Performance test system and method for turbo expander

Abstract

The invention discloses a performance test system and method for a turbo expander, and the system comprises a working medium gas inlet pipeline, a working medium gas exhaust pipeline, a bearing gas inlet pipeline, a bearing gas exhaust pipeline, a sealing gas inlet pipeline, a brake gas inlet pipeline, and a brake gas exhaust pipeline which are connected to the turbo expander. A first pressure reducing valve and a first regulating valve are mounted on the working medium gas inlet pipeline; a second regulating valve is mounted on the working medium gas exhaust pipeline; a second pressure reducing valve and a third adjusting valve are mounted on the bearing gas inlet pipeline; a first stop valve is mounted on the bearing gas exhaust pipeline; a fourth adjusting valve is mounted on the sealing gas inlet pipeline; a fifth regulating valve and a sixth regulating valve are mounted on the brake gas inlet pipeline; and a heat exchanger is mounted on the brake gas exhaust pipeline. According to the invention, multi-performance testing of the hydrostatic bearing turbo expander and the dynamic bearing turbo expander in the statics and operation process can be carried out.

Description

Technical Field

[0001] The present invention relates to the technical field of turbine expanders, and more specifically, to a performance testing system and method for a turbine expander. Background Art

[0002] As a highly efficient rotary machine, the turboexpander mainly transfers energy through the change in the speed of the working gas. In this device, the working gas is first accelerated and depressurized through the nozzle, and then enters the high-speed rotating impeller. In the flow channel of the impeller, the gas continues to reduce pressure and decelerate, and its temperature continues to drop. The turboexpander plays a key role in cryogenic processes. It is the main cooling equipment and is widely used in many fields such as the air separation industry, the chemical industry, and liquefaction plants. This expander has many advantages such as small size, light weight, small footprint, simple structure, no pollution to the working fluid, and easy operation and maintenance, making it an important equipment in industrial production.

[0003] Since the speed of the turbo expander is extremely high, reaching tens of thousands or even hundreds of thousands of revolutions per minute, it is very important to monitor its operating status during the development process. This includes accurately collecting operating status data and ensuring safety and stability during the expander test. In addition, it is necessary to maintain the stability of upstream and downstream pressures and gas supply, and control the cooling rate and heating rate within a certain stable range to ensure the normal operation and efficiency of the equipment.

[0004] However, existing test systems have certain limitations. They cannot simultaneously perform static and operational multi-performance tests on both hydrostatic bearing turboexpanders and hydrodynamic bearing turboexpanders. This means that existing systems cannot provide comprehensive operational data for turboexpander development, limiting the comprehensive understanding and optimization of equipment performance. Summary of the invention

[0005] In order to solve the technical problems existing in the background technology, the present invention innovatively provides a performance testing system and method for a turbine expander, which can perform static and multi-performance tests during the operation of a hydrostatic bearing turbine expander and a hydrodynamic bearing turbine expander, thereby ensuring the safety and stability of the turbine expander performance testing process, maintaining the stability of the flow rate and pressure of the working fluid gas and the bearing gas, and can not only help engineers better understand the performance under different working conditions, but also provide data support for the design of future turbine expanders, thereby promoting the advancement and development of turbine expander technology.

[0006] To achieve the above technical objectives, an embodiment of the present invention discloses a performance test system for a turbine expander, including a working gas inlet pipeline, a working gas exhaust pipeline, a bearing gas inlet pipeline, a bearing gas exhaust pipeline, a sealing gas inlet pipeline, a brake gas inlet pipeline and a brake gas exhaust pipeline, one end of the working gas inlet pipeline is connected to a working gas supply pipe, and the other end of the working gas inlet pipeline is connected to a working gas inlet port of the turbine expander, and the working gas inlet pipeline is provided with the first and second gas exhaust pipes in sequence according to the gas flow direction. a pressure reducing valve and a first regulating valve; one end of the working gas exhaust pipeline is connected to the working gas exhaust port of the turbine expander, the other end of the working gas exhaust pipeline is connected to the working gas exhaust pipe, and a second regulating valve is installed on the working gas exhaust pipeline; one end of the bearing gas inlet pipeline is connected to the bearing gas supply pipe, the other end of the bearing gas inlet pipeline is connected to the bearing gas inlet port of the turbine expander, and a second pressure reducing valve and a third regulating valve are installed on the bearing gas inlet pipeline in sequence according to the gas flow direction; the bearing gas One end of the bearing gas exhaust pipeline is connected to the bearing gas exhaust port of the turbine expander, and the other end of the bearing gas exhaust pipeline is connected to the bearing gas exhaust pipe, and a first stop valve is installed on the bearing gas exhaust pipeline; one end of the sealing gas inlet pipeline is connected to the bearing gas inlet pipeline between the second pressure reducing valve and the third regulating valve, and the other end of the sealing gas inlet pipeline is connected to the sealing gas inlet port of the turbine expander, and a fourth regulating valve is installed on the sealing gas inlet pipeline; one end of the brake gas inlet pipeline is connected to the bearing gas inlet pipeline between the second pressure reducing valve and the third regulating valve, and the other end of the brake gas inlet pipeline is connected to the brake gas inlet port of the turbine expander, and a fifth regulating valve and a sixth regulating valve are installed on the brake gas inlet pipeline in sequence according to the gas flow direction; one end of the brake gas exhaust pipeline is connected to the brake gas exhaust port of the turbine expander, and the other end of the brake gas exhaust pipeline is connected to the brake gas inlet pipeline between the fifth regulating valve and the sixth regulating valve, and a heat exchanger is installed on the brake gas exhaust pipeline.

