Diaphragm assembly, rocket propulsion system starter and rocket propulsion system

Abstract

This application provides a diaphragm assembly, a starter for a rocket propulsion system, and a rocket propulsion system. The diaphragm assembly, used in the starter of a rocket propulsion system, includes: a mounting base, at least partially inserted axially and sealed to the nozzle of the starter; the mounting base includes a first part and a second part distributed axially; the first part has multiple axially oriented perforations; the second part has a recessed structure with its opening facing away from the first part; a diaphragm, the outer peripheral wall of which is connected to the inner peripheral wall of the recessed structure; and perforations communicating between the space within the nozzle and the diaphragm. The diaphragm assembly provided in this application has high connection reliability with the nozzle, good sealing performance, and is easy to replace, thus improving the reusability and economy of the rocket propulsion system starter.

Description

Technical Field

[0001] This application relates to the field of rocket propulsion system technology for launch vehicles, and more specifically, to a diaphragm assembly, a rocket propulsion system starter, and a rocket propulsion system. Background Technology

[0002] In the rocket propulsion system of a launch vehicle, an starter is often required to provide initial kinetic energy for the turbopump of the rocket propulsion system to start spinning. With the rapid development of application technologies such as rocket orbit change, precise rocket orbit insertion, and reusable rockets, the technology of multiple restarts of liquid rocket propulsion systems has become crucial.

[0003] Multiple starts are required for a rocket propulsion system. Each start uses at least one starter to generate energy, driving the turbopump to deliver propellant to the engine combustion chamber for combustion and thrust generation. Taking a secondary start as an example, each start uses a separate starter. The secondary starter must isolate itself from the high-temperature, high-pressure combustion gases generated after the first start to prevent accidental activation of the secondary starter due to continuous gas impact, which could lead to malfunctions in the rocket propulsion system.

[0004] In related technologies, the diaphragm of the starter is easily detached or ruptured by the impact of the high temperature and high pressure gas generated during the previous start-up, which can cause the starter to work abnormally and lead to the failure of the launch vehicle launch. Summary of the Invention

[0005] This application addresses the shortcomings of existing methods by proposing a diaphragm assembly, a starter for a rocket propulsion system, and a rocket propulsion system to solve the technical problem in related technologies where the diaphragm of the starter is easily detached or ruptured due to the impact of high-temperature and high-pressure gas generated during the previous start-up.

[0006] In a first aspect, embodiments of this application provide a diaphragm assembly applied to an starter in a rocket propulsion system, comprising:

[0007] The mounting base extends at least partially into and is sealed to the nozzle of the starter along the axial direction; the mounting base includes a first part and a second part distributed along the axial direction; the first part has multiple axially oriented cutouts; the second part has a recessed structure with an opening facing away from the first part.

[0008] The outer peripheral wall of the diaphragm is connected to the inner peripheral wall of the recessed structure;

[0009] The perforation connects the space inside the nozzle and the diaphragm.

[0010] In some possible embodiments, one side of the diaphragm contacts or abuts against the first part, sealing the perforation.

[0011] In some possible embodiments, at least part of the outer diameter of the second part is larger than the outer diameter of the first part.

[0012] In some possible embodiments, along the radial direction, the peripheral walls of the outermost hollowed-out, recessed structure and the outer peripheral wall of the first part are successively moved away from the axial direction.

[0013] In some possible embodiments, the diaphragm includes a planar portion and an edge portion connected to the outer peripheral wall of the planar portion;

[0014] The edge portion and the flat surface are flush with the side facing the first part, the edge portion extends along the axial direction away from the first part, and gradually thickens along the radial direction away from the flat surface portion.

[0015] In some possible embodiments, the first part is recessed on the side facing into the nozzle, with the deepest recess located at the center of the first part.

[0016] In some possible embodiments, the side of the diaphragm away from the first part has multiple strip-shaped grooves;

[0017] The midpoints of multiple indentations intersect and are located at the center of the membrane;

[0018] The center of the first part coincides with the midpoint of the intersection of multiple engravings along the axial direction.

