Creep test system of turbine rotor blade film hole simulation piece and test method thereof

Abstract

The invention discloses a creep test system of a turbine rotor blade film hole simulation piece and a test method of the creep test system. Comprising a clamping assembly used for fixing a test piece, a loading assembly used for applying a load to the test piece, a strain measuring assembly used for measuring the strain rate of the test piece, a heating assembly used for covering the test piece to form a heating channel, and a cooling assembly used for manufacturing and conveying cooling airflow to flow through the interior of the test piece, the strain measurement assembly is used for measuring the external temperature of the test piece and the internal temperature of the test piece, the control assembly is connected with the strain measurement assembly, the heating assembly, the cooling assembly and the temperature measurement assembly, and the heating assembly is used for manufacturing and conveying high-temperature airflow to flow through the heating channel so as to heat the outside of the test piece to a first set temperature; the cooling assembly is used for cooling the interior of the test piece to a second set temperature, and the heating assembly and the cooling assembly are used for forming a dynamic convection environment around the test piece.

Description

TECHNICAL FIELD

[0001] The present application relates to the technical field of aero-engines, in particular, to a creep test system for a turbine rotor blade film hole simulation piece. Furthermore, the present application also relates to a creep test method for a turbine rotor blade film hole simulation piece. BACKGROUND

[0002] In an aero-engine, the turbine rotor blade is one of the key hot-end components of the aero-engine, and its performance and reliability will directly affect the overall performance and safe operation of the aero-engine. With the continuous development of aero-engine technology, the design requirements for turbine rotor blades are also becoming higher and higher. The turbine rotor blade is in a harsh environment of high temperature, high pressure and high speed during operation, and bears various loads such as centrifugal force, aerodynamic force and thermal stress. In order to improve the high-temperature resistance of the turbine rotor blade, a film hole is usually designed on the blade body, and a thermal barrier coating is coated on the surface of the blade. The thermal barrier coating is a special multilayer ceramic composite coating, mainly used to reduce the heat transfer between the material and the environment at high temperature, to improve its high-temperature resistance. The thermal barrier coating uses a material with low thermal conductivity, which can effectively insulate the high-temperature gas, so that the temperature of the turbine blade is lower than that of the gas, effectively prolonging the service life of the blade. When the thermal barrier coating falls off, the blade substrate is exposed to high-temperature gas, thereby reducing the service life of the blade.

[0003] In actual engineering applications, the thermal barrier coating on the surface of the turbine rotor blade is subjected to extreme non-isothermal tests. The turbine rotor blade surface directly contacts high-temperature gas, while the internal cooling channel reduces the temperature by several hundred degrees through cold gas, forming a significant internal and external temperature difference. This non-isothermal temperature field not only accelerates the accumulation of thermal stress between the thermal barrier coating and the substrate, but also may cause coating peeling, crack propagation and other failure behaviors. In order to realize the coupling effect of high-temperature creep loading and gradient temperature field, and to provide more test conditions close to the actual working conditions for the creep test of the film hole simulation piece. For example, Chinese invention patent CN115420481A discloses an aero-engine turbine blade thermal mechanical fatigue wall thickness direction non-uniform temperature field debugging method, which can determine the cooling gas mass flow rate after determining the turbine blade outer wall surface examination temperature requirement, so that the inner wall surface examination temperature also meets the requirements of the wall thickness direction non-uniform temperature field debugging method.

[0004] However, in the above debugging method, the heating subsystem includes an induction coil and a high-frequency induction heating furnace, i.e. static radiation heating is performed by a high-frequency induction high-heat furnace. This heating method makes the temperature distribution of the simulation piece uniform, and cannot simulate the dynamic convection environment of the turbine rotor blade. It lacks the turbulent flow and thermal shock effect in the real working conditions, ignores the influence of external gas scouring on the creep life, and leads to low verification accuracy of the test results on the creep life of the turbine rotor blade film hole position. SUMMARY

[0005] The present application provides a creep test system for turbine rotor blade film hole simulators and a test method thereof, to solve the technical problem of low verification accuracy of the creep test results of turbine rotor blade film hole simulators on the creep life of turbine rotor blade film hole parts.

