A cooling structure comprehensive cooling effect modeling matching method, system, device and medium

Abstract

The invention discloses a cooling structure comprehensive cooling effect modeling matching method, system, equipment and medium, belonging to the field of aeroengine technology, by simulating the comprehensive cooling effect of the hot end parts of the cooling structure under the influence of radiation, obtaining the comprehensive cooling effect expression and decomposing it, obtaining the adiabatic cooling efficiency and the radiation equivalent heat transfer coefficient ratio, using the Boltzmann number and the Bouguer number to match the radiation term together, obtaining the adiabatic cooling efficiency and the comprehensive cooling effect expression of the matched cooling structure, and obtaining the pressure and radiation equivalent optical thickness of the model; defining the model size ratio under two different working conditions and adjusting the size, matching the Boltzmann number of the cooling structure by changing the radiation equivalent optical thickness under the two different working conditions; matching the Bouguer number of the cooling structure by adjusting the pressure data of the model under the two different working conditions. The method can deeply reflect the heat transfer mechanism under the real radiation convection coupling and improve the matching accuracy.

Description

Technical Field

[0001] The present invention relates to the technical field of aeroengines, and more specifically to a method, system, equipment and medium for modeling and matching the comprehensive cooling effect of a cooling structure under radiation-convection coupling of an aeroengine. Background Art

[0002] For a long period of time in the development of aero-engine technology, since the temperature of the hot end components of the engine was not enough to cause a large radiation effect, people paid more attention to heat conduction-convection heat transfer in the research of thermal protection of high-temperature components. Due to the continuous development of aero-engine technology in recent years, the thrust of aero-engines has also been required to be continuously improved. The increase in thrust will inevitably require the temperature of the combustion chamber to continue to rise, which will bring about the continuous increase in the turbine inlet temperature. From the development of engine technology, the turbine inlet temperature of the next generation of new engines will even reach 2200K-2400K, while the thermal tolerance of the common nickel-based turbine blades is between 1500K-1600K, making the thermal protection of turbine blades more difficult. In order to meet the increasing performance requirements, various cooling structures are used in turbine blades to ensure the life and reliability of hot end components. Internal cooling and film cooling are currently the most commonly used important cooling methods, and the comprehensive cooling efficiency is usually used to evaluate its cooling performance. It comprehensively considers external cooling, internal cooling, radiation heat transfer and solid thermal conductivity factors, and can comprehensively characterize the cooling effect of the cooling structure on the turbine blades.

[0003] According to existing research, if only the conduction-convection coupled heat transfer is considered, the numerical simulation calculation results often deviate greatly from the experiment, and effective thermal protection for turbine blades cannot be achieved. When the gas temperature in the turbine stage is about 2000K, the radiation heat flux of the combustion products to the blades can reach more than 10% of the convective heat flux. In recent years, although many scholars in my country have continuously studied thermal radiation and made good progress, overall, domestic radiation heat transfer research still lags behind convective heat transfer and conduction-convection heat transfer research. This type of simulation research is currently one of the few studies that has the nature of guiding heat transfer and cooling design, but in these studies, scholars usually ignore the radiation effect.

[0004] At present, scholars calculate the wall temperature of hot end components under real high-temperature working conditions from two parts. One is based on the simulation calculation results under typical heat conduction and convection coupling, and the other is to consider the radiation factor separately. If you want to calculate the wall temperature of a high-temperature component, you must rely on the wall temperature calculation results under typical heat conduction and convection, and the wall temperature calculation results under the radiation factor alone. Add the two calculation results.

[0005] In summary, in the theoretical research on comprehensive cooling effect modeling in the existing technology, the radiation factor is mainly considered and calculated separately, and then converted into an equivalent wall temperature and added to the former, which results in a large error in the calculation result and cannot fully reflect the actual heat transfer mechanism under the coupling of radiation and convection, affecting the matching accuracy. Summary of the invention

[0006] In response to the problems existing in the above-mentioned fields, the present invention proposes a method, system, equipment and medium for comprehensive cooling effect modeling matching of cooling structures, which can solve the technical problem that in the theoretical research on comprehensive cooling effect modeling in the prior art, the radiation factor is mainly considered and calculated separately, and the equivalent wall temperature is converted and added to the former, resulting in a large error in the calculation result, which cannot fully reflect the real heat transfer mechanism under the coupling of radiation and convection, and affects the matching accuracy.

