Propellant pressurization system and method for combustion of afterburning cycle engine and test platform

Abstract

The invention relates to an afterburning cycle engine combustion propellant pressurization system, method and test platform, the afterburning cycle engine combustion propellant pressurization system comprises a propellant storage tank, a turbine, a propellant pump and a fuel gas generator, the turbine is coaxially connected with the propellant pump and can drive the propellant pump to operate, and the fuel gas generator is coaxially connected with the turbine. The propellant storage box is connected and communicated with an inlet of the propellant pump through a propellant supply pipeline, an outlet of the propellant pump is connected with a first propellant output pipeline and a second propellant output pipeline, and the first propellant output pipeline and the second propellant output pipeline are respectively connected with a main valve; the outlet of the propellant pump is further connected and communicated with the inlet of the fuel gas generator through a third propellant output pipeline and a fourth propellant output pipeline, and the outlet of the fuel gas generator is communicated with the turbine through a driving pipeline. According to the invention, the turbine and the propellant pump are driven to pressurize the propellant, and the high-pressure inlet condition requirements of the afterburning cycle engine combustion device test piece can be effectively simulated and met in the test environment.

Description

Technical Field

[0001] This invention relates to the field of aerospace engine ground testing technology, specifically to a propellant pressurization system, method, and test platform for staged combustion cycle engines. Background Technology

[0002] In a staged combustion cycle engine, fuel and oxidizer flow through separate pre-combustion chambers, generating fuel-rich and oxygen-rich gases respectively to drive a turbopump. Subsequently, all the gas after driving the turbine enters the main combustion chamber for final combustion. This cycle significantly improves propellant utilization efficiency, avoiding the propellant waste caused by the direct emission of fuel-rich or oxygen-rich gases generated after driving the turbine in traditional gas generator cycles.

[0003] However, the operating pressure of the pre-combustion chamber (gas generator) in a staged combustion cycle liquid rocket engine is much higher than that of the gas generator in a conventional gas generator cycle liquid rocket engine. This high-pressure characteristic poses a severe challenge to ground test rigs. The tank pressure of conventional test rigs that supply propellant from low-pressure tanks is far from meeting the high-pressure propellant supply requirements at the pre-combustion chamber inlet. Therefore, conducting pre-combustion chamber tests directly on such test rigs faces fundamental difficulties. Although high-pressure extrusion rigs can provide higher inlet pressure, the initial inlet pressure of the propellant output from the high-pressure extrusion rig is already high, which does not match the actual operating condition of the pre-combustion chamber of a staged combustion cycle liquid rocket engine, where the inlet pressure gradually increases with the propellant pump pressurization capacity during startup. Rocket engine-specific valves cannot be directly used on extrusion rigs; it is necessary to use the process valves of the test rig or develop new high-pressure valves. However, process valves have a slow response and cannot simulate the rapid sequential actions during actual engine operation; while developing high-pressure, fast-response valves is difficult, costly, and time-consuming. In addition, the high-pressure extrusion platform itself has high construction costs and limited propellant supply capacity, making it difficult to meet the needs of high-condition testing of combustion devices for engines of 100 tons or more. Summary of the Invention

[0004] In order to solve one or more technical problems existing in the prior art, the present invention provides a propellant pressurization system, method and test platform for combustion in a staged combustion cycle engine.

[0005] The technical solution of this invention to solve the above-mentioned technical problems is as follows: This invention provides a propellant pressurization system for a staged combustion cycle engine, including a propellant tank, a turbine, a propellant pump, and a gas generator. The turbine is coaxially connected to the propellant pump and can drive the propellant pump to operate. The propellant tank is connected to the inlet of the propellant pump through a propellant supply pipeline. The outlet of the propellant pump is connected to a first propellant output pipeline and a second propellant output pipeline. A main valve is connected to the first propellant output pipeline and the second propellant output pipeline, respectively. The outlet of the propellant pump is also connected to the inlet of the gas generator through a third propellant output pipeline and a fourth propellant output pipeline. The outlet of the gas generator is connected to the turbine through a drive pipeline.

