CN217582323U - Torch igniter for multiple starting of liquid rocket engine - Google Patents
Torch igniter for multiple starting of liquid rocket engine Download PDFInfo
- Publication number
- CN217582323U CN217582323U CN202220659873.3U CN202220659873U CN217582323U CN 217582323 U CN217582323 U CN 217582323U CN 202220659873 U CN202220659873 U CN 202220659873U CN 217582323 U CN217582323 U CN 217582323U
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- Prior art keywords
- valve
- oxygen
- fuel
- torch
- control
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- 239000007788 liquid Substances 0.000 title claims abstract description 35
- 239000000446 fuel Substances 0.000 claims abstract description 62
- QVGXLLKOCUKJST-UHFFFAOYSA-N atomic oxygen Chemical compound [O] QVGXLLKOCUKJST-UHFFFAOYSA-N 0.000 claims abstract description 56
- 239000001301 oxygen Substances 0.000 claims abstract description 56
- 229910052760 oxygen Inorganic materials 0.000 claims abstract description 56
- 239000007789 gas Substances 0.000 claims abstract description 27
- MYMOFIZGZYHOMD-UHFFFAOYSA-N Dioxygen Chemical compound O=O MYMOFIZGZYHOMD-UHFFFAOYSA-N 0.000 claims description 9
- 239000007800 oxidant agent Substances 0.000 description 9
- 230000001590 oxidative effect Effects 0.000 description 9
- IJGRMHOSHXDMSA-UHFFFAOYSA-N Atomic nitrogen Chemical compound N#N IJGRMHOSHXDMSA-UHFFFAOYSA-N 0.000 description 8
- 230000005284 excitation Effects 0.000 description 4
- 229910052757 nitrogen Inorganic materials 0.000 description 4
- 239000002737 fuel gas Substances 0.000 description 3
- 238000005516 engineering process Methods 0.000 description 2
- 239000003721 gunpowder Substances 0.000 description 2
- 238000012423 maintenance Methods 0.000 description 2
- 239000000463 material Substances 0.000 description 2
- 238000000034 method Methods 0.000 description 2
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000003197 catalytic effect Effects 0.000 description 1
- 239000011248 coating agent Substances 0.000 description 1
- 238000000576 coating method Methods 0.000 description 1
- 238000002485 combustion reaction Methods 0.000 description 1
- 238000005474 detonation Methods 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 239000000843 powder Substances 0.000 description 1
- 238000006467 substitution reaction Methods 0.000 description 1
- 239000013585 weight reducing agent Substances 0.000 description 1
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Abstract
A liquid rocket engine multiple start-oriented torch igniter, comprising: the utility model discloses a torch, spark plug (, oxygen control valve, fire the electrohydraulic valve, oxygen double check valve, fire double check valve, control solenoid valve and oxygen cold discharge valve, wherein, the spark plug is connected with the torch, the torch respectively with oxygen double check valve and fire double check valve exit linkage, oxygen double check valve and oxygen control valve exit linkage, fire double check valve and fire the outlet connection of electrohydraulic valve, the oxygen control valve respectively with control solenoid valve export, oxygen cold discharge valve exit linkage, the fuel electrohydraulic valve is connected with the fuel pump exit linkage, control solenoid valve and control gas exit linkage, the utility model discloses a torch formula ignition system is lighted the fuel in the liquid rocket engine, realizes the liquid rocket engine and realizes compact structure, lighten the quality when lighting up before many times.
Description
Technical Field
The utility model belongs to liquid rocket engine and field especially relate to a torch point firearm towards liquid rocket engine multiple start-up.
Background
The torch type ignition technology is low in price and high in ignition efficiency, and compared with a novel ignition technology such as laser ignition, the requirements for gas sources and materials are reduced; meanwhile, torch ignition is widely applied to occasions with large fuel flow in the thrust chamber due to the characteristics of high ignition energy, convenience in maintenance, repeated ignition and the like. The characteristics meet the development trend of aerospace delivery, manned aerospace flight and expansion cycle engines, so the engine has wide application prospect.
Disclosure of Invention
The utility model aims at realizing the multiple ignition precondition of the liquid rocket engine, realizing compact structure and lightening mass.