[0007] In order to solve the above technical problems, the present invention discloses a cooling structure comprehensive cooling effect modeling matching method, comprising the following steps:

[0008] According to the cooling process of the hot end components of the cooling structure under the influence of radiation, the comprehensive cooling effect expression is obtained;

[0009] The comprehensive cooling efficiency expression is decomposed to obtain the adiabatic cooling efficiency and the radiation equivalent heat transfer coefficient ratio;

[0010] According to the adiabatic cooling efficiency and the radiation equivalent heat transfer coefficient ratio, the Boltzmann number and the Bouguer number are used to match the radiation term, and the radiation equivalent heat transfer coefficient ratio is transformed to obtain the adiabatic cooling efficiency and comprehensive cooling efficiency expression of the matched cooling structure.

[0011] According to the adiabatic cooling efficiency and comprehensive cooling effect expression of the matched cooling structure, the pressure and radiation equivalent optical thickness of the model are obtained; the model size ratio under two different working conditions is defined and the size is adjusted, and the Boltzmann number of the cooling structure is matched by changing the radiation equivalent optical thickness under two different working conditions; the Bouguer number of the cooling structure is matched by adjusting the pressure data of the model under two different working conditions.

[0012] Preferably, obtaining the comprehensive cooling effect expression comprises the following steps:

[0013] Assuming that the wall of the cooling structure is one-dimensional heat conduction and has no internal heat source, its heat conduction control equation is:

[0014]

[0015] The boundary conditions of the cooling structure on the cold air side and the gas side are:

[0016]

[0017]

[0018] The comprehensive cooling effect expression is:

[0019]

[0020] in, represents the solid thermal conductivity of the cooling structure, δ represents the wall thickness of the cooling structure, and represent the wall convection heat transfer coefficients on the cold air side and the gas side of the cooling structure, respectively. The equivalent convection heat transfer coefficient representing the radiation heat transfer of the cooling structure, Indicates the temperature of the cooling air at the entrance of the air film hole of the cooling structure, represents the mainstream gas temperature of the cooling structure, T w represents the wall temperature of the cooling structure, represents the adiabatic wall temperature of the cooling structure, represents the temperature of the cooling structure at the cold air side boundary condition, Represents the temperature of the cooling structure at the gas side boundary condition;

[0021] After dimensionless processing, the one-dimensional comprehensive cooling effect expression is obtained:

[0022]

[0023] in, is the temperature rise coefficient of the secondary flow from inlet to outlet, is the adiabatic cooling efficiency, is the mainstream side Biot number of the cooling structure.

[0024] Preferably, the decomposing the comprehensive cooling efficiency expression comprises the following steps:

[0025] The obtained one-dimensional comprehensive cooling effect expression is decomposed into the temperature rise coefficient of the secondary flow from the inlet to the outlet , Adiabatic Cooling Efficiency , mainstream side Biot number , heat transfer coefficient ratio between mainstream side and cold air side , radiation equivalent heat transfer coefficient ratio ,in:

[0026]

[0027]

[0028]

[0029] in, Indicates the temperature of the cold air at the outlet of the air film hole. Indicates the thickness of the air film plate, k Represents the thermal conductivity of the air film plate.

[0030] Preferably, obtaining the adiabatic cooling efficiency and comprehensive cooling efficiency expression of the matched cooling structure comprises the following steps:

[0031] Use Boltzmann number and Bouguer number to match the radiation equivalent heat transfer coefficient ratio in the radiation term ,in:

[0032] The Boltzmann number represents the intensity of gas radiation, the Bouguer number represents the characteristics of gas radiation, and the Boltzmann number represents the intensity of gas radiation. and Bouguer number The expression is as follows:

[0033]

[0034]

[0035] The numerator and denominator of the Boltzmann number are multiplied by the mainstream gas temperature T After that, the expression characterizes the ratio of radiation heat flux to convection heat flux, and we get:

[0036]

[0037] According to the convection heat transfer coefficient:

[0038]

[0039] Radiation equivalent heat transfer coefficient:

[0040]

[0041] The expressions of adiabatic cooling efficiency and comprehensive cooling efficiency are as follows:

[0042] ,

[0043] in, Bo 1 represents the actual high temperature working condition Boltzmann number, Bo 2 represents the Boltzmann number under laboratory low temperature conditions, q h represents the convective heat transfer, q r represents the radiation heat transfer, is the mainstream gas temperature of the cooling structure, is the coupled wall temperature, is the adiabatic wall temperature, is the secondary flow temperature.