[0006] The beneficial effects of the present invention are as follows: The propellant pressurization system for the combustion of the afterburning cycle engine of the present invention utilizes part of the propellant as fuel to first burn in the gas generator to generate high temperature and high pressure gas to drive the turbine. The turbine drives the propellant pump to pressurize the propellant, thereby effectively simulating and meeting the high pressure inlet conditions required by the test specimen of the combustion device of the afterburning cycle engine and the actual working characteristics of the gradual increase of the inlet pressure of the combustion device during the engine start-up process in the test environment.

[0007] This invention reuses the secondary systems (including a gas generator, turbine, and propellant pump) in a gas generator-cycle liquid rocket engine to build a test combustion device (e.g., the pre-combustion chamber of the engine to be tested). Through this semi-system architecture of a liquid rocket engine, a pressurization system capable of providing high-pressure propellant to the test combustion device can be constructed. This solves the problems that existing propellant supply systems cannot meet the high-pressure inlet requirements of ground tests of test combustion device devices and cannot simulate the actual working characteristics of the gradual increase in inlet pressure of the combustion device during engine start-up.

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

[0009] Furthermore, the propellant tank includes a low-pressure liquid methane tank and a low-pressure liquid oxygen tank; the propellant pump includes a fuel pump and an oxygen pump; the turbine is coaxially driven to the fuel pump and the oxygen pump respectively; the low-pressure liquid methane tank is connected to the inlet of the fuel pump via a first propellant supply pipeline; the low-pressure liquid oxygen tank is connected to the inlet of the oxygen pump via a second propellant supply pipeline; the outlet of the fuel pump and the outlet of the oxygen pump are respectively connected to a first propellant output pipeline and a second propellant output pipeline; the outlet of the fuel pump and the outlet of the oxygen pump are also connected to the inlet of the gas generator via a third propellant output pipeline and a fourth propellant output pipeline respectively.

[0010] The beneficial effects of adopting the above-mentioned further scheme are: using a fuel pump to supply fuel to the gas generator and combustion device test piece, and using an oxygen pump to supply oxidant to the gas generator and combustion device test piece.

[0011] Furthermore, the first propellant output pipeline is connected to a methane emission branch and a methane supply branch, respectively. The methane emission branch is detachably fitted with a methane emission orifice plate and a methane emission cavitation pipe. A methane main valve is installed on the first propellant output pipeline.

[0012] The beneficial effect of adopting the above-mentioned further scheme is that by detachably installing methane emission orifice plates and methane emission cavitation pipes in the methane emission branch, different specifications of methane emission orifice plates and methane emission cavitation pipes can be set as needed to control the amount of methane emission, thereby controlling the amount of methane supply.

[0013] Furthermore, the second propellant output pipeline is connected to an oxygen discharge branch and an oxygen supply branch, respectively. An oxygen discharge orifice plate and an oxygen discharge cavitation pipe are detachably fitted inside the oxygen discharge branch. An oxygen main valve is installed on the second propellant output pipeline.

[0014] The beneficial effect of adopting the above-mentioned further scheme is that by detachably installing oxygen emission orifice plates and oxygen emission cavitation pipes in the oxygen emission branch, different specifications of oxygen emission orifice plates and oxygen emission cavitation pipes can be set as needed to control the oxygen emission amount, thereby controlling the oxygen supply amount.

[0015] Furthermore, a methane auxiliary valve is provided on the third propellant output pipeline connected to the combustion pump, and an oxygen auxiliary valve is connected on the fourth propellant output pipeline connected to the oxygen pump.

[0016] The beneficial effect of adopting the above-mentioned further solution is that by installing a methane auxiliary valve and an oxygen auxiliary valve on the gas pipeline, it is convenient to control the on / off state of the gas pipeline.

[0017] Furthermore, the gas pump is equipped with a first temperature sensor and a first pressure sensor at both its inlet and first outlet; the oxygen pump is equipped with a second temperature sensor and a second pressure sensor at both its inlet and first outlet.

[0018] The beneficial effect of adopting the above-mentioned further solution is that by setting temperature and pressure sensors, it is convenient to detect the inlet and outlet temperatures and pressures of the fuel pump and the oxygen pump.

[0019] Furthermore, the propellant supply pipeline is equipped with valves and flow meters.

