System and method for evaluating thermal barrier coating insulation effect of turbine blade in rotating state

Abstract

The application discloses a system and method for evaluating the heat insulation effect of a turbine blade thermal barrier coating in a rotating state, which comprises a service environment simulation unit, a temperature field measurement unit and an evaluation unit, wherein the service environment simulation unit comprises a turbine blade test piece and a gas jet gun; the temperature field measurement unit comprises an infrared thermal imaging module and a thermocouple module, the thermocouple module comprises a thin film thermocouple and a micro thermocouple, the thin film thermocouple is arranged between the blade and the thermal barrier coating and is used for acquiring the temperature field of the interface; the micro thermocouple is arranged on the surface of the thermal barrier coating away from the blade and is used for acquiring the temperature field of the surface of the thermal barrier coating; and the evaluation unit evaluates the heat insulation effect of the thermal barrier coating according to the temperature measurement result. The application can simulate the real service environment of high temperature and high speed rotation of the turbine blade thermal barrier coating, heat the surface of the thermal barrier coating in the form of an annular gas flame, drive the turbine blade to rotate at a high speed by using a high-power high-speed motor, and realize real-time temperature measurement in the high-speed rotating state.

Description

Technical Field

[0001] This invention belongs to the field of high-pressure turbine blade technology, and relates to the performance evaluation of turbine blade thermal barrier coatings, and particularly to a system and method for evaluating the thermal insulation effect of turbine blade thermal barrier coatings under rotating conditions. Background Technology

[0002] High-pressure turbine blades are core components of aero-engines, bearing both temperature and load. Accurate design and evaluation of their temperature-bearing capacity are crucial. However, testing the temperature field of turbine blades is extremely difficult under rotating, especially high-speed rotating, and high-temperature environments involving interaction with combustion gases and cool air. There is currently no mature engineering technology for testing the surface temperature field of turbine blades, nor are there definitive turbine blade temperature field data.

[0003] In addition, to improve the heat resistance of turbine blades, some aero engines have adopted thermal barrier coatings. Testing the surface and interface temperature field of the thermal barrier coating on turbine blades is the prerequisite and foundation for evaluating the thermal insulation effect of the thermal barrier coating, but there is currently no definitive data, let alone evaluation methods.

[0004] In existing technologies, turbine blade temperature testing and evaluation mainly utilize fluorescence thermometry and high-temperature multi-color irreversible temperature-indicating paint. Fluorescence thermometry offers advantages such as high accuracy, wide range, and immunity to environmental influences. However, testing turbine blade temperature using fluorescence thermometry requires pre-mixing and adding fluorescent materials to the turbine blade's thermal barrier coating, resulting in a demanding manufacturing process and a complex temperature measurement device. Temperature-indicating paint has significant advantages in testing the temperature of high-speed moving and complex-shaped surfaces, but its accuracy is lower, and the measured component must be disassembled for temperature interpretation, making real-time temperature monitoring and evaluation impossible. Summary of the Invention

[0005] In order to overcome the shortcomings of the prior art, the present invention aims to provide a system and method for evaluating the thermal insulation effect of the thermal barrier coating of turbine blades under rotating conditions, so as to solve the problem that the surface and interface temperature of the thermal barrier coating of turbine blades under rotating conditions cannot be measured or is inaccurate, accurately obtain the surface temperature field of the rotating turbine blades under high-temperature gas environment, and evaluate the thermal insulation effect of the thermal barrier coating accordingly, thereby providing a basis for the design of the temperature bearing capacity of turbine blades.

[0006] To achieve the above objectives, the technical solution adopted by the present invention is as follows:

[0007] In a first aspect, the present invention provides a system for evaluating the thermal insulation effect of a turbine blade thermal barrier coating under rotating conditions, comprising a service environment simulation unit, a temperature field measurement unit, and an evaluation unit.

