A regenerative cooling liquid rocket engine purging system and its control method

Abstract

This invention relates to a purging system for a regenerative coolant liquid rocket engine, comprising an oxidizer purging assembly, a fuel purging assembly, and a regenerative coolant liquid rocket engine. The oxidizer purging assembly includes an oxidizer purging gas source tank, a purging gas shut-off valve, an oxidizer purging check valve, and an oxidizer purging nozzle connected in sequence. The fuel purging assembly includes a fuel purging gas source tank, a purging gas shut-off valve, a fuel purging check valve, and a fuel purging nozzle connected in sequence. The invention also relates to a purging control method for a regenerative coolant liquid rocket engine, including pre-test purging, test purging, and post-test purging steps. This invention achieves automatic control of the purging process through differential pressure control of the oxidizer and fuel purging check valves, reducing human error; and ensures the reusability of the engine body by controlling the time difference between oxidizer and fuel purging.

Description

Technical Field

[0001] This invention belongs to the field of liquid rocket engine application technology, specifically a regenerative cooling liquid rocket engine purging system and its control method. Background Technology

[0002] As national space missions become increasingly demanding, the requirements for rocket engine development are also rising, leading to more engine development and testing. In tests of extrusion-type regenerative coolant rocket engines, a purging system is often installed to remove residual propellant from the engine cavity before and after the test. This prevents propellant corrosion of the engine and avoids propellant residue causing ignition deflagration or affecting the engine's start-up process. However, the engine purging system usually requires manually adding control timings to the ignition sequence or manually activating the purging process. In these cases, there are issues such as gas and liquid mixing due to inappropriate purging timing, which can easily cause abnormal engine operation and emergency shutdown. Additionally, the increased number of purging timing points can lead to complex timing sequences and make the process prone to errors. Summary of the Invention

[0003] To overcome human control errors in the purging process of liquid rocket engines and increase the number of times the engine body can be reused, this invention proposes a regenerative cooling liquid rocket engine purging system and its control method.

[0004] A regenerative cooling liquid rocket engine purging system includes an oxidizer purging assembly and a fuel purging assembly.

[0005] The oxidizer purging assembly and the fuel purging assembly are respectively connected to the regenerative cooling liquid rocket engine.

[0006] The oxidizer purging assembly includes an oxidizer purging gas source tank, a purging gas shut-off valve, an oxidizer purging check valve, and an oxidizer purging nozzle connected in sequence. The oxidizer purging nozzle is connected to the regenerative cooling liquid rocket engine.

[0007] The fuel purging assembly includes a fuel purging gas source tank, a purging gas shut-off valve, a fuel purging check valve, and a fuel purging nozzle connected in sequence. The fuel purging nozzle is connected to the regenerative cooling liquid rocket engine.

[0008] In the aforementioned regenerative cooling liquid rocket engine purging system, both the oxidizer purging gas source tank and the fuel purging gas source tank are constant pressure tanks with adjustable pressure.

[0009] The aforementioned regenerative cooling liquid rocket engine purging system includes an oxidizer main valve, a fuel main valve, a fuel cooling pipeline, a fuel main pipeline, a thrust chamber regenerative cooling channel, a thrust chamber, an oxidizer injection port, a fuel injection port, an oxidizer cavity, a fuel main cavity, and a fuel cooling cavity.

[0010] The oxidant main valve is connected to the thrust chamber in sequence through the oxidant pipeline, the oxidant cavity, and the oxidant injection port.

[0011] The main fuel valve is connected to the thrust chamber in sequence through the thrust chamber regeneration cooling channel, the fuel cooling pipeline, and the fuel cooling path cavity. The main fuel valve is also connected to the thrust chamber in sequence through the thrust chamber regeneration cooling channel, the main fuel pipeline, the main fuel path cavity, and the fuel injection port.

[0012] The oxidizer purge nozzle is connected to the pipeline from the oxidizer main valve to the oxidizer chamber, and the fuel purge nozzle is connected to the thrust chamber regeneration cooling channel.

[0013] In the aforementioned regenerative cooling liquid rocket engine purging system, the volume from the oxidizer purge check valve to the oxidizer outlet is smaller than the volume from the fuel purge check valve to the fuel outlet.