[0007] Furthermore, the present invention provides a performance testing system for a turbine expander, which also includes a working gas bypass branch, one end of which is connected to the working gas inlet pipeline between the first pressure reducing valve and the first regulating valve, and the other end of which is connected to the working gas exhaust pipeline between the working gas exhaust pipe and the second regulating valve, and a seventh regulating valve is installed on the working gas bypass branch.

[0008] Furthermore, the present invention provides a performance testing system for a turbine expander, which also includes a rewarming bypass branch, one end of which is connected to the working gas inlet pipeline between the first regulating valve and the working gas inlet port of the turbine expander, and the other end of which is connected to the working gas exhaust pipe between the second regulating valve and the working gas exhaust port of the turbine expander, and a second stop valve is installed on the rewarming bypass branch.

[0009] Furthermore, the present invention provides a performance testing system for a turbine expander, which also includes a pressure-reducing bypass branch, one end of which is connected to the brake air intake pipeline between the fifth regulating valve and the sixth regulating valve, and the other end of the pressure-reducing bypass branch is connected to the bearing air exhaust pipeline between the first stop valve and the bearing air exhaust pipe, and a third stop valve is installed on the pressure-reducing bypass branch.

[0010] Furthermore, the present invention provides a performance testing system for a turbine expander, which also includes a first temperature sensor, a second temperature sensor and a first pressure sensor, wherein the first temperature sensor is installed on the bearing gas exhaust pipeline between the first stop valve and the bearing gas exhaust port of the turbine expander, the second temperature sensor is installed at the bearing gas exhaust end of the turbine expander, and the first pressure sensor is installed at the working gas exhaust end of the turbine expander, and the first temperature sensor, the second temperature sensor and the first pressure sensor are all connected to the fourth regulating valve signal.

[0011] Furthermore, the present invention provides a performance testing system for a turbine expander, which also includes a rotation speed sensor, wherein the rotation speed sensor is installed at the gas bearing of the turbine expander, and the rotation speed sensor is connected to the first submission valve signal.

[0012] Furthermore, the present invention provides a performance testing system for a turbine expander, wherein a first flow sensor is installed on the working gas supply pipeline between the first pressure reducing valve and the first regulating valve, a third temperature sensor and a second pressure sensor are installed on the working gas inlet pipeline between the first regulating valve and the working gas inlet of the turbine expander, a third pressure sensor and a fourth temperature sensor are installed on the working gas exhaust pipeline between the working gas exhaust port of the turbine expander and the second regulating valve, a second flow sensor is installed on the bearing gas inlet pipeline between the second pressure reducing valve and the third regulating valve, a first filter is installed on the bearing inlet pipeline between the third regulating valve and the bearing gas inlet of the turbine expander, a fourth pressure sensor is installed between the first filter and the third regulating valve, a third flow sensor is installed on the sealing gas inlet pipeline between the second pressure reducing valve and the fourth regulating valve, and the fourth regulating valve and the sealing gas of the turbine expander are connected. A second filter is installed on the sealing air inlet pipeline between the air inlets, a fifth pressure sensor is installed between the second filter and the fourth regulating valve, a third filter is installed on the brake air inlet pipeline between the fifth regulating valve and the sixth regulating valve, the secondary side of the heat exchanger is connected to the brake air inlet pipeline between the third filter and the sixth regulating valve, a fifth temperature sensor and a sixth pressure sensor are installed on the brake air inlet pipeline between the sixth regulating valve and the brake air inlet of the turbine expander, a seventh pressure sensor, a sixth temperature sensor and a fourth flow sensor are installed on the brake air exhaust pipeline between the brake air exhaust port of the turbine expander and the primary side of the heat exchanger, and also includes an onboard instrument pipeline and a displacement sensor and a vibration sensor installed on the gas bearing side of the turbine expander, and the first pressure sensor, the second temperature sensor, the speed sensor, the displacement sensor and the vibration sensor are all installed on the onboard instrument pipeline.

[0013] The embodiment of the present invention further provides a test method for a performance test system of a turbine expander, which is applied to the performance test system of a turbine expander. The test method comprises a test preparation step, a gas bearing statics test step, a static pressure operation test step, a dynamic pressure operation test step and a test end step, wherein the gas bearing statics test step, the static pressure operation test step and the dynamic pressure operation test step are performed after the test preparation step;

[0014] The test preparation steps include:

[0015] The openings of the first regulating valve and the second regulating valve are set to 0, and the second stop valve is closed;

[0016] Controlling the openings of the first pressure reducing valve and the seventh regulating valve to stabilize the pressure of the working gas inlet pipeline at a first set pressure value;

[0017] Control the openings of the second pressure reducing valve, the fourth regulating valve, the fifth regulating valve and the sixth regulating valve so that the pressure of the sealing gas intake pipeline is stabilized at the second set pressure value and the pressure of the brake gas supply pipeline is stabilized at the third set pressure value;

[0018] Increase the opening of the third regulating valve to stabilize the pressure of the bearing gas inlet pipeline at a fourth set pressure value;

[0019] The gas bearing statics test steps include:

[0020] Changing the opening of the fifth regulating valve or the sixth regulating valve to test the displacement of the gas bearing of the turbine expander under different brake gas pressures;

[0021] Changing the opening of the fourth regulating valve to test the displacement of the gas bearing of the turbo expander under different sealing gas pressures;

[0022] The static pressure operation test steps include:

[0023] Open the second regulating valve;

[0024] Control the opening of the third regulating valve to stabilize the bearing gas inlet pressure at a set bearing gas inlet pressure value;

[0025] The opening of the first regulating valve is set to the initial setting opening value, the seventh regulating valve is gradually closed, and the opening of the first regulating valve is maintained at the initial setting opening value, so that the turbo expander operates stably at a lower speed;

[0026] gradually increasing the opening of the first regulating valve to a first set opening value of the working fluid gas static pressure bearing test, so that the turbine expander reaches a maximum speed and maintains the turbine expander running stably at the maximum speed;