[0020] The advantages of adopting the above-mentioned further solutions are: by setting valves and flow meters, it is convenient to control the on / off state of the propellant supply pipeline and to detect the flow rate of the internal fluid.

[0021] Furthermore, the propellant tank is connected to a pressurization gas source mechanism, which is connected and communicated with the propellant tank through a pipeline.

[0022] The beneficial effect of adopting the above-mentioned further scheme is that by setting up a pressurizing gas source mechanism, high-pressure gas can be injected into the propellant tank, so that the pressure of the propellant tank can be increased to 0.4~0.8MPa, thereby meeting the minimum pressure requirement of the turbine pump inlet and preventing pump cavitation.

[0023] A method for pressurizing propellant for a staged combustion cycle engine, employing the propellant pressurization system for a staged combustion cycle engine as described above, includes the following steps: S1, the propellant tank supplies propellant to the propellant pump through the propellant supply pipeline; S2, the turbine is started to rotate by external energy, and the turbine drives the propellant pump to rotate synchronously, and the speed gradually increases. The propellant pump delivers propellant to the gas generator through the third propellant output pipeline and the fourth propellant output pipeline. The gas generator uses the propellant to burn and generate high-temperature and high-pressure gas. The high-temperature and high-pressure gas is guided to the turbine through the drive pipeline and drives the turbine together with the external energy. At a specified time after startup, the external rotation energy is turned off, and the turbine is driven only by the high-temperature and high-pressure gas to continue to accelerate and reach the rated speed. S3, the gas generator continues to work, and the turbine drives the propellant pump to gradually accelerate under the high temperature and high pressure of the gas. As the propellant pump gradually increases the pressure of the propellant, according to the preset program, the two main valves are opened at a specified time and the pressurized propellant is output through the first and second propellant output pipelines. The specified time is 0~2s after the engine starts.

[0024] The beneficial effects of the present invention are as follows: The propellant pressurization method for combustion in a staged combustion cycle engine of the present invention utilizes a portion of the propellant as fuel to first burn in the gas generator to generate high-temperature and high-pressure gas, which drives the turbine and propellant pump to pressurize the propellant. This effectively simulates and meets the high-pressure inlet conditions required by the test specimen of the combustion device of the staged combustion cycle engine and the actual working characteristics of the gradual increase of the inlet pressure of the combustion device during the engine start-up process in the test environment.

[0025] The present invention also provides a test platform, including the propellant pressurization system for combustion of a staged combustion cycle engine as described above, and a pre-combustion chamber of the engine to be tested, wherein the propellant output pipeline is connected to and communicates with the pre-combustion chamber of the engine to be tested.

[0026] The beneficial effects of the present invention are as follows: The test platform of the present invention can use the propellant pressurization system of the afterburning cycle engine to pressurize the propellant, and the pressurized propellant is supplied to the pre-combustion chamber of the engine under test, thereby effectively solving the problem that the tank pressure cannot meet the high pressure inlet requirements of the pre-combustion chamber of the engine under test. Attached Figure Description

[0027] Figure 1 This is a schematic diagram of the propellant pressurization system for the afterburning cycle engine of the present invention; Figure 2 This is a schematic diagram of the propellant pressurization system for the combustion of a staged combustion cycle engine according to the present invention.

[0028] The attached diagram lists the components represented by each number as follows: 1. First propellant supply line; 11. Second propellant supply line; 12. First propellant output line; 13. Second propellant output line; 14. Methane emission branch; 15. Methane supply branch; 16. Methane emission orifice plate; 17. Methane emission cavitation pipe; 18. Oxygen emission branch; 19. Oxygen supply branch; 190. Oxygen emission cavitation pipe; 191. Oxygen emission orifice plate; 192. Methane main valve; 193. Oxygen main valve; 2. Turbine; 21. Fuel pump; 22. Oxygen pump; 23. Methane auxiliary valve; 24. Oxygen auxiliary valve; 3. Gas generator; 31. Third propellant output pipeline; 32. Fourth propellant output pipeline; 33. Drive pipeline. Detailed Implementation

[0029] The principles and features of the present invention are described below. The examples given are only for explaining the present invention and are not intended to limit the scope of the present invention.

