A Modeling Method and System for Boundary Conditions of High-Temperature Cold-Effect Experiments of a Stationary Turbine Cascade

Abstract

The present invention relates to the field of heat transfer and mass transfer of aeroengines, and discloses a method and system for modeling boundary conditions of a high-temperature cold effectiveness experiment of a stationary turbine cascade. On the basis of considering the size scaling ratio of the turbine cascade, the simulated boundary conditions under low-temperature modeling working conditions are accurately obtained, so that parameters such as the mainstream temperature, pressure, test cold air temperature, test cold air flow rate, and thermal conductivity of the simulated cascade material under low-temperature modeling working conditions are matched with the mainstream gas temperature, pressure, actual cold air temperature, flow rate conditions, actual cold air flow rate, and thermal conductivity of the turbine cascade material. The present invention can ensure that the Reynolds numbers of the simulated cascade and the actual turbine cascade are consistent under the high-temperature cold effectiveness experiment of the turbine cascade, so that the modeling test can truly reflect the performance of the turbine cascade under actual high-temperature working conditions, thereby improving the accuracy and reliability of the high-temperature cold effectiveness experiment of the turbine cascade and providing strong support for the design and optimization of the turbine cascade.

Description

Technical Field

[0001] The present invention relates to the field of heat transfer and mass transfer of aeroengines, and discloses a method and system for modeling boundary conditions of a high-temperature cold effectiveness experiment of a stationary turbine cascade. Background Art

[0002] Developing an efficient cooling technology for turbine blades has become one of the key factors in the research and development of high-performance engines. At the same time, before the turbine blades are officially installed, they need to undergo strict test experiments to verify whether their cooling performance meets the requirements. The comprehensive cold effectiveness experiment of turbine blades is one of the technical ways to verify the cooling performance of the blades. With the existing experimental conditions, it is extremely difficult to directly carry out the comprehensive cold effectiveness experiment under real working conditions (≮1800K, ≮3MPa, high working conditions). There are mainly the following difficulties: First, it is difficult to collect signal data of pressure, temperature, and flow rate under high-temperature and high-pressure conditions; second, the test bench under high-temperature and high-pressure conditions bears a huge thermal load; third, the experimental cost is extremely high. Therefore, on the premise that it is difficult to carry out the comprehensive cold effectiveness experiment under real working conditions, in order to accurately obtain the real comprehensive cold effectiveness data, it is necessary to carry out a similarity study of the comprehensive cold effectiveness experiment in order to obtain relatively accurate comprehensive cold effectiveness data under low working conditions. Summary of the Invention

[0003] The purpose of the present invention is to provide a method and system for modeling boundary conditions of a high-temperature cold effectiveness experiment of a stationary turbine cascade, which can ensure that the Reynolds numbers of the simulated cascade and the actual turbine cascade are the same under the high-temperature cold effectiveness experiment of the turbine cascade, so that the modeling test can truly reflect the performance of the turbine cascade under the actual high-temperature working conditions, thereby improving the accuracy and reliability of the high-temperature cold effectiveness experiment of the turbine cascade.

[0004] In order to achieve the above technical effects, the technical solution adopted by the present invention is:

[0005] A method for modeling boundary conditions of a high-temperature cold effectiveness experiment of a stationary turbine cascade includes:

[0006] According to the size parameters of the turbine cascade to be analyzed, the turbine cascade is scaled proportionally to obtain the scaling ratio of the simulated cascade of the turbine cascade under the low-temperature modeling working conditions;

[0007] Under the condition that the Mach number and the simulated cascade Reynolds number under the low-temperature modeling working conditions are the same as the Mach number and the turbine cascade Reynolds number under the real working conditions, according to the mainstream gas temperature and mainstream gas pressure of the turbine cascade under the real working conditions, and the designed test mainstream temperature of the simulated cascade under the low-temperature modeling working conditions, the test mainstream pressure of the simulated cascade under the low-temperature modeling working conditions is analyzed and obtained;

