Multi-way connection structure and engine system

Abstract

The present application provides a multi-way connection structure and an engine system. The multi-way connection structure is used to connect a propellant tank of a launch vehicle and at least two engines, and includes: a housing, which is hollow; a propellant inlet is provided at the top end of the housing; at least two first propellant outlets are provided in the circumferential direction of the housing; a flow splitting assembly, which includes a flow splitting member and at least one partition; the flow splitting member is hollow, the opening at the top end is smaller than the propellant inlet, the bottom end passes through the housing and has a second propellant outlet; the outer peripheral wall section starting from the top end of the flow splitting member has a gradually increasing diameter, and the bottom end is connected to the peripheral edge of the bottom end of the housing; each partition is arranged at a circumferential interval along the outer peripheral wall section, and the cavity between the outer peripheral wall section and the housing is separated into at least one independent first flow channel, each of which is communicated with each first propellant outlet. Compared with a right-angle flow channel, the first flow channel of the present application has a larger transition angle, which can reduce the possibility of the propellant forming a vortex in the multi-way connection structure.

Description

Technical Field

[0001] This application relates to the technical field of launch vehicle power systems. Specifically, this application relates to a multi-way connection structure and an engine system. Background Art

[0002] Due to the thrust requirements of launch vehicles, a launch vehicle may need to be equipped with multiple engines. Multiple engines are connected in parallel to form the power system of the launch vehicle, providing the thrust required by the launch vehicle.

[0003] For a launch vehicle with multiple engines connected in parallel, the propellant generally adopts a delivery scheme of "main delivery pipe + multi-way connection structure + branch delivery pipe". The multi-way connection structure is used to achieve the diversion of the propellant, and the propellant in the same propellant tank is respectively delivered to multiple different engines.

[0004] In the traditional multi-way main structure, the flow of the propellant is easily obstructed to a large extent, and thus eddy currents are likely to be formed. Summary of the Invention

[0005] Aiming at the shortcomings of the existing methods, this application proposes a multi-way connection structure and an engine system to solve the technical problem that eddy currents are likely to be formed in the traditional right-angle multi-way in the related art.

[0006] In a first aspect, an embodiment of this application provides a multi-way connection structure for connecting a propellant tank of a launch vehicle and at least two engines, including:

[0007] A housing, which is hollow; a propellant inlet is provided at the top of the housing; at least two first propellant outlets are provided circumferentially on the housing;

[0008] A flow splitting assembly, including a flow splitting member and at least one partition;

[0009] The flow splitting member is hollow, the opening at the top is smaller than the propellant inlet, the bottom end passes through the housing and has a second propellant outlet; the outer peripheral wall section starting from the top of the flow splitting member has a gradually increasing diameter, and the bottom end is connected to the peripheral edge of the bottom end of the housing;

[0010] Each partition is arranged at a circumferential interval along the outer peripheral wall section, separating the cavity between the outer peripheral wall section and the housing into at least one independent first flow channel, each of which communicates with each first propellant outlet.

[0011] In some possible embodiments, the flow splitting member includes:

[0012] A guiding portion, serving as the outer peripheral wall section, is hollow and trumpet-shaped; the opening at the top of the guiding portion is smaller than the opening at the bottom, and it is located at the center of the propellant inlet; the outer peripheral edge of the bottom end of the guiding portion is connected to the opening edge of the bottom end of the housing.

[0013] In some possible embodiments, the partition extends radially along the guiding portion and is connected to the housing; the top end of the partition extends to the edge of the propellant inlet.

[0014] In some possible embodiments, the partition is fan-shaped, the arc side is fittingly connected to the outer peripheral surface of the guiding portion, the top side is flush with the top end of the guiding portion, and the side is connected to the inner peripheral wall of the housing.

[0015] In some possible embodiments, the flow dividing member further includes:

[0016] A straight cylindrical portion, which is cylindrical, with both ends open and hollow;

[0017] The straight cylindrical portion is arranged inside the guiding portion, the top end is integrally formed with the top end of the guiding portion, and there is a gap between the portion near the bottom end and the portion near the bottom end of the guiding portion.

