Disengagement test system and method for high-thrust engine oxidizer turbopump

Abstract

A disengagement test system and method for a high-thrust engine oxidizer turbopump, pertaining to the technical field of non-standard assembly processing equipment. The oxidizer turbopump employs a rotary disengagement seal. Before the oxidizer turbopump of a liquid rocket engine operates, a sealing friction pair is in close contact, and during operation, the sealing friction pair disengages under the action of medium pressure or centrifugal force, allowing the medium to flow. The test system comprises a test console, a nitrogen storage apparatus, a piping system, an automatic control system, and a high-precision displacement test apparatus. An operator, via the test console, drives a plant gas source to charge the nitrogen storage apparatus, and then controls stored gas to quickly inflate an inner cavity of the oxidizer turbopump, thereby performing both a seal disengagement test and an air-tightness test on an oxidizer turbopump product. The automatic control system transmits sealing pressure data acquired by sensors to control software, and plots a turbine-end seal disengagement pressure curve during the test process, thereby enabling automated testing and data acquisition for oxidizer turbopump seal disengagement.

Description

A large-thrust engine turbine oxygen pump disengagement test system and method

[0001] Cross-reference to Related Applications

[0002] The present application claims priority to the Chinese patent application No. 202510305807.4, filed on March 14, 2025, and entitled “A large-thrust engine turbine oxygen pump disengagement test system and method”, the content of which is incorporated herein by reference in its entirety. TECHNICAL FIELD

[0003] The present application relates to a large-thrust engine turbine oxygen pump disengagement test system and method, belonging to the technical field of non-standard assembly process equipment. BACKGROUND

[0004] At present, the sealing performance test of liquid rocket engine turbine pump adopts the traditional nitrogen cylinder connected with hand-operated disengagement air tightness test bench for test. During use, the operator manually rotates the valve to adjust the opening degree, cooperates with the pointer type pressure gauge, and controls the test process of turbine oxygen pump sealing disengagement. The whole process is completed by manual work of the assembly personnel, and the skill and experience requirements of the operator are higher. The turbine pump is the only high-speed rotating component in the rocket engine. As the “heart” of the rocket engine, the performance of the turbine pump directly affects the operation of the engine.

[0005] The mechanicalization and automation of the turbine oxygen pump sealing disengagement performance test method and equipment are closely related. For a long time, the turbine oxygen pump sealing disengagement performance test has always used the traditional air tightness test bench, and the operator is completely manual work. The speed of the operator opening the valve manually may affect the test data of the disengagement pressure of the turbine end sealing at the moment. If the valve is opened too slowly, the turbine end sealing will tend to be air tightness test, and the dynamic sealing cannot be opened instantly, but a slight leakage after gradually increasing the pressure. This is contrary to the sealing design characteristics and the product test process.

[0006] At the same time, due to the limitation of the capacity of the standard nitrogen cylinder and the pipe diameter, the operator uses the traditional nitrogen test bench to open the disengagement valve for disengagement test. The inlet air rate in the turbine oxygen pump cavity is restricted by the outlet pipe diameter of the nitrogen cylinder and the capacity of the nitrogen cylinder. The sealing disengagement test data are affected by many non-product factors, which leads to the authenticity of many test results being doubtful.

[0007] In summary, the deficiencies of the conventional sealing disconnection test system composed of a nitrogen cylinder and a test bench are as follows: the sealing disconnection test is completed by manual work of an assembly personnel, the skill and experience requirements of the operator are high, and the test data are greatly affected by human factors. Meanwhile, due to the capacity of the standard nitrogen cylinder and the pipe diameter limitation, when the turbine end sealing is about to reach the critical point of disconnection, the test bench gas inlet and the turbine end sealing disconnection amount may reach a dynamic balance, that is, the nitrogen filling rate in the pump cavity is the same as the turbine end sealing leakage amount, and the sealing characteristic of instantaneous disconnection cannot be achieved. Meanwhile, due to the measurement limitation of the pointer type pressure gauge, the operator may have a dispersion error in reading at the sealing disconnection moment, which affects the accuracy of the experimental result monitoring. SUMMARY

[0008] The technical problem solved by the present application is to overcome the deficiencies of the prior art, and to provide a large-thrust-engine turbine oxygen pump disconnection test system and method, which avoids the test uncertainty caused by manual operation, greatly simplifies the sealing test link of the turbine oxygen pump, and improves the assembly quality and efficiency of the turbine oxygen pump.

