Full-system combined sealing test device and system for oxygen pump of oxyhydrogen engine

Abstract

The invention discloses a full-system combined sealing test device for an oxygen pump of an oxyhydrogen engine. The full-system combined sealing test device comprises a medium supply system, a rotor assembly and a shell assembly which is used for supporting the rotor assembly and forming a test environment, a static ring assembly to be tested is sleeved on the rotor assembly, is in contact with the moving ring and is fixed on the shell assembly; a plurality of sealing cavities and leakage cavities are formed among the static ring assembly, the shell assembly and the rotor assembly, and the medium supply system communicates with the sealing cavities and is used for providing low-temperature or normal-temperature media for the sealing cavities; during testing, the rotor assembly rotates, the static ring assembly to be tested is in contact with the moving ring to perform dynamic sealing on the rotor assembly, and the sealing leakage rate and the working performance of each static ring assembly are obtained by monitoring the inlet flow rate of each sealing cavity and the leakage rate of each leakage cavity. The invention also provides a full-system combined sealing test system for the oxygen pump of the hydrogen-oxygen engine. According to the invention, the real working condition of the turbine pump can be simulated, the test efficiency is improved by 5 times, and the cost is saved.

Description

Technical Field

[0001] The present invention belongs to the technical field of low-temperature sealing test of liquid rocket engines, and specifically relates to a testing device and system that can test five end face seals at one time and simulate the actual working conditions of the end face seals in a turbo pump. Background Art

[0002] The liquid hydrogen and oxygen rocket engine turbopump adopts a multi-stage end face seal combination seal. The seal is a key component in the turbopump to isolate the working media such as liquid hydrogen and liquid oxygen, and is crucial to the safe operation and function of the turbopump. The end face seal includes two states: normal temperature and low temperature. Before the test run and launch of the liquid rocket engine turbopump, it is necessary to carry out running or random inspection tests on its key components to obtain its sealing performance and wear performance. However, the current sealing test equipment can generally only conduct low-temperature or normal temperature operation tests on one or two products respectively, and cannot simulate the environment of mixed low-temperature and normal temperature media in the turbopump, and cannot achieve a one-time assessment of all sealing products in the turbopump. Summary of the invention

[0003] The technical problem solved by the present invention is to overcome the deficiencies of the prior art and provide a combined sealing test device and system that can simulate the actual working conditions of a turbine pump, increase the test efficiency by 5 times, and save costs.

[0004] The solution of the present invention is:

[0005] A combined sealing test device for the whole system of an oxygen pump of a hydrogen-oxygen engine comprises a medium supply system, a rotor assembly and a shell assembly for supporting the rotor assembly and forming a test environment; a stationary ring assembly to be tested is sleeved on the rotor assembly according to a certain compression amount, contacts with a dynamic ring, and is fixed on the shell assembly; a plurality of sealing cavities and leakage cavities are formed between the stationary ring assembly, the shell assembly and the rotor assembly, and a medium supply system is connected with the sealing cavities to provide low-temperature or normal-temperature medium for the sealing cavities; during the test, the rotor assembly rotates, and the stationary ring assembly to be tested contacts with the dynamic ring to perform dynamic sealing on the rotor assembly, and the sealing leakage and working performance of each stationary ring assembly are obtained simultaneously by monitoring the inlet flow of each sealing cavity and the leakage of each leakage cavity.

[0006] Preferably, the housing assembly includes a first housing and a second housing; one side of the first housing is referred to as the front side, and one side of the second housing is referred to as the rear side;

[0007] The rotor assembly includes a main shaft, a first bearing and a second bearing; the rear end of the main shaft is fixedly mounted on the second housing through the second bearing, and the front end is fixed on the bearing seat through the first bearing, and the bearing seat is fixedly mounted on the first housing.

[0008] Preferably, the inner ring of the first bearing or the second bearing is installed on the main shaft; the outer ring of the second bearing is installed on the second housing, and the outer ring end face is pressed by a thrust nut; the outer ring of the first bearing is installed on the bearing seat, and the bearing adjustment gasket is installed between the outer ring of the first bearing and the bearing seat, and the preload force of the bearing is adjusted by changing the thickness of different bearing adjustment gaskets, and finally the first bearing is locked by the front locking nut.

[0009] Preferably, the stationary ring assemblies to be tested are, from front end to rear end on the rotor assembly, the first low-temperature stationary ring assembly, the first normal temperature stationary ring assembly, the second normal temperature stationary ring assembly, the second low-temperature stationary ring assembly, and the third low-temperature stationary ring assembly.

