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

Abstract

The application discloses a heat exchanger integrated with a precombustion chamber, a rocket engine and a rocket, and belongs to the technical field of rocket engine heat exchange. The heat exchanger comprises a precombustion chamber shell, the inner wall of which is provided with turbine stator blades, and the outer wall of the precombustion chamber shell is provided with a gas collection structure. The inner cavity of the precombustion chamber shell is provided with a reinforcing rib structure, the upper portion of the outer wall of the precombustion chamber shell is provided with a heat exchange medium inlet, and the outer wall of the gas collection structure is provided with a heat exchange medium outlet. The side wall of the precombustion chamber shell, the turbine stator blades and the reinforcing rib structure are provided with a heat exchange medium flow channel in communication. The rocket engine comprises the heat exchanger integrated with the precombustion chamber, and the rocket comprises the rocket engine. The application reduces the processing cost and shortens the processing period, avoids the processes such as milling grooves, brazing and welding of the gas collection cavity ring in the traditional processing, improves the structure utilization rate, effectively reduces the engine structure weight, meets the rocket pressurization demand, and improves the use stability and reliability.

Description

Technical Field

[0001] This invention relates to the field of rocket engine heat exchange technology, specifically to a heat exchanger, rocket engine, and rocket that are integrated with the pre-combustion chamber. Background Technology

[0002] The heat exchanger of a liquid rocket engine is a core component of the rocket pressurization system. It continuously supplies pressurized gas to the air cushion of the rocket tank during engine operation to ensure the propellant supply pressure required for normal engine operation. For example, Chinese patent application number 201910881056.5, patent title: A rocket engine heat exchanger and spacecraft.

[0003] In the process of realizing the above invention, the inventors discovered that the prior art has at least the following problems: although it can meet the general use requirements, it mostly adopts a brazed milling groove structure, and also requires welding of components such as the collector ring belt and inlet / outlet nozzles. Not only are there many processing steps, but the processing cost is also high and the processing cycle is long. At the same time, since it is set up separately from the pre-combustion chamber, it is also limited by the layout of the gas duct, and 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 this invention is to provide a heat exchanger, rocket engine, and rocket with a reasonable structural configuration that is conducive to improving heat exchange efficiency and stability, and which is integrated with the pre-combustion chamber.

[0005] To achieve the above objectives, in a first aspect, embodiments of the present invention provide a heat exchanger integrated with a pre-combustion chamber, including a pre-combustion chamber shell, wherein a plurality of turbine stator blades are integrally formed on the inner wall of the pre-combustion chamber shell, and an air collection structure is integrally formed on the outer wall of the pre-combustion chamber shell;

[0006] The pre-combustion chamber shell has an integrally formed reinforcing rib structure in its inner cavity, and the reinforcing rib structure is connected to the turbine stator blades and the gas collection structure.

[0007] A heat exchange medium inlet is provided on the upper part 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 collection structure;

[0008] The sidewalls of the pre-combustion chamber shell, the turbine stator blades, and the reinforcing rib structure are provided with interconnected heat exchange medium flow channels.

[0009] The heat exchange medium inlet is located at the inlet end of the heat exchange medium flow channel, and the gas collection structure is located at the outlet end of the heat exchange medium flow channel.

[0010] A further preferred embodiment is that the heat exchange medium flow channel includes a first heat exchange medium flow channel, a second heat exchange medium flow channel, and a reinforcing rib section channel;

[0011] The first heat exchange medium flow channel is located inside the side wall of the pre-combustion chamber shell;

[0012] The second heat exchange medium flow channel is located inside the turbine stator blade, and one end of the second heat exchange medium flow channel is connected to the bottom end of the first heat exchange medium flow channel.

[0013] The reinforcing rib section channel is set inside the reinforcing rib structure and is connected to the first heat exchange medium flow channel and the second heat exchange medium flow channel.

[0014] The heat exchange medium inlet is connected to the top of the first heat exchange medium flow channel.

