WO2024093078A1 - 一种变推力针栓式喷注器 - Google Patents

一种变推力针栓式喷注器 Download PDF

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Publication number
WO2024093078A1
WO2024093078A1 PCT/CN2023/079697 CN2023079697W WO2024093078A1 WO 2024093078 A1 WO2024093078 A1 WO 2024093078A1 CN 2023079697 W CN2023079697 W CN 2023079697W WO 2024093078 A1 WO2024093078 A1 WO 2024093078A1
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WO
WIPO (PCT)
Prior art keywords
pintle
flow channel
wall
combustion chamber
shell
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Application number
PCT/CN2023/079697
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English (en)
French (fr)
Inventor
张晓军
宋大亮
李龙飞
章荣军
王化余
卞香港
凌前程
高飞
张泽其
Original Assignee
西安航天动力研究所
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Application filed by 西安航天动力研究所 filed Critical 西安航天动力研究所
Publication of WO2024093078A1 publication Critical patent/WO2024093078A1/zh

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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02K—JET-PROPULSION PLANTS
    • F02K9/00—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof
    • F02K9/42—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof using liquid or gaseous propellants
    • F02K9/44—Feeding propellants
    • F02K9/52—Injectors

Definitions

  • the present application relates to the technical field of injectors, and in particular to a variable thrust pintle injector.
  • Liquid rocket engines are the core components of spacecraft. They are chemical rocket propulsion systems that use liquid chemicals as energy and working fluids.
  • the thrust chamber of the engine is an important component that converts the chemical energy of liquid propellant into thrust.
  • the thrust chamber consists of an injector, a combustion chamber, and a nozzle. Liquid propellant enters the combustion chamber through the injector, and generates combustion products through atomization, mixing, and combustion. The products are ejected from the nozzle at high speed to generate thrust.
  • variable thrust liquid rocket engines The thrust control of variable thrust liquid rocket engines is achieved by controlling the propellant flow rate.
  • the pintle injector when selecting the injector of the variable thrust liquid rocket engine, not only has an adjustable injection area, but also has the advantages of simple structure, high working reliability and low cost.
  • the thrust adjustment of the moving parts of the variable thrust pintle injector is usually mechanically actuated, such as motor-driven adjustment.
  • mechanical actuation has high requirements on the working environment conditions.
  • the mechanical actuation needs to be insulated from low temperature, which makes the injector structure more complicated and the working reliability is low.
  • variable thrust pintle injector which uses actuating fluid to achieve thrust adjustment to avoid the problem that mechanical actuation adjustment has high requirements for working environment conditions, resulting in complex injector structure and low working reliability.
  • the present application provides a variable thrust pintle injector, comprising a housing, a central tube and a pintle.
  • the housing has a first through cavity, a first flow channel for introducing a first propellant is provided on the housing, and the first flow channel is connected to the first cavity.
  • the central tube is sleeved in the first cavity, and the central tube is fastened to the housing.
  • the central tube has a second cavity for introducing a second propellant, and a second flow channel is provided at one end of the central tube close to the combustion chamber, and the second flow channel connects the second cavity and the combustion chamber.
  • the pintle is arranged between the central tube and the shell, and a third flow channel is formed between the inner wall of the shell and the outer wall of the pintle, and the third flow channel connects the first flow channel and the combustion chamber.
  • the pintle can move along the axis extension direction of the central tube, and the pintle can block the outlet end of the first flow channel and the outlet end of the second flow channel. When the pintle moves away from the combustion chamber, the area of the outlet end of the first flow channel and the outlet end of the second flow channel blocked by the pintle gradually decreases.
  • the central tube is also provided with a fourth flow channel for injecting actuating fluid above the pintle.
  • the central tube is also provided with a liquid outlet for outputting actuating fluid.
  • variable thrust pintle injector provided by the present application includes a shell, a center tube and a pintle, the shell has a through first cavity, the center tube is sleeved in the first cavity, and the center tube is tightly connected to the shell, so that the relative position of the center tube and the shell can be fixed, thereby avoiding relative displacement between the center tube and the shell, which affects the consistency of component assembly.
  • a first flow channel for passing the first propellant is opened on the shell, and the first flow channel is connected to the first cavity.
  • the pintle is arranged between the center tube and the shell, and a third flow channel is formed between the inner wall of the shell and the outer wall of the pintle, and the third flow channel connects the first flow channel and the combustion chamber. It can be seen that the first propellant can be transported to the combustion chamber through the first flow channel and the third flow channel.
  • the center tube has a second cavity for passing the second propellant, and a second flow channel is opened at one end of the center tube close to the combustion chamber, and the second flow channel connects the second cavity and the combustion chamber, which shows that the second propellant can be transported to the combustion chamber through the second cavity and the second flow channel.
  • the pintle can move along the axis extension direction of the central tube, and the pintle can block the outlet end of the first flow channel and the outlet end of the second flow channel. When the pintle moves away from the combustion chamber, the area of the outlet end of the first flow channel and the outlet end of the second flow channel blocked by the pintle gradually decreases.
  • the central tube is also provided with a fourth flow channel for injecting actuating fluid above the pintle.
  • the actuating fluid flows to the top of the pintle through the fourth flow channel, and generates pressure on the pintle to move toward the side close to the combustion chamber.
  • the pintle moves toward the side close to the combustion chamber under the pressure of the actuating fluid.
  • the end of the first flow channel away from the first cavity is inclined toward the side close to the combustion chamber.
  • variable thrust pintle injector By adjusting the flow of the actuating fluid, the relative position of the pintle and the central tube in the axial direction is ultimately changed, so that the area blocked by the pintle at the outlet end of the first flow channel and the outlet end of the second flow channel can be adjusted to change, and the flow of the first propellant and the second propellant can be further adjusted.
  • the variable thrust pintle injector uses actuating fluid rather than mechanical actuation adjustment to achieve thrust adjustment, avoiding the problem that mechanical actuation adjustment has high requirements for working environment conditions, resulting in a complex injector structure and low working reliability.
  • FIG1 is a cross-sectional schematic diagram of a variable thrust pintle injector provided in an embodiment of the present application
  • FIG. 2 is a partial schematic diagram of a variable thrust pintle injector provided in an embodiment of the present application.
  • Reusable aircraft is an important development direction in the field of space transportation technology, and is a technology that all major space powers in the world attach great importance to.
  • the reusable Falcon 9 rocket has greatly reduced the launch cost by reusing the first stage, which has become its unique advantage in market competition and has occupied most of the launch market in the United States.
