Composite adjustable dynamic sealing structure of solid rocket engine and preparation method
By using a composite adjustable dynamic sealing structure, and combining a flat graphite ring and a nitrile rubber sealing ring, the sealing failure and gas leakage problems of solid rocket motors under high temperature and high pressure environments are solved, achieving efficient sealing effect and low-cost sealing material application.
Patent Information
- Application Number
- CN202511312816.2
- Authority / Receiving Office
- CN · China
- Patent Type
- Applications(China)
- Current Assignee / Owner
- Filing Date
- 2025-09-15
- Publication Date
- 2025-11-21
AI Technical Summary
Existing dynamic sealing technology for solid rocket motors is prone to failure under high temperature, high pressure, erosion and residue deposition environments, resulting in high gas leakage rates, high material costs and actuator jamming.
It adopts a composite adjustable dynamic sealing structure, which achieves a flexible and reliable seal by combining a flat graphite ring and a nitrile rubber sealing ring. Combined with a labyrinth seal sawtooth structure, the compression rate and preload of the graphite ring can be adjusted to avoid jamming and improve the sealing effect.
High-efficiency dynamic sealing was achieved under high temperature and high pressure conditions, reducing material costs and gas leakage rate, and improving the operating efficiency and sealing reliability of the actuator.
Smart Images
Figure CN120990769A_ABST
Abstract
Description
TECHNICAL FIELD
[0001] The present application relates to the technical field of solid rocket engine, in particular to a composite adjustable solid rocket engine dynamic sealing structure and a preparation method thereof. BACKGROUND
[0002] In the current international military field, space confrontation has gradually become one of the focus problems in the field of space technology and military research in today's world. Space confrontation refers to the military confrontation action against space targets, including "anti-missile" (including anti-ballistic missile and mobile missile) and "anti-defense" and other forms. The typical means of space confrontation is to use a kinetic energy interceptor (KKV) to realize autonomous navigation, accurate detection and guidance control in the process of rapid flight in orbit, realize direct collision or accurate relative motion with the target, and ensure effective kinetic energy collision, controllable or soft-killing target. Solid rocket engine has the advantages of simple structure, reliable operation, easy long-term storage, rapid reaction, simple maintenance, high war readiness rate, etc. In recent years, it is gradually replacing the liquid attitude and orbit control power system. Therefore, the variable thrust regulation and thrust vector control technology of solid rocket engine in space confrontation is particularly important. By adjusting the throat surface or propellant combustion surface of the solid rocket engine through an external driving mechanism, the thrust performance of the solid rocket engine is more flexible, and at the same time, the cooperation of multiple valves can avoid the use of gas valve cancellation method to stabilize the combustion chamber pressure, save system propellant energy, and improve the combat capability of the weapon system.
[0003] The solid rocket engine propellant combustion process produces a high temperature of 2000-3500 degrees Celsius, and the working pressure in the combustion chamber is generally between 5Mpa-30Mpa. At the same time, solid rocket propellant will produce a lot of solid residues during operation, so the variable thrust regulation and thrust vector control of solid rocket engine are required to be very high. Under the environmental conditions of high temperature, high pressure, scouring, ablation and residue deposition, the driving mechanism passes through the engine combustion chamber through the actuator to adjust the gas flow law inside the combustion chamber or the inside of the nozzle, which is particularly difficult.
[0004] In the prior art, the end face static sealing of the O-shaped sealing ring or the radial dynamic sealing of the O-shaped sealing ring, or the labyrinth sealing structure form, or simply through the graphite sealing ring to realize dynamic sealing.
[0005] In the solid rocket engine dynamic sealing technology, the existing dynamic sealing technology mainly has the following problems:
[0006] (1) The end face static sealing of the existing O-shaped sealing ring or the radial dynamic sealing technology of the O-shaped sealing ring requires higher requirements for the heat insulation structure during the sealing process of the long-time, high combustion temperature and high pressure solid rocket engine, to avoid high-temperature gas causing the O-shaped sealing ring to fail; at the same time, the residues in the solid propellant gas cause great damage to the O-shaped sealing ring, and once the residues enter the O-shaped sealing ring, the dynamic sealing structure will soon fail.
