Turbine component testing method and system

Abstract

The present invention relates to the field of ramjet turbine technology, and more specifically, to a turbine assembly testing method and system. The method includes step S10, based on the test requirements of the turbine assembly, detecting the assembly operating in a first operating condition; step S20, based on the temperature of the gas flowing through the third valve reaching a first set range, opening the intake valve of the intake unit and controlling the pressure unit to adjust to a set pressure; step S30, based on the intake valve being open and the pressure unit being adjusted to the set pressure, acquiring first test data for the turbine assembly; and step S40, based on the completion of acquiring the first test data, switching the detection assembly to a second operating condition. This solves the problem of how to improve the efficiency and gas utilization of turbine assembly testing.

Description

Technical Field

[0001] The present invention relates to the technical field of ram turbines, and in particular to a turbine component testing method and system. Background Art

[0002] Ram turbines are crucial energy harvesters for aircraft. They harness the energy of the aircraft's ram air during flight to propel turbine blades, which in turn spin the connected drive shaft at high speed, converting the kinetic energy of the air into mechanical energy. This in turn drives a generator or hydraulic pump to generate electrical or hydraulic energy. Using ram turbines for power generation is a key approach to addressing the growing power demands of high-Mach number aircraft and the limited capacity of generators.

[0003] A ramjet draws air from the main engine's intake duct to generate electrical energy. Its efficiency and output power not only affect the energy quality of onboard systems but also the engine's condition. Simple numerical analysis makes it difficult to assess the impact of a ramjet on an aircraft as a whole, and there are large errors. Experimental research at the whole-machine level is also costly and time-consuming. Currently, when testing the power generation performance of a turbine assembly (i.e., a ramjet), it is necessary to simulate the turbine assembly's power generation performance under various operating conditions in order to study and optimize the ramjet. Improving test efficiency and gas utilization has become a challenge. Summary of the Invention

[0004] In order to solve the problem of how to improve the efficiency and gas utilization rate of turbine component testing, the present invention provides a turbine component testing method and system.

[0005] In a first aspect, the present invention provides a turbine component testing method, the turbine component testing method comprising:

[0006] Step S10, based on the test requirements of the turbine assembly, detecting a first operating condition of the assembly; wherein the first operating condition includes the first heater and the second heater of the heating unit being started and heated to a first temperature threshold, the gas supply unit supplying gas at a first flow rate, and the temperature of the gas flowing through the third valve reaching a first set range;

[0007] Step S20, based on the temperature of the gas flowing through the third valve reaching the first set range, opening the intake valve of the intake unit and controlling the pressure unit to adjust to the set pressure;

[0008] Step S30, acquiring first test data of the turbine assembly based on the intake valve being opened and the pressure unit being adjusted to a set pressure;

[0009] Step S40, based on the completion of the acquisition of the first test data, the detection component switches to the second operating condition; wherein, the second operating condition includes the second heater being turned off, the third heater being started and heated to a second temperature threshold, the gas supply unit supplying gas at a second flow rate, and the temperature of the gas flowing through the third valve reaching a second set range; 0.6*B≤A≤B, A is the first setting range, B is the second setting range; 0.5*M≤N≤M, M is the first flow rate, and N is the second flow rate.

[0010] In some embodiments, step S10 includes:

[0011] Step S11, based on the test requirements of the turbine assembly, controlling the first heater and the second heater of the heating unit to heat to a first temperature threshold;

[0012] Step S12: controlling the gas supply unit to supply gas at a first flow rate based on the heating of the first heater and the second heater to a first temperature threshold;

[0013] Step S13, based on the gas supply unit supplying gas at the first flow rate, opening the first valve, the second valve, and the third valve and obtaining the temperature of the gas flowing through the third valve; wherein the heating unit includes the first heater, the second heater, the third heater, the first valve, the second valve, the third valve, a one-way valve, and a circulation pipe; the gas supply unit, the one-way valve, the first heater, the third heater, and the third valve are sequentially connected by pipelines; one end of the second valve is connected to the pipeline between the one-way valve and the first valve, and the other end is connected to the second heater; the end of the second heater away from the second valve is connected to the pipeline between the first heater and the third heater; one end of the circulation pipe is connected to the end of the third valve away from the third heater, and the other end is connected to the pipeline between the one-way valve and the second valve; the one-way valve blocks the gas from flowing to the gas supply unit;

[0014] Step S14: disconnecting the circulation pipe from the third valve based on the temperature of the gas flowing through the third valve reaching a first set range.

[0015] In some embodiments, step S11 further includes:

[0016] Step S15, based on the fact that the temperature of the gas flowing through the third valve is greater than the first set range, disconnect the circulation pipe from the third valve and open the temperature regulating valve; wherein, one end of the temperature regulating valve is connected to the end of the third valve away from the third heater, and the other end is connected to the pipeline between the one-way valve and the gas supply unit.