[0019] In some possible embodiments, the recessed structure includes a first recessed segment and a second recessed segment distributed along an axial direction away from the first portion;

[0020] The radial dimension of the first recessed section is smaller than the radial dimension of the second recessed section;

[0021] The outer peripheral wall of the diaphragm is connected to the inner peripheral wall of the first recessed section.

[0022] Secondly, embodiments of this application also provide an starter for a rocket propulsion system, including: a starting combustion chamber, a nozzle, and any of the diaphragm assemblies provided in the first aspect above;

[0023] One end of the nozzle is connected to the starting combustion chamber, and the nozzle nozzle at the other end faces away from the starting combustion chamber;

[0024] The diaphragm assembly extends at least partially along the axial direction and is sealed to the nozzle.

[0025] In some possible embodiments, the starter further includes: a sealing ring;

[0026] A sealing ring is placed around the first part of a portion of the diaphragm assembly and is sealed to the nozzle.

[0027] Thirdly, embodiments of this application also provide a rocket propulsion system, including: a turbopump and any of the starters provided in the second aspect above;

[0028] The turbopump is connected to the other end of the starter nozzle.

[0029] The beneficial technical effects of the technical solutions provided in this application include:

[0030] 1. In this embodiment, the diaphragm is indirectly mounted to the nozzle using a mounting base. Compared to the diaphragm, the mounting base has higher thickness and strength, higher reliability of connection with the nozzle, better sealing, and is easier to replace, which can improve the reusability and economy of the rocket propulsion system's starter.

[0031] 2. The diaphragm assembly provided in this application extends at least partially into the nozzle orifice, allowing for installation from the outside of the nozzle orifice inwards. Compared to related technologies where the diaphragm must first be installed inside the nozzle orifice before the nozzle is installed at one end of the starter's combustion chamber, the embodiments of this application do not restrict the installation sequence of the starter and the nozzle. After the starter is ignited, the mounting base can be removed from the nozzle of the starter, allowing the starter's combustion chamber and the nozzle to be reused.

[0032] 3. Unlike related technologies where the installation space inside the nozzle is limited and brazing is the only option to weld the diaphragm to the nozzle, in this embodiment, the diaphragm and the mounting base can be assembled and welded before installation at the nozzle orifice. The welding is less affected by the environment and can be performed using a more reliable welding method than brazing before installation at the nozzle. This improves the connection reliability between the diaphragm and the mounting base, enhances the operational reliability of the starter, and facilitates the normal launch of the launch vehicle.

[0033] Additional aspects and advantages of this application will be set forth in part in the description which follows, and will become apparent from the description or may be learned by practice of this application. Attached Figure Description

[0034] The above and / or additional aspects and advantages of this application will become apparent and readily understood from the following description of the embodiments taken in conjunction with the accompanying drawings, wherein:

[0035] Figure 1 A schematic diagram of the axial cross-section of a diaphragm assembly disposed at the nozzle of a starter, according to an embodiment of this application;

[0036] Figure 2 A side view of a diaphragm assembly provided in an embodiment of this application;

[0037] Figure 3 for Figure 2 Schematic diagram of the cross section at section AA;

[0038] Figure 4 This is a schematic diagram of the structure of a diaphragm in a diaphragm assembly provided in an embodiment of this application;

[0039] Figure 5 This is a schematic diagram of the structure of a mounting base for a diaphragm assembly provided in an embodiment of this application.

[0040] Figure label:

[0041] 10-Diaphragm assembly;

[0042] 11-Mounting base; 111-First part; 1110-Hollowed-out; 112-Second part; 1120-Recessed structure; 1121-First recessed section; 1122-Second recessed section;

[0043] 12-Phase; 121-Planar portion; 122-Edge portion; 123-Scribing mark;

[0044] 20 - Nozzle; 21 - Nozzle opening;

[0045] 30 - Sealing ring. Detailed Implementation

[0046] The embodiments of this application are described below with reference to the accompanying drawings. It should be understood that the embodiments described below with reference to the accompanying drawings are exemplary descriptions for explaining the technical solutions of the embodiments of this application, and do not constitute a limitation on the technical solutions of the embodiments of this application.

