CN116255277A - Gas generator test system and method for gas self-pressurization liquid rocket engine - Google Patents
Gas generator test system and method for gas self-pressurization liquid rocket engine Download PDFInfo
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- CN116255277A CN116255277A CN202211628556.6A CN202211628556A CN116255277A CN 116255277 A CN116255277 A CN 116255277A CN 202211628556 A CN202211628556 A CN 202211628556A CN 116255277 A CN116255277 A CN 116255277A
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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
- F02K9/96—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof characterised by specially adapted arrangements for testing or measuring
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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
- F02K9/42—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof using liquid or gaseous propellants
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Abstract
The invention relates to a gas generator test system and method for a gas self-pressurizing liquid rocket engine, which solve the technical problem that a gas generator can hardly produce gas flow matched with a liquid attitude control rocket engine under different working conditions. The system comprises a propellant supply system, a propellant weighing and metering system, a gas generator, a gas cooling system and a gas discharge valve group, wherein the gas discharge valve group comprises a plurality of groups of gas discharge electromagnetic valves, and an outlet of at least one group of gas discharge electromagnetic valves is provided with an exhaust pore plate. The method comprises the following steps: 1. building up pressure of the gas generator; 2. the gas generator is matched with the gas self-pressurizing liquid rocket engine in working condition, so that the matching relation between the gas flow of the gas generator and the flow of the pressurizing propellant is obtained; 3. and (5) releasing pressure of the test system, and ending the test.
Description
Technical Field
The invention relates to a gas generator test system, in particular to a gas generator test system and method for a gas self-pressurization liquid rocket engine.
Background
The traditional liquid attitude control rocket engine generally adopts a high-pressure nitrogen cylinder and a pressure reducer as a pressurizing module, and the novel liquid attitude control rocket engine adopts a differential storage tank, a gas generator and a pressure stabilizer as a pressurizing module, and pressurizing propellant is stored in the pressurizing propellant storage tank. When the gas self-pressurizing liquid attitude control rocket engine works, the pressurizing propellant is catalytically decomposed and combusted in the gas generator to generate high-temperature and high-pressure gas. The high-temperature high-pressure gas is divided into two paths after regulated by a voltage stabilizer, and one path of high-temperature high-pressure gas flows to a main propellant storage tank air cavity to boost the pressure of the main propellant storage tank, so that main propellant supply required by a liquid attitude control rocket engine thrust chamber is realized; one path of the air flows to the air cavity of the pressurized propellant storage tank to pressurize the pressurized propellant storage tank, so that the supply of the pressurized propellant required by the continuous operation of the gas generator is realized.
The thrust chamber matched with the liquid attitude control rocket engine has a large thrust magnitude span range, the thrust magnitude range is milli-to-ten kilo-newtons, and the flow magnitude range of the propellant is milli-to-ten kilograms when the thrust chambers with different thrust magnitudes work. In order to meet the main propellant supply requirement of the liquid rocket engine, the gas generator is required to work normally under different working conditions so as to match the gas flow requirement of the liquid attitude control rocket engine under different working conditions. Therefore, the performance of the gas generator under different working conditions needs to be checked and tested so as to meet the performance requirement of the gas self-pressurization liquid rocket engine.
When the traditional liquid attitude control rocket engine thrust chamber is tested, the chamber pressure and the mixing ratio of the thrust chamber are generally adjusted by adjusting the pressure of a propellant storage tank, and important attention parameters include the chamber pressure, the mixing ratio, the specific impulse, the throat temperature of the thrust chamber and the like. Compared with a liquid attitude control rocket engine thrust chamber, in the test process of the gas generator, the performance such as the matching characteristics of the gas flow and the flow of the pressurizing propellant under various working conditions of the gas generator, the matching characteristics of the gas flow and the self-pressurizing liquid attitude control rocket engine under various working conditions of the gas generator and the like are required to be paid attention to besides parameters such as chamber pressure, mixing ratio, specific impulse, throat temperature of the thrust chamber and the like.
Disclosure of Invention
The invention provides a gas generator test system and method for a gas self-pressurizing liquid rocket engine, which are used for solving the technical problem that a gas generator can hardly generate gas flow matched with the liquid attitude control rocket engine under different working conditions.
