Heat exchanger integrated with pre-combustion chamber, rocket engine and rocket

Abstract

The invention discloses a heat exchanger integrally designed with a pre-combustion chamber, a rocket engine and a rocket, and belongs to the technical field of rocket engine heat exchange, the heat exchanger comprises a pre-combustion chamber shell, turbine stator blades are arranged on the inner wall of the pre-combustion chamber shell, and a gas collection structure is arranged on the outer wall of the pre-combustion chamber shell; a reinforcing rib structure is arranged in an inner cavity of the pre-combustion chamber shell, a heat exchange medium inlet is formed in the upper portion of the outer wall of the pre-combustion chamber shell, and a heat exchange medium outlet is formed in the outer wall of the gas collection structure. And communicated heat exchange medium circulation channels are arranged in the side wall of the pre-combustion chamber shell, the turbine stator blades and the reinforcing rib structures. The rocket engine comprises the heat exchanger integrated with the pre-combustion chamber, and the rocket comprises the rocket engine. The machining cost is reduced, the machining period is shortened, the working procedures of groove milling, brazing, gas collection cavity ring belt welding and the like in traditional machining are avoided, the structural utilization rate is increased, the structural weight of an engine is effectively reduced, the rocket pressurization requirement can be met, and the use stability and reliability are improved.

Description

Technical Field

[0001] The invention relates to the technical field of rocket engine heat exchange, and in particular to a heat exchanger, a rocket engine and a rocket that are integrated with a precombustion chamber. Background Art

[0002] The liquid rocket engine heat exchanger is the core component in the rocket's booster system. When the engine is working, it continuously supplies pressurized gas to the air cushion of the rocket tank to ensure the propellant supply pressure required for the normal operation of the engine. For example, the Chinese patent application number is: 201910881056.5, and the patent name is: A rocket engine heat exchanger and a spacecraft.

[0003] In the process of realizing the above invention, the inventors found that there are at least the following problems in the prior art: although it can meet the general use requirements, it mostly adopts a brazing milling groove structure, and it is also necessary to weld collector rings, inlet and outlet nozzles and other parts. It not only has many processing steps, high processing costs, and long processing cycles, but also it is separated from the pre-combustion chamber and is also restricted by the layout of the gas duct. It does not have the conditions for large-scale adjustment of the heat exchange channel and heat exchange area, which will affect the heat exchange efficiency and heat exchange stability and reliability. Summary of the invention

[0004] In view of this, the purpose of the embodiments of the present invention is to provide a heat exchanger, a rocket engine and a rocket that are integrated with a precombustion chamber and have a reasonable structural arrangement and are conducive to improving heat exchange efficiency and stability.

[0005] To achieve the above-mentioned purpose, in a first aspect, an embodiment of the present invention provides a heat exchanger integrated with a pre-combustion chamber, comprising a pre-combustion chamber housing, a plurality of turbine stator blades are integrally formed on the inner wall of the pre-combustion chamber housing, and an air collecting structure is integrally formed on the outer wall of the pre-combustion chamber housing; A reinforcing rib structure is integrally formed in the inner cavity of the pre-combustion chamber shell, and the reinforcing rib structure is connected to the turbine stator blades and the air collecting structure; A heat exchange medium inlet is provided on the upper portion of the outer wall of the pre-combustion chamber shell, and a heat exchange medium outlet is provided on the outer wall of the gas collecting structure; The side wall of the pre-combustion chamber shell, the turbine stator blades and the reinforcing rib structure are provided with interconnected heat exchange medium flow channels; The heat exchange medium inlet is arranged at the inlet end of the heat exchange medium circulation channel, and the gas collecting structure is located at the outlet end of the heat exchange medium circulation channel.