[0009] The technical solution of the present application is as follows: in a first aspect, a large-thrust-engine turbine oxygen pump disconnection test system comprises:

[0010] A test console comprises a pneumatic booster pump module, a pipeline system and control valves; the pneumatic booster pump module is used for pumping nitrogen source into a nitrogen storage device for pre-storage; the pipeline system is used for connecting the nitrogen storage device and a pump cavity of the turbine oxygen pump to be tested, forming various disconnection test channels, the disconnection test channels comprising a gas-tight test channel and a disconnection test channel; the control valves are located on the pipelines of the various disconnection test channels; the control valves comprise a gas-tight test pressure increasing rate adjusting gas-tight test pressure regulating valve, a disconnection test pressure and pressure increasing rate controlling disconnection test pressure regulating valve, and a pressure relief valve for controlling the safety pressure threshold of the test system;

[0011] A nitrogen storage device is used for storing the pumped nitrogen and storing the gas for testing;

[0012] A sensor is used for collecting the sealing pressure data of the turbine oxygen pump to be tested;

[0013] A displacement test device is used for monitoring the displacement amount of the sealing disconnection process of the turbine oxygen pump to be tested;

[0014] An automatic control system is used to control the actions of each disconnection test channel and monitor the pressure monitoring value of the turbine oxygen pump chamber. This includes: controlling the booster pump to drive the nitrogen source to pump nitrogen into the nitrogen storage device; controlling the pressure regulating valve of the airtight circuit to perform airtightness test and seal disconnection test on the turbine oxygen pump under test respectively; and plotting the seal disconnection curve of the turbine oxygen pump under test based on the sealing pressure data collected by the sensor and the displacement amount collected by the displacement testing device after the test, thereby realizing the automatic test and data acquisition and plotting of the seal disconnection of the turbine oxygen pump under test.

[0015] Furthermore, the airtightness test channel and the disconnection test channel are respectively the airtightness test pipeline diameter at 0.9MPa pressure and the disconnection test pipeline diameter at 10MPa pressure, and the pipelines of the two test channels are independent of each other.

[0016] Furthermore, the nitrogen storage device has a volume of at least 120L.

[0017] Furthermore, the piping system is kept clean and oil-free before manufacturing and assembly.

[0018] Furthermore, the pressure value of the pressure relief valve ensures the safety of the entire turbine oxygen pump under test; when the test is disconnected and high-pressure nitrogen is introduced but the seal cannot be disconnected normally due to its own problem, the pressure relief valve opens after the pressure threshold of the turbine oxygen pump chamber under test is reached, thus relieving the pressure of the entire test system.

[0019] Furthermore, the sensor is used to collect the return pressure at the sealing part of the pump chamber of the turbo oxygen pump under test, with a sampling frequency greater than 50 Hz and a pressure test accuracy of no more than 0.25% FS.

[0020] Furthermore, the displacement testing device is a laser displacement sensor, used to check the displacement during the seal detachment process of the turbine oxygen pump under test, with a measurement range of not less than 20 mm and an accuracy of not more than 0.05%FS.

[0021] Secondly, a method for testing the disengagement of a high-thrust engine turbine oxygen pump according to the aforementioned high-thrust engine turbine oxygen pump disengagement test system includes:

[0022] Before the test, the nitrogen storage device is filled with gas. Once the nitrogen storage device reaches the predetermined pressure, the filling of the nitrogen storage device is stopped under the control of the automatic control system.