[0017] In some embodiments, step S30 includes:

[0018] Step S31, based on the air intake valve being opened and the pressure unit being adjusted to a set pressure, opening the exhaust valve of the cooling unit;

[0019] Step S32, based on the exhaust valve being opened, adjusting the openings of the exhaust valve and the intake valve to control the speed of the turbine assembly to reach a first set speed;

[0020] Step S33: acquiring first test data of the turbine assembly based on the rotation speed of the turbine assembly reaching a first set rotation speed.

[0021] In some embodiments, step S32 includes:

[0022] Step S321: Based on the exhaust valve being opened, starting the first cooler, the second cooler, and the circulation pump;

[0023] Step S322: Based on the start-up of the first cooler, the second cooler, and the circulation pump, the openings of the exhaust valve and the intake valve are adjusted to control the rotation speed of the turbine assembly to reach a first set rotation speed.

[0024] In some embodiments, step S40 includes:

[0025] Step S41: upon completion of acquiring the first test data, turning off the second heater and starting the third heater to heat the device to a second temperature threshold;

[0026] Step S42, based on the third heater heating to the second temperature threshold, controlling the gas supply unit to supply gas at a second flow rate and gradually reducing the opening of the intake valve;

[0027] Step S42, based on the gas supply unit supplying gas at the second flow rate and the opening of the air intake valve gradually decreasing to a set opening, obtaining the temperature of the gas flowing through the third valve;

[0028] Step S43: Based on the temperature of the gas flowing through the third valve reaching a second set range, adjusting the openings of the exhaust valve and the intake valve to control the speed of the turbine assembly to reach a second set speed; wherein 0.6*B≤A≤B, A is the first set range, B is the second set range; 0.5*M≤N≤M, M is the first flow rate, and N is the second flow rate;

[0029] Step S44 : acquiring second test data of the turbine assembly based on the rotation speed of the turbine assembly reaching a second set rotation speed.

[0030] In some embodiments, turning off the second heater in step S41 includes closing the second valve after the temperature of the second heater is lower than the first temperature threshold.

[0031] In some embodiments, the first test data in step S30 includes the gas temperature and gas pressure at both ends of the turbine assembly, the gas flow rate flowing through the turbine assembly, the speed and torque of the turbine assembly, and the current and voltage flowing through the resistance box of the electric energy unit.

[0032] In a second aspect, the present invention provides a turbine component testing system, which is applied to any one of the turbine component testing methods in the above embodiments, and includes:

[0033] Detection assembly, the detection assembly includes an air supply unit, a heating unit, a pressure unit, an air intake unit, an electric energy unit, and a stand unit; the air supply unit includes a compressor, an air valve, and a filter; the compressor, the air valve, and the filter are connected in sequence; the heating unit includes a first heater, a second heater, a third heater, a first valve, a second valve, a third valve, a one-way valve, and a circulation pipe; the filter, the one-way valve, the first heater, the third heater, and the third valve are connected in sequence through pipelines; one end of the second valve is connected to the pipeline between the one-way valve and the first valve, and the other end is connected to the second heater; an end of the second heater away from the second valve is connected to the pipeline between the first heater and the third heater; one end of the circulation pipe is connected to an end of the third valve away from the third heater, and the other end is connected to the pipeline between the one-way valve and the second valve; the one-way valve blocks the flow of gas to the air supply unit; the air intake unit includes an air intake valve and an air intake pipe; one end of the air intake valve is connected to an end of the third valve away from the third heater, and the other end is connected to the air intake pipe;

[0034] a turbine assembly, the turbine assembly being placed on the platform unit; one end of the turbine assembly being in communication with an end of the intake pipe away from the intake valve, and the other end being in communication with the pressure unit; the turbine assembly being in driving connection with the electric energy unit;

[0035] The detection component also includes a first operating condition and a second operating condition; the first operating condition includes the first heater and the second heater being started and heated to a first temperature threshold, the gas supply unit supplying gas at a first flow rate, and the temperature of the gas flowing through the third valve reaching a first set range; the second operating condition includes the second heater being turned off, the third heater being started and heated to a second temperature threshold, the gas supply unit supplying gas at a second flow rate, and the temperature of the gas flowing through the third valve reaching a second set range; 0.6*B≤A≤B, A is the first setting range, B is the second setting range; 0.5*M≤N≤M, M is the first flow rate, and N is the second flow rate.

[0036] In some embodiments, the detection component also includes a cooling unit and a lubricating oil unit; the cooling unit includes a first cooler, a second cooler, an exhaust valve, and a circulating pump; one end of the first cooler is connected to the external space through the exhaust valve, and the other end is connected to the pipeline between the third valve and the intake valve; the circulating pump is connected to the first cooler and the second cooler respectively; the second cooler is arranged on the pipeline between the turbine assembly and the pressure unit; the lubricating oil unit includes a lubricating oil pump and a lubricating oil tank; the lubricating oil pump, the lubricating oil tank, and the turbine assembly are connected in sequence to form a closed loop.

