CN112797184A - A kind of pneumatic control valve mechanism for liquid rocket engine and rocket engine - Google Patents
A kind of pneumatic control valve mechanism for liquid rocket engine and rocket engine Download PDFInfo
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- CN112797184A CN112797184A CN202110003246.4A CN202110003246A CN112797184A CN 112797184 A CN112797184 A CN 112797184A CN 202110003246 A CN202110003246 A CN 202110003246A CN 112797184 A CN112797184 A CN 112797184A
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- 239000007788 liquid Substances 0.000 title claims abstract description 65
- 230000007246 mechanism Effects 0.000 title claims abstract description 22
- 238000007789 sealing Methods 0.000 claims abstract description 39
- 230000007704 transition Effects 0.000 claims description 4
- 239000000446 fuel Substances 0.000 abstract description 7
- 238000013461 design Methods 0.000 description 3
- 238000010586 diagram Methods 0.000 description 3
- 238000006073 displacement reaction Methods 0.000 description 3
- 230000000694 effects Effects 0.000 description 3
- 238000007664 blowing Methods 0.000 description 2
- 238000000034 method Methods 0.000 description 2
- 238000012986 modification Methods 0.000 description 2
- 230000004048 modification Effects 0.000 description 2
- 230000008569 process Effects 0.000 description 2
- 239000003380 propellant Substances 0.000 description 2
- 235000015842 Hesperis Nutrition 0.000 description 1
- 235000012633 Iberis amara Nutrition 0.000 description 1
- 230000006835 compression Effects 0.000 description 1
- 238000007906 compression Methods 0.000 description 1
- 230000007547 defect Effects 0.000 description 1
- 238000011161 development Methods 0.000 description 1
- 238000004146 energy storage Methods 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 238000002474 experimental method Methods 0.000 description 1
- 230000006872 improvement Effects 0.000 description 1
- 230000000149 penetrating effect Effects 0.000 description 1
- 230000002035 prolonged effect Effects 0.000 description 1
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- XLYOFNOQVPJJNP-UHFFFAOYSA-N water Chemical compound O XLYOFNOQVPJJNP-UHFFFAOYSA-N 0.000 description 1
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
- F16K—VALVES; TAPS; COCKS; ACTUATING-FLOATS; DEVICES FOR VENTING OR AERATING
- F16K11/00—Multiple-way valves, e.g. mixing valves; Pipe fittings incorporating such valves
- F16K11/02—Multiple-way valves, e.g. mixing valves; Pipe fittings incorporating such valves with all movable sealing faces moving as one unit
- F16K11/04—Multiple-way valves, e.g. mixing valves; Pipe fittings incorporating such valves with all movable sealing faces moving as one unit comprising only lift valves
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
- F16K—VALVES; TAPS; COCKS; ACTUATING-FLOATS; DEVICES FOR VENTING OR AERATING
- F16K27/00—Construction of housing; Use of materials therefor
- F16K27/02—Construction of housing; Use of materials therefor of lift valves
- F16K27/0254—Construction of housing; Use of materials therefor of lift valves with conical shaped valve members
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
- F16K—VALVES; TAPS; COCKS; ACTUATING-FLOATS; DEVICES FOR VENTING OR AERATING
- F16K27/00—Construction of housing; Use of materials therefor
- F16K27/08—Guiding yokes for spindles; Means for closing housings; Dust caps, e.g. for tyre valves
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
- F16K—VALVES; TAPS; COCKS; ACTUATING-FLOATS; DEVICES FOR VENTING OR AERATING
- F16K31/00—Actuating devices; Operating means; Releasing devices
- F16K31/12—Actuating devices; Operating means; Releasing devices actuated by fluid
- F16K31/122—Actuating devices; Operating means; Releasing devices actuated by fluid the fluid acting on a piston
- F16K31/1221—Actuating devices; Operating means; Releasing devices actuated by fluid the fluid acting on a piston one side of the piston being spring-loaded
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- Engineering & Computer Science (AREA)
- General Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Lift Valve (AREA)
Abstract
本发明提供了一种液体火箭发动机用气动控制阀机构及火箭发动机。气动阀机构包含壳体、阀芯、阀盖、密封件和弹性件，壳体内侧具有供气体或者液体介质流通且贯穿其两端的第一通道和与第一通道延伸方向不同的第二通道，壳体还设置有用于控制阀芯运动的控制通道。密封件用以对阀芯与壳体内壁进行密封。所述阀芯的端部沿垂直所述阀芯的轴向方向相切所得截面的外形为圆形，且向所述阀盖侧方向上各圆形的直径逐渐变大。阀门工作时，所述控制通道通过控制气，推动所述阀芯向阀盖侧运动，以打开所述第一介质入口，实现液体介质从所述第一通道向所述第二通道的流通。与现有技术相比，可以减少流阻，提高燃料利用率，安全可靠。