The technical scheme provided by the invention is as follows:
a gas generator test system for a gas self-pressurizing liquid rocket engine is characterized in that: the device comprises a propellant supply system, a propellant weighing and metering system, a gas generator, a gas cooling system and a gas discharge valve group;
the propellant supply system comprises a propellant storage tank, a propellant storage tank pressurizing and deflating valve arranged on the propellant storage tank, a manual total supply valve, a pneumatic total supply valve, a flowmeter and a product valve which are sequentially arranged along the output direction of the propellant; the propellant tank is provided with a tank manometer for measuring the tank pressure P t ；
The propellant weighing and metering system comprises a weighing and metering device and a collecting device of a propellant storage tank, and is used for metering the weight of the propellant storage tank in the test process of the gas generator in real time so as to calculate the consumption of the propellant in the test process;
the gas generator is used for receiving the pressurized propellant provided by the propellant supply system and decomposing and combusting the pressurized propellant, a blow-off valve is connected between the gas generator and the product valve, and a generator manometer is arranged on the gas generator and is used for measuring the room pressure P of the gas generator h ；
The gas generator outlet is connected with one end of a gas discharge pipe, the other end of the gas discharge pipe is connected with a gas discharge valve group, and a gas discharge pressure gauge is arranged between the gas generator outlet and the gas discharge pipe and used for measuring the gas discharge pressure P of the gas generator outlet p ；
The gas discharge valve group comprises a plurality of groups of gas discharge electromagnetic valves, the outlet of at least one group of gas discharge electromagnetic valves is provided with an exhaust pore plate, the aperture of the exhaust pore plate and the group number of the gas discharge electromagnetic valves are set according to the gas flow rate of each working condition of the gas self-pressurizing liquid rocket engine corresponding to the gas generator test, and the gas discharge valve group is used for meeting the gas flow rate of each working condition by adjusting the group number of the gas discharge electromagnetic valves and/or the aperture of the exhaust pore plate;
the gas cooling system is used for cooling the gas discharge pipe and the gas discharge valve group.
Further, the gas cooling system comprises a cooling water cooling component and a nitrogen cooling component;
the cooling water cooling component comprises a cooling water tank arranged outside the fuel gas discharge pipe, and cooling water is arranged in the cooling water tank and used for cooling the fuel gas discharge pipe; the cooling gas discharge pipes are arranged in a tube type, so that the contact area with cooling water is increased, and the cooling effect is improved;
the nitrogen cooling assembly comprises a liquid nitrogen supply assembly and a cooling valve connected to the liquid nitrogen supply assembly and used for cooling the fuel gas discharge valve group.
Further, the gas discharge pipes are arranged in a tube type.
Further, the outlet nitrogen pressure range of the cooling valve of the nitrogen cooling assembly is 1-5 MPa.
Further, the gas emergency discharging system comprises a gas emergency discharging pipe and at least one high-temperature pneumatic valve connected in series;
further, the plurality of high-temperature pneumatic valves are arranged in series on the gas emergency discharge pipe, the opening switches of the two adjacent high-temperature pneumatic valves are connected in series, and the closing switches are connected in series, so that the plurality of high-temperature pneumatic valves are controlled by one valve pneumatic signal, a test system is simplified, and the reliability of the test system is improved.
The gas emergency discharge system is used for emergency discharge under the condition of overpressure of gas, the safety of the test system is improved, and the abnormal discharge of gas caused by internal leakage of the high-temperature discharge valves is effectively avoided by the two high-temperature pneumatic valves connected in series.
Further, the propellant supply system further comprises a filter disposed between the pneumatic total supply valve and the flow meter.