[0007] (2) The existing labyrinth sealing technology has high requirements for the material selection and process of the labyrinth structure, and requires that the labyrinth sealing structure material needs to withstand high temperature and not to deform and ablate, so the labyrinth sealing structure material is expensive; at the same time, the labyrinth sealing has a certain gas leakage rate, which causes the loss of propellant energy on the one hand, and the ablation damage of the high-temperature gas leakage to the equipment outside the combustion chamber on the other hand.
[0008] (3) The existing technology of simply realizing dynamic sealing through a graphite sealing ring needs to provide a large pre-tightening force to make the graphite sealing ring have a large compression rate, so as to realize dynamic sealing, but the large pre-tightening force also generates a large friction force on the actuating mechanism, which directly leads to problems such as jamming or low execution efficiency of the actuating mechanism. SUMMARY
[0009] Based on the above technical problems, the present application provides a composite adjustable solid rocket engine dynamic sealing structure and a preparation method to solve the reliable dynamic sealing problem of the solid rocket engine. By adjusting the thickness of the flat graphite ring, different degrees of compression rate are realized, and then the graphite compression deformation realizes residue filtration on the actuating mechanism, avoiding the problem of jamming. By compressing the nitrile rubber sealing ring through the double-layer flat graphite ring, flexible and reliable sealing is realized. The end face static sealing is realized through the meshing of the labyrinth sealing sawtooth and the graphite ring.
[0010] In order to solve the above technical problems, one of the purposes of the present application is to provide a composite adjustable solid rocket engine dynamic sealing structure, which comprises an actuating mechanism 1, a dynamic sealing cover plate A 2, a flat graphite ring 3, a sealing ring 4, a set screw 5, a spring washer 6, a dynamic sealing partition plate 7, a dynamic sealing cover plate B 8, a combustion chamber shell 9 and a combustion chamber insulation layer 10,
[0011] The flat graphite ring 3 and the sealing ring 4 are respectively arranged in the dynamic sealing cover plate A 2 and the dynamic sealing cover plate B 8 to form a composite adjustable assembly;
[0012] The dynamic sealing partition plate 7 serves as an intermediate structure connecting the two composite adjustable assemblies, and is pre-tightened and fixed at the corresponding interface of the combustion chamber shell 9 through the set screw 5 and the spring washer 6;
[0013] The actuating executor 1 passes through the combined dynamic sealing structure and enters the combustion chamber, and rotation actuation or axial reciprocating motion of the actuating executor is realized through the driving mechanism.
[0014] The combustion chamber heat insulation layer 10 protects the combustion chamber shell 9 from heat.
[0015] Further, the sealing ring 4 is a nitrile rubber sealing ring.
[0016] Further, the sealing ring 4 is made of rubber material with a Shore hardness greater than 60, and is selected as a fluororubber ring or a silicone rubber ring.
[0017] Further, the dynamic sealing cover plate A 2 and the dynamic sealing cover plate B 8 are provided with continuous and uniform annular trapezoidal protrusions on the inner flat end faces, and in the process of pressing the composite adjustable assembly through the locking screw 5 and the spring washer 6, the continuous and uniform annular protrusions will be embedded in the flat graphite ring 3, so that the zigzag end face sealing is realized, and the gas leakage through the side end face is well prevented.
[0018] Further, the flat graphite ring 3 is provided with a concave groove at the inner diameter, and the flat graphite ring 3 is formed by flat pressing of multiple layers of graphite sheets, and the multiple layers of graphite sheets are tightly bonded through carbon molecules of graphite, and compared with the integral graphite ring or the longitudinal layered graphite ring, the flat graphite ring can realize good structural stability and ductility in the compression process, and the sealing effect is better.
[0019] Further, the nitrile rubber sealing ring 4 is arranged in the groove between the two flat graphite rings 3, forming a composite sealing structure, and directly contacting the actuating executor 1, and through a certain pre-tightening force, the nitrile rubber sealing ring 4 will produce a certain compression rate, and be attached to the actuating executor 1, realizing radial dynamic sealing.