The invention provides a pneumatic control valve mechanism for a liquid rocket engine and a rocket engine. The pneumatic valve mechanism includes a casing, a valve core, a valve cover, a sealing member and an elastic member. The inner side of the casing has a first channel for the circulation of gas or liquid medium and runs through both ends thereof and a second channel with a different extension direction from the first channel. The housing is also provided with a control channel for controlling the movement of the spool. The seal is used to seal the valve core and the inner wall of the housing. The outer shape of the cross section obtained by tangent to the end of the valve core in the direction perpendicular to the axial direction of the valve core is circular, and the diameter of each circle gradually increases toward the side of the valve cover. When the valve is in operation, the control channel pushes the valve core to move toward the valve cover side through the control gas, so as to open the first medium inlet and realize the flow of liquid medium from the first channel to the second channel. Compared with the prior art, the flow resistance can be reduced, the fuel utilization rate can be improved, and it is safe and reliable.
Description
Technical Field
The invention relates to the technical field of valves of power systems, in particular to a pneumatic control valve mechanism for a liquid rocket engine and the rocket engine.
Background
With the rapid development of the aerospace industry, all the technologies related to the rocket field also realize the rapid advance. The valve is an important part for realizing the starting and shutdown of the liquid rocket engine. In some liquid rockets of the research type, an energy storage medium adopted by a rocket engine is an ultralow-temperature propellant, the medium temperature region is usually about 20K to 120K, and the pressure is more than 10 MPa. The valve operating gas is usually a high-pressure gas having a pressure of about 20 MPa.
Pneumatic control valves are important components of liquid rocket engine propellant supply systems, and the valves can be opened and closed on command. When the valve is applied to a low-temperature liquid rocket engine, at the initial moment of inputting liquid fuel when the valve is opened, the liquid fuel can generate larger flow resistance in the process of entering the valve, so that the time for the fuel to enter a thrust chamber is prolonged, and the utilization rate of the fuel and the safe work of the engine are further influenced.
It is desirable to provide a safe and reliable control valve suitable for low temperature environment, which can reduce flow resistance and improve fuel utilization.
Disclosure of Invention
The invention aims to overcome the defects of the prior art and provides a pneumatic control valve mechanism for a liquid rocket engine and the rocket engine. The valve structure is suitable for low-temperature environment, can reduce flow resistance, improves the fuel utilization rate, is safe and reliable, and further improves the working reliability and efficiency of the liquid rocket engine.
The invention provides a pneumatic control valve mechanism for a liquid rocket engine, which comprises a shell, a valve core, a valve cover, a sealing element and an elastic element, wherein the inner side of the shell is provided with a first channel for gas or liquid medium to flow through and penetrate through two ends of the shell and a second channel which has a different extending direction from the first channel, and the shell is also provided with a control channel for controlling the movement of the valve core;
the valve core is positioned in the shell, the tail part of the valve core is connected with the valve cover positioned on one side of the shell through the elastic part, the end part of the valve core is used for being matched with the transitional inner wall of the first channel and the second channel so as to close the first medium inlet positioned on the first channel, and the sealing part is used for sealing the valve core and the inner wall of the shell;
the end part of the valve core is circular in shape on a cross section obtained by tangency along the axial direction perpendicular to the valve core, the diameter of each circle is gradually increased towards the valve cover side, when the valve works, the control channel pushes the valve core to move towards the valve cover side through control gas so as to open the first medium inlet, and liquid medium is communicated from the first channel to the second channel.
In the same embodiment, the end part of the valve core is a frustum structure, the included angle of the frustum structure is A, and the included angle is more than or equal to 100 degrees and less than or equal to 130 degrees.
In the same embodiment, the end of the valve core is tangent to form a first circle and a second circle at intervals along the axial direction perpendicular to the valve core, and the outer sides of the first circle and the second circle are connected through a circular arc surface.
In the same embodiment, the valve element is designed coaxially with the first channel.
