Gas blowing system and method for turbine pump isolation cavity of liquid rocket engine and rocket

Abstract

The invention provides a liquid rocket engine turbine pump isolation cavity gas blow-down system and method and a rocket, and belongs to the technical field of liquid rocket engine pump isolation cavity blow-down, the blow-down system comprises a fuel gas generator connected with a turbine, an oxygen pump and a fuel pump, the oxygen pump and the fuel pump are connected with the turbine, and an isolation cavity is formed between the oxygen pump and the fuel pump; a liquid oxygen discharge port and a fuel discharge port are formed in the side wall of the isolation cavity; a heat exchanger is arranged in an exhaust pipe of the turbine; the inlet end of the heat exchanger is connected with a low-temperature heat exchange medium supply pipeline; the side wall of the isolation cavity is provided with a blow-off port, and the blow-off port is connected with a heat exchange port of the heat exchanger through a connecting pipeline. The medium subjected to heat exchange by the heat exchanger blows off the isolation cavity, so that the use of gas cylinders is reduced, and the stability and reliability of the blow-off flow are ensured; the blow-off efficiency and the blow-off stability can be improved; the structure weight is reduced, the carrying capacity of the whole rocket is improved, the final assembly difficulty is reduced, and the use reliability is improved.

Description

Technical Field

[0001] The invention relates to the technical field of liquid rocket engine pump isolation chamber blowing, and in particular to a liquid rocket engine turbine pump isolation chamber gas blowing system, method and rocket. Background Art

[0002] During multiple stages when the liquid rocket is on the ground or after takeoff, its liquid engine needs to be blown away by a ground-based blow-off system or an onboard blow-off system to ensure the flight safety of the liquid rocket.

[0003] Maintaining the separation of incompatible fluids is the key to the safe and stable operation of the liquid rocket engine turbopump system. Highly active oxidizers and fuels may cause explosion hazards when mixed, so it is necessary to seal and isolate incompatible fluids on the same axis. The conventional method is to use end face seals to reduce leakage, set up discharge ports to discharge leakage to a safe treatment area, and blow out the isolation cavity between the seals to prevent the two propellants from mixing.

[0004] In the prior art, helium or nitrogen is used to purge the isolation cavity. The purge gas must have sufficient pressure and flow. After entering the isolation cavity for purge, the gas is discharged from the sealed discharge ports on both sides together with the working fluid to prevent the two working fluids from mixing.

[0005] In the process of implementing the prior art, the inventors found that there are at least the following problems in the prior art: although it can meet the requirements of the blow-off operation, in actual application, it is necessary to carry a helium or nitrogen cylinder to achieve continuous blow-off of the engine from before starting to after shutdown, which will greatly increase the difficulty of assembly and will also affect the carrying capacity of liquid rockets to a certain extent. In addition, for the blow-off of gas cylinders, the orifice throttling used in conjunction will cause the blow-off pressure of the isolation chamber to be unstable, and it cannot be used when the pressure is too low. The use of a pressure reducer for blow-off requires the addition of a control valve, which reduces the isolation stability and reliability of the engine isolation chamber, and its applicability is limited. Summary of the invention

[0006] In view of this, the purpose of the embodiments of the present invention is to provide a liquid rocket engine turbine pump isolation chamber gas purge system, method and rocket with a reasonable structural arrangement and conducive to ensuring a smooth and reliable purge flow rate.

[0007] To achieve the above-mentioned object, in a first aspect, the present invention provides a liquid rocket engine turbine pump isolation chamber gas blowing system, comprising a gas generator connected to a turbine, an oxygen pump and a fuel pump connected to the gas generator, an isolation chamber is provided between the oxygen pump and the fuel pump, and a liquid oxygen discharge port and a fuel discharge port are provided on the side wall of the isolation chamber; The liquid oxygen discharge port is arranged on a side of the isolation chamber close to the oxygen pump, and the fuel discharge port is arranged on a side of the isolation chamber close to the fuel pump; A heat exchanger is provided in the exhaust pipe of the turbine; The inlet end of the heat exchanger is connected to a pipeline of low-temperature heat exchange medium; A blow-off port is provided on the side wall of the isolation chamber, the blow-off port is located between the liquid oxygen discharge port and the fuel discharge port, and the blow-off port is connected to the heat exchange port of the heat exchanger through a connecting pipe.

