Turbine blade inner cavity seepage layer performance test method for simulating real working condition

Abstract

The invention discloses a turbine blade inner cavity seepage layer performance test method for simulating real working conditions, which comprises the following steps: S1, determining an inner cavity evaluation area and a blade outer surface heating area of a test blade, and determining test parameters; s3, a test blade is clamped and then subjected to a formal test, cold air with given pressure, temperature and components is introduced into a blade inner cavity of the test blade, a heating area is heated through the spray gun, and loading refers to a real working load atlas in the test; s4, result evaluation: dissecting the test blade at the position of the evaluation area, obtaining an observation sample of the infiltrated layer of the inner cavity of the blade, then observing the infiltrated layer on the observation sample by using a scanning electron microscope, and obtaining the damage condition of the infiltrated layer; and S5, performing statistics on damage conditions of the seepage layer after different test times to form a quantitative relationship between damage of the inner cavity seepage layer and the use time, thereby evaluating whether the inner cavity seepage layer meets the use requirements of the blade or not.

Description

Technical Field

[0001] The invention relates to the technical field of aeroengines and gas turbines, and in particular to a method for testing the performance of a turbine blade inner cavity permeability layer simulating real working conditions. Background Art

[0002] Turbine blades of aircraft engines are generally made of high-temperature alloys and are required to work reliably for a long time when the blade temperature exceeds 1000°C. They are core parts that affect the reliability of the engine. Since turbine blades work in a gas environment, and for carrier-based aircraft power, they also involve a marine salt spray environment, long-term use will cause oxidation and corrosion on the inner and outer surfaces of the blades, which will seriously affect the strength and life of the matrix. Appropriate coatings and infiltration layers must be used for protection to improve the blades' resistance to high-temperature oxidation, gas corrosion, and marine environment corrosion. Since the inner cavity of the turbine blade is a complex cooling channel structure, it is impossible to use a coating process, and a infiltration layer process is generally used. The commonly used infiltration layers are aluminum or aluminide infiltration layers, such as aluminum silicon, aluminum chromium, and aluminum cobalt.

[0003] Due to the large differences in the protective capabilities of different types of infiltration layers, and the serious failures of blade breakage caused by the shedding and cracking of infiltration layers after long-term use at home and abroad, it is necessary to select the type of infiltration layer in combination with the actual working environment and life requirements of the blades when designing turbine blades to ensure that the performance of the infiltration layer meets the use requirements. Due to the poor detectability of the inner cavity of the blade, the difficulty and high cost of simulating the actual working environment of the blade, the protective performance of the infiltration layer is currently only tested in accordance with HB 5258, HB 7740 and HB 20401 for high-temperature oxidation resistance, gas hot corrosion and salt hot corrosion tests at the specimen level to evaluate the basic protective performance of the infiltration layer. For example, when determining the high-temperature oxidation resistance according to HB 5258, 3 to 5 regular cylindrical or sheet-shaped blade substrate material samples with the target infiltration layer are placed in a given high-temperature furnace, and the weight increase of the specimens is measured after cooling at a certain time interval. The average oxidation rate is then calculated using the weight gain value, and the oxidation resistance level of the infiltration layer is determined by comparing with the evaluation standard.

[0004] The above test results can be used as a reference when selecting different penetration layer schemes. However, when evaluating whether a certain penetration layer meets the protection and life requirements of the long-term use of the inner cavity of the turbine blade, the geometric structure of the inner cavity of the turbine blade is far more complex than that of the standard test piece. At the same time, the working temperature, air flow velocity, composition (sulfide, salt, etc.) and large and small working condition loading time are very different from the test piece test, which makes it difficult to reflect the damage of the blade inner cavity penetration layer under actual working conditions and cannot support the design of the blade inner cavity protection scheme. Summary of the invention

[0005] The main purpose of the present invention is to propose a test method for the performance of the inner cavity permeability layer of a turbine blade that simulates real working conditions, so as to achieve a more accurate evaluation of the protective capability of the permeability layer under near-real working conditions by taking a real blade as the test object and simulating the working environment characteristics such as the inner cavity surface temperature, airflow velocity and corrosion components of the blade under typical working conditions, by applying the same load curve as the real working conditions.