  • the key to the reuse of launch vehicles lies in recovery.
  • the rocket engine In order to achieve the recovery of launch vehicles, the rocket engine needs to have a certain variable thrust capability. High-thrust liquid rocket engines with variable thrust capability are currently a hot topic of research.
  • Variable thrust injectors and their reuse technology restrict the low cost of launch vehicles and are bottleneck technologies in the industry.
  • the pintle injector is a single injection unit with a simple structure, good detectability, and easy to reuse.
  • the pintle injector is easy to adjust the injection and convenient for realizing the variable thrust function. From the technical characteristics, the pintle injector has unique advantages in the field of reusable liquid rocket engines.
  • the thrust adjustment of the moving parts of the variable thrust pintle injector is usually mechanically adjusted, such as spring-hydraulic adjustment or motor adjustment.
  • the injector is prone to medium-frequency oscillation problems caused by the coupling of the injector and the spring's natural frequency, and the injector has poor stability.
  • the spring is subjected to large forces and has large movement displacements, and the spring is very prone to structural damage.
  • the motor-actuated variable-thrust pintle injector has high requirements for working environment conditions.
  • the injector's operating temperature is low due to the low temperature of liquid oxygen, and the motor needs to be insulated from low temperatures.
  • the injector structure is relatively complex and has low working reliability.
  • the high-thrust engine requires a very large actuating force from the motor, and the motor structure is heavy and requires a large current, which imposes a heavy burden on the launch vehicle.
  • the core of the present application is to provide a variable thrust pintle injector, including a shell 1, a center tube 2 and a pintle 3.
  • the shell 1 has a through first cavity, and a first flow channel 11 for introducing a first propellant is opened on the shell 1, and the first flow channel 11 is connected to the first cavity.
  • the center tube 2 is sleeved in the first cavity, and the center tube 2 is tightly connected to the shell 1.
  • the center tube 2 has a second cavity 21 for introducing a second propellant, and a second flow channel 22 is opened at one end of the center tube 2 close to the combustion chamber, and the second flow channel 22 connects the second cavity 21 and the combustion chamber.
  • the pintle 3 is arranged between the center tube 2 and the shell 1, and a third flow channel 12 is formed between the inner wall of the shell 1 and the outer wall of the pintle 3, and the third flow channel 12 connects the first flow channel 11 and the combustion chamber.
  • the pintle 3 can move along the axis extension direction of the central cylinder 2, and the pintle 3 can block the outlet end of the first flow channel 11 and the outlet end of the second flow channel 22.
  • the central cylinder 2 is also provided with a fourth flow channel 14 for injecting actuating fluid above the pintle 3.
  • the central cylinder 2 is also provided with a liquid outlet 15, which is connected to the accommodating chamber 17 and is used to output the actuating fluid.
  • variable thrust pintle injector provided in the embodiment of the present application includes a shell 1, a center tube 2 and a pintle 3.
  • the shell 1 has a through first cavity, and the center tube 2 is sleeved in the first cavity.
  • the center tube 2 is tightly connected to the shell 1. In this way, the relative position of the center tube 2 and the shell 1 can be fixed, thereby avoiding relative displacement between the center tube 2 and the shell 1, which affects the consistency of component assembly.
  • the shell 1 is provided with a first flow channel 11 for introducing the first propellant, and the first flow channel 11 is connected to the first cavity.
  • the pintle 3 is arranged between the center tube 2 and the shell 1, and a third flow channel 12 is formed between the inner wall of the shell 1 and the outer wall of the pintle 3.
  • the third flow channel 12 connects the first flow channel 11 and the combustion chamber. It can be seen that the first propellant can be transported to the combustion chamber through the first flow channel 11 and the third flow channel 12.
  • the central tube 2 has a second cavity 21 for introducing the second propellant.
  • a second flow channel 22 is provided at one end of the central tube 2 close to the combustion chamber.
  • the second flow channel 22 connects the second cavity 21 and the combustion chamber, which indicates that the second propellant can be transported into the combustion chamber through the second cavity 21 and the second flow channel 22.
  • the pintle 3 can move along the axis extension direction of the central tube 2, and the pintle 3 can block the outlet end of the first flow channel 11 and the outlet end of the second flow channel 22. When the pintle 3 moves away from the combustion chamber, the area of the outlet end of the first flow channel 11 and the outlet end of the second flow channel 22 blocked by the pintle 3 gradually decreases.
  • the central tube 2 is also provided with a fourth flow channel 14 for injecting an actuating fluid above the pintle 3.
  • the actuating fluid flows to the top of the pintle through the fourth flow channel 14, and exerts pressure on the pintle 3 to move toward the side close to the combustion chamber.
  • the pintle 3 moves toward the side close to the combustion chamber under the pressure of the actuating fluid.
  • the end of the first flow channel 11 away from the first cavity is inclined toward the side close to the combustion chamber.
  • the force of the actuating fluid on the pintle 3 is changed. It should be understood that, at the same time, the pintle 3 is still subjected to a force of the first propellant in the direction away from the combustion chamber.
  • the pintle 3 moves along the axis of the center tube, so that the relative position of the pintle 3 and the center tube 2 in the axial direction is further changed, and finally the outlet end of the first flow channel 11 and the outlet end of the second flow channel 22 can be adjusted to change, and the flow rate of the first propellant and the second propellant can be further adjusted.
  • variable thrust pintle injector provided in the embodiment of the present application uses actuating fluid instead of mechanical actuation adjustment to adjust the thrust, avoiding the problem that the mechanical actuation adjustment has high requirements on the working environment conditions, resulting in a complex structure of the injector and low working reliability.
  • the number of the first flow channels 11 can be multiple, and the multiple first flow channels 11 are uniformly spaced along the circumference of the shell 1.
  • the uniform distribution not only improves the uniformity of the force exerted on the pintle 3 by the first propellant, but also improves the uniformity of the first propellant injected into the combustion chamber, increases the utilization rate of the first propellant, and improves the combustion performance of the engine.
  • the shell 1 can be fastened to the center tube 2 by bolts 9, and the axis of the shell 1 is colinear with the axis of the center tube 2.
  • the shell 1 can also be fastened to the center tube 2 by welding, which is not specifically limited here and is set according to actual conditions.
  • the center tube 2 includes a center tube body and a connecting portion, the connecting portion is located at the periphery of the center tube body, the outer circumferential size of the connecting portion is larger than the outer circumferential size of the center tube body, and the connecting portion is located above the shell 1, and the connecting portion is fastened to the top of the shell 1.