The invention also provides a gas generator test method for the gas self-pressurization liquid rocket engine, which is characterized by comprising the following steps of:
s1, building pressure of gas generator
Adjusting the pressurizing and deflating valve of the propellant storage tank to preset pressure P of the propellant storage tank t The method comprises the steps of carrying out a first treatment on the surface of the The blow-off valve is opened to charge the combustion chamber of the gas generator with pressure P 0 To the pressure in the combustion chamber of the gas generator reaches P 0 To simulate the actual working condition of the gas generator;
opening the manual total supply valve, the pneumatic total supply valve and the product valve, filling the pressurized propellant into the gas generator and generating decomposition combustion, and discharging the gas at the pressure P p Start to rise until the gas discharge pressure P p With tank pressure P t When the difference is smaller than 0.1MPa, the pressure building is finished;
s2, matching working conditions of the gas generator with the built-up pressure and the gas self-pressurizing liquid rocket engine
S2.1, switching the apertures of a plurality of groups of fuel gas discharge electromagnetic valves and the aperture of an exhaust pore plate, and matching the current working condition;
s2.2, obtaining target storage tank pressure P of the propellant storage tank under the current working condition t ' meterCalculating the chamber pressure P of the current gas generator h With target tank pressure P t ' difference;
if the target tank pressure P t ' greater than the chamber pressure P of the current gas generator h And the current tank pressure P t Subtracting the chamber pressure P of the current gas generator h Not more than 0.6MPa, regulating the pressure of the storage tank to the target pressure P of the storage tank through a propellant storage tank pressurizing and deflating valve t ′；
If the target tank pressure P t ' less than the chamber pressure P of the current gas generator h Firstly, closing a product valve, opening a fuel gas discharge valve group until the chamber pressure of a fuel gas generator is reduced to meet the target storage tank pressure P t ' greater than the chamber pressure P of the current gas generator h And the current tank pressure minus the chamber pressure P of the current gasifier h When the pressure is not more than 0.6MPa, closing the fuel gas discharge valve group, opening the product valve, and regulating the storage tank pressure to the target storage tank pressure P through the propellant storage tank pressurizing and deflating valve t ′；
Opening test, recording target storage tank pressure P in real time t ' under the propellant flow, the propellant tank weight, the gas discharge pressure P at the gas generator outlet p The chamber pressure of the gasifier;
s2.3, returning to the step S2.2, and adjusting the target storage tank pressure P t ' until the matching relation between the gas flow of the gas generator and the flow of the pressurizing propellant under the current working condition and the matching relation between the gas flow and the gas self-pressurizing liquid rocket engine are obtained under the pressure of each target storage tank;
s2.4, returning to the step S2.1, and switching the current working condition by switching the apertures of a plurality of groups of fuel gas discharge electromagnetic valves and the aperture of an exhaust pore plate;
until the matching relation between the gas flow of the gas generator and the flow of the pressurizing propellant and the matching relation between the gas flow and the self-pressurizing liquid rocket engine under each working condition are obtained;
s3, pressure relief of gas generator test system
Closing a product valve, opening a gas discharge valve group and a nitrogen cooling system, repeatedly executing a gas discharge program until the chamber pressure of the gas generator is reduced to below 0.15MPa, and closing the gas discharge valve group;
and opening the blowing-off valve, introducing nitrogen into the gas generator, and repeatedly executing the blowing-off program until the chamber pressure of the gas generator is reduced to the atmospheric pressure, and then sequentially closing the blowing-off valve, the gas discharge valve group and the cooling valve to finish the test.
Further, in step S3, the gas discharge procedure and the blow-off procedure are specifically: the gas discharge valve group is opened for 3s and closed for 20s.
The invention has the beneficial effects that:
1. the invention provides a gas generator test system for a gas self-pressurizing liquid rocket engine, which realizes that the matching characteristics of the gas flow of the gas generator and the flow of a pressurizing propellant and the matching characteristics of the gas flow and the matching characteristics of the gas self-pressurizing liquid attitude control rocket engine under various working conditions are simulated by arranging a gas discharge electromagnetic valve group and realizing the opening/closing different combination modes of exhaust pore plates with different specifications and gas discharge electromagnetic valves, and realizes the performance assessment of the gas generator.
2. According to the invention, the cooling mode of cooling water cooling and nitrogen blowing cooling is adopted to realize cooling of the high-temperature high-pressure fuel gas and fuel gas discharge electromagnetic valve bank, so that the working conditions of a fuel gas discharge assembly and a fuel gas discharge valve in the fuel gas discharge electromagnetic valve bank are effectively improved, and the reliability of a test system is improved.
3. According to the invention, the gas emergency discharge system is arranged on the gas discharge system, so that the emergency discharge of high-temperature gas under overpressure can be realized, and the safety of the test system is improved.
4. The invention adopts a way of weighing and metering the pressurized propellant in real time, and can obtain the matching characteristic of the gas flow of the gas generator and the flow of the pressurized propellant.
Drawings
FIG. 1 is a schematic illustration of an embodiment of a gasifier test system for a gas self-pressurizing liquid rocket engine in accordance with the present invention;
FIG. 2 is a schematic diagram of a gas emergency exhaust system according to an embodiment of the present invention.
