A liquid oxygen kerosene gas generator extrusion test system and method

Abstract

The present invention relates to a liquid oxygen-kerosene gas generator extrusion test system and method, including an oxidant supply system, a fuel supply system, a combustion component system and a purge system; the combustion component system includes a gas generator, a turbine cover, a powder starter, a pyrotechnic igniter, and an exhaust pipe, the inlet of the turbine cover is respectively connected to the gas generator and the powder starter, the outlet of the turbine cover is connected to the exhaust pipe, and the center of the gas generator head is connected to the pyrotechnic igniter; the oxidant supply system inputs oxidant into the gas generator, and the gas supply system inputs combustion agent into the gas generator; the purge system purges the pipeline. The present invention has been verified by hot test, and the working characteristics of the gas generator in the engine state environment, the flow characteristics of high-temperature fuel gas in the turbine cavity, the forced starting characteristics of the powder starter and the relay working characteristics of the gas generator are obtained, and at the same time, data support is provided for the determination of the ignition and starting scheme of the whole machine.

Description

Technical Field

[0001] The invention belongs to the technical field of liquid rocket engines and relates to an extrusion test system and method for a liquid oxygen, kerosene and fuel gas generator. Background Art

[0002] The gas generator is an important component of a pump-type liquid rocket engine. The high-temperature gas it produces drives the turbine to do work. During the engine design and development phase, the working performance and combustion stability of the gas generator are assessed through test runs.

[0003] At present, the extrusion test scheme is generally used for the test run of gas generators. Usually, the test bench tank is connected to the gas generator through a pipeline, and the inlet pressure is adjusted to achieve flow control. The gas is discharged through the throat during operation. This method can test the stable working performance of the gas generator. However, when the gas generator is started and ignited, a very high pressure flow peak will appear, and it is difficult to achieve precise control of the starting timing under different working conditions. The product is prone to severe ablation and damage. This test method cannot simulate the flow of the outlet gas in the turbine cavity, and cannot simulate the ignition and start-up of the gunpowder starter and the relay work of the gas generator. Another method is to conduct a joint test and assessment of the gas generator-turbine pump. The large flow propellant of the main system is recovered to the tank through the pipeline after the pump. The test system is complex, the cost is high, and the test safety risk is high. Summary of the invention

[0004] The technical problem solved by the present invention is: to overcome the deficiencies of the prior art, the present invention provides a liquid oxygen kerosene gas generator extrusion test system and method, to examine and study the working characteristics of the gas generator in an engine state environment.

[0005] The technical solution of the present invention is as follows: a liquid oxygen kerosene gas generator extrusion test system, including an oxidant supply system, a fuel supply system, a combustion component system and a blow-off system;

[0006] The combustion assembly system includes a gas generator, a turbine cover, a powder starter, a pyrotechnic igniter, and an exhaust pipe. The inlet of the turbine cover is connected to the gas generator and the powder starter respectively, the outlet of the turbine cover is connected to the exhaust pipe, and the center of the gas generator head is connected to the pyrotechnic igniter.

[0007] The oxidant supply system inputs oxidant into the gas generator, and the fuel gas supply system inputs combustion agent into the gas generator; the purge system purges the pipeline.

[0008] Furthermore, the oxidant supply system includes an oxidant isolation valve, an oxidant auxiliary valve, an oxidant cavitation tube, an oxidant one-way valve and an oxidant pre-cooling discharge valve; the oxidant isolation valve, the oxidant auxiliary valve, the oxidant cavitation tube, and the oxidant one-way valve are connected in sequence along the propellant flow direction; an oxidant pre-cooling discharge valve and a discharge pipeline are arranged on the pipeline between the oxidant isolation valve and the oxidant auxiliary valve; the oxidant one-way valve is connected to the oxidant inlet pipe of the gas generator.

[0009] Furthermore, the fuel supply system includes a fuel isolation valve, a fuel cavitation pipe, a fuel auxiliary valve, a fuel check valve and a fuel discharge valve, wherein the fuel isolation valve, the fuel cavitation pipe, the fuel auxiliary valve and the fuel check valve are sequentially connected along the flow direction of the fuel agent; a fuel discharge valve and a discharge pipeline are arranged on the pipeline between the fuel isolation valve and the fuel auxiliary valve; the fuel check valve is connected to the fuel inlet pipe of the gas generator;

[0010] Furthermore, the purge system includes an oxidant purge valve; the oxidant purge valve is connected to a portion of the gas generator head near the oxidant one-way valve; and the oxidant purge valve is connected to a purge gas source via a purge pipeline.