[0010] Preferably, the installation process of the stationary ring assembly to be tested is as follows:

[0011] Install the second bearing on the second housing and tighten it with the thrust nut, then install the sleeve IV and the moving ring II on the main shaft;

[0012] Install the second low-temperature static ring assembly. The installation method is: install the rear end of the main shaft through the second bearing inner ring, put the second low-temperature static ring assembly on the main shaft, and fix it on the second shell, and set a sealing aluminum gasket between the second low-temperature static ring assembly and the second shell; the graphite ring in the second low-temperature static ring assembly faces the dynamic ring II and contacts with it, and the compression amount of the second low-temperature static ring assembly is adjusted by the length of the sleeve IV and the thickness of the sealing aluminum gasket between the second low-temperature static ring assembly and the second shell.

[0013] Install the second normal temperature static ring assembly. The installation method is: put the second normal temperature static ring assembly on the main shaft and fix it on the second shell, set a static ring gasket between the second normal temperature static ring assembly and the second shell, and install the dynamic ring III on the main shaft; the graphite ring of the second normal temperature static ring assembly faces the dynamic ring III and contacts it, and the compression amount of the second normal temperature static ring assembly is adjusted by the thickness of the static ring gasket.

[0014] Install the first normal temperature static ring assembly. The installation method is: put the first normal temperature static ring assembly on the main shaft and fix it on the first shell, set a static ring gasket between the first normal temperature static ring assembly and the second shell, the graphite ring of the first normal temperature static ring assembly faces the dynamic ring III and contacts it, the first shell and the second shell are fastened by bolts, and the compression of the first normal temperature static ring assembly is adjusted by the thickness of the static ring gasket.

[0015] Install the first low-temperature static ring assembly, and the installation method is: put the first low-temperature static ring assembly on the main shaft and fix it on the first shell, set a sealing gasket between the first low-temperature static ring assembly and the second shell, install the sleeve III and the dynamic ring I on the main shaft, and the sleeve III is located at the rear end of the dynamic ring I; the graphite ring of the first low-temperature static ring assembly faces the dynamic ring I and contacts with it, and the compression of the first low-temperature static ring assembly is adjusted by the length of the sleeve III and the thickness of the sealing gasket.

[0016] Install the sleeve II on the main shaft;

[0017] The bearing seat is fixed on the first housing, the inner ring of the first bearing is sleeved on the front end of the main shaft, the outer ring of the first bearing is installed on the bearing seat, the bearing adjustment gasket is installed between the outer ring of the first bearing and the bearing seat, the preload force of the bearing is adjusted by adjusting the thickness of the bearing adjustment gasket, and the first bearing is locked by the front locking nut;

[0018] Install the second low-temperature static ring assembly, and the installation method is: install the sleeve V and the dynamic ring IV on the main shaft, and the dynamic ring IV is located at the rear end of the sleeve V; sleeve the second low-temperature static ring assembly on the main shaft and fix it on the second shell, and a sealing gasket is arranged between the second low-temperature static ring assembly and the second shell; the graphite ring of the second low-temperature static ring assembly faces the dynamic ring IV and contacts with it, and the compression amount of the second low-temperature static ring assembly is adjusted by the length of the sleeve V and the thickness of the sealing gasket.

[0019] Preferably, the method for adjusting the bearing preload is as follows: after adjusting the compression amount of each stationary ring assembly and completing the installation, all stationary ring assemblies are disassembled, and the dynamic ring I, sleeve III, dynamic ring III, dynamic ring II, dynamic ring IV, and sleeve IV on the shaft system are kept unchanged; the bearing preload is adjusted by the length of the sleeve II and the thickness of the bearing adjustment gasket; after completing the adjustment of the bearing preload, all components are reassembled in the assembly order.

[0020] A combined sealing test system for the whole system of an oxygen pump of a hydrogen-oxygen engine, including a gas distribution system, a medium recovery and discharge system, a motor, and a gear box;

[0021] The output shaft of the motor is connected to the gear box, the output end of the gear box is connected to the main shaft of the test device, the gas distribution system is connected to the medium supply system through a pipeline, and the leakage chamber of the test device is connected to the medium recovery and discharge system through a pipeline;

[0022] After installation, there are 6 cavities formed between the static ring assembly, shell assembly and rotor assembly of the test device, which are, from front to back, the first low-temperature liquid nitrogen high-pressure chamber, the first normal-temperature mixed leakage chamber, the helium-sealed normal-temperature high-pressure chamber, the second normal-temperature mixed leakage chamber, the second low-temperature liquid nitrogen high-pressure chamber, and the low-temperature leakage chamber. Among them, the first low-temperature liquid nitrogen high-pressure chamber, the helium-sealed normal-temperature high-pressure chamber, and the second low-temperature liquid nitrogen high-pressure chamber are all sealed chambers.