[0018] In some possible embodiments, the inlets of the first flow channels are arranged circumferentially around the outer periphery of the top opening of the guiding portion along the circumferential pitch of the outer peripheral wall section;

[0019] In the plane where the propellant inlet is located, the orthographic projections of the inlets of the first flow channels and the top opening of the guiding portion all fall within the range of the propellant inlet.

[0020] In some possible embodiments, the edges of the propellant inlet and the first propellant outlet each have a flanging extending towards the outside of the housing;

[0021] The multi-pass connection structure further includes:

[0022] An inlet flange, one side of which is connected to the flanging at the propellant inlet;

[0023] At least two outlet flanges, each connected to the flanging at the first propellant outlet and the second propellant outlet.

[0024] In some possible embodiments, the inlet flange includes an inner ring and an outer ring. Along the radial direction of the inlet flange, both the inner ring and the outer ring are suspended outside the flanging;

[0025] The inner ring has a plurality of threaded holes distributed at circumferential intervals for connecting with the delivery pipe of the propellant storage tank, and the outer ring of the inlet flange has a plurality of oblong holes distributed at circumferential intervals for connecting with the bottom of the propellant storage tank.

[0026] In a second aspect, the present application further provides an engine system, including: a propellant storage tank, at least two engines, and any one of the multi-pass connection structures provided in the first aspect above;

[0027] The propellant inlet of the multi-pass connection structure is connected to the propellant storage tank, and the first propellant outlet and the second propellant outlet of the multi-pass connection structure are respectively connected to the engines in one-to-one correspondence.

[0028] In some possible embodiments, the engines connected to the first propellant outlet are evenly distributed around the engines connected to the second propellant outlet.

[0029] The beneficial technical effects brought by the technical solutions provided in the embodiments of the present application include:

[0030] The multi-pass connection structure of the embodiments of the present application includes a hollow housing. The flow dividing member divides the housing into spaces that are independent of each other inside and outside the flow dividing member. The space outside the flow dividing member is divided into at least one independent first flow channel through a partition plate, which communicates the propellant inlet and the first propellant outlet; the space inside the flow dividing member communicates the propellant inlet and the second propellant outlet.

[0031] The outer peripheral wall section starting from the top end of the flow dividing member has a gradually increasing diameter, so that the side wall of the first flow channel is arc-shaped. Compared with a right-angle flow channel, the first flow channel of the present application has a larger transition angle, which can reduce the possibility of the propellant forming a vortex in the multi-pass connection structure.

[0032] The flow dividing member penetrates through the housing, so that the space inside the flow dividing member forms a vertical flow channel, making the flow direction of the fluid consistent with the flow channel direction, which can reduce the friction and turbulence phenomena during the flow process, reduce the resistance of the propellant flow, improve the transmission efficiency, and further reduce the possibility of the propellant forming a vortex in the multi-pass connection structure.

[0033] The additional aspects and advantages of the present application will be partially given in the following description, and these will become obvious from the following description, or will be understood through the practice of the present application. Description of the Drawings

[0034] The above-mentioned and / or additional aspects and advantages of the present application will become obvious and easy to understand from the following description of the embodiments in conjunction with the drawings, where:

[0035] Figure 1 is a schematic structural diagram of a multi-pass connection structure provided by an embodiment of the present application from a first perspective;

[0036] Figure 2 is a schematic structural diagram of a multi-pass connection structure provided by an embodiment of the present application from a second perspective;

[0037] Figure 3 is a front view structural schematic diagram of a multi-pass connection structure provided by an embodiment of the present application;

[0038] Figure 4 is a sectional structural schematic diagram of a multi-pass connection structure provided by an embodiment of the present application;

[0039] Figure 5 is a schematic structural diagram of a flow dividing assembly of a multi-pass connection structure provided by an embodiment of the present application.

