Turbine pump isolation cavity heat exchange coefficient testing device and thermal state analysis method

Abstract

The invention relates to a rocket engine accessory, in particular to a turbopump isolation cavity heat exchange coefficient testing device and a thermal state analysis method, and aims to solve the problem that the thermal state of an internal structure of an existing turbopump isolation cavity is difficult to obtain through a test method. The device comprises a fuel cavity simulation piece, an isolation cavity simulation piece and an oxidant cavity simulation piece which are connected in sequence, the fuel cavity simulation part is a first annular cavity, the oxidant cavity simulation part is a third annular cavity, the isolation cavity simulation part is a circular truncated cone of which the large end is connected with one end of a second annular cavity, the small end of the circular truncated cone is connected with one end of the first annular cavity, and the other end of the second annular cavity is connected with one end of the third annular cavity; a first annular plate is arranged at the other end of the first annular cavity, and a third annular plate is arranged at the other end of the third annular cavity; isolation circular ring plates are arranged between the first circular ring cavity and the circular truncated cone and between the second circular ring cavity and the third circular ring cavity.

Description

Technical Field

[0001] The invention relates to a rocket engine accessory, in particular to a turbine pump isolation cavity heat exchange coefficient testing device and a thermal state analysis method. Background Art

[0002] The starting principle of a pump-type liquid rocket engine is to use a turbopump to transport the propellant in the tank to the thrust chamber through a pipeline to achieve starting. A turbopump is a combination of a turbine and a propellant pump. The oxidizer pump and the fuel pump are driven by a turbine, and the turbine is coaxial with the pump or driven by gears. In a liquid oxygen-kerosene engine, the working fluid of the oxidizer pump is liquid oxygen, which is a cryogenic propellant; the working fluid of the fuel pump is kerosene, which is a normal temperature propellant. There is an isolation chamber between the oxidizer pump and the fuel pump. The isolation chamber has two functions: one is to separate the normal temperature fuel pump from the low temperature oxidizer pump, and the other is that there is a small amount of propellant leakage in the seals of the turbopump. After the isolation chamber exists, a purge gas source can be used to purge it, thereby avoiding the adverse effects of the accumulation of the two propellants on the pump performance.

[0003] The heat transfer coefficient in the isolation cavity is an important boundary condition for analyzing the heat transfer state of the isolation cavity of the turbopump. Due to the complex structure of the turbopump, there are many parts and materials involved, and the boundary conditions are complex. Considering the problems of rotating parts and high pressure in the inner cavity of the turbopump, it is difficult to obtain the internal structure thermal state of the bearing cavity through experimental methods. The internal structure thermal state can be obtained through simulation analysis. Based on the structural limitations of the turbopump, the isolation cavity is usually a circular ring structure, and the purge gas source is usually nitrogen. There are also cases where other gases such as helium are used for purge. The purge gas enters from the openings on the circumferential surface of the isolation cavity and flows out from the openings at a certain angle. After the purge gas enters the isolation cavity, the streamlines in the cavity are relatively messy, and it is difficult to obtain the boundary conditions that meet the actual situation through theoretical estimation methods. During the engine test, the analysis of the purge process of the isolation cavity is related to the capacity of the nitrogen bottle carried by the engine when it is actually in service. Accurately estimating the purge state and the required purge gas volume plays an important role in streamlining the structure of the rocket engine and improving the thrust-to-weight ratio. Summary of the invention

[0004] The purpose of the present invention is to solve the problem that it is difficult to obtain the thermal state of the internal structure of the existing turbine pump isolation chamber through experimental methods, and to provide a turbine pump isolation chamber heat transfer coefficient testing device and a thermal state analysis method.