The reference numerals are as follows:
1-propellant storage tank, 2-propellant storage tank pressurization and deflation valve, 3-manual total supply valve, 4-pneumatic total supply valve, 5-filter, 6-flowmeter, 7-product valve, 8-propellant weighing and metering system, 9-gas generator, 10-gas discharge manometer, 11-gas discharge pipe, 12-gas discharge valve group, 13-gas discharge solenoid valve, 14-gas discharge orifice plate, 15-blow-off valve, 16-cooling water tank, 17-cooling valve and 18-high temperature pneumatic valve.
Detailed Description
Referring to fig. 1, the present embodiment provides a gas generator test system for a gas self-pressurizing liquid rocket engine, which includes a propellant supply system, a propellant weighing and metering system 8, a gas generator 9, a gas cooling system, a gas discharge system and a gas emergency discharge system.
The propellant supply system comprises a propellant storage tank 1, a propellant storage tank pressurizing and deflating valve 2 arranged on the propellant storage tank 1, a manual total supply valve 3, a pneumatic total supply valve 4, a filter 5, a flowmeter 6 and a product valve 7 which are sequentially arranged along the output direction of the propellant; the product valve 7 can be a solenoid valve, and the supply or cut-off of the propellant required by the operation of the gas generator 9 can be realized by opening or closing the solenoid valve; the propellant tank 1 is provided with a tank manometer for measuring the tank pressure P t The method comprises the steps of carrying out a first treatment on the surface of the The propellant of the propellant tank 1 is typically hydrazine 70 or anhydrous hydrazine.
The propellant weighing and metering system 8 comprises a weighing and metering device and a collecting device of a propellant storage tank, and is used for metering the weight of the propellant storage tank in the test process of the gas generator in real time so as to calculate the consumption of the propellant in the test process.
The gas generator 9 is used for receiving the pressurized propellant provided by the propellant supply system and decomposing and combusting the pressurized propellant, a blow-off valve 15 is connected between the gas generator 9 and the product valve 7, and a generator manometer is arranged on the gas generator 9 and is used for measuring the room pressure P of the gas generator 9 h 。
The gas discharge system comprises a gas discharge pipe 11 connected with the outlet of the gas generator 9 and a gas discharge valve group 12 connected with the gas discharge pipe 11; a gas discharge manometer 10 is arranged between the outlet of the gas generator 9 and the gas discharge pipe 11 for measuringGas discharge pressure P at the outlet of the gas generator 9 p 。
The gas discharge valve group 12 comprises 6 groups of gas discharge electromagnetic valves 13, wherein the outlets of 3 groups of gas discharge electromagnetic valves 13 are provided with exhaust pore plates 14, the aperture of the exhaust pore plates 14 and the number of groups of the gas discharge electromagnetic valves 13 are set according to the gas flow of each working condition of the gas self-pressurization liquid rocket engine corresponding to the gas generator test, and the gas flow of each working condition is met by adjusting the number of groups of the gas discharge electromagnetic valves 13 and the aperture of the exhaust pore plates 14; in this embodiment, the apertures of the 3 exhaust hole plates 14 are different from each other, and the three exhaust hole plates and the gas exhaust electromagnetic valve 13 form a first exhaust unit, a second exhaust unit and a third exhaust unit respectively, so as to simulate gas flow of 0.08g/s, 0.5g/s and 6g/s, in addition, 3 groups of gas exhaust electromagnetic valves 13 are simultaneously opened to simulate gas flow of 120g/s, and the different combinations of the opening/closing states of the 3 exhaust hole plates and the 3 groups of gas exhaust electromagnetic valves 13 can realize the simulation of the operating characteristics of the gas generator 9 under 24 different working conditions of the gas self-supercharging liquid rocket engine.
The fuel gas cooling system comprises a cooling water cooling component and a nitrogen cooling component; the cooling water cooling assembly comprises a cooling water tank 16 arranged outside the gas discharge pipe 11, and cooling water is arranged between the cooling water tank 16 and the gas discharge pipe 11 and used for cooling the gas discharge pipe 11; the cooling gas discharge pipes 11 are arranged in a tube type, so that the contact area with cooling water is increased, and the cooling effect is improved; the nitrogen cooling assembly comprises a liquid nitrogen supply assembly and a cooling valve 17 connected to the liquid nitrogen supply assembly and is used for cooling the gas discharge valve group 12, and the pressure range of nitrogen at the outlet of the cooling valve 17 of the nitrogen cooling assembly is 1-5 MPa.