[0027] The dynamic pressure operation test steps include:

[0028] Close the fourth regulating valve and open the second regulating valve;

[0029] Adjust the opening of the third regulating valve to stabilize the bearing gas inlet pressure at the set bearing gas inlet pressure value;

[0030] Open the first regulating valve to make the turbine expander rotor have a rotation speed value, and set the opening of the third regulating valve to 0;

[0031] Gradually reduce the opening of the seventh regulating valve, and gradually increase the opening of the first regulating valve to the first set opening value of the working fluid pneumatic pressure bearing test, so that the turbine expander operates at the critical speed;

[0032] Continue to increase the opening of the first regulating valve to the second set opening value of the working fluid pneumatic pressure bearing test, so that the turbine expander reaches the maximum speed and maintains the turbine expander running stably at the maximum speed;

[0033] The test end step includes:

[0034] After the turbine expander operates stably at the maximum speed for a period of time, the opening of the seventh regulating valve is gradually increased and the opening of the first regulating valve is reduced, so that the speed of the turbine expander is reduced, and finally the opening of the first regulating valve is 0;

[0035] Set the openings of the second pressure reducing valve, the third regulating valve, the fourth regulating valve, the fifth regulating valve, and the sixth regulating valve to 0, and open the first stop valve to discharge the bearing gas in the bearing gas pipeline;

[0036] Open the second stop valve to discharge the working gas in the turbine expander.

[0037] Furthermore, the present invention provides a method for testing the performance of a turbo expander, wherein the test preparation step further includes:

[0038] When the openings of the fifth regulating valve and the sixth regulating valve cannot reduce the pressure of the brake air intake pipeline, the third stop valve is opened to perform a venting operation on the brake air intake pipeline.

[0039] Furthermore, the present invention provides a method for testing the performance of a turbo expander, wherein the static pressure operation test step further includes:

[0040] The speed of the turbine expander is controlled by controlling the opening of the sixth regulating valve and the first regulating valve;

[0041] The speed sensor is interlocked with the first regulating valve. When the speed of the turbine expander is too high, the opening of the first regulating valve is reduced. When the speed of the turbine expander is too low, the opening of the first regulating valve is increased.

[0042] The first temperature sensor, the second temperature sensor and the first pressure sensor are interlocked with the fourth regulating valve. When the first temperature sensor and the second temperature sensor are significantly lower than the room temperature or the first pressure sensor is too high, the opening of the fourth regulating valve is increased.

[0043] The beneficial effects of the present invention are as follows: the present invention can perform multiple performance simulation tests of the statics and operation of a hydrostatic bearing turbine expander and a hydrodynamic bearing turbine expander through the valve control logic of the working gas inlet pipeline, the working gas exhaust pipeline, the bearing gas inlet pipeline, the bearing gas exhaust pipeline, the sealing gas inlet pipeline, the brake gas inlet pipeline and the brake gas exhaust pipeline, and ensure the safety and stability of the turbine expander performance test process, and maintain the stability of the working gas and bearing gas flow and pressure. The multi-performance test can not only help engineers better understand the performance under different working conditions, evaluate the static performance of the turbine expander gas bearing and the performance test results during operation, but also provide data support for the design of future turbine expanders, thereby promoting the progress and development of turbine expander technology. BRIEF DESCRIPTION OF THE DRAWINGS

[0044] Figure 1 A schematic diagram of the connection structure of a performance test system for a turbo expander of the present invention;

[0045] Figure 2 The present invention is a flow chart of a control method of a performance testing system for a turbine expander. DETAILED DESCRIPTION

[0046] A performance testing system for a turbine expander of the present invention is explained and illustrated in detail below in conjunction with the accompanying drawings of the specification.