[0006] It is further preferred that: the heat exchange medium circulation channel includes a first heat exchange medium circulation channel, a second heat exchange medium circulation channel and a reinforcing rib section channel; The first heat exchange medium flow channel is located in the side wall of the pre-combustion chamber shell; The second heat exchange medium circulation channel is located in the turbine stator blade, and one end of the second heat exchange medium circulation channel is connected to the bottom end of the first heat exchange medium circulation channel; The reinforcing rib section channel is arranged in the reinforcing rib structure and is connected to the first heat exchange medium circulation channel and the second heat exchange medium circulation channel; The heat exchange medium inlet is communicated with the top end of the first heat exchange medium circulation channel.

[0007] It is further preferred that: the reinforcing rib structure comprises a plurality of inclined ribs and a plurality of transverse ribs; The transverse ribs correspond to the inclined ribs one by one, and one end of the transverse ribs is fixed to the upper part of the inclined ribs, and the other end of the transverse ribs is fixed to the inner wall of the pre-combustion chamber shell and is located on the inner side of the gas collecting structure; The bottom end of the inclined rib is fixed to the end of the turbine stator blade through a vertical rib.

[0008] It is further preferred that: the reinforcing rib section channel includes a third heat exchange medium circulation channel and a fourth heat exchange medium circulation channel; The third heat exchange medium circulation channel is located within the inclined ribs and the vertical ribs, and the bottom end of the third heat exchange medium circulation channel is connected to the other end of the second heat exchange medium circulation channel; The fourth heat exchange medium circulation channel is located in the transverse ribs, one end of the fourth heat exchange medium circulation channel is connected to the top end of the third heat exchange medium circulation channel, and the other end of the fourth heat exchange medium circulation channel is connected to the gas collecting structure.

[0009] It is further preferred that: the first heat exchange medium flow channel is a spiral tube flow channel.

[0010] More preferably, the top ends of all the inclined ribs are integrally formed into a whole.

[0011] More preferably, the plan view structure of the plurality of transverse ribs is in a Y-shape, a cross-shape, a U-shape or a M-shape.

[0012] Further preferably, the gas collecting structure is an annular protrusion radially arranged on the outer wall of the pre-combustion chamber shell, and an annular gas collecting cavity is arranged in the annular protrusion; The end of the fourth heat exchange medium flow channel is connected to the annular gas collecting cavity; The heat exchange medium outlet is communicated with the annular gas collecting cavity, and the heat exchange medium outlet is used for the heat exchange medium to flow out after being heated.

[0013] Further preferably, the heat exchange medium at the heat exchange medium inlet is liquid oxygen, liquid nitrogen, methane or helium.

[0014] It is further preferred that: a gas inlet is provided at the top end of the pre-combustion chamber shell, and a gas outlet is provided at the bottom end of the pre-combustion chamber shell; The turbine stator blades are located in the gas outlet.

[0015] It is further preferred that: a cavitation tube for adjusting the incoming flow rate is provided at the inlet position of the heat exchange medium.

[0016] It is further preferred that: a throttle ring for adjusting the pressure of the pressurized medium is provided at the outlet position of the heat exchange medium.

[0017] In a second aspect, the present invention provides a rocket engine, comprising the above-mentioned heat exchanger integrated with the pre-combustion chamber.

[0018] In a third aspect, the present invention also provides a rocket, comprising the above-mentioned rocket engine.