[0037] To solve the problem of how to improve the efficiency and gas utilization rate of turbine component testing, the present invention has the following advantages:

[0038] During the process of the detection component testing the turbine component, the test is divided into the first working condition and the second working condition, so that the test data of the turbine component under different working conditions can be obtained, and then its power generation performance can be obtained. At the same time, according to the specific working condition test sequence (testing the first working condition first, then testing the second working condition), considering that the first flow rate is greater than the second flow rate (the gas flow rate of the first working condition is greater than the gas flow rate of the second working condition), the first setting range is smaller than the second setting range (the gas temperature of the first working condition is lower than the gas temperature of the second working condition), when the second working condition is tested, the gas temperature can be heated to the required test temperature more quickly, thereby improving the test efficiency to a certain extent. At the same time, the large amount of low-temperature gas consumed due to cooling is avoided, so that the gas is mainly used for heating and testing, thereby improving gas utilization. BRIEF DESCRIPTION OF THE DRAWINGS

[0039] Figure 1 A schematic flow chart of a turbine component testing method according to an embodiment is shown;

[0040] Figure 2 A schematic diagram of a turbine component testing system according to an embodiment is shown.

[0041] Figure markings: 01 detection component; 11 air supply unit; 111 compressor; 112 air valve; 113 filter; 12 heating unit; 121 first heater; 122 first valve; 123 second heater; 124 second valve; 125 third heater; 126 third valve; 127 temperature regulating valve; 128 one-way valve; 129 circulation pipe; 13 cooling unit; 131 first cooler; 132 exhaust valve; 133 second cooler; 134 circulation pump; 14 lubricating oil unit; 141 lubricating oil pump; 142 lubricating oil tank; 15 electric energy unit; 151 generator; 152 controller; 153 resistance box; 16 pressure unit; 161 pressure tank; 162 pressure pump; 163 fourth valve; 164 fifth valve; 17 intake unit; 171 intake valve; 172 intake pipe; 18 test bench unit; 02 turbine assembly. DETAILED DESCRIPTION

[0042] The present disclosure will now be discussed with reference to several exemplary embodiments. It should be understood that these embodiments are discussed only to enable those skilled in the art to better understand and implement the present disclosure, rather than to imply any limitation on the scope of the present disclosure.

[0043] As used herein, the term "including" and its variations are to be interpreted as open-ended terms meaning "including, but not limited to." The term "based on" is to be interpreted as "based, at least in part, on." The terms "one embodiment" and "an embodiment" are to be interpreted as "at least one embodiment." The term "another embodiment" is to be interpreted as "at least one other embodiment." Terms such as "upper," "lower," "left," "right," "front," "back," "top," "bottom," "inner," "outer," "vertical," "horizontal," "transverse," and "longitudinal" indicate orientations or positional relationships based on the orientations or positional relationships shown in the accompanying drawings. These terms are primarily intended to better describe the present application and its embodiments and are not intended to limit the devices, elements, or components indicated to having a specific orientation, or to being constructed and operated in a specific orientation. Furthermore, some of the above terms may be used to indicate other meanings besides orientation or positional relationships. For example, the term "on" may, in certain circumstances, be used to indicate a dependency or connection relationship. Those skilled in the art will understand the specific meanings of these terms in this application based on the specific circumstances. Furthermore, the terms "installed," "disposed," "provided with," "connected," and "connected" are to be interpreted broadly. For example, it can be a fixed connection, a detachable connection, or an integral structure; it can be a mechanical connection, or an electrical connection; it can be directly connected, or indirectly connected through an intermediate medium, or it can be an internal connection between two devices, elements or components. For those of ordinary skill in the art, the specific meanings of the above terms in this application can be understood according to the specific circumstances. In addition, the terms "first", "second", etc. are mainly used to distinguish different devices, elements or components (the specific types and structures may be the same or different), and are not used to indicate or imply the relative importance and quantity of the indicated devices, elements or components. Unless otherwise specified, "plurality" means two or more.

[0044] In this embodiment, the turbine assembly 02 is subjected to simulation tests under different working conditions by the detection assembly 01, so that the test data of the turbine assembly 02 can be obtained to calculate the power generation performance parameters. How to improve the gas utilization rate and test efficiency during the test process becomes one of the problems that need to be solved. To this end, this embodiment discloses a test method for the turbine assembly 02, such as Figure 1 As shown, the turbine assembly 02 test method may include steps S10 to S40, which are described in detail below:

[0045] In step S10, based on the test requirements of turbine assembly 02, detection assembly 01 operates in a first operating condition. This first operating condition may include activating first heater 121 and second heater 123 of heating unit 12 and heating to a first temperature threshold, gas supply unit 11 supplying gas at a first flow rate, and gas temperature passing through third valve 126 reaching a first set range. This ensures that the temperature of the gas subsequently driving turbine assembly 02 meets the test requirements, thereby determining the power generation performance of turbine assembly 02 under the first operating condition. Before operating in the first operating condition, detection assembly 01 may initiate a self-test to verify that each unit is operating normally to avoid errors in subsequent testing.

