High temperature dynamic seal structure and scramjet engine

Abstract

The application discloses a high-temperature dynamic sealing structure and a scramjet engine, and relates to the technical field of engines.The high-temperature dynamic sealing structure comprises a mounting base, a sealing assembly, an elastic adjusting assembly and a gas passage, the gas passage is communicated with a combustion chamber of the scramjet engine, a first accommodating cavity and a second accommodating cavity are formed in the mounting base, the sealing assembly is installed in the first accommodating cavity, the elastic adjusting assembly is installed in the second accommodating cavity, the second accommodating cavity is also communicated with the gas passage, and the abutting force of the sealing assembly on the side wall of the combustion chamber can be adjusted based on the pressure of the gas in the combustion chamber and / or the elastic force of the elastic adjusting assembly.The high-temperature dynamic sealing structure can dynamically adjust the abutting force of the sealing assembly on the side wall of the combustion chamber through the gas in the second accommodating cavity and the elastic adjusting assembly, so that the sealing assembly and the side wall of the combustion chamber can always maintain good sealing performance.

Description

Technical Field

[0001] This invention relates to the field of engine technology, and in particular to a high-temperature dynamic sealing structure and a scramjet engine. Background Technology

[0002] The scramjet engine is a new type of aero-engine primarily used in jet aircraft. It consists of three main parts: a combustor, a turbine, and a compressor. The compressor draws in a large volume of air using rotating blades and compresses it into high-pressure gas. This compressed air enters the combustor, mixes with fuel, and burns to form high-temperature, high-pressure combustion gas. This high-temperature, high-pressure combustion gas drives the turbine, which is connected to the compressor. The turbine's rotation powers the compressor. The high-speed, high-temperature gas exiting the turbine is expelled through nozzles, generating a reaction force that propels the jet aircraft forward. Scramjet engines offer high thrust and fuel efficiency, enabling higher flight speeds and longer ranges, making them suitable for the needs of future high-speed aircraft.

[0003] In related technologies, a sealing structure is installed between the combustion chamber and its sidewall to prevent the high-temperature, high-pressure combustion gases inside the combustion chamber from leaking into the upper space. Specifically, pre-tightening bolts are used in related technologies to fix the sealing device between the combustion chamber and its sidewall. However, the inventors have discovered that during the operation of a scramjet engine, the pressure inside the combustion chamber varies depending on the operating power. When the pressure inside the combustion chamber increases, the sealing performance of the combustion chamber is affected, and the sealing structure in related technologies cannot ensure that the combustion chamber maintains a good seal at all times.

[0004] Therefore, providing a sealing structure that allows the combustion chamber to maintain good sealing performance even when the pressure inside the combustion chamber increases is a technical problem that urgently needs to be solved by those skilled in the art. Summary of the Invention

[0005] This invention discloses a high-temperature dynamic sealing structure and a scramjet engine to solve the technical problem that sealing structures in related technologies cannot maintain good sealing performance of the combustion chamber at all times.

[0006] To solve the above problems, the present invention adopts the following technical solution:

[0007] The first aspect of the present invention provides a high-temperature dynamic sealing structure.

[0008] The high-temperature dynamic sealing structure of the present invention includes a mounting base, a sealing component, an elastic adjustment component, and a gas passage. The gas passage is connected to the combustion chamber of a scramjet engine. The mounting base has a first receiving chamber and a second receiving chamber. The sealing component is installed in the first receiving chamber, and the elastic adjustment component is installed in the second receiving chamber. The second receiving chamber is also connected to the gas passage, and the sealing component's contact force against the side wall of the combustion chamber can be adjusted based on the pressure of the gas in the combustion chamber and / or the elastic force of the elastic adjustment component.

[0009] Furthermore, the high-temperature dynamic sealing structure also includes a pushing part, which is movably installed in the second receiving chamber. The pushing part applies a pushing force to the sealing assembly based on the pressure of the gas in the second receiving chamber and / or the elastic force of the elastic adjustment component.

[0010] Furthermore, a sealing groove is provided in the circumferential direction of the pushing part, the sealing groove is used to install a sealing ring, and the sealing ring is used to keep the pushing part and the mounting base in a sealed connection.