[0005] To achieve the above purpose, the technical solution provided by the present invention is:

[0006] A heat transfer coefficient test device for a turbine pump isolation chamber, which is special in that:

[0007] It includes a fuel cavity simulation part, an isolation cavity simulation part and an oxidant cavity simulation part which are coaxially connected in sequence;

[0008] The fuel cavity simulation piece is a first annular cavity, and the oxidant cavity simulation piece is a third annular cavity; the isolation cavity simulation piece includes a hollow truncated cone and a second annular cavity, one end of the truncated cone is connected to one end of the second annular cavity, the other end of the truncated cone is connected to one end of the first annular cavity, and the other end of the second annular cavity is connected to one end of the third annular cavity; a first annular plate is provided at the other end of the first annular cavity, and a third annular plate is provided at the other end of the third annular cavity; an isolation annular plate is provided between the first annular cavity and the truncated cone, and between the second annular cavity and the third annular cavity;

[0009] The first annular plate is provided with a fuel inlet pipe and a fuel outlet pipe; the third annular plate is provided with an oxidant inlet pipe and an oxidant outlet pipe;

[0010] A plurality of joints are arranged on the side walls of the second annular cavity and / or the truncated cone, and the total number of the joints is at least three, wherein at least two joints are respectively used for simulating the inflow and outflow of the blowing gas during blowing, and at least one joint is used for monitoring the internal temperature and pressure of the isolation cavity simulation component.

[0011] Furthermore, the fuel inlet pipe and the oxidant inlet pipe are both provided with a temperature sensor and a pressure sensor; the fuel outlet pipe and the oxidant outlet pipe are both provided with a temperature sensor.

[0012] Furthermore, the number of the joints is eight, of which four joints are evenly distributed on the side wall of the cone, and the other four joints are evenly distributed on the side wall of the second annular cavity; the joints used for simulating the inflow and outflow of the blowing gas during blowing are pipe joints, and the joints used for measuring temperature and pressure are aviation plugs; the temperature sensor is a thermocouple.

[0013] Furthermore, the second annular cavity and the third annular cavity are connected by a connecting flange, and a sealing ring is arranged between the two connecting flanges; the inner diameters of the first annular plate, the third annular plate, the isolation annular plate, the first annular cavity, the second annular cavity, the third annular cavity and the truncated cone are equal.

[0014] Furthermore, the outer walls of the oxidant inlet pipe, the oxidant outlet pipe and the oxidant chamber simulation component are all covered with thermal insulation materials, and the thermal insulation materials include one or more of high-silica glass fiber cloth, Kevlar cloth and silicone rubber cloth.

[0015] Furthermore, the fuel inlet pipe and the fuel outlet pipe are symmetrically arranged about the axis of the first circular ring plate, and the oxidant inlet pipe and the oxidant outlet pipe are symmetrically arranged about the axis of the third circular ring plate.

[0016] At the same time, the present invention also provides a method for analyzing the thermal state of a turbine pump isolation cavity, which uses the above-mentioned turbine pump isolation cavity heat transfer coefficient testing device, and its special feature is that it includes the following steps:

[0017] Step 1, installing the turbine pump isolation chamber heat transfer coefficient test device to a preset position;

[0018] Step 2, start filling the oxidant into the oxidant chamber simulation part from the oxidant inlet pipe. When the oxidant chamber simulation part is filled, the oxidant automatically flows out from the oxidant outlet pipe. Meanwhile, monitor the temperature T1 and pressure P1 of the oxidant inlet pipe and the temperature T2 of the oxidant outlet pipe until T2 reaches a preset value. Maintain this state for t1 time.

[0019] Step 3, start filling the fuel agent into the fuel cavity simulation part from the fuel inlet pipe. When the fuel cavity simulation part is filled, the fuel agent automatically flows out from the fuel outlet pipe. Meanwhile, monitor the temperature T3 and pressure P2 of the fuel inlet pipe and the temperature T4 of the fuel outlet pipe until T4 reaches the preset value. Keep this state for t2 time.