[0030] Example 1 like Figure 1 and Figure 2 As shown in this embodiment, a propellant pressurization system for a staged combustion cycle engine includes a propellant tank, a turbine 2, a propellant pump, and a gas generator 3. The turbine 2 is coaxially connected to the propellant pump and can drive the propellant pump. The propellant tank is connected to the inlet of the propellant pump via a propellant supply pipeline. The outlet of the propellant pump is connected to a first propellant output pipeline 12 and a second propellant output pipeline 13. Main valves are connected to the first propellant output pipeline 12 and the second propellant output pipeline 13, respectively. The outlet of the propellant pump is also connected to the inlet of the gas generator 3 via a third propellant output pipeline 31 and a fourth propellant output pipeline 32. The outlet of the gas generator 3 is connected to the turbine 2 via a drive pipeline 33. The turbine 2 is directly connected to the atmosphere for exhaust.

[0031] In a preferred embodiment, the propellant supply pipeline is equipped with a valve and a flow meter. By installing the valve and flow meter, it is convenient to control the on / off state of the propellant supply pipeline and to detect the flow rate of the internal fluid.

[0032] A further embodiment of this solution involves connecting the propellant tank to a pressurization gas source mechanism, which is connected and communicates with the propellant tank via a pipeline. By providing the pressurization gas source mechanism, high-pressure gas can be injected into the propellant tank, raising its pressure to 0.4~0.8 MPa, thereby meeting the minimum pressure requirement at the turbopump inlet and preventing pump cavitation. The pressurization gas source mechanism can be a nitrogen tank, which can supply nitrogen gas to the propellant tank via pipeline. The nitrogen gas is used as a high-pressure gas to pressurize the propellant tank, driving the propellant flow to the turbopump (turbine + gas pump + oxygen pump) inlet.

[0033] The propellant pressurization system for the staged combustion cycle engine in this embodiment utilizes a portion of the propellant as fuel to first burn in the gas generator to produce high-temperature and high-pressure gas that drives the turbine. The turbine then drives the propellant pump to pressurize the propellant, thereby effectively simulating and meeting the high-pressure inlet conditions required by the test specimen of the staged combustion cycle engine combustion device and the actual working characteristics of the combustion device inlet pressure gradually increasing during engine start-up in the test environment.

[0034] This invention reuses the secondary systems (including a gas generator, turbine, and propellant pump) in a gas generator-cycle liquid rocket engine to build a test combustion device (e.g., the pre-combustion chamber of the engine to be tested). Through this semi-system architecture of a liquid rocket engine, a pressurization system capable of providing high-pressure propellant to the test combustion device can be constructed. This solves the problems that existing propellant supply systems cannot meet the high-pressure inlet requirements of ground tests of test combustion device devices and cannot simulate the actual working characteristics of the gradual increase in inlet pressure of the combustion device during engine start-up.

[0035] Example 2 Based on Example 1, this example provides a specific design for a propellant storage tank. For example... Figure 1 and Figure 2 As shown, the propellant tank includes a low-pressure liquid methane tank and a low-pressure liquid oxygen tank. The propellant pump includes a fuel pump 21 and an oxygen pump 22. The turbine 2 is coaxially connected to the fuel pump 21 and the oxygen pump 22. The low-pressure liquid methane tank is connected to the inlet of the fuel pump 21 via a first propellant supply line 1, and the low-pressure liquid oxygen tank is connected to the inlet of the oxygen pump 22 via a second propellant supply line 11. The outlets of the fuel pump 21 and the oxygen pump 22 are connected to a first propellant output line 12 and a second propellant output line 13, respectively. The outlets of the fuel pump 21 and the oxygen pump 22 are also connected to the inlet of the gas generator 3 via a third propellant output line 31 and a fourth propellant output line 32, respectively. The fuel pump is used to supply fuel to the gas generator and combustion device test piece, and the oxygen pump is used to supply oxidizer to the gas generator and combustion device test piece.

[0036] Specifically, the first propellant output line 12 is connected to a third propellant output line 31 for connecting to the inlet of the gas generator 3, and the second propellant output line 13 is connected to a fourth propellant output line 32 for connecting to the inlet of the gas generator 3.

