A full-flow cycle liquid rocket engine with a fixed-mixture ratio precombustion chamber

Abstract

The present invention relates to a full-flow cycle liquid rocket engine using a fixed mixing ratio precombustion chamber, and relates to the field of rocket engines. The oxygen-rich precombustion chamber and the fuel-rich precombustion chamber both include combustion components and mixing components. The oxidant feed pipe is respectively connected to the oxygen-rich precombustion chamber combustion component, the oxygen-rich precombustion chamber mixing component, and the fuel-rich precombustion chamber combustion component. The fuel feed pipe is respectively connected to the fuel-rich precombustion chamber mixing component, the fuel-rich precombustion chamber combustion component, and the oxygen-rich precombustion chamber combustion component. The volume ratios of the oxidant and the fuel entering the oxygen-rich precombustion chamber combustion component and the fuel-rich precombustion chamber combustion component are all fixed values. The engine thrust control of the present invention is decoupled, controllability is enhanced, the engine deep throttling capability and low-frequency combustion stability are improved, and the control system is greatly simplified. The mixing ratio of the precombustion chamber combustion process is fixed, the precombustion chamber design is simplified, the combustion stability at deep throttling is improved, and the reliability and high-frequency combustion stability of the precombustion chamber are improved.

Description

Technical Field

[0001] The invention relates to the field of rocket engines, and in particular to a full-flow cycle liquid rocket engine adopting a fixed-mixing ratio pre-combustion chamber. Background Art

[0002] Liquid rocket engines can generally be divided into open cycles and closed cycles in terms of circulation methods. Among them, closed cycles generally have higher chamber pressures and greater specific impulses, which also means that closed cycle engines have higher performance. The full-flow cycle engine is the highest-performance circulation method in the closed cycle. It is equipped with two precombustion chambers, an oxygen-rich precombustion chamber and a fuel-rich precombustion chamber. The oxygen-rich precombustion chamber drives the liquid oxygen pump, and the fuel-rich precombustion chamber drives the fuel pump. The gas exhausted from the two precombustion chambers will be injected into the combustion chamber together with the propellant for supplementary combustion. Since the full-flow cycle engine has two sets of turbo pumps, it has greater turbine power and higher combustion chamber pressure, and the thrust chamber is a gas-to-gas combustion process, which avoids atomization and evaporation at the head of the thrust chamber, enhances the combustion stability of the thrust chamber, and improves combustion efficiency.

[0003] The first engine to adopt this cycle was the Soviet Union's RD270 engine, but it ultimately failed due to combustion instability problems; Rocketdyne modified the SSME engine with two rich-fuel precombustion chambers and two sets of turbopumps into the full-flow cycle RS2100, but failed to complete the development due to the cancellation of the X33; SpaceX's Raptor engine is the first full-flow cycle engine put into use today. The engine chamber pressure can reach 33MPa, and deep throttling is achieved. The thrust adjustment range is 20%-100%, and it has good reusability. It is planned to be used in the I TS interstellar transportation system to achieve low-cost aerospace cargo transportation.

[0004] Low-cost reusable rockets are an unstoppable trend in the current aerospace field. They require engines to have good control characteristics and deep throttling capabilities. Although full-flow cycle engines have high performance, their system flow paths are complex, and the oxidant supply path and the fuel supply path are highly coupled. There is a relatively complex nonlinear relationship between the mixture ratio and flow rate of the two pre-combustion chambers. During variable operating conditions, the matching relationship between turbine power and the pre-combustion chamber mixture ratio is relatively complex. Therefore, the control system design is difficult and the starting process is difficult to control. In addition, since the pre-combustion chamber mixture ratio deviates excessively from the chemical equivalence ratio during variable operating conditions, it is easy to cause combustion instability, making it impossible for the engine to be deeply throttled. Therefore, there are also problems such as difficulty in changing the engine thrust over a large range. Summary of the invention

[0005] The technical problem to be solved by the present invention is how to improve the control performance of a full-flow cycle engine and enable the engine to have variable thrust capability.

[0006] The technical solution of the present invention to solve the above technical problems is as follows: a full-flow cycle liquid rocket engine using a fixed mixing ratio precombustion chamber, comprising an oxidizer feed pipe, a fuel feed pipe, an oxygen-rich precombustion chamber, a fuel-rich precombustion chamber and a thrust chamber, the oxygen-rich precombustion chamber comprising an oxygen-rich precombustion chamber combustion component and an oxygen-rich precombustion chamber mixing component, the outlet of the oxygen-rich precombustion chamber combustion component is connected to the inlet of the oxygen-rich precombustion chamber mixing component, the fuel-rich precombustion chamber comprising a fuel-rich precombustion chamber mixing component and a fuel-rich precombustion chamber combustion component, the outlet of the fuel-rich precombustion chamber combustion component is connected to the inlet of the fuel-rich precombustion chamber mixing component, the oxidizer feed pipe is divided into The fuel feed pipe is respectively connected with the oxygen-rich precombustion chamber combustion component, the oxygen-rich precombustion chamber mixing component and the rich precombustion chamber combustion component, and conveys oxidant. The fuel feed pipe is respectively connected with the rich precombustion chamber mixing component, the rich precombustion chamber combustion component and the oxygen-rich precombustion chamber combustion component, and conveys fuel. The volume ratio of the oxidant and the fuel entering the oxygen-rich precombustion chamber combustion component is a first fixed mixing ratio, and the volume ratio of the oxidant and the fuel entering the rich precombustion chamber combustion component is a second fixed mixing ratio. The outlet of the oxygen-rich precombustion chamber mixing component and the outlet of the rich precombustion chamber mixing component are both connected with the thrust chamber.

