CN101644209B - Straight single-hole fuel gas fluid control valve - Google Patents
Straight single-hole fuel gas fluid control valve Download PDFInfo
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- CN101644209B CN101644209B CN2008101505737A CN200810150573A CN101644209B CN 101644209 B CN101644209 B CN 101644209B CN 2008101505737 A CN2008101505737 A CN 2008101505737A CN 200810150573 A CN200810150573 A CN 200810150573A CN 101644209 B CN101644209 B CN 101644209B
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- control valve
- fuel gas
- fluid control
- fluid
- vortex chamber
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Abstract
The invention discloses a straight single-hole fuel gas fluid control valve. The control valve comprises a fluid control valve body, a fuel gas interface, a control fluid filling tube, a securing ring, a center body, a spray tube and a back end cover, wherein the fuel gas interface is welded on the fluid control valve body; the securing ring is in threaded connection with the fluid control valve body; the back end cover of the fluid control valve is connected with the valve body by ten M12 high-strength bolts; and the fuel gas fluid control valve is connected with a fluid control variable thrust engine by twelve M12 high-strength bolts. The control fluid can be directly and tangentially led in a turbulence chamber by the fuel gas interface and the control fluid filling tube arranged in the fuel gas interface. The control valve of the invention has the advantages of simple structure, convenient assembly and good thermal protection effect.
Description
Technical field
The present invention relates to a kind of control valve unit, particularly relate to a kind of straight single-hole fuel gas fluid control valve that can use the combustion gas control flows.
Background technique
At present, in the experiment of aviation aerospace science and technology, fluid control Variable Thrust Engine is to spray into tangential control flows by the control valve for fluids on the motor, force combustion gas to produce rotation, increase flow resistance, change firing chamber balance pressure, and then influence propellant burning rate, realization reaches the purpose of regulating thrust to the control of combustion gas growing amount and discharge capacity.Mentioned a kind of swirl valve structure in the existing disclosed document " swirl valve geometric parameter to the influence of solid engines thrust regulation characteristic (" Push Technology ", Vol.28, No.4,2007, p352-355) ".Swirl valve structure in the literary composition is that control flows is introduced the vortex chamber by the filling ring that has tangential hole, and the filling ring is the Ordinary Steel overall structure in the literary composition, and control flows is used is compressed nitrogen.Because the temperature of control flows has very big influence to the control characteristic of motor, the use of high-temperature gas can improve the thrust regulation ability of swirl valve.But the swirl valve structure in the literary composition is when the combustion gas control flows of using the solid propellant gas generator to produce, because spray orifice is the throat of gas generator, bear the erosion and the ablation of high temperature, high pressure, high-speed fuel gas stream, and the filling ring structure in the document is the Ordinary Steel overall structure, can not bear the effect of high-temperature fuel gas stream, and will cause spray orifice to become big, thereby can not guarantee the motor stable operation, more or cause filling ring to burn out, make the engine operation failure.And when using hot combustion gas as control flows, because its temperature is up to 1300 ℃, this can make general metallic material all can not use.Therefore, can not use general metallic material as air delivering pipeline.
The content of invention
The technical problem to be solved in the present invention is to provide a kind of control valve for fluids that can use the combustion gas control flows, carries out the solid propellant rocket thrust regulation.
The present invention can realize using the gas flow that is produced by gas generator as control flows, tangentially sprays into fluid control and becomes the thrust solid engines, regulates the thrust size of motor.
In order to achieve the above object, design control valve for fluids structure as shown in Figure 1.In order reliably to use the combustion gas control flows, in combustion gas interface and flow channel, install thermal protection struc ture layer structure additional so that the protection Structural Hardware.Control flows is directly introduced in the control valve for fluids by control flows filling conduit.This structure both can guarantee that combustion gas did not contact with Structural Hardware, had reduced the sealing needs again, can also reduce because of the air current flow loss.All there is thermal protection struc ture the position of the mobile process of control valve for fluids structure gas of the present invention, and therefore can guarantee can be reliable fully in the engine working process.
Composition of the present invention comprises: combustion gas interface (1), control flows filling conduit (2), centerbody (3), retaining ring (4), control valve for fluids body (5), vortex chamber's heat shield (6), jet pipe (7) and rear end cover parts such as (8).
The present invention can carry out the experimental study of high-temperature fuel gas fluid control Variable Thrust Engine.The present invention is simple in structure, and is easy for installation, and thermal protection is respond well.
Brief description of drawings
Fig. 1 is the elevation cross-sectional view of straight single-hole fuel gas fluid control valve of the present invention;
Fig. 2 is the sectional view along A-A line among Fig. 1;
Fig. 3 is engine chamber pressure-time graph;
Fig. 4 is motor power-time graph.
Concrete embodiment
Below in conjunction with accompanying drawing embodiments of the present invention are described in further detail:
The present invention is applied to obtain good effect in the test of combustion gas control flows fluid control Variable Thrust Engine.
Centerbody (3), control flows filling conduit (2), vortex chamber's heat shield (6) and jet pipe (7) adopt high-strength graphite, and other structure adopts the 45# steel.
According to assembling the present invention shown in the accompanying drawing 1:
Before assembling, at first combustion gas interface (5) and valve body (3) are welded.