[0008] It is further preferred that: the blow-off port is connected with a three-way interface; One end of the three-way interface is connected to the blow-off port, one end is connected to the connecting pipe, and the remaining end is connected to the air supply pipe.

[0009] It is further preferred that a throttling regulator is provided on the connecting pipeline.

[0010] It is further preferred that the throttling regulator is a throttling orifice plate, a valve or an automatic device.

[0011] It is further preferred that: the end of the connecting pipe is connected to a propellant pressurizing pipeline; A one-way valve is arranged on the propellant pressurizing pipeline, and the one-way valve realizes one-way control of the propellant delivery of the propellant pressurizing pipeline.

[0012] It is further preferred that the low-temperature heat exchange medium of the low-temperature heat exchange medium pipeline is a low-temperature inert gas.

[0013] It is further preferred that the low-temperature heat exchange medium of the low-temperature heat exchange medium pipeline is liquid nitrogen or cold helium.

[0014] It is further preferred that kerosene is supplied to the inlet end of the fuel pump; and liquid oxygen is supplied to the inlet end of the oxygen pump.

[0015] It is further preferred that: a rotating shaft of the turbine is disposed in the isolation chamber and is connected to the oxygen pump and the fuel pump.

[0016] Further preferably, the end faces of the oxygen pump and the fuel pump are both provided with end face seals, and the end face seals are located at both ends of the isolation cavity.

[0017] In a second aspect, an embodiment of the present invention provides a method for blowing gas out of a liquid rocket engine turbine pump isolation chamber, which is performed by the above-mentioned blowing system, and the method comprises the following steps: During the engine precooling process, the isolation cavity is continuously purged through the air supply pipeline; In the preparation stage before the engine starts, the ground supplies gas from the gas supply pipeline; a time window is preset before the engine starts, the liquid gas inlet isolation valve of the low-temperature heat exchange medium pipeline is opened, and the ground gas supply pipeline is disconnected at the same time as the engine starts, and the propellant booster pipeline alone relays the gas supply; During the stable operation of the engine, the isolation chamber is continuously purged by hot gas from the connecting pipe; When the engine is shut down, the liquid gas inlet isolation valve of the low-temperature heat exchange medium pipeline is closed after the preset shutdown time.

[0018] The third purpose of an embodiment of the present invention is to provide a rocket with a blowing system for a rocket engine isolation cavity, which includes the above-mentioned blowing system.

[0019] A small amount of propellant leaked from the oxygen pump and the fuel pump enters the isolation cavity and is discharged from the liquid oxygen discharge port and the fuel discharge port respectively under the action of the high-temperature heat exchange medium.

[0020] In a third aspect, a liquid rocket is provided, comprising any one of the liquid rocket engine turbine pump isolation chamber gas purge systems described above.

[0021] The above technical solution has the following beneficial effects: 1. The structure of the present invention is reasonably arranged, in which a heat exchanger is arranged in the exhaust pipe of the turbine; the inlet end of the heat exchanger is connected to the low-temperature heat exchange medium pipeline; a blow-off port is arranged on the side wall of the isolation cavity, and the blow-off port is connected to the heat exchange port of the heat exchanger through a connecting pipe. Through the above structure, the isolation cavity can be blown off by the heat exchange medium in the heat exchanger, which not only reduces the use of gas cylinders and reduces the difficulty of assembly, but also is beneficial to improving the carrying capacity of the rocket and ensuring the stability and reliability of the blow-off flow.

[0022] 2. A three-way interface is connected to the blow-off port, one end of the three-way interface is connected to the blow-off port, one end is connected to the connecting pipe, and the remaining end is connected to the air supply pipe. Through the above structure, the pressure in the isolation chamber can be quickly built up and stabilized after the engine is started, thereby improving the effectiveness and reliability of the blow-off.

[0023] 3. Reasonable isolation chamber pressure and the aperture of the throttling regulator on the connecting pipe and the gas supply pipe can ensure that the leakage is within a reasonable range and that the temperature rise of the isolation chamber is small.

[0024] 4. In actual application, the aperture of the throttling regulator can be changed according to the pressure and flow of the isolation chamber to improve its application range.