[0040] Reference numerals:

[0041] 100 - Multi - way connection structure; 101 - First flow channel;

[0042] 10 - Housing;

[0043] 11 - Propellant inlet; 12 - First propellant outlet;

[0044] 20 - Diverting component;

[0045] 21 - Diverter; 210 - Second propellant outlet; 211 - Guiding part; 212 - Straight cylinder part;

[0046] 22 - Partition board;

[0047] 30 - Flange;

[0048] 40 - Inlet flange;

[0049] 41 - Threaded hole; 42 - Oval hole;

[0050] 50 - Outlet flange. Detailed implementation mode

[0051] The embodiments of the present application will be described below with reference to the drawings in the present application. It should be understood that the embodiments described below in conjunction with the drawings are exemplary descriptions for explaining the technical solutions of the embodiments of the present application, and do not constitute limitations on the technical solutions of the embodiments of the present application.

[0052] Those skilled in the art of the present technology can understand that unless specifically stated, the terms "the" and "this" used here may also include plural forms. It should be further understood that the term "including" used in the specification of the present application means the presence of the described features, integers, elements, and / or components, but does not exclude the implementation of other features, information, data, operations, elements, components, and / or their combinations, etc. supported by the art of the present technology. The term "and / or" used here means at least one of the items defined by this term. For example, "A and / or B" can be implemented as "A", or implemented as "B", or implemented as "A and B".

[0053] To make the purpose, technical solutions, and advantages of the present application clearer, the embodiments of the present application will be further described in detail below with reference to the drawings.

[0054] First, the nouns involved in the present application will be introduced and explained:

[0055] Multi - way connection structure: Connected between the propellant tank and multiple engines to divert the propellant into multiple engines.

[0056] Propellant tank: A structure for storing propellant.

[0057] Due to the thrust requirements of the launch vehicle, a launch vehicle may need to be equipped with multiple engines. Multiple engines are connected in parallel to form the power system of the launch vehicle, providing the thrust required by the launch vehicle.

[0058] For a launch vehicle with multiple engines connected in parallel, the propellant generally adopts a delivery scheme of "main delivery pipe + multi-way connection structure + branch delivery pipe". The multi-way connection structure is used to achieve the splitting of the propellant, and the propellant in the same propellant tank is respectively delivered to multiple different engines.

[0059] The traditional multi-way main structure is generally a right-angle multi-way. The internal inlet fluid channel is perpendicular to the outlet fluid channel, that is, the transition angle of the propellant flow channel is a right angle, which causes a large obstruction to the flow of the propellant and is prone to form eddy currents.

[0060] The multi-way connection structure and the engine system provided in this application aim to solve the above technical problems in the related art.

[0061] The following uses specific embodiments to elaborate in detail on the technical solution of this application and how the technical solution of this application solves the above technical problems. It should be noted that the following embodiments can refer to, draw on, or combine with each other. For the same terms, similar features, and similar implementation steps in different embodiments, they will not be described repeatedly.

[0062] An embodiment of this application provides a multi-way connection structure 100 for connecting the propellant tank of a launch vehicle and at least two engines. Please refer to Figures 1 - 4 , the multi-way connection structure 100 includes: a housing 10 and a flow splitting component 20.

[0063] The housing 10 is hollow; a propellant inlet 11 is provided at the top of the housing 10; at least two first propellant outlets 12 are provided on the circumferential direction of the housing 10.

[0064] The flow splitting component 20 includes a flow splitting member 21 and at least one partition 22.

[0065] The flow splitting member 21 is hollow, the opening at the top is smaller than the propellant inlet 11, the bottom end passes through the housing 10 and has a second propellant outlet 210; the outer peripheral wall section starting from the top of the flow splitting member 21 has a gradually increasing diameter, and the bottom end is connected to the bottom periphery of the housing 10.

[0066] Each partition 22 is arranged at a circumferential interval along the outer peripheral wall section, separating the cavity between the outer peripheral wall section and the housing 10 into at least one independent first flow channel 101, each of which is communicated with each first propellant outlet 12.

[0067] In this embodiment, the multi-way connection structure 100 includes a hollow housing 10. The flow divider 21 divides the interior of the housing 10 into independent spaces inside and outside the flow divider 21. The space outside the flow divider 21 is divided into at least one independent first flow channel 101 by a partition 22, which connects the propellant inlet 11 and the first propellant outlet 12. One first propellant outlet 12 is connected to one engine; the space inside the flow divider 21 is connected to the propellant inlet 11 and the second propellant outlet 210, and one second propellant outlet 210 is connected to one engine.