[0046] In step S20, based on the temperature of the gas flowing through the third valve 126 reaching the first set range, the intake valve 171 of the intake unit 17 is opened and the pressure unit 16 is controlled to be adjusted to the set pressure; thereby, the pressure unit 16 can be used to simulate the output end of the aircraft's turbine component 02 being in a back pressure low pressure state, thereby improving the reliability of the test data.

[0047] Step S30, based on the intake valve 171 being opened and the pressure unit 16 being adjusted to the set pressure, obtain the first test data of the turbine assembly 02; the first test data may include the gas temperature, gas pressure, and gas flow at the input end of the turbine assembly 02, the gas temperature, gas pressure, speed, and torque at the output end of the turbine assembly 02, and the current and voltage of the resistor box 153 after the mechanical energy output by the turbine assembly 02 is converted into electrical energy through the generator 151 of the electrical energy unit 15, so as to obtain the power generation performance of the turbine assembly 02.

[0048] In step S40, upon completion of the acquisition of the first test data, the detection component 01 switches to the second operating condition. The second operating condition includes the second heater 123 being turned off, the third heater 125 being turned on and heated to a second temperature threshold, the gas supply unit 11 supplying gas at a second flow rate, and the temperature of the gas flowing through the third valve 126 reaching a second set range. The temperature range is 0.6*B≤A≤B, where A is the first set range and B is the second set range; and 0.5*M≤N≤M, where M is the first flow rate and N is the second flow rate. Because the second flow rate is less than the first flow rate and the second set range is greater than the first set range, the turbine component 02 test can be conducted under the first operating condition first, followed by the turbine component 02 test under the second operating condition. This allows the gas to be heated while flowing through the heating unit 12, thus avoiding waste of the extra low-temperature gas required for cooling. Furthermore, heating the gas heated under the first operating condition allows the gas to reach the test temperature required by the second operating condition more quickly, thereby improving test efficiency to a certain extent.

[0049] In this embodiment, step S10 may include:

[0050] Step S11, based on the test requirements of the turbine assembly 02, controls the first heater 121 and the second heater 123 of the heating unit 12 to heat to a first temperature threshold; that is, the first heater 121 and the second heater 123 are temporarily not fed with gas, and are preheated in advance, such as Figure 2 As shown, the first heater 121 and the second heater 123 can be connected in parallel through pipelines, and the type thereof can be an electric heating furnace.

[0051] In step S12, based on the first heater 121 and the second heater 123 being heated to the first temperature threshold, the gas supply unit 11 is controlled to supply gas at a first flow rate; thereby, the gas flowing through the first heater 121 and the second heater 123 can reach the temperature required by the test more quickly, thereby improving the test efficiency.

[0052] Step S13, based on the gas supply unit 11 supplying gas at a first flow rate, the first valve 122, the second valve 124, and the third valve 126 are opened and the temperature of the gas flowing through the third valve 126 is obtained; wherein, Figure 2 As shown, the heating unit 12 may include a first heater 121, a second heater 123, a third heater 125, a first valve 122, a second valve 124, a third valve 126, a one-way valve 128, and a circulation pipe 129; the gas supply unit 11, the one-way valve 128, the first heater 121, the third heater 125, and the third valve 126 are connected in sequence; one end of the second valve 124 is connected to the pipeline between the one-way valve 128 and the first valve 122, and the other end is connected to the second heater 123; the end of the second heater 123 away from the second valve 124 is connected to the first heater 121, the third heater 125, and the circulation pipe 129; The pipeline between the heat pump 121 and the third heater 125 is connected; one end of the circulation pipe 129 is connected to the end of the third valve 126 away from the third heater 125, and the other end is connected to the pipeline between the one-way valve 128 and the second valve 124; the one-way valve 128 can hinder the gas from flowing to the gas supply unit 11; so that when the gas temperature does not reach the first set range, the gas can flow back to the first heater 121 and the second heater 123 through the circulation pipe 129 and be heated again, thereby further improving the gas heating efficiency, avoiding gas energy waste, and improving gas utilization.

[0053] In step S14, based on the temperature of the gas flowing through third valve 126 reaching a first set range, the connection between circulation pipe 129 and third valve 126 is disconnected. This prevents the gas temperature from dropping due to the influence of circulation pipe 129 when the gas is input into turbine assembly 02, thereby preventing the first test data of turbine assembly 02 from being affected.