[0008] Under the condition that the percentage of the test cold air flow rate in the low-temperature simulation working condition to the designed test mainstream flow rate is consistent with the percentage of the actual cold air flow rate in the real working condition to the mainstream gas flow rate, based on the actual cold air dynamic viscosity in the real working condition, the mainstream gas dynamic viscosity, and the test mainstream dynamic viscosity in the low-temperature simulation working condition, the test cold air dynamic viscosity in the low-temperature simulation working condition is analyzed and obtained;

[0009] Based on the test cold air dynamic viscosity in the low-temperature simulation working condition, the test cold air temperature in the low-temperature simulation working condition is analyzed and obtained;

[0010] Under the condition that the ratio of the test mainstream thermal conductivity to the simulated cascade material thermal conductivity remains consistent with the ratio of the gas thermal conductivity of the mainstream gas to the actual thermal conductivity of the turbine cascade material, based on the gas thermal conductivity of the mainstream gas, the actual thermal conductivity of the turbine cascade material, and the test mainstream thermal conductivity, the simulated cascade material thermal conductivity is analyzed and obtained;

[0011] According to the simulated cascade material thermal conductivity, the simulated cascade material corresponding to the low-temperature simulation working condition is selected to prepare the corresponding simulated cascade. Under the conditions of the designed test mainstream temperature, the analyzed test mainstream pressure, and the test cold air temperature, the static turbine cascade comprehensive cold efficiency experiment is carried out using the simulated cascade.

[0012] Further, the test mainstream pressure of the simulated cascade under the low-temperature simulation working condition is obtained according to analysis, where is the test mainstream pressure under the low-temperature simulation working condition, is the designed test mainstream temperature under the low-temperature simulation working condition, is the dynamic viscosity of the test mainstream under the low-temperature simulation working condition, is the adiabatic index of the test mainstream under the low-temperature simulation working condition, is the scaling ratio of the simulated cascade relative to the turbine cascade, is the mainstream gas pressure under the real working condition, is the mainstream gas temperature under the real working condition, is the dynamic viscosity of the mainstream gas under the real working condition, is the adiabatic index of the mainstream gas under the real working condition.

[0013] Further, the test cold air dynamic viscosity under the low-temperature simulation working condition , where is the test mainstream dynamic viscosity under the low-temperature simulation working condition, is the mainstream gas dynamic viscosity under the real working condition, is the actual cold air dynamic viscosity under the real working condition.

[0014] Further, the method for analyzing and obtaining the test cold air temperature under the low-temperature modularization working condition includes: analyzing and obtaining the test cold air dynamic viscosity under the low-temperature modularization working condition Based on this, use to analyze and obtain the test cold air temperature under the low-temperature modularization working condition where = 1.7894×10 -5 Pa•s, is a constant related to the gas type, and the value for air is 110.4 K.

[0015] Further, the simulated cascade material thermal conductivity is obtained according to analysis, where is the simulated cascade material thermal conductivity, is the thermal conductivity of the mainstream gas under the real working condition, is the actual thermal conductivity of the turbine cascade material, is the thermal conductivity of the test mainstream under the low-temperature modularization working condition.

[0016] To achieve the above technical effects, the present invention also provides a static turbine cascade high-temperature cold efficiency experiment boundary condition modularization system, including:

[0017] A cascade model construction module for proportionally scaling the turbine cascade according to the size parameters of the turbine cascade to be analyzed, obtaining the scaling ratio of the simulated cascade under the low-temperature modularization working condition, and constructing a three-dimensional finite element model of the simulated cascade;

[0018] A mainstream parameter analysis module for analyzing and obtaining the test mainstream pressure of the simulated cascade under the low-temperature modularization working condition according to the mainstream gas temperature and mainstream gas pressure of the turbine cascade under the real working condition, and the designed test mainstream temperature of the simulated cascade under the low-temperature modularization working condition, under the condition that the Mach number and the simulated cascade Reynolds number under the low-temperature modularization working condition are consistent with the Mach number and the turbine cascade Reynolds number of the real working condition;