[0007] The beneficial effects of the present invention are as follows: both the oxygen-rich precombustion chamber and the fuel-rich precombustion chamber are composed of a combustion component and a mixing component with a fixed mixing ratio, and the flow rates entering the combustion component and the mixing component can be controlled separately. When the thrust is changed, the flow rate entering the mixing component can be adjusted to change the propellant flow rate. Since the primary injection and secondary injection flow rates of the precombustion chamber are adjusted separately, the decoupling of the engine thrust control is achieved, the controllability of the engine is enhanced, and the deep throttling capability and low-frequency combustion stability of the engine are improved, and the control system is greatly simplified. In addition, since the mixing ratio of the combustion process of the oxygen-rich precombustion chamber and the fuel-rich precombustion chamber is fixed, the design of the precombustion chamber can be greatly simplified, and its combustion stability at deep throttling is improved, and the reliability and high-frequency combustion stability of the precombustion chamber are improved.

[0008] Based on the above technical solution, the present invention can also be improved as follows.

[0009] Furthermore, it also includes an oxidant pump and an oxygen-rich gas turbine, the oxidant pump is arranged in series in the oxidant feed pipe, the outlet of the oxygen-rich pre-combustion chamber mixing component is connected to the thrust chamber through the oxygen-rich gas turbine, and the oxidant pump and the oxygen-rich gas turbine are connected in a transmission manner.

[0010] The beneficial effect of adopting the above further scheme is that the oxidant pump and the oxygen-rich gas turbine constitute a turbopump to provide power for the flow of the oxidant.

[0011] Furthermore, it also includes a rich fuel gas turbine and a fuel pump, wherein the fuel pump is arranged in series in the fuel feed pipe, and the outlet of the rich fuel pre-combustion chamber mixing component is connected to the thrust chamber through the rich fuel gas turbine.

[0012] The beneficial effect of adopting the above further scheme is that the rich fuel gas turbine and the fuel pump constitute a turbopump to provide power for the flow of fuel.

[0013] Furthermore, it also includes a first oxygen secondary pipeline, a second oxygen secondary pipeline, an oxygen main pipeline, an oxygen secondary fuel-rich precombustion chamber throttle valve, an oxygen secondary oxygen-rich precombustion chamber throttle valve and an oxygen main throttle valve. The oxidant feed pipe is connected to the oxygen-rich precombustion chamber combustion component through the first oxygen secondary pipeline, and the first oxygen secondary pipeline is provided with the oxygen secondary oxygen-rich precombustion chamber throttle valve; the oxidant feed pipe is connected to the fuel-rich precombustion chamber combustion component through the second oxygen secondary pipeline, and the second oxygen secondary pipeline is provided with the oxygen secondary fuel-rich precombustion chamber throttle valve; the oxidant feed pipe is connected to the oxygen-rich precombustion chamber mixing component through the oxygen main pipeline, and the oxygen main pipeline is provided with the oxygen main throttle valve.

[0014] The beneficial effect of adopting the above further scheme is that the oxygen secondary rich precombustion chamber throttle valve and the oxygen secondary oxygen rich precombustion chamber throttle valve are used to control the oxidant flow entering the rich precombustion chamber combustion component and the oxygen rich precombustion chamber combustion component respectively. The oxygen main throttle valve is used to control the oxidant flow entering the oxygen rich precombustion chamber mixing component.

[0015] Furthermore, it also includes a main fuel feed pipeline, a main fuel discharge pipeline and a main fuel throttle valve. The thrust chamber has a thrust chamber cooling groove. The two ends of the main fuel feed pipeline are respectively connected to the fuel feed pipe and the inlet of the thrust chamber cooling groove. The two ends of the main fuel discharge pipeline are respectively connected to the outlet of the thrust chamber cooling groove and the rich-fuel pre-combustion chamber mixing component. The main fuel feed pipeline is provided with the main fuel throttle valve.

[0016] The beneficial effect of adopting the above further scheme is that the fuel flows into the cooling channel of the thrust chamber for heat exchange and then flows into the mixing component of the fuel-rich pre-combustion chamber through the fuel main discharge pipe.

[0017] Furthermore, it also includes a first fuel bypass pipeline, a second fuel bypass pipeline, a fuel bypass rich precombustion chamber throttle valve and a fuel bypass oxygen-rich precombustion chamber throttle valve. The fuel feed pipe is connected to the fuel-rich precombustion chamber combustion component through the first fuel bypass pipeline, and the fuel bypass rich precombustion chamber throttle valve is provided on the first fuel bypass pipeline; the fuel feed pipe is connected to the oxygen-rich precombustion chamber combustion component through the second fuel bypass pipeline, and the fuel bypass oxygen-rich precombustion chamber throttle valve is provided on the second fuel bypass pipeline.

[0018] The beneficial effect of adopting the above further solution is that the secondary fuel path rich precombustion chamber throttle valve is used to control the fuel flow entering the rich precombustion chamber combustion component. The secondary fuel path oxygen-rich precombustion chamber throttle valve is used to control the fuel flow entering the oxygen-rich precombustion chamber combustion component.

[0019] Furthermore, the ignition method of the oxygen-rich pre-combustion chamber is gunpowder ignition, spark plug torch ignition or chemical ignition; the ignition method of the fuel-rich pre-combustion chamber is gunpowder ignition, spark plug torch ignition or chemical ignition.

[0020] Furthermore, the thrust chamber is ignited by gunpowder ignition, spark plug torch ignition or chemical ignition.

[0021] Furthermore, a fuel-rich cooling channel is provided on the side wall of the fuel-rich precombustion chamber combustion component, the fuel feed pipe is connected to the inlet of the fuel-rich cooling channel, and the outlet of the fuel-rich cooling channel is connected to the fuel-rich precombustion chamber combustion component; an oxygen-rich cooling channel is provided on the side wall of the oxygen-rich precombustion chamber combustion component, the fuel feed pipe or the oxidant feed pipe is connected to the inlet of the oxygen-rich cooling channel, and the outlet of the oxygen-rich cooling channel is connected to the oxygen-rich precombustion chamber combustion component.