The utility model discloses the purpose realizes through following technical scheme: a liquid rocket engine multiple start torch igniter, comprising: torch, spark plug, oxygen control valve, fuel liquid valve, oxygen double check valve, fuel double check valve, control solenoid valve, oxygen cold discharge valve and other assembly components. Wherein the spark plug is connected to the torch; the torch is respectively connected with the outlets of the oxygen double check valve and the fuel double check valve; the oxygen double one-way valve is connected with the outlet of the oxygen control valve, and the on-off of the liquid oxygen and the control gas is controlled by utilizing the two-position three-way characteristic of the oxygen control valve: when the control cavity is opened to supply control gas with certain pressure, the valve is opened, the controller is disconnected, the valve is closed, and the discharge port is communicated with the valve outlet; the fuel double one-way valve is connected with an outlet of the fuel liquid valve, the on-off of a fuel pump pipeline is controlled by utilizing the two-position three-way characteristic of the fuel liquid valve, and when the power is off, the fuel liquid valve is closed, and the fuel pump pipeline is disconnected; when the power is on, the fuel liquid valve is opened, and the fuel pump pipeline is opened; the oxygen control valve is respectively connected with the control electromagnetic valve, the oxygen cold exhaust valve and the oxygen pump outlet, the on-off of the control gas pipeline is controlled by using the control electromagnetic valve, and the oxidant pipeline is pre-cooled by using the oxygen cold exhaust valve; the fuel liquid valve is connected with an outlet of a fuel pump; the control electromagnetic valve is connected with the control gas outlet to control the on-off of the control gas pipeline.
The single working time of the torch igniter is 2-3s, and the torch igniter can be repeatedly used for 5-10 times.
According to the torch igniter, the excitation energy of the spark plug is 12J, the excitation frequency is 100Hz, and the power supply voltage is 27 +/-3V, so that the torch is ignited.
In the torch igniter, the oxygen pump pipeline is communicated with the low-temperature liquid oxygen storage tank.
In the torch igniter, the control gas pipeline is communicated with the high-pressure nitrogen storage tank.
In the torch igniter, the fuel pump pipeline is communicated with the low-temperature fuel storage tank.
Compared with the prior art, the utility model has the following beneficial effects that the utility model discloses a fuel in torch formula ignition to the liquid rocket engine is igniteed, compares in traditional gunpowder ignition mode, at first can realize this purpose of many times ignition, has satisfied the development trend that space flight delivery, manned space flight and inflation cycle engine start many times, has extensive application prospect. Simultaneously the utility model discloses can also realize compact structure, proper amount light, this capacity space and the dead weight in having directly saved the engine can provide more storage space and quality for fuel and oxidant, have very big advantage. In addition, compared with some novel ignition modes, such as detonation wave ignition, pneumatic resonance ignition, catalytic ignition, laser ignition and the like, the torch type ignition mode has low requirements on gas sources and materials, so that the torch type ignition mode is low in price and high in ignition efficiency. In view of the above discussion, the present invention has incomparable advantages in structure, quality, price, ignition efficiency, ignition energy and later maintenance.
Drawings
Fig. 1 is a system schematic diagram of the present invention.
Detailed Description
Exemplary embodiments of the present disclosure will be described in more detail below with reference to the accompanying drawings. While exemplary embodiments of the present disclosure are shown in the drawings, it should be understood that the present disclosure may be embodied in various forms and should not be limited to the embodiments set forth herein. Rather, these embodiments are provided so that this disclosure will be thorough and complete, and will fully convey the scope of the disclosure to those skilled in the art. It should be noted that, in the present invention, the embodiments and features of the embodiments may be combined with each other without conflict. The present invention will be described in detail below with reference to the accompanying drawings in conjunction with embodiments.
The attached drawings are the principle drawings of the utility model. As shown in the figure, the torch igniter facing the multiple starting of the liquid rocket engine consists of a torch 1, a spark plug 2, an oxygen control valve 3, a fuel liquid valve 4, an oxygen double one-way valve 5, a fuel double one-way valve 6, a control electromagnetic valve 7 and an oxygen cold discharge valve 8.
The spark plug 2 is connected with the outlet of the torch 1;
the inlet of the torch 1 is respectively connected with the outlet of the oxygen double check valve 5 and the outlet of the fuel double check valve 6; the opening and closing of the valve is controlled by the pressure difference of the inlet and the outlet of the oxygen/fuel double check valve;
the inlet of the oxygen bi-directional valve 5 is connected with the outlet of the oxygen control valve 3, and the on-off of oxygen and control gas is controlled by utilizing the electromagnetic two-position three-way characteristic of the oxygen control valve 3;
the inlet of the fuel double check valve 6 is connected with the outlet of the fuel liquid valve 4, and the on-off of a fuel pump pipeline is controlled by utilizing the electromagnetic two-position three-way characteristic of the fuel liquid valve 4;
and an inlet of the oxygen control valve 3 is respectively connected with an outlet of the control electromagnetic valve 7, an outlet of the oxygen cold discharge valve 8 and an outlet.