[0020] Step 4, start to pass the purge gas from at least one joint to the isolation cavity simulation part. When the isolation cavity simulation part is filled, the purge gas automatically flows out from another joint. Meanwhile, monitor the temperature T5 and pressure P3 of the joint through which the purge gas is passed, as well as the outer wall temperature T6, inner wall temperature T7, internal space temperature T8, and internal space pressure P4 of the isolation cavity simulation part until T6, T7, T8, and P4 all reach a preset steady-state range. Maintain this state for t3 time, and then record the values ​​of T6, T7, T8, and P4 at this time.

[0021] Step 5, changing the temperature and pressure of the purge gas, and then returning to step 4, obtaining and recording the values ​​of T6, T7, T8 and P4 in another preset steady-state range, until the corresponding values ​​of T5 and P3 and T6, T7, T8 and P4 in N preset steady-state ranges are obtained, and after sorting, a flow-heat transfer coefficient table at different temperatures on the inner surface of the isolation cavity is obtained, that is, a qh table;

[0022] Step 6: Establish a heat transfer model of an actual turbo pump, wherein the heat transfer model includes an oxidant chamber, an isolation chamber, and a fuel chamber, and set a plurality of temperature check points on the heat transfer model, and set an actual allowable temperature range for each temperature check point;

[0023] Step 7: Set the boundary conditions of the heat transfer model according to the qh table obtained in step 5;

[0024] Step 8: According to the boundary conditions of the heat transfer model, if the precooling and discharge conditions of the turbopump do not change with time, the thermal state of the turbopump heat transfer model is obtained by a steady-state analysis method; if at least one of the precooling and discharge conditions of the turbopump changes with time, the thermal state of the turbopump heat transfer model is obtained by a transient analysis method;

[0025] Step 9: According to the thermal state of the turbine pump heat transfer model, determine whether the temperature of each temperature check point is within the actual allowable temperature range. If the temperature of each temperature check point is within its corresponding actual allowable temperature range, the boundary conditions of the heat transfer model meet the requirements and the thermal state analysis of the turbine pump isolation cavity is completed; if there is at least one temperature check point whose temperature is not within its corresponding actual allowable temperature range, return to step 7 to modify the boundary conditions of the heat transfer model.

[0026] Furthermore, step 7 is specifically as follows:

[0027] Step 7.1, setting the inner surface of the oxidant chamber to a convection heat transfer condition or a constant temperature condition according to the flow rate of the oxidant during the precooling process, and setting the outer surface of the oxidant chamber to an adiabatic condition;

[0028] Step 7.2, the inner surface of the fuel cavity is set to a convection heat transfer condition or a constant temperature condition according to the fuel flow rate, the heat transfer coefficient h4 of the inner surface of the fuel cavity is calculated according to the DB formula, and the heat transfer temperature Th4 of the inner surface of the fuel cavity is the fuel temperature; the outer surface of the fuel cavity is set to a natural convection heat transfer condition, the heat transfer coefficient h1 of the outer surface of the fuel cavity is estimated according to the natural convection heat transfer formula, and the heat transfer temperature Th1 of the outer surface of the fuel cavity is the ambient temperature during the test;

[0029] Step 7.3, set the inner surface of the isolation cavity to the convection heat transfer condition, the heat transfer coefficient h2 of the inner surface of the isolation cavity is set according to the qh table obtained in step 5, and the heat transfer temperature Th2 of the inner surface of the isolation cavity is set according to the temperature of the blow-off gas in the blow-off cavity; the outer surface of the isolation cavity is set to the natural convection heat transfer condition, the heat transfer coefficient h3 of the outer surface of the isolation cavity is estimated according to the natural convection heat transfer formula, and the heat transfer temperature Th3 of the outer surface of the isolation cavity is the ambient temperature during the test.

[0030] Furthermore, if the temperature check point that does not meet the conditions is located in the isolation cavity, a set of qh values ​​that are different from the selected qh values ​​are reselected in the qh table; if the temperature check point that does not meet the conditions is located in the fuel cavity, the heat transfer coefficient h4 of the inner surface of the fuel cavity and the heat transfer temperature Th4 of the inner surface of the fuel cavity are adjusted.