[0047] like Figure 1As shown, the embodiment of the present invention discloses a performance test system for a turbo expander, including a working gas inlet pipeline 11, a working gas exhaust pipeline 12, a bearing gas inlet pipeline 21, a bearing gas exhaust pipeline 22, a sealing gas inlet pipeline 23, a brake gas inlet pipeline 24 and a brake gas exhaust pipeline 25. One end of the working gas inlet pipeline 11 is connected to the working gas supply pipe, and the other end of the working gas inlet pipeline 11 is connected to the working gas inlet of the turbo expander. The working gas inlet pipeline 11 is sequentially installed with a first pressure reducing valve 111 and a first regulating valve 113 according to the gas flow direction (i.e., the direction from the working gas supply pipe to the working gas inlet of the turbo expander). The working gas inlet pipeline 11 is used to reduce the pressure of the high-pressure working gas and transport the reduced-pressure working gas to the inlet of the expansion end of the turbo expander. The first pressure reducing valve 111 is used to adjust the pressure of the high-pressure working gas, and the first regulating valve 113 is used to adjust the intake flow rate of the working gas. One end of the working gas exhaust pipeline 12 is connected to the working gas exhaust port of the turbine expander, and the other end of the working gas exhaust pipeline 12 is connected to the working gas exhaust pipe. A second regulating valve 123 is installed on the working gas exhaust pipeline 12. The working gas exhaust pipeline 12 forms the exhaust pipeline of the expansion end of the turbine expander. The second regulating valve 123 is used to adjust the exhaust flow of the low-pressure working gas. One end of the bearing gas intake pipeline 21 is connected to the bearing gas supply pipe, and the other end of the bearing gas intake pipeline 21 is connected to the bearing gas intake port of the turbine expander. The second pressure reducing valve 210 and the third regulating valve 212 are installed in sequence on the bearing gas intake pipeline 21 according to the gas flow direction (i.e., the direction from the bearing gas supply pipe to the bearing gas intake port of the turbine expander). The bearing gas intake pipeline 21 is used to provide bearing gas for the gas bearing in the turbine expander. The second pressure reducing valve 210 is used to adjust the pressure of the high-pressure bearing gas, and the third regulating valve 212 is used to adjust the flow of the bearing gas. One end of the bearing gas exhaust pipeline 22 is connected to the bearing gas exhaust port of the turbine expander, and the other end of the bearing gas exhaust pipeline 22 is connected to the bearing gas exhaust pipe. The first stop valve 221 is installed on the bearing gas exhaust pipeline 22. The bearing gas exhaust pipeline 22 forms the exhaust pipeline of the gas bearing of the turbine expander. The first stop valve 221 is used to control the opening and closing of the bearing gas exhaust. One end of the sealing gas inlet pipeline 23 is connected to the bearing gas inlet pipeline 21 between the second pressure reducing valve 210 and the third regulating valve 212, and the other end of the sealing gas inlet pipeline 23 is connected to the sealing gas inlet of the turbine expander. A fourth regulating valve 232 is installed on the sealing gas inlet pipeline 23. The sealing gas inlet pipeline 23 is used to isolate the low-temperature working medium gas of the turbine expander from the bearing gas in the turbine expander. The fourth regulating valve 232 is used to adjust the flow rate of the sealing gas.One end of the brake air inlet pipeline 24 is connected to the bearing air inlet pipeline 21 between the second pressure reducing valve 210 and the third regulating valve 212, and the other end of the brake air inlet pipeline 24 is connected to the brake air inlet port of the turbine expander. The fifth regulating valve 241 and the sixth regulating valve 243 are installed on the brake air inlet pipeline 24 in sequence according to the gas flow direction. One end of the brake air exhaust pipeline 25 is connected to the brake air exhaust port of the turbine expander, and the other end of the brake air exhaust pipeline 25 is connected to the brake air inlet pipeline 24 between the fifth regulating valve 241 and the sixth regulating valve 243. A heat exchanger 254 is installed on the brake air exhaust pipeline 25. The brake air inlet pipeline 24 and the brake air exhaust pipeline 25 are used to provide brake air to the braking end of the turbine expander and adjust the speed. The fifth regulating valve 241 and the sixth regulating valve 243 are used to adjust the flow rate of the brake air. The heat exchanger 254 is used to adjust the temperature of the brake air to keep the brake air within a reasonable temperature range. The bearing gas inlet pipeline 21, the sealing gas inlet pipeline 23 and the brake gas inlet pipeline 24 share the same gas source, which can simplify the system structure and reduce the difficulty of system operation. Through the valve control logic of the working gas inlet pipeline 11, the working gas exhaust pipeline 12, the bearing gas inlet pipeline 21, the bearing gas exhaust pipeline 22, the sealing gas inlet pipeline 23, the brake gas inlet pipeline 24 and the brake gas exhaust pipeline 25, the statics and multi-performance simulation tests of the hydrostatic bearing turbine expander and the hydrodynamic bearing turbine expander during operation can be carried out, and the turbine expander performance test process can be guaranteed to be safe and stable, and the working gas and bearing gas flow and pressure can be maintained stable. Through multi-performance testing, it can not only help engineers better understand the performance under different working conditions, evaluate the static performance of the turbine expander gas bearing and the performance test results during operation, but also provide data support for the design of future turbine expanders, thereby promoting the progress and development of turbine expander technology.

[0048] In one embodiment of the present invention, a working gas bypass branch 13 is also included, one end of the working gas bypass branch 13 is connected to the working gas inlet pipeline 11 between the first pressure reducing valve 111 and the first regulating valve 113, and the other end of the working gas bypass branch 13 is connected to the working gas exhaust pipeline 12 between the working gas exhaust pipe and the second regulating valve 123. A seventh regulating valve 131 is installed on the working gas bypass branch 13. In the test preparation stage, the working gas pressure can be maintained at a certain level by adjusting the opening of the first pressure reducing valve 111 and the seventh regulating valve 131. In the test stage, the seventh regulating valve 131 and the second regulating valve 123 are adjusted to change the working gas pressure and flow rate passing through the turbine expander, thereby conducting turbine expander performance test experiments under different working conditions.

[0049] In one embodiment of the present invention, a rewarming bypass branch 14 is also included, one end of the rewarming bypass branch 14 is connected to the working gas inlet pipeline 11 between the first regulating valve 113 and the working gas inlet port of the turbine expander, and the other end of the rewarming bypass branch 14 is connected to the working gas exhaust pipe between the second regulating valve 123 and the working gas exhaust port of the turbine expander. A second stop valve 141 is installed on the rewarming bypass branch 14. Through the rewarming bypass branch 14, a working gas passage can be formed after the turbine expander is cooled and shut down to help the working gas inlet pipeline 11 and the working gas exhaust pipeline 12 to reheat, so as to carry out the next test.

[0050] In one embodiment of the present invention, a pressure reducing bypass branch 26 is also included, one end of the pressure reducing bypass branch 26 is connected to the brake air intake pipeline 24 between the fifth regulating valve 241 and the sixth regulating valve 243, and the other end of the pressure reducing bypass branch 26 is connected to the bearing air exhaust pipeline 22 between the first stop valve 221 and the bearing air exhaust pipe, and a third stop valve 261 is installed on the pressure reducing bypass branch 26. When adjusting the fifth regulating valve 241 and the sixth regulating valve 243 is still not enough to reduce the pressure of the brake air intake pipeline 24 and the brake air exhaust pipeline 25, the over-pressure brake air can be exhausted by opening the third stop valve 261, and the pressure of the brake air can be adjusted to a reasonable range to ensure the normal and stable operation of the test system.