[0023] Set the pressure value during the airtightness test of the turbine oxygen pump under test, start the test program, perform airtightness test on the turbine oxygen pump under test, and display the pressure change of the pump chamber of the turbine oxygen pump under test in real time on the test control console.

[0024] Set the pressure value during the test of the seal separation performance of the turbine oxygen pump under test: First, set the stable pressure value during the pressurization process of the turbine oxygen pump under test, and then set the peak pressure during the separation test on the test control console;

[0025] Start the turbine oxygen pump seal separation performance test program, conduct turbine end seal separation performance test on the turbine oxygen pump under test, use displacement testing device to detect displacement change value during seal separation process, monitor the value of the sealing cavity return table of the turbine oxygen pump under test in real time on the test control console and plot the curve.

[0026] Furthermore, the pressure values ​​during the test of the airtightness performance of the turbine oxygen pump under test are set to 0.3MPa, 0.6MPa, and 1.0MPa respectively. The pressure regulating valve in the airtightness control console is used to regulate the pressure, with a pressure regulation range of 0 to 2.0MPa and an accuracy of ±1%FS.

[0027] Furthermore, the turbine end seal disengagement performance test includes: first, a uniform and slow pre-pressurization process is performed, controlling the inflation pressure to approximately 0.9 MPa; then, the disengagement test path is set to instantaneous increase mode, and the instantaneous flow rate of the disengagement path charges the nitrogen stored in the nitrogen storage device into the turbine oxygen pump under test; during the inflation pressure stage of 1.5 to 2.5 MPa, the pressurization rate ΔPt is required to be no less than 1.0 MPa / 20 sec.

[0028] The advantages of this invention compared to the prior art are:

[0029] (1) The turbine oxygen pump disengagement test system of the present invention is an integrated airtightness and disengagement test system. The airtightness test circuit and the disengagement test circuit are independent of each other. They are independently controlled by two sets of hydraulic lines to realize the airtightness test of the turbine oxygen pump and the disengagement performance test of the turbine end seal. The airtightness test circuit contains four channels, which can realize the airtightness test in the range of 0 to 2.5 MPa; the disengagement test circuit contains three channels, which can realize the disengagement test in the range of 0 to 6 MPa and 0 to 10 MPa.

[0030] (2) The disconnection test system of this invention adopts automatic control using an industrial computer and software control system. It applies the action of electric regulating valves, electric proportional valves, electric pressure relief valves, and solenoid valves. This achieves the adjustment and control of the airtightness test pipeline and the disconnection test pipeline, thereby realizing the testing function. The test system features high automation, high integration, and high testing accuracy, avoiding the uncertainties caused by manual operation, significantly simplifying the turbine oxygen pump sealing test process, improving the assembly quality and efficiency of the turbine oxygen pump, and reducing the labor intensity of frontline personnel. Attached Figure Description

[0031] Various other advantages and benefits will become apparent to those skilled in the art upon reading the following detailed description of preferred embodiments. The accompanying drawings are for illustrative purposes only and are not intended to limit the invention. Furthermore, the same reference numerals denote the same parts throughout the drawings. In the drawings:

[0032] Figure 1 is a general diagram of the turbo oxygen pump disengagement test system;

[0033] Figure 2 is a diagram of the test system's airtightness, disconnection, and pressure monitoring interfaces;

[0034] Figure 3 is a schematic diagram of the industrial control computer, control panel and printing equipment of the test system;

[0035] Figure 4 is a schematic diagram of the nitrogen storage device and gas source pipeline of the test system;

[0036] Figure 5 is a structural diagram of the internal cylinders and housing of the nitrogen storage device.