[0019] A cold air temperature analysis module for analyzing and obtaining the test cold air dynamic viscosity under the low-temperature modularization working condition according to the actual cold air dynamic viscosity, mainstream gas dynamic viscosity under the real working condition, and test mainstream dynamic viscosity under the low-temperature modularization working condition, under the condition that the percentage of the test cold air flow rate in the designed test mainstream flow rate under the low-temperature modularization working condition is consistent with the percentage of the actual cold air flow rate in the mainstream gas flow rate under the real working condition; and analyzing and obtaining the test cold air temperature under the low-temperature modularization working condition according to the test cold air dynamic viscosity under the low-temperature modularization working condition;

[0020] The simulated cascade parameter determination module is used to analyze and obtain the thermal conductivity of the simulated cascade material according to the gas thermal conductivity of the mainstream gas, the actual thermal conductivity of the turbine cascade material, and the test mainstream thermal conductivity under the condition that the ratio of the test mainstream thermal conductivity to the thermal conductivity of the simulated cascade material remains the same as the ratio of the gas thermal conductivity of the mainstream gas to the actual thermal conductivity of the turbine cascade material;

[0021] The simulation analysis module is used to select the simulated cascade material under the low-temperature modularization working condition according to the thermal conductivity of the simulated cascade material to prepare the corresponding simulated cascade, and carry out the comprehensive cold efficiency simulation analysis of the stationary turbine cascade by using the three-dimensional finite element model of the simulated cascade under the conditions of the designed test mainstream temperature, the analyzed test mainstream pressure, test cold air temperature, and test cold air flow rate.

[0022] Furthermore, in the mainstream parameter analysis module, according to the analyzed test mainstream pressure of the simulated cascade under the low-temperature modularization working condition ; where is the designed test mainstream temperature under the low-temperature modularization working condition, is the dynamic viscosity of the test mainstream, is the adiabatic index of the test mainstream, is the scaling ratio of the simulated cascade relative to the turbine cascade, is the mainstream gas pressure under the real working condition, is the mainstream gas temperature under the real working condition, is the dynamic viscosity of the mainstream gas, is the adiabatic index of the mainstream gas.

[0023] Furthermore, in the cold air temperature analysis module, the dynamic viscosity of the test cold air under the low-temperature modularization working condition, where is the dynamic viscosity of the test mainstream under the low-temperature modularization working condition, is the dynamic viscosity of the mainstream gas under the real working condition, is the actual dynamic viscosity of the cold air under the real working condition; and then use to analyze and obtain the test cold air temperature under the low-temperature modularization working condition, where = 1.7894×10 -5 Pa•s, is a constant related to the gas type, and the value of air is 110.4 K.

[0024] Furthermore, in the simulated cascade parameter determination module, according to analyze and obtain the thermal conductivity of the simulated cascade material , where is the thermal conductivity of the mainstream gas under actual working conditions, is the actual thermal conductivity of the turbine cascade material, is the thermal conductivity of the test mainstream under low-temperature modularization working conditions.

[0025] Compared with the prior art, the beneficial effects of the present invention are as follows: Based on considering the size scaling ratio of the turbine cascade, the present invention accurately obtains the simulated boundary conditions under low-temperature modularization working conditions, so that parameters such as the test mainstream temperature, pressure, test cold air temperature, test cold air flow rate, and simulated cascade material thermal conductivity under low-temperature modularization working conditions match the mainstream gas temperature, pressure, actual cold air temperature, flow rate conditions, actual cold air flow rate, and turbine cascade material thermal conductivity; it can ensure that the Reynolds numbers of the simulated cascade and the actual turbine cascade are consistent in the high-temperature cold efficiency experiment of the turbine cascade, enabling the modularization test to truly reflect the performance of the actual turbine cascade under high-temperature working conditions, thereby improving the accuracy and reliability of the high-temperature cold efficiency experiment of the turbine cascade and providing strong support for the design and optimization of the turbine cascade. Description of the Drawings

[0026] Figure 1 is the flow chart of the modularization method for the boundary conditions of the high-temperature cold efficiency experiment of the stationary turbine cascade in Embodiment 1 or 2;

[0027] Figure 2 is the structural block diagram of the modularization system for the boundary conditions of the high-temperature cold efficiency experiment of the stationary turbine cascade in Embodiment 1;

[0028] Among them, 1. Cascade model construction module; 2. Mainstream parameter analysis module; 3. Cold air temperature analysis module; 4. Simulated cascade parameter determination module; 5. Simulation analysis module. Specific Embodiments

[0029] The present invention will be further described in detail below in conjunction with the embodiments and the drawings. However, this should not be construed as limiting the scope of the above-mentioned subject matter of the present invention to the following embodiments. Any technology implemented based on the content of the present invention belongs to the scope of the present invention.

