Combustion chamber semi-regenerative cooling structure, fuel gas generator, engine and liquid rocket

Abstract

The embodiment of the invention provides a combustion chamber semi-regenerative cooling structure, a fuel gas generator, an engine and a liquid rocket. The combustion chamber semi-regenerative cooling structure comprises a throttling hole and a cooling channel which are formed in the front section of a combustion chamber. The throttling hole is formed in the outer wall of the combustion chamber front section, and the cooling channel is arranged between the inner wall and the outer wall of the combustion chamber front section; the throttling hole communicates with the cooling channel and is used for guiding a small part of the low-temperature fuel in the liquid collecting ring into the cooling channel; the cooling channel extends from the end, provided with the injector, of the combustion chamber front section to the other end and is used for guiding low-temperature fuel out of the combustion chamber front section and injecting the low-temperature fuel onto the inner wall of the combustion chamber rear section connected with the combustion chamber front section so as to cool the inner wall of the combustion chamber front section and the inner wall of the combustion chamber rear section connected with the combustion chamber front section. According to the combustion chamber semi-regenerative cooling structure, the fuel gas generator, the rocket engine and the liquid rocket, the problem that the manufacturing process and the structure are complex can be effectively solved.

Description

Technical Field

[0001] The present invention relates to the technical field of liquid rockets, and in particular to a combustion chamber semi-regenerative cooling structure, a gas generator, an engine and a liquid rocket. Background Art

[0002] The gas generator of a liquid rocket engine is one of the engine's core components. Its function is to generate high-temperature, high-pressure combustion gases that drive the turbine to generate work, then enter the thrust chamber for post-combustion or exhaust. Due to limitations in turbine materials, the gas generator uses off-stoichiometric combustion, typically at temperatures between 500°C and 1000°C. If local thermal protection measures are inadequate or high temperatures occur, the gas generator walls can easily burn through. For example, with liquid oxygen and kerosene propellants, to prevent the gas generator walls from ablation during operation, injectors are typically designed with zoned combustion or regenerative cooling techniques are used to cool the gas generator walls.

[0003] When the injector zoned combustion design is adopted: a separate kerosene (fuel) nozzle will be set in the edge area to maintain a lower mixing ratio condition near the wall and a lower combustion temperature; while a two-component nozzle of liquid oxygen and kerosene will be set in the central area. The mixing ratio in the central area is relatively high and the combustion temperature is also higher.

[0004] When regenerative cooling technology is used to cool the wall surface: the propellant needs to first flow through the gap between the inner and outer walls of the nozzle (often called a cooling jacket) to absorb heat to achieve the purpose of cooling, and then return to the injector and be injected into the combustion chamber for combustion.

[0005] In the process of implementing the present invention, the inventors discovered that the prior art has at least the following problems:

[0006] For gas generators, temperature uniformity of the gas across the transverse cross section is crucial. When using a zoned injector combustion design, a spoiler is required downstream to enhance gas mixing. This design and production of the gas generator is complex, requiring different injector nozzle structures: separate fuel nozzles in the side zones and a dual-propellant nozzle in the center. Furthermore, spoilers are required, as well as space for downstream mixing, which can easily lead to uneven gas mixing downstream.

[0007] If regenerative cooling is used to protect the wall surface, a cooling jacket must be installed between the inner and outer walls of the nozzle. Therefore, the combustion chamber needs to be made into a double-wall structure, and a cooling channel needs to be made in the interlayer of the double wall. After the propellant cools the wall surface, it needs to flow back to the injector. The manufacturing process of the entire flow channel is complicated, which is not conducive to the structural layout. The double-wall structure will increase the overall weight of the rocket and cause the production cost to be too high. Summary of the Invention

[0008] In view of this, the purpose of the embodiments of the present invention is to provide a combustion chamber semi-regenerative cooling structure, a gas generator, a rocket engine and a liquid rocket to improve the problems of manufacturing process and structural complexity in the prior art.