[0015] A further preferred embodiment is that the reinforcing rib structure includes a plurality of inclined ribs and a plurality of transverse ribs;

[0016] The transverse ribs correspond one-to-one with the inclined ribs, and one end of the transverse rib is fixed to the upper part of the inclined rib, while the other end of the transverse rib is fixed to the inner wall of the pre-combustion chamber shell and located inside the gas collection structure.

[0017] The bottom end of the inclined rib is fixed to the end of the turbine stator blade by a vertical rib.

[0018] A further preferred embodiment is that the reinforcing rib segment channel includes a third heat exchange medium flow channel and a fourth heat exchange medium flow channel;

[0019] The third heat exchange medium flow channel is located within the inclined ribs and the vertical ribs, and the bottom end of the third heat exchange medium flow channel is connected to the other end of the second heat exchange medium flow channel;

[0020] The fourth heat exchange medium flow channel is located within the transverse rib. One end of the fourth heat exchange medium flow channel is connected to the top end of the third heat exchange medium flow channel, and the other end of the fourth heat exchange medium flow channel is connected to the gas collection structure.

[0021] A further preferred embodiment is that the first heat exchange medium flow channel is a spiral tube type flow channel.

[0022] A further preferred embodiment is that the top ends of all the inclined ribs are integrally formed as a single unit.

[0023] A further preferred embodiment is that the top view of the plurality of the transverse ribs is Y-shaped, cross-shaped, T-shaped, or rice-shaped.

[0024] A further preferred embodiment is that the gas collecting structure is an annular protrusion radially disposed on the outer wall of the pre-combustion chamber shell, and an annular gas collecting cavity is disposed within the annular protrusion;

[0025] The end of the fourth heat exchange medium flow channel is connected to the annular gas collection cavity;

[0026] The heat exchange medium outlet is connected to the annular gas collecting cavity, and the heat exchange medium outlet is used for the heat exchange medium to flow out after being heated.

[0027] A further preferred embodiment is that the heat exchange medium at the heat exchange medium inlet is liquid oxygen, liquid nitrogen, methane, or helium.

[0028] A further preferred embodiment is that a gas inlet is provided at the top of the pre-combustion chamber shell, and a gas outlet is provided at the bottom of the pre-combustion chamber shell;

[0029] The turbine stator blades are located within the gas outlet.

[0030] A further preferred embodiment is that a cavitation pipe for adjusting the inlet flow rate is provided at the inlet position of the heat exchange medium.

[0031] A further preferred embodiment is that a throttling ring for adjusting the pressure of the boosting medium is provided at the outlet position of the heat exchange medium.

[0032] Secondly, the present invention provides a rocket engine, the rocket engine including the heat exchanger described above that is integrated with the pre-combustion chamber.

[0033] Thirdly, the present invention also provides a rocket, the rocket comprising the aforementioned rocket engine.

[0034] The above technical solution has the following beneficial technical effects:

[0035] 1. The present invention has a reasonable structural design. Its pre-combustion chamber shell, turbine stator blades, gas collection structure and reinforcing rib structure are integrally formed, which can reduce the processing difficulty and processing steps, thereby reducing processing costs and shortening the processing cycle. Moreover, it avoids the milling, brazing and welding of gas collection chamber rings 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 pressurization requirements, and improves the stability and reliability of use.

[0036] 2. A heat exchange medium inlet is provided on the upper part 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 collection structure; interconnected heat exchange medium flow channels are provided in the side wall of the pre-combustion chamber shell, the turbine stator blades and the reinforcing rib structure. The above structure is conducive to improving heat exchange efficiency and stability, and compared with traditional liquid rocket engines with independently set heat exchanger components, it is also conducive to reducing the number of components, thereby improving the inherent reliability of the engine.

[0037] 3. The reinforcing rib structure includes several inclined ribs and several transverse ribs, which 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, ensuring the effectiveness and continuous stability of heat exchange;

[0038] 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. The second heat exchange medium flow channel is located inside the turbine stator blade, the third heat exchange medium flow channel is located inside the inclined rib and the vertical rib, and the fourth heat exchange medium flow channel is located inside the transverse rib. The above structure is the first application of heat exchange and cooling channels in the turbine stator blade of a liquid rocket engine. It can effectively reduce the temperature of the turbine stator blade during engine operation, reduce the temperature resistance requirements of the turbine stator blade raw materials, and improve the working reliability and effectiveness of the turbine stator blade.