[0014] A method for controlling the purging of regenerative coolant in a rocket engine includes the following steps:

[0015] Step 1, blow-dry before test run

[0016] The first step is to open the oxidizer purge gas source tank and the fuel purge gas source tank. The purge gas flows to the fuel purge gas shut-off valve and the oxidizer purge gas shut-off valve, respectively. The two gas lines are the same purge gas, and at this time, the two gas lines arrive at the purge gas shut-off valves at the same time.

[0017] The second step is to simultaneously open the fuel line purge gas shut-off valve and the oxidant line purge gas shut-off valve. The purge gas flows to the oxidant purge check valve and the fuel purge check valve, respectively. At this time, both gas lines reach the oxidant purge check valve and the fuel purge check valve at the same time.

[0018] Third, when the pressure difference across the oxidizer purge check valve and the fuel purge check valve reaches the rated opening pressure, the oxidizer purge check valve and the fuel purge check valve automatically open, and the purge gas purges the engine passages.

[0019] Step 2, Test run and blowdown

[0020] The first step is to test the engine. Before the engine chamber pressure reaches the rated chamber pressure, open the oxidizer purge gas reservoir and the fuel purge gas reservoir. The purge gas flows to the fuel purge gas shut-off valve and the oxidizer purge gas shut-off valve, respectively. The two gas lines are the same purge gas. At this time, the two gas lines arrive at the purge gas shut-off valve at the same time.

[0021] The second step is to simultaneously open the fuel line purge gas shut-off valve and the oxidant line purge gas shut-off valve. The purge gas flows to the oxidant purge check valve and the fuel purge check valve, respectively. The two gas lines are the same type of purge gas. At this time, the two gas lines reach the oxidant purge check valve and the fuel purge check valve at the same time.

[0022] The third step is to bring the engine chamber pressure to the rated chamber pressure, close the oxidizer purge check valve and the fuel purge check valve, and then purge the oxidizer passage and fuel passage with the purge gas.

[0023] Step 3, blow out after test run

[0024] The first step is to shut down the engine, while keeping the main fuel valve open and the main oxidizer valve closed. When the pressure difference across the oxidizer purge check valve reaches the rated opening pressure, the oxidizer purge check valve automatically opens, and purge gas purges the oxidizer passage after the oxidizer purge check valve for a period of T0 to T1.

[0025] In the second step, with the oxidizer purge check valve open, the purge gas continues to purge the oxidizer passage after the engine oxidizer purge check valve. The main fuel valve is then closed, and the pressure difference across the fuel purge check valve reaches the rated opening pressure. The fuel purge check valve automatically opens, and the purge gas purges the fuel passage after the engine fuel purge check valve for a time period of T1 to T2.

[0026] The third step involves simultaneously closing the fuel line purging shut-off valve and the oxidizer line purging shut-off valve, thereby stopping the purging of the oxidizer chamber and the fuel line chamber simultaneously, with the stopping time being from T2 to T3.

[0027] Simultaneously open the fuel line purging valve and the oxidizer line purging valve, and purge the oxidizer line cavity and the fuel line cavity at the same time. The purging time is from T3 to T4.

[0028] The fourth step involves repeatedly closing and opening the fuel path degassing shut-off valve and the oxidizer path degassing shut-off valve until there is no remaining propellant in the engine cavity.

[0029] In the above-mentioned regenerative cooling liquid rocket engine purging control method, in step 2, the oxidizer purging check valve and the fuel purging check valve are in the closed state. When they are in the closed state, the pressure difference between the oxidizer purging check valve and the fuel purging check valve and the pressure difference between the oxidizer purging check valve and the fuel purging check valve is greater than 0.3 MPa.

[0030] In the above-mentioned regenerative cooling liquid rocket engine purging control method, during the purging process after test run in step 3, the rated pressure of the oxidizer purging check valve is 0.2 MPa, and the rated pressure of the fuel purging check valve is 0.2 MPa.

[0031] In the above-mentioned regenerative cooling liquid rocket engine purging control method, during the purging process after test run in step 3, the oxidizer cavity purging time T0 to T1 is 0.3s, the fuel path cavity purging time T1 to T2 is 20s, the simultaneous purging stop time of the oxidizer cavity and fuel path cavity T2 to T3 is 2s, the simultaneous purging time of the oxidizer cavity and fuel path cavity T3 to T4 is 10s, and the simultaneous closing and opening of the fuel path purging gas shut-off valve and the oxidizer path purging gas shut-off valve is repeated 5 times.