In the same embodiment, the first passage includes a first inner passage and a second inner passage communicating with each other, and a transition point of the first inner passage and the second inner passage forms a first step for limiting movement of the spool to the first medium inlet side.
In the same embodiment, the valve element has an internal passage including a second step formed to the outside, and both ends of the elastic member abut against end surfaces of the second step and the valve cover near each other, respectively, in a compressed state, to apply an elastic force toward the medium inlet side to the valve element.
In the same embodiment, a through hole formed in the axial direction of the first channel is formed in the end portion of the valve element, a third channel different from the extending direction of the first channel is formed in the shell, and in an initial state of the valve, liquid media sequentially pass through the through hole and the internal channel and then are discharged from the third channel.
In the same embodiment, the third channel is located on a side of the housing proximate the end cap.
In the same embodiment, the sealing element is of a stopper ring structure, the sealing element comprises a first sealing ring and a second sealing ring which are arranged at intervals along the axial direction of the valve core, and annular grooves for fixing the first sealing ring and the second sealing ring are respectively arranged along the inner wall of the shell and the outer surface of the valve core in the circumferential direction.
Another aspect of the invention provides a rocket engine including a pneumatic control valve mechanism for a liquid rocket engine as described above.
The embodiment of the invention provides a pneumatic control valve mechanism for a liquid rocket engine and the rocket engine. The end part of the valve core is designed to be a frustum structure, the tangent shape along the axial direction perpendicular to the valve core is circular, the diameter of each circle tangent along the axial direction is gradually increased towards the side of the valve cover, the flow resistance of the liquid medium is reduced when the liquid medium passes through the valve, the liquid medium is guaranteed to rapidly enter the thrust chamber, and the utilization rate of the liquid medium is improved. The whole valve structure can be well suitable for low-temperature environment, is safe and reliable, and improves the working reliability and efficiency of the liquid rocket engine.
It is to be understood that both the foregoing general description and the following detailed description are exemplary and explanatory only and are not restrictive of the invention, as claimed.
Drawings
The accompanying drawings, which are incorporated in and constitute a part of this specification, illustrate exemplary embodiments of the invention and together with the description, serve to explain the principles of the invention.
FIG. 1 is a schematic diagram of a pneumatic control valve according to an embodiment of the present invention;
FIG. 2 is a schematic structural diagram of a housing according to an embodiment of the present invention;
FIG. 3 is a schematic structural diagram of a valve cartridge according to an embodiment of the present invention;
FIG. 4 is a schematic structural view of a valve cover in an embodiment of the present invention;
FIG. 5 is a schematic view of the structure of the end portion in the embodiment of the present invention;
FIG. 6 is a graph of the angle of the flow resistance and the included angle of the frustum structure in the embodiment of the invention.
Description of reference numerals:
1 case 2 valve core
3 valve cover 4 sealing element
5 elastic member 6 first passage
7 second channel 8 fourth channel
9 third channel 10 first inner channel
11 second inner passage 12 first step
13 first seal ring 14 second seal ring
15 guide post 16 guide rod
17 seat 18 control channel
19 conical surface 20 one-way valve
21 end of the tube
Detailed Description
Reference will now be made in detail to various exemplary embodiments of the invention, the detailed description should not be construed as limiting the invention but as a more detailed description of certain aspects, features and embodiments of the invention.
It will be apparent to those skilled in the art that various modifications and variations can be made in the specific embodiments of the present disclosure without departing from the scope or spirit of the disclosure. Other embodiments will be apparent to those skilled in the art from consideration of the specification. The specification and examples are exemplary only.
In a first embodiment of the invention, a pneumatic control valve mechanism for a liquid rocket engine is provided. As shown in fig. 1, the pneumatic control valve includes a housing 1, a valve core 2, a valve cover 3, a sealing member 4, and an elastic member 5. The inner side of the shell 1 is provided with a first channel 6 for gas or liquid medium to flow through and penetrating through two ends of the shell and a second channel 7 with the extending direction different from that of the first channel, and the shell 1 is also provided with a control channel 18 for controlling the movement of the valve core 2. The valve core 2 is positioned in the shell 1, the tail part of the valve core 2 is connected with the valve cover 3 positioned on one side of the shell 1 through an elastic part 5, and the end part of the valve core 2 is used for matching with the transition inner wall of the first channel 6 and the second channel 7 to close the first medium inlet positioned on the first channel 6. The sealing member 4 is used for sealing the valve core 2 and the inner wall of the shell 1. The end 21 of the valve element 2 has a circular cross section tangential to the valve element 2 in the axial direction, and the diameter of each circle is gradually increased toward the valve cover 3. When the valve works, the control channel 18 pushes the valve core 2 to move towards the valve cover 3 through control gas so as to open the first medium inlet, and the liquid medium is communicated from the first channel 6 to the second channel 7.