[0054] In this embodiment, step S11 may further include:

[0055] Step S15: Based on the fact that the temperature of the gas flowing through the third valve 126 is greater than the first set range, the connection between the circulation pipe 129 and the third valve 126 is disconnected and the temperature regulating valve 127 is opened; Figure 2 As shown, one end of the temperature regulating valve 127 is connected to the end of the third valve 126 away from the third heater 125, and the other end is connected to the pipeline between the one-way valve 128 and the gas supply unit 11. This allows the temperature regulating valve 127 to introduce cooler gas from the gas supply unit 11 to blend with the hotter gas flowing through the third valve 126 when the gas temperature rises too quickly due to the influence of the circulation pipe 129, thus preventing the gas temperature from being too high when subsequently input into the turbine assembly 02 and affecting the test results.

[0056] In this embodiment, step S30 includes:

[0057] In step S31, based on the air intake valve 171 being opened and the pressure unit 16 being adjusted to the set pressure, the exhaust valve 132 of the cooling unit 13 is opened; thereby, part of the gas can be discharged from the cooling unit 13 to the external space, so that the gas temperature is maintained within the first set range, thereby improving the reliability of the test data.

[0058] In step S32, based on the opening of the exhaust valve 132, the opening of the exhaust valve 132 and the intake valve 171 can be adjusted to control the speed of the turbine assembly 02 to reach the first set speed; thereby, the turbine assembly 02 can output mechanical energy to the electric energy unit 15 at different speeds, which is convenient for testing the power generation performance of the turbine assembly 02 at different speeds.

[0059] Step S33 : acquiring first test data of the turbine assembly 02 based on the rotation speed of the turbine assembly 02 reaching the first set rotation speed.

[0060] In this embodiment, step S32 includes:

[0061] Step S321 , based on the exhaust valve 132 being opened, the first cooler 131 , the second cooler 133 , and the circulation pump 134 are started;

[0062] In step S322, based on the activation of first cooler 131, second cooler 133, and circulating pump 134, the openings of exhaust valve 132 and intake valve 171 are adjusted to control the speed of turbine assembly 02 to a first set speed. This reduces the temperature of the exhaust gas through first cooler 131, and reduces the temperature of the gas discharged from the output end of turbine assembly 02 through second cooler 133, thereby preventing the exhaust gas temperature from being too high and affecting other components.

[0063] In this embodiment, step S40 includes:

[0064] Step S41 , based on the completion of the first test data acquisition, the second heater 123 is turned off and the third heater 125 is turned on to heat the gas to the second temperature threshold; thereby, the gas can be heated to the temperature required by the second operating condition test.

[0065] Step S42, based on the third heater 125 heating to the second temperature threshold, controls the gas supply unit 11 to supply gas at a second flow rate and the opening of the air intake valve 171 gradually decreases; at this time, the gas flow in the heating unit 12 decreases, and the gas flow input to the turbine assembly 02 gradually decreases, and the speed of the turbine assembly 02 can drop smoothly, reducing the impact of the sudden drop in gas flow on the turbine assembly 02.

[0066] In step S42, based on the gas supply unit 11 supplying gas at a second flow rate and the opening of the air inlet valve 171 gradually decreasing to the set opening, the temperature of the gas flowing through the third valve 126 is obtained; at this time, a small amount of gas still flows through the turbine assembly 02, so that the turbine assembly 02 maintains a low speed rotation, so that when the subsequent gas temperature is heated to the second set range and then input into the turbine assembly 02, the turbine assembly 02 can quickly increase the speed to the second set speed for testing, thereby improving the test efficiency.

[0067] Step S43: Based on the temperature of the gas flowing through the third valve 126 reaching the second set range, the openings of the exhaust valve 132 and the intake valve 171 are adjusted to control the speed of the turbine assembly 02 to reach the second set speed; wherein 0.6*B≤A≤B, A is the first set range, B is the second set range; 0.5*M≤N≤M, M is the first flow rate, and N is the second flow rate;

[0068] In step S44, second test data of turbine assembly 02 is obtained based on the rotational speed of turbine assembly 02 reaching the second set rotational speed. Through these steps, detection assembly 01 can smoothly switch from the first operating condition to the second operating condition to test turbine assembly 02, thereby reducing the impact on turbine assembly 02 caused by drastic changes in gas flow and temperature, and ensuring the reliability of the test results.

[0069] In this embodiment, turning off the second heater 123 in step S41 may include closing the second valve 124 after the temperature of the second heater 123 is less than the first temperature threshold. During the process of switching the detection component 01 from the first working condition to the second working condition, the second valve 124 can be maintained open after the second heater 123 is turned off, so that part of the gas supplied to the heating unit by the gas supply unit 11 can exchange heat with the second heater 123, taking away its heat to improve energy utilization, so that the gas heats up faster. The second valve 124 can be closed when the temperature of the second heater 123 drops below the first temperature threshold. In other embodiments, after the second valve 124 is closed, the third valve 126 can be connected to the circulation pipe 129, so that the gas is circulated and heated in the heating unit 12, so that the gas can reach the required test temperature faster, thereby improving the test efficiency.