[0020] Based on the same concept, the application also provides a preparation method of the composite adjustable solid rocket engine dynamic sealing structure, and the specific steps are as follows:
[0021] S1: the flat graphite ring (3) and the nitrile rubber sealing ring (4) are respectively arranged in the dynamic sealing cover plate A (2) and the dynamic sealing cover plate B (8) according to the design state, to form a composite adjustable assembly structure;
[0022] S2: the composite adjustable assembly structure prepared in S1 is connected with the dynamic sealing partition plate (7) through the shaft hole matching, and before assembly, the composite adjustable assembly structure and the dynamic sealing partition plate (7) are cleaned by alcohol to remove impurities on the surface, and after cleaning, the composite adjustable assembly structure and the dynamic sealing partition plate (7) are connected through the shaft hole matching.
[0023] S3: through the adjusting screw (5), spring washer (6), the assembly of S2 assembly and the assembly of the combustion chamber shell (9) and the combustion chamber insulation layer (10) are assembled, the appearance of the assembly is checked and the cleaning is completed, and after the cleaning is completed, the assembly and the combustion chamber shell (9) are assembled;
[0024] S4: the assembly of the actuator in the combustion chamber shell (9) is completed, according to the specific task requirement, the specific connection form of the actuator in the combustion chamber shell (9) is executed according to the specific design requirement;
[0025] S5: the assembly of the external driving mechanism and the actuating actuator (1) is completed, the specific connection form and the interface are executed according to the specific design requirement.
[0026] Further, the S1 is specifically:
[0027] S11: according to the specific task requirement of dynamic sealing, the compression rate of the flat graphite ring (3) and the butyronitrile rubber sealing ring (4) is designed, the corresponding size of the flat graphite ring (3) and the butyronitrile rubber sealing ring (4) is adjusted before assembly, and the end face of the flat graphite ring (3) is ground according to the actual situation to meet the size requirement of the design compression rate;
[0028] S12: the surface and the matching surface of the flat graphite ring (3), the butyronitrile rubber sealing ring (4), the dynamic sealing cover plate A (2) and the dynamic sealing cover plate B (8) are cleaned, and the apparent quality is carefully checked, and after confirming that there is no product quality problem, the assembly of the composite adjustable assembly structure is completed.
[0029] Further, in the S3, the pre-tightening force is uniformly applied by the adjusting screw (5), so that the w gap is not greater than 0.02mm.
[0030] The above one or more technical solutions of the application have at least one or more of the following technical effects:
[0031] Compared with the end face static sealing of the O-shaped sealing ring or the radial dynamic sealing technology of the O-shaped sealing ring, the composite adjustable dynamic sealing structure can solve the high-temperature gas sealing failure problem in the sealing process of the long-time, high-burning temperature and high-pressure solid rocket engine through the combined graphite ring; and the composite adjustable dynamic sealing structure can effectively enter the O-shaped sealing ring, and the dynamic sealing structure failure problem is avoided.
[0032] Compared with the existing labyrinth sealing technology, the composite adjustable dynamic sealing structure greatly reduces the material selection and process requirement, and solves the gas leakage rate problem, avoiding the energy loss of propellant and the ablation damage to the external equipment of the combustion chamber.
[0033] Compared with the existing dynamic sealing technology by graphite sealing ring alone, the rubber component of the nitrile rubber sealing ring melts at high temperature, which has a certain lubricating effect on the dynamic sealing structure, and can realize high actuating efficiency.
[0034] The internal end surface of the dynamic sealing cover plate is provided with continuous and uniform annular trapezoidal protrusions, which realize serrated end surface sealing and can well prevent gas from leaking through the side end surface.
