Self-generated supercharged liquid oxygen methane rocket engine with low-ablation throat liner and method

Abstract

The invention discloses a self-generated supercharged liquid oxygen methane rocket engine with a low-ablation throat liner and a method. The rocket engine comprises a methane fuel supply subsystem, a liquid oxygen supply subsystem and a spray pipe subsystem with a throat liner anti-ablation structure. The methane fuel supply subsystem and the liquid oxygen supply subsystem are connected and communicated with each other through a valve, methane fuel and liquid oxygen raw materials are arranged in the methane fuel supply subsystem and the liquid oxygen supply subsystem, and the spray pipe subsystem with the throat liner ablation prevention structure comprises a spray pipe. And the methane fuel supply subsystem and the liquid oxygen supply subsystem are respectively connected with a spray pipe inlet pipeline at the upper end in the spray pipe subsystem with the throat liner anti-ablation structure through respective internal circulating pipelines. According to the rocket engine, the throat liner structure is designed, gaseous methane is sprayed into the cavity in the spraying pipe to form a heat insulation gas film, the temperature of the throat liner part is reduced, the ablation prevention effect of the throat liner is achieved, and the stability and reliability of the system are improved.

Description

TECHNICAL FIELD

[0001] The present application relates to the field of rocket engines, in particular to a self-pressurized liquid oxygen and methane rocket engine with low ablation of throat liner and a method. BACKGROUND

[0002] The liquid oxygen and methane rocket engine is a liquid rocket engine using liquid oxygen and liquid methane as propellants. In recent years, with the growing demand for reusable launch vehicles and deep space exploration missions, liquid oxygen and methane engines have become a research hotspot in the field of space propulsion due to their high performance, low pollution, and strong reusability.

[0003] The tank pressurization system of the liquid oxygen and methane rocket is crucial for stable delivery of propellants and engine performance. The common pressurization method is external gas pressurization, which stores helium in a high-pressure cylinder, warms the low-temperature or normal-temperature helium with an engine warmer, and then pressurizes the tank. The helium warming and pressurization scheme has the advantages of light weight and high pressurization efficiency, but the system is relatively complex and the cost is high.

[0004] The nozzle of the rocket engine is a device that converts thermal energy into kinetic energy, and the size of the throat determines the operating point of the rocket engine, which can control the pressure and gas flow rate of the combustion chamber, and has an important influence on the performance and safety of the engine. The existing nozzle heat insulation structure mainly uses the method of increasing the thickness of the heat insulation layer to improve the reliability of the engine. This method can reduce the ablation risk and improve the reliability of the engine for one-off rockets or short-time working engines, but it increases the negative mass, which is not conducive to improving the mass ratio of the engine, and excessive thickening may change the effective flow area of the throat, affecting the combustion chamber pressure and specific impulse. SUMMARY

[0005] To solve the problems in the background art, the purpose of the present application is to provide a self-pressurized liquid oxygen and methane rocket engine with low ablation of throat liner and a method. The steam generated by heating the fuel of the rocket engine through the nozzle cooling jacket of the nozzle is used to pressurize the fuel tank of the rocket engine and form a certain thickness of gas film inside the throat diameter of the throat liner, and the temperature of the throat liner part is reduced, thereby slowing down the increase of the throat diameter, so as to improve the stability and reliability of the system, reduce the dependence on external gas source, reduce the cost of the engine, and be suitable for liquid oxygen and methane rocket engines.

[0006] The technical solution of the present application is as follows: The present application comprises a methane fuel supply subsystem, a liquid oxygen supply subsystem, a nozzle subsystem with a throat lining anti-ablation structure; the methane fuel supply subsystem and the liquid oxygen supply subsystem are connected and communicated with each other through valves, and the methane fuel supply subsystem and the liquid oxygen supply subsystem are internally provided with methane fuel and liquid oxygen raw materials; the nozzle subsystem with a throat lining anti-ablation structure comprises a nozzle, and the methane fuel supply subsystem and the liquid oxygen supply subsystem are respectively connected with the nozzle inlet pipeline in the nozzle subsystem with a throat lining anti-ablation structure through the circulation pipelines in the methane fuel supply subsystem and the liquid oxygen supply subsystem.