Specifically, according to the pneumatic control valve mechanism for the liquid rocket engine and the rocket engine provided by the embodiment of the invention, the end part 21 of the valve core 2 is designed to be circular along the tangential shape in the axial direction perpendicular to the valve core 2, and the diameters of the circles in the direction towards the side of the valve cover are gradually increased, so that the flow resistance of a liquid medium is reduced when the liquid medium passes through the valve in the working process of the pneumatic control valve, the liquid medium is ensured to rapidly enter the thrust chamber, and the utilization rate of the liquid medium is improved. The whole valve structure can be well suitable for low-temperature environment, is safe and reliable, and improves the working reliability and efficiency of the liquid rocket engine.
In the same embodiment, as shown in fig. 1, 5 and 6, the end of the valve core 2 is in a frustum structure, wherein the included angle of the frustum structure (the included angle between the conical generatrices corresponding to the frustum) is a. As shown in FIG. 6, the X-axis is the angle of A, the Y-axis is the flow resistance value, wherein the flow resistance value varies with the angle of A in a curve, and through a large number of experiments, when the angle of A is more than or equal to 100 degrees and less than or equal to 130 degrees, the flow resistance value becomes small. Compared with the existing valve core design, the flow resistance of the frustum structure of the valve core can be reduced by at least 30%, so that the liquid medium can be ensured to rapidly enter the thrust chamber, the utilization rate of the liquid medium is improved, the ignition time of the engine is shortened, and the rocket engine can be rapidly started conveniently.
It should be noted that, in order to reduce the impact of the liquid medium on the surface of the valve element 2, for example, a first circle and a second circle are formed at intervals and tangentially along the axial direction perpendicular to the valve element 2, and the outer sides of the first circle and the second circle are connected by an arc surface. The arc surface can make the sealed effect of line that forms between casing and the case better, avoids taking place liquid leakage, increases the area of contact of case 2 with the liquid medium simultaneously, has further increased 2 surface stress areas of case, reduces the impact of liquid medium to case 2, effectively protects case 2, increases case 2's life.
In addition, to facilitate the movement of the spool 2 within the first passage 6, for example, the spool 2 is designed coaxially with the first passage 6.
The present invention relates to a second embodiment which is a further improvement of the first embodiment, and as shown in fig. 1, 2, 3 and 4, a first passage 6 which is provided inside the casing 1 and through which a gas or liquid medium flows and which extends through both ends thereof, and a fourth passage 8 which is connected to the first passage. The fourth channel 8 is used for blowing off the air conveyed in the shell to the interior of the valve body and the engine assembly behind the valve, and preventing the phenomenon of icing caused by the inflow of external water vapor into the engine.
The valve core 2 is positioned in the shell 1, the tail part of the valve core 2 is connected with the valve cover 3 positioned on one side of the shell 1 through the elastic part 5, and the end part of the valve core 2 is matched with the transitional inner wall of the first channel 6 and the second channel 7 to close the first medium inlet positioned on the first channel 6. The sealing element 4 is used for sealing the valve core 2 and the inner wall of the shell 1, the inner side of the sealing element 4 is sleeved on the circumferential surface of the valve core 2, the inner side surface is tightly attached to the valve core 2, and the outer side surface is abutted to the inner wall of the shell 1, so that the liquid medium is prevented from leaking from a gap between the inner wall of the shell 1 and the valve core 2.
In the initial stage of the valve, the second channel 7 is communicated with the fourth channel 8, and one end of the fourth channel 8 can blow off the interior of the valve and downstream engine components of the valve by connecting a high-pressure pipeline. The liquid medium enters through the first channel 6 at a side away from the valve cover 3, and a part of the liquid medium can be discharged from the third channel 9 on the housing 1 through the inner side of the valve core 2 (precooling the interior of the engine). The valve core 2 is communicated with high-pressure gas through the pressurizing channel 18, so that the valve core 2 moves towards the direction close to the valve cover 3, the first channel 6 and the second channel 7 are communicated, and the liquid medium is communicated in the valve.