[0023] Preferably,

[0024] The liquid nitrogen sources of the first cryogenic liquid nitrogen high-pressure chamber and the second cryogenic liquid nitrogen high-pressure chamber are: high-pressure air is pressurized on the liquid nitrogen pressure vessel through the pressure reducing valve of the gas distribution system, and the liquid nitrogen is sequentially passed through the cryogenic filter by extrusion and then divided into two branches, each branch is provided with a cryogenic filter and a cryogenic mass flowmeter, and the measured mass flow rates are Q1 and Q2 respectively, and then enter the first cryogenic liquid nitrogen high-pressure chamber and the second cryogenic liquid nitrogen high-pressure chamber respectively through the medium supply system;

[0025] The outlets of the first cryogenic liquid nitrogen high-pressure chamber and the second cryogenic liquid nitrogen high-pressure chamber are connected to a cryogenic mass flow meter, a cryogenic manual stop valve, and a cryogenic electric regulating valve in sequence. The mass flow rates after the two outlets are Q3 and Q4 respectively, and finally they are collected into the main pipeline and discharged into the medium recovery and discharge system;

[0026] The source of helium in the helium-sealed normal temperature high pressure chamber is: high pressure helium is decompressed by the gas distribution system, then passes through a normal temperature filter, a pressure regulating valve, and a mass flow meter in sequence, the volume flow rate measured by the volume flow meter is Q5, and then enters the helium-sealed normal temperature high pressure chamber;

[0027] The helium in the helium-sealed normal temperature and high pressure chamber leaks through the normal temperature static ring components on both sides and enters the first normal temperature mixed leakage chamber and the second normal temperature mixed leakage chamber respectively;

[0028] The liquid nitrogen medium in the second low-temperature liquid nitrogen high-pressure chamber leaks into the second normal-temperature mixed leakage chamber through the dynamic ring II and the second low-temperature static ring assembly I; the liquid nitrogen medium in the second low-temperature liquid nitrogen high-pressure chamber leaks into the low-temperature leakage chamber through the dynamic ring IV and the third low-temperature static ring assembly;

[0029] The liquid nitrogen medium in the first low-temperature liquid nitrogen high-pressure chamber leaks into the first normal-temperature mixed leakage chamber through the dynamic ring I and the first low-temperature static ring assembly;

[0030] The first normal-low temperature mixed leakage chamber, the second normal-low temperature mixed leakage chamber, and the low temperature leakage chamber are respectively connected to a vaporizer and a volume flow meter in sequence to measure the leakage of the three chambers, which are respectively recorded as Q6, Q7, and Q8;

[0031] According to the above flow measurement results, the leakage of the third low-temperature static ring assembly is Q6, the leakage of the second low-temperature static ring assembly is Q2-Q4-Q6, the leakage of the first low-temperature static ring assembly is Q1-Q3, the leakage of the first normal temperature static ring assembly is Q7-(Q1-Q3), and the leakage of the second normal temperature static ring assembly is Q8-(Q2-Q4-Q6), thereby obtaining the leakage of the five static ring assemblies assembled in the test device.

[0032] The beneficial effects of the present invention compared with the prior art are:

[0033] (1) The test device of the present invention can complete the operation assessment test of all end face seals of a single turbopump of a liquid rocket engine at one time, and can simulate the real environment of low-temperature and normal-temperature mixed media, and truly simulate the actual working conditions of each sealing product in the turbopump;

[0034] (2) The test device and system of the present invention has for the first time constructed a full-system combined sealing test system, overcoming the difficulties of multiple measurement parameters and complex assembly, and completing the assessment test of all end face seals at one time, thereby improving the test efficiency, reducing the test cost, and providing strong support for the development and launch of the engine. BRIEF DESCRIPTION OF THE DRAWINGS

[0035] Figure 1 Schematic diagram of the test device;

[0036] Figure 2 It is a partial diagram of the process combination sealing structure;

[0037] Figure 3 This is the system schematic diagram. DETAILED DESCRIPTION

[0038] The present invention will be further described below in conjunction with the accompanying drawings.