[0011] Furthermore, the purge system also includes a fuel purge valve; the fuel purge valve is arranged on the pipeline between the fuel auxiliary valve and the fuel one-way valve; the fuel purge valve is connected to the purge gas source through the purge pipeline.

[0012] The extrusion test method using the liquid oxygen kerosene gas generator extrusion test system comprises:

[0013] Carry out filling and blowing test before commissioning;

[0014] Carry out nitrogen replacement, purge and pre-cooling filling of the oxidant supply system;

[0015] According to the test control sequence, the gas generator ignition test is carried out under different operating conditions.

[0016] Furthermore, the filling and blowing test before commissioning includes:

[0017] Carry out water medium filling test of fuel supply system to obtain filling characteristic parameters of fuel supply system under different working conditions; obtain filling characteristic parameters of fuel supply system under the supply conditions of real propellant test bench based on test data and simulation calculation;

[0018] Conduct liquid oxygen filling test on the oxidant supply system to obtain filling characteristic parameters of the oxidant supply system under different working conditions;

[0019] Carry out gas generator purge test: single-path purge of oxidant path, single-path purge of fuel path, double-path purge of oxidant path and fuel path, respectively, to obtain the purge gas source pressure P1 under strong purge, the purge gas source pressure P2 under weak purge, the gas generator oxidant pre-spray pressure, and the gas generator fuel pre-spray pressure.

[0020] Further, the nitrogen replacement of the oxidant supply system comprises:

[0021] Open the oxidant precooling discharge valve, blow nitrogen from the blow-off port of the oxidant isolation valve, and replace the pipeline between the oxidant isolation valve and the oxidant auxiliary valve with nitrogen. The blow-off time should be no less than 1 minute.

[0022] The oxidant supply system is blown off, comprising:

[0023] Open the oxidant auxiliary valve, close the oxidant precooling discharge valve, and blow nitrogen from the blow-off port of the oxidant isolation valve. The blow-off time should be no less than 1 minute. After the blow-off is completed, close the oxidant auxiliary valve and open the oxidant precooling discharge valve.

[0024] The oxidant supply system is precooled and filled, comprising:

[0025] Open the purge gas source with a purge pressure of P1, and purge the oxidant and fuel from the gas generator head cavity; open the oxidant isolation valve, and precool the pipeline between the oxidant auxiliary valve and the storage tank of the propellant test bench. When the outlet temperature of the oxidant precooling discharge valve is not higher than -150°C, the precooling filling is completed.

[0026] Furthermore, the test run control sequence includes:

[0027] At -10s, the control signal is triggered, the test control sequence is entered, and the acquisition system starts working;

[0028] At 0s, the gunpowder starter ignites;

[0029] At time t1, the pyrotechnic igniter ignites;

[0030] At time t2, the oxidant auxiliary valve is opened, and liquid oxygen fills the gas generator head chamber;

[0031] At time t3, the fuel auxiliary valve is opened, kerosene is filled into the gas generator, and the gas generator is ignited;

[0032] At 10 seconds, close the oxidant auxiliary valve and open the oxidant precooling discharge valve at the same time. As the pressure in the gas generator chamber drops, the oxidant purge valve automatically opens to purge the oxidant cavity of the gas generator.

[0033] At 10s+t4, the fuel auxiliary valve and the fuel isolation valve are closed, and the fuel purge valve is automatically opened to purge the fuel cavity of the gas generator;

[0034] At 15 seconds, close the oxidant isolation valve and fuel isolation valve;

[0035] At 20s+t4, the control and acquisition system stops working.

[0036] Furthermore, the liquid oxygen-kerosene gas generator extrusion test method also includes a post-processing process after the gas generator ignition test, including:

[0037] Open the fuel drain valve and blow nitrogen through the fuel isolation valve blow-off port;

[0038] Open the oxidant auxiliary valve, close the oxidant precooling discharge valve, blow nitrogen at the blow-off port of the oxidant isolation valve for no less than 1 minute, then open the oxidant precooling discharge valve, close the oxidant auxiliary valve, and continue blowing nitrogen. Stop blowing nitrogen after the oxidant supply system returns to ambient temperature.

