CN112282967A - High-temperature gas valve with safety valve function - Google Patents
High-temperature gas valve with safety valve function Download PDFInfo
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- CN112282967A CN112282967A CN202011051028.XA CN202011051028A CN112282967A CN 112282967 A CN112282967 A CN 112282967A CN 202011051028 A CN202011051028 A CN 202011051028A CN 112282967 A CN112282967 A CN 112282967A
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- valve
- core rod
- valve core
- driving device
- temperature gas
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- 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
- F02K9/08—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof using solid propellants
- F02K9/32—Constructional parts; Details not otherwise provided for
- F02K9/38—Safety devices, e.g. to prevent accidental ignition
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- 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
- F02K9/08—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof using solid propellants
- F02K9/32—Constructional parts; Details not otherwise provided for
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- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Lift Valve (AREA)
- Fluid-Driven Valves (AREA)
Abstract
The invention provides a high-temperature gas valve with a safety valve function, which comprises a valve shell, a valve heat insulation layer, a valve core rod, a valve seat, a spray pipe, a driving device and a sealing ring, wherein the valve heat insulation layer is arranged on the valve shell; the driving device controls the valve core rod to reciprocate, the valve core rod and the valve shell are in dynamic seal by adopting a seal ring, the valve core rod works in the direction facing the airflow, and the driving device has the capability of absorbing overload impact; the valve core rod is in contact with the valve seat and sealed, the valve is closed, and the valve does not generate thrust; the valve core rod and the valve seat are separated to open the valve, and the valve generates thrust; when the valve is closed, the driving force of the driving device is smaller than the valve aerodynamic force equivalent to the maximum design pressure of the combustion chamber, the driving device can absorb impact under the overload condition, and the performance of the driving device keeps the design state, so that when the combustion chamber exceeds the maximum working pressure, the valve is not closed, the valve is opened, the equivalent flow area is increased under the flow state, the healthy pressure of the combustion chamber is maintained, and meanwhile, after the overload state, the high-temperature gas valve can regulate and control the gas flow to generate the required thrust.
Description
Technical Field
The invention relates to a high-temperature gas valve with a safety valve function, and belongs to the technical field of solid attitude and orbit control engines.
Background
The working characteristics of the solid attitude and orbit control engine are similar to those of a solid rocket engine, particularly the situation that the ignition pressure peak is too high exists in the ignition process of the engine at the beginning of the operation of the engine, particularly in the ignition process of a small free volume, and the pressure peak possibly exceeds the average pressure of a combustion chamber by more than one time. In addition, the combustion products of the propellant or the heat insulating layer of the solid engine have more residues and contain particles, the high-temperature gas valve is one of the important executive components of the solid attitude control engine and usually exists in a valve group form, and the possibility of short-time blocking of a certain gas valve can occur in the working process of the engine. In summary, the gas valve is harsh in high-temperature, high-pressure and high-residue gas atmosphere, the valve needs to cope with emergencies such as instantaneous surge of combustion chamber pressure caused by overhigh initial pressure peak and short-time blocking in the work of the solid attitude and orbit control engine, and meanwhile, after the emergencies occur, the valve keeps the capacity of regulating high-temperature gas, so that the corresponding work of the engine is guaranteed.
At present, the common gas valve mainly has the following defects when meeting the limit overload condition in the engine work:
1. the drive current increases. Under the ultimate working pressure of the combustion chamber, the current of the driving device is increased, the temperature of the driving device is increased, on one hand, overheating affects the capacity of the follow-up valve for regulating and controlling the flow of high-temperature gas, on the other hand, the driving device is directly burned out under the condition of larger overheating, and the driving device cannot drive the valve core rod to regulate and control the gas.
2. The gas valve has a single function. The conventional gas valve separates the function of the gas valve from that of the safety valve, and the two valves cannot be simultaneously arranged under the compact layout condition of the solid attitude and orbit control engine, so that the safe and reliable working requirements of upstream customers are difficult to meet.
Disclosure of Invention
The invention solves the problems that: the high-temperature gas valve with the safety valve function can ensure the reliable and safe operation of a solid posture orbit control engine.