[0009] In the first aspect, an embodiment of the present invention provides a semi-regenerative cooling structure for a combustion chamber, comprising a throttle hole and a cooling channel provided on a front section of the combustion chamber; the throttle hole is provided on the outer wall of the front section of the combustion chamber, and the cooling channel is provided between the inner wall and the outer wall of the front section of the combustion chamber; the throttle hole is connected to the cooling channel and is arranged to introduce a small portion of the low-temperature fuel in the liquid collecting ring into the cooling channel; the cooling channel extends from one end of the front section of the combustion chamber where an injector is provided to the other end, and is used to guide the low-temperature fuel out of the front section of the combustion chamber and spray it on the inner wall of the rear section of the combustion chamber connected to the front section of the combustion chamber, so as to cool the inner wall of the front section of the combustion chamber and the inner wall of the rear section of the combustion chamber connected to the front section of the combustion chamber.

[0010] Furthermore, a plurality of the throttle holes are arranged at intervals along the circumference of the front section of the combustion chamber.

[0011] Furthermore, the cooling channel includes a first liquid collecting cavity and a first channel; the throttle hole is connected to the first liquid collecting cavity; and the first liquid collecting cavity is circumferentially arranged around the front section of the combustion chamber.

[0012] Furthermore, the cooling channel also includes a second liquid collecting chamber and a second channel; the second liquid collecting chamber is circumferentially arranged around the front section of the combustion chamber, and the second liquid collecting chamber is connected to the outlet of the first channel.

[0013] Furthermore, the number of the second channels is less than the number of the first channels, and the flow area of ​​a single second channel is no greater than the flow area of ​​a single first channel.

[0014] Furthermore, the first channel and / or the second channel extends in a spiral shape along the axial direction of the front section of the combustion chamber.

[0015] Furthermore, the helix angle of the first channel and / or the second channel ranges from 10° to 40°.

[0016] In a second aspect, an embodiment of the present invention provides a gas generator comprising a combustion chamber front section and a combustion chamber rear section that are connected to each other, wherein the combustion chamber front section is provided with the combustion chamber semi-regenerative cooling structure as described above, and the combustion chamber rear section is a single-layer wall structure, and the cooling channel is used to spray low-temperature fuel onto the inner wall of the combustion chamber rear section at the outlet.

[0017] Furthermore, the diameter of the inner wall of the rear section of the combustion chamber is not greater than the diameter of the inner wall of the front section of the combustion chamber at the outlet of the cooling channel.

[0018] Furthermore, the gas generator also includes a liquid collecting ring and an injector. The liquid collecting ring surrounds the circumferential outer wall of the front section of the combustion chamber away from the end of the rear section of the combustion chamber, and forms a distribution channel for low-temperature fuel between the liquid collecting ring and the outer wall of the front section of the combustion chamber; the injector is arranged on the inner wall of the front section of the combustion chamber away from the end of the rear section of the combustion chamber, and the front section of the combustion chamber is provided with a guide hole, and the guide hole is respectively connected to the distribution channel and the injector.

[0019] Furthermore, the throttle hole is arranged close to the guide hole, and the throttle hole and the injector are configured so that 90%-97% of the low-temperature fuel in the liquid collecting ring enters the injector, and the rest of the low-temperature fuel enters the cooling channel by controlling the size of the throttle hole and the size of the nozzle of the injector nozzle.

[0020] Furthermore, the front section of the combustion chamber and the injector are manufactured in one piece using additive manufacturing technology.

[0021] In a third aspect, an embodiment of the present invention provides a rocket engine comprising the gas generator as described above.

[0022] In a fourth aspect, an embodiment of the present invention provides a liquid rocket, comprising the rocket engine as described above.

[0023] The above technical solution has the following beneficial effects: The semi-regenerative cooling structure for the combustion chamber provided by the present invention does not, as in conventional processes, direct all of the low-temperature fuel in the liquid collecting ring into the cooling channel. Instead, it directs only a small portion of the low-temperature fuel into the cooling channel, while the majority of the fuel flows directly into the injector. This small portion of the low-temperature fuel does not participate in combustion in the cooling channel, while the majority of the fuel enters the injector and is injected into the combustion chamber to participate in combustion. The low-temperature fuel in the cooling channel is used for cooling and regeneration. The low-temperature fuel entering the cooling channel is used to cool the inner walls of both the front section of the combustion chamber and the rear section connected to the front section. This small portion of the low-temperature fuel does not need to return to the injector, but instead flows directly into the rear section of the combustion chamber. Therefore, the cooling channel has a simpler structure and a relatively simpler manufacturing process than conventional cooling channels. The gas generator provided by the present invention cools the combustion chamber by injecting low-temperature fuel onto the inner wall of the rear section of the combustion chamber through the cooling channel outlet. The rear section of the combustion chamber can adopt a single-layer wall structure, which simplifies the structure of the rear section of the combustion chamber, reduces the overall weight of the gas generator, and saves production costs. The rocket engine and liquid rocket provided by the present invention include the above-mentioned gas generator, and therefore also have the above-mentioned beneficial effects. BRIEF DESCRIPTION OF THE DRAWINGS