[0022] The beneficial effect of adopting the above further scheme is that fuel is used to regenerate and cool the wall surface in the fuel-rich precombustion chamber combustion component, and fuel or oxidant is used to regenerate and cool the wall surface in the oxygen-rich precombustion chamber combustion component.

[0023] Furthermore, a first side zone injector for injecting only fuel is arranged at the outermost periphery of the injection disk of the fuel-rich precombustion chamber combustion component, and a second side zone injector for injecting only oxidant is arranged at the outermost periphery of the injection disk of the oxygen-rich precombustion chamber combustion component.

[0024] The beneficial effect of adopting the above further solution is that the pre-combustion chamber combustion component can also be cooled by liquid film. The cooling method of the pre-combustion chamber combustion part can also be a combination of regenerative cooling and liquid film cooling. Since the low-temperature fuel or oxidant in the mixing component accounts for the vast majority of the mass, the mixing component may not need to be cooled if it is reasonably designed.

[0025] The beneficial effects of the present invention are as follows: the oxygen-rich precombustion chamber and the fuel-rich precombustion chamber are both composed of a combustion component with a fixed mixing ratio and a mixing component downstream thereof, and a small portion of the propellant (oxidant or fuel) enters the combustion component through the oxidant feed pipe and the fuel feed pipe, and enters the mixing component after being fully burned. The mixing component of the oxygen-rich precombustion chamber and the mixing component of the fuel-rich precombustion chamber respectively inject the oxidant and the fuel for a second time, and mix them with the fuel gas from the combustion component to reduce the fuel gas temperature, and the fuel-rich fuel gas and oxygen-rich fuel gas with lower temperatures obtained by mixing drive two sets of turbine pumps respectively. Two throttle valves with the same control rate (i.e., the oxygen secondary fuel-rich precombustion chamber throttle valve and the fuel secondary fuel-rich precombustion chamber throttle valve, and the oxygen secondary oxygen-rich precombustion chamber throttle valve and the fuel secondary oxygen-rich precombustion chamber throttle valve) are arranged on the propellant supply flow path of each precombustion chamber combustion component to control the fuel and oxidant flow rates entering them respectively, and control the turbine power by controlling the power of the combustion component, thereby controlling the engine thrust. A throttle valve (oxygen main throttle valve and fuel main throttle valve) is set on the fuel and oxidizer main lines respectively to control the flow of the oxidizer or fuel entering the corresponding mixing component to control the turbine temperature and the thrust chamber mixing ratio.

[0026] Since the mixing ratio of the combustion components of the pre-combustion chamber is not changed during adjustment, the two sets of turbo pumps will not affect each other, and decoupling control of the fuel and oxidant flow rates is achieved. The present invention has a simple control system, high flexibility, good stability, low turbine temperature at startup, and flexible control performance of stage adjustment. In addition, since the pre-combustion chamber isolates the primary injection and secondary injection processes, the jet momentum ratio of the combustion components is constant, the high-frequency and low-frequency combustion stability is good, and the design is simple. Therefore, the present invention can be well applied to recoverable rockets with complex launch missions. BRIEF DESCRIPTION OF THE DRAWINGS

[0027] Figure 1 The present invention is a schematic diagram of a full-flow cycle liquid rocket engine using a fixed-mixing ratio precombustion chamber.

[0028] In the accompanying drawings, the components represented by the reference numerals are listed as follows:

[0029] 101. Oxygen-bypass fuel-rich precombustion chamber throttle valve; 102. Oxygen-bypass fuel-rich precombustion chamber throttle valve; 201. Oxygen-rich precombustion chamber combustion component; 202. Oxygen-rich precombustion chamber mixing component; 3. Oxygen-main throttle valve; 4. Oxidant pump; 5. Oxygen-rich gas turbine; 6. Thrust chamber; 7. Fuel-main throttle valve; 8. Thrust chamber cooling channel; 9. Fuel-rich gas turbine; 10. Fuel pump; 1101. Fuel-rich precombustion chamber mixing component; 1102. Fuel-rich precombustion chamber combustion component; 1201. Fuel-bypass fuel throttle valve; 1202. Fuel-bypass fuel throttle valve. DETAILED DESCRIPTION

[0030] The principles and features of the present invention are described below. The examples given are only used to explain the present invention and are not used to limit the scope of the present invention.

[0031] like Figure 1 As shown, this embodiment provides a full-flow cycle liquid rocket engine using a fixed mixing ratio precombustion chamber, including an oxidizer feed pipe, a fuel feed pipe, an oxygen-rich precombustion chamber, a fuel-rich precombustion chamber and a thrust chamber 6, wherein the oxygen-rich precombustion chamber includes an oxygen-rich precombustion chamber combustion component 201 and an oxygen-rich precombustion chamber mixing component 202, the outlet of the oxygen-rich precombustion chamber combustion component 201 is connected to the inlet of the oxygen-rich precombustion chamber mixing component 202, the fuel-rich precombustion chamber includes a fuel-rich precombustion chamber mixing component 1101 and a fuel-rich precombustion chamber combustion component 1102, the outlet of the fuel-rich precombustion chamber combustion component 1102 is connected to the inlet of the fuel-rich precombustion chamber mixing component 1101, the oxidizer feed pipe is connected to the oxygen-rich precombustion chamber respectively. The combustion component 201, the oxygen-rich precombustion chamber mixing component 202 and the rich precombustion chamber combustion component 1102 are connected and transport oxidant, the fuel feed pipe is respectively connected with the rich precombustion chamber mixing component 1101, the rich precombustion chamber combustion component 1102 and the oxygen-rich precombustion chamber combustion component 201, and transports fuel, the volume ratio of the oxidant and the fuel entering the oxygen-rich precombustion chamber combustion component 201 is a first fixed mixing ratio, the volume ratio of the oxidant and the fuel entering the rich precombustion chamber combustion component 1102 is a second fixed mixing ratio, the outlet of the oxygen-rich precombustion chamber mixing component 202 and the outlet of the rich precombustion chamber mixing component 1101 are both connected to the thrust chamber 6.