[0068] The outer peripheral wall section starting from the top end of the flow divider 21 has a gradually increasing diameter, so that the side wall of the first flow channel 101 is arc-shaped. Compared with a right-angled flow channel, the first flow channel 101 of the present application has a larger transition angle, which can reduce the probability of the propellant forming vortices in the multi-way connection structure 100 or avoid vortices.

[0069] The flow divider 21 penetrates through the housing 10, so that the space inside the flow divider 21 forms a vertical flow channel, making the flow direction of the fluid consistent with the flow channel direction. This can reduce friction and turbulence during the flow process, reduce the resistance of the propellant flow, improve the transmission efficiency, and further reduce the possibility of the propellant forming vortices in the multi-way connection structure 100.

[0070] In some possible embodiments, the housing 10 is spherical, and the first propellant outlets 12 are spaced apart on the equatorial circle of the housing 10, which can improve the space utilization rate of the multi-way connection structure 100, increase the number of first propellant outlets 12, and thus increase the number of engines and improve the thrust of the launch vehicle.

[0071] In some possible embodiments, please refer to Figure 4 , the flow divider 21 includes: a guiding portion 211.

[0072] The guiding portion 211 is an outer peripheral wall section, which is hollow and trumpet-shaped; the top opening of the guiding portion 211 is smaller than the bottom opening and is located at the center of the propellant inlet 11; the outer peripheral edge of the bottom end of the guiding portion 211 is connected to the opening edge of the bottom end of the housing 10.

[0073] In this embodiment, the top opening of the guiding portion 211 is located at the center of the propellant inlet 11, dividing the propellant inlet 11 into different inlets communicating inside and outside the guiding portion 211. The bottom end of the guiding portion 211 is integrally connected to the bottom end of the housing 10, so that the spaces inside and outside the guiding portion 211 are independent of each other. In the spaces inside and outside the guiding portion 211, the flow of the propellant does not affect each other, and thus the possibility of the propellant generating vortices in the multi-way connection structure 100 can be reduced.

[0074] In some possible embodiments, please refer to Figure 1 and Figure 5, the partition 22 extends radially along the guiding part 211 and is connected to the housing 10; the top end of the partition 22 extends to the edge of the propellant inlet 11.

[0075] In this embodiment, the partition 22 is disposed between the housing 10 and the guiding part 211, and divides the space outside the guiding part 211 into a plurality of juxtaposed first flow channels 101. Moreover, the top end of the partition 22 extends to the edge of the propellant inlet 11, and divides the propellant inlet 11 into inlets of a plurality of juxtaposed first flow channels 101. Furthermore, the outlet of the first flow channel 101, i.e., the first propellant outlet 12, is disposed circumferentially of the multi-way connection structure 100, and the guiding part 211 can reasonably transition the first flow channel 101 towards the first propellant outlet 12, thereby improving the space utilization rate of the housing 10.

[0076] In some possible embodiments, please refer to Figure 4 , the outer peripheral surface of the guiding part 211 has a smooth curved surface, so that an arc transition is formed from the top end to the bottom end of the guiding part 211, which has a certain flow guiding effect and can guide the propellant to flow out towards the first propellant outlet 12. Moreover, the arc transition enables the first flow channel 101 to have a relatively large transition angle, which can reduce the resistance of the propellant during the flow process, increase the flow velocity of the propellant, and reduce the possibility of forming vortices in the multi-way connection structure 100.

[0077] In some possible embodiments, please refer to Figure 1 and Figure 5 , the partition 22 is fan-shaped, the arc side is in fitting connection with the outer peripheral surface of the guiding part 211, the top side is flush with the top end of the guiding part 211, and the side is connected to the inner peripheral wall of the housing 10.