[0024] In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the following briefly introduces the drawings required for use in the embodiments or the description of the prior art. 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 any creative work.

[0025] Figure 1 It is a partial cross-sectional structural diagram of the front section of the combustion chamber of an embodiment of the present invention (that is, a structural diagram of the semi-regenerative cooling structure of the combustion chamber).

[0026] Figure 2 yes Figure 1 Schematic diagram of the cross-sectional structure of the first channel of the combustion chamber semi-regenerative cooling structure.

[0027] Figure 3 It is a schematic cross-sectional structural diagram of a gas generator according to an embodiment of the present invention.

[0028] Figure 4 yes Figure 3 A magnified schematic diagram of the structure at point A.

[0029] Figure 5 yes Figure 3 A magnified schematic diagram of the structure at point B.

[0030] (Note: Figure 4 and Figure 5 The arrow in the figure indicates the flow direction of the low-temperature fuel.)

[0031] Figure 6 It is a schematic diagram of the cross-sectional structure of some components of a gas generator according to an embodiment of the present invention.

[0032] The meanings of the reference numerals in the accompanying drawings are as follows:

[0033] 1. Front section of the combustion chamber; 11. Throttle hole; 12. Cooling channel; 121. First collecting chamber; 122. First channel; 123. Second collecting chamber; 124. Second channel; 13. Guide hole; 14. First flange; 15. Second flange; 2. Rear section of the combustion chamber; 3. Collecting ring; 31. Distribution channel; 4. Injector. DETAILED DESCRIPTION

[0034] The features and exemplary embodiments of various aspects of the present invention are described in detail below. In the detailed description that follows, many specific details are set forth in order to provide a comprehensive understanding of the present invention. However, it will be apparent 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 intended only to provide a better understanding of the present invention by illustrating examples of the present invention. In the accompanying drawings and the following description, at least some of the well-known structures and techniques are not shown in order to avoid unnecessary ambiguity in the present invention; and, for clarity, the sizes of some structures may be exaggerated. In addition, the features, structures, or characteristics described below may be combined in any suitable manner in one or more embodiments.

[0035] like Figure 1 and Figure 2 As shown, the semi-regenerative cooling structure of the combustion chamber of the embodiment of the present invention includes a throttle hole 11 and a cooling channel 12 provided on the combustion chamber front section 1; the throttle hole 11 is provided on the outer wall of the combustion chamber front section 1, and the cooling channel 12 is provided between the inner wall and the outer wall of the combustion chamber front section 1; the throttle hole 11 is connected to the cooling channel 12, and is used to introduce a small amount of low-temperature fuel in the liquid collecting ring 3 into the cooling channel 12; the cooling channel 12 extends from one end of the combustion chamber front section 1 where the injector 4 is provided to the other end, and is used to guide the low-temperature fuel out of the combustion chamber front section 1 and spray it on the inner wall of the combustion chamber rear section 2 connected to the combustion chamber front section 1, so as to cool the inner wall of the combustion chamber front section 1 and the inner wall of the combustion chamber rear section 2 connected to the combustion chamber front section 1.