[0006] According to one aspect of the present application, a creep test system for turbine rotor blade film hole simulators is provided, comprising a clamping assembly for fixing a test piece, a loading assembly for applying a load to the test piece, a strain measurement assembly for measuring the strain rate of the test piece, a heating assembly for covering the test piece to form a heating channel, a cooling assembly for manufacturing and delivering a cooling gas flow through the inside of the test piece, a temperature measurement assembly for measuring the outside temperature of the test piece and the inside temperature of the test piece, and a control assembly connected with the strain measurement assembly, the heating assembly, the cooling assembly and the temperature measurement assembly respectively, the heating assembly is used to manufacture and deliver a high-temperature gas flow through the heating channel to heat the outside of the test piece to a first set temperature, the cooling assembly is used to cool the inside of the test piece to a second set temperature, the heating assembly and the cooling assembly are used to form a dynamic convection environment around the test piece, and the control assembly is used to control the flow of the cooling gas flow delivered by the cooling assembly according to the measurement result of the strain rate to maintain the strain rate stable, and control the operation of the heating assembly and the cooling assembly according to the measurement result of the temperature measurement assembly.

[0007] As a further improvement of the above technical solution: Further, the heating assembly comprises a flow guide cover for covering the test piece to form a heating channel, a heater arranged on the gas inlet end of the heating channel and connected with the control assembly for manufacturing a high-temperature gas flow, and a variable frequency fan arranged on the gas inlet end of the heating channel and connected with the control assembly for delivering the high-temperature gas flow into the heating channel.

[0008] Further, the temperature measurement assembly comprises a plurality of temperature sensors one arranged in the heating channel and connected with the control assembly, and a temperature sensor two arranged in the inside of the test piece and connected with the control assembly, the plurality of temperature sensors one are arranged in an array.

[0009] Further, the heating assembly further comprises a rectifier arranged on the gas outlet end of the variable frequency fan.

[0010] Further, the heating assembly further comprises a heat preservation layer sleeved outside the flow guide cover.

[0011] Further, the cooling assembly comprises a refrigeration device for generating and delivering the cooling airflow, an air inlet pipe for connecting the internal air inlet end of the test piece, which is in communication with the refrigeration device, an electromagnetic valve arranged on the air inlet pipe and connected with the control assembly, a flow meter arranged on the air inlet pipe and connected with the control assembly, a pressure stabilizer arranged on the air inlet pipe, and an air outlet pipe for connecting the internal air outlet end of the test piece.

[0012] Further, the clamping assembly comprises a first clamp connected with the loading end of the loading assembly and a second clamp connected with the fixed end of the loading assembly, the first clamp and the second clamp are used for connecting the opposite two ends of the test piece respectively, the first clamp is provided with an air inlet hole for connecting the internal air inlet end of the test piece, which is in communication with the air inlet pipe, and the second clamp is provided with an air outlet hole for connecting the internal air outlet end of the test piece, which is in communication with the air outlet pipe.

[0013] Further, the strain measurement assembly comprises two extensometers arranged on the opposite sides of the test piece.

[0014] According to another aspect of the present application, a creep test method of a turbine rotor blade film hole simulation piece is also provided, which adopts the creep test system of the turbine rotor blade film hole simulation piece, and comprises the following steps: S1: constructing a three-dimensional model of the test piece to perform finite element simulation under service conditions, and obtaining simulation results of the flow field and the temperature field of the test piece; S2: smearing a high-temperature resistant coating on the test piece, fixing the test piece through the clamping assembly, and applying load to the test piece by the loading assembly according to the set loading conditions; S3: forming a heating channel on the outside of the test piece by the heating assembly to generate and deliver high-temperature airflow through the heating channel, and based on the simulation results of the flow field and the temperature field of the test piece, heating the outside of the test piece to a first set temperature and controlling the flow rate of the high-temperature airflow; S4: generating and delivering cooling airflow through the inside of the test piece by the cooling assembly to form a dynamic convection environment around the test piece, and based on the simulation results of the flow field and the temperature field of the test piece, cooling the inside of the test piece to a second set temperature and controlling the flow rate of the cooling airflow; S5: measuring the strain rate of the test piece by the strain measurement assembly, and controlling the flow rate of the cooling airflow in real time according to the measurement results of the strain rate to maintain the strain rate stable until the creep test results are obtained.

[0015] As a further improvement of the above technical solutions: Further, after step S5, the method comprises the following step: S6: importing the temperature field simulation results of the test piece into the simulation software by a user subroutine, performing creep life simulation of the test piece by the subroutine, obtaining creep simulation results of the test piece, and comparing and verifying the creep simulation results with the creep test results.