[0037] Figure 6 is a schematic diagram of the laser displacement sensor connection;

[0038] Figure 7 is a connection diagram of the hydraulic pipeline system. Detailed Implementation

[0039] To better understand the above technical solutions, the technical solutions of the present invention will be described in detail below with reference to the accompanying drawings and specific embodiments. It should be understood that the embodiments of the present invention and the specific features in the embodiments are detailed descriptions of the technical solutions of the present invention, rather than limitations on the technical solutions of the present invention. In the absence of conflict, the embodiments of the present invention and the technical features in the embodiments can be combined with each other.

[0040] The following description, in conjunction with the accompanying drawings, provides a more detailed account of a high-thrust engine turbine oxygen pump disengagement test system and method provided by embodiments of the present invention. Specific implementation methods may include:

[0041] As shown in Figures 1 and 2, the turbine oxygen pump disengagement test system consists of a test control console 1, a nitrogen storage device 2, a piping system 3, an automatic control system 4, and a high-precision displacement testing device 5. The test control console 1 includes a booster pump, a stainless steel piping system, control valves, and console structural components. The nitrogen storage device 2 comprises a large-capacity nitrogen cylinder and a detachable mobile cylinder support structure. The piping system 3 includes disengagement piping, airtight piping, and a hose reel. The automatic control system 4 is built using an industrial control computer (IPC) and data acquisition and control boards, and connects to multiple channel sensors and control valves. The software platform is based on the LabVIEW software platform. The high-precision displacement testing device 5 consists of a laser displacement sensor.

[0042] As shown in Figure 3, the main structure of the test console 1 is a piano-style structure, externally constructed from welded steel profiles and plates, with an electrostatic powder coating finish. The console contains a pneumatic booster pump, a stainless steel piping system, and control valves. The pneumatic booster pump module pumps nitrogen from the plant into the nitrogen storage device 2 for pre-storage. The stainless steel piping system constructs the various disconnection test channels required for the test console, and control valves are connected to the pipelines of each independent test channel. A pressure regulating valve is used to adjust the pressure increase and rate of increase during the airtightness test, while a pressure regulating valve is used for the other disconnection test to control the pressure and boosting rate.

[0043] As shown in Figures 4 and 5, the nitrogen storage device 2 comprises a large-capacity nitrogen storage cylinder and a detachable mobile storage cylinder support structure. The nitrogen storage cylinder stores nitrogen pumped in from the storage facility via a pneumatic booster pump, which is used as a gas reserve for subsequent experiments. The detachable mobile storage cylinder support structure is externally welded from steel plates, and internally equipped with trusses for installing and securing the nitrogen cylinder.

[0044] As shown in Figure 7, the piping system 3 is used for the piping connection between the test bench and the test product.

[0045] As shown in Figure 6, the high-precision displacement testing device 5 is composed of a laser displacement sensor, which has the capability of high-precision displacement monitoring within a certain distance range.

[0046] The automatic control system 4 is built using an industrial control computer (IPC) and data acquisition and control boards, and is programmed based on the LabVIEW software platform. It is used to control the actions of each test channel and provide feedback on the pressure monitoring values. The operator uses the control software to drive the plant's air supply into the nitrogen cylinder, and controls the pipeline booster pump, pressure regulating valve, and pressure relief valve through the automatic control software to perform airtightness and seal detachment tests on the turbopump product. After the test, the automatic control system 4 transmits the sealing pressure data collected by the sensors back to the control software, automatically plotting the turbine end seal detachment curve during the test, ultimately realizing the automatic testing and data acquisition and plotting of the turbo oxygen pump seal detachment.

[0047] The test system itself has gas storage capacity. The nitrogen source or nitrogen group in the plant is injected into the nitrogen storage device 2 through the test control console 1. The volume of the nitrogen storage device is 120L.

[0048] Piping system 3 must be kept highly clean and oil-free before manufacturing and assembly.

[0049] The safety of the entire turbine oxygen pump product is ensured by setting the pressure value of the pressure relief valve on the test control console 1. When high-pressure nitrogen is introduced during the disconnection test and the seal cannot disconnect normally due to its own problem, the pressure relief valve opens to release the pressure of the entire test system after the pressure threshold in the turbine oxygen pump chamber is reached.