[0044] Preferably, obtaining the pressure and radiation equivalent optical thickness of the model comprises the following steps:

[0045] According to the convective heat transfer coefficient, radiation equivalent heat transfer coefficient ratio, adiabatic cooling efficiency and comprehensive cooling efficiency expression, we get:

[0046]

[0047] Combining the ratio of radiation heat flux density to convection heat flux density, when the Boltzmann number has matched, we have:

[0048]

[0049] Adiabatic Cooling Efficiency It is matched according to the mainstream Reynolds number and momentum ratio, that is, , obtained through the Boltzmann number B o The Boltzmann number and the Bouguer number obtained match the radiation term together. is reliable;

[0050] The ratio of the radiation equivalent heat transfer coefficient in the radiation term is matched by the Boltzmann number and the Bouguer number. The matching principle is:

[0051]

[0052]

[0053] in, is the pressure absorption coefficient, is the channel pressure, is the radiation equivalent optical thickness;

[0054] When the mainstream Reynolds number matches = When , the matching of the Boltzmann number is transformed into:

[0055]

[0056] in, and They represent the dynamic viscosity and specific heat capacity of high temperature fuel gas respectively. and Specifically indicates the dynamic viscosity and specific heat capacity of the fuel gas at constant pressure under low temperature conditions.

[0057] Preferably, the decomposition of the comprehensive cooling efficiency expression also includes the temperature rise coefficient of the secondary flow from the inlet to the outlet, the ratio of the inner and outer heat transfer coefficients and the mainstream side Biot number, and also includes matching the temperature rise coefficient of the secondary flow from the inlet to the outlet, the ratio of the inner and outer heat transfer coefficients and the mainstream side Biot number, including the following steps:

[0058] Match the adiabatic cooling efficiency of the models under different working conditions;

[0059] When the adiabatic cooling efficiency meets the requirements, the momentum ratio is used to match the ratio of the inside and outside heat transfer coefficients, and the ratio of the thermal conductivity of the fluid and the solid is used to match the Biot number on the mainstream side.

[0060] When the inner and outer heat transfer coefficients and the mainstream side Biot number meet the conditions, the radiation equivalent heat transfer coefficient ratio is matched.

[0061] Preferably, matching the Bouguer number of the cooling structure comprises the following steps:

[0062] Define the model size ratio as:

[0063]

[0064]

[0065] in, is the model size ratio under two different working conditions, L 1 and L 2 is the model under two different working conditions; is the radiation equivalent optical thickness, V is the volume of the gas bag wall, A is the surface area of ​​the gas envelope wall, 0.9 and 4 are reference coefficients;

[0066] By adjusting the model size ratio , changing the radiation equivalent optical thickness under the two working conditions , to match the Boltzmann number; and by varying the pressure, to match the Bouguer number.

[0067] Preferably, it also includes a cooling structure comprehensive cooling effect modeling matching system, including:

[0068] A comprehensive cooling efficiency acquisition module is used to obtain a comprehensive cooling efficiency expression according to the cooling process of the hot end components of the cooling structure under the influence of radiation;

[0069] Comprehensive cooling efficiency decomposition module, used to decompose the comprehensive cooling efficiency expression to obtain adiabatic cooling efficiency and radiation equivalent heat transfer coefficient ratio;

[0070] The model matching module is used to match the radiation term by using the Boltzmann number and the Bouguer number according to the adiabatic cooling efficiency and the radiation equivalent heat transfer coefficient ratio, transform the radiation equivalent heat transfer coefficient ratio, and obtain the adiabatic cooling efficiency and comprehensive cooling efficiency expression of the matched cooling structure; obtain the pressure and radiation equivalent optical thickness of the model according to the adiabatic cooling efficiency and comprehensive cooling efficiency expression of the matched cooling structure; define the model size ratio under two different working conditions and adjust the size, and match the Boltzmann number of the cooling structure by changing the radiation equivalent optical thickness under two different working conditions; match the Bouguer number of the cooling structure by adjusting the pressure data of the model under two different working conditions.