[0032] Both the oxygen-rich precombustion chamber and the fuel-rich precombustion chamber are composed of combustion components and mixing components with fixed mixing ratios. The flow rates entering the combustion components and the mixing components can be controlled separately. When the thrust is changed, the flow rate entering the mixing component can be adjusted to change the propellant flow rate. Since the flow rates of the primary injection (injection into the combustion component) and the secondary injection (injection into the mixing component) of the precombustion chamber are adjusted separately, the decoupling of the engine thrust control is achieved, the controllability of the engine is enhanced, and the deep throttling capability and low-frequency combustion stability of the engine are improved, which greatly simplifies the control system. In addition, since the mixing ratio of the combustion process of the oxygen-rich precombustion chamber and the fuel-rich precombustion chamber is fixed, the design of the precombustion chamber can be greatly simplified, and its combustion stability at deep throttling can be improved, which improves the reliability and high-frequency combustion stability of the precombustion chamber.

[0033] Specifically, the outlet of the oxygen-rich pre-combustion chamber mixing component 202 and the outlet of the fuel-rich pre-combustion chamber mixing component 1101 are respectively connected to the oxidant chamber and the fuel chamber of the thrust chamber 6.

[0034] On the basis of the above technical solution, it also includes an oxidant pump 4 and an oxygen-rich gas turbine 5. The oxidant pump 4 is arranged in series in the oxidant feed pipe, and the outlet of the oxygen-rich pre-combustion chamber mixing component 202 is connected to the thrust chamber 6 through the oxygen-rich gas turbine 5. The oxidant pump 4 and the oxygen-rich gas turbine 5 are transmission-connected.

[0035] The oxidant pump 4 and the oxygen-rich gas turbine 5 constitute a turbopump, which provides power for the flow of the oxidant.

[0036] On the basis of the above technical solution, it also includes a rich fuel gas turbine 9 and a fuel pump 10, wherein the fuel pump 10 is arranged in series in the fuel feed pipe, and the outlet of the rich fuel pre-combustion chamber mixing component 1101 is connected to the thrust chamber 6 through the rich fuel gas turbine 9.

[0037] The rich-fuel gas turbine 9 and the fuel pump 10 constitute a turbopump, which provides power for the flow of fuel.

[0038] On the basis of the above technical scheme, it also includes a first oxygen secondary pipeline, a second oxygen secondary pipeline, an oxygen main pipeline, an oxygen secondary fuel-rich precombustion chamber throttle valve 101, an oxygen secondary oxygen-rich precombustion chamber throttle valve 102 and an oxygen main throttle valve 3. The oxidant feed pipe is connected with the oxygen-rich precombustion chamber combustion component 201 through the first oxygen secondary pipeline, and the first oxygen secondary pipeline is provided with the oxygen secondary oxygen-rich precombustion chamber throttle valve 102; the oxidant feed pipe is connected with the fuel-rich precombustion chamber combustion component 1102 through the second oxygen secondary pipeline, and the second oxygen secondary pipeline is provided with the oxygen secondary fuel-rich precombustion chamber throttle valve 101; the oxidant feed pipe is connected with the oxygen-rich precombustion chamber mixing component 202 through the oxygen main pipeline, and the oxygen main pipeline is provided with the oxygen main throttle valve 3.

[0039] The oxygen secondary rich precombustion chamber throttle valve 101 and the oxygen secondary rich precombustion chamber throttle valve 102 are used to control the oxidant flow entering the rich precombustion chamber combustion component 1102 and the oxygen rich precombustion chamber combustion component 201 respectively. The oxygen main throttle valve 3 is used to control the oxidant flow entering the oxygen rich precombustion chamber mixing component 202.

[0040] On the basis of the above technical solution, it also includes a main fuel feed pipeline, a main fuel discharge pipeline and a main fuel throttle valve 7. The thrust chamber 6 has a thrust chamber cooling groove 8. The two ends of the main fuel feed pipeline are respectively connected to the fuel feed pipe and the inlet of the thrust chamber cooling groove 8, and the two ends of the main fuel discharge pipeline are respectively connected to the outlet of the thrust chamber cooling groove 8 and the rich fuel pre-combustion chamber mixing component 1101. The main fuel feed pipeline is provided with the main fuel throttle valve 7.

[0041] The fuel flows into the thrust chamber cooling channel 8 for heat exchange, and then flows into the fuel-rich pre-combustion chamber mixing component 1101 through the fuel main discharge pipe.

[0042] On the basis of the above technical solution, it also includes a first fuel bypass pipeline, a second fuel bypass pipeline, a fuel bypass rich precombustion chamber throttle valve 1201 and a fuel bypass oxygen-rich precombustion chamber throttle valve 1202. The fuel feed pipe is connected to the rich precombustion chamber combustion component 1102 through the first fuel bypass pipeline, and the fuel bypass rich precombustion chamber throttle valve 1201 is provided on the first fuel bypass pipeline; the fuel feed pipe is connected to the oxygen-rich precombustion chamber combustion component 201 through the second fuel bypass pipeline, and the fuel bypass oxygen-rich precombustion chamber throttle valve 1202 is provided on the second fuel bypass pipeline.

[0043] The secondary fuel path rich precombustion chamber throttle valve 1201 is used to control the fuel flow entering the rich precombustion chamber combustion component 1102. The secondary fuel path oxygen-rich precombustion chamber throttle valve 1202 is used to control the fuel flow entering the oxygen-rich precombustion chamber combustion component 201.

[0044] The oxygen secondary rich precombustion chamber throttle valve 101 and the fuel secondary rich precombustion chamber throttle valve 1201 are adjusted in proportion to each other, so as to satisfy the second fixed mixing ratio of the volume ratio of the oxidant and the fuel entering the rich precombustion chamber combustion component 1102. The two throttle valves can be linked by mechanical transmission to achieve synchronous adjustment, or can be synchronously adjusted by software control.