Specifically, according to the pneumatic control valve for the liquid rocket engine and the rocket engine provided by the embodiment of the invention, the valve core 2 and the inner wall of the shell 1 are sealed by the sealing element 4, the circumferential surface of the valve core 2 is sleeved by the inner side of the sealing element 4 and is tightly attached to the valve core 2, and the outer side surface of the sealing element 4 is abutted to the inner wall of the shell 1, so that the gap between the valve core 2 and the inner wall of the shell 1 is reduced, and further, the leakage of a liquid medium is reduced. In addition, when the valve works, under the condition that the second channel 7 is communicated with the fourth channel 8, the valve device can be blown off by connecting one end of the fourth channel 8 with a high-pressure pipeline. The fourth channel 8 is arranged, so that high-pressure gas can be conducted into the valve, and on one hand, air outside the second channel 7 can be prevented from flowing back into the second channel 7 in the precooling stage of the engine to cause icing on the inner side of the second channel 7, so that the valve and an engine assembly are blocked, and the safe use of the valve and the engine is influenced; on the other hand, the liquid medium in the valve can be blown off in time, and the reliability and the safety of the valve work are improved. The whole valve structure can be well suitable for low-temperature environment, is safe and reliable, and improves the working reliability and efficiency of the liquid rocket engine.
It should be noted that, as shown in fig. 1 and fig. 2, in the present embodiment, the first channel 6 includes a first inner channel 10 and a second inner channel 11, and the first inner channel 10 communicates with the second channel 7 and the fourth channel 8 to realize the medium circulation in the valve and the valve blow-off. In order to limit the displacement position of the valve element 2 in the second channel 7 to prevent the valve element 2 from slipping out of the second channel 7, for example, the transition portion between the first internal channel 6 and the second internal channel 7 forms a first step 12 for limiting the displacement of the valve element to the first medium inlet side, and when the valve element 2 travels to the limit position to the first medium inlet side in the second channel 7, a circumferential projection at one end of the valve element 2 is just in interference fit with the first step 12.
It should be noted that, in order to ensure that the elastic member 5 is fixed firmly, for example, the valve core 2 has an internal channel, the internal channel includes a second step formed toward the outside, and the two ends of the elastic member 5 are respectively abutted against the second step and the end surface of the valve cover 3 near each other, so that the elastic member 5 is fixed firmly, and the elastic member 5 can provide an elastic force toward the medium inlet direction to the valve core. For example, when the valve is closed, the elastic member 5 is in a compressed state, so that one end of the elastic member 5 is engaged with the valve cap 3 in a fixed state and the other end applies a power for providing the valve element 2 with a direction toward the medium inlet. In one embodiment, for example, the elastic member 5 may be a spring, a compression spring, or the like.
In the present embodiment, in order to reduce the gap between the housing 1 and the valve element 2 and to reduce the outflow of the medium from the gap, the seal 4 includes, for example, a first seal ring 13 and a second seal ring 14 provided at intervals in the axial direction of the valve element 2. For example, a first sealing ring 13 and a second sealing ring 14 are respectively located on both sides of the first step 12 in the second inner channel 7 to achieve sealing between the spool 2 and the housing 1. The valve mechanism of this application embodiment, through adopting twice sealed, guarantee that the sealed between case 2 and the casing 1 is inseparabler, improve sealed effect. It should be mentioned that, in order to facilitate the fixing of the first sealing ring 13 and the second sealing ring 14, for example, an annular groove may be provided on the inner wall of the housing or the outer circumference of the valve core, and the first sealing ring 13 and the second sealing ring 14 are respectively matched with the annular groove, so as to avoid the displacement of the sealing rings, effectively fix the sealing rings, and improve the sealing effect. In addition, the first seal ring 13 and the second seal ring 14 in the embodiment are both of a wiper ring structure.
As shown in fig. 1 and 4, in the present embodiment, in order to ensure rapid movement of the valve element 2 inside the housing 1 and reduce the occurrence of vibration of the valve element 2, for example, the valve cover 3 includes a guide post 15, a guide rod 16, and a base 17. The guide rod 16 is connected with the guide post 15 and the base 17 at two ends respectively, and the radial size of the outer side of the guide post 15 is matched with the inner channel body of the valve core 2 and is obviously larger than the radial size of the guide rod 16, so that the weight of the valve device is reduced. That is, the valve core 2 is internally provided with a channel body, and the guide post 15 and the guide rod 16 are fixedly connected to the valve cover 3 through the base 17, so that the motion of the valve core 2 is guided in the channel body, the valve core 2 is convenient to move, and the working reliability of the valve is improved.