[0036] The throttle hole 11 is used to throttle the low-temperature fuel, which increases the flow resistance. Combined with the increase in the flow area of ​​the channel, it reduces the pressure drop and flow rate. The throttle hole 11 is connected to the cavity of the liquid collecting ring 3. Only the low-temperature fuel entering the cooling channel 12 through the throttle hole 11 plays a cooling and regeneration role, while most of the fuel directly enters the combustion chamber through the injector 4 for combustion. The low-temperature fuel in the cooling channel 12 absorbs the heat from the inner wall of the front section 1 of the combustion chamber, cools it, and is then sprayed onto the inner wall of the rear section 2 of the combustion chamber at the outlet of the cooling channel 12, thereby cooling the rear section 2 of the combustion chamber and participating in combustion there without entering the injector 4. Since the low-temperature fuel does not participate in combustion in the cooling channel 12, the downstream wall can be cooled by introducing less fuel.

[0037] Several throttle holes 11 are evenly distributed along the circumferential outer wall of the combustion chamber head. These holes, serving as the frontal channel for the low-temperature fuel (coolant), are the primary component of low-temperature fuel throttling. Their throttling pressure drop accounts for approximately 90% of the flow resistance of the entire combustion chamber's semi-regenerative cooling structure. After passing through these holes, the low-temperature fuel flows through cooling channel 12, removing heat from the inner wall of the combustion chamber's front section 1 and entering the downstream combustion chamber's rear section 2. The even distribution of these holes 11 ensures uniform temperature distribution within the cooling channel 12, preventing localized overheating.

[0038] In some embodiments, the cooling channel 12 includes a first liquid collecting chamber 121 and a first channel 122; the throttle hole 11 is arranged on the outer wall of the combustion chamber front section 1 corresponding to the first liquid collecting chamber 121; the first liquid collecting chamber 121 is arranged circumferentially around the combustion chamber front section 1; and a plurality of first channels 122 are evenly distributed along the circumference of the combustion chamber front section 1.

[0039] Specifically, the first collecting chamber 121 is arranged corresponding to the throttle hole 11, that is, each throttle hole 11 is connected to the first collecting chamber 121. The first collecting chamber 121 is an annular cavity arranged circumferentially around the front section 1 of the combustion chamber. The low-temperature fuel can directly enter the first collecting chamber 121 through these throttle holes 11. The range of the throttle holes 11 distributed along the circumferential direction of the front section 1 of the combustion chamber coincides with the circumferential range of the annular cavity (for example, in some embodiments, the annular cavity is a full circle of circular rings arranged along the circumference). Through multiple throttle holes 11, the low-temperature fuel is injected into the annular first collecting chamber 121 at multiple points, evenly distributed along the circumference of the annular cavity or unevenly distributed according to the heat load. The fuel is collected and redistributed in the first collecting chamber 121 to achieve the effect of uniform flow and uniform temperature, thereby cooling the front section 1 of the combustion chamber.

[0040] To achieve a better cooling effect for the cooling channel 12, in some embodiments, a second liquid collecting chamber 123 and a second channel 124 may also be provided. The second liquid collecting chamber 123 is arranged circumferentially around the combustion chamber front section 1 and is connected to the outlet of the first channel 122. A plurality of second channels 124 are evenly distributed along the circumference of the combustion chamber front section 1, the number of second channels 124 being less than the number of first channels 122, and the flow area of ​​a single second channel 124 being no greater than the flow area of ​​a single first channel 122. For example, the cross-section of the second channel 124 can be made smaller than the cross-section of the first channel 122, so that the number of first channels 122 and second channels 124 is designed to be multiples. For example, in some embodiments, the number of first channels 122 is 1.5 to 2 times the number of second channels 124.

[0041] The second manifold 123 is connected to the outlet of the first channel 122. After the low-temperature fuel enters the second manifold 123 from the first channel 122, it is collected and redistributed again to further equalize the flow and temperature, thereby achieving good protection for the downstream fuel chamber components.

[0042] When only the first channel 122 is provided and the second channel 124 is omitted, the first channel 122 functions as both a conduction channel and a throttling channel to protect downstream components. When both the first channel 122 and the second channel 124 are provided, the first channel 122 can function solely as a conduction channel, while the second channel 124 functions as a throttling channel. The flow resistance of the second channel 124 accounts for approximately 10% of the flow resistance of the entire cooling structure. Both the first and second cooling channels 12 have rectangular cross-sections. Preferably, all first and second cooling channels 12 have the same cross-section. The total number of second channels 124 is less than the total number of first channels 122. The cross-sectional area of ​​a single second channel 124 is no greater than that of a single first channel 122. More preferably, the cross-sectional area of ​​the second channel 124 is smaller than that of the first channel 122 to better achieve the throttling function.