[0032] The beneficial effects of this invention are:

[0033] A regenerative cooling liquid rocket engine purging system achieves automatic control of the engine purging process by rationally setting the system composition and controlling the pressure difference before and after the one-way valve, which not only meets the engine purging requirements but also reduces the error of human control.

[0034] A regenerative cooling liquid rocket engine purging system controls the purging time difference between the oxidizer path and the fuel path. The oxidizer path is purged first, and the fuel path is purged 300ms later. This allows the fuel to continue cooling the engine body during the subsequent combustion after the oxidizer is purged, ensuring that the engine body is not damaged and that the engine body can be reused.

[0035] A regenerative cooling liquid rocket engine purging system is disclosed. The invention features a throttling orifice in the pipeline after the engine and the one-way valve. By selecting throttling orifices of different diameters, the volumetric flow rate and airflow velocity of the purging gas can be changed. The same system can adapt to the purging requirements of different engines, improving the utilization rate of the purging system and saving test costs.

[0036] A method for controlling the purging of a regenerative cooling liquid rocket engine allows the engine to flexibly adapt to purging requirements while maintaining the same ignition sequence by changing the pressure in the gas tank and altering the opening time of the one-way valve after engine shutdown. Attached Figure Description

[0037] Figure 1This is the purge timing diagram. At time T0, the engine is shut down. At this time, the oxidizer main valve is closed, the pressure after the oxidizer main valve drops, the oxidizer purge check valve opens, and purge begins. The fuel main valve remains open, and the fuel continues to cool the thrust chamber in the regeneration cooling channel. After 0.3 seconds of cooling, the fuel main valve closes, marking time T1. At this time, the pressure after the fuel main valve drops, the fuel purge check valve opens, and purge begins. From time T1, the oxidizer purge check valve and the fuel purge check valve purge simultaneously for 20 seconds, after which the purge gas shut-off valve closes, marking time T2. Two seconds after time T2, the purge gas shut-off valve opens, and the oxidizer and fuel purge check valves automatically open, marking time T3. From time T3, the oxidizer purge check valve and the fuel purge check valve automatically open and purge simultaneously for 10 seconds, after which the purge gas shut-off valve closes, marking time T4. During the entire purge process, the actions from T2 to T4 need to be repeated 5 times to ensure complete purge.

[0038] Figure 2 This is a schematic diagram of a regenerative cooling liquid rocket engine purging system.

[0039] In the diagram: 1. Oxidant purge gas source tank; 2. Fuel purge gas source tank; 3. Purge gas shut-off valve; 4. Oxidant chamber; 5. Fuel purge check valve; 6. Oxidant purge check valve; 7. Oxidant purge nozzle; 8. Fuel purge nozzle; 9. Oxidant main valve; 10. Fuel main valve; 11. Fuel cooling pipeline; 12. Fuel main pipeline; 13. Thrust chamber regeneration cooling channel; 14. Thrust chamber; 15. Oxidant injection port; 16. Fuel injection port; 17. Oxidant inlet; 18. Fuel inlet; 19. Fuel main pipeline chamber; 20. Fuel cooling pipeline chamber. Detailed Implementation

[0040] Example 1

[0041] A regenerative cooling liquid rocket engine purging system includes a gas source tank, a purging gas shut-off valve, a one-way valve, a purging pipe nozzle (purging gas throttle orifice), and the engine. Figure 2 As shown.

[0042] The engine purging uses an automatic control method. During the purging operation, the engine purging gas shut-off valve 3 is opened, and the gas flows to the oxidant purging check valve 6 and the fuel purging check valve 5. When the engine is turned off, the pressure in the engine pipeline decreases, that is, the pressure after the oxidant purging check valve 6 and the fuel purging check valve 5 decreases, while there is purging gas before the check valve. When the pressure difference before and after the check valve reaches a certain value, the check valve opens automatically, and the purging gas begins to purge the engine cavity.

[0043] Both the oxidizer purge gas reservoir 1 and the fuel purge gas reservoir 2 are constant-pressure reservoirs with adjustable pressure. This means that during engine purging, the reservoir pressure remains constant over time. The pressures of the oxidizer purge gas reservoir 1 and the fuel purge gas reservoir 2 may not be identical. The outlets of the oxidizer purge gas reservoir and the fuel purge gas reservoir are connected to pipelines, with two purge gas shut-off valves 3 at the pipeline outlets. These valves control the flow of purge gas, and the control system issues on / off commands to control this flow. The valve is opened and closed. The outlet of the purge gas shut-off valve 3 is connected to the pipeline. The pipeline outlet is connected to the oxidant purge check valve 6 and the fuel purge check valve 5. The oxidant purge check valve 6 and the fuel purge check valve 5 are then connected to the oxidant purge nozzle 7 and the fuel purge nozzle 8. The purge gas is throttled at the oxidant purge nozzle 7 and the fuel purge nozzle 8, that is, the flow area of ​​the cross section is the smallest. By selecting purge nozzles with different orifice diameters, the volume flow rate and airflow velocity of the purge gas can be changed.