[0006] To achieve the above object, the present invention proposes a method for testing the performance of the inner cavity permeability layer of a turbine blade simulating real working conditions, the steps comprising:

[0007] S1. Determine the evaluation area of ​​the inner cavity of the test blade and the heating area of ​​the outer surface of the blade, and determine the test parameters;

[0008] S2. Use the debugging blade to debug the spray gun:

[0009] S3. After clamping the test blade, conduct a formal test: cool air of given pressure, temperature and composition is introduced into the inner cavity of the test blade, and the heating area is heated by a spray gun. The load in the test is referenced to the real working load spectrum;

[0010] S4. Result evaluation: dissect the test blade at the evaluation area to obtain an observation sample of the inner cavity seepage layer of the blade, and then observe the seepage layer on the observation sample using a scanning electron microscope to obtain the damage of the seepage layer;

[0011] S5. Statistically calculate the damage of the seepage layer after different test times to form a quantitative relationship between the damage of the inner cavity seepage layer and the use time, so as to evaluate whether the inner cavity seepage layer meets the use requirements of the blade.

[0012] Preferably, in step S1, the method for determining the evaluation area of ​​the test blade is: using several single-point temperatures on the blade surface measured during operation to correct the three-dimensional temperature field simulation results, and obtain the temperature distribution of the blade during operation; based on the temperature distribution of the inner and outer surfaces of the blade, the inner cavity focus area is selected as the evaluation area in the permeability layer performance test.

[0013] Preferably, in step S1, the method for determining the test blade heating area is: selecting the blade outer surface area corresponding to the inner cavity evaluation area as the test heating area.

[0014] Preferably, in step S1, the test parameters include the surface target temperature T of the test blade heating area, the flow rate Q and temperature T of the inner cavity cold air. C , the proportion of corrosive gas to cold air W, as well as the total test time t, the number of test cycles N and the loading curve.

[0015] Preferably, in step S2, cold air is introduced into the inner cavity of the debugging blade according to the test parameters, a portion on the outer surface of the debugging blade corresponding to the heating area of ​​the test blade is selected, a thermocouple is attached, and then heated by a spray gun, the temperature of the heated portion on the debugging blade is measured by the thermocouple during the debugging process, and the temperature of the heated portion is monitored by an infrared thermometer; by adjusting the amount of fuel and oxygen in the spray gun, when the actual measured temperature of the thermocouple at the heating portion reaches the target temperature T, the measurement situation of the infrared thermometer and the working parameters of the spray gun are recorded as parameters for controlling the heating area of ​​the test blade during the formal test, thereby completing the calibration work before the test.

[0016] Preferably, in step S3, when the test blade is clamped, it is clamped on the tenon of the test blade so that the blade and the airflow at the spray gun outlet are in the required geometric position relationship, simulating the gas airflow temperature, speed and angle to which the heating area of ​​the test blade is subjected.

[0017] Preferably, in step S3, when the test blade is formally tested, loading and unloading are controlled according to the loading curve until the specified N test cycles are completed; water cooling or air cooling cannot be used during the unloading process.

[0018] Preferably, the spray gun is a supersonic gas spray gun.

[0019] Preferably, in step S3, when conducting a formal test, cold air is introduced into the inner cavity of the test blade according to the test parameters, a thermocouple is attached to the outer surface of the heating area of ​​the test blade and then heated by a spray gun, the temperature of the heating area on the test blade during the debugging process is measured by the thermocouple, and the temperature of the heating area is monitored by an infrared thermometer; by adjusting the amount of fuel and oxygen in the spray gun, the actual measured temperature of the thermocouple in the heating area reaches the target temperature T.