  • the axis of the bolt 9 is parallel to the axis of the center tube 2. There are multiple bolts 9, and the multiple bolts 9 are evenly distributed along the circumference of the center tube 2 to enhance the stability of the connection between the shell 1 and the center tube 2.
  • first propellant and the second propellant are one of the fuel or the oxidant.
  • first propellant is a fuel
  • the second propellant is an oxidant
  • the first propellant is set as a fuel or an oxidant, which is set according to the actual situation and is not specifically limited here.
  • the value of the angle ⁇ between the liquid outlet direction of the second flow channel 22 and the liquid outlet direction of the third flow channel 12 is set according to the actual situation, so as to achieve better collision, atomization and mixing of the first propellant and the second propellant after being ejected from the injector.
  • the angle ⁇ can be 90°.
  • this is just an example and is not specifically limited.
  • the liquid outlet direction of the third flow channel 12 is parallel to the axis of the center tube 2
  • the liquid outlet direction of the second flow channel 22 is perpendicular to the axis of the center tube 2.
  • an annular gap is formed between the outer wall of the pintle 3 near one end of the combustion chamber and the inner wall of the shell 1, and the annular gap is the third flow channel 12.
  • the third flow channel 12 for the first propellant to flow can be formed without additional processing of the inner wall of the shell 1 and the outer wall of the pintle 3, so that the overall structure of the variable thrust pintle injector provided in the embodiment of the present application is relatively simple, and the production cycle of the variable thrust pintle injector provided in the embodiment of the present application is shortened.
  • the inner wall of the shell 1 is conical, and the cross-section gradually decreases toward the end near the combustion chamber.
  • variable thrust pintle injector provided in the embodiment of the present application adjusts the flow rate of the actuating fluid, and finally The relative position of the pintle 3 and the central tube 2 in the axial direction is changed, so that the area blocked by the pintle 3 at the outlet end of the first flow channel 11 and the outlet end of the second flow channel 22 can be adjusted to change, and the flow rate of the first propellant and the second propellant can be further adjusted, so as to adjust the thrust of the injector.
  • valves are provided at the inlet end of the fourth flow channel 14 and the liquid outlet 15 to control the circulation of the actuating fluid.
  • a receiving chamber 17 is also provided on the central tube 2, and the receiving chamber 17 is provided along the circumference of the central tube 2.
  • the receiving chamber 17 is connected to the fourth flow channel 14 and the liquid outlet 15, and the actuating fluid flows into the receiving chamber 17 through the fourth flow channel 14.
  • the actuating fluid can be the first propellant, and of course, other liquids can also be used.
  • the actuating fluid can be kerosene or water.
  • the actuating fluid flows into the third flow channel 12, that is, it is required to ensure that the outer wall of the pintle 3 and the inner wall of the housing 1 and the inner wall of the pintle 3 and the outer wall of the central tube 2 are sealed, on the one hand, to prevent the first propellant from flowing into the receiving chamber 17, and on the other hand, to prevent the actuating fluid from flowing into the third flow channel 12.
  • the force of the actuating fluid on the pintle 3 can be reduced accordingly, which can be achieved by reducing the flow rate of the actuating fluid.
  • the valve at the position of the liquid outlet 15 can be opened, and the valve at the inlet end of the fourth flow channel 14 can be closed at the same time, so that the actuating fluid can flow out of the accommodating chamber 17.
  • the pressure of the pintle 3 from the actuating fluid moving toward the side close to the combustion chamber is reduced, and at the same time, the pintle 3 is still subjected to the force of the first propellant moving away from the combustion chamber.
  • the pintle 3 Since the pintle 3 is subjected to the force of the first propellant moving away from the combustion chamber, when the force of the first propellant moving away from the combustion chamber is greater than the pressure of the actuating fluid moving toward the combustion chamber, the pintle 3 moves along the axis of the central tube 2 in the direction away from the combustion chamber, the flow cross-section of the third flow channel 12 increases, the area of the outlet end of the first flow channel 11 and the outlet end of the second flow channel 22 blocked by the pintle 3 gradually decreases, the flow rate of the first propellant and the second propellant increases, and the thrust generated by the injector is further increased.
  • valve at the liquid outlet 15 can be closed and the valve at the inlet end of the fourth flow channel 14 can be opened to increase the amount of the actuating fluid in the accommodating chamber 17.
  • the pressure on the pintle 3 from the actuating fluid moving toward the combustion chamber increases.
  • the pintle 3 is still subjected to the force of the first propellant moving away from the combustion chamber.
  • the pintle 3 When the force on the pintle 3 from the actuating fluid moving toward the combustion chamber is greater than the force on the pintle 3 from the first propellant moving away from the combustion chamber, the pintle 3 will be When a force is applied at one end, the pintle 3 moves toward the combustion chamber, the flow cross-section of the third flow channel 12 decreases, the area blocked by the pintle 3 at the outlet end of the first flow channel 11 and the outlet end of the second flow channel 22 gradually increases, the flow rates of the first propellant and the second propellant decrease, and the thrust is further reduced.
  • the valve at the position of the liquid outlet 15 and the valve at the inlet end of the fourth flow channel 14 are closed at the same time, the force acting on the pintle 3 from the actuating fluid toward the end close to the combustion chamber remains unchanged, the area of the outlet end of the first flow channel 11 and the area of the outlet end of the second flow channel 22 blocked by the pintle 3 remain unchanged, and the flow rate of the first propellant remains unchanged, so that the force acting on the pintle 3 from the first propellant toward the end away from the combustion chamber remains unchanged, and the force acting on the pintle 3 from the actuating fluid toward the end close to the combustion chamber is equal to the force acting on the pintle 3 from the first propellant toward the end away from the combustion chamber, so that the position of the pintle 3 on the axis of the central tube 2 remains unchanged, so that the thrust is stabilized at the required fixed value.
  • reusable launch vehicle engines generally use regenerative cooling bodies. After the engine is shut down, a large amount of fuel remains in the cavity. The residual fuel is not stable during the emptying process, and it is difficult to form a good atomization state. The flame formed by the combustion of the propellant is close to the injector surface, which can easily cause injector surface ablation.
  • a first limit surface 16 that matches the outer wall of the pintle 3 is provided on the inner wall of the housing 1, and the first limit surface 16 is located on the side of the outlet of the first flow channel 11 close to the combustion chamber.