[0008] The service environment simulation unit is mainly used to simulate the actual working environment and state of turbine blades. It includes a turbine blade test piece and a gas jet nozzle. The turbine blade test piece is mounted on a turbine disk with a rotating shaft and is driven to rotate by the rotating shaft and turbine disk. The turbine blade test piece includes blades and a thermal barrier coating on the surface of the blades, which is consistent with the turbine blades in actual operation. The gas jet nozzle is directed toward the turbine blade test piece and is mainly used to provide load to the turbine blade test piece in the rotating state. This load simulates the force and thermal shock in actual operation.

[0009] The temperature field measurement unit is mainly used to measure the temperature at several key locations during the experiment in real time. It includes an infrared thermal imaging module and a thermocouple module. The probe of the infrared thermal imaging module faces the turbine blade test piece to obtain the temperature field on the surface of the thermal barrier coating. The thermocouple module includes a thin-film thermocouple and a micro thermocouple. The thin-film thermocouple is arranged between the blade and the thermal barrier coating to obtain the temperature field at the interface. The micro thermocouple is arranged on the surface of the thermal barrier coating away from the blade to obtain the temperature field on the surface of the thermal barrier coating.

[0010] The evaluation unit is mainly used to evaluate the thermal barrier coating's insulation effect based on the results from the infrared thermal imaging module, thin-film thermocouple, and micro thermocouple.

[0011] The temperature field of the thermal barrier coating surface obtained by the infrared thermal imaging module is mainly used to corroborate the temperature field of the thermal barrier coating surface obtained by the micro thermocouple.

[0012] In one embodiment, there are multiple gas spray guns evenly distributed around the circumference of the combustion platform. They generate high-temperature, high-speed flames with a temperature of 1000℃-1700℃ and a speed of Mach 1-2 through combustion. The high-temperature, high-speed flames act on the leading edge of the turbine blade test piece and can provide loads including centrifugal force, aerodynamic force, and hot spot.

[0013] In one embodiment, an adhesive layer, an insulating layer, and a protective layer are sequentially disposed between the blade and the thermal barrier coating, wherein the adhesive layer is disposed on one side of the blade, the protective layer is disposed on one side of the thermal barrier coating, the thin-film thermocouple is disposed between the insulating layer and the protective layer, the material of the thin-film thermocouple is an iridium-rhodium alloy, and its positive and negative cold ends can be led out to the area not covered by the thermal barrier coating by electrodes, and the material of the micro thermocouple is a platinum-rhodium alloy.

[0014] In one embodiment, the thin-film thermocouple is connected to a temperature acquisition device via lead one, and the miniature thermocouple is connected to the temperature acquisition device via lead two. Lead one and lead two constitute the signal line of the thermocouple module. The signal line is fixed on the blade and sequentially connected to a conductive slip ring via the central channel of the turbine disk and the rotating shaft. The conductive slip ring converts the rotating signal line into a stationary signal line.

[0015] In one embodiment, the conductive slip ring includes a rotor and a stator. The rotor is assembled and connected to the rotating shaft. The rotor has a circuit board and a gold pin at one end near the stator. The signal line passes through the axial through hole of the rotor via the central channel of the rotating shaft and is connected to the rotor.

[0016] In one embodiment, the conductive slip ring receives a temperature signal and converts it into a current signal or a differential voltage signal. Utilizing the contact between the rotor and stator, specifically the connection between the circuit board and the gold pin, the current signal or differential voltage signal is transmitted to a remotely connected temperature acquisition device via a stationary signal line.

[0017] In one embodiment, a Hall effect test module is installed on the rotor or the rotating shaft. The Hall effect test module converts the mechanical geometric displacement of the rotor or rotating shaft into pulses or digital quantities through magnetoelectric conversion, thereby obtaining the position and direction of the rotating shaft, outputting pulse signals with the same time interval, and using the leading edge signal of the pulse signal to trigger the infrared thermal imaging module to take pictures and perform infrared thermal imaging.