[0011] Furthermore, the elastic adjustment assembly includes an elastic element and a fastener, wherein the elastic element is installed between the pusher and the fastener, and the fastener is used to apply a preload to the elastic element and keep the elastic element in a compressed state. A gas channel is formed in the fastener along its axial direction, and the gas channel communicates with the gas passage and the second receiving chamber.

[0012] Furthermore, the sealing assembly includes a sealing element and a force-bearing plate. The sealing element contacts the side wall of the combustion chamber, the force-bearing plate is fitted to the sealing element, and the force-bearing plate is located between the sealing element and the pushing part.

[0013] Furthermore, the seal is formed by stacking at least two sealing sheets, with a metal mesh between adjacent sealing sheets, and the sealing sheets are made of ceramic material.

[0014] Furthermore, the side of the sealing sheet that contacts another sealing sheet is provided with a plurality of sealing teeth, and a groove is formed between two adjacent sealing teeth, the groove being used to fill asbestos strips.

[0015] Furthermore, the first cross-sectional area of ​​the sealing sheet on the side closest to the sidewall is smaller than the second cross-sectional area of ​​the sealing sheet on the side closest to the force-bearing plate.

[0016] Furthermore, the stress plate is made of nickel-based high-temperature alloy material, and the thickness of the stress plate is 1-2 mm.

[0017] A second aspect of the present invention provides a scramjet engine.

[0018] The scramjet engine of the present invention includes the high-temperature dynamic sealing structure described in any of the technical solutions of the present invention.

[0019] The technical solution adopted in this invention can achieve the following beneficial effects:

[0020] The high-temperature dynamic sealing structure of the present invention includes a mounting base, a sealing component, an elastic adjustment component, and a gas passage. The gas passage is connected to the combustion chamber of a scramjet engine. A first receiving chamber and a second receiving chamber are formed within the mounting base. The sealing component is installed in the first receiving chamber, and the elastic adjustment component is installed in the second receiving chamber. The second receiving chamber is also connected to the gas passage. The sealing component's contact force against the side wall of the combustion chamber can be adjusted based on the pressure of the gas in the combustion chamber and / or the elastic force of the elastic adjustment component. This sealing structure allows high-temperature, high-pressure gas in the combustion chamber to enter the second receiving chamber through the gas passage. When the pressure in the combustion chamber increases, the gas pressure in the second receiving chamber also increases, thereby increasing the pressure of the gas in the second receiving chamber on the sealing component. Simultaneously, the increased gas pressure in the second receiving chamber also increases the pressure of the elastic adjustment component on the sealing component, thereby increasing the contact force of the sealing component against the side wall of the combustion chamber, ensuring a good seal between the sealing component and the side wall of the combustion chamber.

[0021] The high-temperature dynamic sealing structure of the present invention can dynamically adjust the contact force between the sealing component and the combustion chamber sidewall by the gas in the second receiving chamber and the elastic force of the elastic adjustment component, thus solving the technical problem in related technologies where the sealing structure cannot maintain good sealing performance of the combustion chamber at all times. Attached Figure Description

[0022] To more clearly illustrate the technical solutions in the embodiments of the present invention or the prior art, the drawings used in the description of the embodiments or the prior art will be briefly introduced below. Obviously, the drawings described below are only some embodiments of the present invention. For those skilled in the art, other drawings can be obtained based on these drawings without creative effort.

[0023] Figure 1 This is a first schematic diagram of the high-temperature dynamic sealing structure according to an embodiment of this application;

[0024] Figure 2 This is a second schematic diagram of the high-temperature dynamic sealing structure according to an embodiment of this application;

[0025] Figure 3 yes Figure 2 AA section view;

[0026] Figure 4 This is an assembly diagram of the elastic adjustment component and the pushing part according to an embodiment of this application;

[0027] Figure 5 This is a schematic diagram of the structure of the mounting base according to an embodiment of this application;

[0028] Figure 6 This is a schematic diagram of the structure of the sealing element according to an embodiment of this application;

[0029] Figure 7 This is a schematic diagram of the structure of the sealing sheet according to an embodiment of this application;

[0030] Figure 8 This is a cross-sectional view of the sealing sheet according to an embodiment of this application;

[0031] Figure 9 This is a schematic diagram of the external structure of the combustion chamber according to an embodiment of this application;

[0032] Figure 10 This is a schematic diagram of the internal structure of the combustion chamber in an embodiment of this application.