  • the outlet end of the first flow channel 11 When the outer wall of the pintle 3 is in contact with the first limit surface 16, the outlet end of the first flow channel 11 is completely blocked, and the outlet of the first flow channel is closed. In this way, the supply and circulation of the first propellant can be cut off, and the thrust of the injector is zero. The risk of injector surface ablation after the engine is shut down is avoided, and the injector can be reused to extend the service life of the injector. After shutdown, the pintle closes the outlet of the first flow channel, cuts off the supply of the first propellant, eliminates the unstable and uncontrolled combustion state after shutdown, and greatly increases the number of reuses and working life of the injector. Of course, when the outer wall of the pintle 3 is in contact with the first limiting surface 16, the outlet end of the second flow channel 22 can also be completely blocked at the same time to cut off the supply of the second propellant.
  • the center tube 2 has a second limiting surface 23, which is located on the side of the pintle 3 away from the combustion chamber, and the first limiting surface 16 and the second limiting surface 23 are used to limit the axial movement distance of the pintle 3.
  • the first limiting surface 16 and the second limiting surface 23 limit the lowest and highest positions of the pintle 3, so that the pintle 3 will not completely separate from the shell 1 and the center tube 2, so that the pintle 3 is restricted between the shell 1 and the center tube 2, ensuring the stable operation of the injector.
  • the second limiting surface 23 may be a limiting step on the central tube 2 , that is, a boss structure as shown in FIG. 1 , and the embodiment of the present application does not make any specific limitation on this.
  • variable thrust pintle injector provided in the embodiment of the present application further includes a connecting member 4, which is arranged between the central tube 2 and the housing 1, and the connecting member 4 is movably arranged on the pintle 3, and the connecting member 4 is located at the end of the pintle 3 away from the combustion chamber.
  • the connecting member 4 can be connected to the pintle 3 by a threaded connection, an external thread is provided on the outer wall of the connecting member 4, and an internal thread matching the external thread of the connecting member 4 is provided at the connection position with the connecting member 4 on the inner wall of the pintle 3, so that the connecting member 4 is fixedly connected to the pintle 3.
  • variable thrust pintle injector further includes an adjusting gasket 5, which is disposed between the central tube 2 and the shell 1.
  • the adjusting gasket 5 is located at the top of the shell 1 and below the connecting portion of the central tube 2.
  • the axis of the adjusting gasket 5 is parallel to the axis of the central tube 2, and the adjusting gasket 5 is used to adjust the distance between the first limiting surface 16 and the second limiting surface 23, so that when the outer wall of the pintle 3 is in limiting contact with the first limiting surface 16, the outlet end of the second flow channel 22 can be completely or partially blocked by the pintle 3, so that when the pintle 3 moves in a direction away from the combustion chamber, the area of the outlet end of the second flow channel 22 blocked by the pintle 3 can be gradually reduced.
  • variable thrust pintle injector provided in the embodiments of the present application further includes a first sealing ring 6, which is sleeved between the outer wall of the central tube 2 and the inner wall of the pintle 3.
  • the first sealing ring 6 is located at one end of the connecting member 4 close to the combustion chamber, and the first sealing ring 6 moves synchronously with the pintle 3.
  • the first sealing ring 6 can prevent the actuating fluid from flowing out of the accommodating chamber 17 along the outer wall of the central tube 2 and the inner wall of the pintle 3, so as not to affect the performance of the injector.
  • variable thrust pintle injector further includes a second sealing ring 7, which is sleeved between the inner wall of the housing 1 and the outer wall of the pintle 3, and the second sealing ring 7 is located at the end of the pintle 3 away from the combustion chamber, and the second sealing ring 7 moves synchronously with the pintle 3.
  • the second sealing ring 7 can prevent the actuating fluid from flowing out of the accommodating chamber 17 along the inner wall of the housing 1 and the outer wall of the pintle 3, and prevent the first propellant from flowing along the inner wall of the housing 1 and the outer wall of the pintle 3 in a direction away from the combustion chamber, so as not to affect the performance of the injector.
  • variable thrust pintle injector further comprises a third sealing ring 8, which is sleeved between the outer wall of the central tube 2 and the inner wall of the housing 1, and the third sealing ring 8 is located within the second limit surface 23.
  • the third sealing ring 8 can prevent the actuating fluid from flowing out along the outer wall of the central tube 2 and the inner wall of the housing 1, so as not to affect the injector. performance.
  • the multiple second flow channels 22 are evenly arranged along the circumference of the center tube 2, so that after the second propellant is ejected from the second flow channel 22, it is evenly arranged on the outer periphery of the center tube 2 close to one end of the combustion chamber, so as to ensure the uniformity of the distribution of the second propellant in the combustion chamber, increase the utilization rate of the second propellant, improve the combustion performance of the engine, and further increase the thrust of the engine thrust chamber when the amount of the second propellant is the same.