[0043] The two liquid collecting chambers are respectively arranged along the circumferential direction of the front section 1 of the combustion chamber, and the two channels (the first channel 122 and the second channel 124) are arranged along the longitudinal direction of the front section 1 of the combustion chamber. For example, the extension trajectory of the two channels is a straight line, and multiple first channels 122 are arranged side by side along the axial direction of the front section 1 of the combustion chamber, and multiple second channels 124 are also arranged side by side along the axial direction of the front section 1 of the combustion chamber. In order to make the cooling effect of the cooling channel 12 stronger, the first channel 122 and / or the second channel 124 can also be extended in a spiral shape along the axial direction of the front section 1 of the combustion chamber, and the range of the spiral angle is controlled to be 10° to 40°. The spiral cooling channel 12 extends the flow path of the low-temperature fuel between the inner and outer walls of the front section 1 of the combustion chamber, increases the contact time of the low-temperature fuel with the inner wall surface, and thus improves the cooling efficiency and effect of the cooling structure on the front section 1 of the combustion chamber. This design enables the coolant to more fully absorb the heat of the inner wall, effectively reducing the temperature of the inner wall surface of the front section 1 of the combustion chamber. The spiral cooling channel 12 also helps evenly distribute the coolant between the inner and outer walls of the combustion chamber front section 1, preventing localized overheating and improving cooling efficiency. Because the spiral cooling channel 12 distributes heat more evenly, it reduces thermal stress concentration caused by large local temperature differences. Controlling the helix pitch angle facilitates additive manufacturing (3D printing).

[0044] like Figures 3 to 6As shown, an embodiment of the present invention further provides a gas generator, comprising a combustion chamber front section 1 and a combustion chamber rear section 2 that are connected to each other, the combustion chamber front section 1 being provided with the combustion chamber semi-regenerative cooling structure of the above embodiment, the combustion chamber rear section 2 being a single-wall cylindrical structure, and the cooling channel 12 being used to spray low-temperature fuel onto the inner wall of the combustion chamber rear section 2 at the outlet.

[0045] Specifically, the combustion chamber front section 1 and combustion chamber rear section 2 can each be manufactured from stainless steel or a high-temperature alloy steel such as GH4169. If the combustion chamber front section 1 and combustion chamber rear section 2 are made of the same or similar materials, they can be integrally molded. If the materials differ significantly, welding can be used to securely connect the two. The combustion chamber rear section 2 is securely connected to the combustion chamber front section 1 at the outlet end of the cooling channel 12.

[0046] The diameter of the inner wall of the combustion chamber rear section 2 is no greater than the diameter of the inner wall of the combustion chamber front section 1 at the outlet of the cooling channel 12, so as to cool the inner wall of the combustion chamber rear section 2. Preferably, the diameter of the inner wall of the combustion chamber rear section 2 is the same as the diameter of the inner wall of the combustion chamber front section 1 at the connection point (at the outlet of the cooling channel 12), so that the low-temperature fuel can be sprayed along the inner wall surface of the combustion chamber rear section 2 after flowing out of the outlet of the second channel 124. The second channels 124 evenly distributed along the circumference of the combustion chamber front section 1 can evenly spray the low-temperature fuel on the inner wall surface of the combustion chamber rear section 2, making the cooling of the combustion chamber rear section 2 more uniform and reliable. The low-temperature fuel in the cooling channel 12 does not participate in combustion within the cooling channel 12, but only removes a small amount of heat from the inner wall of the front section 1 of the combustion chamber. Only after the low-temperature fuel is ejected from the outlet of the second channel 124 onto the inner wall of the rear section 2 of the combustion chamber does it come into contact with the flame in the central combustion zone and slowly begin to burn. Therefore, only a very small amount of low-temperature fuel is needed to effectively protect the inner wall of the rear section 2 of the combustion chamber. As a result, the rear section 2 of the combustion chamber can adopt a simple single-layer wall structure. Conventional combustion chambers are mostly double-layer wall structures. The design of the cooling channel 12 makes the overall structure of the combustion chamber complex, complicated to manufacture, and heavy. Some combustion chambers using a single-layer wall structure require separate cooling nozzles (i.e., single-component fuel nozzles) to be installed at the edge of the injector 4 to cool the inner wall surface. In this structure, the low-temperature fuel is directly involved in combustion in the combustion chamber after being ejected near the front section 1 of the combustion chamber. The cooling distance is short, and it cannot effectively protect the downstream rear section 2 of the combustion chamber. In the cooling structure of the present invention, the low-temperature fuel is extended to the front end of the combustion chamber rear section 2 in the cooling channel 12, and a section of coolant in the combustion chamber front section 1 is not burned, thereby extending the cooling distance of the coolant. Therefore, the wall surface of the downstream combustion chamber rear section 2 can be well protected at the outlet of the second channel 124, and very little coolant is used, and the cooling effect is also very good.