[0020] Preferably, in step S4, when the test blade is dissected, a cross section passing through the inner cavity evaluation area is used as the evaluation section, and the test blade is cut from the evaluation section using a wire cutting process.

[0021] Due to the adoption of the above technical solution, the beneficial effects of the present invention are as follows:

[0022] (1) Compared with the current test method using a simple standard specimen, the method proposed in the present invention uses a real blade as the test object, which can fully reflect the impact of the real complex inner cavity surface on the coating state of the permeation layer, load distribution and other aspects.

[0023] (2) Compared with the current test methods that can only evaluate one aspect of the performance of the carbide layer, the method proposed in the present invention can fully simulate the various loads on the inner and outer surfaces of the turbine blade analysis section in real working conditions, and comprehensively reflect the full range of carbide layer damage effects such as high-temperature oxidation, gas corrosion, salt spray corrosion, gas scouring, and alternating loads in one test, more accurately reflect the performance level of the carbide layer in actual use, and support design decision-making.

[0024] (3) The performance verification of the permeation layer under near-real working conditions can be achieved at low cost. Compared with the tens of millions of manufacturing costs, tens of thousands of hourly operating costs and difficult-to-evaluate maintenance costs of aircraft engines, the equipment involved in the test method proposed in the present invention are all conventional equipment in the industry, and the test system has low assembly costs and maintenance costs. In the test, only one or more certain cross-sections of the blades are tested, and the manufacturing cost of the test pieces is low. The test costs of the fuel, gas source, etc. used in the test are much lower than the actual engine operating costs, especially when the test duration reaches hundreds or thousands of hours of life, the cost reduction effect is very significant. BRIEF DESCRIPTION OF THE DRAWINGS

[0025] In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings required for use in the embodiments or the description of the prior art will be briefly introduced below. Obviously, the drawings described below are only some embodiments of the present invention. For ordinary technicians in this field, other drawings can be obtained based on the structures shown in these drawings without paying creative work.

[0026] Figure 1 It is a schematic diagram of the test equipment used in the present invention;

[0027] Figure 2 The schematic diagram of the air-cooled turbine blade structure shows the appearance of the blade on the left and the cross-sectional view of the inner cavity of the blade on the right.

[0028] Figure 3 Schematic diagram of temperature distribution on the outer surface of turbine blades, where the left side is the outer surface and the right side is the inner surface;

[0029] Figure 4 is the loading curve of the test cycle;

[0030] Figure 5 Schematic diagram of the clamping requirements for the test blade.

[0031] Description of Figure Numbers:

[0032] 1. Spray gun; 2. Oxygen tank; 3. Kerosene tank; 4. Infrared thermometer; 5. Cooling air tank; 6. Thermocouple; 7. CNC / data acquisition system; 8. Corrosive gas component tank; A. Evaluation area; B. Heating area; C. Evaluation section; D. Fixture; E. Spray gun gas direction; Q. Cooling air. DETAILED DESCRIPTION

[0033] The following will be combined with the drawings in the embodiments of the present invention to clearly and completely describe the technical solutions in the embodiments of the present invention. Obviously, the described embodiments are only part of the embodiments of the present invention, not all of the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by ordinary technicians in this field without creative work are within the scope of protection of the present invention.

[0034] It should be noted that all directional indications in the embodiments of the present invention (such as up, down, left, right, front, back, etc.) are only used to explain the relative position relationship, movement status, etc. between the components under a certain specific posture (as shown in the accompanying drawings). If the specific posture changes, the directional indication will also change accordingly.