[0039] 5. The first heat exchange medium flow channel is a spiral tube type flow channel, which can increase the heat exchange contact area, improve the effectiveness and reliability of heat exchange, and improve the heat exchange efficiency.

[0040] 6. The top view of the transverse ribs is Y-shaped, cross-shaped, T-shaped, or rice-shaped. The above structure can increase the heat exchange contact area and improve the effectiveness and stability of heat exchange.

[0041] 7. The gas collection structure is an annular protrusion with an annular gas collection cavity inside, which helps to reduce the welding ring process of the assembly, improves processing efficiency, and also improves the effectiveness of heat exchange.

[0042] 8. The bottom of the outer wall of the pre-combustion chamber shell is integrally formed with perforated mounting lugs, which facilitates the installation and fixing of the overall structure, reduces the difficulty of assembly, and improves the stability and reliability of assembly and use;

[0043] 9. A cavitation pipe is installed at the inlet of the heat exchange medium to adjust the inflow rate, which facilitates the adjustment and control of the inflow rate of the heat exchange medium. A throttling ring is installed at the outlet of the heat exchange medium to adjust the pressure of the pressurizing medium, so as to meet the pressurization requirements of the rocket tank. Attached Figure Description

[0044] To more clearly illustrate the technical solutions in the embodiments of the present invention or the prior art, the drawings used in the description of the embodiments or the prior art will be briefly introduced below. Obviously, the drawings described below are only some embodiments of the present invention. For those skilled in the art, other drawings can be obtained based on these drawings without creative effort.

[0045] Figure 1 This is a cross-sectional structural schematic diagram of an embodiment of the present invention;

[0046] Figure 2 This is a top view of the structure according to an embodiment of the present invention;

[0047] Figure 3 This is a schematic diagram of the specific structure of the turbine stator blade in an embodiment of the present invention;

[0048] Figure 4 for Figure 1 Enlarged structural diagram at point A in the middle;

[0049] Figure 5 for Figure 1 Enlarged structural diagram at point B.

[0050] Explanation of reference numerals in the attached figures:

[0051] 1. Pre-combustion chamber shell; 2. Turbine stator blades; 3. Gas collection structure; 4. Reinforcing rib structure; 5. Heat exchange medium inlet; 6. Heat exchange medium outlet; 7. Heat exchange medium flow channel; 8. Perforated mounting lugs; 9. Gas inlet; 10. Gas outlet;

[0052] 31. Annular protrusion; 32. Annular gas collecting cavity;

[0053] 41. Inclined stiffeners; 42. Horizontal stiffeners; 43. Vertical stiffeners;

[0054] 71. First heat exchange medium flow channel; 72. Second heat exchange medium flow channel; 73. Third heat exchange medium flow channel; 74. Fourth heat exchange medium flow channel. Detailed Implementation

[0055] The features and exemplary embodiments of various aspects of the present invention will now be described in detail. Numerous specific details are set forth in the following detailed description in order to provide a thorough understanding of the invention. However, it will be apparent to those skilled in the art that the invention may be practiced without requiring some of these specific details. The following description of embodiments is merely intended to provide a better understanding of the invention by illustrating examples of the invention. In the accompanying drawings and the following description, at least some well-known structures and techniques have not been shown in order to avoid unnecessarily obscuring the invention; and, for clarity, the dimensions of some structures may be exaggerated. Furthermore, the features, structures, or characteristics described below may be combined in any suitable manner in one or more embodiments.