[0033] In the figure: 110, mounting base; 111, first receiving chamber; 112, second receiving chamber; 120, sealing assembly; 121, sealing element; 1211, sealing plate; 1211a, sealing tooth; 1211b, tooth groove; 122, force plate; 130, elastic adjustment assembly; 131, elastic element; 132, fastener; 1321, gas passage; 140, gas combustion passage; 141, air inlet; 150, pushing part; 151, sealing groove; 200, combustion chamber; 210, side wall; 220, hinge assembly; 230, combustion space; 240, upper space. Detailed Implementation

[0034] To make the objectives, technical solutions, and advantages of this invention clearer, the technical solutions of this invention will be described in detail below. Obviously, the described embodiments are merely some embodiments of this invention, and not all embodiments. Based on the embodiments of this invention, all other implementation methods obtained by those skilled in the art without creative effort are within the scope of protection of this invention.

[0035] The terms "first," "second," etc., used in the specification and claims of this application are used to distinguish similar objects and not to describe a specific order or sequence. It should be understood that such use of data can be interchanged where appropriate so that embodiments of this application can be implemented in orders other than those illustrated or described herein, and the objects distinguished by "first," "second," etc., are generally of the same class and the number of objects is not limited; for example, a first object can be one or more. Furthermore, in the specification and claims, "and / or" indicates at least one of the connected objects, and the character " / " generally indicates that the preceding and following objects are in an "or" relationship.

[0036] The inventors discovered in their research that in related technologies, pre-tightening bolts are used to fix the sealing device between the combustion chamber and its side wall to prevent the high-temperature and high-pressure gas in the combustion chamber from leaking into the external space. However, during the use of a scramjet engine, the pressure inside the combustion chamber varies depending on the power used. When the pressure generated inside the combustion chamber increases, the sealing between the combustion chamber and the burner side wall is insufficient, posing a potential risk of leakage of high-temperature and high-pressure gas inside the combustion chamber.

[0037] Specifically, the inventors discovered that when the pressure inside the combustion chamber increases, the sealing performance between the combustion chamber and its sidewalls may be affected for the following reasons: Firstly, as the internal pressure of the combustion chamber increases, the pressure difference between the combustion chamber and the upper space also increases, resulting in greater force being applied to the sealing structure of the combustion chamber. Existing sealing devices do not have sufficient strength or suitable design to cope with the higher pressure difference, increasing the risk of combustion chamber gas leakage. Secondly, under high pressure, the materials used in the sealing structure may be subjected to pressure compression and deformation. Existing sealing devices cannot resist this compression and deformation, which may lead to the rupture or distortion of the sealing material, thereby reducing the sealing performance. Thirdly, as the internal pressure of the combustion chamber increases, the pressure on the contact surface of the sealing structure also increases, which applies greater stress to the material and connection points of the sealing structure, which may cause the sealing contact surface to loosen, deform, or rupture, thus affecting the sealing performance.

[0038] To address this, this application provides a high-temperature dynamic sealing structure that can dynamically adjust the contact force between the sealing structure and the side wall of the combustion chamber based on the pressure inside the combustion chamber, thereby ensuring good sealing performance even when the pressure inside the combustion chamber increases.

[0039] The high-temperature dynamic sealing structure in this embodiment refers to a structure that achieves dynamic sealing by utilizing the high-temperature gas in the combustion chamber at 2000-2600°C. In other words, it is a structure that dynamically adjusts the sealing performance of the combustion chamber by utilizing the high-temperature gas in the combustion chamber at 2000-2600°C.

[0040] The following is in conjunction with the appendix Figures 1 to 10 The high-temperature dynamic sealing structure and scramjet engine provided in this application are described in detail through specific embodiments and application scenarios.

[0041] The first aspect of this embodiment provides a high-temperature dynamic sealing structure.