[0047] Those skilled in the art will understand that, unless specifically stated otherwise, the terms "described" and "the" as used herein may also include plural forms. It should be further understood that the term "comprising" as used in the specification of this application means the presence of the stated features, integers, elements, and / or components, but does not exclude implementations of other features, information, data, operations, elements, components, and / or combinations thereof supported by the art. The term "and / or" as used herein refers to at least one of the items defined by the term; for example, "A and / or B" can be implemented as "A," or as "B," or as "A and B."

[0048] To make the objectives, technical solutions, and advantages of this application clearer, the embodiments of this application will be described in further detail below with reference to the accompanying drawings.

[0049] First, let me introduce and explain the terms used in this application:

[0050] Starter: A device used to ignite the rocket's propulsion system. It provides initial power to the engine, and its outlet is connected to the engine's turbopump.

[0051] Diaphragm assembly: A separator located at the outlet of the starter. When subjected to an impact, it ruptures, allowing the energy generated by the starter to be transferred from the outlet to the turbopump, thereby starting the turbine.

[0052] Multiple starts are required for a rocket propulsion system. Each start uses at least one starter to generate energy, driving the turbopump to deliver propellant to the engine combustion chamber for combustion and thrust generation. Taking a secondary start as an example, each start uses a separate starter. The secondary starter must isolate itself from the high-temperature, high-pressure combustion gases generated after the first start to prevent accidental activation of the secondary starter due to continuous gas impact, which could lead to malfunctions in the rocket propulsion system.

[0053] In related technologies, the starter outlet is equipped with a nozzle, and the starter's diaphragm assembly is located at the nozzle orifice, isolating the starter's interior from the turbopump, and thus isolating the starter's interior from the engine combustion chamber. Furthermore, because the nozzle opening is larger at the end closer to the starter's combustion chamber and smaller at the end further away from the combustion chamber and closer to the turbopump, the diaphragm must first pass through the larger opening end and be installed inside the nozzle orifice before the nozzle is installed at the starter's combustion chamber end. Therefore, due to the limited space inside the nozzle, the diaphragm and nozzle are mostly fixed using brazing, which inherently results in poor connection strength and heat resistance.

[0054] Moreover, because the diaphragm is welded inside the nozzle, the nozzle fails after the starter is activated, making it difficult to reuse.

[0055] Moreover, the diaphragm is designed to be easily punctured and is very thin. This results in a weak connection between the diaphragm and the nozzle, making the diaphragm susceptible to rupture or even detachment from the nozzle due to the impact of the high-temperature and high-pressure gas generated from the engine combustion chamber during the previous start-up. This can lead to abnormal operation of the starter and cause the launch vehicle to fail to launch.

[0056] The diaphragm assembly, rocket propulsion system starter, and rocket propulsion system provided in this application are intended to solve the above-mentioned technical problems in related technologies.

[0057] The technical solution of this application and how it solves the above-mentioned technical problems are described in detail below with specific embodiments. It should be noted that the following embodiments can be referenced, borrowed, or combined with each other, and the same terms, similar features, and similar implementation steps in different embodiments will not be described again.

[0058] This application provides a diaphragm assembly 10, applied to the starter of a rocket propulsion system. Please refer to... Figures 1-3 The diaphragm assembly 10 includes a mounting base 11 and a diaphragm 12.

[0059] Mounting base 11 extends at least partially into and is sealed to the nozzle 21 of the starter along the axial direction; mounting base 11 includes a first part 111 and a second part 112 distributed along the axial direction; the first part 111 has a plurality of axially oriented cutouts 1110; the second part 112 has a recessed structure 1120 with an opening facing away from the first part 111.

[0060] The outer peripheral wall of the diaphragm 12 is connected to the inner peripheral wall of the recessed structure 1120.

[0061] The perforation 1110 connects the space inside the nozzle 20 and the diaphragm 12.