Referring to fig. 2, the gas emergency exhaust system includes a gas emergency exhaust pipe and two high temperature pneumatic valves 18 connected in series; the opening switches of the two high-temperature pneumatic valves 18 are connected in series, and the closing switches are connected in series, so that one valve pneumatic signal is used for controlling the two high-temperature pneumatic valves 18, a test system is simplified, and the reliability of the test system is improved; the gas emergency discharge system is used for emergency discharge under the condition of overpressure of gas, so that the safety of the test system is improved, and the abnormal discharge of gas caused by internal leakage of the high-temperature pneumatic valves 18 is effectively avoided by the two high-temperature pneumatic valves 18 connected in series.
The test flow of the gas generator test system for the gas self-pressurization liquid rocket engine comprises the following steps:
s1, building pressure of gas generator
Adjusting a propellant storage tank pressurizing and deflating valve to 3.0MPa plus or minus 0.05MPa of the preset propellant storage tank pressure; the blow-off valve 15 is opened to charge 2.4MPa plus or minus 0.05MPa nitrogen into the combustion chamber of the gas generator 9 until the pressure in the combustion chamber of the gas generator 9 reaches 2.4MPa plus or minus 0.05MPa, and the blow-off valve 15 is closed to simulate the actual working condition of the gas generator 9 of the embodiment.
The manual total supply valve 3, the pneumatic total supply valve 4 and the product valve 7 are opened, the pressurized propellant is filled into the gas generator 9 and decomposed and combusted, and the gas discharge pressure P is generated p Start to rise until the gas discharge pressure P p With tank pressure P t And when the difference is smaller than 0.1MPa, the pressure building is finished.
S2, matching working conditions of the gas generator 9 with the built-up pressure and the gas self-pressurizing liquid rocket engine
S2.1, switching the apertures of a plurality of groups of fuel gas discharge electromagnetic valves 13 and the aperture of an exhaust pore plate 14, and matching the current working condition.
S2.2, obtaining target storage tank pressure P of the propellant storage tank under the current working condition t ' calculating the chamber pressure P of the current gas generator 9 h With target tank pressure P t ' difference;
if the target tank pressure P t ' greater than the chamber pressure P of the current gas generator 9 h And the current tank pressure P t Subtracting the chamber pressure P of the current gas generator 9 h Not more than 0.6MPa, regulating the pressure of the storage tank to the target pressure P of the storage tank through a propellant storage tank pressurizing and deflating valve t ′；
If the target tank pressure P t ' less than the chamber pressure P of the current gas generator 9 h The product valve 7 is closed first and the gas discharge valve block 12 is opened until the chamber pressure of the gas generator 9 drops to meet the target tank pressure P t ' greater than the chamber pressure P of the current gas generator 9 h And the current tank pressure minus the chamber pressure P of the current gas generator 9 h When the pressure is not more than 0.6MPa, the gas discharge valve group 12 is closed, and then the pressure of the storage tank is regulated to the target storage tank pressure P through the propellant storage tank pressurizing and deflating valve t ′；
Opening test, recording target storage tank pressure P in real time t ' under the propellant flow, the propellant tank weight, the gas discharge pressure P at the outlet of the gas generator 9 p The chamber pressure of the gasifier 9.
S2.3, returning to the step S2.2, and adjusting the target storage tank pressure P t ' until the matching relation between the gas flow of the gas generator 9 and the flow of the pressurizing propellant under the current working condition and the matching relation between the gas flow and the self-pressurizing liquid rocket engine under the pressure of each target storage tank are obtained.
S2.4, returning to the step S2.1, and switching the current working condition by switching the apertures of a plurality of groups of fuel gas discharge electromagnetic valves 13 and the exhaust pore plates 14;
until the matching relation between the gas flow of the gas generator 9 and the flow of the pressurizing propellant is obtained under each working condition, the matching relation between the gas flow and the self-pressurizing liquid rocket engine is obtained.
If the gas pressure is too high in the test process, the control console is used for opening the gas emergency discharge system to realize emergency pressure relief of the gas.
S3, pressure relief of gas generator test system
Closing the product valve 7, opening the gas discharge valve group 12 and the nitrogen cooling system, repeatedly executing a gas discharge program, opening the gas discharge valve group 12 for 3s, closing for 20s until the chamber pressure of the gas generator 9 is reduced to below 0.15MPa, and closing the gas discharge valve group 12;
the blow-off valve 15 was opened, nitrogen was introduced into the gas generator 9 and the blow-off procedure was repeatedly performed, the gas discharge valve group 12 was opened for 3s, and closed for 20s, until after the chamber pressure of the gas generator 9 was reduced to atmospheric pressure, the blow-off valve 15, the gas discharge valve group 12 and the cooling valve 17 were sequentially closed, and the test was ended.