[0037] In this embodiment, the methane tank and the low-pressure liquid oxygen tank can be connected to a pressurization gas source mechanism to boost propellant output. Although both the tank pressurization and turbine starting external energy sources are high-pressure nitrogen, they are supplied separately.

[0038] In this embodiment, the gas generator can generate high-temperature and high-pressure gas required to drive the turbine by burning a small portion of the propellant (methane and oxygen). The turbopump system includes a coaxial turbine, a gas pump, and an oxygen pump. After being driven by the high-temperature and high-pressure gas, the turbine drives the gas pump and the oxygen pump, which pressurize the low-pressure methane and liquid oxygen at the inlet of the gas pump and the oxygen pump to high pressure. The pressurized propellant is supplied to the pre-combustion chamber of the engine under test, thereby effectively solving the problems that the tank pressure cannot meet the high-pressure inlet requirements of the combustion device test piece and cannot simulate the actual working characteristics of the combustion device inlet pressure gradually increasing during the engine start-up process.

[0039] Example 3 Based on Example 1 or Example 2, this example provides a preferred solution for propellant supply. For example... Figure 1 and Figure 2 As shown, the first propellant output pipeline 12 is connected to a methane emission branch 14 and a methane supply branch 15, respectively. A methane emission orifice plate 16 and a methane emission cavitation pipe 17 are detachably fitted inside the methane emission branch 14. A methane main valve 192 is installed on the first propellant output pipeline 12. By detachably installing the methane emission orifice plate and methane emission cavitation pipe inside the methane emission branch, different specifications of methane emission orifice plates and methane emission cavitation pipes can be set as needed to control the methane emission rate, thereby controlling the methane supply rate.

[0040] like Figure 1 and Figure 2 As shown, the second propellant output pipeline 13 is connected to the oxygen discharge branch 18 and the oxygen supply branch 19, respectively. An oxygen discharge orifice plate 191 and an oxygen discharge cavitation pipe 190 are detachably fitted inside the oxygen discharge branch 18. An oxygen main valve 193 is installed on the second propellant output pipeline 13. By detachably installing the oxygen discharge orifice plate and oxygen discharge cavitation pipe inside the oxygen discharge branch, different specifications of oxygen discharge orifice plates and oxygen discharge cavitation pipes can be set as needed to control the oxygen discharge rate, thereby controlling the oxygen supply rate.

[0041] More specifically, such as Figure 1As shown, a methane auxiliary valve 23 is provided on the third propellant output pipeline 31 connected to the gas pump 21, and an oxygen auxiliary valve 24 is connected to the fourth propellant output pipeline 32 connected to the oxygen pump 22. By providing methane and oxygen auxiliary valves on the gas pipelines, it is convenient to control the on / off state of the gas pipelines.

[0042] Optionally, a first temperature sensor and a first pressure sensor are provided at both the inlet and the first outlet of the fuel pump 21; a second temperature sensor and a second pressure sensor are provided at both the inlet and the first outlet of the oxygen pump 22. By providing temperature and pressure sensors, it is convenient to detect the inlet and outlet temperatures and pressures of the fuel pump and the oxygen pump.

[0043] In this embodiment, the oxygen main valve, oxygen auxiliary valve, methane main valve, and methane auxiliary valve can all be pneumatically controlled valves.

[0044] In this embodiment, the methane supply branch and oxygen supply branch are used to supply fuel to the engine's pre-combustion chamber under test. The methane emission branch and oxygen emission branch are used to adjust the flow rates of the methane supply branch and oxygen supply branch, respectively. The third propellant output line and the fourth propellant output line are used to supply fuel to the gas generator.