The on-off of the control gas N2 pipeline is controlled by utilizing the electromagnetic two-digit three-way characteristic of the control electromagnetic valve 7, if the control electromagnetic valve is electrified and opened, the control gas N2 enters the control cavity of the oxygen control valve 3 along the pipeline and keeps the valve thereof open, so as to realize the function of exhausting; on the contrary, if no high-pressure control gas exists, the valve is kept closed, and the liquid oxygen pipeline is kept opened at the moment;
an oxygen cold discharge valve 8 is communicated with the liquid oxygen pipeline, so that dry nitrogen in the liquid oxygen pipeline before precooling is discharged to the outside from an outlet of the liquid oxygen pipeline;
the inlet of the fuel liquid valve 4 is connected with the outlet of a fuel pump;
the fuel liquid valve 4 is a normally closed electromagnetic two-position three-way valve, and the valve is opened after being electrified and is closed without being electrified, so that the on-off of a fuel pipeline is controlled;
and the inlet of the control electromagnetic valve 7 is connected with the outlet of the control gas N2, and the on-off of the control gas pipeline is controlled by utilizing the electromagnetic two-position three-way characteristic of the control electromagnetic valve 7.
The single working time of the torch 1 is 2-3s, the working flow is not less than 40g/s, and the torch can be repeatedly used for 5-10 times.
The excitation energy of the spark plug 2 is 12J, the excitation frequency is 100Hz, and the power supply voltage is 27 +/-3V, so that the torch 1 is ignited.
The oxygen control valve 3 is a two-position three-way normally closed valve, and the control gas is normal-temperature nitrogen through pneumatic control; when the control cavity is opened to supply control gas with certain pressure, the valve is opened, when the control gas is cut off, the valve is closed, and the discharge port is communicated with the valve outlet; the highest pressure of the inlet is 7MPaA, the opening pressure of the valve is 0.3MPaA, the closing pressure of the valve is 2-4 MPaA, the action times can exceed 300 times, and the continuous working time can exceed 20s; the nitrogen pressure of the control cavity is 5MPaA, the rated flow under the opening pressure is 23.4g/s, the valve action times can exceed 300 times, and the continuous work can exceed 20s; the leakage rate is not more than 1ml at normal temperature, and the rated flow rate is 16.5g/s at the starting pressure;
the fuel liquid valve 4 is a two-position three-way normally closed valve and is electrically controlled to be switched on or off by an outlet pipeline of the fuel pump; the highest pressure of the inlet is about 9MPaA, the opening pressure is 0.3MPaA, and the closing pressure is 2-4 MPaA; the rated flow at the opening pressure is 16.5g/s; the pressure drop of the valve is not more than 0.3MPaA; the allowed direct current voltage is 27 +/-3V, and the allowed maximum current is 1-2A; the time lag does not exceed 35ms.
The oxygen double one-way valve 5 controls the opening and closing of the valve through the pressure difference of the inlet and the outlet, and can reversely seal high-temperature fuel gas.
The combustion double one-way valve 6 controls the opening and closing of the valve through the pressure difference of the inlet and the outlet, and can reversely seal high-temperature gas.
The control solenoid valve 7 is a two-position three-way normally closed valve, and the valve is opened when the power is on and closed after the power is off through electromagnetic control, so that the on-off of the gas pipeline is controlled; the working pressure is 5MPaA; the working temperature is 260-350K; the allowed direct current voltage is 27 +/-3V, and the allowed maximum current is 1-2A; the total action times are about 300 times, and the continuous working time is not more than 100s; the air leakage of the valve under the standard state is not more than 1ml/s.
The utility model can meet certain thermal protection requirements; low-temperature thermal protection is considered for pipelines and components related to liquid oxygen media, and measures such as coating and the like can be properly taken; the cable and the connector are fully considered to be influenced by the thermal environment, and thermal protection is carried out according to the actual condition;
the requirement of measuring point arrangement can be met; can meet the requirement of temperature adaptability between minus 45 ℃ and plus 50 ℃; can meet certain requirements of vibration environment.
The utility model discloses a theory of operation does:
the inlet of the torch 1 is respectively connected with the outlet of the oxygen double check valve 5 and the outlet of the fuel double check valve 6; the opening and closing of the valve is controlled by the pressure difference of the inlet and the outlet of the oxygen/fuel double check valve; the oxygen double check valve 5 is connected with the oxygen control valve 3 through an oxidant/control gas supply pipeline, and the opening and closing of the valve are controlled through the pressure difference of an inlet and an outlet of the oxygen double check valve 5, and high-temperature fuel gas can be reversely sealed; the fuel double check valve 6 is connected with the fuel liquid valve 4 through a fuel supply pipeline, and the opening and closing of the valve are controlled through the pressure difference of the inlet and the outlet of the fuel double check valve 6, so that high-temperature fuel gas can be reversely sealed; the oxygen control valve 3 is connected with a control electromagnetic valve 7 through a control gas supply pipeline, and is connected with an oxidant pump and an oxygen cold discharge valve 8 through an oxidant supply pipeline, when the control cavity is opened to supply control gas with certain pressure, the valve is opened, when the control gas is cut off, the valve is closed, and a discharge port is communicated with a valve outlet; the fuel liquid valve 4 is communicated with a fuel pump through a fuel supply pipeline and is switched on and off through an electromagnetic control pipeline; the control electromagnetic valve 7 is communicated with the control gas storage tank through a control gas supply pipeline, the valve is opened after the power is on, and the valve is closed after the power is off.