[0018] In one embodiment, the infrared thermal imaging module selects a shortwave band of 1.5-1.6 micrometers or a medium wave band of 3.8-4.05 micrometers for infrared thermal imaging, and sets a filter in front of the infrared thermal imaging lens to reduce the influence of the gas flame on the temperature measurement.

[0019] A second aspect of the present invention also provides a method for evaluating the thermal insulation effect of a turbine blade thermal barrier coating under rotating conditions, implemented based on the evaluation system for the thermal insulation effect of a turbine blade thermal barrier coating under rotating conditions described in the first aspect, comprising the following steps:

[0020] The starter motor drives the turbine disk to rotate, and the gas injection gun is opened to provide load to the rotating turbine blade test piece;

[0021] The temperature field on the surface of the thermal barrier coating is collected by an infrared thermal imaging module, the temperature field at the interface between the blade and the thermal barrier coating is collected by a thin-film thermocouple, and the temperature field on the surface of the thermal barrier coating is collected by a miniature thermocouple.

[0022] The thermal barrier coating is evaluated for its thermal insulation effect, which is the difference between the surface temperature of the thermal barrier coating and the interface temperature between the blade and the thermal barrier coating.

[0023] In one embodiment, the turbine disk rotates at a speed of 10,000-20,000 rpm.

[0024] Compared with existing technologies, this invention can simulate the real service environment of high temperature and high speed rotation of the thermal barrier coating of turbine blades. The surface of the thermal barrier coating is heated by an annular gas flame, and a high-power high-speed motor is used to drive the turbine blades to rotate at high speed, so as to realize real-time temperature measurement under high-speed rotation.

[0025] This invention employs three temperature measurement technologies, including both contact and non-contact methods, which can be mutually verified. This invention can simultaneously measure the temperature field of the thermal barrier coating surface and interface, thereby calculating a particularly important performance characteristic of the thermal barrier coating: its heat insulation effect.

[0026] Furthermore, this invention is applicable to flat plates, curved surfaces, and complex real turbine blades, demonstrating the wide applicability of this method. The device has a simple structure, provides a fast temperature response when used for thermal insulation temperature measurement, and the testing process is simple and highly practical. Attached Figure Description

[0027] Figure 1 This is a schematic diagram of the overall structure of the turbine blade thermal barrier coating thermal insulation effect evaluation system under rotating conditions according to the present invention.

[0028] Figure 2 This is a plan view of the arrangement structure of the thermocouples in the thermal barrier coating of the turbine blade according to the present invention.

[0029] Figure 3 This is a cross-sectional view of the arrangement structure of the thermocouples in the thermal barrier coating of the turbine blade according to the present invention.

[0030] Figure 4 This is a schematic diagram of the structure of the present invention, which uses a conductive slip ring to convert a signal line into a stationary signal line.

[0031] Figure 5 This is the temperature measurement result of the thermocouple module in this embodiment of the invention.

[0032] Figure 6 This is the temperature measurement result of the infrared thermal imaging module in this embodiment of the invention. Detailed Implementation

[0033] The embodiments of the present invention will now be described in detail with reference to the accompanying drawings and examples.

[0034] In a rotating state, turbine blades are subjected not only to the impact of high-speed combustion gases and the complex airflow of the cooling film, but also to high-speed centrifugal force, making the testing of the turbine blade temperature field extremely difficult. Contact temperature measurement presents significant challenges in sensor placement, airflow interference, sensor connection under high-speed rotation, and signal transmission. Using contact temperature measurement technologies, such as miniature thermocouples and thin-film thermocouples, ensures robust thermocouple installation, real-time data transmission, and accurate test results calibration. Similarly, non-contact temperature measurement technologies, such as infrared thermometry, face significant difficulties in filtering out high-temperature flames, eliminating temperature interference from adjacent blades, detecting and calibrating curved surfaces, and ensuring reliable results. More importantly, the turbine blade surface is not only affected by high-temperature, high-speed combustion gases and cooling air, but also by high-speed rotating loads. These combined effects generate hot spots, turbulence, and wakes, impacting test results. Therefore, accurately measuring the temperature field of the combustion gases and loads, especially rotating loads, is a crucial factor and a significant challenge.

