, inner circumferential plate;4, outer cylindrical section;5, circumferential liquid inlet;6, radial liquid inlet;7, annular liquid collecting cavity;8, radial through cavity;9, outer shell;21, first flow pipe;22, radial plate wall;31, second flow pipe;32, inner circumferential plate wall. DETAILED DESCRIPTION

[0025] The technical scheme in the utility model embodiments will be apparently and completely described below with reference to the drawings in the utility model embodiments, and obviously, the described embodiments are only part of the embodiments of the utility model, rather than all the embodiments. Based on the embodiments in the utility model, all other embodiments obtained by the person skilled in the art without creative labor fall within the protection scope of the utility model.

[0026] The utility model embodiment provides an integrated baffle for liquid rocket, such as Figure 1As shown, it comprises: an outer shell 9, an inner circumferential plate 3 arranged in the outer shell 9, a radial plate 2 arranged between the outer shell 9 and the inner circumferential plate 3, and an upper end face 1 fixed on the inner circumferential plate 3; the upper end face 1 can be connected with an injector; the outer wall of the outer shell 9 can be tightly matched and connected with the inner wall of the combustion chamber, preferably, the outer wall of the outer shell 9 can be sealingly matched with the inner wall of the combustion chamber; the outer wall of the outer shell 9 is provided with a radial liquid inlet 6; preferably, the upper end face 1 is welded with the injector; wherein, the upper end face 1 is provided with a plurality of circumferential liquid inlets 5, and the circumferential liquid inlets 5 are communicated with the second flow pipes 31. The circumferential liquid inlets 5 are uniformly distributed on the upper end face 1.

[0027] The radial plate 2 is provided with six radial plates and is uniformly distributed along the radial direction of the outer shell 9, and the radial plate 2 divides the combustion chamber into seven small areas in total, six areas are circumferentially distributed, and one area is in the middle. Reasonable partition and liquid discharge realize the partitioned discharge of propellant into the combustion chamber. One end of the radial plate 2 is connected with the outer circumference of the inner circumferential plate 3, and the other end of the radial plate 2 is connected with the inner wall of the outer shell 9; the intersection of the outer wall of the radial plate 2 and the outer wall of the inner circumferential plate 3 adopts a circular arc transition, and the intersection of the outer wall of the radial plate 2 and the outer cylindrical segment of the outer shell 9 also selects a circular arc transition, which effectively improves the mechanical environmental adaptability of the partition plate.

[0028] The radial plate 2 is provided with a radial through cavity 8 in the plate wall along the length direction of the radial plate 2, and a plurality of first flow pipes 21 are arranged in the plate wall along the width direction of the radial plate 2, and the radial through cavity 8 is connected and communicated with the upper end of the first flow pipe 21. Figure 2 As shown, the radial liquid inlet 6 corresponds to and communicates with the radial through cavity 8; each radial through cavity 8 is connected with the radial liquid inlet 6 and communicated with the first flow pipe 21, and the radial entering propellant can be dispersed into the radial partition plate flow pipe (first flow pipe 21) and discharged into the combustion chamber.

[0029] The plate wall of the inner circumferential plate 3 is provided with a plurality of second flow pipes 31 along the circumferential direction, the extension direction of the second flow pipe 31 is parallel to the axial direction of the second flow pipe 31, the plate wall of the inner circumferential plate 3 is provided with an annular liquid collecting cavity 7, the annular liquid collecting cavity 7 is connected and communicated with the upper end of the second flow pipe 31; the annular liquid collecting cavity 7 is communicated with the radial through cavity 8. The top end of the inner circumferential plate 3 is provided with the annular liquid collecting cavity 7, and the annular liquid collecting cavity 7 is respectively communicated with the circumferential liquid inlet 5 and the second flow pipe 31, so that the propellant entering from the circumferential liquid inlet 5 can be dispersed into the second flow pipe 31 (circumferential partition plate flow pipe) and discharged into the combustion chamber. The upper end of the annular liquid collecting cavity 7 is communicated with the circumferential liquid inlet 5, and the lower end of the annular liquid collecting cavity 7 is communicated with the second flow pipe 31, which is conducive to improving the uniformity of the fluid entering the flow pipes of the partition plate.