[0035] As shown in the accompanying drawings, a method for testing the performance of the inner cavity permeability layer of a turbine blade simulating real working conditions comprises the following steps:

[0036] S1, determining the evaluation area A of the inner cavity of the test blade and the heating area B of the outer surface of the blade, and determining the test parameters;

[0037] S2. Use the debugging blade to debug the spray gun 1:

[0038] S3. After clamping the test blade, conduct a formal test: cold air of given pressure, temperature and composition is introduced into the inner cavity of the test blade, and the heating area B is heated by spray gun 1. The load in the test refers to the actual working load spectrum; when conducting the formal test, the inner cavity of the test blade is introduced with cold air to simulate not only the temperature and flow rate in the actual working conditions, but also the corresponding corrosive gas components are added to simulate typical inner cavity working environments such as acidic and marine conditions;

[0039] S4. Result evaluation: dissect the test blade at the evaluation area A to obtain an observation sample of the infiltration layer in the blade cavity, and then observe the infiltration layer on the observation sample using a scanning electron microscope to obtain the damage of the infiltration layer;

[0040] S5. Statistically calculate the damage of the seepage layer after different test times to form a quantitative relationship between the damage of the inner cavity seepage layer and the use time, so as to evaluate whether the inner cavity seepage layer meets the use requirements of the blade.

[0041] Combination Figure 1 As shown, the test equipment used in the test mainly includes four parts: a spray gun 1, a cold air supply system, a temperature calibration device and a numerical control / data acquisition system 7.

[0042] The spray gun 1 is used to achieve a target temperature of the outer surface of the blade, that is, to heat the blade.

[0043] The cold air supply system is used to provide cold air of given pressure, temperature and composition to the inner cavity of the blade. The cold air contains corrosive substances such as sulfides and salts.

[0044] The temperature calibration device realizes the temperature measurement and calibration of the heating area B on the outer surface of the blade.

[0045] The numerical control / data acquisition system 7 realizes the loading control of the spray gun 1 and the cold air supply system in the test according to the load curve of the actual working condition, and collects and monitors the relevant test parameters in real time.

[0046] Spray gun 1 is a supersonic gas spray gun, which can achieve subsonic and supersonic flow rates of gas in the target area. Spray gun 1 is connected to oxygen tank 3 and kerosene tank 2 through pipelines. Spray gun 1 has a pressure regulating structure and a combustion chamber inside. The main body of spray gun 1 has a columnar cavity with contraction characteristics, which mainly receives fuel and oxygen and mixes them into fuel gas, and then burns, accelerates and sprays them in the chamber. Oxygen is stored in oxygen tank 3, and aviation kerosene is stored in kerosene tank 2. The pressure regulating structure inside spray gun 1 mainly controls the supply flow of fuel and oxygen by controlling gas pressure, valve opening, etc., to achieve control of the temperature and speed of the airflow at the spray gun outlet.

[0047] The cold air supply system is mainly composed of a cooling air tank 5, a corrosive gas component tank 8, a heating system and a pressure regulating device, which can realize the control of the cold air temperature, flow rate and quantitative mixing of the corrosive gas, and is connected to the blades through the air supply path to simulate the cold air supply to the blade cavity under real working conditions.

[0048] The CNC / digital acquisition system 7 is mainly used to collect, organize and display in real time the variable measurement signals such as pressure, temperature, flow and valve in the above-mentioned test equipment. At the same time, it can control the adjustment of relevant parameters of the corresponding equipment according to the operator's input commands.

[0049] The temperature calibration device mainly utilizes thermocouple 6, infrared thermometer 4 and other equipment to measure the temperature of the target surface of the blade before calibrating the test conditions, so as to calibrate the heating amount of the target surface of the blade by the spray gun 1 during the test.

[0050] Specifically, the thermocouple 6 and the infrared thermometer 4 are connected to the numerical control / digital acquisition system 7 to collect corresponding signals. The numerical control / digital acquisition system 7 is connected to the spray gun 1 to control the pressure regulating structure inside the spray gun 1 to achieve the control of the airflow temperature and speed at the spray gun outlet.