[0035] The structure is simple, the dynamic sealing efficiency is high, the material source is wide, and the cost is low, and it can be widely and flexibly applied to the field of dynamic sealing technology of solid rocket engines. BRIEF DESCRIPTION OF DRAWINGS
[0036] Figure 1 A composite adjustable solid rocket engine dynamic sealing structure
[0037] Figure 2 A composite adjustable component structure schematic diagram
[0038] 1-actuating execution mechanism; 2-dynamic sealing cover plate A; 3-flat graphite ring; 4-nitrile rubber sealing ring; 5-tightening screw; 6-spring washer; 7-dynamic sealing partition plate; 8-dynamic sealing cover plate B; 9-combustion chamber shell; 10-combustion chamber insulation layer. DETAILED EMBODIMENT
[0039] The dynamic sealing structure of the present application can be applied to the environment conditions of high temperature, high pressure, flushing, ablation and residue deposition, and can ensure high execution efficiency of the actuator, low adiabatic performance requirement, low leakage rate requirement, solve the problem of residue jamming, and has the advantages of multiple actuation and repeated use. The present application relates to a composite adjustable solid rocket engine dynamic sealing structure, in particular to a special solid rocket engine, which is used in the application environment of throat surface adjustment and thrust vector control, and is used for dynamic adjustment of high temperature and high pressure gas flow. The actuation mechanism realizes the adjustment and control of high temperature and high pressure gas flow through a composite adjustable sealing structure during the execution of the actuation process through the combustion chamber, and the selection of dynamic sealing material and the specific forming structure are proposed. Because the solid rocket engine propellant combustion process produces high temperature of 2000-3500 degrees Celsius, the working pressure in the combustion chamber is generally between 5Mpa and 30Mpa, and the solid rocket propellant produces a lot of solid residue during the working process, so the variable thrust adjustment and thrust vector control of the solid rocket engine are proposed with high requirements. It is particularly difficult to adjust the gas flow in the combustion chamber or the nozzle through the actuation execution mechanism driven by the actuation mechanism through the engine combustion chamber under the environment conditions of high temperature, high pressure, flushing, ablation and residue deposition. Therefore, the present application proposes a composite adjustable solid rocket engine dynamic sealing structure, which can withstand high temperature of 2000-3500 degrees Celsius through the flat graphite ring. The thickness of the flat graphite ring is adjusted to realize different compression rates, and then the graphite compression deformation realizes residue filtration of the actuation execution mechanism to avoid jamming. The double-layer flat graphite ring compresses the nitrile rubber seal ring to realize flexible and reliable sealing. The end face static sealing is realized through the engagement of the labyrinth sealing serration with the graphite ring.
[0040] The composite adjustable solid rocket engine dynamic sealing structure of the present application comprises an actuation execution mechanism 1, a dynamic sealing cover plate A2, a flat graphite ring 3, a nitrile rubber seal ring 4, a set screw 5, a spring washer 6, a dynamic sealing partition plate 7, a dynamic sealing cover plate B 8, a combustion chamber shell 9 and a combustion chamber adiabatic layer 10. Figure 1
[0041] The composite adjustable assembly structure is the core of the composite adjustable dynamic sealing structure. The part includes 1 dynamic sealing cover plate, 2 flat graphite rings, and 1 nitrile rubber sealing ring. The 2 flat graphite rings are pressed in the middle by a groove, and 1 nitrile rubber sealing ring, and the combination of the sealing member is installed in the dynamic sealing cover plate. The composite adjustable assembly realizes the combined dynamic sealing structure on both sides through the dynamic sealing partition plate 7. The combined dynamic sealing structure is pressed and connected and fixed to the external port of the combustion chamber through the set screw 5 and the spring washer 6. The actuating mechanism 1 passes through the combined dynamic sealing structure, enters the combustion chamber, and realizes the rotary actuation or axial reciprocating motion of the actuating mechanism through the driving mechanism, thereby controlling the flow regulating mechanism such as a rotary valve, a plug valve or a swing valve, and good dynamic sealing effect can be ensured.
[0042] The technical solutions in the embodiments of the present application will be described clearly and completely below in combination with the embodiments of the present application and the drawings. Obviously, the described embodiments are only some of the embodiments of the present application, rather than all the embodiments. All other embodiments obtained by those skilled in the art based on the embodiments of the present application belong to the scope of protection of the present application.