[0007] The nozzle subsystem with a throat lining anti-ablation structure comprises an air pump with a PID controller, a nozzle and a nozzle cooling jacket; the nozzle is the main body of the nozzle subsystem, a throat is arranged in the middle of the nozzle, two ends of the throat are respectively an inlet end and an outlet end, an air pump with a PID controller is arranged on the outer wall of the nozzle inlet end, the outlet of the air pump is connected with the throat of the nozzle, a nozzle cooling jacket is arranged on the outer wall of the nozzle outlet end, and the nozzle cooling jacket is connected with the methane fuel supply subsystem; two nozzle inlet pipelines are arranged on the nozzle inlet end, and the two nozzle inlet pipelines are respectively connected with the methane fuel supply subsystem and the liquid oxygen supply subsystem; the nozzle cooling jacket wraps around the pipeline.

[0008] The methane fuel supply subsystem comprises a methane storage tank, a methane pre-pressing turbine pump, a methane main pump, a methane turbine, a methane pre-chamber, a methane main valve, a gas check valve and a methane auxiliary valve; the methane storage tank is connected with one end of the methane main valve in sequence through the methane pre-pressing turbine pump and the methane main pump, the other end of the methane main valve is connected with the lower end of the nozzle cooling jacket of the nozzle subsystem, the upper end of the nozzle cooling jacket is connected with the lower part of the methane pre-chamber through a pipeline, the upper end of the nozzle cooling jacket is connected with the lower part of the methane storage tank through a pipeline, the upper end of the nozzle cooling jacket is connected with one end of the gas check valve through a pipeline, the other end of the gas check valve is connected with the air pump inlet of the nozzle subsystem, the upper end of the nozzle cooling jacket is connected with the liquid oxygen supply subsystem through a pipeline provided with the methane auxiliary valve, and the upper end of the methane pre-chamber is connected with one of the nozzle inlet pipelines in the nozzle subsystem through the methane turbine.

[0009] The liquid oxygen supply subsystem comprises a liquid oxygen storage tank, a liquid oxygen pre-pressing turbine pump, a liquid oxygen main pump, a liquid oxygen turbine, an oxygen pre-chamber, a liquid oxygen main valve and a liquid oxygen auxiliary valve; the liquid oxygen storage tank is connected with one end of the liquid oxygen main valve in sequence through the liquid oxygen pre-pressing turbine pump and the liquid oxygen main pump, the other end of the liquid oxygen main valve is connected with the lower part of the oxygen pre-chamber, the other end of the liquid oxygen main valve is connected with the lower part of the methane pre-chamber of the methane fuel supply subsystem through a pipeline provided with the liquid oxygen auxiliary valve, the upper end of the oxygen pre-chamber is connected with the inlet of the liquid oxygen turbine, the outlet of the liquid oxygen turbine is connected with the upper part of the liquid oxygen storage tank, the outlet of the liquid oxygen turbine is connected with the other nozzle inlet pipeline in the nozzle subsystem, and the oxygen pre-chamber and the methane pre-chamber of the methane fuel supply subsystem are connected through a pipeline provided with the methane auxiliary valve.

[0010] The nozzle subsystem with the throat-liner anti-ablation structure also comprises an optical fiber temperature sensor, a throat-liner inner cavity, a throat-liner air duct and a nozzle; an annular cavity is arranged in the sidewall of the nozzle throat as the throat-liner inner cavity, and the air pump outlet of the nozzle subsystem is communicated with the throat-liner inner cavity through the throat-liner air duct arranged through the nozzle throat sidewall outside; a plurality of nozzles are arranged in the throat-liner inner cavity in a circumferential direction, each nozzle is arranged radially and penetrates into the nozzle throat, and the optical fiber temperature sensor is fixedly installed on the inner sidewall of the nozzle throat inlet side.

[0011] The methane main valve, the liquid oxygen main valve and the liquid oxygen auxiliary valve use hydraulic ball valves, and the methane auxiliary valve uses a gas check valve; the methane main pump adopts a two-stage pump structure, and the liquid oxygen main pump adopts a single-stage pump structure.

[0012] The methane in the methane storage tank is sequentially pumped into the pipeline in the nozzle cooling jacket through the methane pre-pressing turbine pump and the methane main pump; after the methane in the pipeline in the nozzle cooling jacket is heated and gasified, part of the methane gas enters the methane pre-combustion chamber, the first route of the remaining methane gas enters the oxygen pre-combustion chamber through the methane auxiliary valve, the second route of the methane gas returns to the methane storage tank, and the third route of the methane gas enters the throat-liner inner cavity through the air pump with a PID controller and is sprayed into the cavity in the nozzle through the nozzles connected with the throat-liner inner cavity; the liquid oxygen in the liquid oxygen storage tank is pumped into the liquid oxygen main pump through the liquid oxygen pre-pressing turbine pump, and the liquid oxygen pumped out of the liquid oxygen main pump is divided into two parts, most of the liquid oxygen enters the oxygen pre-combustion chamber through the liquid oxygen main valve, and the remaining liquid oxygen enters the methane pre-combustion chamber through the liquid oxygen auxiliary valve; the liquid oxygen pumped into the liquid oxygen turbine is divided into two routes, one route of the liquid oxygen enters the cavity in the nozzle through the nozzle inlet pipeline, and the other route of the liquid oxygen returns to the liquid oxygen storage tank.

