Gas hydrogen and liquid oxygen torch ignition system and method for expansion cycle hydrogen and oxygen engine

Abstract

The invention relates to a gas hydrogen and liquid oxygen torch ignition system and method for an expansion cycle hydrogen-oxygen engine. The system comprises an ignition chamber, a thrust chamber, a hydrogen main valve, an oxygen main valve, an oxygen main cavitation tube, a hydrogen pump, an oxygen pump, a hydrogen turbine, and an oxygen turbine. The ignition chamber is a torch ignition chamber, the hydrogen pump is coaxially connected with the hydrogen turbine, and the oxygen pump is coaxially connected with the oxygen turbine. The ignition chamber is connected with the thrust chamber. Liquid hydrogen is pressurized by the hydrogen pump and then heat-exchanged by a thrust chamber jacket to become gas hydrogen, and then enters the hydrogen turbine to do work and drive the hydrogen pump to rotate, and then flows from the hydrogen turbine outlet to the oxygen turbine, driving the oxygen turbine to drive the oxygen pump to rotate, the output end of the oxygen pump is connected to the oxygen main cavitation tube, the oxygen main cavitation tube is divided into two paths, one is connected to the thrust chamber through the oxygen main valve, and the other is connected to the ignition chamber; the output end of the oxygen turbine is divided into two paths, one is connected to the thrust chamber through the hydrogen main valve, and the other is connected to the ignition chamber; the liquid oxygen in the ignition chamber is drawn out from behind the oxygen pump and before the oxygen main valve, and the gas hydrogen is drawn out from behind the oxygen turbine and before the hydrogen main valve.

Description

Technical Field

[0001] The invention relates to a gas hydrogen and liquid oxygen torch ignition system and method for an expansion cycle hydrogen and oxygen engine, belonging to the field of liquid rocket engines. Background Art

[0002] Since the beginning of the 21st century, the world's major space powers have been actively exploring interstellar manned flight plans such as returning to the moon and landing on Mars. According to my country's aerospace industry development plan, heavy-lift launch vehicles will be developed for lunar landing projects and future deep space exploration projects. The core third stage uses an expansion cycle hydrogen-oxygen engine. To meet mission requirements, the engine needs to be ignited and started multiple times during the flight.

[0003] The ignition methods of hydrogen-oxygen engines are mainly divided into gunpowder ignition and torch ignition. Compared with the traditional gunpowder ignition method, the torch ignition method has a greater advantage in achieving multiple ignitions of more than 3 times. At present, the mainstream ignition methods of hydrogen-oxygen engines in various countries in the world are mainly liquid hydrogen and liquid oxygen torch ignition and high-pressure hydrogen and oxygen torch ignition with self-contained gas cylinders. Compared with liquid hydrogen and liquid oxygen film cooling protection, the igniter is easily ablated, and the high-pressure hydrogen and oxygen torch ignition does not require independent hydrogen and oxygen cylinders, and the number of ignitions is limited by the self-contained gas cylinders. Summary of the invention

[0004] The technical problem solved by the present invention is: to overcome the shortcomings of the prior art and provide a gas hydrogen and liquid oxygen torch ignition system and method for an expansion cycle hydrogen and oxygen engine, which is used to meet the multiple starting requirements of the three-stage expansion cycle hydrogen and oxygen engine in the core of a heavy-duty launch vehicle, and is used to ignite the hydrogen and oxygen medium entering the thrust chamber, and can achieve multiple ignitions of 3 times or more.

[0005] The technical solution of the present invention is: a gas hydrogen and liquid oxygen torch ignition system for an expansion cycle hydrogen-oxygen engine, the system comprising an ignition chamber, a thrust chamber, a hydrogen main valve, an oxygen main valve, an oxygen main cavitation tube, a hydrogen pump, an oxygen pump, a hydrogen turbine, and an oxygen turbine; the ignition chamber is a torch ignition chamber, the hydrogen pump is coaxially connected to the hydrogen turbine, the oxygen pump is coaxially connected to the oxygen turbine; the ignition chamber is connected to the thrust chamber;

[0006] After being pressurized by the hydrogen pump, the liquid hydrogen is heat-exchanged in the thrust chamber jacket to become gaseous hydrogen, and then enters the hydrogen turbine to work and drive the hydrogen pump to rotate. Then, it flows from the hydrogen turbine outlet to the oxygen turbine, driving the oxygen turbine to drive the oxygen pump to rotate. The output end of the oxygen pump is connected to the oxygen main cavitation pipe, which is divided into two paths, one of which is connected to the thrust chamber through the oxygen main valve, and the other is connected to the ignition chamber.