[0062] In this embodiment, the mounting base 11 is disposed at the nozzle 21, and the diaphragm 12 is disposed within a recessed structure 1120 on one side of the mounting base 11. The side of the mounting base 11 facing the nozzle 20 has a perforation 1110, allowing the high-pressure gas ejected from the nozzle 20 to pass through the perforation 1110 and break through the diaphragm 12, thereby being conducted to the turbopump and starting the turbopump. In this embodiment, the mounting base 11 is used to indirectly mount the diaphragm 12 to the nozzle 21. Compared to the diaphragm 12, the mounting base 11 has higher thickness and strength, higher reliability of connection with the nozzle 21, better sealing, and is easier to replace, thereby improving the reusability and economy of the rocket propulsion system's starter.

[0063] Furthermore, the diaphragm assembly 10 provided in this application is at least partially inserted into the nozzle 21, allowing it to be installed from the outside of the nozzle 21 inwards. Compared to the related technology where the diaphragm 12 needs to be installed inside the nozzle 21 first, and then the nozzle 20 is installed at one end of the starter's combustion chamber, the embodiment of this application does not restrict the installation order of the starter and the nozzle 20. After the starter is ignited, the mounting base 11 can be removed from the nozzle 20 of the starter, making the starter's combustion chamber and the nozzle 20 reusable.

[0064] Furthermore, unlike related technologies where the installation space within the nozzle 20 is limited and brazing is the only option to weld the diaphragm 12 to the nozzle 20, the diaphragm 12 and the mounting base 11 can be assembled and welded before installation at the nozzle orifice 21. This welding method is less affected by the environment and allows for a more reliable welding method than brazing before installation at the nozzle 20. This improves the connection reliability between the diaphragm 12 and the mounting base 11, enhances the starter's operational reliability, and facilitates the normal launch of the launch vehicle.

[0065] It should be noted that, in the embodiments of this application, the inward end (side) refers to the end (side) facing the inside of the nozzle 20, and the outward end (side) refers to the end (side) facing the outside of the nozzle 20 and facing the turbopump.

[0066] In some possible embodiments, the outer peripheral wall of the diaphragm 12 and the inner peripheral wall of the recessed structure 1120 are welded by vacuum electron beam welding, which can increase the weld strength and improve the heat resistance and precision of the weld.

[0067] In some possible embodiments, such as Figure 3 As shown, one side of the diaphragm 12 contacts or abuts against the first part 111, sealing the perforation 1110.

[0068] In this embodiment, the diaphragm 12 contacts or abuts against the first part 111 to minimize the possibility of gaps between the diaphragm 12 and the first part 111. When subjected to an impact from the turbopump (i.e., an impact force from outside the nozzle 20), the side of the diaphragm 12 facing into the nozzle 20 can be supported by the first part 111 to minimize the deformation of the diaphragm 12 and thus reduce the possibility of the diaphragm 12 breaking due to the impact from the turbopump.

[0069] In some possible embodiments, please refer to Figure 5 At least part of the outer diameter of the second part 112 is larger than the outer diameter of the first part 111.

[0070] In this embodiment, at least part of the outer diameter of the second part 112 is larger than the outer diameter of the first part 111, so that a first stepped surface is formed between the outer periphery of the first part 111 and the second part 112 on the mounting base 11, and the inner wall of the nozzle 21 also has a second stepped surface. When the mounting base 11 is inserted into the nozzle 21, the first stepped surface on the outer periphery of the mounting base 11 abuts against the second stepped surface inside the nozzle 21, which can effectively prevent the mounting base 11 from sliding into the nozzle 20.

[0071] Furthermore, when the starter nozzle 20 is mounted on the turbopump, the turbopump can abut against the mounting base 11. Therefore, the inward side of the mounting base 11 is abutted by the second stepped surface of the nozzle 20, and the outward side of the mounting base 11 is abutted by the turbopump, so that the mounting base 11 can be fixed at the nozzle orifice 21 without the need for welding or other fixing methods between the mounting base 11 and the nozzle 20, which can reduce the installation difficulty and cost of the diaphragm assembly 10 and improve the installation efficiency.