[0056] like Figures 1 to 5As shown, a heat exchanger integrated with the pre-combustion chamber includes a pre-combustion chamber shell 1. The inner wall of the pre-combustion chamber shell 1 is integrally formed with several turbine stator blades 2, and the outer wall of the pre-combustion chamber shell 1 is integrally formed with a gas collecting structure 3. In this embodiment, the pre-combustion chamber shell 1 is a conventional structure of the prior art, simply applied; specifically, it is an annular structure. The turbine stator blades 2 are also conventional structures of the prior art, simply applied, and therefore not described in detail. The above three structures are integrally formed, thereby improving structural utilization and effectively reducing the engine's structural weight. Furthermore, 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 provided within the annular protrusion 31. This reduces processes such as welding the gas collecting cavity ring and also improves the overall structural stability.

[0057] like Figure 1 , Figure 2 , Figure 4 and Figure 5 As 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 blade 2 and the gas collection structure 3. During processing, the reinforcing rib structure 4 includes several inclined ribs 41 and several transverse ribs 42. The transverse ribs 42 correspond one-to-one with the inclined ribs 41, 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 located inside the gas collection structure 3. The bottom end of the inclined rib 41 is fixed to the end of the turbine stator blade 2 by a vertical rib 43. Through the aforementioned structure, the main function of the vertical ribs 43 is to connect the turbine stator and the guide cone, serving as a load-bearing element. Secondly, they also contain cooling channels, increasing the heat exchange contact area and thus improving heat exchange efficiency and stability. Furthermore, the top view of the several transverse ribs 42 can be arranged in a Y-shape, cross shape, T-shape, or star shape, or other radial shapes radiating from the center point, as needed. This increases the number of heat exchange medium flow channels 7 within the inclined ribs 41 and transverse ribs 42, improving heat exchange efficiency and meeting the needs of different applications.

[0058] like Figure 1 and Figure 2As 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 in the heat exchange medium inlet 5 is liquid oxygen, liquid nitrogen, methane, or helium. Furthermore, interconnected heat exchange medium flow channels 7 are provided in the side walls 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 located at the inlet end of the heat exchange medium flow channel 7, and the gas collecting structure 3 is located at the outlet end of the heat exchange medium flow channel 7. By employing a self-pressurization method for the heat exchange medium, which introduces the heat exchange medium from the heat exchange medium inlet 5, the traditional helium pressurization medium supply system can be reduced, effectively simplifying and reducing the configuration of the rocket pressurization system, reducing the overall structural weight, and improving operational reliability. Moreover, in practical applications, different apertures and lengths of the heat exchange medium flow channels 7 can be machined during processing to achieve adjustments in heat exchange area and meet different heat exchange performance requirements.

[0059] Furthermore, to facilitate the adjustment and pressure increase of the heat exchange medium, a cavitation tube for adjusting the inflow rate is installed at the heat exchange medium inlet 5, and a throttling coil for adjusting the pressure of the booster medium is installed at the heat exchange medium outlet 6. Both the cavitation tube and the throttling coil are conventional structures in existing technology, simply applied, and therefore not shown in the figure. This structure can meet the pressurization requirements of the rocket propellant tank.

[0060] like Figure 1 , Figure 2 and Figure 3 As shown, the heat exchange medium flow channel 7 includes a first heat exchange medium flow channel 71, a second heat exchange medium flow channel 72, and a reinforcing rib section channel, the shape of which matches the reinforcing rib structure. Specifically, the reinforcing rib section channel includes a third heat exchange medium flow channel 73 and a fourth heat exchange medium flow channel 74; wherein, the first heat exchange medium flow channel 71 is located inside the side wall of the pre-combustion chamber shell 1; the second heat exchange medium flow channel 72 is located inside the turbine stator blade 2, and one end of the second heat exchange medium flow channel 72 is connected to the bottom end of the first heat exchange medium flow channel 71; ... third heat exchange medium flow channel 72 is located inside the side wall of the pre-combustion chamber shell 1; the second heat exchange medium flow channel 72 is located inside the turbine stator blade 2, and one end of the second heat exchange medium flow channel 72 is connected to the bottom end of the first heat exchange medium flow channel 71; the second heat exchange medium flow channel 72 is located inside the side wall of the pre-combustion chamber shell 1; the second heat exchange medium flow channel 72 is located inside the side wall of the pre-combustion chamber shell 1; the second heat exchange medium flow channel 72 is located inside the side wall of the pre-combustion chamber shell 1; the second heat exchange medium flow channel 72 is located inside the side wall of the pre-combustion chamber shell 1; the second heat exchange medium flow channel 72 is located inside the turbine stator blade 2; the second heat exchange medium flow channel 72 is located inside the turbine stator blade 2; the second heat exchange medium flow channel 72 is located inside the turbine stator blade 2; the The three heat exchange medium flow channels 73 are located within the inclined ribs 41 and the vertical ribs 43. The bottom end of the third heat exchange medium flow channel 73 is connected to the other end of the second heat exchange medium flow channel 72. The fourth heat exchange medium flow channel 74 is located within the transverse ribs 42. One end of the fourth heat exchange medium flow channel 74 is connected to the top end of the third heat exchange medium flow channel 73, and the other end of the fourth heat exchange medium flow channel 74 is connected to the gas collection structure 3. The heat exchange medium inlet 5 is connected to the top end of the first heat exchange medium flow channel 71.