The technical scheme of the invention is as follows: a high-temperature gas valve with safety valve function comprises: the valve comprises a valve shell (1), a valve heat insulating layer (2), a valve core rod (3), a valve seat (4), a spray pipe (5), a driving device (6) and a sealing ring (7);
the shell (1) is provided with a valve seat mounting port, a spray pipe connecting port, a valve core rod connecting port and a valve cavity;
the valve heat insulation layer (2) is arranged on the inner wall of the valve cavity;
a valve seat (4) is arranged at the valve seat mounting opening of the shell (1); a gas inlet is arranged in the valve seat (4)
The solid rocket engine combustion chamber can be directly communicated with the valve cavity through a fuel gas inlet;
a spray pipe (5) is arranged in the spray pipe connecting port, one end of the spray pipe (5) is communicated with the valve cavity, and the other end of the spray pipe (5) is communicated with the outside;
a valve core rod connecting port of the shell (1) is provided with a valve core rod (3), the valve core rod (3) and the valve shell (1) are in dynamic sealing by adopting a sealing ring (7), one end of the valve core rod (3) is positioned in a valve cavity, and the other end of the valve core rod (3) is connected with a driving device (6);
the driving device (6) controls the valve core rod (3) to reciprocate;
under the control of the driving device (6), the valve core rod (3) is in contact with the valve seat (4) and sealed, so that the high-temperature gas valve is closed, and thrust is not generated by the high-temperature gas valve; the valve core rod (3) and the valve seat (4) are separated to open the high-temperature gas valve, and the high-temperature gas valve generates thrust through the spray pipe (5).
Preferably, the driving force of the driving device when the valve is closed is smaller than the valve pneumatic force equivalent to the maximum design pressure of the combustion chamber, and the pneumatic force directly acts on the valve core rod.
Preferably, the driving device can absorb impact (the impact is impact force generated on the valve core rod (3) when the pressure of the combustion chamber exceeds the maximum design pressure) in the overload state of the combustion chamber (the overload state is that the pressure of the combustion chamber exceeds the maximum design pressure), the performance of the driving device keeps in the design state, when the pressure of the combustion chamber reaches the maximum design pressure, the valve core rod (3) is separated from the valve seat (4), the high-temperature gas valve is not closed, the equivalent flow area of the combustion chamber is increased in the flow state, the healthy pressure of the combustion chamber of the solid rocket engine is maintained, and meanwhile, after the overload state, the high-temperature gas valve can regulate and control the gas flow of the valve to generate required thrust.
Preferably, the driving device (6) controls the valve core rod (3) to work in the direction facing the gas flow, and the driving device has the capability of lossless overload impact absorption.
Preferably, the valve heat insulation layer (2) is a carbon fiber molded product and has the capability of resisting the scouring of solid high-temperature fuel gas medium at the temperature of more than 1500 ℃ and the capability of flowing and transferring heat.
Preferably, the drive means is in a constant power drive mode and has a lossless overload shock absorption capability.
Preferably, the valve core rod (3) is separated from the valve seat (4) under the maximum limit pressure of the combustion chamber, the equivalent flow area of the combustion chamber of the solid rocket engine is increased, and the pressure of the combustion chamber is reduced to be close to the average pressure.
Preferably, the passage in the valve seat (4) comprises two sections: the fuel gas inlet is a cylindrical section and a conical section, the cylindrical section is used as a fuel gas inlet, and the conical section is used for sealing and can form a sealing pair with the valve core rod (3);
the small-diameter end of the valve seat (4) is directly connected with the valve cavity, and the large-diameter end of the valve seat is connected with a combustion chamber of the solid rocket engine.
Preferably, a sealing groove is formed in the side wall of the valve core rod connecting port of the valve shell (1), the sealing ring (7) is arranged in the sealing groove, and the valve core rod (3) penetrates through the middle of the sealing ring (7).
Preferably, the valve core rod (3) and the valve shell (1) are in dynamic sealing by adopting a sealing ring (7), and the dynamic sealing is as follows: when the valve core rod (3) moves, the position of the sealing ring (7) is fixed, and the valve core rod (3) continuously seals the valve core rod (3) and the valve shell (1) in the process of reciprocating relative to the sealing ring (7) in the valve core rod connecting port.
Preferably, one end of the valve core rod (3) in the valve cavity is provided with an impact head, the gas facing surface of the impact head is in an ellipsoidal shape and is in contact fit with the valve seat (4) in the closed state of the valve to form sealing.
Compared with the prior art, the invention has the advantages that:
(1) the high-temperature gas valve with the safety valve function can provide the existing gas valve with the capacity of resisting the limit pressure of a combustion chamber and reliably working after limit load, and meanwhile, the safety valve and the gas valve are integrated in performance, so that the multiple requirements of upstream customers are met, and the corresponding working requirements are met.