[0039] The advantages of the present invention compared with the prior art are:

[0040] (1) The method of the present invention adopts a combined ignition scheme of a gas generator and a turbine cover during the test run, which can effectively obtain the working characteristics of the gas generator in an engine state environment and the flow characteristics of the high-temperature fuel gas in the turbine cavity. Compared with the turbine pump joint test scheme, the system is simple, low-cost, safe and reliable.

[0041] (2) The test system of the present invention adopts a real engine auxiliary system and adopts a combined starting and ignition scheme of a gas generator and a gunpowder starter. Compared with a single extrusion test scheme, it can effectively simulate the starting and filling conditions of the auxiliary system and simulate the forced starting of the gunpowder starter and the relay working characteristics of the gas generator.

[0042] (3) The present invention determines the test sequence and start-up plan through simulation calculation of the start-up process, cold adjustment test, and blow-off test, including pre-cooling, blow-off sequence, start-up, and shutdown sequence, etc. It is accurate and reliable in simulating the start-up process of the gas generator.

[0043] (4) The present invention sets a cavitation tube at the entrance of the test system to control the flow rate accurately, eliminate the problem of excessive starting flow rate, and prevent serious ablation and damage to the product. Compared with the flow regulator, the structure is simple and reliable.

[0044] (5) The gas generator head cavity of the present invention is provided with a purge system, which performs protective purge before starting, performs propellant emulsification purge during the starting filling process, and purges residual propellant during the shutdown process. The starting process is safe and reliable, and the post-test processing is simple. A pneumatic control valve is provided, which can be opened multiple times to complete multi-condition test runs, and the test efficiency and quality are high. BRIEF DESCRIPTION OF THE DRAWINGS

[0045] Figure 1 It is a schematic diagram of the liquid oxygen-kerosene gas generator extrusion test system of the present invention.

[0046] Figure 1 Middle: 1 gas generator, 2 turbine cover, 3 exhaust pipe, 4 gunpowder starter, 5 pyrotechnic igniter, 6 oxidizer cavitation tube, 7 fuel cavitation tube, 8 fuel auxiliary valve, 9 oxidizer auxiliary valve, 10 oxidizer blow-off valve, 11 fuel blow-off valve, 12 oxidizer check valve, 13 fuel check valve, 14 oxidizer precooling discharge valve, 15 oxidizer isolation valve, 16 fuel isolation valve, 17 fuel discharge valve

[0047] Figure 2 This is a timing diagram of the extrusion test control of the liquid oxygen-kerosene gas generator of the present invention.

[0048] Figure 3 This is a curve chart of the rising parameters such as chamber pressure and pre-spray pressure of a gas generator extrusion test. DETAILED DESCRIPTION

[0049] The present invention is described with reference to the accompanying drawings.

[0050] The present invention provides a liquid oxygen-kerosene gas generator extrusion test system and method, which is used to evaluate and study the working characteristics of the gas generator in an engine state environment. It includes evaluating the filling characteristics of the auxiliary system; the start-up and shutdown sequence of the gas generator; the performance and combustion stability of the gas generator under different working conditions; the flow characteristics of high-temperature gas in the turbine cavity, the forced start-up characteristics of the gunpowder starter and the relay working characteristics of the gas generator, etc.

[0051] like Figure 1 As shown, the liquid oxygen-kerosene gas generator extrusion test system includes a gas generator 1, a turbine cover 2, an exhaust pipe 3, a gunpowder starter 4, a pyrotechnic igniter 5, an oxidizer cavitation tube 6, a fuel cavitation tube 7, a fuel auxiliary valve 8, an oxidizer auxiliary valve 9, an oxidizer blow-off valve 10, a fuel blow-off valve 11, an oxidizer check valve 12, a fuel check valve 13, an oxidizer pre-cooling discharge valve 14, an oxidizer isolation valve 15, a fuel isolation valve 16, etc.

[0052] The liquid oxygen-kerosene gas generator extrusion test system includes the oxidant supply system, fuel supply system, combustion component system and blow-off system.

[0053] The oxidant supply system includes an oxidant isolation valve 15, an oxidant auxiliary valve 9, an oxidant cavitation tube 6, an oxidant one-way valve 12 and an oxidant precooling discharge valve 14; the oxidant supply system is, in order from the propellant flow direction, an oxidant isolation valve 15, an oxidant auxiliary valve 9, an oxidant cavitation tube 6, an oxidant one-way valve 12, and the oxidant is connected by a thread through a pipeline. An oxidant precooling discharge valve 14 and a discharge pipeline are arranged on the pipeline between the oxidant isolation valve 15 and the oxidant auxiliary valve 9. The oxidant one-way valve 12 is connected to the oxidant inlet pipe of the gas generator 1.