[0072] In some possible implementations, the nozzle 20 also has a third stepped surface, which is further away from the nozzle opening 21 than the second stepped surface. The third stepped surface can abut against the inward side of the first part 111, further ensuring that the mounting base 11 is fixed at the nozzle opening 21, and preventing the mounting base 11 from being blown away from the nozzle opening 21 by the impact from the turbopump, which could lead to accidents such as starter failure.

[0073] In some possible embodiments, please refer to Figure 3Along the radial direction, the outermost hollow 1110, the peripheral wall of the recessed structure 1120 and the outer peripheral wall of the first part 111 are successively moved away from the axial direction.

[0074] In this embodiment, the cutout 1110 is only opened in the middle area of ​​the first part 111 to ensure that the peripheral area of ​​the first part 111 has sufficient strength to support the diaphragm 12 and to ensure effective contact between the first step of the mounting base 11 and the nozzle 21, so as to prevent the mounting base 11 from being blown away from the nozzle 21 by the impact from the turbo pump, which could lead to starter failure and other accidents.

[0075] In some possible embodiments, please refer to Figure 3 and Figure 4 The diaphragm 12 includes a planar portion 121 and an edge portion 122 connected to the outer periphery of the planar portion 121.

[0076] The edge portion 122 and the planar portion 121 are flush with the side facing the first portion 111. The edge portion 122 extends along the axial direction away from the first portion 111 and gradually thickens along the radial direction away from the planar portion 121.

[0077] In this embodiment, the inward-facing side of the diaphragm 12 is flat, while the outward-facing edge portion 122 protrudes axially and is concave. Therefore, compared to the flat portion 121, the edge portion 122 is thicker. When the edge portion 122 is connected to the inner peripheral wall of the recessed structure 1120 of the mounting base 11, the edge portion 122 can better disperse stress and reduce stress concentration, thereby reducing the risk of the diaphragm 12 breaking or separating from the mounting base 11, and thus ensuring the normal operation of the starter.

[0078] In some embodiments, the connection between the inward side of the edge portion 122 of the diaphragm 12 and the outer peripheral wall is smoothly transitioned, which is equivalent to the diaphragm 12 itself being designed with equal strength, thereby improving the connection strength between it and the inner peripheral wall of the recessed structure 1120, and reducing the possibility of accidents caused by single-point failure at the connection.

[0079] In some possible embodiments, such as Figure 1 and Figure 3 As shown, the first part 111 is recessed on one side facing the nozzle 20, and the center of the first part is the deepest recess.

[0080] In this embodiment, the inward side of the first part 111 is recessed to form a bowl shape. The center of the first part corresponds to the center of the bowl-shaped structure, and the recess is the deepest. It can serve as an energy concentration area, which facilitates the concentrated transmission of energy from the starting combustion chamber to the center of the diaphragm 12, ensuring that the diaphragm 12 ruptures normally from the center, thereby allowing energy to be ejected through the nozzle 21.

[0081] In some possible embodiments, such as Figure 2 and Figure 3 As shown, the diaphragm 12 has multiple strip-shaped grooves 123 on the side away from the first part 111.

[0082] The midpoints of multiple notches 123 intersect and are located at the center of the diaphragm 12.

[0083] The center of the first part 111 coincides with the midpoint of the intersection of multiple engravings 123 along the axial direction.

[0084] In this embodiment, the center of the diaphragm 12 coincides with the center of the first part 111 along the axial direction, and the center of the groove 123 coincides with the center of the recess in the first part 111 along the axial direction. When the first part 111 concentrates the energy from the starting combustion chamber to the center of the diaphragm 12, it is beneficial for the energy to act directly on the center where multiple grooves 123 intersect, making it easier for the grooves 123 of the diaphragm 12 to break from the center outwards, thereby improving the working reliability of the starter.