[0013] The fluids in the two pre-combustion chambers enter the methane pre-combustion chamber and the oxygen pre-combustion chamber are combusted, rich combustion gas is generated in the methane pre-combustion chamber after combustion, and oxygen-rich combustion gas is generated in the oxygen pre-combustion chamber; the rich combustion gas drives the methane turbine and then enters the cavity in the nozzle; the oxygen-rich combustion gas drives the oxygen turbine, part of the oxygen-rich combustion gas enters the cavity in the nozzle, and the other part of the oxygen-rich combustion gas enters the liquid oxygen storage tank.

[0014] The optical fiber temperature sensor monitors the temperature of the nozzle inlet, and the power of the air pump with the PID controller is adjusted according to the temperature of the nozzle inlet.

[0015] The present application has the following beneficial effects: 1. The present application uses the fuel gasification and expansion of the system itself to provide the required internal pressure for the storage tank, so that the storage tank structure has sufficient strength and rigidity; this pressurization method does not need to introduce an external gas source, simplifies the system and reduces the cost of the rocket engine.

[0016] 2, The present application utilizes the low temperature characteristics of liquid methane to cool the rocket thrust chamber, and through the design of the throat liner structure, uses gaseous methane to spray into the throat diameter to form a heat insulation gas film, thereby reducing the temperature of the throat liner part, achieving the effect of preventing ablation of the throat liner, thereby slowing the increase of the throat diameter, and improving the system stability and reliability. BRIEF DESCRIPTION OF DRAWINGS

[0017] Figure 1 is a self-pressurized liquid oxygen and methane rocket engine system structure diagram with low ablation of the throat liner provided by the present application; Figure 2 is a planed surface diagram of the nozzle throat liner structure with a throat liner ablation prevention structure provided by the present application; Figure 3 is a control principle diagram of a self-pressurized liquid oxygen and methane rocket engine with low ablation of the throat liner provided by the present application.

[0018] The marks in the figure are as follows: 1-methane storage tank; 2-methane pre-pressing turbine pump; 3-methane main pump; 4-methane turbine; 5-methane pre-chamber; 6-methane main valve; 7-gas check valve; 8-gas pump with PID controller; 9-liquid oxygen storage tank; 10-liquid oxygen pre-pressing turbine pump; 11-liquid oxygen main pump; 12-liquid oxygen turbine; 13-oxygen pre-chamber; 14-liquid oxygen main valve; 15-methane auxiliary valve; 16-liquid oxygen auxiliary valve; 17-nozzle; 17.1-throat liner gas inlet pipeline; 17.2-optical fiber temperature sensor; 17.3-throat liner inner cavity; 17.4-nozzle; 18-nozzle cooling jacket. DETAILED DESCRIPTION

[0019] In order to make the purpose, technical scheme and advantages of the present application clearer and more apparent, the present application will be further described in detail below in combination with the drawings and specific embodiments. It should be understood that the specific embodiments described herein are only used to explain the present application and are not used to limit the present application.

[0020] As shown in Figure 1 , the specific rocket engine includes a methane fuel supply subsystem, a liquid oxygen supply subsystem, and a nozzle subsystem with a throat liner ablation prevention structure; the methane fuel supply subsystem and the liquid oxygen supply subsystem are connected and conducted to each other through valves, and the methane fuel supply subsystem and the liquid oxygen supply subsystem are internally provided with methane fuel and liquid oxygen raw materials; the nozzle subsystem with the throat liner ablation prevention structure comprises a nozzle, and the methane fuel supply subsystem and the liquid oxygen supply subsystem are respectively connected with the nozzle inlet pipeline at the upper end of the nozzle subsystem with the throat liner ablation prevention structure through the circulating pipelines in the respective internal parts thereof.