[0043] The composite adjustable solid rocket engine dynamic sealing structure form of the present application comprises an actuating mechanism 1, a dynamic sealing cover plate A2, flat graphite rings 3, a nitrile rubber sealing ring 4, a set screw 5, a spring washer 6, a dynamic sealing partition plate 7, a dynamic sealing cover plate B 8, a combustion chamber shell 9, and a combustion chamber insulation layer 10. A composite adjustable solid rocket engine dynamic sealing structure schematic diagram is shown in the accompanying Figure 1
[0044] The actuating mechanism 1 passes through the combustion chamber, realizes the rotary actuation or axial reciprocating motion of the actuating mechanism through the driving mechanism, and then controls the flow regulating mechanism.
[0045] The dynamic sealing cover plate A2 and the dynamic sealing cover plate B 8 realize the fixation and limiting of the flat graphite rings and the nitrile rubber sealing ring. At the same time, the internal end face of the dynamic sealing cover plate is provided with continuous and uniform annular trapezoidal protrusions. During the compression process of the composite adjustable assembly by the set screw 5 and the spring washer 6, the continuous and uniform annular protrusions will be embedded in the flat graphite rings 3, realizing the sawtooth end face sealing, which can well prevent the leakage of the combustion gas through the side end face.
[0046] The flat graphite ring 3 is provided with a concave groove at the inner diameter, and is formed by flatly laying and pressing multiple layers of graphite sheets, and the multiple layers of graphite sheets are tightly bonded by carbon molecules of graphite, and compared with an integral graphite ring or a graphite ring with longitudinal layers, the flat graphite ring can achieve good structural stability and ductility during compression. The integral graphite ring is prone to cracking during compression, thereby causing sealing failure, and the graphite ring with longitudinal layers is prone to delamination during compression, thereby causing sealing failure. Meanwhile, the graphite material has good high-temperature resistance, and the temperature conducted to the flat graphite ring 3 by the actuating mechanism is less than the bearing temperature boundary of the graphite ring, so that reliable dynamic sealing can be achieved.
[0047] The nitrile rubber seal ring 4 is arranged in the groove between the two flat graphite rings 3 and directly contacts the actuating mechanism 1, and under the action of a certain pre-tightening force, the nitrile rubber seal ring 4 will be compressed to a certain extent and be attached to the actuating mechanism 1 to achieve radial dynamic sealing. Since the rubber component of the nitrile rubber seal ring 4 melts at high temperature, it has a certain lubricating effect on the dynamic sealing structure, thereby achieving high actuating efficiency.
[0048] The composite adjustable assembly structure composed of the dynamic sealing cover plate, the flat graphite ring 3 and the nitrile rubber seal ring 4 can adjust the compression rate of the flat graphite ring 3 by controlling the size of the w, and through the auxiliary sealing effect of the nitrile rubber seal ring 4, the flat graphite ring 3 can be compressed to a small compression rate to achieve good dynamic sealing effect, and the actuating mechanism 1 will not generate too much frictional resistance, thereby improving the actuating efficiency, and the composite adjustable assembly structure can well control the sealing and actuating effects. Figure 2 The composite adjustable assembly structure is shown in the accompanying drawings. Figure 2
[0049] The dynamic sealing partition plate 7 is an intermediate structure connecting the two composite adjustable assemblies, and is pre-tightened and fixed to the corresponding interfaces of the combustion chamber shell 9 by the set screws 5 and the spring washers 6.
[0050] The combustion chamber insulation layer 10 protects the combustion chamber shell 9 from heat.
[0051] The dynamic sealing structure of the composite adjustable solid rocket engine is assembled as follows:
[0052] First step of assembly: The flat graphite ring 3 and the nitrile rubber seal ring 4 are respectively arranged in the dynamic sealing cover plate A2 and the dynamic sealing cover plate B 8 according to the designed state to form a composite adjustable assembly structure.