[0025] 5. The end of the connecting pipe is connected to a propellant pressurizing pipeline, and a one-way valve is arranged on the propellant pressurizing pipeline. Through the above structure, it can be ensured that the pressurized gas in the tank will not leak into the isolation chamber, thereby improving the stability and effectiveness of use.

[0026] 6. The low-temperature heat exchange medium pipeline is liquid nitrogen or cold helium, which is conducive to ensuring the effectiveness and reliability of blowing and improving the safety of the overall structure.

[0027] 7. If the pressure in the isolation chamber is high during ground blowdown, the pressure will be released from the heat exchanger to reduce the pressure in the isolation chamber. If the pressure in the isolation chamber is high due to the heat exchanger blowdown during flight, the pressure will be released from the engine ground blowdown route. This helps to avoid wear of the floating ring due to high pressure in the isolation chamber.

[0028] 8. The blowing method provided is simple, which is conducive to improving the efficiency and stability of blowing.

[0029] 9. The rockets it provides are conducive to improving the overall rocket's carrying capacity, reducing the difficulty of final assembly, and improving operational reliability.

[0030] 10. A new liquid rocket engine turbo pump isolation chamber purge solution proposed in an embodiment of the present invention uses the engine heat exchanger outlet gas to purge the isolation chamber. When the purge requirements are met, the isolation chamber purge gas bottle is eliminated and the purge flow rate can be guaranteed to be stable. If the isolation valve leakage is small and the isolation chamber pressure is high, another path can be diverted to reduce the isolation chamber pressure. BRIEF DESCRIPTION OF THE DRAWINGS

[0031] In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings required for use in the embodiments or the description of the prior art will be briefly introduced below. Obviously, the drawings described below are only some embodiments of the present invention. For ordinary technicians in this field, other drawings can be obtained based on these drawings without paying creative work.

[0032] Figure 1 is a schematic diagram of a specific structure of an embodiment of the present invention; Figure 2 is a schematic diagram of a local enlarged structure at point A in an embodiment of the present invention; Figure 3 is a schematic diagram of a local enlarged structure at position B in an embodiment of the present invention; Figure 4 It is a method flow chart of an embodiment of the present invention.

[0033] Reference numerals: 1. Turbine; 2. Gas generator; 3. Oxygen pump; 4. Fuel pump; 5. Isolation chamber; 6. Liquid oxygen discharge port; 7. Fuel discharge port; 8. Heat exchanger; 9. Low-temperature heat exchange medium pipeline; 10. Blow-off port; 11. Connecting pipeline; 12. Three-way interface; 13. Air supply pipeline; 14. Throttle regulator; 15. Propellant boost pipeline; 16. One-way valve; 17. Rotating shaft. DETAILED DESCRIPTION

[0034] The features and exemplary embodiments of various aspects of the present invention will be described in detail below. In the detailed description below, many specific details are proposed in order to provide a comprehensive understanding of the present invention. However, it is obvious to those skilled in the art that the present invention can be implemented without some of these specific details. The following description of the embodiments is only to provide a better understanding of the present invention by illustrating examples of the present invention. In the drawings and the following description, at least part of the known structures and technologies are not shown in order to avoid unnecessary ambiguity of the present invention; and, for clarity, the size of some structures may be exaggerated. In addition, the features, structures or characteristics described below may be combined in one or more embodiments in any suitable manner.

[0035] like Figures 1 to 3 As shown, the liquid rocket engine turbine pump isolation chamber gas blowing system includes a gas generator 2 connected to the turbine 1, an oxygen pump 3 and a fuel pump 4 connected to the turbine 1, an isolation chamber 5 is arranged between the oxygen pump 3 and the fuel pump 4, and a liquid oxygen discharge port 6 and a fuel discharge port 7 are arranged on the side wall of the isolation chamber 5; in this embodiment, the interior of the isolation chamber 5 is a sealing structure of the oxygen side and the fuel side respectively.

[0036] The turbine 1 , gas generator 2 , oxygen pump 3 and fuel pump 4 are conventional structures in the prior art and are not described in detail. The rotating shaft 17 of the turbine 1 is passed through the isolation chamber 5 and is connected to the oxygen pump 3 and the fuel pump 4 .