[0019] The above technical solution has the following beneficial technical effects: 1. The structure of the present invention is reasonable. The pre-combustion chamber shell, turbine stator blades, gas collection structure and reinforcing rib structure are integrally formed, which can reduce the difficulty and process of processing, thereby reducing the processing cost and shortening the processing cycle. It also avoids the milling, brazing, welding of the gas collection cavity ring belt and other processes in traditional processing. In addition, the integrated design improves the structural utilization rate, effectively reduces the weight of the engine structure, can meet the rocket supercharging requirements, and improves the stability and reliability of use. 2. A heat exchange medium inlet is provided on the upper part of the outer wall of the precombustion chamber shell, and a heat exchange medium outlet is provided on the outer wall of the gas collecting structure; interconnected heat exchange medium flow channels are provided in the side wall of the precombustion chamber shell, the turbine stator blades and the reinforcing rib structure. The above structure is conducive to improving the heat exchange efficiency and stability, and is also conducive to reducing the number of components compared to the traditional liquid rocket engine with independently arranged heat exchanger components, thereby improving the inherent reliability of the engine; 3. The reinforcing rib structure includes a number of inclined ribs and a number of transverse ribs, which can not only achieve the purpose of strengthening the connection, thereby improving the stability and reliability of the overall structure, but also facilitate the setting of interconnected heat exchange medium flow channels to ensure the effectiveness and continuous stability of heat exchange; 4. The heat exchange medium flow channel includes a first heat exchange medium flow channel, a second heat exchange medium flow channel, a third heat exchange medium flow channel and a fourth heat exchange medium flow channel, and the second heat exchange medium flow channel is located in the turbine stator blade, the third heat exchange medium flow channel is located in the inclined ribs and the vertical ribs, and the fourth heat exchange medium flow channel is located in the transverse ribs. The above structure is the first application of setting a heat exchange cooling channel in the turbine stator blade of a liquid rocket engine, which can effectively reduce the temperature of the turbine stator blade during the operation of the engine, reduce the temperature resistance requirements of the raw materials of the turbine stator blade, and improve the working reliability and effectiveness of the turbine stator blade; 5. The first heat exchange medium flow channel is a spiral tube flow channel, which can increase the contact area of ​​heat exchange, improve the effectiveness and reliability of heat exchange, and improve the efficiency of heat exchange; 6. The top view structure of the transverse ribs is in the shape of a Y, a cross, a large letter or a cross. The above structure can increase the contact area of ​​heat exchange, improve the effectiveness and stability of heat exchange; 7. The gas collecting structure is an annular protrusion, and an annular gas collecting cavity is arranged inside the annular protrusion, which is conducive to reducing the welding process of the collector ring belt, improving the processing efficiency, and also improving the effectiveness of heat exchange; 8. The outer wall bottom of the pre-combustion chamber shell is integrally formed with a mounting lug with a hole, which is convenient for the installation and fixation of the overall structure, reduces the difficulty of assembly, and improves the stability and reliability of assembly and use; 9. A cavitation tube for adjusting the incoming flow is provided at the inlet of the heat exchange medium, which facilitates the regulation and control of the incoming flow of the heat exchange medium. A throttle ring for adjusting the pressure of the pressurized medium is provided at the outlet of the heat exchange medium to meet the pressurization requirements of the rocket tank. BRIEF DESCRIPTION OF THE DRAWINGS

[0020] In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings required for use in the embodiments or the description of the prior art will be briefly introduced below. Obviously, the drawings described below are only some embodiments of the present invention. For ordinary technicians in this field, other drawings can be obtained based on these drawings without paying creative work.

[0021] Figure 1 is a schematic cross-sectional view of an embodiment of the present invention; Figure 2 It is a schematic diagram of a top view of the structure of an embodiment of the present invention; Figure 3 A schematic diagram of the specific structure of a turbine stator blade in an embodiment of the present invention; Figure 4 for Figure 1 The enlarged structural diagram at A in the middle; Figure 5for Figure 1 Enlarged structural diagram at B in the middle.

[0022] Description of reference numerals: 1. Pre-combustion chamber shell; 2. Turbine stator blades; 3. Gas collecting structure; 4. Reinforcement rib structure; 5. Heat exchange medium inlet; 6. Heat exchange medium outlet; 7. Heat exchange medium flow channel; 8. Mounting lug with holes; 9. Gas inlet; 10. Gas outlet; 31. annular protrusion; 32. annular gas collecting cavity; 41. inclined ribs; 42. transverse ribs; 43. vertical ribs; 71. First heat exchange medium circulation channel; 72. Second heat exchange medium circulation channel; 73. Third heat exchange medium circulation channel; 74. Fourth heat exchange medium circulation channel. DETAILED DESCRIPTION