[0039] In order to make ground tests close to real working conditions, accurately evaluate the rationality of sealing product structural parameters and sealing performance, and improve product test adequacy and coverage, a test device and system is proposed that can simulate the assembly relationship and working environment of all static sealing products in liquid rocket engine turbopumps, and complete the assessment and verification of all sealing components in one test, thereby saving test costs and improving test reliability, and providing basic guarantee for model development tasks for high-density launches.

[0040] The main structural components of the full system combined sealing test device of the present invention are as follows: Figure 1 As shown, it includes a rotor assembly for rotation and a shell assembly for supporting the rotor assembly and forming a test environment, a sealing assembly, and a medium supply system. The stationary ring assembly to be tested is mounted on the rotor assembly according to a certain compression amount, contacts the dynamic ring, and is fixed to the shell assembly. Different sealing cavities and leakage cavities are formed between the stationary ring assembly, the shell assembly, and the rotor assembly. The medium supply system is connected to the sealing cavity to provide low-temperature or normal-temperature medium to the sealing cavity; the flow meter behind the leakage cavity is connected to measure the leakage amount of each leakage cavity.

[0041] During the test, the rotor assembly rotates, and the stationary ring assembly to be tested combines with the dynamic ring to dynamically seal the rotor assembly. By monitoring each inlet flow and each leakage cavity flow and calculating through a formula, the sealing leakage and working performance of the five stationary ring assemblies are obtained at the same time.

[0042] The full-system combined sealing test device of the present invention comprises a housing assembly and a rotor component, wherein the housing comprises a first housing 3 and a second housing 4;

[0043] One side of the first shell 3 is recorded as the front side, and one side of the second shell 4 is recorded as the rear side;

[0044] The rotor component includes a main shaft 8, a first bearing and a second bearing; the first bearing is located at the front side of the test device, and the second bearing is located at the rear side of the test device;

[0045] One end of the main shaft 8 is fixedly mounted on the second housing 4 through the second bearing, and the other end is fixedly mounted on the first housing 3 through the bearing seat 13; the inner ring of the first bearing or the second bearing is mounted on the main shaft 8; the outer ring of the second bearing is mounted on the second housing 4, and the outer ring end face is pressed by the thrust nut 77; the outer ring of the first bearing is mounted on the bearing seat 13, and the bearing adjustment gasket 81 is installed between the outer ring of the bearing and the bearing seat 13. The preload force of the bearing is adjusted by replacing the thickness of different bearing adjustment gaskets 81, and finally the second bearing cover and the second bearing sleeve are tightened by bolts to bring the clamping force.

[0046] The installation order of the static ring components of the test device of the present invention from front end to rear end is first low-temperature static ring component 71, first normal temperature static ring component 731, second normal temperature static ring component 732, second low-temperature static ring component 741, and third low-temperature static ring component 742.

[0047] The installation method of the second low-temperature static ring assembly 741 is: install the second bearing (rear end B7206 low-temperature bearing) on ​​the second shell 4, and lock it with the thrust nut 77, then install the sleeve IV 76 and the dynamic ring II75 on the main shaft 8, install the driving end side of the main shaft 8 through the inner ring of the bearing, install the second low-temperature static ring assembly 741 on the second shell 4, and the graphite ring faces the dynamic ring II 75 and contacts it. The compression amount is adjusted by the different thicknesses of the sleeve IV 76 and the different thicknesses of the sealing aluminum gaskets between the second low-temperature static ring assembly 741 and the second shell 4 35.

[0048] Install the second normal temperature static ring assembly 732. The installation method is: put the second normal temperature static ring assembly 732 on the main shaft 8 and fix it on the second shell 4. A static ring gasket is set between the second normal temperature static ring assembly 732 and the second shell, and the dynamic ring III79 is installed on the main shaft 8; the graphite ring of the second normal temperature static ring assembly 732 faces the dynamic ring III 79 and contacts it, and the compression amount of the second normal temperature static ring assembly 732 is adjusted by the thickness of the static ring gasket 14.

[0049] Install the first normal temperature static ring assembly 731. The installation method is: put the first normal temperature static ring assembly 731 on the main shaft 8 and fix it on the first shell 3. A static ring gasket is set between the first normal temperature static ring assembly 731 and the second shell. The graphite ring of the first normal temperature static ring assembly 731 faces the dynamic ring III 79 and contacts it. The first shell 3 and the second shell 4 are fastened by bolts. The compression of the first normal temperature static ring assembly 731 is adjusted by the thickness of the static ring gasket.