[0054] The fuel supply system includes a fuel isolation valve 16, a fuel cavitation pipe 7, a fuel auxiliary valve 8, a fuel check valve 13 and a fuel discharge valve 17. The fuel supply system includes the fuel isolation valve 16, the fuel cavitation pipe 7, the fuel auxiliary valve 8, the fuel check valve 13 in the direction of propellant flow, and the fuel supply system is connected by threads through pipelines. The fuel discharge valve 17 and the discharge pipeline are arranged on the pipeline between the fuel isolation valve 16 and the fuel auxiliary valve 8. The fuel check valve 13 is connected to the fuel inlet pipe of the gas generator 1.

[0055] The combustion assembly system includes a gas generator 1, a turbine cover 2, a powder starter 4, a pyrotechnic igniter 5, and an exhaust pipe 3. The turbine cover has two inlets, one connected to the gas generator through a flange, and the other welded to the powder starter. The exhaust pipe is welded to the turbine cover outlet, and the pyrotechnic igniter is welded to a hole punched in the center of the head of the gas generator 1.

[0056] The purge system includes an oxidant purge valve 10 and a fuel purge valve 11. The oxidant purge valve 10 is punched and welded at the head of the gas generator 1 near the oxidant check valve 12. The fuel purge valve 11 is arranged on the pipeline between the fuel auxiliary valve 8 and the fuel check valve 13. The oxidant purge valve 10 and the fuel purge valve 11 are connected to the purge gas source through the purge pipeline.

[0057] The gas generator extrusion test system simulates the high-temperature gas flow process. Fuel auxiliary valve 8 and oxidizer auxiliary valve 9 are set at the entrance of the oxidizer and fuel paths. Both are pneumatic control valves, which can be opened and closed multiple times to achieve multiple ignition tests. Oxidizer cavitation tube 6 and fuel cavitation tube 7 are set in the oxidizer and fuel paths, which can realize accurate control of propellant flow and eliminate starting overshoot. Oxidizer and fuel blow-off are set in the head cavity of the gas generator 1. Protective blow-off is performed before starting work, propellant emulsification blow-off is performed during the starting filling process, and residual propellant is blown off during the shutdown process. Protective blow-off during startup can prevent the temperature of the fuel assembly adjacent to liquid oxygen from being too low. Auxiliary system check valves (oxidizer check valve 12 and fuel check valve 13) are set to prevent the gas generated by the gunpowder starter 4 from backflowing during startup. Oxidizer pre-cooling discharge valve 14 is set at the entrance of the oxidizer path. Through pre-cooling discharge, the oxidizer inlet temperature meets the requirements. The fuel path medium is a normal temperature propellant, and flange-rubber ring and cone-rubber ring are used for sealing. The oxidant line is cryogenic liquid oxygen and is sealed with a step-type copper gasket. The sealing structure is simple, reliable and has good reusability.

[0058] Through cold adjustment filling test and simulation calculation, the starting filling characteristics of propellant under multiple working conditions are obtained, and the starting working sequence is determined. Through the gas generator blow-off test and cold adjustment test, the blow-off pressure and flow rate are determined. According to the engine extrusion test system and pre-test preparation work in the present invention, the working procedure of the engine starting process is designed: first, the gunpowder starter 4 ignites and works, and the high-temperature gas is discharged through the turbine cover 2 and the exhaust pipe 3, and the pressure is built up in the gas generator 1. Then the pyrotechnic igniter 5 ignites and works, forming a stable flame in the middle of the combustion chamber of the gas generator 1. Then the oxidant auxiliary valve 9 is opened, and liquid oxygen fills the oxidant auxiliary system pipeline and reaches the head cavity of the gas generator 1. Then the fuel auxiliary valve 8 is opened, and kerosene reaches the head cavity through the fuel auxiliary system pipeline and the gas generator 1 cooling jacket. Kerosene enters the gas generator 1 and ignites, and the gas generator chamber pressure and pre-spray pressure rise rapidly. After that, the gas generator 1 and the gunpowder starter 4 overlap and work. After the gunpowder starter 4 finishes working, the gas generator 1 works alone in a stable working condition.