[0047] The gas generator of this embodiment also includes a liquid collecting ring 3 and an injector 4. The liquid collecting ring 3 surrounds the circumferential outer wall of the combustion chamber front section 1 away from the combustion chamber rear section 2, and forms a distribution channel 31 for low-temperature fuel between the liquid collecting ring 3 and the outer wall of the combustion chamber front section 1; the injector 4 is arranged on the inner wall of the combustion chamber front section 1 away from the combustion chamber rear section 2, and the combustion chamber front section 1 is provided with guide holes 13. The guide holes 13 are evenly distributed along the circumference of the combustion chamber front section 1, and the guide holes 13 are respectively connected to the distribution channel 31 and the injector 4.

[0048] A first flange 14 is provided on the circumferential outer wall of the combustion chamber front section 1 at the end facing away from the combustion chamber rear section 2. A second flange 15 is also provided on the circumferential outer wall of the combustion chamber front section 1, spaced apart from the first flange 14. The two edges of the liquid collecting ring 3 shell are fixedly connected to the first and second flanges 14, 15, respectively, forming a distribution channel 31 between the liquid collecting ring 3 and the outer wall of the combustion chamber front section 1. In some embodiments, the liquid collecting ring 3 and the combustion chamber front section 1 can also be integrally formed. The guide hole 13 and the throttle hole 11 are provided on the outer wall of the combustion chamber front section 1 between the first and second flanges 14, 15, with the guide hole 13 positioned proximate to the first flange 14. To facilitate the molding of the guide hole 13 during additive manufacturing, the guide hole 13 can be designed as a waist-shaped hole, with its length aligning with the length of the combustion chamber front section 1. The outer wall diameter of the combustion chamber front section 1 near the second flange 15 is larger than the outer wall diameter near the first flange 14.

[0049] The injector 4 is disposed within the inner cavity of the combustion chamber front section 1, located between the first flange 14 and the second flange 15, and is integrally formed with the combustion chamber front section 1 through additive manufacturing. The low-temperature fuel in the liquid collecting ring 3 enters the injector 4 through the guide hole 13, is injected into the inner cavity of the combustion chamber front section 1, and then ignites and burns. Because the inner wall of the combustion chamber front section 1 of this embodiment can be cooled by the low-temperature fuel in the cooling channel 12, the injector 4 only needs to be equipped with a two-component centrifugal nozzle, without the need for a spoiler. This ensures the temperature uniformity of the gas in the transverse cross section while simplifying the structure of the gas generator and reducing production costs.

[0050] The throttle hole 11 is positioned near the guide hole 13 to facilitate the distribution of the cryogenic fuel. The throttle hole 11 and the injector 4 are configured so that, by controlling the size of the throttle hole 11 and the size of the nozzle of the injector 4, 90%-97% of the cryogenic fuel in the liquid collector ring 3 flows into the injector 4, while the remainder flows into the cooling channel 12. Directing the majority of the fuel to the injector 4, while using only a small portion as coolant to cool the combustion chamber inner wall, ensures fuel combustion efficiency while simplifying the structure of the cooling channel 12. The cryogenic fuel, acting as coolant, does not need to return to the injector 4 but instead enters the combustion chamber rear section 2 directly and participates in combustion there. The number of guide holes 13 and throttle holes 11 can be multiples, allowing them to be staggered. For example, the number of guide holes 13 can be three times the number of throttle holes 11, with a throttle hole 11 positioned for every three guide holes 13. The guide hole 13 is mainly used to guide the flow to the injector 4 , and the throttle hole 11 is used for throttling, and its aperture is smaller than the guide hole 13 .