[0050] Install the first low-temperature static ring assembly 71. The installation method is: put the first low-temperature static ring assembly 71 on the main shaft 8 and fix it on the first shell 3. A sealing gasket is set between the first low-temperature static ring assembly 71 and the second shell. The sleeve III72 and the dynamic ring I 70 are installed on the main shaft 8, and the sleeve III72 is located at the rear end of the dynamic ring I 70; the graphite ring of the first low-temperature static ring assembly 71 faces the dynamic ring I 70 and contacts it. The compression amount of the first low-temperature static ring assembly 71 is adjusted by the length of the sleeve III72 and the thickness of the sealing gasket 40.

[0051] Install the sleeve II12 on the main shaft 8;

[0052] The bearing seat 13 is fixed on the first housing, the inner ring of the first bearing is sleeved on the front end of the main shaft 8, the outer ring of the first bearing is installed on the bearing seat 13, the bearing adjustment gasket 80 is installed between the outer ring of the first bearing and the bearing seat 13, the preload force of the bearing is adjusted by adjusting the thickness of the bearing adjustment gasket 80, and the first bearing is locked by the front locking nut 15;

[0053] Install the second low-temperature static ring assembly 742, and the installation method is: install the sleeve V 78 and the dynamic ring IV751 on the main shaft 8, and the dynamic ring IV751 is located at the rear end of the sleeve V 78; sleeve the second low-temperature static ring assembly 742 on the main shaft 8 and fix it on the second shell 4, and a sealing gasket 39 is arranged between the second low-temperature static ring assembly 742 and the second shell 4; the graphite ring of the second low-temperature static ring assembly 742 faces the dynamic ring IV751 and contacts it, and the compression amount of the second low-temperature static ring assembly 742 is adjusted by the length of the sleeve V 78 and the thickness of the sealing gasket 39.

[0054] The bearing preload adjustment method is as follows: after the compression of the five stationary ring components is adjusted and installed, all stationary ring components are disassembled, and the moving ring I 70, the sleeve III 72, the moving ring III 79, the moving ring II 75, the moving ring IV 751, and the sleeve IV 76 on the shaft system are kept unchanged, and the moving ring is adjusted by using the sleeve II 12 of different lengths and the bearing adjustment gasket 80. After the bearing preload adjustment is completed, all components are reassembled according to the assembly sequence.

[0055] like Figure 2As shown, the test device of the present invention is divided into 6 cavities formed by the sealing assembly, the rotor assembly, and the shell assembly, which are respectively, from left to right, the first low-temperature liquid nitrogen high-pressure chamber, the first normal-temperature mixed leakage chamber, the helium-sealed normal-temperature high-pressure chamber, the second normal-temperature mixed leakage chamber, the second low-temperature liquid nitrogen high-pressure chamber, and the low-temperature leakage chamber, wherein the first low-temperature liquid nitrogen high-pressure chamber, the helium-sealed normal-temperature high-pressure chamber, and the second low-temperature liquid nitrogen high-pressure chamber are all sealed chambers.

[0056] The liquid nitrogen sources of the first cryogenic liquid nitrogen high-pressure chamber and the second cryogenic liquid nitrogen high-pressure chamber are: high-pressure air is pressurized on the liquid nitrogen pressure vessel through the pressure reducing valve of the gas distribution system, and the liquid nitrogen is sequentially passed through the cryogenic filter by extrusion and then divided into two branches, each branch is provided with a cryogenic filter and a cryogenic mass flowmeter, and the measured mass flow rates are Q1 and Q2 respectively, and then enter the first cryogenic liquid nitrogen high-pressure chamber and the second cryogenic liquid nitrogen high-pressure chamber respectively through the medium supply system;

[0057] The outlets of the first cryogenic liquid nitrogen high-pressure chamber and the second cryogenic liquid nitrogen high-pressure chamber are connected to a cryogenic mass flow meter, a cryogenic manual stop valve, and a cryogenic electric regulating valve in sequence. The mass flow rates after the two outlets are Q3 and Q4 respectively, and finally they are collected into the main pipeline and discharged into the medium recovery and discharge system;

[0058] The source of helium in the helium-sealed normal temperature high pressure chamber is: high pressure helium is decompressed by the gas distribution system, then passes through a normal temperature filter, a pressure regulating valve, and a mass flow meter in sequence, the volume flow rate measured by the volume flow meter is Q5, and then enters the helium-sealed normal temperature high pressure chamber;