[0035] like Figure 1 As shown, the present invention provides a system for evaluating the thermal insulation effect of a turbine blade thermal barrier coating under rotating conditions, which mainly includes three parts: a service environment simulation unit, a temperature field measurement unit, and an evaluation unit.

[0036] The service environment simulation unit mainly includes a turbine blade test piece 1 and a gas spray gun 4. The turbine blade test piece 1 is the object of testing and evaluation, including blades 6 and a thermal barrier coating 64 applied to the surface of the blades 6. The turbine blade test piece 1 is mounted on a turbine disk 2 with a rotating shaft 3. This invention employs a high-power, high-speed motor to drive the rotating shaft 3 at high speed, designing a rotor module that includes a power drive motor, gearbox, multi-stage rotating shaft, and lubrication system. The rotating shaft 3 is fixedly connected to the turbine disk 2, thereby driving the turbine disk 2 to rotate, and consequently, driving the turbine blade test piece 1 to rotate. Clearly, there are multiple blades 6, and they are installed symmetrically at the center. The gas spray gun 4 is fixedly positioned and faces each turbine blade test piece 1, its function being to provide loads to the rotating turbine blade test piece 1, including centrifugal force, aerodynamic force, and hot spots. Therefore, the service environment simulation unit of this invention can simulate the real service environment of high-temperature, high-speed rotation of the turbine blade thermal barrier coating.

[0037] The temperature field measurement unit mainly includes an infrared thermal imaging module 7 and a thermocouple module 8. The probe of the infrared thermal imaging module 7 faces the turbine blade test piece 1, acquiring the temperature field on the surface of the thermal barrier coating 64 based on infrared thermal imaging technology. Thermocouple module 8 is used for contact measurement and includes thin-film thermocouples 81 and miniature thermocouples 82, such as... Figure 2As shown. A thin-film thermocouple 81 is arranged between the blade 6 and the thermal barrier coating 64 to obtain the temperature field of the interface, and a miniature thermocouple 82 is arranged on the surface of the thermal barrier coating 64 away from the blade 6 to obtain the temperature field of the surface of the thermal barrier coating 64.

[0038] The evaluation unit assesses the thermal barrier coating 64's insulation performance based on the results from the infrared thermal imaging module 7, the thin-film thermocouple 81, and the miniature thermocouple 82. For example, the evaluation unit can be any processor with computational capabilities. This invention enables the evaluation of the thermal barrier coating 64's insulation performance on turbine blades rotating at high speeds of 10,000-20,000 rpm.

[0039] When testing the thermal insulation effect of different thermal barrier coatings 64, the inherent blade 6 can be used as the substrate and different thermal barrier coatings 64 can be applied. Compared with the processing technology in actual applications, there is basically no increase in process steps or special materials.

[0040] In some embodiments of the present invention, such as Figure 1 As shown, there are four gas jets 4, evenly distributed around the circumference of the combustion platform 5. The combustion of fuel, oxygen, and air generates a high-temperature, high-speed flame with a temperature of 1000℃-1700℃ and a speed of Mach 1-2, which acts on the leading edge of the turbine blade test piece 1, generating loads such as centrifugal force, aerodynamic force, and hot spot. Through this structure, the present invention can heat the surface of the thermal barrier coating 64 using a ring-shaped gas jet flame, maximally replicating the real service environment. For example, kerosene can be used as the fuel.

[0041] In some embodiments of the present invention, the thermocouple module 8 performs contact-type measurements, requiring the signal line 9 to connect to the temperature acquisition device. Specifically, as shown... Figure 2 As shown, the thin-film thermocouple 81 is connected to the temperature acquisition device via lead 91, and the miniature thermocouple 82 is connected to the temperature acquisition device via lead 92. The signal line 9 consists of lead 91 and lead 92. Figure 1 As shown, the signal line 9 is fixed on the blade 6 and is connected to the conductive slip ring 10 through the central channel of the turbine disk 2 and the rotating shaft 3 in sequence. The conductive slip ring 10 converts the rotating signal line 9 into a stationary signal line 11.