[0042] The high-temperature dynamic sealing structure in this embodiment is used to seal the combustion chamber of a scramjet engine. Figure 9 and Figure 10 Schematic diagrams of the external and internal structures of the scramjet engine combustion chamber are shown respectively. Figure 9 and Figure 10 As shown, the combustion chamber 200 of the scramjet engine is a cavity structure enclosed by multiple plates. Preferably, the combustion chamber 200 of this application is a variable combustion chamber. A hinge assembly 220 is provided inside the combustion chamber 200, which divides the internal space of the combustion chamber 200 into a combustion space 230 and an upper space 240. The hinge assembly 220 can move up and down to adjust the size of the combustion space 230. In this embodiment, a high-temperature dynamic sealing structure is located between the hinge assembly 220 and the side wall 210 of the combustion chamber 200 to keep the combustion space 230 sealed.

[0043] The high-temperature dynamic sealing structure of this embodiment includes a mounting base 110, a sealing assembly 120, an elastic adjustment assembly 130, and a gas passage 140, as shown below. Figures 1-4 As shown. Mounting base 110 provides a mounting base for sealing assembly 120, flexible adjustment assembly 130, and gas passage 140. Sealing assembly 120 provides a sealing function. Flexible adjustment assembly 130 dynamically adjusts the contact force between sealing assembly 120 and the side wall 210 of combustion chamber 200. Gas passage 140 allows gas to pass through.

[0044] Furthermore, the gas passage 140 is connected to the combustion chamber 200 of the scramjet engine, allowing the high-temperature, high-pressure gas in the combustion chamber 200 to enter the gas passage 140. Specifically, the air inlet 141 of the gas passage 140 is connected to the combustion space 230. A first receiving chamber 111 and a second receiving chamber 112 are formed within the mounting base 110. A sealing assembly 120 is installed in the first receiving chamber 111, and an elastic adjustment assembly 130 is installed in the second receiving chamber 112. The second receiving chamber 112 is also connected to the gas passage 140, allowing the contact force of the sealing assembly 120 against the side wall 210 of the combustion chamber 200 to be adjusted based on the pressure of the gas in the combustion chamber 200 and / or the elastic force of the elastic adjustment assembly 130. Figure 3 and Figure 5 As shown. It can be seen that, for the sake of the stability of the gas passage 140 installation, the gas passage 140 may also be located in the receiving cavity within the mounting base 110.

[0045] Preferably, the gas passage 140 can be a microchannel heat exchanger. High-temperature gas at 2000–2600°C is generated in the combustion chamber 200. To prevent damage to the sealing structure from such high temperatures, the gas can be cooled as it passes through the gas passage 140. More preferably, the gas passage 140 has a curved structure, increasing the path length of the high-temperature gas and thus enhancing the heat exchange effect of the gas passage 140 on the high-temperature gas, ensuring the service life of the sealing structure. Specifically, after passing through the gas passage 140, the high-temperature gas can be reduced to 100–120°C, thereby ensuring the service life of the sealing structure.

[0046] The high-temperature dynamic sealing structure in the above technical solution allows high-temperature, high-pressure gas in the combustion chamber 200 to enter the second receiving chamber 112 through the gas passage 140. When the pressure in the combustion chamber 200 increases, the gas pressure in the second receiving chamber 112 also increases, thereby increasing the pressure of the gas in the second receiving chamber 112 on the sealing assembly 120. Simultaneously, the increased gas pressure in the second receiving chamber 112 increases the compression degree of the elastic adjustment assembly 130, thus increasing the pressure of the elastic adjustment assembly 130 on the sealing assembly 120. This increases the contact force between the sealing assembly 120 and the side wall of the combustion chamber 200, ensuring a consistently good seal between the sealing assembly 120 and the side wall of the combustion chamber 200. In other words, the high-temperature dynamic sealing structure of this embodiment dynamically adjusts the contact force of the sealing assembly 120 on the side wall of the combustion chamber 200 through the gas in the second receiving chamber 112 and the elastic adjustment assembly 130, solving the technical problem in related technologies where sealing structures cannot maintain a consistently good seal when the pressure in the combustion chamber 200 increases.