[0050] The sensor is used to collect the return pressure at the sealing part of the turbo oxygen pump chamber. The sampling frequency is greater than 50 Hz, and the pressure test accuracy is ≤0.25%FS.

[0051] The displacement testing device 5 is a laser displacement sensor used to check the displacement during the process of the turbine oxygen pump seal detachment. The measurement range is ≥20mm and the accuracy is ≤0.05%FS.

[0052] The turbine oxygen pump disconnection test system includes the following steps:

[0053] (1) Before the test, connect the drive gas supply pipeline and connect the nitrogen supply in the plant to the test bench. Connect the outlet of the test bench to the test inlet of the turbine pump chamber. The operator sets up the operation control software and uses the test system to fill the nitrogen cylinder. After the nitrogen cylinder reaches the predetermined pressure, the control system stops filling the nitrogen cylinder.

[0054] (2) The operator sets the pressure value during the airtightness performance test of the turbo oxygen pump using the operating software. Test pressures of 0.3 MPa, 0.6 MPa, and 1.0 MPa are selected respectively. The test program is started, and the pressure regulating valve controls the gas cylinder to pressurize the pump chamber. After reaching the predetermined pressure, the pressure regulating valve closes, and the entire pipeline outlet connected to the turbo oxygen pump is disconnected from the front-end test bench. The turbo oxygen pump then undergoes an airtightness test. The pressure sensor at the pipeline outlet provides real-time feedback on the pressure changes within the pump chamber.

[0055] (3) The operator sets the pressure value during the turbine oxygen pump seal disconnection performance test using the operating software. The initial pressure setting during the test bench pressurization process is 0.9 MPa. Then, the control system issues a disconnection test command, instructing the pressure regulating valve to open to ≥90%. Nitrogen from the gas storage device is rapidly injected into the test product cavity through a pneumatic regulating valve. When the cavity medium pressure increases to approximately 2.5 MPa, the turbine oxygen pump seal disconnection structure should quickly disconnect. A high-precision displacement testing device 5 detects the displacement change during the seal disconnection process. A pressure sensor is connected via a pipeline near the turbine oxygen pump disconnection seal cavity to collect pressure data at the disconnection seal. The pressure data of the turbine pump seal cavity is detected in real time and stored in the computer. The software control system plots the disconnection seal pressure change curve.

[0056] As shown in Figure 1, the high-thrust engine turbine oxygen pump disengagement test system of this invention, provided in the embodiment of the present invention, consists of a test console 11, a nitrogen storage device 22, a piping system 33, an automatic control system 44, and a high-precision displacement testing device 55. The test console 11 includes an operating table structure, an airtight test pipeline interface 1-1, a pressure gauge return pipeline connector 1-2, a disengagement test pipeline connector 1-3, an industrial control computer 1-4, a data printer 1-5, and a control panel 1-6. The nitrogen storage device 22 includes a 120L gas cylinder 2-1 and a gas cylinder housing 2-2. The piping system 33 includes a compressed air management system 3-1, a nitrogen source pipeline 3-2, a pressure relief pipeline 3-3, a booster pump 3-4, a disengagement pressure regulating valve 3-5, and an airtightness pressure regulating valve 3-6. The automatic control system 44, developed using LabVIEW software, is used to control the actions of each test channel and provide feedback on each pressure monitoring value. It includes a human-machine interface panel, a control cabinet, and a manual operating handle. The high-precision displacement testing device 55 consists of a laser displacement sensor.

[0057] Example

[0058] When the test object is a turbine oxygen pump, the specific assembly steps are as follows:

[0059] (1) Before the test, the operator connects the compressed air line 3-1 and the nitrogen source line 3-2 between the nitrogen source in the plant and the test bench. Through the operating interface of the automatic control system 44, the target gas source pressure of the nitrogen storage device 2 is set, and then the booster pump 3-4 operates to pressurize the nitrogen storage device. Once the predetermined pressure is reached in the nitrogen cylinder, the control system stops pressurizing the nitrogen cylinder. Connect the airtightness test connector 1-1 at the outlet of the test bench to the test inlet of the turbine pump chamber.