[0042] In some embodiments of the present invention, such as Figure 3As shown, between the blade 6 and the thermal barrier coating 64, along the direction from the blade 6 to the thermal barrier coating 64, an adhesive layer 61, an insulating layer 62, and a protective layer 63 are sequentially disposed. A thin-film thermocouple 81 is arranged between the insulating layer 62 and the protective layer 63. For example, the blade 6 of the present invention is made of a nickel-based high-temperature alloy; the adhesive layer 61 is made of NiCrAlY or NiCoCrAlY; the insulating layer 62 is an aluminized oxide layer, an amorphous YSZ layer, or an Al2O3 layer; the protective layer 63 is an Al2O3 layer or a YZrAlO layer; and the thermal barrier coating 64 is generally made of YSZ.

[0043] In some embodiments of the present invention, the material of the thin-film thermocouple 81 is a conventional thin-film thermocouple material such as iridium-rhodium or NiCr / NiSi, or other electrode materials with high temperature resistance, oxidation resistance and good conductivity. The material of the miniature thermocouple 82 is a platinum-rhodium alloy, specifically a double platinum-rhodium thermocouple wire. The positive and negative cold ends of the thin-film thermocouple 81 are led out to the area not covered by the thermal barrier coating 64, i.e., the blade tenon, and the signal is acquired through the lead wire 91.

[0044] In some embodiments of the present invention, such as Figure 4 As shown, the conductive slip ring 10 includes a rotor 101 and a stator 102. The static-dynamic switching of the contact temperature measurement lead is mainly achieved by the rotor 101 and the stator 102. The rotor 101 is assembled and fixedly connected to the rotating shaft 3. A circuit board 103 and a gold needle 104 are provided at one end of the rotor 101 near the stator 102. The signal line 9 passes through the central channel of the rotating shaft 3 and enters the axial through hole of the rotor 101 and connects to the rotor 101. The rotor 101 has signal acquisition components that can acquire the temperature signal transmitted by the signal line 9. Specifically, the rotor 101 is first connected to the lead 91 of the thin film thermocouple 81 and the lead 92 of the miniature thermocouple 82, which rotate with the rotating shaft 3. The two leads are passed through the through hole of the conductive slip ring 10. At the same time, the rotor 101 is fixed to the tail end of the rotating shaft 3 using a flange structure 105, allowing it to rotate with the shaft.

[0045] Both the thin-film thermocouple 81 and the miniature thermocouple 82 use conductors of two different materials to form a closed loop. When a temperature gradient exists between the two ends, current flows through the loop, and an electromotive force exists between the two ends. Therefore, based on a contact temperature measurement method, the present invention distributes the thin-film thermocouple 81 and the miniature thermocouple 82 at the interface between the blade 6 and the thermal barrier coating 64 and on the surface of the thermal barrier coating 64, respectively. Their leads are fixed on the turbine disk 2 and rotated with the shaft through the central channel of the rotating shaft 3. Then, their leads are connected to the rotor 101 of the conductive slip ring. The conductive slip ring 10 receives the temperature signal and converts it into a current signal or a differential voltage signal. The current signal or differential voltage signal is transmitted to a remotely connected temperature acquisition device through the stationary signal line 11 by the contact between the rotor 101 and the stator 102, mainly through the connection of the circuit board 103 and the gold needle 104. This enables the detection of the temperature field on the surface and interface of the thermal barrier coating 64 of the turbine blade under high-speed rotation.

[0046] Circuit board 103 is a ring or circuit structure in a conductive slip ring product, with pinholes on it. Gold needles 104 are placed in the pinholes to form a gold-gold superconducting self-lubricating contact.