[0051] In one embodiment of the present invention, the first temperature sensor 132, the second temperature sensor 302 and the first pressure sensor 301 are also included. The first temperature sensor 132 is installed on the bearing gas exhaust pipeline 22 between the first stop valve 221 and the bearing gas exhaust port of the turbine expander, the second temperature sensor 302 is installed at the bearing gas exhaust end of the turbine expander, and the first pressure sensor 301 is installed at the working gas exhaust end of the turbine expander. The first temperature sensor 132, the second temperature sensor 302 and the first pressure sensor 301 are all connected to the fourth regulating valve 232 by signal. The interlocking structure of the first temperature sensor 132, the second temperature sensor 302 and the first pressure sensor 301 and the fourth regulating valve 232 can increase the opening of the fourth regulating valve 232 when the first temperature sensor 132 and the second temperature sensor 302 are obviously lower than the room temperature or the first pressure sensor 301 is too high, thereby ensuring the safe and stable operation of the test system.

[0052] In one embodiment of the present invention, a speed sensor 303 is further included. The speed sensor 303 is installed at the gas bearing of the turbo expander, and the speed sensor 303 is connected to the first delivery valve signal. The interlocking structure between the speed sensor 303 and the first regulating valve 113 can enable the test system to reduce the opening of the first regulating valve 113 when the speed of the turbo expander is too high, and increase the opening of the first regulating valve 113 when the speed of the turbo expander is too low, thereby ensuring the safe and stable operation of the test system.

[0053] In one embodiment of the present invention, in order to obtain the operating status of each pipeline and the turbine expander in real time during the test process, a first flow sensor 112 is installed on the working gas supply pipeline between the first pressure reducing valve 111 and the first regulating valve 113, which is used to detect the flow rate of the working gas. A third temperature sensor 114A, 114B and a second pressure sensor 115 are installed on the working gas inlet pipeline 11 between the first regulating valve 113 and the working gas inlet of the turbine expander, which are respectively used to detect the temperature and pressure of the working gas inlet pipeline 11. A third pressure sensor 121 and a fourth temperature sensor 122A, 122B are installed on the working gas exhaust pipeline 12 between the working gas exhaust port of the turbine expander and the second regulating valve 123, which are respectively used to detect the pressure and temperature of the working gas exhaust pipeline 12. A second flow sensor 211 is installed on the bearing gas inlet pipeline 21 between the second pressure reducing valve 210 and the third regulating valve 212, which is used to detect the flow rate of the bearing gas inlet pipeline 21. A first filter 214 is installed on the bearing air intake pipeline between the third regulating valve 212 and the bearing air intake port of the turbine expander, and is used to filter impurities in the bearing air. A fourth pressure sensor 213 is installed between the first filter 214 and the third regulating valve 212, and is used to detect the pressure of the bearing air intake pipeline 21. A third flow sensor 231 is installed on the sealing air intake pipeline 23 between the second pressure reducing valve 210 and the fourth regulating valve 232, and is used to detect the flow of the sealing air intake pipeline 23. A second filter 234 is installed on the sealing air intake pipeline 23 between the fourth regulating valve 232 and the sealing air intake port of the turbine expander, and is used to filter impurities in the sealing air. A fifth pressure sensor 233 is installed between the second filter 234 and the fourth regulating valve 232, and is used to detect the pressure of the sealing air intake pipeline 23. A third filter 242 is installed on the brake air intake pipeline 24 between the fifth regulating valve 241 and the sixth regulating valve 243, and is used to filter impurities in the brake air. The secondary side of the heat exchanger 254 is connected to the brake gas inlet pipeline 24 between the third filter 242 and the sixth regulating valve 243 to adjust the temperature of the brake gas. A fifth temperature sensor 244 and a sixth pressure sensor 245 are installed on the brake gas inlet pipeline 24 between the sixth regulating valve 243 and the brake gas inlet of the turbine expander, which are respectively used to detect the temperature and pressure of the brake gas inlet pipeline 24. A seventh pressure sensor 251, a sixth temperature sensor 252 and a fourth flow sensor 253 are installed on the brake gas exhaust pipeline 25 between the brake gas exhaust port of the turbine expander and the primary side of the heat exchanger 254, which are respectively used to detect the pressure, temperature and flow of the brake gas exhaust pipeline 25. It also includes an onboard instrument pipeline 30 and a displacement sensor 304 and vibration sensors 305A, 305B installed on the gas bearing side of the turbine expander, which are respectively used to detect the displacement of the gas bearing of the turbine expander and the vibration value of the turbine expander.The first pressure sensor 301, the second temperature sensor 302, the rotation speed sensor 303, the displacement sensor 304 and the vibration sensors 305A and 305B are all installed on the onboard instrument pipeline 30, which is convenient for connection with the turbine expander to be tested when in use, while ensuring the overall neatness of the test system.

[0054] like Figure 2 As shown, an embodiment of the present invention further provides a test method for a performance test system of a turbine expander, which is applied to a performance test system of a turbine expander. The test method includes a test preparation step, a gas bearing statics test step, a static pressure operation test step, a dynamic pressure operation test step and a test end step. The gas bearing statics test step, the static pressure operation test step and the dynamic pressure operation test step are performed after the test preparation step.

[0055] The test preparation steps include:

[0056] The openings of the first regulating valve 113 and the second regulating valve 123 are set to 0, and the second stop valve 141 is closed;

[0057] Control the openings of the first pressure reducing valve 111 and the seventh regulating valve 131 to stabilize the pressure of the working gas inlet pipeline 11 at a first set pressure value;

[0058] Control the openings of the second pressure reducing valve 210, the fourth regulating valve 232, the fifth regulating valve 241 and the sixth regulating valve 243 so that the pressure of the sealing gas intake pipeline 23 is stabilized at the second set pressure value and the pressure of the brake gas supply pipeline is stabilized at the third set pressure value;

[0059] Increasing the opening of the third regulating valve 212 to stabilize the pressure of the bearing gas inlet pipeline 21 at a fourth set pressure value;

[0060] Through the test preparation steps, the working gas and bearing gas can be stabilized within the set pressure range, providing a stable gas source for subsequent tests under different working conditions.