[0071] Preferably, a computer device is also included, the computer device comprising a memory and a processor, the memory storing a computer program, and when the computer program is executed by the processor, the processor executes the following steps:

[0072] According to the cooling process of the hot end components of the cooling structure under the influence of radiation, the comprehensive cooling effect expression is obtained;

[0073] The comprehensive cooling efficiency expression is decomposed to obtain the adiabatic cooling efficiency and the radiation equivalent heat transfer coefficient ratio;

[0074] According to the adiabatic cooling efficiency and the radiation equivalent heat transfer coefficient ratio, the Boltzmann number and the Bouguer number are used to match the radiation term, and the radiation equivalent heat transfer coefficient ratio is transformed to obtain the adiabatic cooling efficiency and comprehensive cooling efficiency expression of the matched cooling structure.

[0075] According to the adiabatic cooling efficiency and comprehensive cooling effect expression of the matched cooling structure, the pressure and radiation equivalent optical thickness of the model are obtained; the model size ratio under two different working conditions is defined and the size is adjusted, and the Boltzmann number of the cooling structure is matched by changing the radiation equivalent optical thickness under two different working conditions; the Bouguer number of the cooling structure is matched by adjusting the pressure data of the model under two different working conditions.

[0076] Preferably, it further comprises a computer-readable storage medium, wherein the computer-readable storage medium stores a computer program, and when the computer program is executed by a processor, the processor executes the following steps:

[0077] According to the cooling process of the hot end components of the cooling structure under the influence of radiation, the comprehensive cooling effect expression is obtained;

[0078] The comprehensive cooling efficiency expression is decomposed to obtain the adiabatic cooling efficiency and the radiation equivalent heat transfer coefficient ratio;

[0079] According to the adiabatic cooling efficiency and the radiation equivalent heat transfer coefficient ratio, the Boltzmann number and the Bouguer number are used to match the radiation term, and the radiation equivalent heat transfer coefficient ratio is transformed to obtain the adiabatic cooling efficiency and comprehensive cooling efficiency expression of the matched cooling structure.

[0080] According to the adiabatic cooling efficiency and comprehensive cooling effect expression of the matched cooling structure, the pressure and radiation equivalent optical thickness of the model are obtained; the model size ratio under two different working conditions is defined and the size is adjusted, and the Boltzmann number of the cooling structure is matched by changing the radiation equivalent optical thickness under two different working conditions; the Bouguer number of the cooling structure is matched by adjusting the pressure data of the model under two different working conditions.

[0081] Compared with the prior art, the present invention has the following beneficial effects:

[0082] The cooling structure comprehensive cooling effect modeling matching method proposed in the present invention can overcome the technical defects in the prior art that the radiation factor is mainly considered separately for calculation, converted into equivalent wall temperature and added to the former, resulting in large errors in the calculation results, which cannot fully reflect the heat transfer mechanism under the real radiation convection coupling and affect the matching accuracy. The method analyzes the heat exchange of the entire cooling structure from a theoretical level by setting boundary conditions, and provides basic theoretical support for the one-dimensional expression of comprehensive cooling effect. The comprehensive cooling effect expression is decomposed to obtain the adiabatic cooling efficiency and the radiation equivalent heat transfer coefficient ratio. The radiation equivalent heat transfer coefficient ratio is a specific embodiment of the radiation participation in the entire heat exchange process, which is more in line with the actual situation with radiation participation. The radiation terms are matched with the Boltzmann number and the Bouguer number. When the matching of each item of the comprehensive cooling effect expression is met, it can be considered that the wall temperature prediction capability of the corresponding high temperature working condition is obtained. By adjusting the radiation equivalent optical thickness, the Boltzmann number is matched, so that the radiation intensity characteristics between the high and low working conditions are relatively consistent; by adjusting the pressure spectrum absorption coefficient, it is matched with the Bouguer number of the high temperature working condition. This method can deeply reflect the heat transfer mechanism under the real radiation-convection coupling and improve the matching accuracy. BRIEF DESCRIPTION OF THE DRAWINGS