[0045] The oxygen auxiliary oxygen-enriched precombustion chamber throttle valve 102 and the fuel auxiliary oxygen-enriched precombustion chamber throttle valve 1202 are adjusted in proportion to each other, so as to satisfy the first fixed mixing ratio of the volume ratio of the oxidant and the fuel entering the oxygen-enriched precombustion chamber combustion component 201. The two throttle valves can be linked by mechanical transmission to achieve synchronous adjustment, or can be synchronously adjusted by software control.

[0046] On the basis of the above technical scheme, the ignition mode of the oxygen-rich pre-combustion chamber adopts gunpowder ignition, spark plug torch ignition or chemical ignition; the ignition mode of the fuel-rich pre-combustion chamber adopts gunpowder ignition, spark plug torch ignition or chemical ignition.

[0047] On the basis of the above technical solution, the thrust chamber 6 is ignited by gunpowder ignition, spark plug torch ignition or chemical ignition.

[0048] Regarding the cooling method of the precombustion chamber combustion component, optionally, a fuel-rich cooling channel is provided on the side wall of the fuel-rich precombustion chamber combustion component 1102, the fuel feed pipe is connected to the inlet of the fuel-rich cooling channel, and the outlet of the fuel-rich cooling channel is connected to the fuel-rich precombustion chamber combustion component 1102; an oxygen-rich cooling channel is provided on the side wall of the oxygen-rich precombustion chamber combustion component 201, the fuel feed pipe or the oxidant feed pipe is connected to the inlet of the oxygen-rich cooling channel, and the outlet of the oxygen-rich cooling channel is connected to the oxygen-rich precombustion chamber combustion component 201.

[0049] In the fuel-rich precombustion chamber combustion component, fuel is used to regenerate the wall surface, and in the oxygen-rich precombustion chamber combustion component, fuel or oxidant is used to regenerate the wall surface.

[0050] The fuel in the fuel feed pipe flows through the fuel-rich cooling channel and then enters the fuel-rich precombustion chamber combustion component 1102 for regenerative cooling. The first fuel secondary pipeline provided with the fuel secondary rich precombustion chamber throttle valve 1201 can be changed to be connected to the inlet of the fuel-rich cooling channel; or, on the basis of the first fuel secondary pipeline, a new pipeline connecting the fuel feed pipe and the inlet of the fuel-rich cooling channel is added, and a throttle valve is set on the new pipeline.

[0051] Similarly, the fuel of the fuel feed pipe or the oxidant of the oxidant feed pipe flows through the oxygen-enriched cooling channel for regenerative cooling. The first oxygen secondary pipeline provided with the oxygen secondary oxygen-enriched precombustion chamber throttle valve 102 can be changed to be connected to the inlet of the oxygen-enriched cooling channel; or the second fuel secondary pipeline provided with the fuel secondary oxygen-enriched precombustion chamber throttle valve 1202 can be changed to be connected to the inlet of the oxygen-enriched cooling channel; or, a new pipeline is added to connect the fuel feed pipe or the oxidant feed pipe with the inlet of the oxygen-enriched cooling channel, and a throttle valve is set on the new pipeline.

[0052] Regarding the cooling method of the precombustion chamber combustion component, optionally, a first side zone injector that only injects fuel is set at the outermost periphery of the injection disk of the fuel-rich precombustion chamber combustion component 1102, and a second side zone injector that only injects oxidant is set at the outermost periphery of the injection disk of the oxygen-rich precombustion chamber combustion component 201.

[0053] Liquid film cooling can also be used for the combustion components of the pre-combustion chamber. The cooling method of the combustion part of the pre-combustion chamber can also be a combination of regenerative cooling and liquid film cooling. Since the low-temperature fuel or oxidant in the mixing component accounts for the vast majority of the mass, the mixing component may not need cooling if it is reasonably designed.

[0054] Based on the above technical solution, the combustion components of the fuel-rich precombustion chamber and the oxygen-rich precombustion chamber can have exactly the same structure to reduce design costs, or they can be designed separately. If the gas diversion problem can be solved, the two precombustion chambers can also share one combustion component.

[0055] In one specific embodiment: This embodiment provides a full-flow cycle liquid rocket engine using a fixed mixture ratio pre-combustion chamber, as shown in the attached Figure 1 As shown, the propellant type can be a combination of liquid oxygen / methane, hydrogen peroxide / hydrocarbons, nitrogen oxides / hydrocarbons, liquid oxygen / liquid hydrogen, etc. It mainly includes: oxygen-rich precombustion chamber combustion component 201, fuel-rich precombustion chamber combustion component 1102, oxygen-rich precombustion chamber mixing component 202, fuel-rich precombustion chamber mixing component 1101, fuel-rich gas turbine 9, fuel pump 10, oxygen-rich gas turbine 5, oxidant pump 4, thrust chamber 6 and valves, etc. Among them, the propellant bypass (first oxygen bypass pipeline, second oxygen bypass pipeline, first fuel bypass pipeline and second fuel bypass pipeline) adopts a throttle valve to control the flow, and a flow regulator can also be used.

[0056] The external fuel tank is connected to the inlet of the fuel pump 10 through the front pipeline of the fuel pump. The fuel pump 10 drives the fuel flow. The fuel feed pipe after the outlet of the fuel pump 10 is divided into a main route and a secondary route. The secondary route is divided into two routes (the first fuel secondary route pipeline and the second fuel secondary route pipeline) and is connected to the rich-fuel precombustion chamber combustion component 1102 and the oxygen-rich precombustion chamber combustion component 201 with a fixed mixing ratio. The two secondary routes are respectively provided with a fuel secondary route rich-fuel precombustion chamber throttle valve 1201 and a fuel secondary route oxygen-rich precombustion chamber throttle valve 1202. The main fuel feed pipeline is connected to the inlet of the thrust chamber cooling groove 8 of the thrust chamber, and a main fuel throttle valve 7 is arranged in the pipeline. The outlet of the thrust chamber cooling groove 8 is connected to the fuel secondary injection inlet channel of the rich-fuel precombustion chamber mixing component 1101 through the main fuel discharge pipeline.