[0023] The features and exemplary embodiments of various aspects of the present invention will be described in detail below. In the detailed description below, many specific details are proposed in order to provide a comprehensive understanding of the present invention. However, it is obvious to those skilled in the art that the present invention can be implemented without some of these specific details. The following description of the embodiments is only to provide a better understanding of the present invention by illustrating examples of the present invention. In the drawings and the following description, at least part of the known structures and technologies are not shown in order to avoid unnecessary ambiguity of the present invention; and, for clarity, the size of some structures may be exaggerated. In addition, the features, structures or characteristics described below may be combined in one or more embodiments in any suitable manner.

[0024] like Figures 1 to 5 As shown, a heat exchanger with an integrated precombustion chamber design comprises a precombustion chamber shell 1, the inner wall of the precombustion chamber shell 1 is integrally formed with a plurality of turbine stator blades 2, and the outer wall of the precombustion chamber shell 1 is integrally formed with an air collecting structure 3; in this embodiment, the precombustion chamber shell 1 is a conventional structure of the prior art, which is simply applied, specifically, it is a circular ring structure, the turbine stator blades 2 are a conventional structure of the prior art, which is simply applied, so they are not recorded in detail, the above three structures are integrally formed, thereby improving the structural utilization rate and effectively reducing the weight of the engine structure, and the air collecting structure 3 is an annular protrusion 31 radially arranged on the outer wall of the precombustion chamber shell 1, and an annular air collecting cavity 32 is arranged in the annular protrusion 31; the processes such as welding the air collecting cavity ring belt are reduced, and the stability of the overall structure can also be improved.

[0025] like Figure 1 , Figure 2 , Figure 4 and Figure 5As shown, a reinforcing rib structure 4 is integrally formed in the inner cavity of the pre-combustion chamber shell 1, and the reinforcing rib structure 4 is connected to the turbine stator blades 2 and the air collecting structure 3; during processing, the reinforcing rib structure 4 includes a plurality of inclined ribs 41 and a plurality of transverse ribs 42; the transverse ribs 42 correspond to the inclined ribs 41 one by one, and one end of the transverse rib 42 is fixed to the upper part of the inclined rib 41, and the other end of the transverse rib 42 is fixed to the inner wall of the pre-combustion chamber shell 1 and is located on the inner side of the air collecting structure 3; the bottom end of the inclined rib 41 is fixed to the end of the turbine stator blade 2 through the vertical rib 43. Through the above structure, the vertical ribs 43 mainly connect the turbine stator and the guide cone to bear the force and transfer the load; secondly, there are cooling channels inside, which can increase the contact area of ​​heat exchange, thereby improving the heat exchange efficiency and stability, and it can also be required to make the top view structure of several of the transverse ribs 42 Y-shaped, cross-shaped, large-shaped or cross-shaped, or other shapes that radiate from the center point to the circumference. In this way, the number of heat exchange medium flow channels 7 in the inclined ribs 41 and the transverse ribs 42 can be increased, the heat exchange efficiency can be improved, and the use requirements of different situations can be met.

[0026] like Figure 1 and Figure 2 As shown, a heat exchange medium inlet 5 is provided on the upper part of the outer wall of the pre-combustion chamber shell 1, and a heat exchange medium outlet 6 is provided on the outer wall of the gas collecting structure 3; the heat exchange medium of the heat exchange medium inlet 5 is liquid oxygen, liquid nitrogen, methane or helium. In addition, a heat exchange medium flow channel 7 is provided in communication with each other in the side wall of the pre-combustion chamber shell 1, the turbine stator blades 2 and the reinforcing rib structure 4; the heat exchange medium inlet 5 is provided at the entrance end of the heat exchange medium flow channel 7, and the gas collecting structure 3 is at the outlet end of the heat exchange medium flow channel 7. The heat exchange medium self-pressurization method is adopted, and the heat exchange medium is introduced from the heat exchange medium inlet 5, which can reduce the traditional helium pressurization medium supply system, effectively simplify and reduce the configuration of the rocket pressurization system, reduce the overall structural mass, and improve the working reliability. In addition, in the actual application process, it can also process the aperture and length of different heat exchange medium flow channels 7 during processing, so as to achieve the adjustment of different heat exchange areas and meet the requirements of different heat exchange performances.