[0030] Embodiment 1

[0031] Refer to Figure 1 and Figure 2 , a modularization method for the boundary conditions of the high-temperature cold efficiency experiment of a stationary turbine cascade, including:

[0032] According to the size parameters of the turbine cascade to be analyzed, the turbine cascade is scaled proportionally to obtain the simulated cascade scaling ratio of the turbine cascade under low-temperature modularization working conditions;

[0033] Under the condition that the Mach number and the simulated cascade Reynolds number under the low-temperature simulation working conditions are consistent with the Mach number and the turbine cascade Reynolds number under the actual working conditions, according to the mainstream gas temperature and mainstream gas pressure of the turbine cascade under the actual working conditions, as well as the designed test mainstream temperature of the simulated cascade under the low-temperature simulation working conditions, the test mainstream pressure of the simulated cascade under the low-temperature simulation working conditions is analyzed and obtained;

[0034] Under the condition that the percentage of the test cold air flow rate in the designed test mainstream flow rate under the low-temperature simulation working conditions is consistent with the percentage of the actual cold air flow rate in the mainstream gas flow rate under the actual working conditions, according to the actual cold air dynamic viscosity, mainstream gas dynamic viscosity under the actual working conditions, and the test mainstream dynamic viscosity under the low-temperature simulation working conditions, the test cold air dynamic viscosity under the low-temperature simulation working conditions is analyzed and obtained;

[0035] According to the test cold air dynamic viscosity under the low-temperature simulation working conditions, the test cold air temperature under the low-temperature simulation working conditions is analyzed and obtained;

[0036] Under the condition that the ratio of the test mainstream thermal conductivity to the thermal conductivity of the simulated cascade material remains consistent with the ratio of the gas thermal conductivity of the mainstream gas to the actual thermal conductivity of the turbine cascade material, according to the gas thermal conductivity of the mainstream gas, the actual thermal conductivity of the turbine cascade material, and the test mainstream thermal conductivity, the thermal conductivity of the simulated cascade material is analyzed and obtained;

[0037] According to the thermal conductivity of the simulated cascade material, select the simulated cascade material under the low-temperature simulation working conditions to prepare the corresponding simulated cascade. Under the conditions of the designed test mainstream temperature, the test mainstream pressure and test cold air temperature analyzed and obtained, use the simulated cascade to carry out the comprehensive cold efficiency experiment of the stationary turbine cascade.

[0038] In this embodiment, on the basis of considering the size scaling ratio of the turbine cascade, the simulated boundary conditions under the low-temperature simulation working conditions are accurately obtained, so that parameters such as the test mainstream temperature, pressure, test cold air temperature, test cold air flow rate, and thermal conductivity of the simulated cascade material under the low-temperature simulation working conditions match the mainstream gas temperature, pressure, actual cold air temperature, flow rate conditions, actual cold air flow rate, and thermal conductivity of the turbine cascade material, ensuring that the Reynolds number of the simulated cascade and the actual turbine cascade is kept consistent under the high-temperature cold efficiency experiment of the turbine cascade, so that the simulation test can truly reflect the performance of the turbine cascade under the actual high-temperature working conditions, thereby improving the accuracy and reliability of the high-temperature cold efficiency experiment of the turbine cascade and providing strong support for the design and optimization of the turbine cascade.