[0045] Example 4 This embodiment provides a method for pressurizing propellant in a staged combustion cycle engine, employing the propellant pressurization system for a staged combustion cycle engine as described in Embodiment 1 above, and includes the following steps: S1, the propellant tank supplies propellant to the propellant pump through the propellant supply pipeline; S2, turbine 2 is started to rotate by external energy. Turbine 2 drives the propellant pump to rotate synchronously, and the speed gradually increases. The propellant pump delivers propellant to gas generator 3 through the third propellant output pipe 31 and the fourth propellant output pipe 32. Gas generator 3 uses the propellant to burn, producing high-temperature and high-pressure gas. The pressure of the high-temperature and high-pressure gas is 5~15 MPa, and the temperature is 600~1200 K. The high-temperature and high-pressure gas is guided to the turbine through the drive pipe and drives turbine 2 together with the external energy. At a specified time after start-up, the external rotation-starting energy is turned off, and the turbine continues to accelerate and reach the rated speed only driven by the high-temperature and high-pressure gas. S3, the gas generator 3 continues to operate, and the turbine 2, driven by the high-temperature and high-pressure gas, gradually accelerates the propellant pump. As the propellant pump gradually increases its pressurization, according to a preset program, two main valves are opened at designated times, and pressurized propellant is output through the first and second propellant output pipelines. The designated time is 0-2 seconds after engine start-up. The preset pressure is 10-25 MPa.

[0046] The propellant pressurization method for the combustion of a staged combustion cycle engine in this embodiment utilizes a portion of the propellant as fuel to first burn in the gas generator to produce high-temperature and high-pressure gas, which drives the turbine and propellant pump to pressurize the propellant. This effectively simulates and meets the high-pressure inlet conditions required by the test specimen of the combustion device of the staged combustion cycle engine and the actual working characteristics of the combustion device inlet pressure gradually increasing during the engine start-up process in the test environment.

[0047] Example 5 This embodiment provides a method for pressurizing propellant in a staged combustion cycle engine, employing the propellant pressurization system for a staged combustion cycle engine as described in Embodiment 2 or Embodiment 3 above, and includes the following steps: S1, the propellant tank supplies propellant to the propellant pump through the propellant supply pipeline; S2, turbine 2 is started to rotate by external energy. Turbine 2 drives the fuel pump and oxygen pump to rotate synchronously, and the speed gradually increases. The fuel pump and oxygen pump deliver methane and liquid oxygen to gas generator 3 through the third propellant output pipe 31 and the fourth propellant output pipe 32. Gas generator 3 uses the methane and liquid oxygen to burn, producing high-temperature and high-pressure gas. The pressure of the high-temperature and high-pressure gas is 5~15 MPa, and the temperature is 600~1200 K. The high-temperature and high-pressure gas is guided to turbine 2 through drive pipe 33 and drives turbine 2 together with external energy. At a specified time after start-up, the external rotation-starting energy is turned off, and the turbine continues to accelerate and reach the rated speed only driven by the high-temperature and high-pressure gas. S3, the gas generator 3 continues to operate. Driven by the high-temperature, high-pressure gas, the turbine 2 gradually accelerates the gas pump 21 and oxygen pump 22. As the pressure increase of the gas pump 21 and oxygen pump 22 on the methane and liquid oxygen gradually increases, according to a preset program, the two main methane valves 192 and oxygen valve 193 are opened at designated times, and the pressurized methane and liquid oxygen are output through the first and second propellant output pipelines. The designated time is 0-2 seconds after engine start-up. Under steady-state conditions, the pressures of methane and liquid oxygen are 10-25 MPa. At this time, the pressure levels of methane and liquid oxygen are approximately 25 times higher than the initial tank pressure (0.4-0.8 MPa) (15 MPa / 0.6 MPa = 25).

[0048] High-pressure methane, pressurized by fuel pump 21, and high-pressure oxygen, pressurized by oxygen pump 22, are supplied to the engine's combustion device test specimen (e.g., the engine's pre-combustion chamber under test) through their respective delivery pipelines. The high-pressure propellant meets the high inlet pressure requirements for the combustion device test specimen's operation and simulates the actual operating characteristics of the combustion device's inlet pressure gradually increasing during engine start-up, far exceeding the tank's own pressurization capacity. Thus, the system completes the process of stably supplying propellant from the low-pressure tank to the high-pressure combustion device test specimen.