(2) The invention adopts the scheme that the driving force of the driving device is smaller than the maximum pressure equivalent impact force of the combustion chamber, when the pressure of the combustion chamber exceeds the maximum design pressure, the valve is changed from a closed state to an open state, the equivalent flow area of the engine is increased, the pressure of the combustion chamber is reduced, and the safety of the engine is ensured.
(3) The driving device adopts the scheme of the spiral electromagnetic actuator, the spiral electromagnetic actuator can quickly respond to the surge of the combustion chamber, the constant power driving mode of the spiral electromagnetic actuator can nondestructively absorb the overload impact force exceeding the maximum design pressure of the combustion chamber, and the gas valve has the capability of regulating and controlling the gas flow in the subsequent combustion work of the engine.
Drawings
Fig. 1 is a schematic diagram of a high-temperature gas valve with a safety valve function according to a preferred embodiment of the present invention.
Detailed Description
The high-temperature gas valve with the safety valve function of the present invention will be further described in detail with reference to the accompanying drawings.
The invention provides a high-temperature gas valve with a safety valve function, which comprises a valve shell, a valve heat insulation layer, a valve core rod, a valve seat, a spray pipe, a driving device and a sealing ring, wherein the valve heat insulation layer is arranged on the valve shell; the driving device controls the valve core rod to reciprocate, the valve core rod and the valve shell are in dynamic seal by adopting a seal ring, the valve core rod works in the direction facing the airflow, and the driving device has the capability of absorbing overload impact; the valve core rod is in contact with the valve seat and sealed, the valve is closed, and the valve does not generate thrust; the valve core rod and the valve seat are separated to open the valve, and the valve generates thrust; when the valve is closed, the driving force of the driving device is smaller than the valve aerodynamic force equivalent to the maximum design pressure of the combustion chamber, the driving device can absorb impact under the overload condition, and the performance of the driving device keeps the design state, so that when the combustion chamber exceeds the maximum working pressure, the valve is not closed, the valve is opened, the equivalent flow area is increased under the flow state, the healthy pressure of the combustion chamber is maintained, and meanwhile, after the overload state, the high-temperature gas valve can regulate and control the gas flow to generate the required thrust.
When the solid rocket engine is ignited and started, the pressure of the combustion chamber is increased suddenly due to the fact that the initial pressure peak of the solid combustion chamber is too high or the initial combustion surface of the combustion chamber is increased accidentally, on one hand, the high-temperature gas valve plays a role of a safety valve, the peak pressure is reduced, the safety of the engine is guaranteed, on the other hand, the gas valve is a non-destructive safety valve and still has the capacity of regulating and controlling gas flow, and the problems that the valve is destroyed due to overload of a driving device under the situation that the combustion chamber is suddenly increased, and the safety and the function of the engine are guaranteed simultaneously under the limited space are.
As shown in fig. 1, the gas valve includes a valve housing 1, a valve heat insulating layer 2, a valve core rod 3, a valve seat 4, a nozzle 5, a driving device 6, and a sealing ring 7.
Preferably, the valve heat insulation layer 2 is a carbon fiber molded product and has scouring and flowing heat transfer of solid high-temperature fuel gas medium at the temperature of more than 1500 ℃.
Preferably, the drive means 6 controls the spool rod 3 to reciprocate.
Preferably, the valve core rod 3 and the valve shell 1 are movably sealed by a sealing ring 7.
Preferably, the working direction of the valve core rod 3 is the direction facing the air flow.
Preferably, the valve core rod 3 is in contact seal with the valve seat 4, the gas inlet is blocked, the valve is closed, and the valve does not generate thrust.
Preferably, the valve core rod 3 is separated from the valve seat 4, so that the valve is opened and generates thrust.
Preferably, the drive means 6 is in constant power drive mode and has a lossless overload shock absorption capability.
Preferably, the driving force of the driving means 6 is smaller than the valve pneumatic force equivalent to the maximum design pressure of the combustion chamber.
Preferably, the valve core rod 3 is separated from the valve seat 4 under the maximum design pressure of the combustion chamber, the equivalent flow area of the combustion chamber is increased, and the pressure of the combustion chamber is reduced to be close to the average pressure.