[0061] In use, the heat exchange medium enters through the heat exchange medium inlet 5 and passes sequentially through the first heat exchange medium flow channel 71, the second heat exchange medium flow channel 72, the third heat exchange medium flow channel 73, and the fourth heat exchange medium flow channel 74 before entering the gas collection structure 3. It is then discharged outward through the heat exchange medium outlet 6. The heat exchange operation is achieved through the first heat exchange medium flow channel 71, the second heat exchange medium flow channel 72, the third heat exchange medium flow channel 73, and the fourth heat exchange medium flow channel 74, realizing the effect of heat exchange and cooling of the heat exchange medium. Moreover, the diameters of different sections can be the same or different according to actual needs.

[0062] Furthermore, the second heat exchange medium flow channel 72 is located inside the turbine stator blade 2. This 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 turbine stator blade 2 raw materials, and improve the working reliability of the turbine stator blade 2.

[0063] The third heat exchange medium flow channel 73 is located within the inclined rib 41 and the vertical rib 43, and the fourth heat exchange medium flow channel 74 is located within the transverse rib 42. It can also cool the flow guiding structure while exchanging heat, thus improving the stability and reliability of use.

[0064] like Figure 1 As shown, the first heat exchange medium flow channel 71 is a spiral tube type flow channel. It can be a regular or irregular spiral tube type flow channel, which is beneficial to increase the heat exchange contact area and improve the heat exchange efficiency and effectiveness.

[0065] like Figure 1 As shown, the top ends of all the inclined ribs 41 are integrally formed as a single unit. This structure improves the overall stability and reliability of the structure.

[0066] And, as Figure 1 As shown, the end of the fourth heat exchange medium flow channel 74 is connected to the annular gas collecting cavity 32; the heat exchange medium outlet 6 is connected to the annular gas collecting cavity 32, and the heat exchange medium outlet 6 is used for the heat exchange medium to flow out after heating. The annular gas collecting cavity 32 can collect the heat exchange medium and discharge it outward from the heat exchange medium outlet 6, improving stable and reliable operation.

[0067] like Figure 1 As shown, the bottom of the outer wall of the pre-combustion chamber shell 1 is integrally formed with a perforated mounting lug 8. A gas inlet 9 is provided at the top of the pre-combustion chamber shell 1, and a gas outlet 10 is provided at the bottom; the turbine stator blade 2 is located within the gas outlet 10. This facilitates the installation and fixing of the overall structure, reduces the difficulty of assembly, and improves the stability and reliability of assembly and use.

[0068] This embodiment has undergone ground-based hot-fire testing of the engine and flight testing of the TL-2 rocket. Its performance meets the rocket pressurization requirements, and it is the first engineering application in the field of liquid rocket engines.

[0069] In another embodiment, a rocket engine is also provided, the rocket engine including the heat exchanger described above that is integrated with the pre-combustion chamber.

[0070] In yet another embodiment, a rocket is also provided, the rocket comprising the rocket engine described above.