[0059] The extrusion test method of liquid oxygen-kerosene gas generator includes: filling and blowing test before test, pre-test preparation, ignition test and post-test treatment.

[0060] Among them, the filling and blowing test before trial run is divided into three steps.

[0061] The first step is to conduct a water medium filling test on the fuel supply system. The filling characteristic parameters of the fuel system under different working conditions are obtained. Combining the test data and simulation calculations, the filling characteristic parameters of the fuel system under the supply conditions of the real propellant test bench are obtained.

[0062] The second step is to test the liquid oxygen filling of the oxidant supply system to obtain the filling characteristic parameters of the oxidant circuit under different working conditions.

[0063] The third step is the gas generator purge test. Perform single-path purge of the oxidant path, single-path purge of the fuel path, and dual-path purge of the oxidant path and the fuel path. Obtain the purge gas source pressure P1 under strong purge (large flow rate, flow rate is 50-60g / s), the purge gas source pressure P2 under weak purge (small flow rate, flow rate is 5-10g / s), the gas generator oxidant pre-spray pressure, and the gas generator fuel pre-spray pressure.

[0064] The preparation work before the test run is divided into three steps.

[0065] The first step is to replace the oxidant supply system with nitrogen. Open the oxidant precooling discharge valve 14, blow nitrogen from the blow-off port of the oxidant isolation valve 15, and replace the pipeline between the oxidant isolation valve 15 and the oxidant auxiliary valve 9 with nitrogen. The blowing time is not less than 1 minute.

[0066] The second step is to purge the oxidant supply system. Open the oxidant auxiliary valve 9, close the oxidant precooling discharge valve 14, and blow nitrogen from the purge port of the oxidant isolation valve 15. The purge time is not less than 1 minute. After the purge is completed, close the oxidant auxiliary valve 9 and open the oxidant precooling discharge valve 14.

[0067] The third step is precooling and filling of the oxidant supply system. Open the purge gas source, the purge pressure is P1 (in MPa), and purge the oxidant and fuel from the head cavity of the gas generator 1. Open the oxidant isolation valve 15, precool the pipeline between the oxidant auxiliary valve 9 and the tank of the propellant test bench, and the precooling filling is completed when the outlet temperature of the oxidant precooling discharge valve 14 is not higher than -150℃.

[0068] The test run procedure is as follows:

[0069] according to Figure 2 The test control sequence is shown below.

[0070] -10s, the control signal is triggered, the timing is entered, and the acquisition system starts working;

[0071] 0s, the gunpowder starter 4 ignites;

[0072] At time t1, the pyrotechnic igniter 5 ignites;

[0073] At time t2, the oxidant auxiliary valve 9 is opened, and liquid oxygen fills the head chamber of the gas generator 1;

[0074] At time t3, the fuel sub-valve 8 is opened, kerosene is filled into the gas generator 1, and the gas generator 1 is ignited.

[0075] 10s, close the oxidant auxiliary valve 9, and open the oxidant precooling discharge valve 14 at the same time. As the pressure in the gas generator chamber drops, the oxidant purge valve 10 automatically opens to purge the oxidant cavity of the gas generator 1;

[0076] At 10s+t4, the fuel auxiliary valve 8 and the fuel isolation valve 16 are closed, and the fuel purge valve 11 is automatically opened to purge the fuel cavity of the gas generator 1;

[0077] 15s, close the oxidant isolation valve 15 and the fuel isolation valve 16;

[0078] At 20s+t4, the acquisition system stops working.

[0079] 0 <t1<t2<t3<10s,0<t4<5s。

[0080] According to the actual working conditions and requirements of the engine, different operating test conditions are set, including rated operating conditions, a series of high and low flow conditions (set according to test requirements), and a series of high and low operating condition mixing ratios (set according to test requirements).

[0081] The post-test processing process is as follows:

[0082] Open the fuel discharge valve 17, blow nitrogen at the blow-off port of the fuel isolation valve 16 to accelerate the discharge of kerosene in the pipeline between the fuel sub-valve 8 and the fuel isolation valve 16; open the oxidant sub-valve 9, close the oxidant pre-cooling discharge valve 14, blow nitrogen at the blow-off port of the oxidant isolation valve 15 to accelerate the discharge of liquid oxygen in the pipeline between the oxidant sub-valve 9 and the oxidant check valve 12. The blowing time should be no less than 1 minute. Then open the oxidant pre-cooling discharge valve 14, close the oxidant sub-valve 9, and continue blowing nitrogen. After the oxidant supply system returns to ambient temperature, stop blowing nitrogen.