[0070] In this embodiment, the first test data in step S30 may include the gas temperature and pressure at both ends of turbine assembly 02, the gas flow rate through turbine assembly 02, the speed and torque of turbine assembly 02, and the current and voltage flowing through resistor box 153 of power unit 15. The second test data can also obtain the above parameters, thereby determining the power generation performance of turbine assembly 02 under different operating conditions and improving the reliability of the test.

[0071] In this embodiment, if Figure 2As shown, this embodiment discloses a turbine component 02 test system, and the turbine component 02 test system is applied to any of the turbine component 02 test methods in the above embodiments. The turbine component 02 test system may include: a detection component 01, a turbine component 02. The detection component 01 may include an air supply unit 11, a heat supply unit 12, a pressure unit 16, an air intake unit 17, an electric energy unit 15, and a test bench unit 18; the air supply unit 11 includes a compressor 111, an air valve 112, and a filter 113; the compressor 111, the air valve 112, and the filter 113 are connected in sequence; thus, the compressor 111 can compress the gas and output the set flow rate of gas, so that the gas pressure and flow rate meet the test requirements, and the filter 113 can filter foreign matter in the gas to prevent foreign matter in the gas from causing damage to the turbine component 02 test system. The heating unit 12 includes a first heater 121, a second heater 123, a third heater 125, a first valve 122, a second valve 124, a third valve 126, a one-way valve 128, and a circulation pipe 129; the filter 113, the one-way valve 128, the first heater 121, the third heater 125, and the third valve 126 are connected in sequence through pipelines; one end of the second valve 124 is connected to the pipeline between the one-way valve 128 and the first valve 122, and the other end is connected to the second heater 123; the end of the second heater 123 away from the second valve 124 is connected to the pipeline between the first heater 121 and the third heater 125; thereby, the heating unit 12 can simulate the gas temperature under various working conditions and improve the test requirements of the turbine component 02. One end of the circulation pipe 129 is connected to the end of the third valve 126 away from the third heater 125, and the other end is connected to the pipeline between the one-way valve 128 and the second valve 124; thereby, the gas can be circulated and heated in the heating unit 12 through the circulation pipe 129, thereby improving the gas utilization rate and facilitating the rapid heating of the gas. The one-way valve 128 blocks the flow of gas to the gas supply unit 11; thereby, it is possible to prevent high-temperature gas from flowing back into the gas supply unit 11 and causing damage to the equipment. The air intake unit 17 includes an air intake valve 171 and an air intake pipe 172; one end of the air intake valve 171 is connected to the end of the third valve 126 away from the third heater 125, and the other end is connected to the air intake pipe 172; thereby, the gas flow input to the turbine assembly 02 can be controlled by adjusting the opening of the air intake valve 171, thereby controlling the speed change of the turbine assembly 02, so as to obtain multiple sets of data through testing.

[0072] Turbine assembly 02 is placed on test bench unit 18. One end of turbine assembly 02 is connected to the end of intake pipe 172 away from intake valve 171, and the other end is connected to pressure unit 16. Intake pipe 172 can be made of a high-temperature resistant metal hose to accommodate turbine assemblies 02 of varying heights. Pressure unit 16 can simulate the backpressure and low-pressure conditions at the output of turbine assembly 02, improving the reliability of test data. Turbine assembly 02 is connected to power unit 15, allowing the mechanical energy output by turbine assembly 02 to be converted into electrical energy through power unit 15.

[0073] The detection component 01 also includes a first operating condition and a second operating condition; the first operating condition includes the first heater 121 and the second heater 123 being started and heated to a first temperature threshold, the gas supply unit 11 supplying gas at a first flow rate, and the temperature of the gas flowing through the third valve 126 reaching a first set range; the second operating condition includes the second heater 123 being turned off, the third heater 125 being started and heated to a second temperature threshold, the gas supply unit 11 supplying gas at a second flow rate, and the temperature of the gas flowing through the third valve 126 reaching a second set range; 0.6*B≤A≤B, A is the first setting range, B is the second setting range; 0.5*M≤N≤M, M is the first flow rate, and N is the second flow rate.

[0074] In other embodiments, the pressure unit 16 may include a pressure tank 161, a pressure pump 162, a fourth valve 163, and a fifth valve 164. One end of the pressure tank 161 is connected to the end of the turbine assembly 02 away from the intake valve 171 (i.e., the output end of the turbine assembly 02) through a pipeline, and the other end is connected to the pressure pump 162 through the fourth valve 163, so that the pressure pump 162 can suck the gas in the pressure tank 161, so that the output end of the turbine assembly 02 forms a back pressure low pressure condition. The pressure tank 161 can be connected to the external space through the fifth valve 164. The power unit 15 may include a generator 151, a controller 152, and a resistor box 153. One end of the generator 151 is drive-connected to the output end of the turbine assembly 02, and the other end is electrically connected to the resistor box 153, so that the mechanical energy generated by the rotation of the turbine assembly 02 can be converted into electrical energy and input into the resistor box 153. The controller 152 is signal-connected to the generator 151.