[0037] like Figure 1 As shown, the liquid oxygen discharge port 6 is arranged on the side of the isolation chamber 5 close to the oxygen pump 3, and the fuel discharge port 7 is arranged on the side of the isolation chamber 5 close to the fuel pump 4; and a heat exchanger 8 is arranged in the exhaust pipe of the turbine 1; the heat exchanger 8 heats and raises the temperature of the low-temperature heat exchange medium from the low-temperature heat exchange medium pipeline 9.

[0038] like Figure 1 and Figure 3As shown, in this embodiment, the inlet end of the heat exchanger 8 is connected to the cryogenic heat exchange medium pipeline 9; wherein the inlet end of the heat exchanger 8 is connected to a cryogenic heat exchange medium bottle or a storage tank, which is used to continuously inject cryogenic heat exchange medium into the heat exchanger 8. In addition, a blow-off port 10 is provided on the side wall of the isolation chamber 5, and the blow-off port 10 is located between the liquid oxygen discharge port 6 and the fuel discharge port 7, and the blow-off port 10 is connected to the heat exchange port of the heat exchanger 8 through a connecting pipe 11. After the heat exchanger 8 exchanges heat, the cryogenic heat exchange medium in its cryogenic heat exchange medium pipeline 9 becomes a high-temperature medium, and flows to the blow-off port 10 for blowing off the gas supply, which can reduce the use of gas bottles and ensure the continuous effectiveness of blowing off. In this embodiment, the cryogenic heat exchange medium uses liquid nitrogen, the temperature of which is about 104K (-170℃), and other commonly used, such as cold helium, the temperature of which is about 84k (-190℃). "Low temperature" is related to the specific substance.

[0039] In this embodiment, the low-temperature heat exchange medium of the low-temperature heat exchange medium pipeline 9 is a low-temperature inert gas. Specifically, the low-temperature heat exchange medium of the low-temperature heat exchange medium pipeline 9 is liquid nitrogen or cold helium.

[0040] like Figure 1 and Figure 2 As shown, the blow-off port 10 is connected to a three-way interface 12; one end of the three-way interface 12 is connected to the blow-off port 10, one end is connected to the connecting pipe 11, and the remaining end is connected to the air supply pipe 13. In this embodiment, the connection between the three-way interface 12 and the blow-off port 10 is reverse threaded, which is conducive to improving the stability and reliability of the connection.

[0041] like Figure 1 As shown, a throttling regulator 14 is provided on the connecting pipe 11. The throttling regulator 14 is a throttling orifice plate, a valve or an automatic device. When in use, the throttling regulator 14 can adjust the aperture of the throttling regulator 14 according to the pressure and flow in the connecting pipe 11, the air supply pipe 13 and the isolation chamber 5 to meet the working requirements and ensure the stability of use.

[0042] like Figure 1 As shown, the end of the connecting pipe 11 is connected to a propellant pressurizing pipeline 15, and a one-way valve 16 is arranged on the propellant pressurizing pipeline 15, and the one-way valve 16 realizes one-way control of the propellant delivery of the propellant pressurizing pipeline 15, thereby ensuring that the tank pressurized gas will not leak into the isolation chamber 5.

[0043] like Figure 1 As shown, kerosene is supplied to the inlet end of the fuel pump 4, and liquid oxygen is supplied to the inlet end of the oxygen pump 3. The end faces of the oxygen pump 3 and the fuel pump 4 are both provided with end face seals, which are located at both ends of the isolation chamber 5. The end face seals are dynamic seals.

[0044] A small amount of leaked liquid from the oxygen pump 3 and the fuel pump 4 enters the isolation chamber 5, and is discharged from the liquid oxygen discharge port 6 and the fuel discharge port 7 respectively under the blowing action of the high-temperature heat exchange medium. In this embodiment, the high-temperature heat exchange medium is a liquid gas that enters from the low-temperature heat exchange medium pipeline 9, is heated to about 450K (177°C) in the heat exchanger 8, and becomes nitrogen, which is respectively transported upward from the propellant booster pipeline 15 for boosting, and is passed into the isolation chamber 5 from the connecting pipeline 11 for blowing.