[0057] The external oxidant tank is connected to the inlet of the oxidant pump 4 through the oxidant pump front pipeline. The oxidant pump 4 drives the oxidant to flow. The oxidant feed pipe at the outlet of the oxidant pump 4 is divided into a main route and a secondary route. The secondary route is divided into two routes (a first oxygen secondary route pipeline and a second oxygen secondary route pipeline) connected to two fixed mixing ratio fuel-rich precombustion chamber combustion components 1102 and oxygen-rich precombustion chamber combustion components 201. The two secondary routes are respectively provided with an oxygen secondary route fuel-rich precombustion chamber throttle valve 101 and an oxygen secondary route oxygen-rich precombustion chamber throttle valve 102. The oxygen main route pipeline is connected to the oxidant secondary injection inlet channel of the oxygen-rich precombustion chamber mixing component 202, and an oxygen main route throttle valve 3 is provided in the pipeline. The outlet of the fuel-rich precombustion chamber combustion component 1102 is connected to the inlet of the fuel-rich precombustion chamber mixing component 1101, the outlet of the fuel-rich precombustion chamber mixing component 1101 is connected to the fuel inlet of the fuel-rich gas turbine 9, and the fuel outlet of the fuel-rich gas turbine 9 is connected to the fuel cavity of the thrust chamber 6. The outlet of the oxygen-rich precombustion chamber combustion component 201 is connected to the inlet of the oxygen-rich precombustion chamber mixing component 202, the outlet of the oxygen-rich precombustion chamber mixing component 202 is connected to the fuel gas inlet of the oxygen-rich gas turbine 5, and the fuel gas outlet of the oxygen-rich gas turbine 5 is connected to the oxidant chamber of the thrust chamber 6.

[0058] The working process of the full-flow circulation liquid rocket engine of this embodiment is as follows:

[0059] The liquid fuel is first pre-pressurized by the pre-pressure pump, and then enters the fuel pump 10 for further pressurization, and is divided into two main and auxiliary routes. Most of the methane fuel flows into the thrust chamber cooling channel 8 for cooling and heat exchange, and the other part of the methane enters the rich pre-combustion chamber combustion component 1102 and the oxygen-rich pre-combustion chamber combustion component 201, and is ejected from the nozzle. The methane entering the thrust chamber cooling channel 8 is combined and all enters the fuel inlet of the rich pre-combustion chamber mixing component 1101.

[0060] Similar to liquid fuel, the liquid oxidizer is first pre-pressurized by a pre-pressure pump, and then enters the oxidizer pump 4 for further pressurization and is divided into two paths. The main oxidizer enters the oxygen-rich precombustion chamber mixing component 202, and the secondary oxidizer enters the fuel-rich precombustion chamber combustion component 1102 and the oxygen-rich precombustion chamber combustion component 201, and is ejected from the nozzle.

[0061] The mixing ratio of the fuel and the oxidant entering the fuel-rich precombustion chamber combustion component 1102 and the oxygen-rich precombustion chamber combustion component 201 is a fixed mixing ratio. The combustion gases after the propellants of the two precombustion chamber combustion components are fully burned enter their respective fuel-rich precombustion chamber mixing components 1101 and oxygen-rich precombustion chamber mixing components 202, wherein the combustion gases of the fuel-rich precombustion chamber are mixed with the methane that has cooled the thrust chamber 6 in the fuel-rich precombustion chamber mixing component 1101 to obtain fuel-rich combustion gases with lower temperatures, and the combustion gases generated by the oxygen-rich precombustion chamber combustion component 201 are mixed with the mainstream of the oxidant after the pump in the oxygen-rich precombustion chamber mixing component 202 to obtain oxygen-rich combustion gases with lower temperatures. The fuel-rich combustion gases and oxygen-rich combustion gases generated by the fuel-rich precombustion chamber and the oxygen-rich precombustion chamber drive the fuel-rich combustion gas turbine 9 and the oxygen-rich combustion gas turbine 5 respectively, and then enter the fuel chamber and the oxidant chamber of the thrust chamber 6, burn through the gas-gas injector, and generate thrust after being discharged through the nozzle.

[0062] The control method of the full-flow circulation liquid rocket engine of this embodiment is as follows:

[0063] Before starting, the fuel is filled to the front of the fuel main throttle valve 7, the fuel secondary rich pre-combustion chamber throttle valve 1201 and the fuel secondary oxygen-rich pre-combustion chamber throttle valve 1202, and the oxidant is filled to the front of the oxygen main throttle valve 3, the oxygen secondary rich pre-combustion chamber throttle valve 101 and the oxygen secondary oxygen-rich pre-combustion chamber throttle valve 102.