[0030] The diameter of the outer shell 9 is 350mm-420mm; preferably, the diameter of the outer shell 9 is 400mm. The height of the inner circumferential plate 3 is 90mm-110mm, the height of the radial plate 2 is 90mm-110mm, and the height of the inner circumferential plate 3 is the same as that of the radial plate 2. The risk of burning due to the too high partition plate is reduced, while the effect of inhibiting unstable combustion is ensured. The wall thickness of the radial plate 2 is 1mm-1.5mm; the wall thickness of the inner circumferential plate 3 is 1mm-1.5mm. In this way, the strength of the integrated partition plate is well maintained, while the reasonable weight of the integrated partition plate is ensured, and the risk of ablation of the outer surface is avoided. The wall of the inner circumferential plate 3 and the wall of the radial plate 2 are wavy. On the one hand, it is beneficial to improve the strength of the partition plate and can reduce the weight; on the other hand, it is beneficial to heat exchange between the liquid in the flow pipe and the gas in the combustion chamber, so as to better cool the partition plate;

[0031] The radial liquid inlet 6 and the circumferential liquid inlet 5 are both communicated with the cavity between the inner wall and the outer wall of the combustion chamber. The propellant flows from the cavity of the combustion chamber to the injection disc (injector) above, the propellant enters the circumferential liquid inlet 5 on the upper end face 1 from the annular cavity above the injection disc, and then flows into the annular liquid collecting cavity 7, and then the propellant is discharged by the integrated partition plate through the second flow pipe 31; in addition, as shown, the propellant flows from the cavity of the combustion chamber to the radial liquid inlet 6, and then enters the radial through cavity 8 from the radial liquid inlet 6, and then is discharged by the integrated partition plate through the first flow pipe 21. By partitioning the liquid in the combustion chamber, the height of the solid partition plate into the combustion chamber is indirectly extended by the liquid jet, and the inhibition effect of unstable combustion is stronger. Figure 4

[0032] The utility model embodiment provides a kind of integrated partition plate for liquid rocket, integrated partition plate is used for the engine of liquid rocket, as shown in figure, Figure 3 The integrated partition plate structure of the utility model is 3D printing integrated partition plate, one week six radial structure, end face and lateral liquid inlet, liquid is discharged by injector to combustion chamber by the flow pipe structure arranged circumferentially and radially of partition plate, the height of partition plate is extended by liquid jet wall, the deficiency of traditional partition plate to extend the distance of injector end face is made up, and high-frequency unstable combustion is effectively inhibited. Meanwhile, the partition plate structure is novel, and the integration degree is high, and the structure is simple and compact, reduces the manufacturing process of multiple parts, reduces cost, effectively improves reliability.

[0033] As shown in figure, Figure 1 A kind of integrated partition plate for liquid rocket includes: one upper end face 1, six radial plates 2, one inner circumferential plate 3 and outer shell 9;

[0034] ​The outer shell 9 has an outer cylindrical section 4; the upper end surface 1 of the inner circumferential plate 3 is connected to the thrust chamber injector by brazing, and a plurality of circumferential liquid inlets 5 are arranged on the upper end surface 1; the outer cylindrical section 4 is connected to the thrust chamber combustion chamber by oxygen arc welding, and six radial liquid inlets 6 (radial partition liquid inlets) are arranged on the side of the integrated partition;

[0035] The radial plate 2 comprises a first flow pipe 21 arranged in a radial plate wall 22; similarly, the inner circumferential plate 3 comprises a second flow pipe 31 (circumferential partition flow pipe) arranged inside an inner circumferential plate wall 32; the radial plate 2 is provided with radial through cavities 8, each of which is connected to the radial partition liquid inlet (radial liquid inlet 6) and in communication with the first flow pipe 21, so that the propellant entering radially can be dispersed into the first flow pipe 21 and discharged into the combustion chamber;

[0036] The top of the inner circumferential plate 3 is provided with an annular liquid collecting cavity 7, which is in communication with the circumferential liquid inlet 5 and the circumferential second flow pipe 31 respectively, so that the propellant entering through the circumferential liquid inlet 5 can be dispersed into the second flow pipe 31 and discharged into the combustion chamber; each radial through cavity 8 is in communication with the annular liquid collecting cavity 7 of the circumferential partition, which is conducive to improving the uniformity of the fluid entering each flow pipe of the partition.

[0037] Preferably, the inner circumferential plate wall 32 and the radial plate wall 22 are designed in a wavy shape, which is conducive to improving the strength of the partition and reducing the weight; on the other hand, it is conducive to heat exchange between the liquid in the flow pipe and the gas in the combustion chamber, so as to better cool the partition;

[0038] According to the actual verification results, the wall thickness of the radial plate wall 22 and the inner circumferential plate wall 32 is generally selected to be 1mm-1.5mm; in this way, the strength of the integrated partition is well maintained, while the reasonable weight of the integrated partition is ensured, and the risk of ablation of the outer surface is avoided.

[0039] The height of the radial plate 2 and the inner circumferential plate 3 can be generally selected to be 90mm-110mm, which is conducive to improving the strength of the partition and reducing the weight; the diameter of the outer shell 9 is 400mm.

[0040] Preferably, a circular arc transition is adopted at the intersection of the radial partition outer wall and the circumferential partition outer wall, and a circular arc transition is also selected at the intersection of the radial partition outer wall and the outer cylindrical section, which effectively improves the mechanical environmental adaptability of the partition; further, the material of the integrated partition based on 3D printing can be selected from stainless steel, GH4169 and copper alloy, etc.