[0075] In this embodiment, if Figure 2As shown, the detection component 01 can also include a cooling unit 13 and a lubricating oil unit 14. The cooling unit 13 includes a first cooler 131, a second cooler 133, an exhaust valve 132, and a circulating pump 134. One end of the first cooler 131 is connected to the external space through the exhaust valve 132, and the other end is connected to the pipeline between the third valve 126 and the intake valve 171. This allows the gas discharged from the heating unit 12 to be cooled and discharged to the external space, preventing the gas temperature from being too high and causing damage to the equipment. The circulating pump 134 is connected to the first cooler 131 and the second cooler 133 respectively. The second cooler 133 is set in the pipeline between the turbine component 02 and the pressure unit 16. This allows it to exchange heat with the gas in the pipeline, remove the heat from the gas, and prevent the gas discharged from the turbine component 02 from affecting the operation of the pressure unit 16. The lubricating oil unit 14 includes a lubricating oil pump 141 and a lubricating oil tank 142 ; the lubricating oil pump 141 , the lubricating oil tank 142 and the turbine assembly 02 are connected in sequence to form a closed loop, thereby lubricating and cooling the turbine assembly 02 to prevent the turbine assembly 02 from overheating during rotation.

[0076] Those skilled in the art will appreciate that the above-mentioned embodiments are specific examples for implementing the present disclosure, and that in actual applications, various changes may be made thereto in form and detail without departing from the spirit and scope of the present disclosure.

Claims

1. A turbine component testing method, characterized in that: The turbine assembly test method includes: Step S10, based on the test requirements of the turbine component, detecting the first operating condition of the component; wherein, the first operating condition includes the first heater and the second heater of the heating unit being started and heated to a first temperature threshold, the gas supply unit supplying gas at a first flow rate, and the temperature of the gas flowing through the third valve reaching a first set range; the heating unit includes the first heater, the second heater, the third heater, the first valve, the second valve, the third valve, a one-way valve and a circulation pipe; the gas supply unit, the one-way valve, the first heater, the third heater and the third valve are connected in sequence by pipelines; one end of the second valve is connected to the pipeline between the one-way valve and the first valve, and the other end is connected to the second heater; the end of the second heater away from the second valve is connected to the pipeline between the first heater and the third heater; one end of the circulation pipe is connected to the end of the third valve away from the third heater, and the other end is connected to the pipeline between the one-way valve and the second valve; the one-way valve blocks the flow of gas to the gas supply unit; Step S20, based on the temperature of the gas flowing through the third valve reaching the first set range, opening the intake valve of the intake unit and controlling the pressure unit to adjust to the set pressure; Step S30: Acquiring first test data of the turbine assembly based on the intake valve being opened and the pressure unit being adjusted to a set pressure; the first test data including the gas temperature and gas pressure at both ends of the turbine assembly, the gas flow rate flowing through the turbine assembly, the speed and torque of the turbine assembly, and the current and voltage flowing through the resistance box of the electric energy unit; Step S40: Based on the completion of the acquisition of the first test data, the detection component switches to a second operating condition; wherein the second operating condition includes the second heater being turned off, the third heater being turned on and heated to a second temperature threshold, the gas supply unit supplying gas at a second flow rate, and the temperature of the gas flowing through the third valve reaching a second set range; 0.6*B≤A≤B, where A is the first set range and B is the second set range; and 0.5*M≤N≤M, where M is the first flow rate and N is the second flow rate. Step S50, based on the temperature of the gas flowing through the third valve reaching a second set range, adjusting the openings of the exhaust valve and the intake valve to control the speed of the turbine assembly to reach a second set speed; wherein 0.6*B≤A≤B, A is the first set range, B is the second set range; 0.5*M≤N≤M, M is the first flow rate, and N is the second flow rate; Step S60 : acquiring second test data of the turbine assembly based on the rotation speed of the turbine assembly reaching a second set rotation speed.

2. A turbine component testing method according to claim 1, characterized in that: The step S10 includes: Step S11, based on the test requirements of the turbine assembly, controlling the first heater and the second heater of the heating unit to heat to a first temperature threshold; Step S12: controlling the gas supply unit to supply gas at a first flow rate based on the heating of the first heater and the second heater to a first temperature threshold; Step S13, based on the gas supply unit supplying gas at the first flow rate, opening the first valve, the second valve, and the third valve and obtaining the temperature of the gas flowing through the third valve; Step S14: disconnecting the circulation pipe from the third valve based on the temperature of the gas flowing through the third valve reaching a first set range.