[0064] During startup, the starter works, and the oxygen-rich gas turbine 5 and the fuel-rich gas turbine 9 respectively drive the oxidant pump 4 and the fuel pump 10 to rotate, and the pressure after the pump increases. When the pressure after the pump rises to a certain value, the fuel main throttle valve 7, the fuel secondary fuel-rich precombustion chamber throttle valve 1201 and the fuel secondary oxygen-rich precombustion chamber throttle valve 1202, and the oxidant is filled to the oxygen main throttle valve 3, the oxygen secondary fuel-rich precombustion chamber throttle valve 101 and the oxygen secondary oxygen-rich precombustion chamber throttle valve 102 are opened to the low operating opening of low precombustion chamber gas temperature and low thrust chamber flow. After the thrust chamber is pressurized, the opening of the six valves is gradually increased to increase the propellant flow and the precombustion chamber gas temperature, so that the engine enters the rated operating condition. When the thrust is changed, the flow rate of the propellant is changed proportionally by adjusting the opening of the oxygen main throttle valve 3 and the fuel main throttle valve 7 used for mixing, and the openings of the fuel auxiliary rich fuel precombustion chamber throttle valve 1201 and the oxygen auxiliary rich fuel precombustion chamber throttle valve 101, as well as the fuel auxiliary oxygen-rich precombustion chamber throttle valve 1202 and the oxygen auxiliary oxygen-rich precombustion chamber throttle valve 102 are adjusted according to the fixed mixing ratio relationship, thereby adjusting the power of the oxygen-rich gas turbine 5 and the fuel-rich gas turbine 9, and then adjusting the chamber pressure of the thrust chamber 6 and the specific impulse of the engine.

[0065] When shutting down, reduce the opening of the fuel auxiliary rich precombustion chamber throttle valve 1201, the oxygen auxiliary rich precombustion chamber throttle valve 101, the fuel auxiliary oxygen rich precombustion chamber throttle valve 1202 and the oxygen auxiliary oxygen rich precombustion chamber throttle valve 102 to reduce the power of the oxygen-rich gas turbine 5 and the rich fuel gas turbine 9, and the flow of the oxidant pump 4 and the fuel pump 10 will decrease accordingly, and the engine will be shut down.

[0066] In summary, the technical advantages of the full-flow cycle liquid rocket engine of this embodiment are:

[0067] Since supercritical combustion experiments and simulations are very difficult, it is very difficult to design a full-flow cycle engine precombustion chamber that can adapt to a wide range of variable thrust. The precombustion chamber of the present invention is composed of a combustion component and a mixing component, wherein the mixing ratio of the combustion component is maintained at a fixed mixing ratio, which makes the precombustion chamber easier to design. The mixing experiments and simulations of gas-liquid two-phase flow are relatively mature. Since most of the chemical reactions have been completed in the combustion component, the mixing component does not need to consider the chemical reaction, so its design is relatively simple. In addition, since the mixing ratio in the precombustion chamber combustion component does not change and the fuel and oxidant jets are always maintained at a fixed momentum ratio, the precombustion chamber has better high-frequency combustion stability when the engine is adjusted for thrust. Since the flow rates of the primary injection and secondary injection processes of the precombustion chamber are isolated, the precombustion chamber has better low-frequency stability.

[0068] In terms of engine starting and control, the fixed mixture ratio precombustion chamber full flow cycle engine proposed in the present invention further decouples the relationship between the thermal performance of each regulating component and the precombustion chamber compared with the conventional full flow cycle engine, thereby reducing the complexity of the engine thrust regulation system, improving the controllability of the thrust automatic control system, and reducing the coupling degree and design difficulty of the thrust automatic control system. At the same time, because the temperature of the precombustion chamber after the secondary injection can be actively controlled, the flow of the thrust chamber and the chamber pressure of the thrust chamber can be adjusted separately, which is convenient for reducing the thermal load of the precombustion chamber and the turbine assembly during the engine starting process, and realizing low thrust, high chamber pressure, high specific impulse working conditions and high thrust, low chamber pressure, low specific impulse working conditions, improving the flexibility of engine thrust regulation, and more conducive to improving the reliability of the engine for completing flight missions through the liquid rocket engine health monitoring system. In addition, the shutdown process only needs to gradually reduce the flow of the precombustion chamber combustion components, and through the adaptation of the turbo pump, a smooth shutdown is achieved, with simpler shutdown steps.

[0069] The full-flow cycle liquid rocket engine with a fixed-mixing ratio precombustion chamber proposed by the present invention has excellent stability and controllability and can be well applied to recoverable rockets with complex launch missions.

[0070] In the description of the present invention, the terms "first" and "second" are used for descriptive purposes only and should not be understood as indicating or implying relative importance or implicitly indicating the number of the indicated technical features. Therefore, the features defined as "first" and "second" may explicitly or implicitly include at least one of the features.

[0071] In the description of this specification, the description with reference to the terms "one embodiment", "some embodiments", "example", "specific example" or "some examples" etc. means that the specific features, structures, materials or characteristics described in conjunction with the embodiment or example are included in at least one embodiment or example of the present invention. In this specification, the schematic representations of the above terms do not necessarily refer to the same embodiment or example. Moreover, the specific features, structures, materials or characteristics described may be combined in any one or more embodiments or examples in a suitable manner. In addition, those skilled in the art may combine and combine the different embodiments or examples described in this specification and the features of the different embodiments or examples, unless they are contradictory.

[0072] The above description is only a preferred embodiment of the present invention and is not intended to limit the present invention. Any modifications, equivalent substitutions, improvements, etc. made within the spirit and principle of the present invention should be included in the protection scope of the present invention.