[0053] Firstly, according to the specific task requirements of dynamic sealing, the compression rate of the flat graphite ring 3 and the butadiene-acrylonitrile rubber sealing ring 4 is designed, and the corresponding size adjustment of the flat graphite ring 3 and the butadiene-acrylonitrile rubber sealing ring 4 is completed before assembly. The end face of the flat graphite ring 3 is ground according to the actual situation to meet the size requirement of the designed compression rate.
[0054] The surface and mating surface of the flat graphite ring 3, the butadiene-acrylonitrile rubber sealing ring 4, the dynamic sealing cover plate A 2 and the dynamic sealing cover plate B 8 are cleaned, and the apparent quality is carefully checked, and after confirming that there is no product quality problem, the appendix Figure 2 The assembly of the composite adjustable assembly structure is completed.
[0055] The second step assembly: the composite adjustable assembly structure is connected with the dynamic sealing partition plate 7 through the shaft hole matching.
[0056] Before assembly, the composite adjustable assembly structure and the dynamic sealing partition plate 7 are cleaned by alcohol to remove surface impurities. After cleaning, the composite adjustable assembly structure and the dynamic sealing partition plate 7 are connected through the shaft hole matching.
[0057] The third step assembly: through the set screw 5 and the spring washer 6, the assembly of the second step assembly and the combustion chamber shell 9 and the combustion chamber insulation layer 10 assembly is completed.
[0058] Firstly, the appearance of the assembly is checked and cleaned, and the cleaning process can use anhydrous ethanol for cleaning. After cleaning, the assembly and the combustion chamber shell 9 are assembled. By uniformly applying the pre-tightening force through the set screw 5, the appendix Figure 2 The w gap shown is not greater than 0.02 mm.
[0059] The fourth step assembly: the assembly of the internal actuator of the combustion chamber shell 9 is completed.
[0060] According to the specific task requirements, the internal actuator of the combustion chamber shell 9 is a rotary valve, a plug valve or a swing valve, and the specific connection form is executed according to the specific design requirements.
[0061] The fifth step assembly: the assembly of the external driving mechanism and the actuating actuator 1 is completed.
[0062] According to the specific design requirements, the external driving mechanism is a rudder assembly, an electromagnet assembly, a hydraulic drive or a cylinder structure, and the specific connection form and interface are executed according to the specific design requirements.
[0063] Obviously, those skilled in the art can make various modifications and variations to the embodiments of the present application without departing from the spirit and scope of the embodiments of the present application. Thus, if these modifications and variations of the embodiments of the present application fall within the scope of the claims of the present application and their equivalent technologies, the present application also intends to include these modifications and variations.
[0064] The application is mainly directed to the drive and execution mechanism involved in the adjustment process of the throat surface or propellant combustion surface of a solid rocket engine, and particularly proposes a dynamic sealing technology that can provide a solid power system with resistance to the particle-containing, high-temperature and high-pressure gas flow scouring environment, which is of great significance to improving the performance of China's space countermeasure weapon system.
Claims
1. A composite dynamically sealed structure for a solid rocket motor with adjustable grain, characterized in that: It comprises an actuating executor (1), a dynamic sealing cover plate A (2), a flat graphite ring (3), a sealing ring (4), a fastening screw (5), a spring washer (6), a dynamic sealing partition plate (7), a dynamic sealing cover plate B (8), a combustion chamber shell (9) and a combustion chamber heat insulation layer (10), The flat graphite ring (3) and the sealing ring (4) are respectively arranged in the dynamic sealing cover plate A (2) and the dynamic sealing cover plate B (8) to form a composite adjustable assembly. The dynamic sealing partition plate (7) is used as an intermediate structure connecting the two composite adjustable assemblies, and is pre-tightened and fixed at the corresponding interfaces of the combustion chamber shell (9) through the fastening screw (5) and the spring washer (6). The actuating executor (1) penetrates through the combined dynamic sealing structure and enters the combustion chamber, and realizes the rotary actuation or axial reciprocating motion of the actuating executor through a driving mechanism. The combustion chamber heat insulation layer (10) protects the combustion chamber shell (9) from heat.