[0071] The above technical solution has the following beneficial effects:

[0072] 1. The present invention has a reasonable structural design. Its pre-combustion chamber shell, turbine stator blades, gas collection structure and reinforcing rib structure are integrally formed, which can reduce the processing difficulty and processing steps, thereby reducing processing costs and shortening the processing cycle. Moreover, it avoids the milling, brazing and welding of gas collection chamber rings and other processes in traditional processing. The integrated design improves the structural utilization rate, effectively reduces the weight of the engine structure, can meet the rocket pressurization requirements, and improves the stability and reliability of use.

[0073] 2. A heat exchange medium inlet is provided on the upper part 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 collection structure; interconnected heat exchange medium flow channels are provided in the side wall of the pre-combustion chamber shell, the turbine stator blades and the reinforcing rib structure. The above structure is conducive to improving heat exchange efficiency and stability, and compared with the traditional liquid rocket engine with independently set heat exchanger components, it is also conducive to reducing the number of components, thereby improving the inherent reliability of the rocket engine.

[0074] 3. The reinforcing rib structure includes several inclined ribs and several transverse ribs, which 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, ensuring the effectiveness and continuous stability of heat exchange;

[0075] 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. The second heat exchange medium flow channel is located inside the turbine stator blade, the third heat exchange medium flow channel is located inside the inclined rib and the vertical rib, and the fourth heat exchange medium flow channel is located inside the transverse rib. The above structure is the first application of heat exchange and cooling channels in the turbine stator blade of a liquid rocket engine. It can effectively reduce the temperature of the turbine stator blade during engine operation, reduce the temperature resistance requirements of the turbine stator blade raw materials, and improve the working reliability and effectiveness of the turbine stator blade.

[0076] 5. The first heat exchange medium flow channel is a spiral tube type flow channel, which can increase the heat exchange contact area, improve the effectiveness and reliability of heat exchange, and improve the heat exchange efficiency.

[0077] 6. The top view of the transverse ribs is Y-shaped, cross-shaped, T-shaped, or rice-shaped. The above structure can increase the heat exchange contact area and improve the effectiveness and stability of heat exchange.

[0078] 7. The gas collection structure is an annular protrusion with an annular gas collection cavity inside; this reduces the welding process of the collector ring, improves processing efficiency, and also enhances the effectiveness of heat exchange.

[0079] 8. The bottom of the outer wall of the pre-combustion chamber shell is integrally formed with perforated mounting lugs, which facilitates the installation and fixing of the overall structure, reduces the difficulty of assembly, and improves the stability and reliability of assembly and use.

[0080] 9. A cavitation pipe is installed at the inlet of the heat exchange medium to adjust the inflow rate, which facilitates the adjustment and control of the inflow rate of the heat exchange medium. A throttling ring is installed at the outlet of the heat exchange medium to adjust the pressure of the pressurizing medium, which can meet the pressurization requirements of the rocket propellant tank.

[0081] In the description of this invention, it should be noted that the terms "upper," "lower," "inner," and "outer," etc., indicate the orientation or positional relationship based on the orientation or positional relationship shown in the accompanying drawings. These terms are used only for the convenience of describing the invention and for simplifying the description, and do not indicate or imply that the device or element referred to must have a specific orientation, or be constructed and operated in a specific orientation. Therefore, they should not be construed as limitations on the invention. Furthermore, the terms "first," "second," or "third" are used for descriptive purposes only and should not be construed as indicating or implying relative importance.

[0082] Unless otherwise explicitly specified and limited, the terms "installation," "connection," and "joining" in this invention should be interpreted broadly. For example, they can refer to fixed connections, detachable connections, or integral connections; similarly, they can refer to mechanical connections, electrical connections, or direct connections, or indirect connections through an intermediate medium, or internal connections between two components. Those skilled in the art can understand the specific meaning of the above terms in this invention based on the specific circumstances.