Claims

1. A full-flow cycle liquid rocket engine using a fixed-mixing ratio precombustion chamber, comprising an oxidizer feed pipe, a fuel feed pipe, an oxygen-rich precombustion chamber, a fuel-rich precombustion chamber and a thrust chamber (6), characterized in that: The invention also comprises an oxidant pump (4), an oxygen-rich gas turbine (5), a fuel-rich gas turbine (9) and a fuel pump (10); the oxygen-rich precombustion chamber comprises an oxygen-rich precombustion chamber combustion component (201) and an oxygen-rich precombustion chamber mixing component (202); the outlet of the oxygen-rich precombustion chamber combustion component (201) is communicated with the inlet of the oxygen-rich precombustion chamber mixing component (202); the fuel-rich precombustion chamber comprises a fuel-rich precombustion chamber mixing component (1101) and a fuel-rich precombustion chamber combustion component (1102); the outlet of the fuel-rich precombustion chamber combustion component (1102) is communicated with the inlet of the fuel-rich precombustion chamber mixing component (1101); The oxidant feed pipe is respectively connected to the oxygen-rich precombustion chamber combustion component (201), the oxygen-rich precombustion chamber mixing component (202) and the fuel-rich precombustion chamber combustion component (1102), and conveys the oxidant; the fuel feed pipe is respectively connected to the fuel-rich precombustion chamber mixing component (1101), the fuel-rich precombustion chamber combustion component (1102) and the oxygen-rich precombustion chamber combustion component (201), and conveys the fuel; the volume ratio of the oxidant and the fuel entering the oxygen-rich precombustion chamber combustion component (201) is a first fixed mixing ratio; the volume ratio of the oxidant and the fuel entering the fuel-rich precombustion chamber combustion component (1102) is a second fixed mixing ratio; the outlet of the oxygen-rich precombustion chamber mixing component (202) and the outlet of the fuel-rich precombustion chamber mixing component (1101) are both connected to the thrust chamber (6); The oxidant pump (4) is arranged in series in the oxidant feed pipe, the outlet of the oxygen-enriched pre-combustion chamber mixing component (202) is connected to the thrust chamber (6) through the oxygen-enriched gas turbine (5), and the oxidant pump (4) and the oxygen-enriched gas turbine (5) are connected by transmission; The fuel pump (10) is arranged in series in the fuel feed pipe, and the outlet of the rich-fuel pre-combustion chamber mixing component (1101) is connected to the thrust chamber (6) through the rich-fuel gas turbine (9).

2. A full-flow cycle liquid rocket engine with a fixed-mixing ratio precombustion chamber according to claim 1, characterized in that: It also includes a first oxygen secondary pipeline, a second oxygen secondary pipeline, an oxygen main pipeline, an oxygen secondary fuel-rich precombustion chamber throttle valve (101), an oxygen secondary oxygen-rich precombustion chamber throttle valve (102) and an oxygen main throttle valve (3), The oxidant feed pipe is connected to the oxygen-enriched precombustion chamber combustion component (201) via the first oxygen secondary pipeline, and the first oxygen secondary pipeline is provided with the oxygen secondary oxygen-enriched precombustion chamber throttle valve (102). The oxidant feed pipe is connected to the fuel-rich precombustion chamber combustion component (1102) through the second oxygen secondary pipe, and the second oxygen secondary pipe is provided with the oxygen secondary fuel-rich precombustion chamber throttle valve (101). The oxidant feed pipe is in communication with the oxygen-enriched pre-combustion chamber mixing component (202) via the oxygen main pipeline, and the oxygen main pipeline is provided with the oxygen main throttle valve (3).

3. A full-flow cycle liquid rocket engine with a fixed-mixing ratio precombustion chamber according to claim 1, characterized in that: It also includes a main fuel feed pipeline, a main fuel discharge pipeline and a main fuel throttle valve (7); the thrust chamber (6) has a thrust chamber cooling channel (8); the two ends of the main fuel feed pipeline are respectively connected to the fuel feed pipe and the inlet of the thrust chamber cooling channel (8); the two ends of the main fuel discharge pipeline are respectively connected to the outlet of the thrust chamber cooling channel (8) and the rich fuel pre-combustion chamber mixing component (1101); the main fuel feed pipeline is provided with the main fuel throttle valve (7).

4. A full-flow cycle liquid rocket engine using a fixed-mixing ratio precombustion chamber according to claim 3, characterized in that: It also includes a first fuel secondary pipeline, a second fuel secondary pipeline, a fuel secondary fuel-rich pre-combustion chamber throttle valve (1201) and a fuel secondary oxygen-rich pre-combustion chamber throttle valve (1202), The fuel feed pipe is connected to the fuel-rich precombustion chamber combustion component (1102) through the first fuel secondary pipeline, and the fuel secondary pipeline is provided with the fuel-rich precombustion chamber throttle valve (1201). The fuel feed pipe is connected to the oxygen-enriched precombustion chamber combustion component (201) via the second fuel secondary pipeline, and the fuel secondary oxygen-enriched precombustion chamber throttle valve (1202) is provided on the second fuel secondary pipeline.

5. A full-flow cycle liquid rocket engine using a fixed-mixing ratio precombustion chamber according to any one of claims 1 to 4, characterized in that: The ignition mode of the oxygen-rich pre-combustion chamber is gunpowder ignition, spark plug torch ignition or chemical ignition; the ignition mode of the fuel-rich pre-combustion chamber is gunpowder ignition, spark plug torch ignition or chemical ignition.

6. A full-flow cycle liquid rocket engine using a fixed-mixing ratio precombustion chamber according to any one of claims 1 to 4, characterized in that: The thrust chamber (6) is ignited by gunpowder ignition, spark plug torch ignition or chemical ignition.

7. A full-flow cycle liquid rocket engine with a fixed-mixing ratio precombustion chamber according to claim 1, characterized in that: A fuel-rich cooling channel is provided on the side wall of the fuel-rich precombustion chamber combustion component (1102), the fuel feed pipe is in communication with the inlet of the fuel-rich cooling channel, and the outlet of the fuel-rich cooling channel is in communication with the fuel-rich precombustion chamber combustion component (1102); An oxygen-rich cooling channel is provided on a side wall of the oxygen-rich precombustion chamber combustion component (201); the fuel feed pipe or the oxidant feed pipe is connected to the inlet of the oxygen-rich cooling channel; and the outlet of the oxygen-rich cooling channel is connected to the oxygen-rich precombustion chamber combustion component (201).

8. A full-flow cycle liquid rocket engine with a fixed-mixing ratio precombustion chamber according to claim 1 or 7, characterized in that: A first side zone injector for injecting only fuel is arranged at the outermost periphery of the injection disk of the fuel-rich precombustion chamber combustion component (1102), and a second side zone injector for injecting only oxidant is arranged at the outermost periphery of the injection disk of the oxygen-rich precombustion chamber combustion component (201).

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