[0047] According to a preferred embodiment, the high-temperature dynamic sealing structure further includes a pushing part 150, such as... Figure 3 and Figure 4 As shown. The pushing part 150 is movably installed in the second receiving chamber 112. The pushing part 150 applies a pushing force to the sealing assembly 120 based on the pressure of the gas in the second receiving chamber 112 and / or the elastic force of the elastic adjustment component 130. The pushing part 150 can be a piston rod. The movable installation of the pushing part 150 in the second receiving chamber 112 allows the pushing part 150 to slide within the second receiving chamber 112 based on the magnitude of the gas pressure, thereby dynamically adjusting the contact force of the sealing assembly 120 against the side wall of the combustion chamber 200. The high-temperature dynamic sealing structure of the preferred embodiment applies a pushing force to the sealing assembly 120 through the pushing part 150. Compared with the method of directly applying a pushing force to the sealing assembly 120 through the elastic adjustment component 130, the contact area between the pushing part 150 and the sealing assembly 120 is larger, resulting in more uniform force on the sealing assembly 120 and reducing the likelihood of deformation due to excessive local force.

[0048] According to a preferred embodiment, a sealing groove 151 is provided in the circumferential direction of the pushing part 150. The sealing groove 151 is used to install a sealing ring, and the sealing ring is used to maintain a sealed connection between the pushing part 150 and the mounting base 110. Figure 4 As shown. Preferably, the sealing ring is made of stainless steel. The high-temperature dynamic sealing structure of the preferred technical solution in this embodiment can keep the pushing part 150 and the mounting base 110 sealed together by the sealing ring, so as to avoid gas leakage in the second receiving chamber 112, which would reduce the pressure in the second receiving chamber 112 and fail to enhance the sealing assembly 120's contact force with the side wall of the combustion chamber 200.

[0049] According to a preferred embodiment, the elastic adjustment assembly 130 includes an elastic element 131 and a fastener 132, such as Figure 3 and Figure 4 As shown. The elastic element 131 is, for example, a spring. The fastener 132 is, for example, an adjusting bolt. The adjusting bolt is threadedly connected to the mounting base 110. The elastic element 131 is mounted between the pushing part 150 and the fastener 132. Grooves are provided on both opposite end faces of the pushing part 150 and the fastener 132, and these grooves are used to limit the two ends of the elastic element 131. The fastener 132 is also used to apply a preload to the elastic element 131 and keep the elastic element 131 in a compressed state, such as... Figure 3 and Figure 4 As shown. Preferably, the elastic element 131 initially maintains a preload of 20%, so that even when the combustion chamber 200 is under low pressure, the elastic force of the elastic element 131 can still be used to maintain sufficient contact force between the sealing assembly 120 and the side wall 210 of the combustion chamber 200, thereby ensuring good sealing performance even when the pressure inside the combustion chamber 200 is low. On the other hand, the compression degree of the elastic element 131 can also be adjusted according to actual needs by means of the fastener 132. A gas passage 1321 is formed in the fastener 132, which runs through it in the axial direction. The gas passage 1321 communicates with the gas passage 140 and the second receiving chamber 112.

[0050] The degree of compression of the elastic element 131 is proportional to the external pressure it receives. When the pressure inside the combustion chamber 200 increases, the gas pressure entering the second receiving chamber 112 through the gas passage 140 and the gas passage 1321 also increases. That is, the gas pressure inside the second receiving chamber 112 increases, and the pressure difference on the elastic element 131 also increases, thereby increasing the degree of compression of the elastic element 131. At this time, the thrust exerted by the elastic element 131 on the pushing part 150 increases, which helps to increase the contact force between the sealing assembly 120 and the side wall of the combustion chamber 200.

[0051] According to a preferred embodiment, the sealing assembly 120 includes a seal 121 and a load-bearing plate 122, such as Figure 1 and Figure 3 As shown. The seal 121 contacts the side wall 210 of the combustion chamber 200, and the force-bearing plate 122 is fitted with the seal 121, with the force-bearing plate 122 located between the seal 121 and the pusher 150, as shown. Figure 3 As shown. In this preferred embodiment, a high-temperature dynamic sealing structure is provided with a force-bearing plate 122 between the sealing element 121 and the pushing part 150. The force-bearing plate 122 helps to make the sealing element 121 bear force evenly, thereby ensuring that the combustion chamber 200 has reliable sealing performance.