[0031] Compared with the prior art, the present invention has the following beneficial effects:

[0032] 1. A turbine pump isolation chamber heat transfer coefficient test device provided by the present invention includes a fuel chamber simulation part, an isolation chamber simulation part and an oxidant chamber simulation part, which can test the heat transfer coefficient more conveniently and simulate the actual working condition of the turbine pump isolation chamber, providing a basis for the thermal state analysis of the turbine pump isolation chamber;

[0033] 2. The present invention provides a method for analyzing the thermal state of a turbine pump isolation chamber. The heat transfer coefficient of the isolation chamber can be obtained by calculation, and the temperature data of each important point in the turbine pump, that is, the thermal state, can be further obtained. This can more accurately evaluate the state of the turbine pump's blowing process and determine whether the temperature of the turbine pump bearings and seals is within the allowable temperature range of the material. If there is a starting risk for the engine, this method can be used to predict the thermal state of the improvement plan, optimize the test system process, and ensure normal starting of the engine turbine pump. BRIEF DESCRIPTION OF THE DRAWINGS

[0034] Figure 1 It is a structural schematic diagram of an embodiment of a device for testing the heat transfer coefficient of a turbine pump isolation chamber according to the present invention;

[0035] Figure 2 A cross-sectional view of an embodiment of a device for testing heat transfer coefficient of a turbine pump isolation chamber according to the present invention;

[0036] Figure 3 for Figure 2 A magnified image of point A;

[0037] Description of reference numerals:

[0038] 1-fuel inlet pipe, 2-fuel cavity simulation, 3-joint, 4-isolation cavity simulation, 5-sealing ring, 6-connecting flange, 8-oxidizer cavity simulation, 9-oxidizer inlet pipe, 10-fuel outlet pipe, 11-oxidizer outlet pipe. DETAILED DESCRIPTION

[0039] The present invention will be further described below in conjunction with the accompanying drawings and specific embodiments.

[0040] A test device for the heat transfer coefficient of the turbine pump isolation chamber, see Figure 1 to Figure 3 ; including a fuel chamber simulation member 2, an isolation chamber simulation member 4 and an oxidant chamber simulation member 8 which are coaxially connected in sequence;

[0041] The fuel cavity simulation part 2 is a first annular cavity, and the oxidant cavity simulation part 8 is a third annular cavity; the isolation cavity simulation part 4 includes a hollow truncated cone and a second annular cavity, the large end of the truncated cone is connected to one end of the second annular cavity, the small end of the truncated cone is connected to one end of the first annular cavity, and the other end of the second annular cavity is connected to one end of the third annular cavity; a first annular plate is provided at the other end of the first annular cavity, and a third annular plate is provided at the other end of the third annular cavity; isolation annular plates are provided between the first annular cavity and the truncated cone, and between the second annular cavity and the third annular cavity; the first annular plate, the third annular plate The inner diameters of the isolation annular plate, the first annular cavity, the second annular cavity, the third annular cavity and the cone are equal; the first annular plate is provided with a fuel inlet pipe 1 and a fuel outlet pipe 10; the third annular plate is provided with an oxidant inlet pipe 9 and an oxidant outlet pipe 10; four joints 3 are evenly distributed on the side walls of the second annular cavity and the cone, four of which are arranged on the side walls of the cone, and four joints 5 are arranged on the side walls of the second annular cavity. The joints 3 used for introducing nitrogen and flowing nitrogen out during simulation of blowing are pipe joints, and the joints 3 used for measuring temperature and pressure data information are aviation plugs.

[0042] In order to facilitate the assembly and disassembly of the isolation cavity simulation part 4, the second annular cavity and the third annular cavity are connected by a connecting flange 6; at the same time, in order to enhance the sealing performance, a sealing ring 5 is arranged between the two connecting flanges 6.

[0043] In this embodiment, temperature sensors and pressure sensors are provided in the fuel inlet pipe 1 and the oxidant inlet pipe 9, and temperature sensors are provided in the fuel outlet pipe 10 and the oxidant outlet pipe 10. The temperature sensors are all thermocouples.