[0021] More specifically, the methane fuel supply subsystem is connected with the nozzle subsystem with throat-liner anti-ablation structure through the nozzle cooling jacket 18, the gas pump's inlet pipeline, the nozzle inlet pipeline, and the methane fuel supply subsystem is connected with the liquid oxygen supply subsystem through the pipeline where the methane sub-valve 15 is located; The liquid oxygen supply subsystem is connected with the methane fuel supply subsystem through the pipeline where the liquid oxygen sub-valve 16 is located, and the liquid oxygen supply subsystem is connected with the nozzle subsystem with throat-liner anti-ablation structure through the nozzle inlet pipeline.

[0022] The innovation of the present application is to provide a steam which is vaporized after the fuel of the rocket engine is heated by the nozzle cooling jacket 18 of the nozzle, to pressurize the fuel tank of the rocket engine, to make it have sufficient strength and rigidity, and to form a certain thickness of gas film inside the throat diameter of the throat-liner, to reduce the temperature of the throat-liner part, to slow down the increase of the throat diameter, to have the effect of throat-liner anti-ablation, to reduce the dependence on external air source, and to reduce the cost of the engine on the basis of improving the stability and reliability of the system.

[0023] The nozzle subsystem with throat-liner anti-ablation structure comprises a gas pump 8 with a PID controller, a nozzle 17, and a nozzle cooling jacket 18; the nozzle 17 serves as the main body of the nozzle subsystem, a throat is arranged in the middle of the nozzle 17, two ends of the throat are respectively an inlet end and an outlet end, an outer wall of the inlet end above the throat of the nozzle 17 is provided with the gas pump 8 with a PID controller, an outlet of the gas pump 8 is connected with the throat of the nozzle 17, an outer wall of the outlet end above the throat of the nozzle 17 is provided with the nozzle cooling jacket 18, and the nozzle cooling jacket 18 is connected with the methane fuel supply subsystem; the inlet end of the nozzle 17 is provided with two nozzle inlet pipelines, and the two nozzle inlet pipelines are respectively connected with the methane fuel supply subsystem and the liquid oxygen supply subsystem; and the nozzle cooling jacket 18 wraps around the pipeline once.

[0024] The methane fuel supply subsystem comprises a methane tank 1, a methane pre-pressing turbo pump 2, a methane main pump 3, a methane turbine 4, a methane pre-combustion chamber 5, a methane main valve 6, a gas check valve 7, and a methane sub-valve 15; the methane tank 1 is connected with one end of the methane main valve 6 in sequence after the methane pre-pressing turbo pump 2 and the methane main pump 3, the other end of the methane main valve 6 is connected with the lower end of the nozzle cooling jacket 18 of the nozzle subsystem with throat-liner anti-ablation structure, the upper end of the nozzle cooling jacket 18 is connected with the lower part of the methane pre-combustion chamber 5 through a pipeline, the upper end of the nozzle cooling jacket 18 is connected with the lower part of the methane tank 1 through a pipeline, the upper end of the nozzle cooling jacket 18 is connected with one end of the gas check valve 7 through a pipeline, the other end of the gas check valve 7 is connected with the inlet of the gas pump 8 of the nozzle subsystem with throat-liner anti-ablation structure; the upper end of the nozzle cooling jacket 18 is connected with the liquid oxygen supply subsystem through a pipeline with the methane sub-valve 15; and the upper end of the methane pre-combustion chamber 5 is connected with one of the nozzle inlet pipelines of the nozzle subsystem with throat-liner anti-ablation structure through the methane turbine 4.

[0025] In the specific implementation, three tee components are arranged between the upper end of the nozzle cooling jacket 18, the lower part of the methane pre-chamber 5, the lower part of the methane tank 1, one end of the gas check valve 7, and the liquid oxygen supply subsystem. The upper end of the nozzle cooling jacket 18 is connected to one end of a first tee, the other two ends of the first tee are respectively connected to one end of the gas check valve 7 and one end of a second tee, the other two ends of the second tee are respectively connected to the lower part of the methane pre-chamber 5 and the lower end of the gas pump 8 of the nozzle subsystem with throat-liner anti-ablation structure. The nozzle cooling jacket 18 is connected to one end of a third tee, the other two ends of the third tee are respectively connected to the liquid oxygen supply subsystem and one end of the second tee.