[0007] The output of the oxygen turbine is divided into two paths, one connected to the thrust chamber through the hydrogen main valve, and the other connected to the ignition chamber;

[0008] The liquid oxygen in the ignition chamber is led out from behind the oxygen pump and before the oxygen main valve, and the gaseous hydrogen is led out from behind the oxygen turbine and before the hydrogen main valve.

[0009] Preferably, the gas hydrogen and liquid oxygen torch ignition system for the expansion cycle hydrogen-oxygen engine also includes an oxygen ignition valve; one end of the oxygen ignition valve is connected in parallel with the oxygen main valve and connected to the output end of the oxygen main cavitation tube, and the other end is connected to the ignition chamber.

[0010] Preferably, the above-mentioned gas hydrogen and liquid oxygen torch ignition system for the expansion cycle hydrogen-oxygen engine also includes a hydrogen ignition valve and a hydrogen ignition sonic nozzle. The hydrogen ignition sonic nozzle is connected in parallel with the hydrogen main valve and connected to the output end of the oxygen turbine; one end of the hydrogen ignition valve is connected to the hydrogen ignition sonic nozzle, and the other end is connected to the ignition chamber.

[0011] Preferably, the torch ignition chamber is located at the center of the thrust chamber head.

[0012] Preferably, the ignition chamber is ignited by an ignition device.

[0013] Preferably, the ignition device comprises an electric nozzle, an ignition cable, and an exciter;

[0014] The exciter receives an external electrical trigger signal, which is transmitted to the electric nozzle through the ignition cable. The electric nozzle generates an electric spark under the drive of the electrical trigger signal, and the electric spark ignites the fuel in the ignition chamber of the torch.

[0015] Preferably, the head of the ignition chamber is a gaseous hydrogen and liquid oxygen injection interface, wherein the oxygen nozzle is arranged in the middle of the injector, which is a direct current mutual impact structure, and the liquid oxygen is atomized after impact.

[0016] Based on the above system, the present invention also provides a gas hydrogen and liquid oxygen torch ignition method for an expansion cycle hydrogen and oxygen engine, the method comprising the following steps:

[0017] S1. Initialize the gas hydrogen liquid oxygen torch ignition system: close the oxygen main valve, hydrogen main valve, oxygen ignition valve, and hydrogen ignition valve;

[0018] S2, engine precooling: open the oxygen ignition valve to discharge the oxygen medium through the flare ignition chamber and thrust chamber to the outside, so as to cool the liquid oxygen pipeline of the flare ignition chamber;

[0019] S3, thrust chamber preheating: open the hydrogen ignition valve, and at the same time, energize the ignition device. The ignition chamber ignites under the pressure of the hydrogen and oxygen tanks to form a high-temperature torch, which is sprayed into the thrust chamber;

[0020] S4, torch ignition start: open the oxygen main valve and hydrogen main valve respectively, and the hydrogen and oxygen medium entering the thrust chamber is ignited by the high-temperature torch to complete the engine ignition;

[0021] S5. After the engine combustion chamber pressure rises to more than 90% of the rated operating conditions, the oxygen ignition valve can be closed while the hydrogen ignition valve is kept open to maintain the flow of gas and hydrogen so that the flow of gas and hydrogen can reliably protect the ignition chamber.

[0022] Preferably, the above-mentioned gas hydrogen and liquid oxygen torch ignition method for an expansion cycle hydrogen and oxygen engine further comprises the step of the propellant sinking to the bottom during the rocket vacuum gliding:

[0023] During the rocket's vacuum gliding, the oxygen ignition valve and the hydrogen ignition valve are opened, the ignition chamber ignites to produce combustion gas, which is ejected through the thrust chamber to generate thrust, achieving propellant sinking to the bottom with a small overload.