[0051] When conducting a test, it is necessary to determine the test conditions. The test conditions are mainly divided into two parts: physical load and loading curve. The physical load part is determined according to the attached Figure 2It can be seen that the working environment and load of the inner cavity of the turbine blade are mainly determined by the outer surface temperature of the blade and the cold air flow, temperature and corrosive gas composition in the inner cavity of the blade. Before the test, the above-mentioned test equipment is used to simulate the corresponding physical load based on the data of blade surface temperature, cold air flow (or blade cold air inlet and outlet pressure difference), temperature and the proportion of corrosive components in the cold air measured or simulated under the actual operation of the engine. The loading curve mainly refers to the load spectrum of the engine during its entire life cycle, that is, the order and duration of various working conditions during the entire life cycle, which determines the final damage of the permeation layer.

[0052] Since the load spectrum and blade surface temperature field in the actual working condition of the turbine blade are complex, it is difficult or costly to strictly reproduce the actual situation. Therefore, the following two methods are used to simplify them:

[0053] One is to simplify the load spectrum. In engine operating conditions, the damage to blades or inner cavity seepage layers is mainly determined by conditions with large loads and a high proportion of action time. Therefore, strength simulation can be used to obtain the corresponding blade damage coefficients under various operating conditions, and the damage to the blades in small states can be converted to large states, thereby reducing the operating conditions that need to be simulated during the test to one or two, while ensuring that the degree of damage is consistent.

[0054] Another method is to simplify the evaluation area of ​​the blade cavity. The temperature field on the outer surface of the blade is very complex and can only be reproduced in a real engine. Since the area most affected by oxidation and corrosion of the carbide layer is the highest temperature area of ​​the blade, the maximum temperature area of ​​the blade cavity can be selected as the research object, that is, the highest temperature area is selected as the area of ​​concern. When heating the outer surface, it is only necessary to reproduce the temperature load of this area, which greatly reduces the measurement cost.

[0055] The inspectability of the inner cavity of the turbine blade is very poor. The currently feasible method is to dissect the blade and observe the evaluation area with a scanning electron microscope. The turbine blade after the test is cut off near the evaluation area using the wire cutting process, and then the test is inlaid, ground and etched according to the metallographic analysis process. Finally, the following is obtained: Figure 3 The observation sample of the evaluation section C is shown. Then, a scanning electron microscope is used to measure the thickness of the inner cavity of the blade in the evaluation section C, and the state of the penetration layer shedding and cracking is observed to obtain a quantitative damage condition of the penetration layer, thereby supporting the compliance of the penetration layer with the use requirements.

[0056] In step S1, the temperature field of the inner and outer surfaces of the turbine blade during operation is difficult to measure. Generally, the three-dimensional temperature field simulation results are corrected by using several single-point temperatures of the blade surface measured during operation to obtain the temperature distribution of the blade during operation. Based on the temperature distribution of the inner and outer surfaces of the blade, the highest temperature area of ​​the inner cavity is selected as the evaluation area A in the permeation layer performance test, such as Figure 3As shown in the figure. Since it is difficult to measure the temperature of the blade cavity, the local temperature of the blade cavity can be controlled by controlling the local temperature of the outer surface and the inner cavity cooling and working state to ensure the actual temperature of the inner cavity evaluation area A indirectly. Therefore, the outer surface area of ​​the blade corresponding to the inner cavity evaluation area A is selected as the heating area B in the test, and then the specific target temperature T at B is obtained.

[0057] The test parameters include the surface target temperature T of the test blade heating area B, the flow rate Q and temperature T of the inner cavity cold air C , the ratio of corrosive gas to cold air W, as well as the total test time t, the number of test cycles N and the loading curve. The above test parameters can be directly obtained or converted according to the design parameters of the engine and the use load, and will not be repeated here.