[0026] The liquid oxygen supply subsystem includes a liquid oxygen tank 9, a liquid oxygen pre-pressurization turbo pump 10, a liquid oxygen main pump 11, a liquid oxygen turbine 12, an oxygen pre-chamber 13, a liquid oxygen main valve 14, and a liquid oxygen auxiliary valve 16. The liquid oxygen tank 9 is connected to one end of the liquid oxygen main valve 14 in sequence through the liquid oxygen pre-pressurization turbo pump 10 and the liquid oxygen main pump 11. The other end of the liquid oxygen main valve 14 is connected to the lower part of the oxygen pre-chamber 13. The other end of the liquid oxygen main valve 14 is connected to the lower part of the methane pre-chamber 5 of the methane fuel supply subsystem through a pipeline with the liquid oxygen auxiliary valve 16. The upper end of the oxygen pre-chamber 13 is connected to the inlet of the liquid oxygen turbine 12. The outlet of the liquid oxygen turbine 12 is connected to the upper part of the liquid oxygen tank 9 and another nozzle inlet pipeline in the nozzle subsystem with throat-liner anti-ablation structure. The oxygen pre-chamber 13 and the methane pre-chamber 5 of the methane fuel supply subsystem are connected through a pipeline with the methane auxiliary valve 15.

[0027] More specifically, two tee components are arranged between the upper part of the liquid oxygen tank 9, one end of the liquid oxygen main valve 14, the lower part of the methane pre-chamber 5, the lower part of the oxygen pre-chamber 13, the outlet of the liquid oxygen turbine 12, and the nozzle inlet pipeline. The outlet of the liquid oxygen turbine 12 is connected to one end of a fourth tee. The other two ends of the first tee are respectively connected to the upper part of the liquid oxygen tank 9 and another nozzle inlet pipeline in the nozzle subsystem with throat-liner anti-ablation structure. One end of the liquid oxygen main valve 14 is connected to one end of a second tee. The other two ends of the second tee are respectively connected to the lower part of the methane pre-chamber 5 of the methane fuel supply subsystem and the lower part of the oxygen pre-chamber 13.

[0028] As Figure 2As shown, the nozzle subsystem with throat-liner anti-ablation structure further comprises an optical fiber temperature sensor 17.2, a throat-liner inner cavity 17.3, a throat-liner inlet duct 17.1 and a plurality of nozzles 17.4; the annular cavity in the sidewall of the nozzle 17 throat is arranged as the throat-liner inner cavity 17.3, and the outlet of the gas pump 8 of the nozzle subsystem with throat-liner anti-ablation structure is communicated through the throat-liner inlet duct 17.1 and the throat-liner inner cavity 17.3 arranged through the outer nozzle 17 throat sidewall; a plurality of nozzles 17.4 are arranged on the inner side of the throat-liner inner cavity 17.3 in a circumferential direction, each nozzle 17.4 is arranged radially and penetrates the nozzle 17 throat sidewall to connect to the nozzle 17 throat, and the optical fiber temperature sensor 17.2 is fixedly installed on the inner sidewall of the nozzle 17 throat inlet side, and the optical fiber temperature sensor 17.2 is located on the inlet side of the nozzle 17 relative to the throat-liner inner cavity 17.3.

[0029] The methane main valve 6, the liquid oxygen main valve 14 and the liquid oxygen auxiliary valve 16 use hydraulic ball valves, and the methane auxiliary valve 15 uses a gas check valve; the methane main pump 3 adopts a two-stage pump structure considering the low density of methane, and the liquid oxygen main pump 11 adopts a single-stage pump structure.

[0030] In a specific implementation, the liquid methane in the methane storage tank 1 is pressurized by the methane pre-pressurization turbine pump 2 to increase the inlet pressure of the methane main pump 3, and the liquid methane is heated and gasified after passing through the pipeline in the nozzle cooling jacket 18 under the pressurization of the methane main pump 3 and the adjustment of the methane main valve 6, and at the same time, the cavity in the nozzle is cooled; most of the gasified methane gas enters the methane pre-combustion chamber 5, the rest of the first route methane gas enters the oxygen pre-combustion chamber 13 through the adjustment of the methane auxiliary valve 15, the second route methane gas returns to the methane storage tank 1 to pressurize it, and the third route methane gas enters the gas pump 8 with a PID controller after passing through the gas check valve 7.

[0031] The methane gas in the methane pre-combustion chamber 5 is mixed with a small amount of liquid oxygen provided by the liquid oxygen supply subsystem to combust, to generate rich combustion gas, and the rich combustion gas drives the methane turbine 4 and then enters the cavity in the nozzle; the cavity in the nozzle is the thrust chamber in the rocket engine.