[0049] The propellant pressurization method for the combustion of the staged combustion cycle engine in this embodiment utilizes a portion of the propellant as fuel to first burn in the gas generator to produce high-temperature and high-pressure gas, which drives the turbine and propellant pump to pressurize the propellant. This effectively simulates and meets the high-pressure inlet conditions required by the test specimen of the combustion device of the staged combustion cycle engine and the actual working characteristics of the combustion device inlet pressure gradually increasing during engine start-up in the test environment.

[0050] Example 6 This embodiment provides a test platform, including the propellant pressurization system for a staged combustion cycle engine as described above, and a pre-combustion chamber for the engine under test. The propellant output pipeline is connected to and communicates with the pre-combustion chamber of the engine under test. This test platform can verify the key performance characteristics of combustion device test pieces, including head filling characteristics, design reliability, and outlet gas temperature uniformity.

[0051] The test platform in this embodiment can use a propellant pressurization system for afterburning cycle engines to pressurize the propellant. The pressurized propellant is then supplied to the pre-combustion chamber of the engine under test, thereby effectively solving the problem that the tank pressure cannot meet the high-pressure inlet requirements of the pre-combustion chamber of the engine under test and simulate the actual working characteristics of the pre-combustion chamber inlet pressure rise during engine start-up.

[0052] In the description of this invention, it should be understood that the terms "inner" and "outer", etc., indicate the orientation or positional relationship based on the orientation or positional relationship shown in the drawings, and are only for the convenience of describing this invention and simplifying the description, and do not indicate or imply that the device or element referred to must have a specific orientation, or be constructed and operated in a specific orientation, and therefore should not be construed as a limitation of this invention.

[0053] Furthermore, the terms "first" and "second" are used for descriptive purposes only and should not be construed as indicating or implying relative importance or implicitly specifying the number of technical features indicated. Thus, a feature defined as "first" or "second" may explicitly or implicitly include at least one of that feature. In the description of this invention, "a plurality of" means at least two, such as two, three, etc., unless otherwise explicitly specified.

[0054] In this invention, unless otherwise explicitly specified and limited, the terms "installation," "connection," "linking," and "fixing," etc., should be interpreted broadly. For example, they can refer to a fixed connection, a detachable connection, or an integral part; they can refer to a direct connection or an indirect connection through an intermediate medium; they can refer to the internal communication of two components or the interaction between two components, unless otherwise explicitly limited. Those skilled in the art can understand the specific meaning of the above terms in this invention according to the specific circumstances.

[0055] In this invention, unless otherwise explicitly specified and limited, "above" or "below" the second feature can mean that the first feature is in direct contact with the second feature, or that the first feature is in indirect contact with the second feature through an intermediate medium. Furthermore, "above," "over," and "on top" of the second feature can mean that the first feature is directly above or diagonally above the second feature, or simply that the first feature is at a higher horizontal level than the second feature. "Below," "below," and "under" the second feature can mean that the first feature is directly below or diagonally below the second feature, or simply that the first feature is at a lower horizontal level than the second feature.

[0056] In the description of this specification, the references to terms such as "one embodiment," "some embodiments," "example," "specific example," or "some examples," etc., refer to specific features, structures, materials, or characteristics described in connection with that embodiment or example, which are included in at least one embodiment or example of the present invention. In this specification, the illustrative expressions of the above terms do not necessarily refer to the same embodiment or example. Furthermore, the specific features, structures, materials, or characteristics described may be combined in any suitable manner in one or more embodiments or examples. Moreover, without contradiction, those skilled in the art can combine and integrate the different embodiments or examples described in this specification, as well as the features of different embodiments or examples.

[0057] Although embodiments of the present invention have been shown and described above, it is understood that the above embodiments are exemplary and should not be construed as limiting the present invention. Those skilled in the art can make changes, modifications, substitutions and variations to the above embodiments within the scope of the present invention.

Claims

1. A propellant pressurization system for a staged combustion cycle engine, characterized in that, The device includes a propellant tank, a turbine, a propellant pump, and a gas generator. The turbine is coaxially connected to the propellant pump and can drive the propellant pump. The propellant tank is connected to the inlet of the propellant pump via a propellant supply pipeline. The outlet of the propellant pump is connected to a first propellant output pipeline and a second propellant output pipeline, and a main valve is connected to each of the first and second propellant output pipelines. The outlet of the propellant pump is also connected to the inlet of the gas generator via a third propellant output pipeline and a fourth propellant output pipeline. The outlet of the gas generator is connected to the turbine via a drive pipeline.