It is to be noted that, in order to avoid the occurrence of the wobbling during the reciprocating movement of the valve body 2, for example, according to the positional relationship of the valve device in fig. 1, the surface of the guide post 15 below the axial direction of the first passage 6 abuts against the lower inner wall of the valve body 2 (the surface of the guide post 15 at the lower half portion away from the second passage 7 abuts against the lower inner wall of the valve body 2). For example, a through hole formed in the axial direction of the first channel 6 is formed in the end portion of the valve element 2, a third channel 9 different from the extending direction of the first channel 6 is formed in the housing 1, the surface of the guide post 15 above the axial direction of the first channel 6 is in clearance fit with the upper inner wall of the valve element 2 (the surface of the guide post 15 near the upper half portion of the second channel 7 is in clearance fit with the upper inner wall of the valve element 2), in an initial state of the valve, liquid media are discharged from the third channel 9 after sequentially passing through the through hole, the guide post 15 and the gap of the valve element 2, and the whole design can fully realize precooling treatment on the valve.
It should be noted that to increase the area of the valve that is pre-cooled, for example, the third passage 9 is located on the side of the housing 1 that is adjacent to the end cap 3.
It is particularly noted that, in order to control the opening of the valve, for example, a control passage 18 for the entry of high-pressure gas is further provided in the housing 1, and a tapered surface communicating with the control passage 18 is provided along the circumferential surface of the spool 2. One side of the large end of the conical surface is close to the tail part of the valve core 2, one side of the small end of the conical surface is close to the head part of the valve core 2, and the conical surface is opposite to the first step 12. High-pressure gas enters the shell 1 through the control channel 18 and acts on the conical cambered surface to push the valve core 2 to move towards the side close to the valve cover 3. In this embodiment, the design of conical surface, ingenious increase the area of contact of high-pressure gas with case 2, can effectually alleviate high-pressure gas's impact force simultaneously, and then can be fast, stably drive case 2 to being close to valve gap 3 one side motion.
It should be particularly noted that, in order to prevent the liquid medium from flowing out of the fourth channel 8, a high-pressure pipeline is convenient for blowing off the inner wall of the second channel 7, for example, a check valve 20 is arranged on the fourth channel 8.
Another aspect of the invention provides a rocket engine comprising a pneumatic control valve as above for a liquid rocket engine.
The foregoing is merely an illustrative embodiment of the present invention, and any equivalent changes and modifications made by those skilled in the art without departing from the spirit and principle of the present invention should fall within the protection scope of the present invention.
Claims (10)
1. The pneumatic control valve mechanism for the liquid rocket engine is characterized by comprising a shell, a valve core, a valve cover, a sealing element and an elastic element, wherein a first channel and a second channel, wherein the first channel and the second channel are arranged on the inner side of the shell, the first channel is used for allowing gas or liquid media to flow through and penetrate through two ends of the shell, the second channel is different from the first channel in the extending direction, and the shell is also provided with a control channel used for controlling the movement of the valve core;
the valve core is positioned in the shell, the tail part of the valve core is connected with the valve cover positioned on one side of the shell through the elastic part, the end part of the valve core is used for being matched with the transitional inner wall of the first channel and the second channel so as to close the first medium inlet positioned on the first channel, and the sealing part is used for sealing the valve core and the inner wall of the shell;
the end part of the valve core is circular in shape on a cross section obtained by tangency along the axial direction perpendicular to the valve core, the diameter of each circle is gradually increased towards the valve cover side, when the valve works, the control channel pushes the valve core to move towards the valve cover side through control gas so as to open the first medium inlet, and liquid medium is communicated from the first channel to the second channel.
2. The pneumatic control valve mechanism for a liquid rocket engine according to claim 1, wherein the end of the valve core is a frustum structure, the included angle of the frustum structure is A, and the included angle is 100 degrees to 130 degrees.
3. The pneumatic control valve mechanism for a liquid rocket engine according to claim 1, wherein said end portion of said valve core is tangent to form a first circle and a second circle at intervals along a direction perpendicular to an axial direction of said valve core, and outer sides of said first circle and said second circle are connected by an arc surface.