[0032] The liquid oxygen in the liquid oxygen storage tank 9 is pressurized by the liquid oxygen pre-pressurization turbine pump 10 to increase the inlet pressure of the liquid oxygen injection pump 11, and the liquid oxygen is pressurized by the liquid oxygen main pump 11 and adjusted by the liquid oxygen main valve 6, most of the liquid oxygen enters the oxygen pre-combustion chamber 13, and the rest of the liquid oxygen enters the methane pre-combustion chamber 5 through the adjustment of the liquid oxygen auxiliary valve 16; The oxygen in the oxygen pre-combustion chamber 13 is mixed with a small amount of methane gas provided by the methane supply subsystem to combust, to generate rich oxygen gas, and most of the rich oxygen gas drives the methane turbine 12 and then enters the inner cavity of the nozzle, and the rest of the rich oxygen gas enters the liquid oxygen storage tank 9 to pressurize it.

[0033] Under normal conditions, the methane main valve 6, the liquid oxygen main valve 14, the methane auxiliary valve 15, and the liquid oxygen auxiliary valve 16 are all open. The control principle diagram of this invention is shown below. Figure 3 As shown, methane vapor passes through Figure 1 After passing through the one-way gas valve 7, the gas enters the air pump 8 equipped with a PID controller.

[0034] The fiber optic temperature sensor 17.2 monitors the inlet gas temperature at the nozzle throat in real time. The air pump 8 with a PID controller adjusts its power according to the temperature signal and under the regulation of the PID controller, pumping methane gas evenly through the throat liner inlet pipe 17.1 into the throat liner cavity 17.3. The gas in the cavity enters the nozzle cavity through several nozzles 17.4, forming a uniform gas film that isolates the high-temperature gas from the throat liner, thus preventing throat liner ablation and extending the throat liner's lifespan. The throat liner refers to the throat of the nozzle.

[0035] like Figure 3 As shown, the specific working process of the self-pressurized liquid oxygen methane rocket engine of the present invention is as follows: The methane in the methane storage tank 1 is sequentially pumped into the nozzle cooling jacket 18 through the methane pre-pressurization turbine pump 2 and the main methane pump 3 via two-stage pressurization to cool the cavity inside the nozzle. Simultaneously, after the methane in the nozzle cooling jacket 18 is heated and vaporized, a large portion of the methane gas enters the methane pre-combustion chamber 5. The remaining small portion of the first path of methane gas enters the oxygen pre-combustion chamber 13 through the methane auxiliary valve 15. The second path of methane gas returns to the methane storage tank 1 to be pressurized. The third path of methane gas enters the throat liner inlet pipe 17.1 through the air pump 8 with a PID controller and then enters the throat liner cavity 17.3. It is then sprayed into the cavity inside the nozzle through the nozzle 17.4 connected to the throat liner cavity 17.3, forming a heat-insulating gas film, which reduces the temperature of the throat liner and prevents throat liner ablation, thereby slowing down the increase in throat diameter.

[0036] Liquid oxygen in liquid oxygen storage tank 9 is pumped into liquid oxygen main pump 11 by liquid oxygen pre-pressurization turbine pump 10. After pressurization, the liquid oxygen pumped out by liquid oxygen main pump 11 is divided into two parts. Most of the liquid oxygen enters oxygen pre-combustion chamber 13 through liquid oxygen main valve 14, and the remaining liquid oxygen enters methane pre-combustion chamber 5 through liquid oxygen secondary valve 16. The liquid oxygen that enters oxygen pre-combustion chamber 13 is pumped into liquid oxygen turbine 12 and then divided into two paths. One path of liquid oxygen enters the cavity inside the nozzle through the nozzle inlet pipe, and the other path of liquid oxygen returns to liquid oxygen storage tank 9 to pressurize it.

[0037] The fluid combustion in the two pre-combustion chambers of the methane pre-combustion chamber 5 and the oxygen pre-combustion chamber 13 produces rich combustion gas in the methane pre-combustion chamber 5 and rich oxygen gas in the oxygen pre-combustion chamber 13; the rich combustion gas drives the methane turbine 4 and then enters the cavity in the nozzle; the rich oxygen gas drives the oxygen turbine 12 and then a large part of the rich oxygen gas enters the cavity in the nozzle and the other part of the rich oxygen gas enters the liquid oxygen storage tank to increase the pressure; the rich combustion refers to the mixture of methane and oxygen, in which the content of methane is relatively high and the content of oxygen is relatively low; the rich oxygen refers to the mixture of methane and oxygen, in which the content of oxygen is relatively high and the content of methane is relatively low.