[0039] Based on the same inventive concept, this embodiment also provides a system for modeling the boundary conditions of the high-temperature cold efficiency experiment of a stationary turbine cascade, including:

[0040] The cascade model construction module 1 is used to perform equal-proportion scaling on the turbine cascade according to the size parameters of the turbine cascade to be analyzed, obtain the simulation cascade scaling ratio of the turbine cascade under the low-temperature model working conditions, and construct a three-dimensional finite element model of the simulation cascade;

[0041] The mainstream parameter analysis module 2 is used to analyze and obtain the test mainstream pressure of the simulation cascade under the low-temperature model working conditions according to the mainstream gas temperature and mainstream gas pressure of the turbine cascade under the actual working conditions, and the designed test mainstream temperature of the simulation cascade under the low-temperature model working conditions, on the condition that the Mach number and the Reynolds number of the simulation cascade under the low-temperature model working conditions are kept consistent with the Mach number and the Reynolds number of the actual working conditions;

[0042] The cold air temperature analysis module 3 is used to analyze and obtain the test cold air dynamic viscosity under the low-temperature model working conditions according to the actual cold air dynamic viscosity, mainstream gas dynamic viscosity under the actual working conditions, and the test mainstream dynamic viscosity under the low-temperature model working conditions, on the condition that the percentage of the test cold air flow rate in the designed test mainstream flow rate under the low-temperature model working conditions is consistent with the percentage of the actual cold air flow rate in the mainstream gas flow rate under the actual working conditions; and analyze and obtain the test cold air temperature under the low-temperature model working conditions according to the test cold air dynamic viscosity under the low-temperature model working conditions;

[0043] The simulation cascade parameter determination module 4 is used to analyze and obtain the simulation cascade material thermal conductivity according to the gas thermal conductivity of the mainstream gas, the actual thermal conductivity of the turbine cascade material, and the test mainstream thermal conductivity, on the condition that the ratio of the test mainstream thermal conductivity to the simulation cascade material thermal conductivity is kept consistent with the ratio of the gas thermal conductivity of the mainstream gas to the actual thermal conductivity of the turbine cascade material;

[0044] The simulation analysis module 5 is used to select the simulation cascade material under the low-temperature model working conditions according to the simulation cascade material thermal conductivity to prepare the corresponding simulation cascade, and carry out the comprehensive cold efficiency simulation analysis of the stationary turbine cascade by using the three-dimensional finite element model of the simulation cascade under the designed test mainstream temperature and the analyzed test mainstream pressure, test cold air temperature, and test cold air flow rate conditions.

[0045] Embodiment 2

[0046] See Figure 1 , a method for modeling the boundary conditions of the high-temperature cold efficiency experiment of a stationary turbine cascade, including:

[0047] Step 1: Perform equal-proportion scaling on the turbine cascade according to the size parameters of the turbine cascade to be analyzed, and obtain the simulation cascade scaling ratio of the turbine cascade under the low-temperature model working conditions.

[0048] Step 2: Under the condition that the Mach number and the simulated cascade Reynolds number under the low-temperature modularization working condition are consistent with the Mach number and the turbine cascade Reynolds number under the real working condition, according to the mainstream gas temperature and mainstream gas pressure of the turbine cascade under the real working condition, as well as the designed test mainstream temperature of the simulated cascade under the low-temperature modularization working condition, analyze and obtain the test mainstream pressure of the simulated cascade under the low-temperature modularization working condition;

[0049] In this embodiment, when conducting the comprehensive cold efficiency experiment, the temperature and pressure of the mainstream gas under the high-temperature working condition are known, and the given designed test mainstream temperature under the low-temperature modularization working condition is . According to the actual test conditions, use to analyze and obtain the test mainstream pressure of the simulated cascade under the low-temperature modularization working condition; where is the designed test mainstream temperature under the low-temperature modularization working condition, is the dynamic viscosity of the test mainstream, is the adiabatic index of the test mainstream, is the scaling ratio of the simulated cascade relative to the turbine cascade, is the mainstream gas pressure under the real working condition, is the mainstream gas temperature under the real working condition, is the dynamic viscosity of the mainstream gas, is the adiabatic index of the mainstream gas. At this time, it is necessary to judge whether the test mainstream pressure requirement can be met according to the actual test conditions. If not, the test mainstream temperature under the low-temperature modularization working condition can be reduced, and iterative calculation can be carried out again until the actual test conditions meet the test mainstream pressure requirement corresponding to the test mainstream temperature.