[0016] The present application has the following advantages: The creep test system of the turbine rotor blade film hole simulation piece of the application fixes the test piece through the clamping assembly, then applies load to the test piece through the loading assembly, so that the test piece creeps; the heating assembly is covered outside the test piece to form a heating channel, high-temperature airflow is manufactured and delivered to flow through the heating channel, the high-temperature airflow flushes the outside of the test piece, the outside of the test piece is heated to a first set temperature, then the cooling assembly manufactures and delivers cooling airflow to flow through the inside of the test piece, the inside of the test piece is cooled to a second set temperature, an internal and external non-isothermal temperature field is formed, airflow flows in and out of the test piece, a dynamic convection environment is formed around the test piece, the cooling airflow in the inside of the test piece can flow out of the film hole on the test piece to the outside, that is, an uneven temperature field is formed outside the test piece, so that the turbine rotor blade film hole part is truly simulated, and the verification accuracy of the test piece to the real component is improved; the strain rate of the test piece is measured through the strain measurement assembly, the cooling airflow flow rate delivered by the cooling assembly is controlled by the control assembly according to the measurement result of the strain rate, so that the strain rate is maintained stable, and the heating assembly and the cooling assembly are controlled according to the measurement result of the temperature measurement assembly, so that the real service condition is further accurately simulated, and the verification accuracy of the test piece to the real component is improved; compared with the prior art, when the creep test is performed, the non-isothermal temperature field is formed inside and outside the test piece at the same time, the dynamic convection environment is formed around the test piece through the airflow flowing in and out, the uneven temperature field is formed outside the test piece, the test piece bears the effects of turbulent flow and thermal shock, the influence of the external high-temperature airflow flushing on the creep life of the test piece is fully considered, the verification accuracy of the creep test result to the creep life of the turbine rotor blade film hole part is greatly improved, the practicality is high, and the application is suitable for wide promotion and application.

[0017] The turbine rotor blade film hole simulation piece creep test method of the application constructs a three-dimensional model of the test piece to perform finite element simulation under service conditions, obtains simulation results of the flow field and temperature field of the test piece to provide data support for subsequent creep tests; high-temperature resistant coating is applied on the test piece, the test piece is fixed by a clamping assembly, and a loading assembly applies load on the test piece according to the set loading conditions to ensure the accuracy and reliability of the creep test; a heating assembly forms a heating channel outside the test piece to generate and transport high-temperature gas flow through the heating channel, and based on the simulation results of the flow field and temperature field of the test piece, the outside of the test piece is heated to a first set temperature, and the flow rate of the high-temperature gas flow is controlled, and then a cooling assembly generates and transports cooling gas flow through the inside of the test piece to form a dynamic convection environment around the test piece, based on the simulation results of the flow field and temperature field of the test piece, the inside of the test piece is cooled to a second set temperature, and the flow rate of the cooling gas flow is controlled to accurately simulate the non-isothermal temperature field inside and outside the test piece and the non-uniform temperature field outside the test piece, thereby improving the accuracy of the creep test results; the strain rate of the test piece is measured by a strain measurement assembly, and the cooling gas flow rate is controlled in real time according to the measurement results of the strain rate to maintain a stable strain rate until the creep test results are obtained, thereby further improving the reliability of the creep test results and improving the verification accuracy of the creep life of the real component; compared with the prior art, when the creep test is performed, a non-isothermal temperature field is formed inside and outside the test piece, a dynamic convection environment is formed around the test piece by the flow of the internal and external gas flow, and a non-uniform temperature field is formed outside the test piece, so that the test piece is subjected to turbulent flow and thermal shock effect, the influence of external high-temperature gas flow scouring on the creep life of the test piece is fully considered, simulation simulation is used to provide data support for the actual test, and the verification accuracy of the creep test results on the creep life of the turbine rotor blade film hole position is greatly improved, which is practical and suitable for wide promotion and application.

[0018] In addition to the objects, features, and advantages described above, the present application has other objects, features, and advantages. The present application will be further described in detail below with reference to the drawings. BRIEF DESCRIPTION OF DRAWINGS

[0019] The accompanying drawings, which form a part of this application, are included to provide a further understanding of the application, illustrate preferred embodiments of the application, and assist in the explanation of the application. In the drawings: Figure 1 is a structure schematic diagram of a turbine rotor blade film hole simulation piece creep test system of a preferred embodiment of the application; Figure 2 is a structure schematic diagram of a heating assembly in a turbine rotor blade film hole simulation piece creep test system of a preferred embodiment of the application; Figure 3is a step flow chart of a creep test method of a turbine rotor blade film hole mockup of a preferred embodiment of the present invention.

[0020] Legend: 11, first clamp; 12, second clamp; 20, loading assembly; 30, heating assembly; 31, fairing; 32, heater; 33, variable frequency fan; 34, rectifier; 35, insulation layer; 41, refrigeration unit; 42, air inlet pipe; 43, electromagnetic valve; 44, flow meter; 45, pressure stabilizer; 46, air outlet pipe; 50, control assembly. DETAILED DESCRIPTION

[0021] The following description provides specific applications and requirements of the present specification, in order to enable a person skilled in the art to manufacture and use the contents of the present specification. Various partial modifications of the disclosed embodiments are obvious to those skilled in the art, and the general principles defined herein can be applied to other embodiments and applications without departing from the spirit and scope of the present specification. Therefore, the present specification is not limited to the embodiments shown, but is consistent with the widest scope of the claims.