[0085] Optionally, such as Figure 2 As shown, the notch 123 is in the shape of a " The diaphragm 12 is engraved on the side away from the first part 111. The side of the diaphragm 12 closest to the first part 111 has no engravings, so that the side of the diaphragm 12 without engravings can directly adhere to the first part 111 when subjected to high-pressure gas generated from the engine combustion chamber, and is not easily broken under the support of the first part 111.

[0086] In some possible embodiments, such as Figure 3 and Figure 5 As shown, the recessed structure 1120 includes a first recessed segment 1121 and a second recessed segment 1122 distributed along an axial direction away from the first part 111.

[0087] The radial dimension of the first recessed section 1121 is smaller than the radial dimension of the second recessed section 1122.

[0088] The outer peripheral wall of the diaphragm 12 is connected to the inner peripheral wall of the first recessed section 1121.

[0089] In this embodiment, the diaphragm 12 is disposed in the first recessed section 1121 closer to the first part 111, and the second recessed section 1122 is larger in size, which facilitates welding the diaphragm 12 into the first recessed section 1121 through the second recessed section 1122. Moreover, the second recessed section 1122 can also be adapted to the connector size of the turbopump and the starter, so that the connector of the turbopump blocks the second recessed section 1122 and abuts against the second recessed section 1122, without being squeezed into the first recessed section 1121, ensuring that the diaphragm 12 located in the first recessed section 1121 is not damaged by the connector, thereby improving the reliability of the diaphragm assembly 10.

[0090] Based on the same inventive concept, this application also provides a starter for a rocket propulsion system, including: a starting combustion chamber, a nozzle 20, and any of the diaphragm assemblies 10 provided in the foregoing embodiments.

[0091] One end of the nozzle 20 is connected to the starting combustion chamber, and the nozzle orifice 21 at the other end faces away from the starting combustion chamber.

[0092] The diaphragm assembly 10 extends at least partially into and is sealed to the nozzle 21 along the axial direction.

[0093] In this embodiment, since the starter of the rocket propulsion system adopts any of the diaphragm components 10 provided in the foregoing embodiments, the principle and technical effects are described in the foregoing embodiments and will not be repeated here.

[0094] In this embodiment, the mounting base 11 is disposed at the nozzle 21, and the diaphragm 12 is disposed within a recessed structure 1120 on one side of the mounting base 11. The side of the mounting base 11 facing the nozzle 20 has a perforation 1110, allowing the high-pressure gas ejected from the nozzle 20 to pass through the perforation 1110 and break through the diaphragm 12, thereby being conducted to the turbopump and starting the turbopump. The diaphragm assembly 10 provided in this application is at least partially inserted into the nozzle 21 and can be installed from the outside of the nozzle 21 inwards. Compared to the related technology where the diaphragm 12 needs to be installed in the nozzle 21 first, and then the nozzle 20 is installed at one end of the starter's combustion chamber, this embodiment does not restrict the installation order of the starter and the nozzle 20. After the starter is ignited, the mounting base 11 can be removed from the nozzle 20 of the starter, making the starter's combustion chamber and the nozzle 20 reusable.

[0095] Furthermore, unlike related technologies where the installation space within the nozzle 20 is limited and brazing is the only option to weld the diaphragm 12 to the nozzle 20, the diaphragm 12 and the mounting base 11 can be assembled and welded before installation at the nozzle orifice 21. This welding method is less affected by the environment and allows for a more reliable welding method than brazing before installation at the nozzle 20. This improves the connection reliability between the diaphragm 12 and the mounting base 11, enhances the starter's operational reliability, and facilitates the normal launch of the launch vehicle.

[0096] In some possible embodiments, the starter also includes a sealing ring 30.

[0097] The sealing ring 30 is disposed around the first part 111 of the partial diaphragm assembly 10 and is sealed to the nozzle 21.

[0098] In this embodiment, the sealing ring 30 is disposed around the first part 111 of the partial diaphragm assembly 10 and is axially pressed between the second part 112 and the nozzle 20, so that the space inside and outside the nozzle 20 is effectively isolated by the diaphragm assembly 10, thereby ensuring the normal operation of the starter.