Claims (9)
1. A gas generator test system for gas self-pressurization liquid rocket engine, its characterized in that: the device comprises a propellant supply system, a propellant weighing and metering system (8), a gas generator (9), a gas cooling system and a gas discharge valve group (12);
the propellant supply system comprises a propellant storage tank (1), a propellant storage tank pressurizing and deflating valve (2) arranged on the propellant storage tank (1), a manual total supply valve (3), a pneumatic total supply valve (4), a flowmeter (6) and a product valve (7) which are sequentially arranged along the output direction of the propellant; the propellant storage tank (1) is provided with a storage tank manometer for measuring the storage tank pressure P t ；
The propellant weighing and metering system (8) comprises a weighing and metering device and a collecting device of a propellant storage tank (1) and is used for metering the weight of the propellant storage tank (1) in the test process in real time so as to calculate the consumption of the propellant in the test process;
the gas generator (9) is used for receiving the pressurized propellant provided by the propellant supply system and decomposing and combusting the pressurized propellant, a blow-off valve (15) is connected between the gas generator (9) and the product valve (7), and a generator manometer is arranged on the gas generator (9) and is used for measuring the room pressure P of the gas generator (9) h ；
The outlet of the gas generator (9) is connected with one end of a gas discharge pipe (11), the other end of the gas discharge pipe (11) is connected with a gas discharge valve group (12), a gas discharge pressure gauge (10) is arranged between the outlet of the gas generator (9) and the gas discharge pipe (11) and is used for measuring the gas discharge pressure P of the outlet of the gas generator (9) p ；
The gas discharge valve group (12) comprises a plurality of groups of gas discharge electromagnetic valves (13), and the outlet of at least one group of gas discharge electromagnetic valves (13) is provided with an exhaust pore plate (14) for meeting the gas flow of each working condition by adjusting the group number of the gas discharge electromagnetic valves (13) and/or the pore diameter of the exhaust pore plate (14);
the gas cooling system is used for cooling the gas discharge pipe (11) and the gas discharge valve group (12).
2. A gasifier test system for a gas self-pressurizing liquid rocket engine as recited in claim 1, wherein:
the fuel gas cooling system comprises a cooling water cooling component and a nitrogen cooling component;
the cooling water cooling component comprises a cooling water tank (16) arranged outside the fuel gas discharge pipe (11), and cooling water is arranged in the cooling water tank (16) and used for cooling the fuel gas discharge pipe (11);
the nitrogen cooling assembly comprises a liquid nitrogen supply assembly and a cooling valve (17) connected to the liquid nitrogen supply assembly for cooling the gas discharge valve group (12).
3. A gasifier test system for a gas self-pressurizing liquid rocket engine according to claim 2, wherein:
the gas discharge pipes (11) are arranged in a tube type.
4. A gasifier test system for a gas self-pressurizing liquid rocket engine according to claim 3, wherein:
the outlet nitrogen pressure range of the cooling valve (17) of the nitrogen cooling assembly is 1-5 MPa.
5. A gas generator testing system for a gas self-pressurizing liquid rocket engine according to any of claims 1-4, wherein:
the system also comprises a gas emergency discharge system, wherein the gas emergency discharge system comprises a gas emergency discharge pipe and at least one high-temperature pneumatic valve (18).
6. A gasifier test system for a gas self-pressurizing liquid rocket engine as recited in claim 5, wherein:
the high-temperature pneumatic valves (18) are arranged in series on the gas emergency discharge pipe, the opening switches of two adjacent high-temperature pneumatic valves (18) are connected in series, and the closing switches are connected in series and are used for controlling the high-temperature pneumatic valves (18) by pneumatic signals of one valve.
7. The gasifier test system for a gas self-pressurizing liquid rocket engine as recited in claim 6, wherein:
the propellant supply system further comprises a filter (5), the filter (5) being arranged between the pneumatic total supply valve (4) and the flow meter (6).