1. vortex chamber's heat shield (6) is pressed in the control valve for fluids body (5), guarantees that vortex chamber's heat shield (6) is consistent with the tangential hole center on the control valve for fluids body (5);
2. the conduit (2) of control flows being annotated is pressed in the combustion gas interface (1), guarantees that the cambered surface of control flows filling conduit (2) is consistent with the intrados of vortex chamber's heat shield (6);
3. centerbody (3) is pressed in the control valve for fluids body (5), guarantees that centerbody (3) closely contacts with vortex chamber's heat shield (6);
4. retaining ring (4) is connected with control valve for fluids body (5) by screw thread, guarantee that retaining ring (4) closely contacts with centerbody (3);
5. jet pipe (7) is pressed in the valve body (3), guarantees that jet pipe closely contacts with vortex chamber's heat shield (6);
6. adopt the high-strength bolt of 10 M12 that rear end cover of the present invention (8) and control valve for fluids body (5) are linked, use the high-strength bolt of 12 M12 that the present invention is connected with fluid control Variable Thrust Engine then, the present invention is connected with the solid propellant gas generator by screw thread.
It is 1300 ℃ of no aluminium propellant agents that the solid propellant gas generator uses fuel gas temperature, and flow is 0.048kg/s, and pressure is 9MPa, uses two of single-ended combustion powder columns, and every combustion face diameter is 50mm.
Test according to the solid propellant rocket experimental implementation.Test records engine chamber pressure-time graph and thrust time graph as shown in Figure 3, Figure 4.
Test result is stable as can be seen by Fig. 3, Fig. 4, has realized that motor becomes the requirement of thrust.Disassemble motor after experiment finishes and find that the control valve for fluids structure is intact.
Claims (4)
1. straight single-hole fuel gas fluid control valve, comprise control valve for fluids body, combustion gas interface, control flows filling conduit, retaining ring and rear end cover, it is characterized in that: described combustion gas interface (1) and control valve for fluids body (5) welding, combustion gas interface (1) is connected with the control flows filling conduit (2) that sets within it, the cambered surface of control flows filling conduit (2) is consistent with the intrados of vortex chamber's heat shield (6), and control flows is annotated by control flows, and conduit (2) is directly tangential to be introduced in the vortex chamber.
2. straight single-hole fuel gas fluid control valve according to claim 1 is characterized in that: described vortex chamber heat shield (6) is pressed in the control valve for fluids body (5), guarantees that vortex chamber's heat shield (6) is consistent with the tangential hole center on the control valve for fluids body (5).
3. straight single-hole fuel gas fluid control valve according to claim 1, it is characterized in that: an end of described control valve for fluids body (5) and retaining ring (4) pass through scyewed joint, control valve for fluids body (5) adopts the high-strength bolt of 10 M12 to connect with rear end cover (8), uses the high-strength bolt of 12 M12 that fuel gas fluid control valve is connected with fluid control Variable Thrust Engine then.
4. straight single-hole fuel gas fluid control valve according to claim 1 and 2 is characterized in that: described control flows filling conduit (2) and vortex chamber's heat shield (6) adopt high-strength graphite.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2008101505737A CN101644209B (en) | 2008-08-08 | 2008-08-08 | Straight single-hole fuel gas fluid control valve |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2008101505737A CN101644209B (en) | 2008-08-08 | 2008-08-08 | Straight single-hole fuel gas fluid control valve |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN101644209A CN101644209A (en) | 2010-02-10 |
| CN101644209B true CN101644209B (en) | 2011-06-15 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN2008101505737A Expired - Fee Related CN101644209B (en) | 2008-08-08 | 2008-08-08 | Straight single-hole fuel gas fluid control valve |
Country Status (1)
| Country | Link |
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| CN (1) | CN101644209B (en) |
Families Citing this family (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105090592B (en) * | 2015-07-14 | 2017-08-29 | 西北工业大学 | A kind of change controlling stream for solid Variable Thrust Engine supplies angle swirl valve |
| CN110529290B (en) * | 2019-07-24 | 2021-06-04 | 上海空间推进研究所 | Series redundant device |
Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US3219048A (en) * | 1963-05-22 | 1965-11-23 | Palmisano Rosso Richard | Vortex flow control valve |
| US3366370A (en) * | 1965-12-06 | 1968-01-30 | Honeywell Inc | Control apparatus |
| US3486521A (en) * | 1967-12-08 | 1969-12-30 | Bendix Corp | Flowing probe vortex device |
| US3702536A (en) * | 1971-01-18 | 1972-11-14 | Nasa | Rocket thrust throttling system |
| US4817863A (en) * | 1987-09-10 | 1989-04-04 | Honeywell Limited-Honeywell Limitee | Vortex valve flow controller in VAV systems |
| CN2048944U (en) * | 1989-04-20 | 1989-12-06 | 湖南淮海仪表厂 | Cyclone type cold and heat separator |
-
2008
- 2008-08-08 CN CN2008101505737A patent/CN101644209B/en not_active Expired - Fee Related
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US3219048A (en) * | 1963-05-22 | 1965-11-23 | Palmisano Rosso Richard | Vortex flow control valve |
| US3366370A (en) * | 1965-12-06 | 1968-01-30 | Honeywell Inc | Control apparatus |
| US3486521A (en) * | 1967-12-08 | 1969-12-30 | Bendix Corp | Flowing probe vortex device |
| US3702536A (en) * | 1971-01-18 | 1972-11-14 | Nasa | Rocket thrust throttling system |
| US4817863A (en) * | 1987-09-10 | 1989-04-04 | Honeywell Limited-Honeywell Limitee | Vortex valve flow controller in VAV systems |
| CN2048944U (en) * | 1989-04-20 | 1989-12-06 | 湖南淮海仪表厂 | Cyclone type cold and heat separator |
Non-Patent Citations (2)
| Title |
|---|
| 张为华等.固体发动机推力随机调节的涡流阀方案研究.《推进技术》.1995,(第5期),34-39. * |
| 魏祥庚等.涡流阀几何参数对固体发动机推力调节特性的影响.《推进技术》.2007,第28卷(第4期),352-355. * |
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| Publication number | Publication date |
|---|---|
| CN101644209A (en) | 2010-02-10 |
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