[0099] Based on the same inventive concept, this application also provides a rocket propulsion system, including: a turbopump and any of the starters provided in the foregoing embodiments.

[0100] The turbopump is connected to the other end of the nozzle 20 of the starter.

[0101] In this embodiment, since the rocket propulsion system uses any of the starters provided in the foregoing embodiments, the principle and technical effects are described in the foregoing embodiments and will not be repeated here.

[0102] In this embodiment, the mounting base 11 is disposed at the nozzle 21, and the diaphragm 12 is disposed in the recessed structure 1120 on one side of the mounting base 11. The side of the mounting base 11 facing the nozzle 20 has a perforation 1110, so that the high-pressure gas ejected from the nozzle 20 can break through the diaphragm 12 through the perforation 1110 and then be conducted to the turbo pump, thereby starting the turbo pump.

[0103] The diaphragm assembly 10 can effectively isolate the turbopump from the starting combustion chamber, which is equivalent to effectively isolating the starting combustion chamber from the engine combustion chamber. This ensures that the diaphragm assembly 10 remains in normal condition after the previous start and before the current start, preventing the starter from being ruptured by the impact of the high-temperature and high-pressure gas generated during the previous start, and improving the reliability of the starter.

[0104] Optionally, the rocket propulsion system includes a rocket engine.

[0105] By applying the embodiments of this application, at least the following beneficial effects can be achieved:

[0106] 1. In this embodiment, the mounting base 11 is disposed at the nozzle 21, and the diaphragm 12 is disposed within a recessed structure 1120 on one side of the mounting base 11. The side of the mounting base 11 facing the nozzle 20 has a perforation 1110, allowing the high-pressure gas ejected from the nozzle 20 to pass through the perforation 1110 and break through the diaphragm 12, thereby being conducted to the turbopump and starting the turbopump. In this embodiment, the mounting base 11 is used to indirectly mount the diaphragm 12 to the nozzle 21. Compared to the diaphragm 12, the mounting base 11 has higher thickness and strength, higher reliability of connection with the nozzle 21, better sealing, and is easier to replace, thereby improving the reusability and economy of the rocket propulsion system's starter.

[0107] 2. The diaphragm assembly 10 provided in this application extends at least partially into the nozzle 21, allowing it to be installed from the outside of the nozzle 21 inwards. Compared to the related technology where the diaphragm 12 needs to be installed inside the nozzle 21 first, and then the nozzle 20 is installed at one end of the starter's combustion chamber, the embodiment of this application does not restrict the installation order of the starter and the nozzle 20. After the starter is ignited, the mounting base 11 can be removed from the nozzle 20 of the starter, making the starter's combustion chamber and the nozzle 20 reusable.

[0108] 3. Unlike related technologies where the installation space within the nozzle 20 is limited and brazing is the only option to weld the diaphragm 12 to the nozzle 20, the diaphragm 12 and the mounting base 11 can be assembled and welded before installation at the nozzle orifice 21. The welding is less affected by the environment and can be performed using a more reliable welding method than brazing before installation at the nozzle 20. This improves the connection reliability between the diaphragm 12 and the mounting base 11, enhances the operational reliability of the starter, and facilitates the normal launch of the launch vehicle.

[0109] 4. In this embodiment, the diaphragm 12 contacts or abuts against the first part 111 to minimize the possibility of gaps between the diaphragm 12 and the first part 111. When subjected to an impact from the turbopump (i.e., an impact force from outside the nozzle 20), the side of the diaphragm 12 facing the inside of the nozzle 20 can be supported by the first part 111 to minimize the deformation of the diaphragm 12 and thus reduce the possibility of the diaphragm 12 breaking due to the impact from the turbopump.

[0110] 5. In this embodiment of the application, at least part of the outer diameter of the second part 112 is larger than the outer diameter of the first part 111, so that a first stepped surface is formed between the outer periphery of the first part 111 and the second part 112 on the mounting seat 11, and the inner wall of the nozzle 21 also has a second stepped surface. When the mounting seat 11 is inserted into the nozzle 21, the first stepped surface on the outer periphery of the mounting seat 11 abuts against the second stepped surface inside the nozzle 21, which can effectively prevent the mounting seat 11 from sliding into the nozzle 20.