[0022] The terms used herein are only for the purpose of describing specific example embodiments, and are not limiting. For example, unless the context clearly indicates otherwise, as used herein, the singular forms "a", "an", and "the" can also include the plural forms. When used in the present specification, the terms "comprise", "include" and / or "contain" mean that the associated integer, step, operation, element and / or component exists, but do not exclude the presence of one or more other features, integers, steps, operations, elements, components and / or groups.

[0023] These features of the present specification and other features, as well as the operation and function of related elements of the structure, and the combination and economy of manufacture of the components can be significantly improved in view of the following description. With reference to the drawings, all of which form part of the present specification. However, it should be clearly understood that the drawings are for illustrative and descriptive purposes only, and are not intended to limit the scope of the present specification. It should also be understood that the drawings are not drawn to scale.

[0024] As Figure 1As shown, the creep test system of the turbine rotor blade film hole simulation piece of the embodiment includes a clamping assembly for fixing the test piece, a loading assembly 20 for applying a load to the test piece, a strain measurement assembly (not shown in the figure) for measuring the strain rate of the test piece, a heating assembly 30 for covering the outside of the test piece to form a heating channel, a cooling assembly for manufacturing and delivering a cooling gas flow through the inside of the test piece, a temperature measurement assembly (not shown in the figure) for measuring the outside temperature of the test piece and the inside temperature of the test piece, and a control assembly 50 connected with the strain measurement assembly, the heating assembly 30, the cooling assembly and the temperature measurement assembly respectively. The heating assembly 30 is used to manufacture and deliver a high-temperature gas flow through the heating channel to heat the outside of the test piece to a first set temperature. The cooling assembly is used to cool the inside of the test piece to a second set temperature. The heating assembly 30 and the cooling assembly are used to form a dynamic convection environment around the test piece. The control assembly 50 is used to control the flow of the cooling gas flow delivered by the cooling assembly according to the measurement result of the strain rate, so that the strain rate is maintained stable, and to control the operation of the heating assembly 30 and the cooling assembly according to the measurement result of the temperature measurement assembly.

[0025] As Figure 1As shown, specifically, the creep test system of the turbine rotor blade film hole simulation piece of the present application fixes the test piece through the clamping assembly, and then applies a load to the test piece through the loading assembly 20 to make the test piece creep; the heating assembly 30 is covered outside the test piece to form a heating channel, high-temperature airflow is manufactured and delivered to flow through the heating channel, the high-temperature airflow washes the outside of the test piece to heat the outside of the test piece to a first set temperature, and then the cooling assembly manufactures and delivers cooling airflow to flow through the inside of the test piece to cool the inside of the test piece to a second set temperature, forming an internal and external non-isothermal temperature field, and airflow flows in and out of the test piece, forming a dynamic convection environment around the test piece, the cooling airflow in the inside of the test piece can flow out of the film hole on the test piece to the outside, that is, an uneven temperature field is formed outside the test piece, thereby realizing the real simulation of the turbine rotor blade film hole position, and improving the verification accuracy of the test piece on the real component; the strain rate of the test piece is measured through the strain measurement assembly, the cooling airflow flow rate delivered by the cooling assembly is controlled by the control assembly 50 according to the measurement result of the strain rate to make the strain rate stable, and the heating assembly 30 and the cooling assembly are controlled according to the measurement result of the temperature measurement assembly, thereby further realizing the accurate simulation of the real service condition and improving the verification accuracy of the test piece on the real component; compared with the prior art, when the creep test is performed, the non-isothermal temperature field is formed inside and outside the test piece, the dynamic convection environment is formed around the test piece through the airflow flowing in and out of the test piece, and the uneven temperature field is formed outside the test piece, so that the test piece bears the effects of turbulent flow and thermal shock, the influence of the external high-temperature airflow washing on the creep life of the test piece is fully considered, the verification accuracy of the creep test result on the turbine rotor blade film hole position is greatly improved, the practicability is high, and the present application is suitable for wide promotion and application.

[0026] It should be understood that the test piece refers to the turbine rotor blade film hole simulation piece.

[0027] It should be understood that since the film holes on the test piece are arranged to match the turbine rotor blade film hole position, the internal cooling airflow can flow out of the test piece through the airflow holes to form a protective film, and the external high-temperature airflow washes the protective film, thereby simulating the real working state of the turbine rotor blade film hole position and improving the reliability of the creep test result.