[0045] The above technical solution has the following beneficial effects: 1. The structure of the present invention is reasonably arranged. A heat exchanger is arranged in the exhaust pipe of the turbine; the inlet end of the heat exchanger is connected to the low-temperature heat exchange medium pipeline; a blow-off port is arranged on the side wall of the isolation cavity, and the blow-off port is connected to the heat exchange port of the heat exchanger through a connecting pipe. Through the above structure, the isolation cavity can be blown off by the heat exchange medium in the heat exchanger, which not only reduces the use of gas cylinders and reduces the difficulty of assembly, which is beneficial to improving the carrying capacity of the rocket, but also helps to ensure the stability and reliability of the blow-off flow.

[0046] 2. A three-way interface is connected to the blow-off port, one end of the three-way interface is connected to the blow-off port, one end is connected to the connecting pipe, and the remaining end is connected to the gas supply pipe. The isolation cavity is blown off before starting, and the isolation cavity is no longer blown off through the channel after starting. The hot gas after the heat exchanger is used to blow off the isolation cavity. Compared with the solution of blowing off with a gas cylinder, it is more stable.

[0047] 3. Through reasonable isolation chamber pressure and changing the aperture of the throttling regulator set on the connecting pipeline and the gas supply pipeline, the leakage can be kept within a reasonable range and the temperature rise of the isolation chamber can be kept small.

[0048] 4. In actual application, the aperture of the throttling regulator can be changed according to the pressure and flow of the isolation chamber to improve its application range.

[0049] 5. The end of the connecting pipe is connected to a propellant pressurizing pipeline, and a one-way valve is arranged on the propellant pressurizing pipeline. Through the above structure, it can be ensured that the pressurized gas in the tank will not leak into the isolation chamber, thereby improving the stability and effectiveness of use.

[0050] 6. The low-temperature heat exchange medium pipeline is liquid nitrogen or cold helium, which is conducive to ensuring the effectiveness and reliability of blowing and improving the safety of the overall structure.

[0051] 7. If the pressure in the isolation chamber is high during ground blowdown, the pressure will be released from the heat exchanger line to reduce the pressure in the isolation chamber. Similarly, if the pressure in the isolation chamber is high due to heat exchanger line blowdown during flight, the pressure will be released from the engine ground blowdown line. This helps to avoid wear of the floating ring due to high pressure in the isolation chamber.

[0052] like Figure 4 As shown, in another embodiment, a method for blowing gas out of the isolation chamber of a liquid rocket engine turbine pump is also provided. When in use, liquid oxygen enters the oxygen pump 3, and kerosene enters the fuel pump 4. After being pressurized, part of the liquid oxygen and kerosene enter the gas generator 2 and burn, generating high-temperature combustion gas to drive the turbine 1 and then discharge from the turbine combustion gas exhaust port. The liquid gas enters from the low-temperature heat exchange medium pipeline 9, passes through the heat exchanger 8, exchanges heat with the high-temperature combustion gas at the turbine combustion gas exhaust port, and becomes hot gas, which is introduced into the rocket's propellant tank through the propellant boosting pipeline 15 to boost it.

[0053] A small amount of liquid oxygen leaking from the end face seal leaks from the oxygen pump 3 into the isolation chamber 5 and is discharged from the liquid oxygen discharge port 6. A small amount of kerosene leaking from the end face seal leaks from the fuel pump 4 into the isolation chamber 5 and is discharged from the fuel discharge port 7. Hot gas continues to enter the isolation chamber 5 through the connecting pipe 11 to isolate liquid oxygen and kerosene to prevent the two leaked propellants from mixing in the isolation chamber 5, and the hot gas will be discharged from the liquid oxygen discharge port 6 and the fuel discharge port 7 together with the two propellants.

[0054] The method comprises the following steps: S10: During the engine precooling process, the isolation chamber 5 is continuously purged through the air supply pipe 13 .

[0055] According to the current pressure of the ground blow-off gas cylinder and the isolation chamber 5 and the diameter of the throttling regulator 14 on the connecting pipe 11, it can be known that the nitrogen flow rate of the ground blow-off gas leaking back through the throttling regulator 14, the connecting pipe 11, and the propellant boosting pipeline 15 to the tank boosting nitrogen cylinder is relatively small (for example, less than 3g / s). When the tank is pressurized, according to the pressure of the isolation chamber 5 and the diameter of the throttling regulator 14 on the gas supply pipe 13, the nitrogen flow rate leaking back through the gas supply pipe 13 after entering the isolation chamber 5 from the connecting pipe 11 is also relatively small.