[0024] Preferably, the above-mentioned gas hydrogen and liquid oxygen torch ignition method for the expansion cycle hydrogen and oxygen engine also includes a separate small flow precooling step during the rocket vacuum gliding:

[0025] During the rocket's vacuum gliding, the oxygen ignition valve is opened to allow the oxygen medium to be discharged outward through the torch ignition chamber and thrust chamber, thereby achieving small-flow cooling of the engine oxygen system pipelines, controlling the temperature of the liquid oxygen pipelines, and creating favorable conditions for engine ignition.

[0026] The beneficial effects of the present invention compared with the prior art are:

[0027] (1) The ignition system of the present invention is simple, light in weight, and has unlimited ignition times. Since the medium used in the ignition system comes from the main engine system, there is no need to carry hydrogen and oxygen cylinders separately, and no pre-cooling discharge pipelines are set for the hydrogen and oxygen ignition circuits, which simplifies the system configuration and reduces the structural weight;

[0028] (2) Theoretically, the present invention can ignite the engine as long as there is propellant in the hydrogen and oxygen tanks and the power supply has electricity, and the number of ignitions is not subject to other restrictions.

[0029] (3) The head of the ignition chamber of the present invention is injected with gaseous hydrogen and liquid oxygen. The oxygen nozzle is arranged in the middle of the injector, which is a direct current mutual impact structure. The liquid oxygen is atomized after impact; the hydrogen nozzle is arranged in two rows under the electric nozzle, which is a tangential hole structure. On the one hand, this design can make the mixing ratio near the electric nozzle higher, which is conducive to ignition. On the other hand, the gaseous hydrogen away from the electric nozzle forms a protective gas film on the inner wall and downstream of the ignition chamber, protecting the inner wall of the ignition chamber and the head of the thrust chamber from being ablated.

[0030] (4) The hydrogen and oxygen ignition circuits of the present invention are both provided with ignition valves, so that the ignition system has better independence. Not only can the oxygen ignition circuit precooling and torch ignition timing be independently controlled, but the torch ignition system can also work independently for a long time, which is used for thrust chamber preheating, low thrust sinking, and low flow precooling of the engine hydrogen and oxygen system, etc.

[0031] (5) In the present invention, the gaseous hydrogen in the ignition chamber is led out from the rear of the oxygen turbine and in front of the hydrogen main valve. Compared with leading it out from the outlet of the thrust chamber jacket, it can avoid the influence of the gaseous hydrogen flow diverted from the hydrogen ignition path on the working capacity of the hydrogen turbine, does not affect the main stage working condition of the engine, and the hydrogen ignition pipeline is the shortest; the liquid oxygen in the ignition chamber is led out from the front of the oxygen main valve, which can shorten the oxygen ignition pipeline, which is beneficial to cooling and weight reduction. BRIEF DESCRIPTION OF THE DRAWINGS

[0032] Figure 1 The present invention provides a gas hydrogen liquid oxygen torch ignition system solution.

[0033] In the figure: 1. Torch ignition chamber; 2. Thrust chamber; 3. Hydrogen ignition valve; 4. Hydrogen ignition sonic nozzle; 5. Hydrogen main valve; 6. Oxygen ignition valve; 7. Oxygen main valve; 8. Oxygen main cavitation tube; 9. Hydrogen pump; 10. Oxygen pump; 11. Hydrogen turbine; 12. Oxygen turbine; 13. Electric nozzle; 14. Ignition cable; 15. Exciter.

[0034] Figure 2 This is a starting timing diagram of the torch ignition system provided by the present invention.

[0035] In the figure: 1# is the hydrogen ignition valve; 2# is the oxygen ignition valve; 3# is the hydrogen main valve; 4# is the oxygen main valve; DH is the actuator; ↑ is power on; ↓ is power off; t1~t6 are the interval time. DETAILED DESCRIPTION

[0036] The present invention will be further described below in conjunction with the embodiments.