[0058] In step S2, the temperature of the heating area B is calibrated, and the spray gun is debugged using a debugging blade. Before the formal test, the measured temperature of the heating area needs to be calibrated, and the working parameters of the spray gun are preliminarily given. The cooling system passes cold air into the inner cavity of the debugging blade according to the test parameters. After the thermocouple is attached to the outer surface of the debugging blade corresponding to the heating area B of the test blade, the spray gun 1 is used for heating. The temperature of the heating part on the debugging blade during the debugging process is measured by the thermocouple, and the temperature of the heating part is monitored by the infrared thermometer at the same time; by adjusting the fuel and oxygen amount of the spray gun 1, when the actual measured temperature of the thermocouple of the heating part reaches the target temperature T, the measurement of the infrared thermometer and the working parameters of the spray gun 1 are recorded as the parameters for controlling the heating area B of the test blade during the formal test, and the calibration work before the test is completed.

[0059] Combination Figure 5 As shown, in step S3, when clamping the test blade, the fixture D is used to clamp the tenon of the test blade, so that the blade and the airflow at the outlet of the spray gun are in the required geometric position relationship, simulating the gas airflow temperature, speed and angle of the heating area of ​​the test blade. Specifically, the height H and angle of the airflow direction of the spray gun 1 outlet need to be determined according to the torsion angle α at the position of the gas direction E and the blade heating area B during operation, to ensure that the high-temperature airflow can accurately act on the rounded corner of the air inlet edge of the heating area B of the test blade after clamping.

[0060] When the test blade is formally tested, the working parameters of the spray gun and the working parameters of the cooling system determined during calibration are used, and cooling air is introduced into the inner cavity of the test blade. After the thermocouple is attached to the outer surface of the heating area B of the test blade, the spray gun 1 is used for heating. The temperature of the heating area B on the test blade during the debugging process is measured by the thermocouple, and the temperature of the heating area B is monitored by an infrared thermometer. By adjusting the amount of fuel and oxygen of the spray gun 1, the actual measured temperature of the thermocouple in the heating area B reaches the target temperature T. Loading and unloading are controlled according to the loading curve until the specified N test cycles are completed; the interval time after each unloading should be determined according to the time required for the blade temperature to cool to the specified temperature, to ensure that the blade temperature meets the requirements after each unloading. In order to avoid additional cold and hot shocks caused by the rapid cooling of the blade, water cooling or air cooling cannot be used during the unloading process.

[0061] In step S4, after the test leaf completes all the test contents, the dissected leaf is Figure 3 The inner cavity part of the evaluation section C shown is observed by scanning electron microscope. Specifically, the cross section through the inner cavity evaluation area A is used as the evaluation section C, and the blade after the test is cut off from the evaluation section C by wire cutting technology, and then the sample is inlaid, ground and corroded according to the metallographic sample production process, and finally the observation sample of the analysis section C is obtained. Then, the thickness of the blade inner cavity permeation layer of the analysis section C is measured by scanning electron microscope, and the state of shedding and cracking of the permeation layer is observed to obtain the quantitative damage of the permeation layer. By statistically analyzing the damage of the inner cavity evaluation section C after different test times, a quantitative relationship between the damage of the inner cavity permeation layer and the use time is formed, so as to evaluate whether the inner cavity permeation layer meets the blade use requirements.

[0062] The above description is only a preferred embodiment of the present invention, and does not limit the patent scope of the present invention. All equivalent structural changes made by using the contents of the present invention specification and drawings under the inventive concept of the present invention, or directly / indirectly applied in other related technical fields are included in the patent protection scope of the present invention.

Claims

1. A method for testing the performance of the inner cavity permeability layer of a turbine blade simulating real working conditions, characterized in that the steps include: S1. Determine the evaluation area of ​​the inner cavity of the test blade and the heating area of ​​the outer surface of the blade, and determine the test parameters; S2. Use the debugging blade to debug the spray gun: S3. After clamping the test blade, conduct a formal test: cool air of given pressure, temperature and composition is introduced into the inner cavity of the test blade, and the heating area is heated by a spray gun. The load in the test is referenced to the real working load spectrum; S4. Result evaluation: dissect the test blade at the evaluation area to obtain an observation sample of the inner cavity seepage layer of the blade, and then observe the seepage layer on the observation sample using a scanning electron microscope to obtain the damage of the seepage layer; S5. Statistically calculate the damage of the seepage layer after different test times to form a quantitative relationship between the damage of the inner cavity seepage layer and the use time, so as to evaluate whether the inner cavity seepage layer meets the use requirements of the blade.