[0056] S20: In the preparation stage before the engine starts, air is supplied from the air supply pipeline 13 on the ground; in a preset time window before the engine starts, for example, -1s to -5s, the liquid gas inlet isolation valve of the low-temperature heat exchange medium pipeline 9 is opened, and the air supply pipeline 13 on the ground is disconnected while the engine starts, and the propellant booster pipeline 15 alone takes over the air supply.

[0057] If the liquid gas inlet isolation valve of the cryogenic heat exchange medium pipeline 9 is opened too early before starting, liquid gas discharge will be seen at the liquid oxygen discharge port 6 and the fuel discharge port 7. In order to ensure that the liquid gas does not enter the isolation chamber 5 too early, the liquid gas inlet isolation valve of the cryogenic heat exchange medium pipeline 9 needs to be opened in advance.

[0058] S30: During the stable operation of the engine, the isolation chamber 5 is continuously purged by the hot gas from the connecting pipe 11 .

[0059] Under the existing orifice plate structure design, part of the hot gas will leak from the gas supply pipe 13. According to the hot gas temperature and pressure of the connecting pipe 11 and the pressure of the isolation chamber 5, it can be known that the leakage flow is small. The hot gas heat exchange amount is calculated by the temperature difference between the hot gas inlet and outlet. According to the material specific heat and weight of the isolation chamber 5, the temperature rise of the isolation chamber 5 is about 2°C. The hot gas has little effect on the temperature rise of the isolation chamber 5. The flow of the connecting pipe 11 accounts for a very small proportion of the flow of the propellant boosting pipeline 15, and there is no need to modify the original propellant boosting pipeline 15 components.

[0060] S40: When the engine is shut down, the liquid gas inlet isolation valve of the low-temperature heat exchange medium pipeline 9 is closed after a preset shutdown time.

[0061] Specifically, after shutdown, the heat exchange capacity of the heat source at the heat exchanger 8 is weakened. To prevent liquid gas from entering the isolation chamber 5, the liquid gas inlet isolation valve of the low-temperature heat exchange medium pipeline 9 needs to be closed after a preset time according to the heat exchange capacity of the heat exchanger 8.

[0062] Among them, the above-mentioned preset duration is approximately t+5s to t+10s (t is the time when the engine is shut down), which is specifically determined according to the temperature change in the exhaust pipe after the engine of this model is shut down.

[0063] The above-mentioned blowing method is beneficial to improving the efficiency and stability of blowing.

[0064] This embodiment also provides a rocket, including the above-mentioned liquid rocket engine turbo pump isolation chamber gas blowing system, which is beneficial to improving the carrying capacity of the entire rocket, reducing the difficulty of final assembly, and improving the reliability of use.

[0065] In the description of the present invention, it should be noted that the directions or positional relationships indicated by the terms "upper, lower, inner and outer" are based on the directions or positional relationships shown in the drawings, and are only for the convenience of describing the present invention and simplifying the description, rather than indicating or implying that the device or element referred to must have a specific direction, be constructed and operated in a specific direction, and therefore cannot be understood as limiting the present invention. In addition, the terms "first, second or third" are only used for descriptive purposes and cannot be understood as indicating or implying relative importance.

[0066] In the present invention, unless otherwise clearly specified and limited, the terms "install, connect, connect" should be understood in a broad sense, for example: it can be a fixed connection, a detachable connection or an integral connection; it can also be a mechanical connection, an electrical connection or a direct connection, or it can be indirectly connected through an intermediate medium, or it can be the internal communication of two components. For ordinary technicians in this field, the specific meanings of the above terms in the present invention can be understood according to specific circumstances.

[0067] Although the present invention has been described with reference to preferred embodiments, various modifications may be made thereto and parts thereof may be replaced by equivalents without departing from the scope of the present invention. In particular, the various technical features mentioned in the various embodiments may be combined in any manner as long as there are no structural conflicts. The present invention is not limited to the specific embodiments disclosed herein, but includes all technical solutions falling within the scope of the claims.