[0028] It should be understood that the stress borne by the turbine rotor blade under the real service condition is constant, and thus the strain rate is relatively stable.

[0029] Optionally, the control assembly 50 is a controller or a computer.

[0030] Optionally, the test piece is arranged in a circular tube shape.

[0031] As Figure 2As shown, in the embodiment, the heating assembly 30 comprises a flow guide cover 31 for covering the test piece to form a heating channel, a heater 32 arranged at the air inlet end of the heating channel and connected with the control assembly 50 for generating high-temperature airflow, and a variable frequency fan 33 arranged at the air inlet end of the heating channel and connected with the control assembly 50 for delivering the high-temperature airflow into the heating channel. Specifically, the heating assembly 30 covers the test piece through the flow guide cover 31 to form the heating channel, heats the air at the air inlet end of the heating channel through the heater 32 to generate high-temperature airflow, and delivers the high-temperature airflow into the heating channel through the variable frequency fan 33, and the control assembly 50 can control the air speed of the variable frequency fan 33 to simulate the gas flow rate under different working conditions, thereby improving the reliability of the creep test results.

[0032] Optionally, the heater 32 is a resistance wire.

[0033] In the embodiment, the temperature measurement assembly comprises a plurality of temperature sensors I arranged in the heating channel and connected with the control assembly 50, and a temperature sensor II arranged in the interior of the test piece and connected with the control assembly 50, and the plurality of temperature sensors I are arranged in an array. Specifically, the temperature at different positions in the heating channel can be measured through the plurality of temperature sensors I arranged in an array, so as to obtain the external temperature field of the test piece, and the control assembly 50 can control the heating assembly 30 to work according to the external temperature field of the test piece, so as to make the external temperature field of the test piece simulate the real working condition; the internal temperature of the test piece can be measured through the temperature sensor II, and the control assembly 50 can control the cooling assembly to work according to the internal temperature of the test piece, so as to control the internal temperature of the test, so that the internal and external non-isothermal temperature fields of the test piece simulate the real working condition, thereby improving the reliability of the creep test results.

[0034] As shown in the figure, Figure 2 In the embodiment, the heating assembly 30 further comprises a rectifier 34 arranged at the air outlet end of the variable frequency fan 33. Specifically, the uniformity of the high-temperature airflow when flowing is improved through the rectifier 34, and the turbulence degree is reduced, so as to facilitate the accurate control of the external flow field of the test piece, and then facilitate the accurate control of the external temperature field of the test piece, thereby improving the reliability of the creep test results.

[0035] As shown in the figure, Figure 2 In the embodiment, the heating assembly 30 further comprises a heat preservation layer 35 sleeved outside the flow guide cover 31. Specifically, the heat loss rate of the heating channel is reduced through the heat preservation layer 35, so as to try to ensure the temperature stability in the heating channel, and then facilitate the accurate control of the external temperature field of the test piece, thereby improving the reliability of the creep test results.

[0036] As shown in the figure, Figure 1As shown, in this embodiment, the cooling assembly includes a refrigeration component 41 for generating and conveying cooling airflow, an air inlet pipe 42 connected to the refrigeration component 41 for connecting the internal air inlet end of the test piece, a solenoid valve 43 arranged on the air inlet pipe 42 and connected to the control component 50, a flow meter 44 arranged on the air inlet pipe 42 and connected to the control component 50, a pressure regulator 45 arranged on the air inlet pipe 42, and an air outlet pipe 46 for connecting the internal exhaust end of the test piece. Specifically, the opening degree of the solenoid valve 43 is controlled by the control component 50 to regulate the cooling airflow. The cooling airflow is generated and delivered by the refrigeration component 41 and delivered to the test piece through the inlet pipe 42. The cooling airflow flows through the interior of the test piece and is then discharged through the outlet pipe 46, thereby cooling the interior of the test piece. The flow meter 44 measures the cooling airflow. The control component 50 controls the opening degree of the solenoid valve 43 or the working state of the refrigeration component 41 to control the cooling airflow and achieve accurate control of the internal temperature of the test piece. The pressure is monitored by the pressure regulator 45 to ensure stable delivery of the cooling airflow.

[0037] It should be understood that, since the temperature of the high-temperature airflow is relatively high, the ambient air is the cooling airflow relative to the high-temperature airflow. The cooling component 41 is a centrifugal fan, which is used to transport outside air through the interior of the test piece to cool the test piece.

[0038] Alternatively, in another embodiment, the cooling component 41 is a combination of a condenser and a fan.