The further preferable scheme is as follows: the driving device can absorb impact under the overload state of the combustion chamber, the performance of the driving device keeps a design state, when the pressure of the combustion chamber reaches the maximum design pressure, the valve core rod (3) is separated from the valve seat (4), the high-temperature gas valve is not closed, the equivalent flow area of the combustion chamber is increased under the flow state, the healthy pressure of the combustion chamber of the solid rocket engine is maintained, and meanwhile, after the overload state, the high-temperature gas valve can regulate and control the gas flow of the valve to generate required thrust.
In the invention, when the gas valve is in a closed state, namely the valve core rod 3 and the valve seat 4 seal and block a gas inlet to control gas flow, the valve does not generate thrust, if the initial pressure peak of a solid combustion chamber is too high or the pressure of the combustion chamber is increased due to accidental abnormal increase of the initial combustion surface of the combustion chamber, because the driving force of the driving device 6 is smaller than the valve aerodynamic force equivalent to the maximum design pressure of the combustion chamber, when the pressure of the combustion chamber exceeds the maximum design pressure, the valve core rod 3 is acted by the gas aerodynamic force to overcome the driving force of the driving device 6, the valve core rod 3 moves away from the valve seat 4, the gas circulates, the equivalent circulation area of an engine is increased, the pressure of the combustion chamber is reduced by regulation, the pressure of the combustion chamber is ensured to be in an average pressure state, the continuous increase of the pressure of the combustion chamber is avoided; after the pressure of the combustion chamber is suddenly increased, the driving device 6 adopts a constant power driving mode and has the capability of nondestructively absorbing overload impact, and the gas valve keeps the capability of driving the valve core rod 3 to regulate and control the gas flow.
The driving device 6 preferably adopts a scheme of a spiral electromagnetic actuator, the spiral electromagnetic actuator can quickly respond to the surge of the combustion chamber, the spiral electromagnetic actuator works at constant power, the overload impact force exceeding the maximum design pressure of the combustion chamber can be absorbed in a lossless manner, and the gas valve has the capability of regulating and controlling the gas flow in the subsequent combustion work of the engine.
In the invention, the thickness of the heat insulating layer 6 is important besides the importance of materials, the gas temperature, the valve flow and the working time are determining factors influencing the wall thickness of the heat insulating layer, and the further preferable scheme is as follows: the fuel gas temperature of a certain solid rocket engine is 3000 ℃, the working time is 10s, the flow rate is 1kg/s, the wall thickness of the heat insulating layer 6 of the fuel gas valve is not less than 4mm according to the requirement of flow heat transfer, and the upper limit value is designed according to the limit of the valve volume and the temperature of the outer wall surface of the valve shell.
According to the further scheme for improving the reliability of the valve, the valve core rod 3 is of a composite structure, so that the rigidity of the valve core rod is guaranteed, and the sealing performance of the sealing ring 7 is guaranteed. The valve core rod 3 main body structure is metal in the specific implementation, and the heat conductivity coefficient of the valve core rod 3 is reduced by winding a non-metal material, so that the temperature of the position of the sealing ring 7 in the working time is not higher than the failure temperature of 350 ℃.
In a preferred embodiment of the invention, other variants are possible, such as: the driving device shown in fig. 1 is preferably an electromagnetic driver such as a motor, and may be a combination device such as a pilot valve; the valve can be used in the technical field of solid rocket engines, and can also be used in the liquid engines or the civil field; the valve heat-insulating layer 2 is not only a heat-insulating and scouring-resistant material similar to a carbon fiber molded product, but also a composite structure similar to a carbon fiber and high silica winding piece and the like; the gas temperature of the solid engine is also suitable below 1500 ℃.
Although the present invention has been described with reference to the preferred embodiments, it is not intended to limit the present invention, and those skilled in the art can make variations and modifications of the present invention without departing from the spirit and scope of the present invention by using the methods and technical contents disclosed above.