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  • Engineering & Computer Science (AREA)
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  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Fuel-Injection Apparatus (AREA)

Abstract

本申请公开公开一种变推力针栓式喷注器，涉及喷注器技术领域，以规避机械作动调节对工作环境条件要求高，导致喷注器结构复杂且工作可靠性低的问题。变推力针栓式喷注器包括壳体、中心筒和针栓。壳体具有贯通的第一腔体，壳体上开设有用于通入第一推进剂的第一流道，第一流道与第一腔体连通。中心筒套设于第一腔体内，中心筒具有用于通入第二推进剂的第二腔体，中心筒的靠近燃烧室的一端开设有第二流道。针栓设置于中心筒与壳体之间，壳体的内壁与针栓的外壁之间形成第三流道。当针栓向远离燃烧室的方向运动时，第一流道的出口端和第二流道的出口端被针栓遮挡的面积逐渐减小。中心筒上还设置有用于向针栓的上方注入作动液的第四流道。

Description

一种变推力针栓式喷注器
本申请要求于2022年11月03日提交中国专利局、申请号为202211365423.4、申请名称为“一种变推力针栓式喷注器”的中国专利优先权，其全部内容通过引用结合在本申请中。
技术领域
本申请涉及喷注器技术领域，尤其涉及一种变推力针栓式喷注器。
背景技术
液体火箭发动机是航天飞行器的核心部件，是使用液态化学物质作为能源和工质的化学火箭推进系统，发动机的推力室是将液体推进剂的化学能转变成推力的重要组件。推力室由喷注器、燃烧室、喷管组成，液体推进剂经喷注器进入燃烧室，经雾化、混合和燃烧等过程生成燃烧产物，从喷管高速喷出产生推力。
变推力液体火箭发动机的推力控制是通过控制推进剂流量来实现的。为达到最佳的喷注效果，在选择变推力液体火箭发动机的喷注器时，针栓式喷注器不仅喷注面积可调，还具有结构简单、工作可靠性高、成本低等优点。
变推力针栓式喷注器运动件的推力调节通常采用机械作动调节，例如电机驱动调节。但机械作动对工作环境条件要求高，喷注器工作环境温度较低时，需要对机械作动做好隔绝低温处理，使得喷注器结构比较复杂且工作可靠性低。
发明内容
有鉴于此，本申请公开了变推力针栓式喷注器，采用作动液实现推力调节，以规避机械作动调节对工作环境条件要求高，导致喷注器结构复杂且工作可靠性低的问题。
本申请提供一种变推力针栓式喷注器，包括壳体、中心筒和针栓。其中，壳体具有贯通的第一腔体，壳体上开设有用于通入第一推进剂的第一流道，第一流道与第一腔体连通。中心筒套设于第一腔体内，中心筒与壳体紧固连 接。中心筒具有用于通入第二推进剂的第二腔体，中心筒的靠近燃烧室的一端开设有第二流道，第二流道连通第二腔体和燃烧室。针栓设置于中心筒与壳体之间，壳体的内壁与针栓的外壁之间形成第三流道，第三流道连通第一流道和燃烧室。第二流道的出液方向与第三流道的出液方向之间具有夹角α，0°＜α＜180°。针栓可沿中心筒的轴线延伸方向运动，针栓能够遮挡第一流道的出口端和第二流道的出口端，当针栓向远离燃烧室的方向运动时，第一流道的出口端和第二流道的出口端被针栓遮挡的面积逐渐减小。中心筒上还设置有用于向针栓的上方注入作动液的第四流道。中心筒上还设置有出液口，用于输出作动液。
采用上述技术方案的情况下，本申请提供的变推力针栓式喷注器包括壳体、中心筒和针栓，壳体具有贯通的第一腔体，中心筒套设于第一腔体内，中心筒与壳体紧固连接，如此，能够将中心筒与壳体的相对位置固定，从而避免中心筒与壳体之间产生相对位移，影响组件装配的一致性。壳体上开设有用于通入第一推进剂的第一流道，第一流道与第一腔体连通。针栓设置于中心筒与壳体之间，壳体的内壁与针栓的外壁之间形成第三流道，第三流道连通第一流道和燃烧室，由此可见，第一推进剂可通过第一流道和第三流道输送至燃烧室内。中心筒具有用于通入第二推进剂的第二腔体，中心筒的靠近燃烧室的一端开设有第二流道，第二流道连通第二腔体和燃烧室，由此表明，第二推进剂可通过第二腔体和第二流道输送至燃烧室内。另外，第二流道的出液方向与第三流道的出液方向之间具有夹角α，0°＜α＜180°，综上可知，第一推进剂从第三流道喷出后会与从第二流道喷出的第二推进剂在燃烧室内发生碰撞，之后进一步雾化、混合，为充分燃烧提供条件。不仅如此，针栓可沿中心筒的轴线延伸方向运动，针栓能够遮挡第一流道的出口端和第二流道的出口端，当针栓向远离燃烧室的方向运动时，第一流道的出口端和第二流道的出口端被针栓遮挡的面积逐渐减小。基于此，当针栓沿中心筒的轴线延伸方向运动时，第一流道的出口端和第二流道的出口端被针栓遮挡的面积出现变化，从而可以调整第一推进剂和第二推进剂喷注入燃烧室内的流量，使第一推进剂与第二推进剂撞击、混合和燃烧的效率也会产生相应的改变，进而使得喷注器的推力得到调整。
另外，中心筒上还设置有用于向针栓的上方注入作动液的第四流道。具体实施时，作动液经第四流道流动至针栓的上方，并对针栓产生向靠近燃烧室一侧移动的压力，针栓在作动液的压力作用下向靠近燃烧室的一侧运动。第一流道远离第一腔体的一端向靠近燃烧室的一侧倾斜，当第一推进剂经过第一流道喷注在针栓的外壁上时，针栓受到第一推进剂的向远离燃烧室的一侧运动的作用力。通过调整作动液的流量，最终使得针栓与中心筒的轴向上的相对位置得到改变，从而可调节第一流道的出口端和第二流道的出口端被针栓遮挡的面积出现变化，进一步调整第一推进剂和第二推进剂的流量。综上可知，本申请提供的变推力针栓式喷注器采用作动液而非机械作动调节实现推力的调节，规避了机械作动调节对工作环境条件要求高，导致喷注器结构复杂且工作可靠性低的问题。
附图说明
为了更清楚地说明本申请实施例或现有技术中的技术方案，下面将对实施例或现有技术描述中所需要使用的附图进行说明：
图1为本申请实施例提供的变推力针栓式喷注器的剖面示意图；
图2为本申请实施例提供的变推力针栓式喷注器的局部示意图。
具体实施方式
