Turbine assembly test method and system

Abstract

The invention relates to the technical field of stamping turbines, in particular to a turbine assembly test method and system. The method comprises the steps that S10, based on the test requirement of the turbine assembly, the assembly is detected to run in a first working condition; s20, based on the fact that the temperature of gas flowing through a third valve reaches a first set range, an air inlet valve of an air inlet unit is opened, and a pressure unit is controlled to be adjusted to set pressure; s30, acquiring first test data of the turbine assembly on the basis that the air inlet valve is opened and the pressure unit is adjusted to the set pressure; and S40, on the basis of completion of acquisition of the first test data, the detection assembly is switched to the second working condition. Therefore, the problem of how to improve the efficiency of the turbine assembly test and the gas utilization rate is solved.

Description

Technical Field

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

[0002] The ramjet turbine is an important energy acquisition device for aircraft. It uses the energy of the ram air of the aircraft in flight to blow the turbine blades to rotate, driving the connected transmission shaft to rotate at high speed, converting the kinetic energy of the gas into mechanical energy, thereby driving the generator or hydraulic pump to output electrical energy or hydraulic energy. Using ramjet turbines to generate electricity is a key way for high Mach number aircraft to solve the contradiction between the growing electricity demand and the limited capacity of generators.

[0003] The ramjet turbine can draw air from the main engine's air intake and then perform work to output electrical energy. Its efficiency and output power will not only affect the energy quality of the onboard system, but also have an impact on the state of the engine. Simple numerical analysis is difficult to evaluate the impact of the ramjet turbine on the aircraft as a whole, and there are large errors. The cost of whole-machine-level experimental research is too high and the cycle is long. At present, when testing the power generation performance of the turbine assembly (i.e., the ramjet turbine), the detection component needs to simulate the power generation performance of the turbine assembly under various working conditions in order to study and optimize the ramjet turbine. How to improve the efficiency of the test and the gas utilization rate has become one of the problems that need to be solved. 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 component, detecting a 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;

[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, based on the first heater and the second heater both being heated to a first temperature threshold, controlling the gas supply unit to supply gas at a first flow rate;

[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 comprises 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; one 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 one 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, based on the temperature of the gas flowing through the third valve reaching a first set range, disconnecting the circulation pipe from the third valve.

[0015] In some embodiments, the 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 an end of the third valve away from the third heater, and the other end is connected to the one-way valve and the pipeline between the gas supply unit.

[0017] In some embodiments, step S30 includes:

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

[0019] Step S32, based on the exhaust valve opening, 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 circulating pump, adjust the opening of the exhaust valve and the intake valve 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, based on the completion of acquiring the first test data, turning off the second heater and starting the third heater to heat 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 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, 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 less 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 test system, the turbine component test system is applied to any one of the turbine component test methods in the above embodiments, and the turbine component test system comprises:

[0033] A detection component, the detection component 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; one 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 one 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 one 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 is placed on the bench unit; one end of the turbine assembly is connected to an end of the intake pipe away from the intake valve, and the other end is connected to the pressure unit; the turbine assembly is drivingly connected to 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 setting 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 setting 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 third valve and the pipeline between 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] In order 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] In 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 (first test the first working condition, then test 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 less 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 up to the required test temperature faster, which improves the test efficiency to a certain extent. At the same time, it avoids the large amount of low-temperature gas consumed due to cooling, so that the gas is mainly used for heating and testing, thereby improving the gas utilization rate. BRIEF DESCRIPTION OF THE DRAWINGS

[0039] Figure 1 A schematic diagram 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 numerals: 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 component. 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 thus implement the present disclosure, rather than implying any limitation on the scope of the present disclosure.

[0043] As used herein, the term "including" and its variants 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". The orientation or position relationship indicated by the terms "upper", "lower", "left", "right", "front", "back", "top", "bottom", "inner", "outer", "vertical", "horizontal", "lateral", "longitudinal" and the like is based on the orientation or position relationship shown in the accompanying drawings. These terms are mainly for better describing the present application and its embodiments, and are not used to limit the indicated devices, elements or components to have a specific orientation, or to be constructed and operated in a specific orientation. In addition, in addition to being used to indicate an orientation or position relationship, some of the above terms may also be used to indicate other meanings, such as the term "upper" may also be used to indicate a certain dependency or connection relationship in some cases. For those of ordinary skill in the art, the specific meanings of these terms in this application can be understood according to the specific circumstances. In addition, the terms "install", "set", "provided with", "connected" and "connected" should be understood in a broad sense. 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 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, and the above steps may be described in detail below:

[0045] Step S10, based on the test requirements of the turbine assembly 02, the detection assembly 01 operates in the first operating condition; wherein the first operating condition may include the first heater 121 and the second heater 123 of the heating unit 12 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; thereby, the temperature of the gas driving the turbine assembly 02 to rotate subsequently can meet the test requirements, so as to obtain the power generation performance of the turbine assembly 02 under the first operating condition. Before the detection assembly 01 operates in the first operating condition, the detection assembly 01 can start self-test to check whether the operation of each unit is normal to avoid errors in subsequent tests.

[0046] 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 facilitating the improvement of the reliability of the test data.

[0047] Step S30, based on the air 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, rotation 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 electric energy unit 15, so as to obtain the power generation performance of the turbine assembly 02.

[0048] Step S40, based on the completion of the acquisition of the first test data, the detection component 01 switches to the second working condition; wherein the second working condition includes the second heater 123 being turned off, the third heater 125 being started and heated to the second temperature threshold, the gas supply unit 11 supplying gas at the second flow rate, and the temperature of the gas flowing through the third valve 126 reaching the second setting 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. Since the second flow rate is less than the first flow rate, and the second setting range is greater than the first setting range, the order of first conducting the turbine component 02 test under the first working condition and then conducting the turbine component 02 test under the second working condition can be followed, so that the gas is in a state of heating up during the process of flowing through the heating unit 12, avoiding the waste of the low-temperature gas consumed extra due to cooling, and at the same time, heating the gas heated by the first working condition can enable the gas to reach the test temperature required by the second working condition more quickly, thereby improving the 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, the first heater 121 and the second heater 123 of the heating unit 12 are controlled 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 check valve 128, and a circulation pipe 129; the gas supply unit 11, the check valve 128, the first heater 121, the third heater 125, and the third valve 126 are connected in sequence by pipelines; one end of the second valve 124 is connected to the pipeline between the check 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 The pipeline between the heat unit 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 for reheating, which can further improve the gas heating efficiency, avoid gas energy waste, and improve gas utilization.

[0053] Step S14, based on the temperature of the gas flowing through the third valve 126 reaching the first set range, disconnect the circulation pipe 129 from the third valve 126. This can prevent the gas temperature from dropping due to the influence of the circulation pipe 129 when the gas is input into the turbine assembly 02, and prevent the first test data of the 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, disconnect the circulation pipe 129 from the third valve 126 and open the temperature regulating valve 127; wherein, 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 one-way valve 128 and the pipeline between the gas supply unit 11. Therefore, when the gas temperature rises too fast due to the influence of the circulation pipe 129 and exceeds the first set range, the temperature regulating valve 127 can introduce a lower temperature gas from the gas supply unit 11 to reconcile with the high temperature gas flowing through the third valve 126, so as to avoid the subsequent gas temperature input to the turbine assembly 02 being too high and affecting the test results.

[0056] In this embodiment, step S30 includes:

[0057] 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] 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 a 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, based on the rotation speed of the turbine assembly 02 reaching the first set rotation speed, first test data of the turbine assembly 02 is obtained.

[0060] In this embodiment, step S32 includes:

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

[0062] Step S322, based on the start-up of the first cooler 131, the second cooler 133, and the circulating pump 134, the opening of the exhaust valve 132 and the intake valve 171 are adjusted to control the speed of the turbine assembly 02 to reach the first set speed. Thus, the exhaust gas temperature can be reduced by the first cooler 131, and the exhaust gas temperature at the output end of the turbine assembly 02 can be reduced by the second cooler 133, thereby avoiding the exhaust gas temperature being too high to affect other components.

[0063] In this embodiment, step S40 includes:

[0064] Step S41, based on the completion of the acquisition of the first test data, the second heater 123 is turned off and the third heater 125 is started to heat 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 rotation 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] Step S42, based on the air supply unit 11 supplying gas at a second flow rate and the opening of the intake 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, adjusting the opening of the exhaust valve 132 and the intake valve 171 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, N is the second flow rate;

[0068] Step S44, based on the rotation speed of the turbine component 02 reaching the second set rotation speed, obtain the second test data of the turbine component 02. Through the above steps, the detection component 01 can be switched from the first working condition to the second working condition to test the turbine component 02 more smoothly, which can reduce the impact of the drastic changes in gas flow and temperature on the turbine component 02 to a certain extent, and ensure the reliability of the test results.