[0051] The liquid collecting ring 3, the injector 4 and the combustion chamber front section 1 can be integrally formed by additive manufacturing. The integral forming method can reduce the workload of processing and welding, and at the same time can reduce the overall number of parts and improve the reliability of the gas generator. Alternatively, the liquid collecting ring 3, the injector 4, the combustion chamber rear section 2 and the combustion chamber front section 1 can be manufactured separately, and then the components can be fixed together by welding. For example, the combustion chamber rear section 2 and the combustion chamber front section 1 can be welded and fixed by electron beam welding or laser welding, the liquid collecting ring 3 and the combustion chamber front section 1 can be connected and fixed by argon arc welding, and the inner wall of the combustion chamber front section 1 and the injector 4 can be connected and fixed by brazing.

[0052] An embodiment of the present invention further provides a rocket engine, which includes the gas generator of the above embodiment.

[0053] The embodiment of the present invention further provides a liquid rocket, which includes the rocket engine of the above embodiment. The liquid rocket of this embodiment is applicable to all liquid fuels, such as kerosene, liquid hydrogen, methane, etc.

[0054] The combustion chamber semi-regenerative cooling structure, gas generator, rocket engine and liquid rocket provided by the embodiment of the present invention adopt an integrated semi-regenerative cooling structure based on 3D printing, which adopts a two-stage throttling structure, a two-circle liquid collecting structure, and a spiral channel structure, which greatly improves the uniformity of the coolant. The fuel in the injector is introduced into the middle or downstream of the combustion chamber through the cooling channel on the inner wall of the combustion chamber, so that the coolant is extended and moved downward. By introducing less low-temperature fuel, the downstream combustion chamber wall can be effectively thermally protected. The gas generator of the present invention eliminates the zoned combustion design of the injector and the spoiler device, and the two-component nozzle with the same injector arrangement structure simplifies the overall structural design of the device and greatly improves the uniformity of the gas temperature in the transverse section of the gas generator outlet end. The downstream combustion chamber (the rear section of the combustion chamber) of the gas generator of the embodiment of the present invention has a simple structure and can be made of a single wall, which effectively reduces the overall weight of the gas generator. The combustion chamber semi-regenerative cooling structure, gas generator, rocket engine and liquid rocket provided by the embodiments of the present invention have a simple and compact structure, reduce the manufacturing process of multiple parts, reduce costs, improve reliability, meet the requirements of efficient, reliable and stable combustion of liquid oxygen-kerosene rocket engines using open or closed cycles, and can also be widely applied to other types of liquid propellants.

[0055] In the description of the present invention, it should be noted that the terms "upper, lower, inner, and outer" and other references to orientations or positional relationships are based on the orientations or positional relationships shown in the accompanying drawings and are intended solely to facilitate and simplify the description of the present invention. They are not intended to indicate or imply that the devices or components referred to must have, be constructed, or operate in a specific orientation, and therefore should not be construed as limitations on the present 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.

[0056] In this disclosure, unless otherwise specified or limited, the terms "mounted," "connected," and "connected" should be interpreted broadly. For example, they may refer to fixed, removable, or integral connections. They may also refer to mechanical, electrical, or direct connections, indirect connections through an intermediary, or internal communication between two components. Those skilled in the art will understand the specific meanings of these terms in this disclosure.

[0057] While the present invention has been described with reference to preferred embodiments, various modifications may be made and equivalent components may be substituted without departing from the scope of the present invention. In particular, the various technical features described in the various embodiments may be combined in any manner, provided no structural conflicts exist. The present invention is not limited to the specific embodiments disclosed herein, but encompasses all technical solutions within the scope of the claims.