[0059] The helium in the helium-sealed normal temperature and high pressure chamber leaks through the normal temperature static ring components on both sides and enters the first normal temperature mixed leakage chamber and the second normal temperature mixed leakage chamber respectively;

[0060] The liquid nitrogen medium in the second low-temperature liquid nitrogen high-pressure chamber leaks into the second normal-temperature mixed leakage chamber through the dynamic ring II75 and the second low-temperature static ring assembly I741; the liquid nitrogen medium in the second low-temperature liquid nitrogen high-pressure chamber leaks into the low-temperature leakage chamber through the dynamic ring IV751 and the third low-temperature static ring assembly 742;

[0061] The liquid nitrogen medium in the first low-temperature liquid nitrogen high-pressure chamber leaks into the first normal-temperature mixed leakage chamber through the dynamic ring I70 and the first low-temperature static ring assembly 71;

[0062] The first normal-low temperature mixed leakage chamber, the second normal-low temperature mixed leakage chamber, and the low temperature leakage chamber are respectively connected to a vaporizer and a volume flow meter in sequence to measure the leakage of the three chambers, which are respectively recorded as Q6, Q7, and Q8;

[0063] According to the above flow measurement results, the leakage of the third low-temperature static ring assembly is Q6, the leakage of the second low-temperature static ring assembly is Q2-Q4-Q6, the leakage of the first low-temperature static ring assembly 71 is Q1-Q3, the leakage of the first normal temperature static ring assembly 731 is Q7-(Q1-Q3), and the leakage of the second normal temperature static ring assembly 732 is Q8-(Q2-Q4-Q6), thereby obtaining the leakage of the five static ring assemblies assembled in the test device.

[0064] Figure 3 This is the system schematic diagram.

[0065] Although the present invention has been disclosed as above in the form of a preferred embodiment, it is not intended to limit the present invention. Any person skilled in the art may make possible changes and modifications to the technical solution of the present invention by using the methods and technical contents disclosed above without departing from the spirit and scope of the present invention. Therefore, any simple modifications, equivalent changes and modifications made to the above embodiments based on the technical essence of the present invention without departing from the content of the technical solution of the present invention shall fall within the protection scope of the technical solution of the present invention.

Claims

1. A combined sealing test device for the whole system of a hydrogen-oxygen engine oxygen pump, characterized in that: It includes a medium supply system, a rotor assembly and a shell assembly for supporting the rotor assembly and forming a test environment; the stationary ring assembly to be tested is mounted on the rotor assembly according to a certain compression amount, contacts the dynamic ring, and is fixed on the shell assembly; a plurality of sealing cavities and leakage cavities are formed between the stationary ring assembly, the shell assembly and the rotor assembly, and the medium supply system is connected to the sealing cavity to provide low-temperature or normal-temperature medium for the sealing cavity; during the test, the rotor assembly rotates, and the stationary ring assembly to be tested contacts the dynamic ring to perform dynamic sealing on the rotor assembly, and the sealing leakage and working performance of each stationary ring assembly are obtained by monitoring the inlet flow of each sealing cavity and the leakage of each leakage cavity.

2. A hydrogen-oxygen engine oxygen pump full system combined sealing test device according to claim 1, characterized in that: The housing assembly comprises a first housing (3) and a second housing (4); one side of the first housing (3) is referred to as the front side, and one side of the second housing (4) is referred to as the rear side; The rotor assembly comprises a main shaft (8), a first bearing (118) and a second bearing (119); the rear end of the main shaft (8) is fixedly mounted on the second housing (4) via the second bearing (119), and the front end of the main shaft (8) is fixedly mounted on the bearing seat (13) via the first bearing (118); and the bearing seat (13) is fixedly mounted on the first housing (3).

3. A hydrogen-oxygen engine oxygen pump full system combined sealing test device according to claim 2, characterized in that: The inner ring of the first bearing or the second bearing is mounted on the main shaft (8); the outer ring of the second bearing is mounted on the second housing (4), and the outer ring end face is pressed by a thrust nut (77); the outer ring of the first bearing is mounted on the bearing seat (13), and a bearing adjustment gasket (80) is mounted between the outer ring of the first bearing and the bearing seat (13). The preload force of the bearing is adjusted by replacing the thickness of different bearing adjustment gaskets (80), and finally the first bearing is locked by a front locking nut (15).