[0047] In some embodiments of the present invention, a Hall effect test module 12 is installed on the rotor 101 or the rotating shaft 3. When the rotating shaft 3 rotates one revolution and reaches the Hall effect test module 12, a pulse signal is generated. Thus, the Hall effect test module 12 converts the mechanical geometric displacement of the rotor 101 or the rotating shaft 3 into a pulse or digital quantity through magnetoelectric conversion, thereby acquiring the position and orientation of the rotating shaft 3, the turbine disk 2, and the blades 6. By outputting pulse signals with the same time interval, the leading edge of the pulse signal triggers the infrared thermal imaging module 7 to take a picture, performing infrared thermal imaging. Here, the leading edge specifically refers to the rising edge of the pulse signal waveform. For example, based on the flame spectral characteristics, the present invention selects a short-wavelength band of 1.5-1.6 micrometers or a medium-wavelength band of 3.8-4.05 micrometers for infrared thermal imaging. Simultaneously, a filter is placed in front of the infrared thermal imaging lens to reduce the influence of the combustion flame on the temperature measurement, enabling the infrared thermal imaging to penetrate the flame and measure the temperature of the thermal barrier coating 64, thereby realizing the data acquisition and recording of the temperature field of the turbine blade thermal barrier coating under high-speed rotation.

[0048] With this structure, the present invention measures the temperature field of the surface of the thermal barrier coating 64 based on infrared thermal imaging temperature measurement technology in non-contact temperature measurement methods. Only when the temperature field collected by the infrared thermal imaging module 7 and the temperature field collected by the miniature thermocouple 82 are within the allowable error range is it considered to be a valid surface temperature acquisition, and the thermal insulation effect is evaluated based on the temperature field collected by the miniature thermocouple 82.

[0049] Based on the above system, the present invention provides a method for evaluating the thermal insulation effect of a turbine blade thermal barrier coating under rotating conditions, comprising the following steps:

[0050] The motor is started to drive the turbine disk 2 to rotate, and the gas injection gun 4 is opened to provide load to the turbine blade test piece 1 in the rotating state.

[0051] The temperature field on the surface of the thermal barrier coating 64 is collected by the infrared thermal imaging module 7, the temperature field at the interface between the blade 6 and the thermal barrier coating 64 is collected by the thin film thermocouple 81, and the temperature field on the surface of the thermal barrier coating 64 is collected by the micro thermocouple 82.

[0052] The thermal insulation effect of the thermal barrier coating 64 is evaluated, wherein the thermal insulation effect is the difference between the surface temperature of the thermal barrier coating 64 and the interface temperature between the blade 6 and the thermal barrier coating 64.

[0053] This invention can provide technical support for measuring the temperature field and evaluating the thermal insulation effect of the thermal barrier coating on turbine blades under high-speed rotation, which is beneficial to the design of turbine blade components and the application of thermal barrier coatings.

[0054] To verify the effectiveness of the present invention, a specific embodiment for evaluating the heat insulation effect of the present invention is provided, with the following steps:

[0055] Step 1: Attach thin-film thermocouples 81 and micro thermocouples 82 to the surface and interface of the thermal barrier coating 64 of the turbine blade, respectively.

[0056] First, NiCrAlY is sequentially sprayed onto the surface of blade 6 as an adhesive layer 61 and Al2O3 as an insulating layer 62. Then, a thin-film thermocouple 81 made of iridium-rhodium alloy is prepared on the surface of insulating layer 62 by magnetron sputtering and reinforced by spraying a protective layer 63. Finally, a YSZ of a certain thickness is deposited as a thermal barrier coating 64 by electron beam physical vapor deposition and a miniature thermocouple 82 made of double platinum-rhodium is attached to the surface of thermal barrier coating 64 by flame spraying.

[0057] Step 2: Connect the signal leads of the thin-film thermocouple 81 and the miniature thermocouple 82 to achieve dynamic-to-static conversion.