Claims

1. A liquid rocket engine turbine pump isolation chamber gas purge system, comprising a gas generator (2) connected to a turbine (1), an oxygen pump (3) and a fuel pump (4) connected to the turbine (1), characterized in that: An isolation chamber (5) is provided between the oxygen pump (3) and the fuel pump (4), and a liquid oxygen discharge port (6) and a fuel discharge port (7) are provided on a side wall of the isolation chamber (5); The liquid oxygen discharge port (6) is arranged on a side of the isolation chamber (5) close to the oxygen pump (3), and the fuel discharge port (7) is arranged on a side of the isolation chamber (5) close to the fuel pump (4); A heat exchanger (8) is arranged in the exhaust pipe of the turbine (1); The inlet end of the heat exchanger (8) is connected to a low-temperature heat exchange medium pipeline (9); A blow-off port (10) is provided on the side wall of the isolation chamber (5); the blow-off port (10) is located between the liquid oxygen discharge port (6) and the fuel discharge port (7); the blow-off port (10) is connected to the heat exchange port of the heat exchanger (8) via a connecting pipe (11).

2. A liquid rocket engine turbo pump isolation chamber gas purge system according to claim 1, characterized in that: The blow-off port (10) is connected to a three-way interface (12); One end of the three-way interface (12) is connected to the blow-off port (10), one end is connected to the connecting pipe (11), and the remaining end is connected to the air supply pipe (13); The connecting pipe (11) is provided with a throttling regulator (14); The throttling regulator (14) is a throttling orifice plate, a valve or an automatic device.

3. A liquid rocket engine turbo pump isolation chamber gas purge system according to claim 2, characterized in that: The end of the connecting pipe (11) is connected to a propellant pressurizing pipeline (15); The propellant pressurizing pipeline (15) is provided with a one-way valve (16), and the one-way valve (16) realizes one-way control of the propellant delivery in the propellant pressurizing pipeline (15).

4. A liquid rocket engine turbo pump isolation chamber gas purge system according to claim 1, characterized in that: The low-temperature heat exchange medium of the low-temperature heat exchange medium pipeline (9) is a low-temperature inert gas; The low-temperature heat exchange medium entering the heat exchanger (8) from the low-temperature heat exchange medium pipeline (9) is liquid nitrogen or cold helium.

5. A liquid rocket engine turbo pump isolation chamber gas purge system according to claim 1, characterized in that: Kerosene is supplied to the inlet end of the fuel pump (4); liquid oxygen is supplied to the inlet end of the oxygen pump (3).

6. A liquid rocket engine turbo pump isolation chamber gas purge system according to claim 1, characterized in that: The rotating shaft (17) of the turbine (1) is disposed in the isolation chamber (5) and is connected to the oxygen pump (3) and the fuel pump (4).

7. A liquid rocket engine turbo pump isolation chamber gas purge system according to claim 1, characterized in that: The end faces of the oxygen pump (3) and the fuel pump (4) are both provided with end face seals, and the end face seals are located at both ends of the isolation chamber (5); The leaked liquid of the oxygen pump (3) and the fuel pump (4) enters the isolation chamber (5) and is discharged from the liquid oxygen discharge port (6) and the fuel discharge port (7) respectively under the action of the high-temperature heat exchange medium.

8. A method for blowing out gas from the isolation chamber of a liquid rocket engine turbo pump, characterized in that: The method is performed by the liquid rocket engine turbopump isolation chamber gas purge system according to any one of claims 3 to 7, and the method comprises the following steps: S10: During the engine precooling process, the isolation chamber (5) is continuously purged through the air supply pipe (13); S20: In the preparation stage before the engine starts, the ground supplies gas from the gas supply pipeline (13); in a preset time window before the engine starts, the liquid gas inlet isolation valve of the low-temperature heat exchange medium pipeline (9) is opened, and when the engine starts, the ground gas supply pipeline (13) is disconnected, and the propellant booster pipeline (15) alone takes over the gas supply; S30: During the stable operation period of the engine, the isolation chamber (5) is continuously purged by hot gas from the connecting pipe (11); S40: When the engine is shut down, the liquid gas inlet isolation valve of the low-temperature heat exchange medium pipeline (9) is closed after a preset shutdown time.

9. The method for blowing out gas from the isolation chamber of a liquid rocket engine turbo pump according to claim 8, characterized in that: The preset duration is 5 to 10 seconds; The preset time window is -1 second to -10 seconds.

10. A liquid rocket, characterized in that: A liquid rocket engine turbopump isolation chamber gas purge system comprising any one of claims 1 to 7.

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