[0037] like Figure 1 As shown, the present invention provides a gas hydrogen and liquid oxygen torch ignition system for an expansion cycle hydrogen-oxygen engine, the system comprising an ignition chamber 1, a thrust chamber 2, a hydrogen main valve 5, an oxygen main valve 7, an oxygen main cavitation tube 8, a hydrogen pump 9, an oxygen pump 10, a hydrogen turbine 11, and an oxygen turbine 12; the ignition chamber 1 is a torch ignition chamber, the hydrogen pump 9 is coaxially connected to the hydrogen turbine 11, and the oxygen pump 10 is coaxially connected to the oxygen turbine 12; the torch ignition chamber is arranged at the center of the thrust chamber head, and the ignition chamber 1 is connected to the thrust chamber 2.

[0038] After being pressurized by the hydrogen pump 9, the liquid hydrogen is heat-exchanged in the thrust chamber jacket to become gaseous hydrogen, and then enters the hydrogen turbine 11 to do work to drive the hydrogen pump 9 to rotate, and then flows from the outlet of the hydrogen turbine 11 to the oxygen turbine 12, driving the oxygen turbine 12 to drive the oxygen pump 10 to rotate, and the output end of the oxygen pump 10 is connected to the oxygen main cavitation pipe 8, and the oxygen main cavitation pipe 8 is divided into two paths, one of which is connected to the thrust chamber 2 through the oxygen main valve 7, and the other is connected to the ignition chamber 1;

[0039] The output end of the oxygen turbine 12 is divided into two paths, one of which is connected to the thrust chamber 2 through the hydrogen main valve 5, and the other is connected to the ignition chamber 1;

[0040] Liquid oxygen in the ignition chamber is led out from behind the oxygen pump 10 and before the oxygen main valve 7, and gaseous hydrogen is led out from behind the oxygen turbine 12 and before the hydrogen main valve 5.

[0041] Preferably, the gas hydrogen and liquid oxygen torch ignition system for the expansion cycle hydrogen-oxygen engine further comprises an oxygen ignition valve 6; one end of the oxygen ignition valve 6 is connected in parallel with the oxygen main valve 7 and connected to the output end of the oxygen main cavitation tube, and the other end is connected to the ignition chamber.

[0042] Preferably, the gas hydrogen and liquid oxygen torch ignition system for the expansion cycle hydrogen-oxygen engine further comprises a hydrogen ignition valve 3 and a hydrogen ignition sonic nozzle 4. The hydrogen ignition sonic nozzle 4 is connected in parallel with the hydrogen main valve 5 and connected to the output end of the oxygen turbine 12. One end of the hydrogen ignition valve 3 is connected to the hydrogen ignition sonic nozzle 4, and the other end is connected to the ignition chamber. The gas hydrogen flow is controlled by the sonic nozzle, and the liquid oxygen flow is controlled by the ignition chamber oxygen nozzle, thereby controlling the ignition mixing ratio of the ignition chamber.

[0043] The present invention introduces a stream of gaseous hydrogen from behind the oxygen turbine and before the hydrogen main valve into the ignition chamber through the hydrogen ignition valve, and introduces a stream of liquid oxygen from behind the oxygen pump and before the oxygen main valve into the ignition chamber through the oxygen ignition valve, and the path is relatively short.

[0044] Preferably, the torch ignition chamber 1 is located at the center of the head of the thrust chamber 2 .

[0045] Preferably, the ignition chamber is ignited by an ignition device.

[0046] Preferably, the ignition device comprises an electric nozzle 13, an ignition cable 14, and an exciter 15;

[0047] The exciter 15 receives an external electric trigger signal, and the electric trigger signal is transmitted to the electric nozzle 13 through the ignition cable 14. The electric nozzle 13 generates an electric spark under the drive of the electric trigger signal, and the electric spark ignites the fuel in the ignition chamber of the torch.

[0048] Preferably, two sets of redundantly designed ignition devices and two redundantly designed electric nozzles may be provided, and the electric nozzles are powered by two independent exciters and cables.