[0027] In order to facilitate the adjustment and increase of the pressure of the heat exchange medium, a cavitation tube for adjusting the incoming flow is provided at the heat exchange medium inlet 5, which is convenient for adjusting and controlling the incoming flow of the heat exchange medium, and a throttle ring for adjusting the pressure of the pressurized medium is provided at the heat exchange medium outlet 6. The cavitation tube and the throttle ring are conventional structures of the prior art, which are simply applied, so they are not shown in the figure. The above structure can meet the pressurization requirements of the rocket tank.

[0028] like Figure 1 , Figure 2 and Figure 3 As shown, the heat exchange medium circulation channel 7 includes a first heat exchange medium circulation channel 71, a second heat exchange medium circulation channel 72 and a reinforcing rib section channel, and its shape matches the reinforcing rib structure. Specifically, the reinforcing rib section channel includes a third heat exchange medium circulation channel 73 and a fourth heat exchange medium circulation channel 74; wherein, the first heat exchange medium circulation channel 71 is located in the side wall of the pre-combustion chamber shell 1; the second heat exchange medium circulation channel 72 is located in the turbine stator blade 2, and one end of the second heat exchange medium circulation channel 72 is connected to the bottom end of the first heat exchange medium circulation channel 71; the second heat exchange medium circulation channel 72 is located in the turbine stator blade 2, and one end of the second heat exchange medium circulation channel 72 is connected to the bottom end of the first heat exchange medium circulation channel 71; The third heat exchange medium circulation channel 73 is located in the inclined rib 41 and the vertical rib 43, and the bottom end of the third heat exchange medium circulation channel 73 is connected to the other end of the second heat exchange medium circulation channel 72; the fourth heat exchange medium circulation channel 74 is located in the transverse rib 42, and one end of the fourth heat exchange medium circulation channel 74 is connected to the top of the third heat exchange medium circulation channel 73, and the other end of the fourth heat exchange medium circulation channel 74 is connected to the gas collecting structure 3; the heat exchange medium inlet 5 is connected to the top of the first heat exchange medium circulation channel 71.

[0029] When in use, the heat exchange medium enters through the heat exchange medium inlet 5, and passes through the first heat exchange medium circulation channel 71, the second heat exchange medium circulation channel 72, the third heat exchange medium circulation channel 73 and the fourth heat exchange medium circulation channel 74 in sequence, and then enters the gas collecting structure 3, and is discharged outward through the heat exchange medium outlet 6. The heat exchange operation is realized through the first heat exchange medium circulation channel 71, the second heat exchange medium circulation channel 72, the third heat exchange medium circulation channel 73 and the fourth heat exchange medium circulation channel 74, and the heat exchange and cooling effect of the heat exchange medium is achieved. In addition, the diameters of different sections can be the same or different according to actual needs.

[0030] In addition, the second heat exchange medium flow channel 72 is located in the turbine stator blade 2, which is the first application of setting a cooling heat exchange channel in the turbine stator blade 2 of a liquid rocket engine. It can effectively reduce the temperature of the turbine stator blade 2 during engine operation, reduce the temperature resistance requirements of the raw materials of the turbine stator blade 2, and improve the working reliability of the turbine stator blade 2.

[0031] The third heat exchange medium circulation channel 73 is located in the inclined ribs 41 and the vertical ribs 43, and the fourth heat exchange medium circulation channel 74 is located in the transverse ribs 42. This can cool the guide structure while exchanging heat, thereby improving stability and reliability in use.