[0041] In another aspect, the utility model provides a kind of liquid rocket engine, it is installed with above-mentioned a kind of liquid rocket integrated partition.Effective inhibition high-frequency unstable combustion.Simultaneously, integrated partition structure is novel, integration degree is high, structure is simple, compact, reduce the manufacturing process of multiple parts, reduce cost, effectively improve reliability.

[0042] In another aspect, the utility model provides a kind of liquid rocket, it is installed with above-mentioned a kind of liquid rocket engine.Effective inhibition high-frequency unstable combustion.

[0043] The utility model adopts stainless steel or GH4169 etc high-temperature alloy steel 3D printing integrated processing, has simplified partition design, cancelled brazing, avoided propellant outward leakage, can effectively improve manufacturing process and the problem of complex structure, greatly improve the reliability of partition structure.Increase the structure of discharge, the height of partition is indirectly lengthened, make up the height deficiency of original partition protruding injection surface.Reduce the risk of being ablated because of partition protruding injection surface too high, the effect of inhibiting unstable combustion is better.

[0044] The above-mentioned is only the specific embodiment of the utility model schematically, and is not used to limit the range of the utility model.Each component of the utility model can be combined mutually under the condition of not conflict, any equivalent change and modification made by any person skilled in the art without departing from the concept and principle of the utility model should belong to the range of the utility model protection.

Claims

1. An integrated bulkhead for liquid rockets, characterized by, It comprises: an outer shell (9), an inner circumferential plate (3) arranged in the outer shell (9), a radial plate (2) arranged between the outer shell (9) and the inner circumferential plate (3), and an upper end face (1) fixed on the inner circumferential plate (3); the radial plate (2) extends along the radial direction of the outer shell (9) and is arranged at intervals along the circumferential direction of the outer shell (9), one end of the radial plate (2) is connected with the outer circumference of the inner circumferential plate (3), and the other end of the radial plate (2) is connected with the inner wall of the outer shell (9); a radial through cavity (8) is formed in one end of the plate wall of the radial plate (2) close to the upper end face (1), the radial through cavity (8) is arranged along the radial direction of the outer shell (9) on the radial plate (2), a plurality of first flow pipes (21) flowing in the axial direction are formed in the plate wall of the radial plate (2) along the radial direction of the outer shell (9), the radial through cavity (8) is connected with and communicates with the upper end of the first flow pipe (21); a radial liquid inlet (6) corresponds to and communicates with the radial through cavity (8); a plurality of second flow pipes (31) flowing in the axial direction are formed in the plate wall of the inner circumferential plate (3) along the circumferential direction, an annular liquid collecting cavity (7) is arranged in the plate wall of the inner circumferential plate (3), the annular liquid collecting cavity (7) is connected with and communicates with the upper end of the second flow pipe (31); the annular liquid collecting cavity (7) communicates with the radial through cavity (8).

2. The integrated bulkhead for liquid rockets as claimed in claim 1, wherein The radial plate (2) is provided with six radial plates and is uniformly distributed along the radial direction of the outer shell (9).

3. The integrated bulkhead for liquid rockets of claim 1, wherein A plurality of circumferential liquid inlets (5) are arranged on the upper end face (1), and the circumferential liquid inlets (5) communicate with the second flow pipes (31).

4. The integrated bulkhead for liquid rockets as claimed in claim 3, wherein The circumferential liquid inlets (5) are uniformly distributed on the upper end face (1).

5. The integrated bulkhead for liquid rockets as claimed in claim 3, wherein The upper end of the annular liquid collecting cavity (7) communicates with the circumferential liquid inlets (5), and the lower end of the annular liquid collecting cavity (7) communicates with the second flow pipes (31).

6. The integrated bulkhead of claim 1, wherein The height of the radial plate (2) and the height of the inner circumferential plate (3) are both 90mm-110mm, the plate wall of the radial plate (2) is wavy, and the plate wall of the inner circumferential plate (3) is also wavy.

7. The integrated bulkhead of claim 1, wherein The diameter of the outer shell (9) is 350mm-420mm; the wall thickness of the plate wall of the radial plate (2) is 1mm-1.5mm; and the wall thickness of the plate wall of the inner circumferential plate (3) is 1mm-1.5mm.

8. The integrated bulkhead for liquid rockets of claim 5, wherein The radial liquid inlet (6) and the circumferential liquid inlet (5) both communicate with the cavity between the inner wall and the outer wall of the combustion chamber.

9. A liquid rocket engine, characterized in that It is installed with the integrated baffle for liquid rocket engine according to any one of claims 1-8; The upper end face (1) of the baffle is used for being connected with an injector, the outer wall of the outer shell (9) of the baffle is used for being connected with the inner wall of a combustion chamber, and the outer wall of the outer shell (9) is provided with a radial liquid inlet (6).

10. A liquid rocket, characterized in that, It is installed with the liquid rocket engine according to claim 9.

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