[0069] In this embodiment, closing 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 may be maintained open after closing the second heater 123, 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 may 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 and the circulation pipe 129 may be connected, 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 gas pressure at both ends of the turbine assembly 02, the gas flow rate flowing through the turbine assembly 02, the speed and torque of the turbine assembly 02, and the current and voltage flowing through the resistor box 153 of the power unit 15. The second test data may also obtain the above parameters, so as to obtain the power generation performance of the turbine assembly 02 under different working conditions and improve 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 one 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 the 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; thus, 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 gas from flowing to the gas supply unit 11; thus, it can be prevented that the high-temperature gas flows back to the gas supply unit 11 and causes equipment damage. 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; thus, the gas flow rate input to the turbine assembly 02 can be controlled by adjusting the opening of the air intake valve 171, and the speed change of the turbine assembly 02 can be controlled, so as to obtain multiple sets of data through experiments.

[0072] The turbine assembly 02 is placed on the test bench unit 18. One end of the turbine assembly 02 is connected to the end of the intake pipe 172 away from the intake valve 171, and the other end is connected to the pressure unit 16; the intake pipe 172 can use a high-temperature resistant metal hose to adapt to turbine assemblies 02 of different heights, and the pressure unit 16 can simulate the back pressure and low pressure conditions at the output end of the turbine assembly 02, so that the reliability of the test data is improved. The turbine assembly 02 is connected to the electric energy unit 15; so that the mechanical energy output by the turbine assembly 02 is converted into electrical energy through the electric energy 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 connected to the output end of the turbine assembly 02 by driving, 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 connected to the generator 151 by signal.

[0075] In this embodiment, if Figure 2As shown, the detection component 01 may 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; thereby, the gas discharged from the heating unit 12 can be discharged to the external space after cooling, so as to avoid damage to the equipment caused by excessive gas temperature. The circulating pump 134 is connected to the first cooler 131 and the second cooler 133 respectively; the second cooler 133 is arranged on the pipeline between the turbine component 02 and the pressure unit 16; thereby, it can exchange heat with the gas in the pipeline, take away the heat of 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 sequentially connected to form a closed loop, so that the turbine assembly 02 can be lubricated and cooled 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 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 component test method includes: Step S10, based on the test requirements of the turbine component, detecting a 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; 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; 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.

2. A turbine component testing method according to claim 1, characterized in that: The step S10 comprises: 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, based on the first heater and the second heater both being heated to a first temperature threshold, controlling the gas supply unit to supply gas at a first flow rate; 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 comprises 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; one 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 one 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; Step S14, based on the temperature of the gas flowing through the third valve reaching a first set range, disconnecting the circulation pipe from the third valve.

3. A turbine component testing method according to claim 2, characterized in that: The step S11 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 an end of the third valve away from the third heater, and the other end is connected to the one-way valve and the pipeline between the gas supply unit.

4. A turbine component testing method according to claim 1, characterized in that: The step S30 comprises: Step S31, opening the exhaust valve of the cooling unit based on the intake valve being opened and the pressure unit being adjusted to a set pressure; Step S32, based on the exhaust valve opening, 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 S33: 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 comprises: Step S321, based on the exhaust valve being opened, starting the first cooler, the second cooler, and the circulation pump; Step S322, based on the start-up of the first cooler, the second cooler, and the circulating pump, adjust the opening of the exhaust valve and the intake valve 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 comprises: Step S41, based on the completion of acquiring the first test data, turning off the second heater and starting the third heater to heat 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 S42, 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, obtaining the temperature of the gas flowing through the third valve; 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, N is the second flow rate; 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.

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 method according to claim 1, characterized in that: 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 rotation speed and torque of the turbine assembly, and the current and voltage flowing through the resistance box of the power unit.

9. A turbine component testing system, the turbine component testing system being applied to a turbine component testing method as claimed in any one of claims 1 to 8, characterized in that: The turbine component test system includes: A detection component, the detection component 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; one 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 one 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 one end of the third valve away from the third heater, and the other end is connected to the air intake pipe; A turbine assembly, the turbine assembly is placed on the bench unit; one end of the turbine assembly is connected to an end of the intake pipe away from the intake valve, and the other end is connected to the pressure unit; the turbine assembly is drivingly connected to 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 setting 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 setting 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.

10. A turbine component testing system according to claim 9, 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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