2. A turbine blade inner cavity permeability layer performance test method simulating real working conditions as claimed in claim 1, characterized in that: In step S1, the method for determining the evaluation area of ​​the test blade is: using several single-point temperatures on the blade surface measured during operation to correct the three-dimensional temperature field simulation result, and obtaining the temperature distribution of the blade during operation; Based on the temperature distribution on the inner and outer surfaces of the blade, the inner cavity area of ​​interest was selected as the evaluation area in the permeability layer performance test.

3. A turbine blade inner cavity permeability layer performance test method simulating real working conditions as claimed in claim 2, characterized in that: In step S1, the method for determining the test blade heating area is: selecting the blade outer surface area corresponding to the inner cavity evaluation area as the test heating area.

4. A turbine blade inner cavity permeability layer performance test method simulating real working conditions as claimed in claim 1, characterized in that: In step S1, the test parameters include the surface target temperature T of the test blade heating area, the flow rate Q and temperature T of the inner cavity cold air. C , the proportion of corrosive gas to cold air W, as well as the total test time t, the number of test cycles N and the loading curve.

5. A turbine blade inner cavity permeability layer performance test method simulating real working conditions as claimed in claim 4, characterized in that: In step S2, cold air is introduced into the inner cavity of the debugging blade according to the test parameters, a portion corresponding to the heating area of ​​the test blade is selected on the outer surface of the debugging blade, a thermocouple is attached, and then heated by a spray gun. The temperature of the heated portion on the debugging blade during the debugging process is measured by the thermocouple, and the temperature of the heated portion is monitored by an infrared thermometer. By adjusting the amount of fuel and oxygen in the spray gun, when the actual measured temperature of the thermocouple at the heating portion reaches the target temperature T, the measurement situation of the infrared thermometer and the working parameters of the spray gun are recorded as parameters for controlling the heating area of ​​the test blade during the formal test, thereby completing the calibration work before the test.

6. A turbine blade inner cavity permeability layer performance test method simulating real working conditions as claimed in claim 1, characterized in that: In step S3, when the test blade is clamped, it is clamped on the tenon of the test blade so that the blade and the airflow at the spray gun outlet are in the required geometric position relationship, simulating the gas airflow temperature, speed and angle to which the heating area of ​​the test blade is subjected.

7. A turbine blade inner cavity permeability layer performance test method simulating real working conditions as claimed in claim 4, characterized in that: In step S3, when the test blade is formally tested, loading and unloading are controlled according to the loading curve until the specified N test cycles are completed; water cooling or air cooling cannot be used during the unloading process.

8. A turbine blade inner cavity permeability layer performance test method simulating real working conditions as claimed in claim 1, characterized in that: The spray gun is a supersonic gas spray gun.

9. A turbine blade inner cavity permeability layer performance test method simulating real working conditions as claimed in claim 1, characterized in that: In step S3, when conducting a formal test, cold air is introduced into the inner cavity of the test blade according to the test parameters, a thermocouple is attached to the outer surface of the heating area of ​​the test blade and then heated by a spray gun. The temperature of the heating area on the test blade during the debugging process is measured by the thermocouple, and the temperature of the heating area is monitored by an infrared thermometer. By adjusting the amount of fuel and oxygen in the spray gun, the actual measured temperature of the thermocouple in the heating area reaches the target temperature T.

10. A turbine blade inner cavity permeability layer performance test method simulating real working conditions as claimed in claim 1, characterized in that: In step S4, when the test blade is dissected, a cross section passing through the inner cavity evaluation area is used as the evaluation section, and the test blade is cut from the evaluation section using a wire cutting process.

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