[0078] In this embodiment, the arc side of the partition 22 is in contact with the outer peripheral surface of the guiding part 211, and the side is connected to the inner peripheral wall of the housing 10 to form a plurality of independent first flow channels 101. The top side of the partition 22 is flush with the top end of the guiding part 211, and divides the propellant inlet 11 into inlets of a plurality of juxtaposed first flow channels 101, which are respectively communicated with a plurality of first flow channels 101.

[0079] In some possible embodiments, please refer to Figure 4 , the flow dividing member 21 further includes: a straight cylinder part 212.

[0080] The straight cylinder part 212 is cylindrical, with both ends open and hollow.

[0081] The straight cylinder part 212 is disposed inside the guiding part 211, the top end is integrally connected with the top end of the guiding part 211, and there is a gap between the part near the bottom end and the part of the guiding part 211 near the bottom end.

[0082] In this embodiment, a straight tube portion 212 is provided inside the guiding portion 211. The flow channel inside the straight tube portion 212 is straight and smooth, such that the resistance encountered by the propellant during flow is small. Since the flow direction of the fluid is consistent with the direction of the flow channel, the friction and turbulence phenomena during the flow process are reduced, thereby improving the fluid transmission efficiency. Moreover, there is a gap between the portion of the straight tube portion 212 near the bottom end and the portion of the guiding portion 211 near the bottom end, which is equivalent to a hollowing-out design between the guiding portion 211 and the straight tube portion 212, capable of reducing the weight of the flow dividing member 21 and saving the material cost of the flow dividing member 21.

[0083] In the related art, the multi-way connection structure 100 is spherical and is manufactured by adopting an overall machining process or a process scheme of "pressure inflation molding + electron beam welding". The overall machining process can only manufacture multi-way connection structures 100 with relatively small sizes. The "pressure inflation molding + electron beam welding" process additionally invests in a molding die, and the entire sphere manufactured has a relatively large volume.

[0084] Therefore, in some possible embodiments, the multi-way connection structure 100 can be manufactured by adopting laser precision machining technology. Laser precision machining uses computer programming and can perform material nesting for products with different shapes. For example, it can perform a hollowing-out design between the guiding portion 211 and the straight tube portion 212, maximizing the material utilization rate, reducing the weight of the flow dividing member 21, and saving the material cost of the flow dividing member 21.

[0085] In some possible embodiments, please refer to Figure 1 , the circumferential spacing of the inlets of the respective first flow channels 101 is disposed around the outer periphery of the top opening of the guiding portion 211.

[0086] In the plane of the propellant inlet 11, the projections of the inlets of the respective first flow channels 101 and the top opening of the guiding portion 211 all fall within the range of the propellant inlet 11.

[0087] In this embodiment, the circumferential spacing of the inlets of the respective first flow channels 101 is disposed around the outer periphery of the top opening of the guiding portion 211 and is evenly distributed, which can reduce the safety risks caused by uneven local pressure and improve the safety and reliability of the entire propulsion system. The projections of the inlets of the respective first flow channels 101 and the top opening of the guiding portion 211 all fall within the range of the propellant inlet 11, ensuring that the propellant inlet 11 area completely covers the inlets of the respective first flow channels 101 and the top opening area of the guiding portion 211, and further ensuring the flow rate of the propellant flowing into the respective first flow channels 101 and the straight tube portion 212, and ensuring the effective operation of multiple engines.

[0088] In some possible embodiments, please refer to Figure 1 and Figure 3, the edges of the propellant inlet 11 and the first propellant outlet 12 each have flanges 30 extending outwardly towards the outside of the housing 10.

[0089] The multi-pass connection structure 100 further includes:

[0090] An inlet flange 40, one side of which is connected to the flange 30 at the propellant inlet 11;

[0091] At least two outlet flanges 50, each connected to the flange 30 at the first propellant outlet 12 and the second propellant outlet 210 respectively.

[0092] In this embodiment, the flange 30 extends out of the propellant inlet 11 and the first propellant outlet 12. The flange 30 at the propellant inlet 11 is fixedly connected to one side of the inlet flange 40, and the inlet flange 40 is connected to the propellant tank, so that the propellant inlet 11 is connected to the propellant tank.