Claims

1. A combustion chamber semi-regenerative cooling structure, characterized in that: The invention comprises a throttle hole (11) and a cooling channel (12) provided on a front section (1) of the combustion chamber; the throttle hole (11) is provided on the outer wall of the front section (1) of the combustion chamber, and the cooling channel (12) is provided between the inner wall and the outer wall of the front section (1) of the combustion chamber; the throttle hole (11) is connected to the cooling channel (12) and is used to introduce a small portion of the low-temperature fuel in the liquid collecting ring (3) into the cooling channel (12); the cooling channel (12) extends from one end of the front section (1) of the combustion chamber where the injector (4) is provided to the other end, and is used to guide the low-temperature fuel out of the front section (1) of the combustion chamber and inject it onto the inner wall of the rear section (2) of the combustion chamber connected to the front section (1), so as to cool the inner wall of the front section (1) of the combustion chamber and the inner wall of the rear section (2) of the combustion chamber connected to the front section (1).

2. The combustion chamber semi-regenerative cooling structure according to claim 1, characterized in that: A plurality of throttle holes (11) are arranged at intervals along the circumference of the combustion chamber front section (1).

3. The combustion chamber semi-regenerative cooling structure according to claim 1, characterized in that: The cooling channel (12) comprises a first liquid collecting cavity (121) and a first channel (122); the throttle hole (11) is connected to the first liquid collecting cavity (121); and the first liquid collecting cavity (121) is circumferentially arranged around the front section (1) of the combustion chamber.

4. The combustion chamber semi-regenerative cooling structure according to claim 3, characterized in that: The cooling channel (12) further comprises a second liquid collecting cavity (123) and a second channel (124); the second liquid collecting cavity (123) is arranged circumferentially around the front section (1) of the combustion chamber, and the second liquid collecting cavity (123) is connected to the outlet of the first channel (122).

5. The combustion chamber semi-regenerative cooling structure according to claim 4, characterized in that: The number of the second channels (124) is less than the number of the first channels (122), and the flow area of ​​a single second channel (124) is no greater than the flow area of ​​a single first channel (122).

6. The combustion chamber semi-regenerative cooling structure according to claim 4, characterized in that: The first channel (122) and / or the second channel (124) extend in a spiral shape along the axial direction of the combustion chamber front section (1).

7. The combustion chamber semi-regenerative cooling structure according to claim 6, characterized in that: The helix angle of the first channel (122) and / or the second channel (124) ranges from 10° to 40°.

8. A gas generator, characterized in that: The invention comprises a combustion chamber front section (1) and a combustion chamber rear section (2) which are connected to each other, wherein the combustion chamber front section (1) is provided with a combustion chamber semi-regenerative cooling structure as described in any one of claims 1 to 7, and the combustion chamber rear section (2) is a single-layer wall structure, and the cooling channel (12) is used to spray low-temperature fuel onto the inner wall of the combustion chamber rear section (2) at the outlet.

9. The gas generator according to claim 8, characterized in that The diameter of the inner wall of the combustion chamber rear section (2) is not greater than the diameter of the inner wall of the combustion chamber front section (1) at the outlet of the cooling channel (12).

10. The gas generator according to claim 8, characterized in that It also includes a liquid collecting ring (3) and an injector (4), wherein the liquid collecting ring (3) surrounds the circumferential outer wall of the front section (1) of the combustion chamber away from the rear section (2) of the combustion chamber, and forms a distribution channel (31) for low-temperature fuel between the liquid collecting ring and the outer wall of the front section (1) of the combustion chamber; the injector (4) is arranged on the inner wall of the front section (1) of the combustion chamber away from the rear section (2) of the combustion chamber, and the front section (1) of the combustion chamber is provided with a guide hole (13), and the guide hole (13) is connected to the distribution channel (31) and the injector (4) respectively.

11. The gas generator according to claim 10, characterized in that The throttle hole (11) is arranged close to the guide hole (13), and the throttle hole (11) and the injector (4) are configured so that 90%-97% of the low-temperature fuel in the liquid collecting ring (3) enters the injector (4) by controlling the size of the throttle hole (11) and the size of the nozzle of the injector (4), and the remaining low-temperature fuel enters the cooling channel (12).

12. The gas generator according to claim 10, wherein: The combustion chamber front section (1) and the injector (4) are manufactured in one piece by using additive manufacturing technology.

13. A rocket engine, characterized in that: Comprising the gas generator according to any one of claims 8 to 12.

14. A liquid rocket, characterized in that: Comprising a rocket engine as claimed in claim 13.

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