可重复使用飞行器是航天运输技术领域的重要发展方向,是当前世界各航天大国均非常重视的一项技术。可重复使用的猎鹰9火箭通过一级重复使用大幅降低了发射成本，成为其市场竞争的独有优势，占据了美国绝大部分发射市场。运载火箭重复使用的关键在于回收，为了实现运载火箭回收需要火箭发动机具备一定的变推力能力。具备变推力能力的大推力液体火箭发动机是当前的研究热点，变推力喷注器及其重复使用技术制约运载火箭低成本，属于行业瓶颈技术。
针栓喷注器为单喷注单元，结构简单、检测性好，易于实现重复使用；针栓喷注器易于实现喷注调节，便于变推力功能的实现。从技术特点看，针栓喷注器在可重复使用液体火箭发动机领域具有独特的优势。
变推力针栓式喷注器运动件的推力调节通常采用机械作动调节，例如可以采用弹簧-液压作动调节或电机作动调节。但是，弹簧-液压作动变推力针栓 式喷注器易出现喷注器与弹簧固有频率耦合的中频振荡问题，喷注器稳定性不好。并且，在大推力发动机上，弹簧受力大、运动位移大，弹簧极易出现结构破坏。电机作动变推力针栓式喷注器对工作环境条件要求高，对于液氧/煤油、液氧/甲烷等推进剂组合，由于液氧温度低，导致喷注器工作温度低，电机需要做好隔绝低温处理，喷注器结构比较复杂且工作可靠性低，并且大推力发动机需要电机提供的作动力非常大，电机结构质量重、需要的电流大，对运载火箭造成较重的负担。
本申请的核心是提供了一种变推力针栓式喷注器，包括壳体1、中心筒2和针栓3。其中，壳体1具有贯通的第一腔体，壳体1上开设有用于通入第一推进剂的第一流道11，第一流道11与第一腔体连通。中心筒2套设于第一腔体内，中心筒2与壳体1紧固连接。中心筒2具有用于通入第二推进剂的第二腔体21，中心筒2的靠近燃烧室的一端开设有第二流道22，第二流道22连通第二腔体21和燃烧室。针栓3设置于中心筒2与壳体1之间，壳体1的内壁与针栓3的外壁之间形成第三流道12，第三流道12连通第一流道11和燃烧室。第二流道22的出液方向与第三流道12的出液方向之间具有夹角α，0°＜α＜180°。针栓3可沿中心筒2的轴线延伸方向运动，针栓3能够遮挡第一流道11的出口端和第二流道22的出口端，当针栓3向远离燃烧室的方向运动时，第一流道11的出口端和第二流道22的出口端被针栓3遮挡的面积逐渐减小。中心筒2上还设置有用于向针栓3的上方注入作动液的第四流道14。中心筒2上还设置有出液口15，出液口15与容纳腔17连通，用于输出作动液。
采用上述技术方案的情况下，本申请实施例提供的变推力针栓式喷注器包括壳体1、中心筒2和针栓3，壳体1具有贯通的第一腔体，中心筒2套设于第一腔体内，中心筒2与壳体1紧固连接，如此，能够将中心筒2与壳体1的相对位置固定，从而避免中心筒2与壳体1之间产生相对位移，影响组件装配的一致性。壳体1上开设有用于通入第一推进剂的第一流道11，第一流道11与第一腔体连通。针栓3设置于中心筒2与壳体1之间，壳体1的内壁与针栓3的外壁之间形成第三流道12，第三流道12连通第一流道11和燃烧室，由此可见，第一推进剂可通过第一流道11和第三流道12输送至燃烧室 内。中心筒2具有用于通入第二推进剂的第二腔体21，中心筒2的靠近燃烧室的一端开设有第二流道22，第二流道22连通第二腔体21和燃烧室，由此表明，第二推进剂可通过第二腔体21和第二流道22输送至燃烧室内。另外，第二流道22的出液方向与第三流道12的出液方向之间具有夹角α，0°＜α＜180°，综上可知，第一推进剂从第三流道12喷出后会与从第二流道22喷出的第二推进剂在燃烧室内发生碰撞，之后进一步雾化、混合，为充分燃烧提供条件。不仅如此，针栓3可沿中心筒2的轴线延伸方向运动，针栓3能够遮挡第一流道11的出口端和第二流道22的出口端，当针栓3向远离燃烧室的方向运动时，第一流道11的出口端和第二流道22的出口端被针栓3遮挡的面积逐渐减小。基于此，当针栓3沿中心筒2的轴线延伸方向运动时，第一流道11的出口端和第二流道22的出口端被针栓3遮挡的面积出现变化，从而可以调整第一推进剂和第二推进剂的流量，使第一推进剂与第二推进剂撞击、混合和燃烧的效率也会产生相应的改变，进而使得喷注器的推力得到调整。
另外，中心筒2上还设置有用于向针栓3的上方注入作动液的第四流道14。具体实施时，作动液经第四流道14流动至针栓的上方，并对针栓3产生向靠近燃烧室一侧移动的压力，针栓3在作动液的压力作用下向靠近燃烧室的一侧运动。第一流道11远离第一腔体的一端向靠近燃烧室的一侧倾斜，当第一推进剂经过第一流道11喷注在针栓3的外壁上时，针栓3受到第一推进剂的向远离燃烧室的一侧运动的作用力。通过调整作动液的流量，使得针栓3受到作动液的作用力发生变化，应理解的是，与此同时，针栓3仍然受到第一推进剂的向远离燃烧室方向的作用力。当针栓3受到作动液的作用力发生变化时，针栓3沿中心筒的轴线方向运动，如此使得针栓3与中心筒2的轴向上的相对位置进一步得到改变，最终可调节第一流道11的出口端和第二流道22的出口端被针栓3遮挡的面积出现变化，进一步调整第一推进剂和第二推进剂的流量。综上可知，本申请实施例提供的变推力针栓式喷注器采用作动液而非机械作动调节实现推力的调节，规避了机械作动调节对工作环境条件要求高，导致喷注器结构复杂且工作可靠性低的问题。
第一流道11的数量可以为多个，且多个第一流道11沿壳体1的周向均 匀布设，不仅使针栓3所受到的来自于第一推进剂的作用力的均匀性得到提升，而且能够提升第一推进剂喷注在燃烧室内的均匀性，增大第一推进剂的利用率，提高发动机的燃烧性能。
具体实施时，壳体1可以通过螺栓9与中心筒2之间紧固连接，壳体1的轴线与中心筒2的轴线共线。当然，壳体1也可以通过焊接方式与中心筒2紧固连接，此处不作具体限定，根据实际情况进行设置。中心筒2包括中心筒本体和连接部，连接部位于中心筒本体的外周，连接部的外周尺寸大于中心筒本体的外周尺寸，且连接部位于壳体1的上方，连接部与壳体1的顶部紧固连接。螺栓9的轴线平行于中心筒2的轴线。螺栓9的数量为多个，且多个螺栓9沿中心筒2的周向均匀分布，以增强壳体1与中心筒2连接的稳固性。