[0093] In some possible embodiments, the size of the first propellant outlet 12 is the same as that of the second propellant outlet 210, and the sizes of the corresponding outlet flanges 50 are all the same, which is convenient for communicating with multiple pipes of the same specification.

[0094] In some possible embodiments, please refer to Figure 1 and Figure 2 , the inlet flange 40 includes an inner ring and an outer ring. Along the radial direction of the inlet flange 40, both the inner ring and the outer ring are suspended outside the flange 30.

[0095] The inner ring has a plurality of threaded holes 41 distributed at circumferential intervals for connecting with the delivery pipe of the propellant tank. The outer ring of the inlet flange 40 has a plurality of oblong holes 42 distributed at circumferential intervals for connecting with the bottom of the propellant tank.

[0096] In this embodiment, both the inner ring and the outer ring are suspended outside the flange 30, which is convenient for the staff to operate and connect the inlet flange 40 to the delivery pipe of the propellant tank and the bottom of the propellant tank. Moreover, the oblong holes 42 in the outer ring of the inlet flange 40 have a certain compensation effect, which is convenient for improving the possibility of aligning the outer ring of the inlet flange 40 with the bottom of the propellant tank while aligning the inner ring of the inlet flange 40 with the propellant delivery pipe, thereby improving the connection efficiency.

[0097] Based on the same inventive concept, the present application also provides an engine system, including: a propellant tank, at least two engines, and the multi-pass connection structure 100 provided in any of the above embodiments.

[0098] The propellant inlet 11 of the multi-pass connection structure 100 is connected to the propellant tank, and the first propellant outlet 12 and the second propellant outlet 210 of the multi-pass connection structure 100 are respectively connected to the engines in one-to-one correspondence.

[0099] In this embodiment, since the engine system adopts any one of the multi-pass connection structures 100 provided in the foregoing embodiments, for the principles and technical effects, please refer to the foregoing embodiments and will not be elaborated herein. The engine system further includes a plurality of engines connected in parallel through the multi-pass connection structure 100. The propellant tank conveys propellant to the plurality of engines through the multi-pass connection structure 100, so that the plurality of engines can simultaneously have a source of propellant and can operate at the required time, providing sufficient thrust for the launch vehicle.

[0100] Moreover, the outer peripheral wall section starting from the top end of the diverter 21 of the multi-pass connection structure 100 has an increasing diameter, so that the side wall of the first flow channel 101 is arc-shaped. Compared with a right-angle flow channel, the first flow channel 101 of the present application has a larger transition angle, which can reduce the possibility of the propellant forming vortices in the multi-pass connection structure 100.

[0101] The diverter 21 penetrates through the housing 10, so that the space inside the diverter 21 forms a vertical flow channel, enabling the flow direction of the fluid to be consistent with the flow channel direction, which can reduce friction and turbulence phenomena during the flow process, reduce the resistance of the propellant flow, improve the transmission efficiency, and further reduce the possibility of the propellant forming vortices in the multi-pass connection structure 100.

[0102] In some possible embodiments, the engines connected to the first propellant outlet 12 are evenly distributed around the engines connected to the second propellant outlet 210.

[0103] In this embodiment, the engine connected to the second propellant outlet 210 is arranged in the center and at least partially coincides with the second propellant inlet 11 in the vertical direction, so that the pipeline connecting the second propellant outlet 210 and the engine goes straight down and is connected to the top end of the engine without bending, ensuring that the propellant always has low resistance and high transmission rate during the process of flowing from the second propellant outlet 210 to the engine. Around the engine connected to the second propellant outlet 210, a plurality of engines are evenly distributed and are connected to the first propellant outlet 12 one by one through pipelines. The pipelines are in a shape of '7', starting from the first propellant outlet 12 arranged circumferentially on the multi-pass connection structure 100, extending horizontally, bending downward in the middle, and then vertically connecting to the top end of the engine. The engine layout in this embodiment is reasonable, which can adapt to the orientations of the outlets of the multi-pass connection structure 100, making the spatial layout of the engine system evenly distributed, optimizing the weight distribution, and also being beneficial to improving the flow balance of the propellant flowing into each engine.