[0032] like Figure 1As shown, the first heat exchange medium flow channel 71 is a spiral tube flow channel. It can be a regular or irregular spiral tube flow channel, which is beneficial to increase the heat exchange contact area and improve the heat exchange efficiency and effectiveness.

[0033] like Figure 1 As shown, the top ends of all the inclined ribs 41 are integrally formed into a whole. Through the above structure, the stability and reliability of the overall structure can be improved.

[0034] And, if Figure 1 As shown, the end of the fourth heat exchange medium flow channel 74 is connected to the annular gas collecting chamber 32; the heat exchange medium outlet 6 is connected to the annular gas collecting chamber 32, and the heat exchange medium outlet 6 is used for the heat exchange medium to flow out after heating. The annular gas collecting chamber 32 can collect the heat exchange medium and discharge it outward from the heat exchange medium outlet 6, thereby improving the stability and reliability of use.

[0035] like Figure 1 As shown, the bottom of the outer wall of the pre-combustion chamber housing 1 is integrally formed with a mounting lug 8 with a hole. The top of the pre-combustion chamber housing 1 is provided with a gas inlet 9, and the bottom of the pre-combustion chamber housing 1 is provided with a gas outlet 10; the turbine stator blades 2 are located in the gas outlet 10. This makes it easier to install and fix the overall structure, reduces the difficulty of assembly, and improves the stability and reliability of assembly and use.

[0036] This embodiment has passed the ground engine hot test and TL-2 rocket flight test. Its performance meets the rocket pressurization requirements and is the first engineering application in the field of liquid rocket engines.

[0037] In another embodiment, a rocket engine is provided, comprising the above-mentioned heat exchanger integrated with the pre-combustion chamber.

[0038] In yet another embodiment, a rocket is also provided, comprising the above-mentioned rocket engine.

[0039] The above technical solution has the following beneficial effects: 1. The structure of the present invention is reasonable. The pre-combustion chamber housing, turbine stator blades, gas collecting structure and reinforcing rib structure are integrally formed, which can reduce the difficulty and process of processing, thereby reducing the processing cost and shortening the processing cycle. In addition, it avoids the processes of milling grooves, brazing, and welding of gas collecting cavity ring belts in traditional processing. It adopts an integrated design to improve the structural utilization rate, effectively reduce the weight of the engine structure, meet the rocket supercharging requirements, and improve the stability and reliability of use. 2. A heat exchange medium inlet is provided on the upper part of the outer wall of the precombustion chamber shell, and a heat exchange medium outlet is provided on the outer wall of the gas collecting structure; interconnected heat exchange medium flow channels are provided in the side wall of the precombustion chamber shell, the turbine stator blades and the reinforcing rib structure. The above structure is conducive to improving the heat exchange efficiency and stability, and is also conducive to reducing the number of components compared to the traditional liquid rocket engine with independently arranged heat exchanger components, thereby improving the inherent reliability of the rocket engine; 3. The reinforcing rib structure includes a number of inclined ribs and a number of transverse ribs, which can not only achieve the purpose of strengthening the connection, thereby improving the stability and reliability of the overall structure, but also facilitate the setting of interconnected heat exchange medium flow channels to ensure the effectiveness and continuous stability of heat exchange; 4. The heat exchange medium flow channel includes a first heat exchange medium flow channel, a second heat exchange medium flow channel, a third heat exchange medium flow channel and a fourth heat exchange medium flow channel, and the second heat exchange medium flow channel is located in the turbine stator blade, the third heat exchange medium flow channel is located in the inclined ribs and the vertical ribs, and the fourth heat exchange medium flow channel is located in the transverse ribs. The above structure is the first application of setting a heat exchange cooling channel in the turbine stator blade of a liquid rocket engine, which can effectively reduce the temperature of the turbine stator blade during the operation of the engine, reduce the temperature resistance requirements of the raw materials of the turbine stator blade, and improve the working reliability and effectiveness of the turbine stator blade; 5. The first heat exchange medium flow channel is a spiral tube flow channel, which can increase the contact area of ​​heat exchange, improve the effectiveness and reliability of heat exchange, and improve the efficiency of heat exchange; 6. The top view structure of the transverse ribs is in the shape of a Y, a cross, a large letter or a cross. The above structure can increase the contact area of ​​heat exchange, improve the effectiveness and stability of heat exchange; 7. The gas collecting structure is an annular protrusion, and an annular gas collecting cavity is arranged inside the annular protrusion; the welding process of the collector ring belt is reduced, the processing efficiency is improved, and the effectiveness of heat exchange can also be improved; 8. The outer wall bottom of the pre-combustion chamber shell is integrally formed with a mounting lug with a hole, which is convenient for the installation and fixation of the overall structure, reduces the difficulty of assembly, and improves the stability and reliability of assembly and use.