4. A hydrogen-oxygen engine oxygen pump full system combined sealing test device according to claim 2, characterized in that: The stationary ring assemblies to be tested are, from the front end to the rear end on the rotor assembly, a first low-temperature stationary ring assembly (71), a first normal-temperature stationary ring assembly (731), a second normal-temperature stationary ring assembly (732), a second low-temperature stationary ring assembly (741), and a third low-temperature stationary ring assembly (742).

5. A hydrogen-oxygen engine oxygen pump full system combined sealing test device according to claim 4, characterized in that: The installation process of the stationary ring assembly to be tested is as follows: Install the second bearing on the second housing and tighten it with a thrust nut (77), then install the sleeve IV (76) and the moving ring II (75) on the main shaft (8); The second low-temperature static ring assembly (741) is installed by: installing the rear end of the main shaft (8) through the inner ring of the second bearing, sleeve the second low-temperature static ring assembly (741) on the main shaft (8), and fix it on the second shell (4), and set a sealing aluminum gasket between the second low-temperature static ring assembly (741) and the second shell (4); the graphite ring in the second low-temperature static ring assembly faces the dynamic ring II (75) and contacts it, and the compression amount of the second low-temperature static ring assembly is adjusted by the length of the sleeve IV (76) and the thickness of the sealing aluminum gasket between the second low-temperature static ring assembly (741) and the second shell (4). The second normal temperature static ring assembly (732) is installed, and the installation method is as follows: the second normal temperature static ring assembly (732) is sleeved on the main shaft (8) and fixed on the second shell (4), a static ring gasket is arranged between the second normal temperature static ring assembly (732) and the second shell, and the dynamic ring III (79) is installed on the main shaft (8); the graphite ring of the second normal temperature static ring assembly (732) faces the dynamic ring III (79) and contacts it, and the compression amount of the second normal temperature static ring assembly (732) is adjusted by the thickness of the static ring gasket. The first normal temperature static ring assembly (731) is installed. The installation method is as follows: the first normal temperature static ring assembly (731) is sleeved on the main shaft (8) and fixed on the first shell (3). A static ring gasket is arranged between the first normal temperature static ring assembly (731) and the second shell. The graphite ring of the first normal temperature static ring assembly (731) faces the dynamic ring III (79) and contacts it. The first shell (3) and the second shell (4) are fastened by bolts. The compression amount of the first normal temperature static ring assembly (731) is adjusted by the thickness of the static ring gasket. The first low-temperature static ring assembly (71) is installed. The installation method is as follows: the first low-temperature static ring assembly (71) is sleeved on the main shaft (8) and fixed on the first shell (3), a sealing gasket is arranged between the first low-temperature static ring assembly (71) and the second shell, and the sleeve III (72) and the dynamic ring I (70) are installed on the main shaft (8), and the sleeve III (72) is located at the rear end of the dynamic ring I (70); the graphite ring of the first low-temperature static ring assembly (71) faces the dynamic ring I (70) and contacts it, and the compression amount of the first low-temperature static ring assembly (71) is adjusted by the length of the sleeve III (72) and the thickness of the sealing gasket (40). Install the sleeve II (12) on the main shaft (8); The bearing seat (13) is fixed on the first housing, the inner ring of the first bearing is sleeved on the front end of the main shaft (8), the outer ring of the first bearing is installed on the bearing seat (13), the bearing adjustment gasket (80) is installed between the outer ring of the first bearing and the bearing seat (13), the preload force of the bearing is adjusted by adjusting the thickness of the bearing adjustment gasket (80), and the first bearing is locked by the front locking nut (15); The second low-temperature static ring assembly (742) is installed, and the installation method is as follows: the sleeve V (78) and the dynamic ring IV (751) are installed on the main shaft (8), and the dynamic ring IV (751) is located at the rear end of the sleeve V (78); the second low-temperature static ring assembly (742) is sleeved on the main shaft (8) and fixed on the second shell (4), and a sealing gasket (39) is arranged between the second low-temperature static ring assembly (742) and the second shell (4); the graphite ring of the second low-temperature static ring assembly (742) faces the dynamic ring IV (751) and contacts it, and the compression amount of the second low-temperature static ring assembly (742) is adjusted by the length of the sleeve V (78) and the thickness of the sealing gasket (39).