[0038] The optical fiber temperature sensor 17.2 monitors the temperature of the throat inlet, adjusts the power of the air pump 8 with a PID controller according to the temperature of the throat inlet, and then controls the intake amount of the rich combustion gas to achieve good throat liner anti-ablation effect.

[0039] The above specific embodiments are used to explain and illustrate the present application, rather than limit the present application, and any modification and change made to the present application within the protection scope of the claims of the present application falls into the protection scope of the present application.

Claims

1. A self-pressurized liquid oxygen-methane rocket engine with low throat liner ablation, characterized in that: It includes a methane fuel supply subsystem, a liquid oxygen supply subsystem, and a nozzle subsystem with a throat liner for erosion protection. The methane fuel supply subsystem and the liquid oxygen supply subsystem are connected and circulated to each other via valves. The methane fuel supply subsystem and the liquid oxygen supply subsystem contain methane fuel and liquid oxygen feedstock. The nozzle subsystem with a throat liner for erosion protection contains a nozzle. The methane fuel supply subsystem and the liquid oxygen supply subsystem are respectively connected to the nozzle inlet pipe of the nozzle subsystem with a throat liner for erosion protection through their own internal circulation pipelines.

2. The self-pressurized liquid oxygen-methane rocket engine with low throat liner ablation according to claim 1, characterized in that: The nozzle subsystem with throat lining anti-ablation structure includes an air pump (8) with a PID controller, a nozzle (17), and a nozzle cooling jacket (18). The nozzle (17) is the main body of the nozzle subsystem. A throat is provided in the middle of the nozzle (17). The two ends of the throat are the inlet end and the outlet end, respectively. An air pump (8) with a PID controller is installed on the outer wall of the inlet end of the nozzle (17). The outlet of the air pump (8) is connected to the throat of the nozzle (17). A nozzle cooling jacket (18) is provided on the outer wall of the outlet end of the nozzle (17). The nozzle cooling jacket (18) is connected to the methane fuel supply subsystem. Two nozzle inlet pipes are provided at the inlet end of the nozzle (17). The two nozzle inlet pipes are connected to the methane fuel supply subsystem and the liquid oxygen supply subsystem, respectively. The nozzle cooling jacket (18) wraps around the pipes.

3. The self-pressurized liquid oxygen-methane rocket engine with low throat liner ablation according to claim 2, characterized in that: The methane fuel supply subsystem includes a methane storage tank (1), a methane pre-compression turbopump (2), a methane main pump (3), a methane turbine (4), a methane pre-combustion chamber (5), a methane main valve (6), a gas check valve (7), and a methane auxiliary valve (15). The methane storage tank (1) is connected to one end of the methane main valve (6) after passing through the methane pre-compression turbopump (2) and the methane main pump (3). The other end of the methane main valve (6) is connected to the lower end of the nozzle cooling jacket (18) of the nozzle subsystem. The upper end of the nozzle cooling jacket (18) is connected to the methane main valve (6) via a pipeline. The lower part of the methane pre-combustion chamber (5) is connected to the lower part of the nozzle cooling jacket (18) via a pipe. The upper end of the nozzle cooling jacket (18) is connected to one end of the gas check valve (7) via a pipe. The other end of the gas check valve (7) is connected to the inlet of the gas pump (8) of the nozzle subsystem. The upper end of the nozzle cooling jacket (18) is connected to the liquid oxygen supply subsystem via a pipe with a methane auxiliary valve (15). The upper end of the methane pre-combustion chamber (5) is connected to one of the nozzle inlet pipes in the nozzle subsystem via the methane turbine (4).

4. The self-pressurized liquid oxygen-methane rocket engine with low throat liner ablation according to claim 3, characterized in that: The liquid oxygen supply subsystem includes a liquid oxygen tank (9), a liquid oxygen pre-compression turbine pump (10), a liquid oxygen main pump (11), a liquid oxygen turbine (12), an oxygen pre-combustion chamber (13), a liquid oxygen main valve (14), and a liquid oxygen auxiliary valve (16). The liquid oxygen tank (9) is connected to one end of the liquid oxygen main valve (14) via the liquid oxygen pre-compression turbine pump (10) and the liquid oxygen main pump (11) in sequence. The other end of the liquid oxygen main valve (14) is connected to the lower part of the oxygen pre-combustion chamber (13). The other end of the liquid oxygen main valve (14) is connected via a... The pipeline with the liquid oxygen auxiliary valve (16) is connected to the lower part of the methane pre-combustion chamber (5) of the methane fuel supply subsystem. The upper end of the oxygen pre-combustion chamber (13) is connected to the inlet of the liquid oxygen turbine (12). The outlet of the liquid oxygen turbine (12) is connected to the upper part of the liquid oxygen storage tank (9). The outlet of the liquid oxygen turbine (12) is connected to another nozzle inlet pipeline in the nozzle subsystem. The oxygen pre-combustion chamber (13) and the methane pre-combustion chamber (5) of the methane fuel supply subsystem are connected via a pipeline with a methane auxiliary valve (15).