[0040] 9. A cavitation tube for adjusting the incoming flow is provided at the inlet of the heat exchange medium, which facilitates the regulation and control of the incoming flow of the heat exchange medium. A throttle ring for adjusting the pressure of the pressurized medium is provided at the outlet of the heat exchange medium, which can meet the pressurization requirements of the rocket tank.

[0041] In the description of the present invention, it should be noted that the directions or positional relationships indicated by the terms "upper, lower, inner and outer" are based on the directions or positional relationships shown in the drawings, and are only for the convenience of describing the present invention and simplifying the description, rather than indicating or implying that the device or element referred to must have a specific direction, be constructed and operated in a specific direction, and therefore cannot be understood as limiting the present invention. In addition, the terms "first, second or third" are only used for descriptive purposes and cannot be understood as indicating or implying relative importance.

[0042] In the present invention, unless otherwise clearly specified and limited, the terms "install, connect, connect" should be understood in a broad sense, for example: it can be a fixed connection, a detachable connection or an integral connection; it can also be a mechanical connection, an electrical connection or a direct connection, or it can be indirectly connected through an intermediate medium, or it can be the internal communication of two components. For ordinary technicians in this field, the specific meanings of the above terms in the present invention can be understood according to specific circumstances.

[0043] Although the present invention has been described with reference to preferred embodiments, various modifications may be made thereto and parts thereof may be replaced by equivalents without departing from the scope of the present invention. In particular, the various technical features mentioned in the various embodiments may be combined in any manner as long as there are no structural conflicts. The present invention is not limited to the specific embodiments disclosed herein, but includes all technical solutions falling within the scope of the claims.

Claims

1. A heat exchanger integrated with a pre-combustion chamber, comprising a pre-combustion chamber housing (1), wherein the inner wall of the pre-combustion chamber housing (1) is integrally formed with a plurality of turbine stator blades (2), characterized in that: A gas collecting structure (3) is integrally formed on the outer wall of the pre-combustion chamber shell (1); A reinforcing rib structure (4) is integrally formed in the inner cavity of the pre-combustion chamber shell (1), and the reinforcing rib structure (4) is connected to the turbine stator blades (2) and the air collecting structure (3); A heat exchange medium inlet (5) is provided on the upper portion of the outer wall of the pre-combustion chamber shell (1), and a heat exchange medium outlet (6) is provided on the outer wall of the gas collecting structure (3); The side wall of the pre-combustion chamber shell (1), the turbine stator blades (2) and the reinforcing rib structure (4) are provided with interconnected heat exchange medium flow channels (7); The heat exchange medium inlet (5) is arranged at the entrance end of the heat exchange medium circulation channel (7), and the gas collecting structure (3) is located at the exit end of the heat exchange medium circulation channel (7).