2. The composite dynamically sealed structure of a solid rocket motor according to claim 1, wherein: The sealing ring (4) is a nitrile rubber sealing ring.
3. The dynamic seal structure for a composite, throttling solid rocket engine of claim 1 or 2, wherein: The sealing ring (4) is made of rubber material with a Shore hardness greater than 60, and is selected as a fluororubber ring or a silicone rubber ring.
4. The dynamic seal structure for a composite, adjustable solid rocket engine of claim 1, wherein: The flat end surface inside the dynamic sealing cover plate A (2) and the dynamic sealing cover plate B (8) is provided with continuous and uniform annular trapezoidal protrusions, which will be embedded in the flat graphite ring (3) during the compression process of the composite adjustable assembly by the fastening screw (5) and the spring washer (6), so as to realize the zigzag end surface sealing and effectively prevent gas leakage through the side end surface.
5. The composite dynamically sealed structure of a solid rocket motor according to claim 1, wherein: The flat graphite ring (3) is provided with a concave groove at the inner diameter, and is formed by pressing multiple layers of graphite sheets. The multiple layers of graphite sheets are tightly bonded by carbon molecules of graphite. Compared with an integral graphite ring or a longitudinal layered graphite ring, the flat graphite ring can achieve good structural stability and ductility during compression, and has better sealing effect.
6. The dynamic seal structure for a composite, throttable solid rocket engine of claim 2, wherein: The nitrile rubber sealing ring (4) is arranged in the groove between the two flat graphite rings (3) to form a composite sealing structure, which is in direct contact with the actuating executor (1). Through a certain pre-tightening force, the nitrile rubber sealing ring (4) will be compressed to a certain extent and adhere to the actuating executor (1) to realize radial dynamic sealing.
7. The method of claim 1-6, wherein the method further comprises, The specific steps are as follows: S1: The flat graphite ring (3) and the nitrile rubber sealing ring (4) are respectively arranged in the dynamic sealing cover plate A (2) and the dynamic sealing cover plate B (8) to form a composite adjustable assembly structure; S2: The composite adjustable assembly structure obtained in S1 is connected with the dynamic sealing partition plate (7) through the shaft hole matching, and the surface impurities of the composite adjustable assembly structure and the dynamic sealing partition plate (7) are removed before assembly. After cleaning, the composite adjustable assembly structure and the dynamic sealing partition plate (7) are connected through the shaft hole matching; S3: The assembly completed in S2 is assembled with the combustion chamber shell (9) and the combustion chamber heat insulation layer (10) assembly through the fastening screw (5) and the spring washer (6). The assembly is inspected and cleaned, and then the assembly is completed with the combustion chamber shell (9). S4: complete the assembly of the internal actuator in the combustion chamber shell (9), including but not limited to the plug valve core, rotary valve or swing valve, the assembly method is threaded connection, pin connection or interference fit; S5: complete the assembly of the external driving mechanism and the actuator (1), including but not limited to steering gear, cylinder, hydraulic cylinder or electromagnet, the assembly method is threaded connection, pin connection or interference fit.
8. The method of claim 7, wherein the method further comprises, The S1 is specifically: S11: according to the specific task requirements of dynamic sealing, the compression rate of the flat graphite ring (3) and the butyronitrile rubber sealing ring (4) is designed, and the corresponding size of the flat graphite ring (3) and the butyronitrile rubber sealing ring (4) is adjusted before assembly. The end face of the flat graphite ring (3) is ground according to the actual situation to meet the size requirement of the designed compression rate; S12: clean the surface and matching surface of the flat graphite ring (3), butyronitrile rubber sealing ring (4), dynamic sealing cover plate A (2) and dynamic sealing cover plate B (8), and carefully check the apparent quality. After confirming that there is no product quality problem, the assembly of the composite adjustable assembly structure is completed.
9. The method of claim 7, wherein the method further comprises: In the S3, the pre-tightening force is uniformly applied by the locking screw (5), so that the w gap is not greater than 0.02 mm.