[0083] Example:

[0084] The liquid oxygen kerosene gas generator extrusion test system and method have been verified through multiple ignition tests. Figure 2 The test control sequence, the change curves of the gas generator 1 chamber pressure, the gas generator 1 pre-spray pressure, and the pyrotechnic igniter 5 chamber pressure during a test run are as follows: Figure 3As shown. At 0s, after the gunpowder starter 1 issues the ignition command, the chamber pressure of the gas generator 1 and the pre-spray pressure of the gas generator 1 begin to climb. At t1s, the pyrotechnic igniter 5 issues the ignition command, and at t2s, the oxidant auxiliary valve 9 opens, and liquid oxygen begins to fill into the head cavity of the gas generator 1 and builds pressure to maintain stability. At t3s, the fuel auxiliary valve 8 opens, kerosene enters the gas generator 1 and ignites, and the chamber pressure of the gas generator 1 and the pre-spray pressure of the gas generator 1 rise rapidly. Thereafter, the gas generator 1 and the gunpowder starter 4 overlap to work. After reaching the peak, the chamber pressure of the gas generator 1 drops rapidly, and then the chamber pressure of the gas generator 1 and the pre-spray pressure of the gas generator 1 reach the steady-state value and remain until shutdown. Through the test run, the ignition working characteristics and steady-state working performance of the gas generator 1 under different working conditions were obtained, especially the working characteristics of the gas generator 1 in the engine state environment, and the expected test run purpose was achieved.

[0085] The contents not described in detail in the specification of the present invention belong to the common knowledge of those skilled in the art.

Claims

1. A liquid oxygen, kerosene and gas generator extrusion test method, wherein the liquid oxygen, kerosene and gas generator extrusion test system used in the method comprises: An oxidant supply system, a fuel supply system, a combustion component system and a blow-off system; wherein the combustion component system comprises a gas generator (1), a turbine cover (2), a powder starter (4), a pyrotechnic igniter (5) and an exhaust pipe (3); the inlet of the turbine cover (2) is respectively connected to the gas generator (1) and the powder starter (4); the outlet of the turbine cover (2) is connected to the exhaust pipe (3); the center of the head of the gas generator (1) is connected to the pyrotechnic igniter (5); the oxidant supply system inputs oxidant into the gas generator (1); the fuel supply system inputs fuel into the gas generator (1); the blow-off system blows off the pipeline; The invention is characterized by comprising: Carry out filling and blowing test before commissioning; Carry out nitrogen replacement, purge and pre-cooling filling of the oxidant supply system; According to the test control sequence, the gas generator ignition test is carried out under different working conditions; The different working conditions include rated working conditions, a series of high and low flow working conditions, and a series of high and low working condition mixed ratios. The high and low flow working conditions are set according to the test requirements, and the high and low working condition mixed ratios are set according to the test requirements. Filling and blowing test before commissioning, including: Carry out water medium filling test of fuel supply system to obtain filling characteristic parameters of fuel supply system under different working conditions; obtain filling characteristic parameters of fuel supply system under the supply conditions of real propellant test bench based on test data and simulation calculation; Conduct liquid oxygen filling test on the oxidant supply system to obtain filling characteristic parameters of the oxidant supply system under different working conditions; Carry out gas generator purge test: single-path purge of oxidant path, single-path purge of fuel path, double-path purge of oxidant path and fuel path, respectively, to obtain the purge gas source pressure P1 under strong purge, the purge gas source pressure P2 under weak purge, the gas generator oxidant pre-spray pressure, and the gas generator fuel pre-spray pressure.

2. A liquid oxygen kerosene gas generator extrusion test method according to claim 1, characterized in that: The oxidant supply system comprises an oxidant isolation valve (15), an oxidant auxiliary valve (9), an oxidant cavitation tube (6), an oxidant non-return valve (12) and an oxidant pre-cooling discharge valve (14); the oxidant isolation valve (15), the oxidant auxiliary valve (9), the oxidant cavitation tube (6) and the oxidant non-return valve (12) are connected in sequence along the flow direction of the propellant; the oxidant pre-cooling discharge valve (14) and the discharge pipeline are arranged on the pipeline between the oxidant isolation valve (15) and the oxidant auxiliary valve (9); the oxidant non-return valve (12) is connected to the oxidant inlet pipe of the gas generator (1).