[0050] Step 3: Under the condition that the percentage of the test cold air flow rate in the designed test mainstream flow rate under the low-temperature modularization working condition is consistent with the percentage of the actual cold air flow rate in the mainstream gas flow rate under the real working condition, according to the actual cold air dynamic viscosity, mainstream gas dynamic viscosity under the real working condition, and the test mainstream dynamic viscosity under the low-temperature modularization working condition, analyze and obtain the test cold air dynamic viscosity under the low-temperature modularization working condition;

[0051] The test cold air dynamic viscosity under the low-temperature modularization working condition in this embodiment, where is the test mainstream dynamic viscosity under the low-temperature modularization working condition, is the mainstream gas dynamic viscosity under the real working condition, is the actual cold air dynamic viscosity under the real working condition.

[0052] Step 4: According to the test cold air dynamic viscosity under the low-temperature modularization working condition, analyze and obtain the test cold air temperature under the low-temperature modularization working condition;

[0053] In this embodiment, on the basis of analyzing and obtaining the test cold air dynamic viscosity under the low-temperature modularization condition, adopt to analyze and obtain the test cold air temperature under the low-temperature modularization condition , where = 1.7894×10 -5 Pa•s, is a constant related to the gas type, and the value of air is 110.4 K.

[0054] Step Five: Under the condition that the ratio of the test mainstream thermal conductivity to the simulated cascade material thermal conductivity remains consistent with the ratio of the mainstream gas thermal conductivity of the mainstream gas to the actual thermal conductivity of the turbine cascade material, analyze and obtain the simulated cascade material thermal conductivity according to the mainstream gas thermal conductivity of the mainstream gas, the actual thermal conductivity of the turbine cascade material, and the test mainstream thermal conductivity;

[0055] The comprehensive cold effect is a dimensionless temperature evaluation index that comprehensively considers the internal cooling, solid heat conduction, and external film cooling of the turbine cascade. The thermal conductivity of the solid material not only affects the heat transfer inside the material, but also affects the proportion of internal cooling and external film cooling in the comprehensive cold effect. Therefore, the selection of solid materials has a significant impact on the cold effect experiment. In this embodiment, is used to analyze and obtain the simulated cascade material thermal conductivity , which can ensure that the ratio of the test mainstream thermal conductivity to the simulated cascade material thermal conductivity remains consistent with the ratio of the mainstream gas thermal conductivity of the mainstream gas to the actual thermal conductivity of the turbine cascade material, so as to select a suitable processing material for the simulated cascade test piece to ensure that the solid material does not affect the comprehensive cold effect under high and low conditions. Among them is the thermal conductivity of the mainstream gas under the real working condition, is the actual thermal conductivity of the turbine cascade material, is the thermal conductivity of the test mainstream under the low-temperature modularization condition.

[0056] Step Six: Select the simulated cascade material corresponding to the simulated cascade under the low-temperature modularization condition according to the simulated cascade material thermal conductivity, and carry out the comprehensive cold effect experiment of the stationary turbine cascade under the conditions of the designed test mainstream temperature, the analyzed test mainstream pressure, test cold air temperature, and test cold air flow rate.

[0057] The boundary condition modularization method system for the high-temperature cold effect experiment of the stationary turbine cascade in this embodiment comprehensively considers the influence of the Reynolds number on the modularization effect and broadens the application range of mainstream modularization.

[0058] The above are only the preferred embodiments of the present invention, and are not intended to limit the present invention. Any modifications, equivalent replacements, improvements, etc. made within the spirit and principle of the present invention shall be included within the protection scope of the present invention.