[0049] Preferably, the head of the ignition chamber is a gas hydrogen and liquid oxygen injection interface, wherein the oxygen nozzle is arranged in the middle of the injector, which is a direct current mutual impact structure, and the liquid oxygen is atomized after impact, and the hydrogen nozzle is arranged in 2 rows under the electric nozzle, which is a tangential hole structure, which is conducive to ignition and the formation of a protective gas film downstream. Compared with liquid hydrogen and liquid oxygen, the gas hydrogen and liquid oxygen torch ignition method adopted by the present invention is conducive to liquid oxygen atomization and ignition of the igniter. At the same time, the gas hydrogen flow rate is relatively high, which is conducive to the use of gas film cooling to protect the igniter from being ablated; compared with the high-pressure gas hydrogen and gas oxygen torch ignition, the gas hydrogen and liquid oxygen torch ignition provided by the present invention does not need to carry independent hydrogen and oxygen cylinders, the number of ignitions is not limited by the self-carried gas cylinders, and the system structure is simple.

[0050] Based on the above ignition system, the present invention also provides a gas hydrogen and liquid oxygen torch ignition method for an expansion cycle hydrogen and oxygen engine, the method comprising the following steps:

[0051] S1. Initialize the gas hydrogen liquid oxygen torch ignition system: close the oxygen main valve 7, hydrogen main valve 5, oxygen ignition valve 6, and hydrogen ignition valve 3;

[0052] S2, engine precooling: open the oxygen ignition valve 6, so that the oxygen medium is discharged outward through the torch ignition chamber 1 and the thrust chamber 2, so as to realize the cooling of the liquid oxygen pipeline of the torch ignition chamber 1;

[0053] S3, thrust chamber preheating: open the hydrogen ignition valve 3, and at the same time, energize the two nozzles of the ignition device, ignite the ignition chamber 1 under the pressure of the hydrogen and oxygen tanks to form a high-temperature torch, which is sprayed into the thrust chamber 2;

[0054] S4, torch ignition start: open the oxygen main valve 7 and the hydrogen main valve 5 respectively, and the hydrogen and oxygen medium entering the thrust chamber 2 is ignited by the high-temperature torch, completing the first engine ignition;

[0055] S5. After the engine combustion chamber pressure rises to more than 90% of the rated operating condition, the oxygen ignition valve 6 can be closed while the hydrogen ignition valve is kept open to maintain the flow of gas and hydrogen so that the flow of gas and hydrogen can reliably protect the ignition chamber 1.

[0056] Since the present invention adopts a torch ignition method, steps S1 to S5 can be repeated to achieve multiple engine starts.

[0057] In addition to being used for ignition of the thrust chamber 2, this technical solution can also be used for propellant sinking, thrust chamber preheating and engine precooling.

[0058] The specific steps for the propellant to sink to the bottom during the rocket vacuum glide are:

[0059] During the rocket's vacuum gliding, the oxygen ignition valve 6 and the hydrogen ignition valve 3 are opened, the ignition chamber 1 ignites to produce combustion gas, which is ejected through the thrust chamber 2 to generate thrust, thereby achieving a small overload of the propellant and sinking to the bottom.

[0060] Specific steps for precooling with a small flow rate during rocket vacuum gliding:

[0061] During the rocket's vacuum glide, the oxygen ignition valve 6 is opened to discharge the oxygen medium through the torch ignition chamber 1 and the thrust chamber 2, thereby cooling the liquid oxygen pipeline of the torch ignition chamber 1 and controlling the temperature of the liquid oxygen pipeline. The combustion gas produced by the ignition chamber 1 can preheat the thrust chamber 2 to provide energy for the expansion cycle engine to start; at the same time, the engine's hydrogen and oxygen systems have a small flow of hydrogen and oxygen medium, respectively, which can maintain continuous cooling of the hydrogen and oxygen systems and shorten the precooling process before the engine is ignited again.

[0062] Hereinafter, several features of the present invention will be reiterated in conjunction with the accompanying drawings:

[0063] (1) Figure 1 As shown, the gaseous hydrogen in the ignition chamber is drawn out from behind the oxygen turbine 12 and before the hydrogen main valve 5, and the hydrogen ignition flow rate is controlled by the sonic nozzle 4 arranged in the hydrogen ignition path.