[0061] The gas bearing static test steps include:

[0062] The opening of the fifth regulating valve 241 or the sixth regulating valve 243 is changed to test the displacement of the gas bearing of the turbine expander under different brake gas pressures;

[0063] Changing the opening of the fourth regulating valve 232 to test the displacement of the gas bearing of the turbo expander under different sealing gas pressures;

[0064] Through the gas bearing statics test, the displacement data of the gas bearing in the turbine expander under static conditions, different brake gas pressures and different sealing gas pressures can be obtained through the displacement sensor 304.

[0065] The static pressure operation test steps include:

[0066] Open the second regulating valve 123;

[0067] Control the opening of the third regulating valve 212 to stabilize the bearing gas inlet pressure at a set bearing gas inlet pressure value;

[0068] The opening of the first regulating valve 113 is set to the initial setting opening value, the seventh regulating valve 131 is gradually closed, and the opening of the first regulating valve 113 is maintained at the initial setting opening value, so that the turbo expander operates stably at a lower speed;

[0069] Gradually increase the opening of the first regulating valve 113 to a first set opening value of the working gas static pressure bearing test, so that the turbine expander reaches the maximum speed and maintains the turbine expander running stably at the maximum speed;

[0070] Through the static pressure operation test, the operating status of the turbo expander under static pressure low speed and high speed conditions can be tested to obtain the corresponding static pressure operation data of the turbo expander.

[0071] The dynamic pressure operation test steps include:

[0072] Close the fourth regulating valve 232 and open the second regulating valve 123;

[0073] Adjust the opening of the third regulating valve 212 to stabilize the bearing gas inlet pressure at a set bearing gas inlet pressure value;

[0074] Open the first regulating valve 113 to make the turbine expander rotor have a rotation speed value, and set the opening of the third regulating valve 212 to 0;

[0075] Gradually reduce the opening of the seventh regulating valve 131, and gradually increase the opening of the first regulating valve 113 to the first set opening value of the working fluid pneumatic pressure bearing test, so that the turbine expander operates at the critical speed;

[0076] Critical speed refers to the speed at which the rotor of a turbo expander reaches a certain speed during startup. Due to the centrifugal force, the rotor will leave the bearing and begin to float on the oil film of the bearing. This speed is called the "take-off" speed. This speed marks the critical point at which the turbo expander transitions from a stationary state to a stable operating state.

[0077] Continue to increase the opening of the first regulating valve 113 to the second set opening value of the working fluid pneumatic pressure bearing test, so that the turbine expander reaches the maximum speed and maintains the turbine expander running stably at the maximum speed;

[0078] Through the dynamic pressure operation test steps, the operating state of the turbine expander under the dynamic pressure critical speed and maximum speed conditions can be tested to obtain the corresponding dynamic pressure operation data of the turbine expander.

[0079] The test closing steps include:

[0080] After the turbine expander operates stably at the maximum speed for a period of time, the opening of the seventh regulating valve 131 is gradually increased and the opening of the first regulating valve 113 is reduced, so that the speed of the turbine expander is reduced, and finally the opening of the first regulating valve 113 is 0;

[0081] Set the openings of the second pressure reducing valve 210, the third regulating valve 212, the fourth regulating valve 232, the fifth regulating valve 241, and the sixth regulating valve 243 to 0, and open the first stop valve 221 to discharge the bearing gas in the bearing gas pipeline;

[0082] Open the second stop valve 141 to discharge the working gas in the turbine expander.

[0083] In this embodiment, a stable test environment is provided through the valve control logic of the working gas inlet pipeline 11, the working gas exhaust pipeline 12, the bearing gas inlet pipeline 21, the bearing gas exhaust pipeline 22, the sealing gas inlet pipeline 23, the brake gas inlet pipeline 24 and the brake gas exhaust pipeline 25. Under a stable test environment, multiple performance simulation tests (i.e., gas bearing statics test, static pressure operation test and dynamic pressure operation test) can be performed on the statics and operation of the hydrostatic bearing turbine expander and the hydrodynamic bearing turbine expander, and the performance test process of the turbine expander can be guaranteed to be safe and stable, and the flow rate and pressure of the working gas and the bearing gas can be maintained stable. Multi-performance testing can not only help engineers better understand the performance under different working conditions, record the data of each pipeline, evaluate the statics performance of the turbine expander gas bearing and the performance test results during operation, but also provide data support for the design of future turbine expanders, thereby promoting the advancement and development of turbine expander technology.

[0084] In one embodiment of the present invention, the test preparation step further includes:

[0085] When the opening of the fifth regulating valve 241 and the sixth regulating valve 243 cannot reduce the pressure of the brake air intake pipeline 24, the third stop valve 261 is opened to vent the brake air intake pipeline 24 to prevent the air brake air pressure from being too high, thereby ensuring the safety and stability of the test process.

[0086] In one embodiment of the present invention, the static pressure operation test step further includes:

[0087] The speed of the turbine expander is controlled by controlling the opening of the sixth regulating valve 243 and the first regulating valve 113, so that the speed control of the turbine expander is more flexible.

[0088] The speed sensor 303 is interlocked with the first regulating valve 113. When the speed of the turbine expander is too high, the opening of the first regulating valve 113 is reduced. When the speed of the turbine expander is too low, the opening of the first regulating valve 113 is increased.