需要说明的是，第一推进剂和第二推进剂为燃料或氧化剂的其中一种，当第一推进剂为燃料时，则第二推进剂为氧化剂；当第一推进剂为氧化剂时，则第二推进剂为燃料。第一推进剂设置为燃料或氧化剂，根据实际情况进行设置，此处不作具体限定。第二流道22的出液方向与第三流道12的出液方向之间的夹角α的数值根据实际情况进行设置，以能实现第一推进剂和第二推进剂从喷注器喷出后能够较好的碰撞、雾化和混合为主。在本申请实施例提供的变推力针栓式喷注器中，夹角α可以为90°，当然此处只是举例说明，不作具体限定。在这种情况下，如图1所示，第三流道12的出液方向平行于中心筒2的轴线，第二流道22的出液方向垂直于中心筒2的轴线。
在一种选方式中，针栓3靠近燃烧室一端的外壁与壳体1的内壁之间形成环形缝隙，环形缝隙为第三流道12。如此，不需对壳体1的内壁与针栓3的外壁进行额外加工，即可形成供第一推进剂流通的第三流道12，使得本申请实施例提供的变推力针栓式喷注器的整体结构较为简单，缩短了本申请实施例提供的变推力针栓式喷注器的生产周期。可以理解的是，从图1可知，环形缝隙位置处，壳体1的内壁为锥形，且向靠近燃烧室一端的截面逐渐减小。当针栓3向远离燃烧室的方向运动时，针栓3靠近燃烧室一端的外壁与壳体1的内壁之间的距离增大，从而可进一步使第一推进剂的流量增大。
本申请实施例提供的变推力针栓式喷注器通过调整作动液的流量，最终 使得针栓3与中心筒2的轴向上的相对位置得到改变，从而可调节第一流道11的出口端和第二流道22的出口端被针栓3遮挡的面积出现变化，进一步调整第一推进剂和第二推进剂的流量，从而实现喷注器的推力大小的调节。实际情况下，在第四流道14的入口端以及出液口15位置处设置有阀门，以控制作动液的流通。
参见图1和图2所示，在中心筒2上还设置有容纳腔17，容纳腔17沿中心筒2的周向设置。容纳腔17与第四流道14以及出液口15均连通，作动液通过第四流道14流进容纳腔17内。需要说明的是，作动液可以采用第一推进剂，当然，也可以采用其它液体，示例性地，作动液可以为煤油或者水等。在本申请提供的实施例中，要求规避作动液流进第三流道12的现象，即要求保证针栓3的外壁与壳体1的内壁之间以及针栓3的内壁与中心筒2的外壁之间密封，一方面避免第一推进剂流进容纳腔17，另一方面避免作动液流进第三流道12。
具体实施时，当需要增大推力时，可以相应的减小作动液作用在针栓3上的作用力，可以通过降低作动液的流量实现。示例性地，可以打开出液口15位置处的阀门，同时关闭第四流道14的入口端的阀门，以便于作动液从容纳腔17内流出。此种情况下，针栓3受到的来自于作动液的向靠近燃烧室一侧移动的压力减小，与此同时，针栓3仍然受到第一推进剂的向远离燃烧室一端的作用力。由于针栓3受到第一推进剂的向远离燃烧室一端的作用力，当针栓3受到的第一推进剂的向远离燃烧室一端的作用力大于针栓3受到的来自于作动液的向靠近燃烧室一侧移动的压力时，使得针栓3沿着中心筒2的轴线向远离燃烧室的方向运动，第三流道12的流通截面增大，第一流道11的出口端和第二流道22的出口端被针栓3遮挡的面积逐渐减小，第一推进剂和第二推进剂的流量增大，进一步使得喷注器产生的推力增大。
当需要减小推力时，可以关闭出液口15位置处的阀门，打开第四流道14的入口端的阀门，以使得容纳腔17内的作动液的量增大，此种情况下，针栓3受到的来自于作动液的向靠近燃烧室一侧移动的压力增大，与此同时，针栓3仍然受到第一推进剂的向远离燃烧室一端的作用力。当针栓3受到来自作动液的向靠近燃烧室一端的作用力大于针栓3受到第一推进剂的向远离燃烧室 一端的作用力时，针栓3向靠近燃烧室的方向运动，第三流道12的流通截面减小，第一流道11的出口端和第二流道22的出口端被针栓3遮挡的面积逐渐增大，第一推进剂和第二推进剂的流量减小，进一步使得推力减小。
当需要推力保持在一定值时，同时关闭出液口15位置处的阀门以及第四流道14的入口端的阀门，针栓3所受到的来自作动液的向靠近燃烧室一端的作用力保持不变，针栓3所遮挡的第一流道11的出口端的面积和第二流道22的出口端的面积保持不变，第一推进剂的流量不变，从而使得针栓3受到的来自第一推进剂的向远离燃烧室一端的作用力保持不变，并且针栓3受到的来自作动液的向靠近燃烧室一端的作用力等于针栓3受到的来自第一推进剂的向远离燃烧室一端的作用力，使得针栓3在中心筒2的轴线上的位置保持不变，从而使得推力稳定在需求的固定值。
现有技术中，可重复使用运载火箭发动机一般采用再生冷却身部，发动机关机后容腔内残存了大量的燃料，残存燃料排空过程流动不稳定，难以形成良好的雾化状态，推进剂燃烧形成的火焰靠近喷注器面，极易造成喷注器面烧蚀。鉴于此，在一种可能的实现方式中，如图1所示，壳体1的内壁上设置与针栓3的外壁相配合的第一限位面16，第一限位面16位于第一流道11的出口靠近燃烧室的一侧。当针栓3的外壁与第一限位面16限位接触时，第一流道11的出口端被全部遮挡，第一流道出口关闭。如此，可以切断第一推进剂的供应流通，喷注器的推力为零。避免了发动机关机后喷注器面烧蚀的风险，该喷注器可以重复使用，延长喷注器的使用寿命。关机后针栓将第一流道出口关闭，切断了第一推进剂的供应，消除了关机后不稳定、不受控的燃烧状态，喷注器的重复使用次数及工作寿命大幅提高。当然，当针栓3的外壁与第一限位面16限位接触时，也可以同时将第二流道22的出口端全部遮挡，切断第二推进剂的供应。
在一些示例中，如图1所示，中心筒2具有第二限位面23，第二限位面23位于针栓3远离燃烧室的一侧，第一限位面16与第二限位面23用于限定针栓3的轴向运动距离。第一限位面16以及第二限位面23限制了针栓3运动的最低位置以及最高位置，使得针栓3不会完全脱离壳体1与中心筒2，使针栓3被限制在壳体1与中心筒2之间，保证喷注器稳定工作。在实际中， 第二限位面23可以为中心筒2上的限位台阶，即如图1所示的凸台结构，本申请实施例对此不做具体限定。
在一种可选方式中，本申请实施例提供的变推力针栓式喷注器还包括连接件4，设置于中心筒2与壳体1之间，连接件4随动地设置于针栓3，连接件4位于针栓3远离燃烧室的一端。连接件4可以通过螺纹连接方式与针栓3连接，在连接件4的外壁上开设外螺纹，在针栓3的内壁上的与连接件4的连接位置处开设与连接件4的外螺纹相配合的内螺纹，从而使得连接件4与针栓3固定连接。