4. A pneumatic control valve mechanism for a liquid rocket engine according to claim 1, wherein said spool is designed coaxially with said first passage.
5. The pneumatic control valve mechanism for a liquid rocket engine according to claim 1, wherein said first passage comprises a first internal passage and a second internal passage communicating with each other, and a transition point of said first internal passage and said second internal passage forms a first step for limiting movement of said spool to a side of said first medium inlet.
6. The pneumatic control valve mechanism for a liquid rocket engine according to claim 5, wherein said valve core has an internal passage, said internal passage includes a second step formed toward the outside, and in a compressed state, both ends of said elastic member abut against end surfaces of said second step and said valve cover near each other, respectively, to apply an elastic force toward the medium inlet side to said valve core.
7. The pneumatic control valve mechanism for a liquid rocket engine according to claim 6, wherein a through hole opened along the axial direction of the first passage is provided at an end of the valve core, a third passage different from the extending direction of the first passage is provided on the housing, and in an initial state of the valve, the liquid medium passes through the through hole and the internal passage in sequence and then is discharged from the third passage.
8. A pneumatic control valve mechanism for a liquid rocket engine according to claim 7, wherein said third passageway is located on a side of said housing adjacent said end cap.
9. The pneumatic control valve mechanism for a liquid rocket engine according to claim 1, wherein said sealing member is a stopper ring structure, and said sealing member comprises a first sealing ring and a second sealing ring spaced apart from each other in an axial direction of said valve core, and annular grooves for fixing said first sealing ring and said second sealing ring are respectively provided in circumferential directions along an inner wall of said housing and an outer surface of said valve core.
10. A rocket engine, characterized by: a pneumatic control valve mechanism for a liquid rocket engine comprising any one of claims 1-9.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202110003246.4A CN112797184B (en) | 2021-01-04 | 2021-01-04 | Pneumatic control valve mechanism for liquid rocket engine and rocket engine |
Applications Claiming Priority (1)
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| JPH061753U (en) * | 1992-06-08 | 1994-01-14 | 石川島播磨重工業株式会社 | Propellant valve |
| CN201599414U (en) * | 2009-12-24 | 2010-10-06 | 中国航天科技集团公司第六研究院第十一研究所 | High pressure ultra-low temperature pneumatic controlled mushroom valve |
| CN204477321U (en) * | 2015-03-25 | 2015-07-15 | 大连庆功林流体机械有限公司 | A kind of high voltage precision flow taper control valve |
| CN110454300A (en) * | 2019-07-26 | 2019-11-15 | 蓝箭航天空间科技股份有限公司 | Valve structure for liquid rocket motor and liquid motor |
| CN111636979A (en) * | 2020-06-08 | 2020-09-08 | 安徽九州云箭航天技术有限公司 | Switch and flow regulating valve for liquid oxygen main circuit of pump pressure variable thrust liquid rocket engine |
| CN111664257A (en) * | 2019-09-30 | 2020-09-15 | 蓝箭航天空间科技股份有限公司 | Valve structure of liquid rocket engine and liquid rocket engine |
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2021
- 2021-01-04 CN CN202110003246.4A patent/CN112797184B/en active Active
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPH061753U (en) * | 1992-06-08 | 1994-01-14 | 石川島播磨重工業株式会社 | Propellant valve |
| CN201599414U (en) * | 2009-12-24 | 2010-10-06 | 中国航天科技集团公司第六研究院第十一研究所 | High pressure ultra-low temperature pneumatic controlled mushroom valve |
| CN204477321U (en) * | 2015-03-25 | 2015-07-15 | 大连庆功林流体机械有限公司 | A kind of high voltage precision flow taper control valve |
| CN110454300A (en) * | 2019-07-26 | 2019-11-15 | 蓝箭航天空间科技股份有限公司 | Valve structure for liquid rocket motor and liquid motor |
| CN111664257A (en) * | 2019-09-30 | 2020-09-15 | 蓝箭航天空间科技股份有限公司 | Valve structure of liquid rocket engine and liquid rocket engine |
| CN111636979A (en) * | 2020-06-08 | 2020-09-08 | 安徽九州云箭航天技术有限公司 | Switch and flow regulating valve for liquid oxygen main circuit of pump pressure variable thrust liquid rocket engine |
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| CN112797184B (en) | 2022-02-01 |
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