[0064] (2) Figure 1 As shown, the liquid oxygen in the ignition chamber is drawn out from behind the oxygen pump 10 and before the oxygen main valve 7, and the flow rate is controlled by the oxygen nozzle in the ignition chamber. No special throttling element is set in the oxygen ignition circuit.

[0065] (3) Figure 2 As shown, the torch ignition timing is controlled by the power supply of the hydrogen ignition valve 3, the oxygen ignition valve 6 and the actuator 15.

[0066] (4) Figure 1 and Figure 2 As shown, the independent working scheme of the torch is: first open the oxygen ignition valve 6 to discharge the oxygen medium through the torch ignition chamber 1 and the thrust chamber 2 to the outside, realize the cooling of the liquid oxygen pipeline of the torch ignition chamber 1, then open the hydrogen ignition valve 3, and at the same time, the two electric nozzles 13 are energized, and the ignition chamber 1 ignites under the pressure of the hydrogen and oxygen tanks to form a high-temperature torch, which is sprayed into the thrust chamber 2. It can be used for thrust chamber preheating, small thrust sinking, small flow precooling, etc.

[0067] like Figure 1 and Figure 2 As shown, the torch ignition start-up scheme is: first open the oxygen ignition valve 6 to discharge the oxygen medium through the ignition chamber 1 and the thrust chamber 2 to the outside, so as to cool the liquid oxygen pipeline of the ignition chamber 1, then open the hydrogen ignition valve 3, and at the same time, the two nozzles 13 are energized, and the ignition chamber 1 ignites under the pressure of the hydrogen and oxygen tanks to form a high-temperature torch, which is sprayed into the thrust chamber 2. After the engine is precooled, open the oxygen main valve 7 and the hydrogen main valve 5 respectively, and the hydrogen and oxygen medium entering the thrust chamber 3 is ignited by the high-temperature torch to complete the engine ignition. After the pressure of the engine combustion chamber climbs to more than 90% of the rated operating condition, the oxygen ignition valve 6 can be closed to keep the gas and hydrogen flowing to reliably protect the ignition chamber.

[0068] Although the present invention has been disclosed as above in the form of a preferred embodiment, it is not intended to limit the present invention. Any person skilled in the art may make possible changes and modifications to the technical solution of the present invention by using the methods and technical contents disclosed above without departing from the spirit and scope of the present invention. Therefore, any simple modifications, equivalent changes and modifications made to the above embodiments based on the technical essence of the present invention without departing from the content of the technical solution of the present invention shall fall within the protection scope of the technical solution of the present invention.

Claims

1. A gas hydrogen and liquid oxygen torch ignition system for an expansion cycle hydrogen and oxygen engine, characterized in that The invention comprises an ignition chamber (1), a thrust chamber (2), a hydrogen main valve (5), an oxygen main valve (7), an oxygen main cavitation tube (8), a hydrogen pump (9), an oxygen pump (10), a hydrogen turbine (11), and an oxygen turbine (12); the ignition chamber (1) is a torch ignition chamber, the hydrogen pump (9) is coaxially connected to the hydrogen turbine (11), and the oxygen pump (10) is coaxially connected to the oxygen turbine (12); the ignition chamber (1) is in communication with the thrust chamber (2); After being pressurized by a hydrogen pump (9), liquid hydrogen is converted into gaseous hydrogen through heat exchange in a thrust chamber jacket, and then enters a hydrogen turbine (11) to perform work and drive the hydrogen pump (9) to rotate, and then flows from the outlet of the hydrogen turbine (11) to an oxygen turbine (12), driving the oxygen turbine (12) to drive the oxygen pump (10) to rotate, and the output end of the oxygen pump (10) is connected to an oxygen main cavitation pipe (8), and the oxygen main cavitation pipe (8) is divided into two paths, one of which is connected to the thrust chamber (2) through an oxygen main valve (7), and the other is connected to the ignition chamber (1); The output end of the oxygen turbine (12) is divided into two paths, one of which is connected to the thrust chamber (2) through the hydrogen main valve (5), and the other is connected to the ignition chamber (1); The ignition chamber is ignited by an ignition device; The ignition device comprises an electric nozzle (13), an ignition cable (14), and an exciter (15); The exciter (15) receives an external electric trigger signal, and the electric trigger signal is transmitted to the electric nozzle (13) through the ignition cable (14). The electric nozzle (13) generates an electric spark under the drive of the electric trigger signal, and the electric spark ignites the fuel in the torch ignition chamber; The head of the ignition chamber is a gaseous hydrogen and liquid oxygen injection interface, wherein the oxygen nozzle is arranged in the middle of the injector, which is a direct current mutual impact structure, and the liquid oxygen is atomized after impact; the hydrogen nozzle is arranged in 2 rows under the electric nozzle, which is a tangential hole structure, which is conducive to ignition and the formation of a protective gas film downstream.