The starting process comprises the following steps: according to a specific time sequence, firstly, the oxygen control valve 3 is opened, the liquid oxygen pipeline is connected with the supply of the oxidant, then, the spark plug 1 is electrified, finally, the fuel liquid valve 4 is electrified, the fuel supply pipeline is connected with the supply of the fuel, and finally, the oxidant and the fuel are respectively filled in a torch channel and are ignited by the igniter; the oxidant pump motor and the fuel pump rotate, the pressure after the pump gradually rises, when the pressure of a flare supply pipeline rises to 1MPa, the oxygen double check valve 5 and the flare double check valve 6 are opened under the action of the pressure difference between an inlet and an outlet, and the flare system continuously works.
Shutdown process: after the pressure continuously rises after the pump, after the oxygen double check valve 5 and the fuel double check valve 6 are opened for about 1-2s, the oxygen control valve 3 and the fuel liquid valve 4 are sequentially closed through time sequence control, and the torch system is shut down.
The utility model discloses a torch formula is igniteed the fuel in to the engine, compares in traditional powder ignition mode, can realize this purpose of igniteing many times, has satisfied the development trend that space flight delivery, manned space flight and inflation cycle engine started many times, consequently has extensive application prospect. Meanwhile, a torch system is used for ignition, the purposes of compact structure and proper weight reduction of the engine are achieved, and compared with the traditional gunpowder ignition scheme, more storage space and storage quality are provided for the oxidant and the fuel.
The above-described embodiments are merely preferred embodiments of the present invention, and the general changes and substitutions performed by those skilled in the art within the scope of the technical solution of the present invention should be included in the protection scope of the present invention.
Claims (3)
1. A torch igniter for multiple starts of a liquid rocket engine, comprising: the device comprises a torch (1), a spark plug (2), an oxygen control valve (3), a fuel liquid valve (4), an oxygen double one-way valve (5), a fuel double one-way valve (6), a control electromagnetic valve (7) and an oxygen cold discharge valve (8);
the spark plug (2) is connected with the outlet of the torch (1);
the inlet of the torch (1) is respectively connected with the outlet of the oxygen double check valve (5) and the outlet of the fuel double check valve (6);
the inlet of the oxygen double one-way valve (5) is connected with the outlet of the oxygen control valve (3);
the inlet of the fuel double check valve (6) is connected with the outlet of the fuel liquid valve (4);
the inlet of the oxygen control valve (3) is respectively connected with the outlet of the control electromagnetic valve (7) and the outlet of the oxygen cold discharge valve (8);
the oxygen cold discharge valve (8) is communicated with the liquid oxygen pipeline;
the inlet of the fuel liquid valve (4) is connected with the outlet of a fuel pump;
the fuel liquid valve (4) is an electromagnetic two-position three-way valve;
and the inlet of the control electromagnetic valve (7) is connected with the outlet of the control gas N2.
2. A liquid rocket engine multiple start torch igniter as defined in claim 1, wherein: the oxygen control valve (3) is a two-position three-way normally closed valve.
3. A liquid rocket engine multiple start torch igniter as defined in claim 1, wherein: the fuel liquid valve (4) is a two-position three-way normally closed valve.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202220659873.3U CN217582323U (en) | 2022-03-17 | 2022-03-17 | Torch igniter for multiple starting of liquid rocket engine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202220659873.3U CN217582323U (en) | 2022-03-17 | 2022-03-17 | Torch igniter for multiple starting of liquid rocket engine |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN217582323U true CN217582323U (en) | 2022-10-14 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202220659873.3U Expired - Fee Related CN217582323U (en) | 2022-03-17 | 2022-03-17 | Torch igniter for multiple starting of liquid rocket engine |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN217582323U (en) |
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2022
- 2022-03-17 CN CN202220659873.3U patent/CN217582323U/en not_active Expired - Fee Related
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|---|---|---|---|
| GR01 | Patent grant | ||
| GR01 | Patent grant | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20221014 |
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| CF01 | Termination of patent right due to non-payment of annual fee |