[0104] Applying the embodiments of the present application can at least achieve the following beneficial effects:

[0105] 1. In some embodiments, the outer peripheral wall segment starting from the top end of the flow splitter 21 has a gradually increasing diameter, such that the side wall of the first flow channel 101 is arc-shaped. Compared with a right-angle flow channel, the first flow channel 101 of the present application has a larger transition angle, which can reduce the probability of the propellant forming eddy currents in the multi-pass connection structure 100 or avoid eddy currents. The flow splitter 21 penetrates the housing 10, such that the space within the flow splitter 21 forms a vertical flow channel, enabling the flow direction of the fluid to be consistent with the flow channel direction, which can reduce friction and turbulence during the flow process, reduce the resistance of the propellant flow, improve the transmission efficiency, and thus also reduce the possibility of the propellant forming eddy currents in the multi-pass connection structure 100.

[0106] 2. In some embodiments, the top opening of the guiding portion 211 is located at the center of the propellant inlet 11, separating the propellant inlet 11 into different inlets communicating the inside and outside of the guiding portion 211. The bottom end of the guiding portion 211 is integrally connected to the bottom end of the housing 10, such that the spaces inside and outside the guiding portion 211 are independent of each other. In the spaces inside and outside the guiding portion 211, the flow of the propellant does not affect each other, and thus the possibility of the propellant generating eddy currents in the multi-pass connection structure 100 can be reduced.

[0107] 3. In some embodiments, a straight cylinder portion 212 is provided inside the guiding portion 211. The flow channel inside the straight cylinder portion 212 is straight and smooth, such that the resistance encountered by the propellant during the flow process is small. Since the flow direction of the fluid is consistent with the flow channel direction, friction and turbulence during the flow process are reduced, thereby improving the transmission efficiency of the fluid. Moreover, a gap exists between the portion of the straight cylinder portion 212 near the bottom end and the portion of the guiding portion 211 near the bottom end, which is equivalent to a hollow design between the guiding portion 211 and the straight cylinder portion 212, capable of reducing the weight of the flow splitter 21 and saving the material cost of the flow splitter 21.

[0108] 4. In some embodiments, the inlets of the respective first flow channels 101 are circumferentially spaced along the outer peripheral wall segment and are disposed around the outer periphery of the top opening of the guiding portion 211 and are evenly distributed, which can reduce the safety risks caused by local pressure unevenness and improve the safety and reliability of the entire propulsion system. The orthographic projections of the inlets of the respective first flow channels 101 and the top opening of the guiding portion 211 all fall within the range of the propellant inlet 11, ensuring that the propellant inlet 11 area completely covers the inlets of the respective first flow channels 101 and the top opening area of the guiding portion 211, and thus ensuring the flow rate of the propellant flowing into the respective first flow channels 101 and the straight cylinder portion 212 and ensuring the effective operation of multiple engines.

[0109] In the description of the present application, the directions or positional relationships indicated by terms such as "center", "upper", "lower", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", etc. are based on the exemplary directions or positional relationships shown in the drawings, and are for the convenience of describing or simplifying the embodiments of the present application, rather than indicating or implying that the device or component referred to must have a specific orientation, or be constructed and operated in a specific orientation. Therefore, it should not be construed as a limitation to the present application.

[0110] The terms "first" and "second" are used only for descriptive purposes, and should not be construed as indicating or implying relative importance or implicitly specifying the quantity of the indicated technical features. Thus, features defined with "first" and "second" may explicitly or implicitly include one or more of such features. In the description of the present application, unless otherwise specified, the meaning of "a plurality" is two or more.

[0111] In the description of the present application, it should be noted that, unless otherwise clearly specified and limited, the terms "mounted", "connected" and "coupled" should be understood in a broad sense. For example, it may be a fixed connection, a detachable connection, or an integral connection; it may be a direct connection, or an indirect connection through an intermediate medium, and it may be the communication inside two elements. For those of ordinary skill in the art, the specific meanings of the above terms in the present application can be understood according to specific circumstances.