3. A turbine component testing method according to claim 2, characterized in that: The step S10 further includes: Step S15, based on the fact that the temperature of the gas flowing through the third valve is greater than the first set range, disconnect the circulation pipe from the third valve and open the temperature regulating valve; wherein, one end of the temperature regulating valve is connected to the end of the third valve away from the third heater, and the other end is connected to the pipeline between the one-way valve and the gas supply unit.

4. A turbine component testing method according to claim 1, characterized in that: The step S30 includes: Step S31, based on the air intake valve being opened and the pressure unit being adjusted to a set pressure, opening the exhaust valve of the cooling unit; Step S32, based on the exhaust valve being opened, adjusting the openings of the exhaust valve and the intake valve to control the speed of the turbine assembly to reach a first set speed; Step S60 : acquiring first test data of the turbine assembly based on the rotation speed of the turbine assembly reaching a first set rotation speed.

5. A turbine component testing method according to claim 4, characterized in that: The step S32 includes: Step S321: Based on the exhaust valve being opened, starting the first cooler, the second cooler, and the circulating pump; the cooling unit includes the first cooler, the second cooler, the exhaust valve, and the circulating pump; one end of the first cooler is connected to the external space through the exhaust valve, and the other end is connected to the pipeline between the third valve and the intake valve; the circulating pump is connected to the first cooler and the second cooler respectively; the second cooler is provided in the pipeline between the turbine assembly and the pressure unit; Step S322: Based on the start-up of the first cooler, the second cooler, and the circulation pump, the openings of the exhaust valve and the intake valve are adjusted to control the rotation speed of the turbine assembly to reach a first set rotation speed.

6. A turbine component testing method according to claim 1, characterized in that: The step S40 includes: Step S41: upon completion of acquiring the first test data, turning off the second heater and starting the third heater to heat the device to a second temperature threshold; Step S42, based on the third heater heating to the second temperature threshold, controlling the gas supply unit to supply gas at a second flow rate and gradually reducing the opening of the intake valve; Step S43 : Based on the gas supply unit supplying gas at the second flow rate and the opening of the intake valve gradually decreasing to a set opening, the temperature of the gas flowing through the third valve is acquired.

7. A turbine component testing method according to claim 6, characterized in that: Turning off the second heater in step S41 includes closing the second valve after the temperature of the second heater is lower than the first temperature threshold.

8. A turbine component testing system, wherein the turbine component testing system is applied to a turbine component testing method according to any one of claims 1 to 7, characterized in that: The turbine component test system includes: a detection assembly comprising an air supply unit, a heating unit, a pressure unit, an air intake unit, an electric energy unit and a stand unit; the air supply unit comprising a compressor, an air valve and a filter; the compressor, the air valve and the filter being connected in sequence; the heating unit comprising a first heater, a second heater, a third heater, a first valve, a second valve, a third valve, a one-way valve and a circulation pipe; the filter, the one-way valve, the first heater, the third heater and the third valve being connected in sequence through pipelines; one end of the second valve being connected to a pipeline between the one-way valve and the first valve, and the other end being connected to the second heater; an end of the second heater away from the second valve being connected to a pipeline between the first heater and the third heater; one end of the circulation pipe being connected to an end of the third valve away from the third heater, and the other end being connected to a pipeline between the one-way valve and the second valve; the one-way valve obstructs the flow of gas to the air supply unit; the air intake unit comprising an air intake valve and an air intake pipe; one end of the air intake valve being connected to an end of the third valve away from the third heater, and the other end being connected to the air intake pipe; a turbine assembly, the turbine assembly being placed on the platform unit; one end of the turbine assembly being in communication with an end of the intake pipe away from the intake valve, and the other end being in communication with the pressure unit; the turbine assembly being in driving connection with the electric energy unit; The detection component also includes a first operating condition and a second operating condition; the first operating condition includes the first heater and the second heater being started and heated to a first temperature threshold, the gas supply unit supplying gas at a first flow rate, and the temperature of the gas flowing through the third valve reaching a first set range; the second operating condition includes the second heater being turned off, the third heater being started and heated to a second temperature threshold, the gas supply unit supplying gas at a second flow rate, and the temperature of the gas flowing through the third valve reaching a second set range; 0.6*B≤A≤B, A is the first setting range, B is the second setting range; 0.5*M≤N≤M, M is the first flow rate, and N is the second flow rate.

9. A turbine component testing system according to claim 8, characterized in that: The detection component also includes a cooling unit and a lubricating oil unit; the cooling unit includes a first cooler, a second cooler, an exhaust valve and a circulating pump; one end of the first cooler is connected to the external space through the exhaust valve, and the other end is connected to the pipeline between the third valve and the intake valve; the circulating pump is connected to the first cooler and the second cooler respectively; the second cooler is arranged on the pipeline between the turbine assembly and the pressure unit; the lubricating oil unit includes a lubricating oil pump and a lubricating oil tank; the lubricating oil pump, the lubricating oil tank and the turbine assembly are connected in sequence to form a closed loop.

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