6. A hydrogen-oxygen engine oxygen pump full system combined sealing test device according to claim 5, characterized in that: The method for adjusting the bearing preload is as follows: after the compression amount of each stationary ring assembly is adjusted and installed, all stationary ring assemblies are disassembled, and the movable ring I (70), sleeve III (72), movable ring III (79), movable ring II (75), movable ring IV (751), and sleeve IV (76) on the shaft system are kept unchanged, and the bearing preload is adjusted by the length of sleeve II (12) and the thickness of the bearing adjustment gasket (80). After the bearing preload is adjusted, all components are reassembled according to the assembly sequence.

7. A combined sealing test system for the oxygen pump of a hydrogen-oxygen engine, characterized in that: Including gas distribution system, medium recovery and discharge system, motor, gear box; The output shaft of the motor is connected to the gear box, the output end of the gear box is connected to the main shaft of the test device, the gas distribution system is connected to the medium supply system through a pipeline, and the leakage chamber of the test device is connected to the medium recovery and discharge system through a pipeline; After installation, there are 6 cavities formed between the static ring assembly, shell assembly and rotor assembly of the test device, which are, from front to back, the first low-temperature liquid nitrogen high-pressure chamber, the first normal-temperature mixed leakage chamber, the helium-sealed normal-temperature high-pressure chamber, the second normal-temperature mixed leakage chamber, the second low-temperature liquid nitrogen high-pressure chamber, and the low-temperature leakage chamber. Among them, the first low-temperature liquid nitrogen high-pressure chamber, the helium-sealed normal-temperature high-pressure chamber, and the second low-temperature liquid nitrogen high-pressure chamber are all sealed chambers.

8. A hydrogen-oxygen engine oxygen pump full system combined sealing test system according to claim 7, characterized in that: The liquid nitrogen sources of the first cryogenic liquid nitrogen high-pressure chamber and the second cryogenic liquid nitrogen high-pressure chamber are: high-pressure air is pressurized on the liquid nitrogen pressure vessel through the pressure reducing valve of the gas distribution system, and the liquid nitrogen is sequentially passed through the cryogenic filter by extrusion and then divided into two branches, each branch is provided with a cryogenic filter and a cryogenic mass flowmeter, and the measured mass flow rates are Q1 and Q2 respectively, and then enter the first cryogenic liquid nitrogen high-pressure chamber and the second cryogenic liquid nitrogen high-pressure chamber respectively through the medium supply system; The outlets of the first cryogenic liquid nitrogen high-pressure chamber and the second cryogenic liquid nitrogen high-pressure chamber are connected to a cryogenic mass flow meter, a cryogenic manual stop valve, and a cryogenic electric regulating valve in sequence. The mass flow rates after the two outlets are Q3 and Q4 respectively, and finally they are collected into the main pipeline and discharged into the medium recovery and discharge system; The source of helium in the helium-sealed normal temperature high pressure chamber is: high pressure helium is decompressed by the gas distribution system, then passes through a normal temperature filter, a pressure regulating valve, and a mass flow meter in sequence, the volume flow rate measured by the volume flow meter is Q5, and then enters the helium-sealed normal temperature high pressure chamber; The helium in the helium-sealed normal temperature and high pressure chamber leaks through the normal temperature static ring components on both sides and enters the first normal temperature mixed leakage chamber and the second normal temperature mixed leakage chamber respectively; The liquid nitrogen medium in the second low-temperature liquid nitrogen high-pressure chamber leaks into the second normal-temperature mixed leakage chamber through the dynamic ring II (75) and the second low-temperature static ring assembly I (741); the liquid nitrogen medium in the second low-temperature liquid nitrogen high-pressure chamber leaks into the low-temperature leakage chamber through the dynamic ring IV (751) and the third low-temperature static ring assembly (742); The liquid nitrogen medium in the first low-temperature liquid nitrogen high-pressure chamber leaks into the first normal-temperature mixed leakage chamber through the dynamic ring I (70) and the first low-temperature static ring assembly (71); The first normal-low temperature mixed leakage chamber, the second normal-low temperature mixed leakage chamber, and the low temperature leakage chamber are respectively connected to a vaporizer and a volume flow meter in sequence to measure the leakage of the three chambers, which are respectively recorded as Q6, Q7, and Q8; According to the above flow measurement results, the leakage of the third low-temperature static ring assembly is Q6, the leakage of the second low-temperature static ring assembly is Q2-Q4-Q6, the leakage of the first low-temperature static ring assembly (71) is Q1-Q3, the leakage of the first normal temperature static ring assembly (731) is Q7-(Q1-Q3), and the leakage of the second normal temperature static ring assembly (732) is Q8-(Q2-Q4-Q6), thereby obtaining the leakage of the five static ring assemblies assembled in the test device.

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