[0058] First, the lead 91 of the thin-film thermocouple 81 is fixed to the turbine disk and the high-speed shaft, and the lead 92 of the miniature thermocouple 82 is fixed to the turbine disk and the high-speed shaft, and then connected to the rotor 101 of the conductive slip ring 10. At the same time, the stator 102 of the conductive slip ring 10 is also connected to the temperature acquisition device through the stationary signal line 11.

[0059] Step 3: Connect the infrared thermal imaging module 7 and the rotating axis 3 for synchronous triggering, and set the corresponding parameters.

[0060] First, connect the infrared thermal imaging module 7 to the Hall test module 12 on the conductive slip ring 10, start the rotating shaft 3, and test whether the synchronous trigger is stable. In this embodiment, the infrared emissivity is set to 0.85.

[0061] Step 4: Activate the service environment simulation unit. In this embodiment, the rotation speed is set to 10,000 rpm, the temperature to 1150°C, and the experimental time to 60 seconds.

[0062] Step 5: By exporting data from the thin-film thermocouple 81, the micro thermocouple 82, and the infrared thermal imaging module 7, the surface and interface temperature values ​​of the thermal barrier coating 64 are obtained, and the heat insulation effect of the thermal barrier coating 64 is calculated.

[0063] The results of the thin-film thermocouple 81 and the micro thermocouple 82 in this embodiment are as follows: Figure 5 As shown, it can be observed that when the surface temperature of the thermal barrier coating 64 is 1150℃, the temperature at the interface is 1140℃. The results of infrared thermal imaging are as follows. Figure 6 As shown, the surface temperature of the thermal barrier coating 64 is 1154℃, which is basically consistent with the data of the miniature thermocouple 82. Therefore, it can be calculated that the thermal insulation effect of the thermal barrier coating 64 in this service environment is approximately 110℃.

Claims

1. A system for evaluating the thermal insulation effect of a turbine blade thermal barrier coating under rotating conditions, characterized in that, It includes a service environment simulation unit, a temperature field measurement unit, and an evaluation unit; The service environment simulation unit includes a turbine blade test piece (1) and a gas jet (4). The turbine blade test piece (1) is mounted on a turbine disk (2) with a rotating shaft (3) and includes blades (6) and a thermal barrier coating (64) coated on the surface of the blades (6). The gas jet (4) is directed toward the turbine blade test piece (1) and provides load to the turbine blade test piece (1) in a rotating state. The temperature field measurement unit includes an infrared thermal imaging module (7) and a thermocouple module (8). The probe of the infrared thermal imaging module (7) faces the turbine blade test piece (1) to acquire the temperature field of the surface of the thermal barrier coating (64). The thermocouple module (8) includes a thin film thermocouple (81) and a miniature thermocouple (82). The thin film thermocouple (81) is arranged between the blade (6) and the thermal barrier coating (64) to acquire the temperature field of the interface. The miniature thermocouple (82) is arranged on the surface of the thermal barrier coating (64) away from the blade (6) to obtain the temperature field on the surface of the thermal barrier coating (64); The evaluation unit evaluates the heat insulation effect of the thermal barrier coating (64) based on the results of the infrared thermal imaging module (7), the thin film thermocouple (81), and the micro thermocouple (82).

2. The evaluation system for the thermal barrier coating insulation effect of turbine blades in a rotating state according to claim 1, characterized in that, There are multiple gas spray guns (4), which are evenly distributed around the circumference of the combustion platform (5). The combustion produces a high-temperature and high-speed flame with a temperature of 1000℃-1700℃ and a speed of 1-2 Mach. The high-temperature and high-speed flame acts on the leading edge of the turbine blade test piece (1), and the load provided includes centrifugal force, aerodynamic force and hot spot.