[0052] According to a preferred embodiment, the seal 121 is formed by stacking at least two sealing pieces 1211, such as... Figure 6 As shown, a metal mesh is disposed between two adjacent sealing sheets 1211. Preferably, the metal mesh is a nickel-based metal mesh. Preferably, the sealing sheet 1211 is made of ceramic material. The sealing sheet 1211 made of ceramic material has the advantages of high temperature resistance and wear resistance, which helps to ensure the service life of the sealing structure.

[0053] Since the sealing sheet 1211 made of ceramic material is usually relatively fragile and has the potential to crack, the preferred technical solution of this embodiment is a high-temperature dynamic sealing structure. The sealing element 121 is formed by stacking at least two sealing sheets 1211, which can distribute the stress on the sealing element 121 to each sealing sheet 1211, reduce the stress on a single sealing sheet 1211, and thus improve the impact resistance and crack propagation resistance of the sealing element 121. On the other hand, a metal mesh is provided between two adjacent sealing sheets 1211. The metal mesh layer can provide better structural support for the sealing sheet 1211 and enhance the overall strength of the sealing element 121, prevent displacement or deformation of the sealing sheet 1211 during use, and also provide space for the deformation and rebound of the sealing element 121.

[0054] According to a preferred embodiment, the side of the sealing sheet 1211 that contacts another sealing sheet 1211 is provided with a plurality of sealing teeth 1211a, and a groove 1211b is formed between two adjacent sealing teeth 1211a. The groove 1211b is used to fill asbestos strips, such as... Figure 6 and Figure 7 As shown. Preferably, the asbestos strip is made of multiple layers of asbestos rolled up. The high-temperature dynamic sealing structure of the preferred technical solution in this embodiment can ensure the sealing between two adjacent sealing pieces 1211 through the asbestos strip, and at the same time, it can further enhance the stability of the sealing element 121 and prevent the sealing piece 1211 from being displaced or deformed during use.

[0055] According to a preferred embodiment, the first cross-sectional area of ​​the sealing sheet 1211 near the sidewall 210 is smaller than the second cross-sectional area of ​​the sealing sheet 1211 near the load-bearing plate 122, such as... Figure 8As shown. That is, the sealing sheet 1211 is formed with one end smaller and the other end larger. Preferably, the area of ​​the first cross-section is slightly smaller than the area of ​​the second cross-section. Specifically, the angle α between the sidewall of the sealing sheet 1211 and the horizontal plane is about 0.5°, such as... Figure 8 As shown (to clearly illustrate the included angle), Figure 8 (The included angle is slightly larger). The high-temperature dynamic sealing structure of the preferred technical solution in this embodiment has a first cross-sectional area smaller than the second cross-sectional area, which helps to maintain a certain gap between the sealing sheet 1211 and the mounting base 110. When the pressure on the sealing member 121 increases, it is convenient for the sealing member 121 to deform in the direction closer to the side wall 210 of the combustion chamber 200.

[0056] According to a preferred embodiment, the load-bearing plate 122 is made of a nickel-based high-temperature alloy material, and the thickness of the load-bearing plate 122 is 1-2 mm. In this preferred embodiment, the high-temperature dynamic sealing structure, with a load-bearing plate 122 thickness of 1-2 mm, allows the load-bearing plate 122 to possess a certain degree of flexibility while ensuring strength. This enables the load-bearing plate 122 to better withstand stress under high-temperature and high-pressure environments, absorb or alleviate stress concentration problems caused by temperature and pressure changes, reduce stress fatigue and deformation of the load-bearing plate 122, and thus improve the service life and performance stability of the load-bearing plate 122.

[0057] The second aspect of this embodiment provides a scramjet engine.

[0058] The scramjet engine of this embodiment includes the high-temperature dynamic sealing structure of any of the technical solutions in this embodiment. The remaining structure of the scramjet engine is the same as that of the prior art, and will not be described in detail here.

[0059] The scramjet engine of this embodiment includes a high-temperature dynamic sealing structure according to any of the technical solutions in this embodiment. Through the high-temperature dynamic sealing structure, the contact force between the sealing component 120 and the side wall of the combustion chamber 200 can be dynamically adjusted, thereby ensuring that the combustion chamber of the scramjet engine always maintains good sealing performance.