[0044] The outlet of the oxidizer purge nozzle 7 is connected to the pipeline after the oxidizer main valve 9 and is connected to the oxidizer cavity 4 at the head of the thrust chamber. The purge gas blows out the residual propellant in the oxidizer cavity 4 through the flow channel, so that there is no residual propellant in the engine cavity.

[0045] The outlet of the fuel purging nozzle 8 is connected to the thrust chamber regeneration cooling channel 13. The fuel purging nozzle 8 is located at the bottom of the thrust chamber regeneration cooling channel. The outlet of the regeneration cooling channel 13 is divided into two paths through connecting pipes. One path is connected to the main fuel channel 19, and the other path is connected to the fuel cooling channel 20. The purging gas blows away the residual propellant in the regeneration cooling channel 13, the main fuel channel 19, and the fuel cooling channel 20 through the flow channel. The thrust chamber regeneration cooling channel and the fuel cooling channel together ensure the normal operation of the thrust chamber body and prevent the thrust chamber body from burning.

[0046] In particular, when the engine is shut down, the residual propellant in the engine will continue to react and release heat. In order to avoid engine burn-out, a measure is proposed to control the time difference between the purging of the oxidizer path and the fuel path. The oxidizer path is purged first, and the fuel path is purged 300ms later. This allows the fuel to continue cooling the engine body during the subsequent combustion of the oxidizer, ensuring that the engine body is not damaged.

[0047] A method for controlling the purging of regenerative coolant in a rocket engine includes the following steps:

[0048] Step 1: Blow out the air before test run;

[0049] The first step is to set up the pipeline to ensure that the size and length of the purge gas pipeline from the storage tank to the shut-off valve are the same in the oxidizer purge line and the fuel purge line. Open the oxidizer purge gas source storage tank and the fuel purge gas source storage tank, and the purge gas flows to the two purge gas shut-off valves 3 respectively. The two gas lines are the same purge gas. At this time, the two gas lines arrive at the shut-off valve at the same time.

[0050] The second step is to set up the pipelines to ensure that the size and length of the purge gas from the purge gas shut-off valve to the fuel purge check valve and the oxidizer purge check valve are consistent in the oxidizer purge line and the fuel purge check valve. At the same time, open the fuel purge gas shut-off valve 3, and the purge gas flows to the oxidizer purge check valve 6 and the fuel purge check valve 5 respectively. The two gas lines are the same purge gas. At this time, the two gas lines arrive at the fuel purge check valve and the oxidizer purge check valve at the same time.

[0051] Third, at this time the engine is not running, and the pressure after the oxidizer purge check valve 6 and the fuel purge check valve 5 is atmospheric pressure. As long as the positive pressure difference before and after the oxidizer purge check valve 6 and the fuel purge check valve 5 is greater than or equal to 0.2MPa, the oxidizer purge check valve 6 and the fuel purge check valve 5 can open automatically, and the purge gas purges the engine cavity. The volume from the oxidizer purge check valve to the oxidizer outlet is set to be smaller than the volume from the fuel purge check valve to the fuel outlet, so that the engine purges the oxidizer path first and then starts purging the fuel path.

[0052] Step 2, test run and purging (pipeline size and length settings are the same as in Step 1);

[0053] First, after the engine chamber pressure reaches the rated chamber pressure, open the oxidizer purge gas reservoir and the fuel purge gas reservoir. The purge gas flows to the two purge gas shut-off valves 3. The two gas streams are the same type of purge gas. At this time, both gas streams arrive at the shut-off valves simultaneously.

[0054] The second step is to open the two purge gas shut-off valves 3 at the same time. The purge gas flows to the oxidant purge check valve 6 and the fuel purge check valve 5 respectively. The two gas lines are the same purge gas. At this time, the two gas lines arrive at the oxidant purge check valve 6 and the fuel purge check valve 5 at the same time.