[0089] The first temperature sensor 132, the second temperature sensor 302 and the first pressure sensor 301 are interlocked with the fourth regulating valve 232. When the first temperature sensor 132 and the second temperature sensor 302 are significantly lower than the room temperature or the first pressure sensor 301 is too high, the opening of the fourth regulating valve 232 is increased to ensure the safety and stability of the test process.

[0090] In the description of the present invention, unless otherwise clearly specified and limited, the terms "install", "connect", "connect", "fix" and the like should be understood in a broad sense, for example, it can be a fixed connection, a detachable connection, or an integral connection; it can be a mechanical connection or an electrical connection; it can be a direct connection or an indirect connection through an intermediate medium, it can be the internal connection of two elements or the interaction relationship between two elements, unless otherwise clearly defined. For ordinary technicians in this field, the specific meanings of the above terms in the present invention can be understood according to specific circumstances.

[0091] In addition, the terms "first" and "second" are used for descriptive purposes only and should not be understood as indicating or implying relative importance or implicitly indicating the number of the indicated technical features. Therefore, the features defined as "first" and "second" may explicitly or implicitly include at least one of the features. In the description of the present invention, the meaning of "plurality" is at least two, such as two, three, etc., unless otherwise clearly and specifically defined.

[0092] The above description is only a preferred embodiment of the present invention and is not intended to limit the present invention. Any modifications, equivalent substitutions and simple improvements made to the essential contents of the present invention should be included in the protection scope of the present invention.

Claims

1. A performance test system for a turbo expander, characterized in that: It includes a working gas inlet pipeline, a working gas exhaust pipeline, a bearing gas inlet pipeline, a bearing gas exhaust pipeline, a sealing gas inlet pipeline, a brake gas inlet pipeline and a brake gas exhaust pipeline, one end of the working gas inlet pipeline is connected to the working gas supply pipe, the other end of the working gas inlet pipeline is connected to the working gas inlet of the turbine expander, and a first pressure reducing valve and a first regulating valve are sequentially installed on the working gas inlet pipeline according to the gas flow direction; one end of the working gas exhaust pipeline is connected to the working gas exhaust port of the turbine expander, the other end of the working gas exhaust pipeline is connected to the working gas exhaust pipe, and a second regulating valve is installed on the working gas exhaust pipeline; one end of the bearing gas inlet pipeline is connected to the bearing gas supply pipe, the other end of the bearing gas inlet pipeline is connected to the bearing gas inlet of the turbine expander, and a second pressure reducing valve and a third regulating valve are sequentially installed on the bearing gas inlet pipeline according to the gas flow direction; one end of the bearing gas exhaust pipeline is connected to the bearing of the turbine expander The air exhaust port is connected, and the other end of the bearing air exhaust pipeline is connected to the bearing air exhaust pipe, and a first stop valve is installed on the bearing air exhaust pipeline; one end of the sealing air inlet pipeline is connected to the bearing air inlet pipeline between the second pressure reducing valve and the third regulating valve, and the other end of the sealing air inlet pipeline is connected to the sealing air inlet of the turbine expander, and a fourth regulating valve is installed on the sealing air inlet pipeline; one end of the brake air inlet pipeline is connected to the bearing air inlet pipeline between the second pressure reducing valve and the third regulating valve, and the other end of the brake air inlet pipeline is connected to the brake air inlet of the turbine expander, and a fifth regulating valve and a sixth regulating valve are installed on the brake air inlet pipeline in sequence according to the gas flow direction; one end of the brake air exhaust pipeline is connected to the brake air exhaust port of the turbine expander, and the other end of the brake air exhaust pipeline is connected to the brake air inlet pipeline between the fifth regulating valve and the sixth regulating valve, and a heat exchanger is installed on the brake air exhaust pipeline.

2. A turbo expander performance test system according to claim 1, characterized in that: The system also includes a working gas bypass branch, one end of which is connected to the working gas inlet pipeline between the first pressure reducing valve and the first regulating valve, and the other end of which is connected to the working gas exhaust pipeline between the working gas exhaust pipe and the second regulating valve, and a seventh regulating valve is installed on the working gas bypass branch.

3. A turbo expander performance testing system according to claim 2, characterized in that: It also includes a rewarming bypass branch, one end of which is connected to the working gas inlet pipeline between the first regulating valve and the working gas inlet of the turbine expander, and the other end of the rewarming bypass branch is connected to the working gas exhaust pipe between the second regulating valve and the working gas exhaust port of the turbine expander, and a second stop valve is installed on the rewarming bypass branch.

4. A turbo expander performance test system according to claim 3, characterized in that: It also includes a pressure-reducing bypass branch, one end of which is connected to the brake air intake pipeline between the fifth regulating valve and the sixth regulating valve, and the other end of the pressure-reducing bypass branch is connected to the bearing air exhaust pipeline between the first stop valve and the bearing air exhaust pipe, and a third stop valve is installed on the pressure-reducing bypass branch.

5. A turbo expander performance test system according to claim 4, characterized in that: It also includes a first temperature sensor, a second temperature sensor and a first pressure sensor. The first temperature sensor is installed on the bearing gas exhaust pipeline between the first stop valve and the bearing gas exhaust port of the turbine expander, the second temperature sensor is installed at the bearing gas exhaust end of the turbine expander, and the first pressure sensor is installed at the working gas exhaust end of the turbine expander. The first temperature sensor, the second temperature sensor and the first pressure sensor are all connected to the fourth regulating valve signal.

6. A turbo expander performance testing system according to claim 5, characterized in that: It also includes a rotation speed sensor, which is installed at the gas bearing of the turbine expander and is connected to the first submission valve signal.