Claims

1. A method for modeling the boundary conditions of a high-temperature cold efficiency experiment of a stationary turbine cascade, characterized in that, Comprising: According to the dimensional parameters of the turbine cascade to be analyzed, performing an equal-proportion scaling on the turbine cascade to obtain the scaling ratio of the simulated cascade of the turbine cascade under the low-temperature modeling working condition; Under the condition that the Mach number and the simulated cascade Reynolds number under the low-temperature modeling working condition are kept consistent with the Mach number and the turbine cascade Reynolds number under the real working condition, based on the mainstream gas temperature and mainstream gas pressure of the turbine cascade under the real working condition, and the designed test mainstream temperature of the simulated cascade under the low-temperature modeling working condition, analyzing and obtaining the test mainstream pressure of the simulated cascade under the low-temperature modeling working condition; Under the condition that the percentage of the test cold air flow rate in the designed test mainstream flow rate under the low-temperature modeling working condition is consistent with the percentage of the actual cold air flow rate in the mainstream gas flow rate under the real working condition, based on the actual cold air dynamic viscosity, mainstream gas dynamic viscosity under the real working condition, and the test mainstream dynamic viscosity under the low-temperature modeling working condition, analyzing and obtaining the test cold air dynamic viscosity under the low-temperature modeling working condition; Based on the test cold air dynamic viscosity under the low-temperature modeling working condition, analyzing and obtaining the test cold air temperature under the low-temperature modeling working condition; Under the condition that the ratio of the test mainstream thermal conductivity to the simulated cascade material thermal conductivity is kept consistent with the ratio of the gas thermal conductivity of the mainstream gas to the actual thermal conductivity of the turbine cascade material, based on the gas thermal conductivity of the mainstream gas, the actual thermal conductivity of the turbine cascade material, and the test mainstream thermal conductivity, analyzing and obtaining the simulated cascade material thermal conductivity; Selecting the simulated cascade material under the low-temperature modeling working condition according to the simulated cascade material thermal conductivity to prepare the corresponding simulated cascade, and under the conditions of the designed test mainstream temperature, the test mainstream pressure and test cold air temperature obtained by analysis, carrying out a comprehensive cold efficiency experiment of the stationary turbine cascade by using the simulated cascade.

2. The boundary condition modeling method for the high-temperature cold efficiency experiment of the stationary turbine cascade according to claim 1, characterized in that The test mainstream pressure of the simulated cascade under the low-temperature model working condition is determined according to analysis, where is the test mainstream pressure under the low-temperature model working condition, is the designed test mainstream temperature under the low-temperature model working condition, is the dynamic viscosity of the test mainstream under the low-temperature model working condition, is the adiabatic index of the test mainstream under the low-temperature model working condition, is the scaling ratio of the simulated cascade relative to the turbine cascade, is the mainstream gas pressure under the actual working condition, is the mainstream gas temperature under the actual working condition, is the dynamic viscosity of the mainstream gas under the actual working condition, is the adiabatic index of the mainstream gas under the actual working condition.

3. The boundary condition modeling method for the high-temperature cold efficiency experiment of the stationary turbine cascade according to claim 1, characterized in that The test cold air dynamic viscosity under the low temperature modeling conditions ,in is the mainstream dynamic viscosity of the test under low temperature modeling conditions, is the dynamic viscosity of mainstream fuel gas under real working conditions, It is the actual cooling air dynamic viscosity under real working conditions.

4. The method for modeling the boundary conditions of the high-temperature cold efficiency experiment of a stationary turbine cascade according to claim 3, wherein The method for analyzing and obtaining the test cold air temperature under the low-temperature conditioning working conditions includes: on the basis of analyzing and obtaining the test cold air dynamic viscosity under the low-temperature conditioning working conditions , adopting to analyze and obtain the test cold air temperature under the low-temperature conditioning working conditions , where = 1.7894×10 -5 Pa•s, is a constant related to the gas type, and the value for air is 110.4 K.

5. The method for modeling the boundary conditions of the high-temperature cold efficiency experiment of the stationary turbine cascade according to claim 1, wherein The thermal conductivity of the simulated cascade material is obtained according to analysis, where is the thermal conductivity of the simulated cascade material, is the thermal conductivity of the mainstream gas under actual working conditions, is the actual thermal conductivity of the turbine cascade material, is the thermal conductivity of the test mainstream under low-temperature model working conditions.