[0044] The fuel inlet pipe 1 and the fuel outlet pipe 10 are arranged radially symmetrically about the first circular ring plate, and the oxidant inlet pipe 9 and the oxidant outlet pipe 10 are arranged radially symmetrically about the third circular ring plate. Such an arrangement can facilitate the entry and exit of the oxidant and the fuel. Since the oxidant is generally liquid oxygen, which is a cryogenic medium, it is generally necessary to coat it during the test to reduce heat leakage. Therefore, the outer walls of the oxidant inlet pipe 9, the oxidant outlet pipe 10 and the oxidant chamber simulation part 8 are all coated with a heat insulating material, and the heat insulating material includes one or more of high-silica glass fiber cloth, Kevlar cloth and silicone rubber cloth.

[0045] The purpose of calculating the thermal state of the isolation chamber is to confirm the precooling and blowing of the turbo pump before the test run or launch of the liquid rocket engine to ensure that the low temperature of liquid oxygen will not be transferred to the kerosene pump chamber (i.e., the fuel chamber) and cause low temperature damage to the kerosene pump chamber bearings, sealing rings and other sealing parts. In this regard, this embodiment also provides a method for analyzing the thermal state of the turbo pump isolation chamber, using the above-mentioned turbo pump isolation chamber heat transfer coefficient test device, including the following steps:

[0046] Step 1, installing the turbine pump isolation chamber heat transfer coefficient test device to a preset position;

[0047] Step 2, start filling the oxidant into the oxidant chamber simulation part 8 from the oxidant inlet pipe 9. When the oxidant chamber simulation part 8 is filled, the oxidant automatically flows out from the oxidant outlet pipe 10. Meanwhile, monitor the temperature T1 and pressure P1 of the oxidant inlet pipe 9 and the temperature T2 of the oxidant outlet pipe 10 until reaching a preset value (e.g., T2 < -153°C), and maintain this state for t1 ≥ 3 min.

[0048] Step 3, start filling the fuel agent into the fuel cavity simulation part 2 from the fuel inlet pipe 1. When the fuel cavity simulation part 2 is filled, the fuel agent automatically flows out from the fuel outlet pipe 10. Meanwhile, monitor the temperature T3 and pressure P2 of the fuel inlet pipe 1 and the temperature T4 of the fuel outlet pipe 10 until T4 reaches a preset value. Maintain this state for t2≥3min.

[0049] Step 4, start to pass the purge gas from the two joints 3 to the isolation cavity simulation part 4. When the isolation cavity simulation part 4 is filled, the purge gas automatically flows out from the other joint 3. At the same time, monitor the temperature T5 and pressure P3 of the joint 3 through which the purge gas is passed, as well as the outer wall temperature T6, inner wall temperature T7, internal space temperature T8, and internal space pressure P4 of the isolation cavity simulation part 4, until T6, T7, T8, and P4 all reach the preset steady-state range, maintain this state t3 ≥ 3min, and then record the values ​​of T6, T7, T8, and P4 at this time;

[0050] Step 5, changing the temperature and pressure of the purge gas, and then returning to step 4, obtaining and recording the values ​​of T6, T7, T8 and P4 in another preset steady-state range, until the corresponding values ​​of T5 and P3 and T6, T7, T8 and P4 in N preset steady-state ranges are obtained, and after sorting, a flow-heat transfer coefficient table at different temperatures on the inner surface of the isolation cavity is obtained, that is, a qh table;

[0051] Step 6. Use TMG, ANSYS THERMAL or other heat transfer software to establish a heat transfer model of the actual turbo pump. The heat transfer model includes an oxidizer chamber, an isolation chamber, and a fuel chamber. Set several temperature check points on the heat transfer model, and set an actual allowable temperature range for each temperature check point. In the heat transfer software, it is necessary to set the corresponding material properties and contact relationship properties, and set the kerosene pump chamber bearings, seals, and other seals or other key parts as the main temperature check points.