3. The evaluation system for the thermal barrier coating effect of turbine blades in a rotating state according to claim 1, characterized in that, An adhesive layer (61), an insulating layer (62), and a protective layer (63) are sequentially disposed between the blade (6) and the thermal barrier coating (64). The adhesive layer (61) is disposed on one side of the blade (6), and the protective layer (63) is disposed on one side of the thermal barrier coating (64). The thin-film thermocouple (81) is disposed between the insulating layer (62) and the protective layer (63). The material of the thin-film thermocouple (81) is iridium-rhodium alloy, and the material of the micro thermocouple (82) is platinum-rhodium alloy.

4. The evaluation system for the thermal barrier coating effect of turbine blades in a rotating state according to claim 1, characterized in that, The thin-film thermocouple (81) is connected to the temperature acquisition device via lead one (91), and the miniature thermocouple (82) is connected to the temperature acquisition device via lead two (92). Lead one (91) and lead two (92) form the signal line (9) of the thermocouple module (8). The signal line (9) is fixed on the blade (6) and is connected to the conductive slip ring (10) in sequence through the central channel of the turbine disk (2) and the rotating shaft (3). The conductive slip ring (10) converts the signal line into a stationary signal line (11).

5. The evaluation system for the thermal barrier coating insulation effect of turbine blades in a rotating state according to claim 4, characterized in that, The conductive slip ring (10) includes a rotor (101) and a stator (102). The rotor (101) is assembled and connected to the rotating shaft (3). The rotor (101) has a circuit board (103) and a gold needle (104) at one end near the stator (102). The signal line (9) passes through the central channel of the rotating shaft (3) into the axial through hole of the rotor (101) and is connected to the rotor (101).

6. The evaluation system for the thermal barrier coating effect of turbine blades in a rotating state according to claim 5, characterized in that, The conductive slip ring (10) receives the temperature signal and converts it into a current signal or a differential voltage signal. By utilizing the contact between the rotor (101) and the stator (102), the current signal or differential voltage signal is transmitted to the temperature acquisition device connected at a remote end through the stationary signal line (11).

7. The evaluation system for the thermal barrier coating effect of turbine blades in a rotating state according to claim 5, characterized in that, A Hall test module (12) is installed on the rotor (101) or the rotating shaft (3). The Hall test module (12) converts the mechanical geometric displacement on the rotor (101) or the rotating shaft (3) into pulses or digital quantities through magnetoelectric conversion, thereby obtaining the position and direction of the rotating shaft (3), outputting pulse signals with the same time interval, and using the leading edge signal of the pulse signal to trigger the infrared thermal imaging module (7) to take pictures and perform infrared thermal imaging.

8. The evaluation system for the thermal barrier coating insulation effect of turbine blades in a rotating state according to claim 5, characterized in that, The infrared thermal imaging module (7) selects a shortwave band of 1.5-1.6 micrometers or a medium wave band of 3.8-4.05 micrometers for infrared thermal imaging, and sets a filter in front of the infrared thermal imaging lens to reduce the influence of the gas flame on the temperature measurement.

9. A method for evaluating the thermal insulation effect of a turbine blade thermal barrier coating under rotating conditions, implemented based on the evaluation system for the thermal insulation effect of a turbine blade thermal barrier coating under rotating conditions as described in claim 1, characterized in that... Includes the following steps: The motor is started to drive the turbine disk (2) to rotate, and the gas injection gun (4) is opened to provide load to the turbine blade test piece (1) in the rotating state; The temperature field of the thermal barrier coating (64) surface is collected by the infrared thermal imaging module (7), the temperature field of the interface between the blade (6) and the thermal barrier coating (64) is collected by the thin film thermocouple (81), and the temperature field of the thermal barrier coating (64) surface is collected by the micro thermocouple (82). The thermal barrier coating (64) is evaluated for its thermal insulation effect, which is the difference between the surface temperature of the thermal barrier coating (64) and the interface temperature between the blade (6) and the thermal barrier coating (64).

10. The method for evaluating the thermal insulation effect of a turbine blade thermal barrier coating under rotating conditions according to claim 9, characterized in that, The rotational speed of the turbine disk (2) is 10,000-20,000 rpm.

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