2. The heat exchanger integrated with the pre-combustion chamber according to claim 1, characterized in that: The heat exchange medium circulation channel (7) comprises a first heat exchange medium circulation channel (71), a second heat exchange medium circulation channel (72) and a reinforcing rib section channel; The first heat exchange medium circulation channel (71) is located in the side wall of the pre-combustion chamber shell (1); The second heat exchange medium circulation channel (72) is located in the turbine stator blade (2), and one end of the second heat exchange medium circulation channel (72) is connected to the bottom end of the first heat exchange medium circulation channel (71); The reinforcing rib section channel is arranged in the reinforcing rib structure (4) and is connected to the first heat exchange medium circulation channel (71) and the second heat exchange medium circulation channel (72); The heat exchange medium inlet (5) is in communication with the top end of the first heat exchange medium circulation channel (71).

3. The heat exchanger integrated with the pre-combustion chamber according to claim 2, characterized in that: The reinforcing rib structure (4) comprises a plurality of inclined ribs (41) and a plurality of transverse ribs (42); The transverse ribs (42) correspond to the inclined ribs (41) one by one, and one end of the transverse ribs (42) is fixed to the upper part of the inclined ribs (41), and the other end of the transverse ribs (42) is fixed to the inner wall of the pre-combustion chamber shell (1) and is located on the inner side of the gas collecting structure (3); The bottom end of the inclined rib (41) is fixed to the end of the turbine stator blade (2) via a vertical rib (43).

4. The heat exchanger integrated with the pre-combustion chamber according to claim 3, characterized in that: The reinforcing rib section channel comprises a third heat exchange medium circulation channel (73) and a fourth heat exchange medium circulation channel (74); The third heat exchange medium circulation channel (73) is located within the inclined ribs (41) and the vertical ribs (43), and the bottom end of the third heat exchange medium circulation channel (73) is connected to the other end of the second heat exchange medium circulation channel (72); The fourth heat exchange medium circulation channel (74) is located in the transverse rib (42), one end of the fourth heat exchange medium circulation channel (74) is connected to the top end of the third heat exchange medium circulation channel (73), and the other end of the fourth heat exchange medium circulation channel (74) is connected to the gas collecting structure (3).

5. The heat exchanger integrated with the pre-combustion chamber according to claim 4, characterized in that: The first heat exchange medium flow channel (71) is a spiral tube flow channel.

6. The heat exchanger integrated with the pre-combustion chamber according to claim 3, characterized in that: The top ends of all the inclined ribs (41) are integrally formed as a whole.

7. A heat exchanger integrated with a pre-combustion chamber according to claim 3 or claim 6, characterized in that: The top view structures of the plurality of transverse ribs (42) are in a Y-shape, a cross-shape, a U-shape or a M-shape.

8. The heat exchanger integrated with the pre-combustion chamber according to claim 4, characterized in that: The gas collecting structure (3) is an annular protrusion (31) radially arranged on the outer wall of the pre-combustion chamber shell (1), and an annular gas collecting cavity (32) is arranged in the annular protrusion (31); An end of the fourth heat exchange medium flow channel (74) is in communication with the annular gas collecting cavity (32); The heat exchange medium outlet (6) is in communication with the annular gas collecting cavity (32), and the heat exchange medium outlet (6) is used for the heat exchange medium to flow out after being heated.

9. The heat exchanger integrated with the pre-combustion chamber according to claim 1, characterized in that: The top end of the pre-combustion chamber shell (1) is provided with a gas inlet (9), and the bottom end of the pre-combustion chamber shell (1) is provided with a gas outlet (10); The turbine stator blades (2) are located in the gas outlet (10).

10. The heat exchanger integrated with the pre-combustion chamber according to claim 1, characterized in that: The heat exchange medium inlet (5) is provided with a cavitation tube for adjusting the incoming flow rate; and / or the heat exchange medium outlet (6) is provided with a throttle ring for adjusting the pressure of the boosting medium.

11. A rocket engine, characterized in that: The rocket engine comprises a heat exchanger designed to be integrated with a pre-combustion chamber as described in any one of claims 1-10.

12. A rocket, characterized in that: The rocket comprises the rocket engine of claim 11.

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