[0052] Step 7: Set the boundary conditions of the heat transfer model according to the qh table obtained in step 5;

[0053] Step 7.1, setting the inner surface of the oxidant chamber to a convection heat transfer condition or a constant temperature condition according to the flow rate of the oxidant during the precooling process, and setting the outer surface of the oxidant chamber to an adiabatic condition;

[0054] Step 7.2, the inner surface of the fuel cavity is set to a convection heat transfer condition or a constant temperature condition according to the fuel flow rate, the heat transfer coefficient h4 of the inner surface of the fuel cavity is calculated according to the DB formula, and the heat transfer temperature Th4 of the inner surface of the fuel cavity is the fuel temperature; the outer surface of the fuel cavity is set to a natural convection heat transfer condition, the heat transfer coefficient h1 of the outer surface of the fuel cavity is estimated according to the natural convection heat transfer formula, and the heat transfer temperature Th1 of the outer surface of the fuel cavity is the ambient temperature during the test;

[0055] Step 7.3, set the inner surface of the isolation cavity to the convection heat transfer condition, the heat transfer coefficient h2 of the inner surface of the isolation cavity is set according to the qh table obtained in step 5, and the heat transfer temperature Th2 of the inner surface of the isolation cavity is set according to the temperature of the blow-off gas in the blow-off cavity; set the outer surface of the isolation cavity to the natural convection heat transfer condition, the heat transfer coefficient h3 of the outer surface of the isolation cavity is estimated according to the natural convection heat transfer formula, and the heat transfer temperature Th3 of the outer surface of the isolation cavity is the ambient temperature during the test;

[0056] Step 8: According to the boundary conditions of the heat transfer model, if the precooling and discharge conditions of the turbopump do not change with time, the thermal state of the turbopump heat transfer model is obtained by a steady-state analysis method; if at least one of the precooling and discharge conditions of the turbopump changes with time, the thermal state of the turbopump heat transfer model is obtained by a transient analysis method;

[0057] Step 9. According to the thermal state of the turbine pump heat transfer model, determine whether the temperature of each temperature check point is within the actual allowable temperature range. If the temperature of each temperature check point is within its corresponding actual allowable temperature range, the boundary conditions of the heat transfer model meet the requirements, and the thermal state analysis of the turbine pump isolation cavity is completed; if there is at least one temperature check point whose temperature is not within its corresponding actual allowable temperature range, return to step 7 to modify the boundary conditions of the heat transfer model. The modification method is: if the temperature check point that does not meet the conditions is in the isolation cavity, then reselect a set of qh values ​​that are different from the selected qh values ​​in the qh table; if the temperature check point that does not meet the conditions is in the fuel cavity, adjust the heat transfer coefficient h4 of the inner surface of the fuel cavity and the heat transfer temperature Th4 of the inner surface of the fuel cavity.

[0058] This embodiment can test the heat transfer coefficient more conveniently and simulate the actual working condition of the turbine pump isolation chamber, thereby providing a basis for the thermal state analysis of the turbine pump isolation chamber.

Claims

1. A test device for heat transfer coefficient of a turbine pump isolation chamber, characterized in that: It comprises a fuel chamber simulation part (2), an isolation chamber simulation part (4) and an oxidant chamber simulation part (8) which are coaxially connected in sequence; The fuel chamber simulation component (2) is a first annular chamber, and the oxidant chamber simulation component (8) is a third annular chamber; the isolation chamber simulation component (4) comprises a hollow truncated cone and a second annular chamber, one end of the truncated cone is connected to one end of the second annular chamber, the other end of the truncated cone is connected to one end of the first annular chamber, and the other end of the second annular chamber is connected to one end of the third annular chamber; a first annular plate is arranged at the other end of the first annular chamber, and a third annular plate is arranged at the other end of the third annular chamber; isolation annular plates are arranged between the first annular chamber and the truncated cone, and between the second annular chamber and the third annular chamber; The first annular plate is provided with a fuel inlet pipe (1) and a fuel outlet pipe (10); the third annular plate is provided with an oxidant inlet pipe (9) and an oxidant outlet pipe (11); A plurality of joints (3) are arranged on the side wall of the second annular cavity and / or the truncated cone, and the total number of the joints (3) is at least three, wherein at least two joints (3) are respectively used for simulating the inflow and outflow of the blowing gas during blowing, and at least one joint (3) is used for monitoring the internal temperature and pressure of the isolation cavity simulation part (4).