[0039] like Figure 1 As shown, in this embodiment, the clamping assembly includes a first clamp 11 connected to the loading end of the loading assembly 20 and a second clamp 12 connected to the fixing end of the loading assembly 20. The first clamp 11 and the second clamp 12 are respectively connected to the opposite ends of the test piece. The first clamp 11 has an air inlet hole that communicates with the air inlet pipe 42 to connect to the internal air inlet end of the test piece. The second clamp 12 has an exhaust hole that communicates with the exhaust pipe to connect to the internal exhaust end of the test piece. Specifically, the first clamp 11 and the second clamp 12 are respectively connected to the opposite ends of the test piece to cooperate with the loading assembly 20 to fix the test piece; the air inlet hole is connected to the air inlet pipe 42 so that the cooling airflow is delivered to the interior of the test piece through the air inlet pipe 42 and the air inlet hole; and the exhaust hole is connected to the exhaust pipe so that the cooling airflow inside the test piece is discharged through the exhaust hole and the exhaust pipe.

[0040] Optionally, the test piece includes a test section, and clamping section one and clamping section two arranged at opposite ends of the test section and connected to the first clamp 11 and the second clamp 12 respectively. The first clamp 11 and clamping section one are connected by a threaded structure, and the second clamp 12 and clamping section two are connected by a thread.

[0041] Optionally, the loading component 20 is a creep testing machine.

[0042] Optionally, the temperature sensor two is a K-type thermocouple, which extends into the interior of the test piece through the air inlet hole, and the measuring point is located at the axial middle part of the test piece.

[0043] In the embodiment, the first set temperature refers to the axial middle part temperature outside the test piece, that is, the axial middle part outside the test piece is heated to the first set temperature, and the second set temperature is the axial middle part inside the test piece, that is, the axial middle part inside the test piece is cooled to the second set temperature, so as to realize accurate control of the temperature difference in the non-isothermal temperature field.

[0044] Optionally, in an embodiment, the test piece is arranged in a circular tube shape, with an inner diameter of 6 mm and an outer diameter of 8 mm.

[0045] Optionally, in an embodiment, the first set temperature is 1100°C, and the second set temperature is 1000°C.

[0046] In the embodiment, the strain measurement assembly includes two extensometers, which are arranged on opposite sides of the test piece. Specifically, the two extensometers work together to accurately measure the strain rate.

[0047] As shown in FIG. 1, the test piece 1 is arranged in a circular tube shape, with an inner diameter of 6 mm and an outer diameter of 8 mm. Figure 3As shown, the creep test method of the turbine rotor blade film hole simulation piece of the embodiment comprises the following steps: S1: a three-dimensional model of the test piece is constructed to perform finite element simulation under service conditions to obtain simulation results of the flow field and temperature field of the test piece; S2: a high-temperature resistant coating is applied on the test piece, the test piece is fixed by the clamping assembly, and the loading assembly 20 applies load to the test piece according to the set loading conditions; S3: the heating assembly 30 forms a heating channel outside the test piece to generate and transport high-temperature gas flow through the heating channel, and based on the simulation results of the flow field and temperature field of the test piece, the outside of the test piece is heated to a first set temperature, and the high-temperature gas flow rate is controlled; S4: the cooling assembly generates and transports cooling gas flow through the inside of the test piece to form a dynamic convection environment around the test piece, based on the simulation results of the flow field and temperature field of the test piece, the inside of the test piece is cooled to a second set temperature, and the cooling gas flow rate is controlled; S5: the strain rate of the test piece is measured by the strain measurement assembly, and the cooling gas flow rate is controlled in real time according to the measurement results of the strain rate to maintain the strain rate stable until the creep test results are obtained.Specifically, the creep test method of the turbine rotor blade film hole simulation piece of the present application constructs a three-dimensional model of the test piece to perform finite element simulation under service conditions, obtains simulation results of the flow field and temperature field of the test piece to provide data support for subsequent creep tests; high-temperature resistant coating is applied on the test piece, the test piece is fixed by the clamping assembly, the loading assembly 20 applies load to the test piece according to the set loading conditions to ensure the accuracy and reliability of the creep test; the heating assembly 30 forms a heating channel outside the test piece to generate and transport high-temperature gas flow through the heating channel, and based on the simulation results of the flow field and temperature field of the test piece, the outside of the test piece is heated to a first set temperature, and the flow rate of the high-temperature gas flow is controlled, and then the cooling assembly generates and transports cooling gas flow through the inside of the test piece to form a dynamic convection environment around the test piece, based on the simulation results of the flow field and temperature field of the test piece, the inside of the test piece is cooled to a second set temperature, and the flow rate of the cooling gas flow is controlled, to accurately simulate the non-isothermal temperature field inside and outside the test piece and the non-uniform temperature field outside the test piece, thereby improving the accuracy of the creep test results; the strain rate of the test piece is measured by the strain measurement assembly, and the cooling gas flow rate is controlled in real time according to the measurement results of the strain rate to maintain a stable strain rate until the creep test results are obtained, thereby further improving the reliability of the creep test results and improving the verification accuracy of the creep life of the real component; compared with the prior art, when the creep test is performed, a non-isothermal temperature field is formed inside and outside the test piece, a dynamic convection environment is formed around the test piece by the flow of the internal and external gas, and a non-uniform temperature field is formed outside the test piece, so that the test piece is subjected to turbulent flow and thermal shock effect, fully considering the influence of external high-temperature gas flow on the creep life of the test piece, while using simulation to provide data support for actual tests, greatly improving the verification accuracy of the creep test results on the creep life of the turbine rotor blade film hole position, and having strong practicality and being suitable for wide promotion and application.