8. A gas generator testing method for a gas self-pressurizing liquid rocket engine, characterized by comprising the following steps based on the gas generator testing system for a gas self-pressurizing liquid rocket engine as recited in claim 1:
s1, building pressure of gas generator
Adjusting the propellant storage tank pressurizing and deflating valve (2) to preset storage tank pressure P t The method comprises the steps of carrying out a first treatment on the surface of the The blowing valve (15) is opened to charge the combustion chamber of the gas generator (9) with the pressure P 0 To the pressure in the combustion chamber of the gas generator (9) reaches P 0 To simulate the actual condition of the gas generator (9);
opening a manual total supply valve (3), a pneumatic total supply valve (4) and a product valve (7), filling the pressurized propellant into a gas generator (9) and generating decomposition combustion, and discharging the gas at a pressure P p Start to rise until the gas discharge pressure P p With tank pressure P t When the difference is smaller than 0.1MPa, the pressure building is finished;
s2, matching working conditions of the gas generator (9) with the built-up pressure and the gas self-pressurizing liquid rocket engine
S2.1, switching the apertures of a plurality of groups of fuel gas discharge electromagnetic valves (13) and exhaust pore plates (14), and matching the current working condition;
s2.2, obtaining the target storage tank pressure P of the propellant storage tank (1) under the current working condition t ' calculating the chamber pressure P of the current gas generator (9) h With target tank pressure P t ' difference;
if the target tank pressure P t ' greater than the chamber pressure P of the current gas generator (9) h And the current tank pressure P t Subtracting the chamber pressure P of the current gas generator (9) h Not more than 0.6MPa, the pressure of the propellant storage tank is regulated to the target storage tank pressure P through a propellant storage tank pressurizing and deflating valve (2) t ′；
If the target tank pressure P t ' smaller than the chambers of the current gas generator (9)Pressure P h The product valve (7) is closed first, and the gas discharge valve group (12) is opened until the chamber pressure of the gas generator (9) is reduced to meet the target storage tank pressure P t ' greater than the chamber pressure P of the current gas generator (9) h And the current tank pressure minus the chamber pressure P of the current gas generator (9) h When the pressure is not more than 0.6MPa, the gas discharge valve group (12) is closed, the product valve (7) is opened, and then the storage tank pressure is regulated to the target storage tank pressure P through the propellant storage tank pressurizing and deflating valve (2) t ′；
Opening test, recording target storage tank pressure P in real time t ' under the ' position ', the propellant flow, the weight of the propellant storage tank (1), the gas discharge pressure P of the outlet of the gas generator (9) p The chamber pressure of the gas generator (9);
s2.3, returning to the step S2.2, and adjusting the target storage tank pressure P t ' until the matching relation between the gas flow of the gas generator (9) and the flow of the pressurizing propellant under the current working condition and the matching relation between the gas flow and the self-pressurizing liquid rocket engine under the pressure of each target storage tank are obtained;
s2.4, returning to the step S2.1, and switching the current working condition by switching the apertures of a plurality of groups of fuel gas discharge electromagnetic valves (13) and the exhaust pore plates (14);
until the matching relation between the gas flow of the gas generator (9) and the flow of the pressurizing propellant and the matching relation between the gas flow and the self-pressurizing liquid rocket engine are obtained under all working conditions;
s3, pressure relief of gas generator test system
Closing a product valve, opening a gas discharge valve group (12) and a nitrogen cooling system, repeatedly executing a gas discharge program until the chamber pressure of the gas generator (9) is reduced to below 0.15MPa, and closing the gas discharge valve group (12);
and opening the blowing-off valve (15), introducing nitrogen into the gas generator (9), and repeatedly executing the blowing-off procedure until the chamber pressure of the gas generator (9) is reduced to the atmospheric pressure, and then sequentially closing the blowing-off valve (15), the gas discharge valve group (12) and the cooling valve (17), thereby ending the test.
9. The method for gasifier testing of a gas self-pressurizing liquid rocket engine as recited in claim 8, wherein:
in step S3, the gas discharge procedure and the blow-off procedure are specifically: the gas discharge valve group (12) is opened for 3s and closed for 20s.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
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| CN117569948A (en) * | 2023-11-23 | 2024-02-20 | 北京天兵科技有限公司 | Pressurizing conveying system, liquid carrier rocket and control method of pressurizing conveying system |
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| CN117569948A (en) * | 2023-11-23 | 2024-02-20 | 北京天兵科技有限公司 | Pressurizing conveying system, liquid carrier rocket and control method of pressurizing conveying system |
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