3. The liquid oxygen-kerosene gas generator extrusion test method according to claim 1, characterized in that: The fuel supply system comprises a fuel isolation valve (16), a fuel cavitation pipe (7), a fuel auxiliary valve (8), a fuel check valve (13) and a fuel discharge valve (17); the fuel isolation valve (16), the fuel cavitation pipe (7), the fuel auxiliary valve (8) and the fuel check valve (13) are connected in sequence along the flow direction of the fuel agent; the fuel discharge valve (17) and the discharge pipeline are arranged on the pipeline between the fuel isolation valve (16) and the fuel auxiliary valve (8); and the fuel check valve (13) is connected to the fuel inlet pipe of the gas generator (1).

4. A liquid oxygen kerosene gas generator extrusion test method according to claim 2, characterized in that: The purge system comprises an oxidant purge valve (10); a portion of the head of the gas generator (1) close to the oxidant check valve (12) is connected to the oxidant purge valve (10); and the oxidant purge valve (10) is connected to a purge gas source via a purge pipeline.

5. The liquid oxygen-kerosene gas generator extrusion test method according to claim 3, characterized in that: The purge system further comprises a fuel purge valve (11); the fuel purge valve (11) is arranged on the pipeline between the fuel auxiliary valve (8) and the fuel check valve (13); the fuel purge valve (11) is connected to a purge gas source via a purge pipeline.

6. The liquid oxygen-kerosene gas generator extrusion test method according to claim 1, characterized in that: The nitrogen replacement of the oxidant supply system comprises: Open the oxidant precooling discharge valve (14), blow nitrogen gas from the blow-off port of the oxidant isolation valve (15), and replace the pipeline between the oxidant isolation valve (15) and the oxidant auxiliary valve (9) with nitrogen gas. The blow-off time shall not be less than 1 minute. The oxidant supply system is blown off, comprising: Open the oxidant auxiliary valve (9), close the oxidant precooling discharge valve (14), and blow nitrogen gas from the blow-off port of the oxidant isolation valve (15). The blow-off time is not less than 1 minute. After the blow-off is completed, close the oxidant auxiliary valve (9) and open the oxidant precooling discharge valve (14); The oxidant supply system is precooled and filled, comprising: The purge gas source is turned on, the purge pressure is P1, and the oxidant and fuel are purged from the head cavity of the gas generator (1); the oxidant isolation valve (15) is opened, and the pipeline between the oxidant auxiliary valve (9) and the storage tank of the propellant test bench is precooled. When the outlet temperature of the oxidant precooling discharge valve (14) is not higher than -150°C, the precooling filling is completed.

7. The liquid oxygen-kerosene gas generator extrusion test method according to claim 1, characterized in that: The test run control sequence includes: At -10s, the control signal is triggered, the test control sequence is entered, and the acquisition system starts working; At time 0s, the gunpowder starter (4) ignites; At time t1, the pyrotechnic igniter (5) ignites; At time t2, the oxidant auxiliary valve (9) is opened, and liquid oxygen fills the head chamber of the gas generator (1); At time t3, the fuel sub-valve (8) is opened, kerosene is filled into the gas generator (1), and the gas generator (1) is ignited; At the 10 second mark, the oxidant auxiliary valve (9) is closed and the oxidant precooling discharge valve (14) is opened at the same time. As the pressure in the gas generator chamber drops, the oxidant purge valve (10) automatically opens to purge the oxidant cavity of the gas generator (1). At the moment 10s+t4, the fuel auxiliary valve (8) and the fuel isolation valve (16) are closed, and the fuel purge valve (11) is automatically opened to purge the fuel cavity of the gas generator (1); At 15 seconds, close the oxidant isolation valve (15) and the fuel isolation valve (16); At 20s+t4, the control and acquisition system stops working.

8. The liquid oxygen-kerosene gas generator extrusion test method according to claim 1, characterized in that: It also includes the post-processing process after the gas generator ignition test, including: Open the fuel discharge valve (17) and blow nitrogen gas through the blow-off port of the fuel isolation valve (16); Open the oxidant auxiliary valve (9), close the oxidant precooling discharge valve (14), blow nitrogen at the blow-off port of the oxidant isolation valve (15) for not less than 1 minute, then open the oxidant precooling discharge valve (14), close the oxidant auxiliary valve (9), and continue blowing nitrogen. Stop blowing nitrogen after the oxidant supply system returns to ambient temperature.

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