[0111] In the description of this application, the terms "center," "upper," "lower," "front," "rear," "left," "right," "vertical," "horizontal," "top," "bottom," "inner," and "outer," etc., indicate directions or positional relationships based on the exemplary directions or positional relationships shown in the accompanying drawings. They are used to facilitate the description or simplification of the embodiments of this application and are not intended to indicate or imply that the device or component 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 this application.

[0112] The terms "first" and "second" are used for descriptive purposes only and should not be construed as indicating or implying relative importance or implicitly specifying the number of technical features indicated. Therefore, a feature defined as "first" or "second" may explicitly or implicitly include one or more of that feature. In the description of this application, unless otherwise stated, "a plurality of" means two or more.

[0113] In the description of this specification, specific features, structures, materials, or characteristics may be combined in any suitable manner in one or more embodiments or examples.

[0114] The above description is only a partial embodiment of this application. It should be noted that for those skilled in the art, other similar implementation methods based on the technical concept of this application, without departing from the technical concept of this application, also fall within the protection scope of the embodiments of this application.

Claims

1. A diaphragm assembly, characterized in that, Starters used in rocket propulsion systems include: A mounting base, at least partially inserted axially and sealed to the nozzle of the starter; the mounting base includes a first part and a second part distributed axially; the first part has multiple axially oriented cutouts; the second part has a recessed structure with an opening facing away from the first part; the recessed structure includes a first recessed segment and a second recessed segment distributed axially away from the first part; the radial dimension of the first recessed segment is smaller than the radial dimension of the second recessed segment; the outer peripheral wall of the diaphragm is connected to the inner peripheral wall of the first recessed segment; the connector of the turbopump plugs the second recessed segment and abuts against the second recessed segment; at least a portion of the outer diameter of the second part is larger than the outer diameter of the first part; the mounting base forms a first stepped surface between the outer peripheries of the first and second parts; the inner wall at the nozzle has a second stepped surface. The outer peripheral wall of the diaphragm is connected to the inner peripheral wall of the recessed structure; The perforation connects the space inside the nozzle and the diaphragm.

2. The diaphragm assembly according to claim 1, characterized in that, One side of the diaphragm contacts or abuts against the first part, sealing the perforation.

3. The diaphragm assembly according to claim 1, characterized in that, Along the radial direction, the outermost hollowed-out structure, the peripheral wall of the recessed structure, and the outer peripheral wall of the first part are successively moved away from the axial direction.

4. The diaphragm assembly according to claim 1, characterized in that, The diaphragm includes a planar portion and an edge portion connected to the outer periphery of the planar portion; The edge portion and the planar portion are flush with the side facing the first portion, the edge portion extends axially away from the first portion, and gradually thickens radially away from the planar portion.

5. The diaphragm assembly according to claim 1, characterized in that, The first part is recessed on one side facing the nozzle, with the deepest recess at the center of the first part.

6. The diaphragm assembly according to claim 5, characterized in that, The diaphragm has multiple strip-shaped grooves on the side away from the first part; The midpoints of the plurality of the grooves intersect and are located at the center of the membrane; The center of the first part coincides axially with the midpoint of the intersection of the plurality of said grooves.

7. A starter for a rocket propulsion system, characterized in that, include: The combustion chamber, the nozzle, and the diaphragm assembly as described in any one of claims 1-6 are started; One end of the nozzle is connected to the starting combustion chamber, and the nozzle orifice at the other end faces away from the starting combustion chamber. The diaphragm assembly extends at least partially along the axial direction and is sealed to the nozzle.

8. The starter according to claim 7, characterized in that, Also includes: Sealing ring; The sealing ring is disposed around the first part of a portion of the diaphragm assembly and is sealed to the nozzle.

9. A rocket propulsion system, characterized in that, include: A turbopump and a starter as described in any of claims 7-8 above; The turbopump is connected to the other end of the nozzle of the starter.

Images