7. A turbo expander performance test system according to claim 6, characterized in that: A first flow sensor is installed on the working gas supply pipeline between the first pressure reducing valve and the first regulating valve, a third temperature sensor and a second pressure sensor are installed on the working gas inlet pipeline between the first regulating valve and the working gas inlet of the turbine expander, a third pressure sensor and a fourth temperature sensor are installed on the working gas exhaust pipeline between the working gas exhaust port of the turbine expander and the second regulating valve, a second flow sensor is installed on the bearing gas inlet pipeline between the second pressure reducing valve and the third regulating valve, a first filter is installed on the bearing inlet pipeline between the third regulating valve and the bearing gas inlet of the turbine expander, a fourth pressure sensor is installed between the first filter and the third regulating valve, a third flow sensor is installed on the sealing gas inlet pipeline between the second pressure reducing valve and the fourth regulating valve, and a sealing gas inlet pipeline between the fourth regulating valve and the sealing gas inlet of the turbine expander is installed. A second filter is installed on the road, a fifth pressure sensor is installed between the second filter and the fourth regulating valve, a third filter is installed on the brake air intake pipeline between the fifth regulating valve and the sixth regulating valve, the secondary side of the heat exchanger is connected to the brake air intake pipeline between the third filter and the sixth regulating valve, a fifth temperature sensor and a sixth pressure sensor are installed on the brake air intake pipeline between the sixth regulating valve and the brake air inlet of the turbine expander, a seventh pressure sensor, a sixth temperature sensor and a fourth flow sensor are installed on the brake air exhaust pipeline between the brake air exhaust port of the turbine expander and the primary side of the heat exchanger, and also includes an onboard instrument pipeline and a displacement sensor and a vibration sensor installed on the gas bearing side of the turbine expander, and the first pressure sensor, the second temperature sensor, the speed sensor, the displacement sensor and the vibration sensor are all installed on the onboard instrument pipeline.

8. A method for testing the performance of a turbo expander, applied to the performance testing system for a turbo expander as claimed in claim 7, characterized in that: The test method comprises a test preparation step, a gas bearing statics test step, a static pressure operation test step, a dynamic pressure operation test step and a test end step, wherein the gas bearing statics test step, the static pressure operation test step and the dynamic pressure operation test step are performed after the test preparation step; The test preparation steps include: The openings of the first regulating valve and the second regulating valve are set to 0, and the second stop valve is closed; Controlling the openings of the first pressure reducing valve and the seventh regulating valve to stabilize the pressure of the working gas inlet pipeline at a first set pressure value; Control the openings of the second pressure reducing valve, the fourth regulating valve, the fifth regulating valve and the sixth regulating valve so that the pressure of the sealing gas intake pipeline is stabilized at the second set pressure value and the pressure of the brake gas supply pipeline is stabilized at the third set pressure value; Increase the opening of the third regulating valve to stabilize the pressure of the bearing gas inlet pipeline at a fourth set pressure value; The gas bearing statics test steps include: Changing the opening of the fifth regulating valve or the sixth regulating valve to test the displacement of the gas bearing of the turbine expander under different brake gas pressures; Changing the opening of the fourth regulating valve to test the displacement of the gas bearing of the turbo expander under different sealing gas pressures; The static pressure operation test steps include: Open the second regulating valve; Control the opening of the third regulating valve to stabilize the bearing gas inlet pressure at a set bearing gas inlet pressure value; The opening of the first regulating valve is set to the initial setting opening value, the seventh regulating valve is gradually closed, and the opening of the first regulating valve is maintained at the initial setting opening value, so that the turbo expander operates stably at a lower speed; gradually increasing the opening of the first regulating valve to a first set opening value of the working fluid gas static pressure bearing test, so that the turbine expander reaches a maximum speed and maintains the turbine expander running stably at the maximum speed; The dynamic pressure operation test steps include: Close the fourth regulating valve and open the second regulating valve; Adjust the opening of the third regulating valve to stabilize the bearing gas inlet pressure at the set bearing gas inlet pressure value; Open the first regulating valve to make the turbine expander rotor have a rotation speed value, and set the opening of the third regulating valve to 0; Gradually reduce the opening of the seventh regulating valve, and gradually increase the opening of the first regulating valve to the first set opening value of the working fluid pneumatic pressure bearing test, so that the turbine expander operates at the critical speed; Continue to increase the opening of the first regulating valve to the second set opening value of the working fluid pneumatic pressure bearing test, so that the turbine expander reaches the maximum speed and maintains the turbine expander running stably at the maximum speed; The test ending steps include: After the turbine expander operates stably at the maximum speed for a period of time, the opening of the seventh regulating valve is gradually increased and the opening of the first regulating valve is reduced, so that the speed of the turbine expander is reduced, and finally the opening of the first regulating valve is 0; Set the openings of the second pressure reducing valve, the third regulating valve, the fourth regulating valve, the fifth regulating valve, and the sixth regulating valve to 0, and open the first stop valve to discharge the bearing gas in the bearing gas pipeline; Open the second stop valve to discharge the working gas in the turbine expander.

9. A method for testing the performance of a turbo expander according to claim 6, characterized in that: The test preparation step also includes: When the openings of the fifth regulating valve and the sixth regulating valve cannot reduce the pressure of the brake air intake pipeline, the third stop valve is opened to perform a venting operation on the brake air intake pipeline.

10. A method for testing the performance of a turbo expander according to claim 8, characterized in that: The static pressure operation test step also includes: The speed of the turbine expander is controlled by controlling the opening of the sixth regulating valve and the first regulating valve; The speed sensor is interlocked with the first regulating valve. When the speed of the turbine expander is too high, the opening of the first regulating valve is reduced. When the speed of the turbine expander is too low, the opening of the first regulating valve is increased. The first temperature sensor, the second temperature sensor and the first pressure sensor are interlocked with the fourth regulating valve. When the first temperature sensor and the second temperature sensor are significantly lower than the room temperature or the first pressure sensor is too high, the opening of the fourth regulating valve is increased.

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