[0048] In this embodiment, the set loading conditions include the loading stress value, the loading duration and the loading rate.

[0049] In this embodiment, after step S5, the following step S6 is included: S6: the crystal plasticity constitutive model is collected into the simulation software through a user subroutine, the temperature field simulation results of the test piece are imported, the creep life simulation of the test piece is performed by using the subroutine, and the creep simulation results of the test piece are obtained to be compared and verified with the creep test results. Specifically, the creep simulation results and the creep test results are compared and verified to further improve the reliability of the creep test results; that is, when the creep simulation results and the creep test results are basically consistent, it is judged that the creep test results are reliable, and when the creep simulation results and the creep test results have a large difference, it is judged that the creep test results are unreliable, and the creep test needs to be performed again.

[0050] Optionally, during the test, the loading assembly 20, the strain measuring assembly and the temperature measuring assembly need to be zeroed.

[0051] In view of the foregoing, it will be seen that the foregoing detailed description is only illustrative in nature and not restrictive. Only the exemplary embodiments have been disclosed herein, although alterations, improvements, and modifications will become apparent to those skilled in the art from the foregoing detailed description. It is the intention that the scope of the application claimed herein should not be limited by any of the foregoing detailed description, but should be given the broadest interpretation of the appended claims to include any and all embodiments which become apparent from the following claims, or can include such forms as can become obvious after in view of the foregoing detailed description and claims. Changes in or substitutions of equivalents of parts and materials as set forth in the exemplary embodiments described above are contemplated by those skilled in the art and within the full intended scope of the following claims. Accordingly, many modifications can be made by those skilled in the art without departing from the scope of the disclosure.

[0052] Further, certain terminology has been used in the present description for the purpose of reference only. For example, "one embodiment", "an embodiment" and / or "some embodiments" means that a particular feature, structure or characteristic described in connection with the embodiment is included in at least one embodiment. Thus, use of the terms "in one embodiment" or "in an embodiment" or "in some embodiments" appearing throughout this description are not necessarily all referring to the same embodiment. Furthermore, the particular features, structures, or characteristics can be combined in any suitable manner in one or more embodiments. It has to be understood that, in the foregoing description, for the purpose of brevity, various features of the application are described in a single embodiment, in a certain order, and in a certain manner, and that these features are not necessarily arranged in the same order or in the same manner in other embodiments.

[0053] It is to be understood that the foregoing description is directed to individual embodiments for the purpose of aiding in understanding one feature, for the purpose of simplifying the present description, the present description combines various features in a single embodiment, drawing or description thereof. However, this does not imply that a combination of these features is mandatory, a person skilled in the art, upon reading the present description, would be able to identify a part of the apparatus as a separate embodiment. That is, the embodiments of the present description can also be understood as an integration of several sub-embodiments. Each sub-embodiment is valid as long as it comprises less than all the features of the single foregoing disclosed embodiment.

Claims

1. A creep test system for a turbine rotor blade film hole mockup, characterized by, The device comprises a clamping assembly for fixing a test piece, a loading assembly (20) for applying a load to the test piece, a strain measuring assembly for measuring a strain rate of the test piece, a heating assembly (30) for covering the test piece to form a heating channel, a cooling assembly for manufacturing and delivering a cooling airflow to flow through the inside of the test piece, a temperature measuring assembly for measuring the outside temperature of the test piece and the inside temperature of the test piece, and a control assembly (50) connected with the strain measuring assembly, the heating assembly (30), the cooling assembly and the temperature measuring assembly respectively, the heating assembly (30) is used for manufacturing and delivering a high-temperature airflow to flow through the heating channel to heat the outside of the test piece to a first set temperature, the cooling assembly is used for cooling the inside of the test piece to a second set temperature, the heating assembly (30) and the cooling assembly are used for forming a dynamic convection environment around the test piece, and the control assembly (50) is used for controlling the flow of the cooling airflow delivered by the cooling assembly according to the measurement result of the strain rate to maintain the strain rate stable, and controlling the heating assembly (30) and the cooling assembly to work according to the measurement result of the temperature measuring assembly.