[0060] (2) The operator sets the pressure value during the airtightness performance test of the turbo oxygen pump through the airtightness test interface of the automatic control system 44. Test pressures of 0.3MPa, 0.6MPa, and 1.0MPa are selected respectively, and the test program is started. The industrial control computer 1-4 sends instructions to the pressure regulating valve 3-6 of the corresponding passage in the airtight pipeline to control the air source pressure to fill the turbo oxygen pump chamber. Pressurization stops when the pressure gauge connector 1-2 displays that the pressure in the turbo oxygen pump chamber has reached the set pressure. The operator then performs an airtightness test, and the pressure change in the chamber is displayed in real time on the control panel 1-6. The stored test pressure data after the test is completed can be printed using the data printer 1-5.

[0061] (3) The operator connects the pressure return connector 1-2 to the corresponding measuring point near the desealment of the turbine oxygen pump, and sets the pressure stabilization and charging value for the first stage of the desealment test through the desealment test interface of the automatic control system 44. The test program is started, and the industrial control computer 1-4 sends a command to the pressure regulating valve 3-5 in the corresponding passage of the airtight pipeline to slowly pressurize to the set pressure. Then, the industrial control computer 1-4 controls the opening of the pressure regulating valve 3-5 to form an instantaneous large-capacity pressurization process. The turbine end seal desealment performance test is performed on the turbine oxygen pump. The high-precision displacement testing device 55 detects the displacement change value during the seal desealment process. The operating console software interface 4 detects the pressure return value of the turbine pump sealing cavity in real time and plots the curve. The stored desealment pressure data can be printed through the data printer 1-5.

[0062] Obviously, those skilled in the art can make various modifications and variations to this invention without departing from its spirit and scope. Therefore, if these modifications and variations fall within the scope of the claims of this invention and their equivalents, this invention also intends to include these modifications and variations.

[0063] The contents not described in detail in this specification are common knowledge to those skilled in the art.

Claims

1. A test system for disconnecting a turbine oxygen pump from a high-thrust engine, characterized in that, include: The test control console (1) includes a pneumatic booster pump module, a pipeline system (3), and control valves; the pneumatic booster pump module is used to pump nitrogen source into nitrogen storage device (2) for pre-storage; the pipeline system (3) is used to connect nitrogen storage device (2) and the pump chamber of the turbine oxygen pump to be tested to form various disconnection test channels, including airtight disconnection test channel and disconnection path disconnection test channel; The control valves are located on the pipelines of each disconnection test channel; the control valves include: an airtight path pressure regulating valve for adjusting the pressure increase rate of the airtight test, a disconnection path pressure regulating valve for controlling the pressure and pressure increase rate of the disconnection test, and a pressure relief valve for controlling the safety pressure threshold of the test system. Nitrogen storage device (2) is used to store the pumped nitrogen gas for gas reserves for experiments; Sensors are used to collect sealing pressure data of the turbo oxygen pump under test; Displacement testing device (5) is used to monitor the displacement during the seal detachment process of the turbine oxygen pump under test; The automatic control system (4) is used to control the action of each disconnection test channel and monitor the pressure monitoring value of the turbine oxygen pump chamber, including: controlling the booster pump to drive the nitrogen source to pump into the nitrogen storage device (2); controlling the pressure regulating valve of the airtight path, and conducting airtight test and seal disconnection test on the turbine oxygen pump under test respectively; after the test, according to the sealing pressure data collected by the sensor and the displacement collected by the displacement test device (5), the seal disconnection curve of the turbine oxygen pump under test during the test process is plotted, so as to realize the automatic test and data acquisition plotting of the seal disconnection of the turbine oxygen pump under test.