2. The propellant pressurization system for a staged combustion cycle engine according to claim 1, characterized in that, The propellant tank includes a low-pressure liquid methane tank and a low-pressure liquid oxygen tank. The propellant pump includes a fuel pump and an oxygen pump. The turbine is coaxially driven to the fuel pump and the oxygen pump, respectively. The low-pressure liquid methane tank is connected to the inlet of the fuel pump via a first propellant supply line. The low-pressure liquid oxygen tank is connected to the inlet of the oxygen pump via a second propellant supply line. The outlets of the fuel pump and the oxygen pump are connected to a first propellant output line and a second propellant output line, respectively. The outlets of the fuel pump and the oxygen pump are also connected to the inlet of the gas generator via a third propellant output line and a fourth propellant output line, respectively.

3. The propellant pressurization system for a staged combustion cycle engine according to claim 2, characterized in that, The first propellant output pipeline is connected to a methane emission branch and a methane supply branch, respectively. The methane emission branch is detachably fitted with a methane emission orifice plate and a methane emission cavitation pipe. A methane main valve is installed on the first propellant output pipeline.

4. The propellant pressurization system for a staged combustion cycle engine according to claim 2, characterized in that, The second propellant output pipeline is connected to the oxygen discharge branch and the oxygen supply branch respectively. The oxygen discharge branch is detachably fitted with an oxygen discharge orifice plate and an oxygen discharge cavitation pipe. An oxygen main valve is installed on the second propellant output pipeline.

5. The propellant pressurization system for a staged combustion cycle engine according to claim 2, characterized in that, A methane auxiliary valve is provided on the third propellant output pipeline connected to the combustion pump, and an oxygen auxiliary valve is connected on the fourth propellant output pipeline connected to the oxygen pump.

6. The propellant pressurization system for a staged combustion cycle engine according to claim 2, characterized in that, The gas pump is equipped with a first temperature sensor and a first pressure sensor at both its inlet and first outlet; the oxygen pump is equipped with a second temperature sensor and a second pressure sensor at both its inlet and first outlet.

7. The propellant pressurization system for a staged combustion cycle engine according to claim 1, characterized in that, The propellant supply pipeline is equipped with valves and flow meters.

8. The propellant pressurization system for a staged combustion cycle engine according to claim 1, characterized in that, The propellant tank is connected to a pressurization gas source mechanism, which is connected to and communicates with the propellant tank through a pipeline.

9. A method for pressurizing propellant in a staged combustion cycle engine, characterized in that, The propellant pressurization system for a staged combustion cycle engine as described in any one of claims 1 to 8 includes the following steps: S1, the propellant tank supplies propellant to the propellant pump through the propellant supply pipeline; S2, the turbine is started to rotate by external energy, and the turbine drives the propellant pump to rotate synchronously, and the speed gradually increases. The propellant pump delivers propellant to the gas generator through the third propellant output pipeline and the fourth propellant output pipeline. The gas generator uses the propellant to burn and generate high-temperature and high-pressure gas. The high-temperature and high-pressure gas is guided to the turbine through the drive pipeline and drives the turbine together with the external energy. At a specified time after startup, the external rotation energy is turned off, and the turbine is driven only by the high-temperature and high-pressure gas to continue to accelerate and reach the rated speed. S3, the gas generator continues to work, and the turbine drives the propellant pump to gradually accelerate under the high temperature and high pressure of the gas. As the propellant pump gradually increases the pressure of the propellant, according to the preset program, the two main valves are opened at a specified time and the pressurized propellant is output through the first and second propellant output pipelines. The specified time is 0~2s after the engine starts.

10. An experimental platform, characterized in that, The system includes a propellant pressurization system for combustion in a staged combustion cycle engine as described in any one of claims 1 to 8, and further includes a pre-combustion chamber of the engine to be tested, wherein the propellant output pipeline is connected to and communicates with the pre-combustion chamber of the engine to be tested.

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