2. The creep test system for turbine rotor blade film hole analogs of claim 1, wherein, The heating assembly (30) comprises a flow guide cover (31) for covering the test piece to form the heating channel, a heater (32) arranged on the air inlet end of the heating channel and connected with the control assembly (50) and used for manufacturing the high-temperature airflow, and a variable frequency fan (33) arranged on the air inlet end of the heating channel and connected with the control assembly (50) and used for delivering the high-temperature airflow into the heating channel.

3. The creep test system for turbine rotor blade film hole analogs of claim 2, wherein, The temperature measuring assembly comprises a plurality of temperature sensors I arranged in the heating channel and connected with the control assembly (50), and a temperature sensor II arranged in the inside of the test piece and connected with the control assembly (50), and the plurality of temperature sensors I are arranged in an array.

4. The creep test system for turbine rotor blade film hole analogs of claim 2, wherein, The heating assembly (30) further comprises a rectifier (34) arranged on the air outlet end of the variable frequency fan (33).

5. The creep test system for turbine rotor blade film hole analogs of claim 4, wherein, The heating assembly (30) further comprises a heat preservation layer (35) sleeved outside the flow guide cover (31).

6. The creep test system of the turbine rotor blade film hole analogue of claim 5, wherein, The cooling assembly comprises a refrigeration device (41) for manufacturing and delivering the cooling airflow, an air inlet pipe (42) for connecting the air inlet end of the inside of the test piece and communicated with the refrigeration device (41), an electromagnetic valve (43) arranged on the air inlet pipe (42) and connected with the control assembly (50), a flow meter (44) arranged on the air inlet pipe (42) and connected with the control assembly (50), a pressure stabilizer (45) arranged on the air inlet pipe (42), and an air outlet pipe (46) for connecting the air outlet end of the inside of the test piece.

7. The creep test system for turbine rotor blade film hole analogs of any of claims 1-6, wherein, The clamping assembly comprises a first clamp (11) connected with the loading end of the loading assembly (20) and a second clamp (12) connected with the fixed end of the loading assembly (20), the first clamp (11) and the second clamp (12) are used for connecting with the opposite two ends of the test piece respectively, the first clamp (11) is provided with an air inlet hole for connecting the air inlet end of the inside of the test piece and communicated with the air inlet pipe (42), and the second clamp (12) is provided with an air outlet hole for connecting the air outlet end of the inside of the test piece and communicated with the air outlet pipe.

8. The creep test system for turbine rotor blade film hole analogs of any of claims 1-6, wherein, The strain measurement assembly includes two extensometers arranged on opposite sides of the test piece.

9. A method of creep testing a turbine rotor blade film hole analogue, characterised by, The creep test system of the turbine rotor blade film hole simulation piece according to any one of claims 1-8 comprises the following steps: S1: constructing a three-dimensional model of the test piece to perform finite element simulation under service conditions to obtain simulation results of the flow field and temperature field of the test piece; S2: applying a high-temperature resistant coating on the test piece, fixing the test piece through the clamping assembly, and applying load on the test piece by the loading assembly (20) according to the set loading conditions; S3: forming a heating channel on the outside of the test piece by the heating assembly (30) to generate and deliver high-temperature gas flow through the heating channel, and based on the simulation results of the flow field and temperature field of the test piece, heating the outside of the test piece to a first set temperature and controlling the flow rate of the high-temperature gas flow; S4: generating and delivering cooling gas flow through the inside of the test piece by the cooling assembly to form a dynamic convection environment around the test piece, based on the simulation results of the flow field and temperature field of the test piece, cooling the inside of the test piece to a second set temperature and controlling the flow rate of the cooling gas flow; S5: measuring the strain rate of the test piece by the strain measurement assembly, and controlling the cooling gas flow rate in real time according to the measurement results of the strain rate to maintain the strain rate stable until the creep test results are obtained.

10. The creep test method of a turbine rotor blade film hole mockup of claim 9, wherein, After step S5, the following step is included: S6: importing the temperature field simulation results of the test piece into the simulation software by a user subroutine, performing creep life simulation of the test piece by the subroutine, obtaining creep simulation results of the test piece, and comparing and verifying the creep simulation results with the creep test results.

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