2. A turbine pump isolation chamber heat transfer coefficient test device according to claim 1, characterized in that: The fuel inlet pipe (1) and the oxidant inlet pipe (9) are both provided with a temperature sensor and a pressure sensor; the fuel outlet pipe (10) and the oxidant outlet pipe (11) are both provided with a temperature sensor.

3. A turbine pump isolation chamber heat transfer coefficient test device according to claim 2, characterized in that: The number of the joints (3) is eight, of which four joints (3) are evenly distributed on the side wall of the truncated cone, and the other four joints (3) are evenly distributed on the side wall of the second annular cavity; the joint (3) used for the inflow and outflow of the purge gas during the simulation of purge is a pipe joint, and the joint (3) used for measuring the temperature and pressure is an aviation plug; the temperature sensor is a thermocouple.

4. A turbine pump isolation chamber heat transfer coefficient test device according to claim 3, characterized in that: The second annular cavity and the third annular cavity are connected via a connecting flange (6), and a sealing ring (5) is arranged between the two connecting flanges (6); the inner diameters of the first annular plate, the third annular plate, the isolation annular plate, the first annular cavity, the second annular cavity, the third annular cavity and the truncated cone are equal.

5. A turbine pump isolation chamber heat transfer coefficient testing device according to claim 4, characterized in that: The outer walls of the oxidant inlet pipe (9), the oxidant outlet pipe (11) and the oxidant chamber simulation component (8) are all covered with a heat insulating material, and the heat insulating material includes one or more of high-silica glass fiber cloth, Kevlar cloth and silicone rubber cloth.

6. A turbine pump isolation chamber heat transfer coefficient testing device according to claim 5, characterized in that: The fuel inlet pipe (1) and the fuel outlet pipe (10) are symmetrically arranged about the axis of the first circular ring plate, and the oxidant inlet pipe (9) and the oxidant outlet pipe (11) are symmetrically arranged about the axis of the third circular ring plate.