2. The high-thrust engine turbine oxygen pump disengagement test system according to claim 1, characterized in that, The airtightness test channel and the disconnection test channel are respectively the diameter of the airtightness test pipeline under 0.9MPa pressure and the diameter of the disconnection test pipeline under 10MPa pressure. The pipelines of the two test channels are independent of each other.

3. The high-thrust engine turbine oxygen pump disengagement test system according to claim 1, characterized in that, The nitrogen storage device (2) has a volume of at least 120L.

4. The high-thrust engine turbine oxygen pump disengagement test system according to claim 1, characterized in that, The piping system (3) is kept clean and oil-free before manufacturing and assembly.

5. The high-thrust engine turbine oxygen pump disengagement test system according to claim 1, characterized in that, The pressure value of the pressure relief valve ensures the safety of the entire turbine oxygen pump under test; when the test is disconnected and high-pressure nitrogen is introduced but the seal cannot be disconnected normally due to its own problem, the pressure relief valve opens after the pressure threshold of the turbine oxygen pump chamber under test is reached, thus relieving the pressure of the entire test system.

6. The high-thrust engine turbine oxygen pump disengagement test system according to claim 1, characterized in that, The sensor is used to collect the pressure at the sealing part of the pump chamber of the turbo oxygen pump under test. The sampling frequency is greater than 50 Hz, and the pressure test accuracy is not greater than 0.25% FS.

7. The high-thrust engine turbine oxygen pump disengagement test system according to claim 1, characterized in that, The displacement testing device (5) is a laser displacement sensor, used to check the displacement during the process of the turbine oxygen pump being tested being unsealed. The measurement range is not less than 20 mm and the accuracy is not greater than 0.05%FS.

8. A method for testing the disengagement of a high-thrust engine turbine oxygen pump, implemented using a high-thrust engine turbine oxygen pump disengagement test system according to any one of claims 1 to 7, characterized in that, include: Before the test, the nitrogen storage device (2) is filled with gas. After the nitrogen storage device (2) reaches the predetermined pressure, the filling of the nitrogen storage device (2) is stopped under the control of the automatic control system (4). Set the pressure value during the air tightness test of the turbine oxygen pump under test, start the test program, perform air tightness test on the turbine oxygen pump under test, and display the pressure change of the pump chamber of the turbine oxygen pump under test in real time on the test control console (1). Set the pressure value during the test of the seal separation performance of the turbine oxygen pump under test: First, set the stable pressure value during the pressurization process of the turbine oxygen pump under test, and then set the pressure peak value during the separation test on the test control console (1); Start the turbine oxygen pump seal separation performance test program, and conduct a turbine end seal separation performance test on the turbine oxygen pump under test. The displacement test device (5) detects the displacement change value during the seal separation process. The value of the seal cavity return table of the turbine oxygen pump under test is monitored in real time on the test control console (1) and the curve is plotted.

9. The test method for disconnecting the turbine oxygen pump of a high-thrust engine according to claim 8, characterized in that, The pressure values ​​during the test of the air tightness performance of the turbine oxygen pump to be tested are set to 0.3MPa, 0.6MPa and 1.0MPa respectively. The air tightness test of the turbine oxygen pump to be tested is carried out by the pressure regulating valve in the air tightness control console (1). The pressure regulation range is 0~2.0MPa and the accuracy meets ±1%FS.

10. The test method for disconnecting the turbine oxygen pump of a high-thrust engine according to claim 8, characterized in that, The turbine end seal disconnection performance test includes: first, a uniform and slow pre-pressurization process is carried out, controlling the inflation pressure to about 0.9 MPa, and then the disconnection test path is set to instantaneous increase mode, and the instantaneous flow rate of the disconnection path fills the nitrogen stored in the nitrogen storage device (2) into the turbine oxygen pump under test; during the inflation pressure stage of 1.5 to 2.5 MPa, the pressurization rate ΔPt is required to be not less than 1.0 MPa / 20 sec.

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