Claims (9)
1. The utility model provides a have high temperature gas valve of relief valve function concurrently which characterized in that includes: the valve comprises a valve shell (1), a valve heat insulating layer (2), a valve core rod (3), a valve seat (4), a spray pipe (5), a driving device (6) and a sealing ring (7);
the shell (1) is provided with a valve seat mounting port, a spray pipe connecting port, a valve core rod connecting port and a valve cavity;
the valve heat insulation layer (2) is arranged on the inner wall of the valve cavity;
a valve seat (4) is arranged at the valve seat mounting opening of the shell (1); a gas inlet is arranged in the valve seat (4)
The solid rocket engine combustion chamber can be directly communicated with the valve cavity through a fuel gas inlet;
a spray pipe (5) is arranged in the spray pipe connecting port, one end of the spray pipe (5) is communicated with the valve cavity, and the other end of the spray pipe (5) is communicated with the outside;
a valve core rod connecting port of the shell (1) is provided with a valve core rod (3), the valve core rod (3) and the valve shell (1) are in dynamic sealing by adopting a sealing ring (7), one end of the valve core rod (3) is positioned in a valve cavity, and the other end of the valve core rod (3) is connected with a driving device (6);
the driving device (6) controls the valve core rod (3) to reciprocate;
under the control of the driving device (6), the valve core rod (3) is in contact with the valve seat (4) and sealed, so that the high-temperature gas valve is closed, and thrust is not generated by the high-temperature gas valve; the valve core rod (3) and the valve seat (4) are separated to open the high-temperature gas valve, and the high-temperature gas valve generates thrust through the spray pipe (5).
2. The high-temperature gas valve with the safety valve function as claimed in claim 1, wherein: when the valve is closed, the driving force of the driving device is smaller than the valve pneumatic force equivalent to the maximum design pressure of the combustion chamber, and the pneumatic force directly acts on the valve core rod.
3. The high-temperature gas valve with the safety valve function as claimed in claim 1, wherein: the driving device (6) controls the valve core rod (3) to work in the direction facing the gas flow, and the driving device has the capability of lossless overload impact absorption.
4. The high-temperature gas valve with the safety valve function as claimed in claim 1, wherein: the valve heat insulation layer (2) is a carbon fiber molded product and has the capability of resisting the scouring of solid high-temperature fuel gas medium at the temperature of more than 1500 ℃ and the capability of flowing heat transfer.
5. The high-temperature gas valve with the safety valve function as claimed in claim 1, wherein: the driving device adopts a constant power driving mode and has the capability of nondestructively absorbing overload impact.
6. The high-temperature gas valve with the safety valve function as claimed in claim 1, wherein: the valve core rod (3) is separated from the valve seat (4) under the maximum limit pressure of the combustion chamber, the equivalent flow area of the combustion chamber of the solid rocket engine is increased, and the pressure of the combustion chamber is reduced to be close to the average pressure.
7. The high-temperature gas valve with the safety valve function as claimed in claim 1, wherein: the inner channel of the valve seat (4) comprises two sections: the fuel gas inlet is a cylindrical section and a conical section, the cylindrical section is used as a fuel gas inlet, and the conical section is used for sealing and can form a sealing pair with the valve core rod (3);
the small-diameter end of the valve seat (4) is directly connected with the valve cavity, and the large-diameter end of the valve seat is connected with a combustion chamber of the solid rocket engine.
8. The high-temperature gas valve with the safety valve function as claimed in claim 1, wherein: the side wall of a valve core rod connecting port of the valve shell (1) is provided with a sealing groove, a sealing ring (7) is arranged in the sealing groove, and the valve core rod (3) penetrates through the middle of the sealing ring (7).
9. The high-temperature gas valve with the safety valve function as claimed in claim 1, wherein: the valve core rod (3) and the valve shell (1) are in dynamic sealing by adopting a sealing ring (7), and the dynamic sealing is as follows: when the valve core rod (3) moves, the position of the sealing ring (7) is fixed, and the valve core rod (3) continuously seals the valve core rod (3) and the valve shell (1) in the process of reciprocating relative to the sealing ring (7) in the valve core rod connecting port.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202011051028.XA CN112282967B (en) | 2020-09-29 | 2020-09-29 | High-temperature gas valve with safety valve function |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202011051028.XA CN112282967B (en) | 2020-09-29 | 2020-09-29 | High-temperature gas valve with safety valve function |
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| Publication Number | Publication Date |
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| CN112282967A true CN112282967A (en) | 2021-01-29 |
| CN112282967B CN112282967B (en) | 2022-07-05 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN202011051028.XA Active CN112282967B (en) | 2020-09-29 | 2020-09-29 | High-temperature gas valve with safety valve function |
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Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN115059559A (en) * | 2022-07-26 | 2022-09-16 | 哈尔滨工业大学 | Valve capable of accurately regulating thrust of solid rocket engine |
| CN115807717A (en) * | 2022-12-07 | 2023-03-17 | 湖北三江航天红林探控有限公司 | Side-spraying solid rocket engine |
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| CN115807717A (en) * | 2022-12-07 | 2023-03-17 | 湖北三江航天红林探控有限公司 | Side-spraying solid rocket engine |
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| CN112282967B (en) | 2022-07-05 |
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