[0083] Although the invention has been described with reference to preferred embodiments, various modifications can be made and components can be replaced with equivalents without departing from the scope of the invention. In particular, the technical features mentioned in the various embodiments can be combined in any manner as long as there is no structural conflict. The 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 shell (1), wherein a plurality of turbine stator blades (2) are integrally formed on the inner wall of the pre-combustion chamber shell (1), characterized in that: The heat exchanger is used in rocket engines, and the outer wall of the pre-combustion chamber shell (1) is integrally formed with a gas collection structure (3). The pre-combustion chamber shell (1) has an integrally formed reinforcing rib structure (4) in its inner cavity, and the reinforcing rib structure (4) is connected to the turbine stator blade (2) and the gas collection structure (3). The upper part of the outer wall of the pre-combustion chamber shell (1) is provided with a heat exchange medium inlet (5), and the outer wall of the gas collection structure (3) is provided with a heat exchange medium outlet (6). 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 located at the inlet end of the heat exchange medium flow channel (7), and the gas collection structure (3) is located at the outlet end of the heat exchange medium flow channel (7). The heat exchange medium flow channel (7) includes a first heat exchange medium flow channel (71), a second heat exchange medium flow channel (72), and a reinforcing rib section channel; The first heat exchange medium flow channel (71) is located inside the side wall of the pre-combustion chamber shell (1); The second heat exchange medium flow channel (72) is located inside the turbine stator blade (2), and one end of the second heat exchange medium flow channel (72) is connected to the bottom end of the first heat exchange medium flow channel (71); The reinforcing rib section channel is disposed within the reinforcing rib structure (4) and is connected to the first heat exchange medium flow channel (71) and the second heat exchange medium flow channel (72); The heat exchange medium inlet (5) is connected to the top of the first heat exchange medium flow channel (71); the reinforcing rib structure (4) includes a number of inclined ribs (41) and a number of transverse ribs (42). The transverse ribs (42) correspond one-to-one with the inclined ribs (41), 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 located inside the gas collection structure (3). The bottom end of the inclined rib (41) is fixed to the end of the turbine stator blade (2) by the vertical rib (43); the reinforcing rib section channel includes a third heat exchange medium flow channel (73) and a fourth heat exchange medium flow channel (74). The third heat exchange medium flow channel (73) is located within the inclined rib (41) and the vertical rib (43), and the bottom end of the third heat exchange medium flow channel (73) is connected to the other end of the second heat exchange medium flow channel (72); The fourth heat exchange medium flow channel (74) is located inside the transverse rib (42). One end of the fourth heat exchange medium flow channel (74) is connected to the top end of the third heat exchange medium flow channel (73), and the other end of the fourth heat exchange medium flow channel (74) is connected to the gas collection structure (3). The first heat exchange medium flow channel (71) is a spiral tube flow channel. The gas collection structure (3) is an annular protrusion (31) radially arranged on the outer wall of the pre-combustion chamber shell (1), and an annular gas collection cavity (32) is provided inside the annular protrusion (31). The end of the fourth heat exchange medium flow channel (74) is connected to the annular gas collection cavity (32); The heat exchange medium outlet (6) is connected to the annular gas collection cavity (32), and the heat exchange medium outlet (6) is used for the heat exchange medium to flow out after heating; the top ends of all the inclined ribs (41) are integrally formed into a whole. The top of the pre-combustion chamber shell (1) is provided with a gas inlet (9), and the bottom of the pre-combustion chamber shell (1) is provided with a gas outlet (10); the turbine stator blade (2) is located inside the gas outlet (10), the turbine stator blade (2) is located at the outlet end of the pre-combustion chamber shell (1), and the turbine stator blade (2) is located below the reinforcing rib structure (4).

2. The heat exchanger integrated with the pre-combustion chamber according to claim 1, characterized in that: The top view of several of the transverse ribs (42) is Y-shaped, cross-shaped, T-shaped or rice-shaped.

3. 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 inlet flow rate; and / or, the heat exchange medium outlet (6) is provided with a throttling ring for adjusting the pressure of the boosting medium.

4. A rocket engine, characterized in that: The rocket engine includes a heat exchanger integrated with the pre-combustion chamber as described in any one of claims 1-3.

5. A rocket, characterized in that: The rocket includes the rocket engine as described in claim 4.

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