示例性地，如图1所示，变推力针栓式喷注器还包括调整垫片5，设置于中心筒2与壳体1之间。调整垫片5位于壳体1的顶部，且位于中心筒2的连接部的下方。调整垫片5的轴线与中心筒2的轴线平行，调整垫片5用于调节第一限位面16与第二限位面23之间的距离，使得当针栓3的外壁与第一限位面16限位接触时，第二流道22的出口端能够被被针栓3全部或部分遮挡，以便于在针栓3向远离燃烧室的方向运动时，能够实现第二流道22的出口端被针栓3所遮挡的面积逐渐减小的现象。
在一些实施例中，本申请实施例提供的变推力针栓式喷注器还包括第一密封圈6，套设于中心筒2的外壁与针栓3的内壁之间。第一密封圈6位于连接件4靠近燃烧室的一端，第一密封圈6与针栓3同步运动。第一密封圈6可以避免作动液沿中心筒2的外壁与针栓3的内壁之间从容纳腔17内流出，以免影响喷注器的性能。
在另一种示例中，变推力针栓式喷注器还包括第二密封圈7，套设于壳体1的内壁与针栓3的外壁之间，第二密封圈7位于针栓3远离燃烧室的一端，第二密封圈7与针栓3同步运动。第二密封圈7可以避免作动液沿壳体1的内壁与针栓3的外壁之间从容纳腔17内流出，同时避免第一推进剂沿壳体1的内壁与针栓3的外壁之间向远离燃烧室一端的方向流动，以免影响喷注器的性能。
再者，变推力针栓式喷注器还包括第三密封圈8，套设于中心筒2的外壁与壳体1的内壁之间，第三密封圈8位于第二限位面23内。第三密封圈8可以避免作动液沿中心筒2的外壁与壳体1的内壁之间流出，以免影响喷注器 的性能。
作为一种可能的实现方式，第二流道22的数量为多个，多个第二流道22沿中心筒2的周向均匀布设，以使得第二推进剂从第二流道22喷出后，均匀的布设于中心筒2靠近燃烧室一端的外周，以保证第二推进剂在燃烧室内分布的均匀性，增大第二推进剂的利用率，提高发动机的燃烧性能，在第二推进剂的用量相同的情况下，进一步提高发动机推力室的推力。
尽管在此结合各实施例对本申请进行了描述，然而，在实施所要求保护的本申请过程中，本领域技术人员通过查看附图、公开内容、以及所附权利要求书，可理解并实现公开实施例的其他变化。在权利要求中，“包括”
(comprising)一词不排除其他组成部分或步骤，“一”或“一个”不排除多个的情况。单个处理器或其他单元可以实现权利要求中列举的若干项功能。相互不同的从属权利要求中记载了某些措施，但这并不表示这些措施不能组合起来产生良好的效果。
尽管结合具体特征及其实施例对本申请进行了描述，显而易见的，在不脱离本申请的精神和范围的情况下，可对其进行各种修改和组合。相应地，本说明书和附图仅仅是所附权利要求所界定的本申请的示例性说明，且视为已覆盖本申请范围内的任意和所有修改、变化、组合或等同物。显然，本领域的技术人员可以对本申请进行各种改动和变型而不脱离本申请的精神和范围。这样，倘若本申请的这些修改和变型属于本申请权利要求及其等同技术的范围之内，则本申请也意图包括这些改动和变型在内。

Claims (10)

  1. 一种变推力针栓式喷注器，其特征在于，包括：
    壳体，具有贯通的第一腔体，所述壳体上开设有用于通入第一推进剂的第一流道，所述第一流道与所述第一腔体连通，且所述第一流道远离所述第一腔体的一端向靠近燃烧室的一侧倾斜；
    中心筒，套设于所述第一腔体内，所述中心筒与所述壳体紧固连接；所述中心筒具有用于通入第二推进剂的第二腔体，所述中心筒的靠近所述燃烧室的一端开设有第二流道，所述第二流道连通所述第二腔体和所述燃烧室；
    针栓，设置于所述中心筒与所述壳体之间；所述壳体的内壁与所述针栓的外壁之间形成第三流道，所述第三流道连通所述第一流道和所述燃烧室；所述第二流道的出液方向与所述第三流道的出液方向之间具有夹角α，0°＜α＜180°；所述针栓可沿所述中心筒的轴线延伸方向运动；所述针栓能够遮挡所述第一流道的出口端和所述第二流道的出口端；当所述针栓向远离所述燃烧室的方向运动时，所述第一流道的出口端和所述第二流道的出口端被所述针栓遮挡的面积逐渐减小；所述中心筒上还设置有用于向所述针栓的上方注入作动液的第四流道，所述中心筒上还设置有出液口，用于输出所述作动液。
  2. 根据权利要求1所述的变推力针栓式喷注器，其特征在于，所述壳体的内壁上设置有与所述针栓的外壁相配合的第一限位面，所述第一限位面位于所述第一流道的出口靠近所述燃烧室的一侧；当所述针栓的外壁与所述第一限位面限位接触时，所述第一流道的出口端被全部遮挡。
  3. 根据权利要求2所述的变推力针栓式喷注器，其特征在于，所述中心筒具有第二限位面，所述第二限位面位于所述针栓远离所述燃烧室的一侧；所述第一限位面与所述第二限位面用于限定所述针栓的轴向运动距离。
  4. 根据权利要求1所述的变推力针栓式喷注器，其特征在于，还包括连接件，设置于所述中心筒与所述壳体之间；所述连接件随动地设置于所述针栓。
  5. 根据权利要求2所述的变推力针栓式喷注器，其特征在于，还包括调整垫片，设置于所述中心筒与所述壳体之间；所述调整垫片的轴线与所述中心筒的轴线平行；所述调整垫片用于使得当所述针栓的外壁与所述第一限位面限位接触时，所述第二流道的出口端能够被所述针栓遮挡。
  6. 根据权利要求4所述的变推力针栓式喷注器，其特征在于，还包括第 一密封圈，套设于所述中心筒的外壁与所述针栓的内壁之间；所述第一密封圈位于所述连接件靠近所述燃烧室的一端，所述第一密封圈与所述针栓同步运动。
  7. 根据权利要求1所述的变推力针栓式喷注器，其特征在于，还包括第二密封圈，套设于所述壳体的内壁与所述针栓的外壁之间，所述第二密封圈位于所述针栓远离所述燃烧室的一端，所述第二密封圈与所述针栓同步运动。
  8. 根据权利要求1所述的变推力针栓式喷注器，其特征在于，还包括第三密封圈，套设于所述中心筒的外壁与所述壳体的内壁之间。
  9. 根据权利要求1所述的变推力针栓式喷注器，其特征在于，所述第二流道的数量为多个，多个所述第二流道沿所述中心筒的周向均匀布设。
  10. 根据权利要求1所述的变推力针栓式喷注器，其特征在于，所述针栓靠近所述燃烧室一端的外壁与所述壳体的内壁之间形成环形缝隙，所述环形缝隙为所述第三流道。
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