[0060] It should be noted that, in this document, the terms "comprising," "including," or any other variations thereof are intended to cover non-exclusive inclusion, such that a process, method, article, or apparatus that comprises a list of elements includes not only those elements but also other elements not expressly listed, or elements inherent to such a process, method, article, or apparatus. Without further limitations, an element defined by the phrase "comprising one..." does not exclude the presence of other identical elements in the process, method, article, or apparatus that includes that element. Furthermore, it should be noted that the scope of the methods and apparatuses in the embodiments of this application is not limited to performing functions in the order shown or discussed, but may also include performing functions substantially simultaneously or in the reverse order, depending on the functions involved. For example, the described methods may be performed in a different order than described, and various steps may be added, omitted, or combined. Additionally, features described with reference to certain examples may be combined in other examples.

[0061] The above description is merely a specific embodiment of the present invention, but the scope of protection of the present invention is not limited thereto. Any changes or substitutions that can be easily conceived by those skilled in the art within the scope of the technology disclosed in the present invention should be included within the scope of protection of the present invention.

Claims

1. A high temperature dynamic seal structure, characterized by, It includes a mounting base (110), a sealing assembly (120), a flexible adjustment assembly (130), and a gas passage (140), wherein, The gas passage (140) is connected to the combustion chamber (200) of the scramjet engine. The mounting base (110) has a first receiving chamber (111) and a second receiving chamber (112). The sealing assembly (120) is installed in the first receiving chamber (111), and the elastic adjustment assembly (130) is installed in the second receiving chamber (112). The second receiving chamber (112) is also connected to the gas passage (140), and the contact force of the sealing assembly (120) against the side wall (210) of the combustion chamber (200) can be adjusted based on the pressure of the gas in the combustion chamber (200) and the elastic force of the elastic adjustment assembly (130). The high-temperature dynamic sealing structure also includes a pushing part (150), which is movably installed in the second receiving chamber (112). The pushing part (150) applies a pushing force to the sealing assembly (120) based on the pressure of the gas in the second receiving chamber (112) and the elastic force of the elastic adjustment component (130). The elastic adjustment assembly (130) includes an elastic element (131) and a fastener (132), wherein, The elastic element (131) is installed between the pushing part (150) and the fastener (132), and the fastener (132) is used to apply a preload to the elastic element (131) and keep the elastic element (131) in a compressed state. The fastener (132) has a gas channel (1321) extending along its axial direction, and the gas channel (1321) is connected to the gas passage (140) and the second receiving chamber (112).

2. The high-temperature dynamic seal structure of claim 1, wherein, The push part (150) is provided with a sealing groove (151) in the circumferential direction. The sealing groove (151) is used to install a sealing ring. The sealing ring is used to keep the push part (150) and the mounting base (110) in a sealed connection.

3. The high-temperature dynamic sealing structure according to claim 1 or 2, characterized in that, The sealing assembly (120) includes a seal (121) and a force plate (122). The seal (121) contacts the side wall (210) of the combustion chamber (200), the force plate (122) fits against the seal (121), and the force plate (122) is located between the seal (121) and the pusher (150).

4. The high-temperature dynamic sealing structure according to claim 3, characterized in that, The seal (121) is formed by stacking at least two sealing sheets (1211), with a metal mesh between two adjacent sealing sheets (1211), and the sealing sheets (1211) are made of ceramic material.

5. The high-temperature dynamic sealing structure according to claim 4, characterized in that, The side of the sealing piece (1211) that contacts another sealing piece (1211) is provided with a plurality of sealing teeth (1211a), and a tooth groove (1211b) is formed between two adjacent sealing teeth (1211a), the tooth groove (1211b) being used to fill asbestos strips.

6. The high-temperature dynamic sealing structure according to claim 4, characterized in that, The first cross-sectional area of ​​the sealing sheet (1211) on the side wall (210) is smaller than the second cross-sectional area of ​​the sealing sheet (1211) on the side plate (122).

7. The high-temperature dynamic sealing structure according to claim 3, characterized in that, The load-bearing plate (122) is made of nickel-based high-temperature alloy material, and the thickness of the load-bearing plate (122) is 1~2mm.

8. A scramjet engine, characterized in that, The high-temperature dynamic sealing structure includes any one of claims 1 to 7.

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