7. A method for analyzing the thermal state of a turbine pump isolation chamber, using a turbine pump isolation chamber heat transfer coefficient testing device according to any one of claims 1 to 6, characterized in that: The following steps are involved: Step 1, installing the turbine pump isolation chamber heat transfer coefficient test device to a preset position; Step 2, start filling the oxidant into the oxidant chamber simulation part (8) from the oxidant inlet pipe (9), when the oxidant chamber simulation part (8) is fully filled, the oxidant automatically flows out from the oxidant outlet pipe (11), and at the same time monitor the temperature T1 and pressure P1 of the oxidant inlet pipe (9) and the temperature T2 of the oxidant outlet pipe (11), until T2 reaches a preset value, and maintain this state for a period of time t1; Step 3, start filling the fuel agent into the fuel cavity simulation part (2) from the fuel inlet pipe (1), when the fuel cavity simulation part (2) is filled, the fuel agent automatically flows out from the fuel outlet pipe (10), and at the same time monitor the temperature T3 and pressure P2 of the fuel inlet pipe (1) and the temperature T4 of the fuel outlet pipe (10), until T4 reaches a preset value, and maintain this state for t2 time; Step 4, start to pass the purge gas into the isolation chamber simulation part (4) from at least one joint (3), when the isolation chamber simulation part (4) is filled, the purge gas automatically flows out from another joint (3), and at the same time monitor the temperature T5 and pressure P3 of the joint (3) through which the purge gas is passed, as well as the outer wall temperature T6, the inner wall temperature T7, the internal space temperature T8, and the internal space pressure P4 of the isolation chamber simulation part (4), until T6, T7, T8 and P4 all reach a preset steady-state range, maintain this state for t3 time, and then record the values ​​of T6, T7, T8 and P4 at this time; Step 5, changing the temperature and pressure of the purge gas, and then returning to step 4, obtaining and recording the values ​​of T6, T7, T8 and P4 in another preset steady-state range, until the corresponding values ​​of T5 and P3 and T6, T7, T8 and P4 in N preset steady-state ranges are obtained, and after sorting, a flow-heat transfer coefficient table at different temperatures on the inner surface of the isolation cavity is obtained, that is, a qh table; Step 6: Establish a heat transfer model of an actual turbo pump, wherein the heat transfer model includes an oxidant chamber, an isolation chamber, and a fuel chamber, and set a plurality of temperature check points on the heat transfer model, and set an actual allowable temperature range for each temperature check point; Step 7: Set the boundary conditions of the heat transfer model according to the qh table obtained in step 5; Step 8: According to the boundary conditions of the heat transfer model, if the precooling and discharge conditions of the turbopump do not change with time, the thermal state of the turbopump heat transfer model is obtained by a steady-state analysis method; if at least one of the precooling and discharge conditions of the turbopump changes with time, the thermal state of the turbopump heat transfer model is obtained by a transient analysis method; Step 9: According to the thermal state of the turbine pump heat transfer model, determine whether the temperature of each temperature check point is within the actual allowable temperature range. If the temperature of each temperature check point is within its corresponding actual allowable temperature range, the boundary conditions of the heat transfer model meet the requirements and the thermal state analysis of the turbine pump isolation cavity is completed; if there is at least one temperature check point whose temperature is not within its corresponding actual allowable temperature range, return to step 7 to modify the boundary conditions of the heat transfer model.

8. A method for analyzing thermal state of a turbo pump isolation chamber according to claim 7, characterized in that: Step 7 is as follows: Step 7.1, setting the inner surface of the oxidant chamber to a convection heat transfer condition or a constant temperature condition according to the flow rate of the oxidant during the precooling process, and setting the outer surface of the oxidant chamber to an adiabatic condition; Step 7.2, the inner surface of the fuel cavity is set to a convection heat transfer condition or a constant temperature condition according to the fuel flow rate, the heat transfer coefficient h4 of the inner surface of the fuel cavity is calculated according to the DB formula, and the heat transfer temperature Th4 of the inner surface of the fuel cavity is the fuel temperature; the outer surface of the fuel cavity is set to a natural convection heat transfer condition, the heat transfer coefficient h1 of the outer surface of the fuel cavity is estimated according to the natural convection heat transfer formula, and the heat transfer temperature Th1 of the outer surface of the fuel cavity is the ambient temperature during the test; Step 7.3, set the inner surface of the isolation cavity to the convection heat transfer condition, the heat transfer coefficient h2 of the inner surface of the isolation cavity is set according to the qh table obtained in step 5, and the heat transfer temperature Th2 of the inner surface of the isolation cavity is set according to the temperature of the blow-off gas in the blow-off cavity; the outer surface of the isolation cavity is set to the natural convection heat transfer condition, the heat transfer coefficient h3 of the outer surface of the isolation cavity is estimated according to the natural convection heat transfer formula, and the heat transfer temperature Th3 of the outer surface of the isolation cavity is the ambient temperature during the test.

9. A method for analyzing thermal state of a turbo pump isolation chamber according to claim 8, characterized in that: The boundary conditions for modifying the heat transfer model in step 9 are specifically: If the temperature check point that does not meet the conditions is located in the isolation cavity, a set of qh values ​​that are different from the selected qh values ​​are reselected in the qh table; if the temperature check point that does not meet the conditions is located in the fuel cavity, the heat transfer coefficient h4 of the inner surface of the fuel cavity and the heat transfer temperature Th4 of the inner surface of the fuel cavity are adjusted.

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