6. A boundary condition modeling system for high-temperature cold efficiency experiments of a stationary turbine cascade, characterized in that, Comprising: A cascade model construction module, configured to perform an equal-proportion scaling on the turbine cascade according to the dimensional parameters of the turbine cascade to be analyzed, obtain the scaling ratio of the simulated cascade of the turbine cascade under the low-temperature modeling working condition, and construct a three-dimensional finite element model of the simulated cascade; A mainstream parameter analysis module, configured to, under the condition that the Mach number and the simulated cascade Reynolds number under the low-temperature modeling working condition are kept consistent with the Mach number and the turbine cascade Reynolds number under the real working condition, based on the mainstream gas temperature and mainstream gas pressure of the turbine cascade under the real working condition, and the designed test mainstream temperature of the simulated cascade under the low-temperature modeling working condition, analyze and obtain the test mainstream pressure of the simulated cascade under the low-temperature modeling working condition; A cold air temperature analysis module, configured to, under the condition that the percentage of the test cold air flow rate in the designed test mainstream flow rate under the low-temperature modeling working condition is consistent with the percentage of the actual cold air flow rate in the mainstream gas flow rate under the real working condition, based on the actual cold air dynamic viscosity, mainstream gas dynamic viscosity under the real working condition, and the test mainstream dynamic viscosity under the low-temperature modeling working condition, analyze and obtain the test cold air dynamic viscosity under the low-temperature modeling working condition; and based on the test cold air dynamic viscosity under the low-temperature modeling working condition, analyze and obtain the test cold air temperature under the low-temperature modeling working condition; The simulated cascade parameter determination module is used to analyze and obtain the thermal conductivity of the simulated cascade material according to the gas thermal conductivity of the mainstream gas, the actual thermal conductivity of the turbine cascade material, and the test mainstream thermal conductivity, under the condition that the ratio of the test mainstream thermal conductivity to the thermal conductivity of the simulated cascade material remains the same as the ratio of the gas thermal conductivity of the mainstream gas to the actual thermal conductivity of the turbine cascade material; The simulation analysis module is used to select the simulated cascade material under the low-temperature modular working condition according to the thermal conductivity of the simulated cascade material to prepare the corresponding simulated cascade, and carry out the comprehensive cold efficiency simulation analysis of the stationary turbine cascade by using the three-dimensional finite element model of the simulated cascade under the conditions of the designed test mainstream temperature, the analyzed test mainstream pressure, test cold air temperature, and test cold air flow rate.

7. The static turbine cascade high-temperature cold efficiency experiment boundary condition modeling system according to claim 6, characterized in that, In the mainstream parameter analysis module, according to the test mainstream pressure of the simulated cascade under the low-temperature modularization working condition is obtained through analysis ; where is the designed test mainstream temperature under the low-temperature modularization working condition, is the dynamic viscosity of the test mainstream, is the adiabatic index of the test mainstream, is the scaling ratio of the simulated cascade relative to the turbine cascade, is the mainstream gas pressure under the real working condition, is the mainstream gas temperature under the real working condition, is the dynamic viscosity of the mainstream gas, is the adiabatic index of the mainstream gas.

8. The static turbine cascade high-temperature cold efficiency experiment boundary condition modeling system according to claim 6, characterized in that In the cold air temperature analysis module, the test cold air dynamic viscosity under the low-temperature modularization working condition , where is the test mainstream dynamic viscosity under the low-temperature modularization working condition, is the mainstream gas dynamic viscosity under the actual working condition, is the actual cold air dynamic viscosity under the actual working condition; then use to analyze and obtain the test cold air temperature under the low-temperature modularization working condition , where = 1.7894×10 -5 Pa•s, is a constant related to the gas type, and the value of air is 110.4 K.

9. The static turbine cascade high-temperature cold efficiency experiment boundary condition modeling system according to claim 6, characterized in that, In the simulated cascade parameter determination module, according to the thermal conductivity of the simulated cascade material obtained through analysis , where is the thermal conductivity of the mainstream gas under actual working conditions, is the actual thermal conductivity of the turbine cascade material, is the thermal conductivity of the test mainstream under low-temperature modeling working conditions.

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