2. A gas hydrogen and liquid oxygen torch ignition system for an expansion cycle hydrogen and oxygen engine according to claim 1, characterized in that It also includes an oxygen ignition valve (6); one end of the oxygen ignition valve (6) is connected in parallel with the oxygen main valve (7) and connected to the output end of the oxygen main cavitation tube (8), and the other end is connected to the ignition chamber (1).

3. The gas hydrogen and liquid oxygen torch ignition system for an expansion cycle hydrogen and oxygen engine according to claim 1, characterized in that It also includes a hydrogen ignition valve (3) and a hydrogen ignition sonic nozzle (4). The hydrogen ignition sonic nozzle (4) is connected in parallel with the hydrogen main valve (5) and is connected to the output end of the oxygen turbine (12). One end of the hydrogen ignition valve (3) is connected to the hydrogen ignition sonic nozzle (4), and the other end is connected to the ignition chamber.

4. The gas hydrogen and liquid oxygen torch ignition system for an expansion cycle hydrogen and oxygen engine according to claim 1, characterized in that The torch ignition chamber (1) is located at the center of the head of the thrust chamber (2).

5. The ignition method of a gas hydrogen and liquid oxygen torch ignition system for an expansion cycle hydrogen and oxygen engine according to claim 3, characterized in that The steps include: S1. Initialize the gas hydrogen liquid oxygen torch ignition system: close the oxygen main valve (7), hydrogen main valve (5), oxygen ignition valve (6), and hydrogen ignition valve (3); S2, engine precooling: open the oxygen ignition valve (6) to discharge the oxygen medium through the flare ignition chamber (1) and the thrust chamber (2) to the outside, so as to cool the liquid oxygen pipeline of the flare ignition chamber (1); S3, thrust chamber preheating: open the hydrogen ignition valve (3), and at the same time, energize the ignition device, so that the ignition chamber (1) ignites under the pressure of the hydrogen and oxygen tanks to form a high-temperature torch, which is sprayed into the thrust chamber (2); S4, torch ignition start: open the oxygen main valve (7) and the hydrogen main valve (5) respectively, and the hydrogen and oxygen medium entering the thrust chamber (2) is ignited by the high-temperature torch, completing the engine ignition; S5. After the pressure in the engine combustion chamber rises to more than 90% of the rated operating condition, the oxygen ignition valve (6) can be closed while the hydrogen ignition valve is kept open to keep the gas and hydrogen flowing so that the gas and hydrogen flow can reliably protect the ignition chamber (1); The steps for the propellant to sink to the bottom during the rocket's vacuum glide are: During the vacuum gliding of the rocket, the oxygen ignition valve (6) and the hydrogen ignition valve (3) are opened, the ignition chamber (1) ignites to generate combustion gas, and the combustion gas is ejected through the thrust chamber (2) to generate thrust, thereby achieving the propellant sinking to the bottom with a small overload; Separate small flow precooling steps during rocket vacuum gliding: During the rocket's vacuum gliding, the oxygen ignition valve (6) is opened to discharge the oxygen medium through the torch ignition chamber (1) and the thrust chamber (2), thereby achieving small-flow cooling of the engine oxygen system pipeline and controlling the temperature of the liquid oxygen pipeline.

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