5. The self-pressurized liquid oxygen-methane rocket engine with low throat liner ablation according to claim 1, characterized in that: The nozzle subsystem with throat lining anti-ablation structure also includes a fiber optic temperature sensor (17.2), a throat lining cavity (17.3), a throat lining air inlet pipe (17.1), and a nozzle (17.4); an annular cavity is provided in the side wall of the throat of the nozzle (17) as the throat lining cavity (17.3), and the outlet of the air pump (8) of the nozzle subsystem is connected to the throat lining cavity (17.3) through the throat lining air inlet pipe (17.1) arranged through the side wall of the throat of the nozzle (17) on the outside; multiple nozzles (17.4) are arranged circumferentially on the inner side of the throat lining cavity (17.3), and each nozzle (17.4) is arranged radially and connected through the throat of the nozzle (17). A fiber optic temperature sensor (17.2) is fixedly installed on the inner side wall of the inlet side of the throat of the nozzle (17).

6. A self-pressurized liquid oxygen-methane rocket engine with low throat liner ablation according to claim 3 or 4, characterized in that: The methane main valve (6), liquid oxygen main valve (14), and liquid oxygen auxiliary valve (16) are hydraulic ball valves, and the methane auxiliary valve (15) is a gas check valve; the methane main pump (3) adopts a two-stage pump structure, and the liquid oxygen main pump (11) adopts a single-stage pump structure.

7. A method for preventing ablation of the throat liner of a self-pressurized liquid oxygen-methane rocket engine as described in any one of claims 2-5, characterized in that: The methane in the methane storage tank (1) is pumped sequentially through the methane pre-compression turbine pump (2) and the methane main pump (3) into the pipeline inside the nozzle cooling jacket (18). After the methane in the pipeline of the nozzle cooling jacket (18) is heated and vaporized, a portion of the methane gas enters the methane pre-combustion chamber (5). The remaining first path of methane gas enters the oxygen pre-combustion chamber (13) through the methane auxiliary valve (15). The second path of methane gas returns to the methane storage tank (1). The third path of methane gas enters the throat liner inlet pipeline (17.1) through the air pump (8) with a PID controller and then enters the throat liner inner cavity (17.3). (17.3) The nozzle (17.4) connected to the nozzle sprays into the cavity inside the nozzle pipe; the liquid oxygen in the liquid oxygen storage tank (9) is pumped into the liquid oxygen main pump (11) through the liquid oxygen pre-pressurization turbine pump (10). The liquid oxygen pumped out by the liquid oxygen main pump (11) is divided into two parts. Most of the liquid oxygen enters the oxygen pre-combustion chamber (13) through the liquid oxygen main valve (14), and the remaining liquid oxygen enters the methane pre-combustion chamber (5) through the liquid oxygen secondary valve (16). The liquid oxygen that enters the oxygen pre-combustion chamber (13) is pumped into the liquid oxygen turbine (12) and then divided into two paths. One path of liquid oxygen enters the cavity inside the nozzle pipe through the nozzle inlet pipe, and the other path of liquid oxygen returns to the liquid oxygen storage tank (9).

8. The throat liner low-ablation method according to claim 7, characterized in that: The fluid entering the two pre-combustion chambers, methane pre-combustion chamber (5) and oxygen pre-combustion chamber (13), is combusted. After combustion, fuel-rich gas is generated in methane pre-combustion chamber (5) and oxygen-rich gas is generated in oxygen pre-combustion chamber (13). The fuel-rich gas drives the methane turbine (4) and then enters the cavity inside the nozzle; After the oxygen-enriched gas drives the oxygen turbine (12), part of the oxygen-enriched gas enters the cavity inside the nozzle, and the other part of the oxygen-enriched gas enters the liquid oxygen storage tank.

9. A self-pressurized liquid oxygen-methane rocket engine with low throat liner ablation according to claim 7, characterized in that: The fiber optic temperature sensor (17.2) monitors the temperature of the throat inlet and adjusts the power of the air pump (8) with a PID controller according to the temperature of the throat inlet.

Images