[0055] Third, the engine is running at this time. The pressure after the oxidizer purge check valve 6 and the fuel purge check valve 5 are the pressure after the oxidizer main valve and the fuel main valve minus the pressure after the flow resistance of the purge nozzle. This pressure is greater than the pressure before the oxidizer purge check valve 6 and the fuel purge check valve 5. The check valve is in the closed state and the gas is not purged. The difference between this pressure and the pressure before the check valve should be greater than 0.3 MPa, leaving a certain safety margin.

[0056] Step 3, blow out after test run

[0057] like Figure 1 As shown, after the engine is shut down, the regenerative cooling channel is protected. The engine regenerative cooling passage needs to be cooled for a short period of time. Therefore, the fuel main valve closes 300ms after the oxidizer main valve closes to ensure that fuel flow remains in the regenerative cooling passage for cooling. After shutdown, the oxidizer main valve closes simultaneously, and the pressure after the oxidizer check valve gradually decreases. When the positive pressure difference across the oxidizer purge check valve 6 is greater than or equal to 0.2MPa, the oxidizer purge check valve 6 automatically opens, and the purge gas purges the oxidizer path cavity after the engine check valve. After 300ms, the fuel main valve closes, and the pressure after the fuel check valve gradually decreases. When the positive pressure difference across the fuel purge check valve 5 is greater than or equal to 0.2MPa, the fuel purge check valve 5 automatically opens, and the purge gas purges the fuel path cavity after the engine fuel purge check valve. After purging both paths simultaneously for a period of time, both shut-off valves are closed. After 2s, both shut-off valves are opened simultaneously again, and the two paths are purged simultaneously for a period of time. This process is repeated 5 times to ensure that the engine propellant is completely purged. The volume from the one-way valve to the oxidant outlet is set to be smaller than the volume from the one-way valve to the fuel outlet, ensuring that the engine purges the oxidant path first, and then starts purging the fuel path.

Claims

1. A regeneratively cooled liquid rocket engine bleed system, characterized by, The system comprises an oxidant purging assembly and a fuel purging assembly. The oxidant purging assembly and the fuel purging assembly are connected to a regeneratively cooled liquid rocket engine respectively. The oxidant purging assembly comprises an oxidant purging gas source tank (1), a purging gas shut-off valve (3), an oxidant purging check valve (6) and an oxidant purging connector (7) connected in sequence. The fuel purging assembly comprises a fuel purging gas source tank (2), a purging gas shut-off valve (3), a fuel purging check valve (5) and a fuel purging connector (8) connected in sequence. The regeneratively cooled liquid rocket engine comprises an oxidant main valve (9), a fuel main valve (10), a fuel cooling pipeline (11), a fuel main pipeline (12), a thrust chamber regenerative cooling channel (13), a thrust chamber (14), an oxidant injection port (15), a fuel injection port (16), an oxidant cavity (4), a fuel main cavity (19) and a fuel cooling cavity (20). The oxidant main valve (9) is connected to the thrust chamber (14) through an oxidant pipeline, the oxidant cavity (4) and the oxidant injection port (15) in sequence. The fuel main valve (10) is connected to the thrust chamber (14) through the thrust chamber regenerative cooling channel (13), the fuel cooling pipeline (11) and the fuel cooling cavity (20) in sequence. The fuel main valve (10) is connected to the thrust chamber (14) through the thrust chamber regenerative cooling channel (13), the fuel main pipeline (12), the fuel main cavity (19) and the fuel injection port (16) in sequence.

2. The regenerative cooling liquid rocket engine bleed system of claim 1, wherein, The oxidant purging connector (7) is connected to the pipeline from the oxidant main valve (9) to the oxidant cavity (4), and the fuel purging connector (8) is connected to the thrust chamber regenerative cooling channel (13).

3. The regenerative cooling liquid rocket engine bleed system of claim 1 or 2, wherein, The oxidant purging gas source tank (1) and the fuel purging gas source tank (2) are constant pressure tanks with adjustable pressure.