[0112] In the description of this specification, the specific features, structures, materials or characteristics may be combined in a suitable manner in any one or more of the embodiments or examples.

[0113] The above are only some embodiments of the present application. It should be noted that for those of ordinary skill in the art, without departing from the technical concept of the present application, other similar implementation means based on the technical idea of the present application also belong to the protection scope of the embodiments of the present application.

Claims

1. A multi-way connection structure, characterized in that, For connecting a propellant tank of a launch vehicle and at least two engines, comprising: A housing, which is hollow; a propellant inlet is provided at the top end of the housing; at least two first propellant outlets are provided circumferentially on the housing. A flow splitting assembly, comprising a flow splitter and at least one partition. The flow splitter is hollow, the opening at the top end is smaller than the propellant inlet, the bottom end passes through the housing, and the flow splitter has a second propellant outlet. The space inside the flow splitter communicates the propellant inlet and the second propellant outlet; the outer peripheral wall section starting from the top end of the flow splitter has a gradually increasing diameter, and the bottom end is connected to the peripheral edge of the bottom end of the housing. Each of the partitions is arranged at a circumferential interval along the outer peripheral wall section, separating the cavity between the outer peripheral wall section and the housing into at least one independent first flow channel, each communicating with each of the first propellant outlets.

2. The multi-way connection structure according to claim 1, wherein The flow splitter comprises: A guiding portion, which is the outer peripheral wall section, hollow and in a horn shape; the opening at the top end of the guiding portion is smaller than the opening at the bottom end, and is located at the center of the propellant inlet; the outer peripheral edge of the bottom end of the guiding portion is connected to the opening edge of the bottom end of the housing.

3. The multi-way connection structure according to claim 2, wherein, The partition extends radially along the guiding portion and is connected to the housing; the top end of the partition extends to the edge of the propellant inlet.

4. The multi-way connection structure according to claim 3, wherein, The partition is in a fan shape, the arc edge is fittingly connected to the outer peripheral surface of the guiding portion, the top edge is flush with the top end of the guiding portion, and the side edge is connected to the inner peripheral wall of the housing.

5. The multi-way connection structure according to claim 2, characterized in that, The flow splitter further comprises: A straight cylinder portion, which is cylindrical, with both ends open and hollow. The straight cylinder portion is arranged inside the guiding portion, the top end is integrally connected with the top end of the guiding portion, and there is a gap between the part near the bottom end and the part near the bottom end of the guiding portion.

6. The multi-way connection structure according to claim 2, characterized in that, The inlets of each of the first flow channels are circumferentially arranged at intervals around the outer periphery of the opening at the top end of the guiding portion. In the plane where the propellant inlet is located, the projections of the inlets of each of the first flow channels and the opening at the top end of the guiding portion all fall within the range of the propellant inlet.

7. The multi-way connection structure according to claim 1, characterized in that, Flanges extend outward from the edges of the propellant inlet and the first propellant outlet respectively towards the outside of the housing. The multi-way connection structure further comprises: An inlet flange, one side of which is connected to the flange at the propellant inlet. At least two outlet flanges, each connected to the flange at the first propellant outlet and the second propellant outlet respectively.

8. The multi-way connection structure according to claim 7, characterized in that, The inlet flange includes an inner ring and an outer ring. Along the radial direction of the inlet flange, both the inner ring and the outer ring are suspended outside the flange. The inner ring has a plurality of threaded holes distributed at circumferential intervals for connecting with the delivery pipe of the propellant tank, and the outer ring of the inlet flange has a plurality of oblong holes distributed at circumferential intervals for connecting with the bottom of the propellant tank.

9. An engine system, characterized in that, Comprising: A propellant tank, at least two engines and a multi-way connection structure as described in any one of claims 1 - 8 above. The propellant inlet of the multi-way connection structure is connected to the propellant tank, and the first propellant outlet and the second propellant outlet of the multi-way connection structure are respectively connected to the engines in one-to-one correspondence.

10. The engine system according to claim 9, characterized in that, The engines connected to the first propellant outlet are evenly distributed around the engines connected to the second propellant outlet.

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