4. A regeneratively cooled liquid rocket engine bleed control method, characterized by, The volume from the oxidant purging check valve to the oxidant outlet is smaller than the volume from the fuel purging check valve to the fuel outlet. The regeneratively cooled liquid rocket engine purging system according to any one of claims 1 to 3 comprises the following steps: Step 1: pre-test purging First, the oxidant purging gas source tank (1) and the fuel purging gas source tank (2) are opened, and the purging gas flows to the fuel purging gas shut-off valve (3) and the oxidant purging gas shut-off valve (3) respectively. Second, the fuel purging gas shut-off valve (3) and the oxidant purging gas shut-off valve (3) are opened simultaneously, and the purging gas flows to the oxidant purging check valve (6) and the fuel purging check valve (5) respectively. Third, the fuel purging check valve (5) and the oxidant purging check valve (6) are opened simultaneously, and the purging gas flows to the fuel injection port (16) and the oxidant injection port (15) respectively. Third step, the pressure difference before and after the oxidant blowing check valve (6) and the fuel blowing check valve (5) reaches the opening pressure rating, the oxidant blowing check valve (6) and the fuel blowing check valve (5) are automatically opened, and the blowing gas blows the engine cavity; Step 2, test blowing: First step, engine test, before the engine chamber pressure reaches the rated chamber pressure, open the oxidant blowing gas source tank (1) and the fuel blowing gas source tank (2), blowing gas flows to the fuel blowing gas cutoff valve (3) and the oxidant blowing gas cutoff valve (3) respectively, the two gases are the same blowing gas, at this time the two gases reach the blowing gas cutoff valve (3) at the same time; Second step, open the fuel blowing gas cutoff valve (3) and the oxidant blowing gas cutoff valve (3) at the same time, blowing gas flows to the oxidant blowing check valve (6) and the fuel blowing check valve (5) respectively, the two gases are the same blowing gas, at this time the two gases reach the oxidant blowing check valve (6) and the fuel blowing check valve (5) at the same time; Third step, the engine chamber pressure reaches the rated chamber pressure, the oxidant blowing check valve (6) and the fuel blowing check valve (5) are in a closed state, and the blowing gas does not blow the oxidant road cavity and the fuel road cavity; Step 3, post-test blowing: First step, engine shutdown, the fuel main valve (10) continues to remain in an open state, and the oxidant main valve (9) is closed; the pressure difference before and after the oxidant blowing check valve (6) reaches the opening pressure rating, the oxidant blowing check valve (6) is automatically opened, and the blowing gas blows the oxidant cavity (4) behind the engine oxidant blowing check valve (6), and the blowing time is T0 to T1; Second step, the oxidant blowing check valve (6) is in an open state, and the blowing gas continues to blow the oxidant cavity (4) behind the engine oxidant blowing check valve (6); the fuel main valve (10) is closed, the pressure difference before and after the fuel blowing check valve (5) reaches the opening pressure rating, the fuel blowing check valve (5) is automatically opened, and the blowing gas blows the fuel road cavity behind the engine fuel blowing check valve (5), and the blowing time is T1 to T2; Third step, the fuel blowing gas cutoff valve (3) and the oxidant blowing gas cutoff valve (3) are closed at the same time, and the blowing of the oxidant cavity (4) and the fuel road cavity is stopped at the same time, and the stopping time is T2 to T3; The fuel blowing gas cutoff valve (3) and the oxidant blowing gas cutoff valve (3) are opened at the same time, and the oxidant cavity (4) and the fuel road cavity are blown at the same time, and the blowing time is T3 to T4; Fourth step, repeat the process of closing and opening the fuel blowing gas cutoff valve (3) and the oxidant blowing gas cutoff valve (3) at the same time, until there is no residual propellant in the engine cavity.

5. The regenerative cooling liquid rocket engine bleed control method of claim 4, wherein, In the third step of the step 2, the oxidant blowing check valve (6) and the fuel blowing check valve (5) are in a closed state, and the pressure difference before and after the oxidant blowing check valve (6) and the fuel blowing check valve (5) in the closed state is greater than 0.3MPa.

6. The regenerative cooling liquid rocket engine bleed control method of claim 4, wherein, The step 3 test run after blowing, the oxidant blowing one-way valve (6) opening pressure rating is 0.2MPa, fuel blowing one-way valve (5) opening pressure rating is 0.2MPa.

7. The regenerative cooling liquid rocket engine bleed control method of claim 4, wherein, The step 3 test run after blowing, the oxidant cavity (4) blowing time T0 to T1 is 0.3s, fuel cavity blowing time T1 to T2 is 20s, the oxidant cavity (4), fuel cavity blowing stop time T2 to T3 is 2s, the oxidant cavity (4), fuel cavity blowing time T3 to T4 is 10s, repeat fuel cavity blowing gas stop valve (3), oxidant cavity blowing gas stop valve (3) close, open 5 times.

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