[0083] Figure 1 It is a schematic diagram of the overall method flow of the present invention;

[0084] Figure 2 For the traditional model heat exchange process;

[0085] Figure 3 The impact divergence boundary condition provided in the first embodiment of the present invention;

[0086] Figure 4 The size of the impact divergence structure provided in the first embodiment of the present invention;

[0087] Figure 5Comparison of comprehensive cooling effect cloud diagrams of impact-radiating flat plates under high and medium temperature conditions provided in Example 1 of the present invention;

[0088] Figure 6 The comprehensive cooling effect matching error of case A and case C including the radiation-free control group provided in the first embodiment of the present invention;

[0089] Figure 7 The turbine blade calculation model and boundary conditions provided in the second embodiment of the present invention;

[0090] Figure 8 A schematic diagram of the relative positions of the guide vane model and the air film holes provided in the second embodiment of the present invention;

[0091] Fig. 9 A distribution cloud diagram of the comprehensive cooling efficiency matching results of high and low temperature working conditions with a momentum ratio I=1 provided in the second embodiment of the present invention;

[0092] Fig.10 The spanwise average of the comprehensive cooling efficiency matching of high and low temperature working conditions with momentum ratio I=1 provided in the second embodiment of the present invention;

[0093] In the figure: T g represents the mainstream inlet temperature; represents the mainstream import density; represents the mainstream thermal conductivity; Indicates the mainstream import speed; T c,e Indicates the cold flow outlet temperature; represents the cold flow outlet density; represents the cold flow outlet velocity; T w represents the wall temperature; q r represents the radiative heat flow; It represents the convection heat transfer coefficient on the gas side; δ Indicates the wall thickness; represents the thermal conductivity of solid; represents the convective heat transfer coefficient on the cold air side; T c,i Indicates the cold flow inlet temperature; represents the cold flow inlet density; represents the cold flow thermal conductivity; Represents the cold flow inlet velocity. DETAILED DESCRIPTION

[0094] The following will be combined with the attached embodiment of the present invention Figure 1-10 , the technical solutions in the embodiments of the present invention are clearly and completely described. It should be understood that the terms described in the present invention are only used to describe specific implementation methods and are not used to limit the present invention.

[0095] like Figure 1 As shown, the present invention proposes a cooling structure comprehensive cooling effect modeling matching method, comprising the following steps:

[0096] S1: Figure 2 As shown, the wall, cold air side and gas side boundary conditions of the cooling structure are set, the comprehensive cooling effect of the hot end components of the cooling structure under the influence of radiation is simulated, the comprehensive cooling efficiency expression is obtained, the heat transfer of the entire cooling structure is analyzed from a theoretical level, and the basic theoretical support is provided for the one-dimensional expression of the comprehensive cooling efficiency.

[0097] S2: Decompose the comprehensive cooling efficiency expression to obtain the temperature rise coefficient of the secondary flow from the inlet to the outlet, the ratio of the inside and outside heat transfer coefficients, the mainstream side Biot number, the adiabatic cooling efficiency and the radiation equivalent heat transfer coefficient ratio. The radiation equivalent heat transfer coefficient ratio is a specific manifestation of the participation of radiation in the entire heat exchange process. In other words, the comprehensive cooling efficiency expression is more in line with the actual situation with radiation participation.

[0098] S3: According to the adiabatic cooling efficiency and the radiation equivalent heat transfer coefficient ratio, the Boltzmann number and the Bouguer number are used to match the radiation term, and the radiation equivalent heat transfer coefficient ratio is transformed to obtain the adiabatic cooling efficiency and comprehensive cooling efficiency expression of the matched cooling structure. When the matching of each item of the comprehensive cooling efficiency expression is met, it can be considered that the corresponding high-temperature working condition wall temperature prediction capability is possessed.

[0099] S4: According to the adiabatic cooling efficiency and comprehensive cooling efficiency expression of the matched cooling structure, the pressure and radiation equivalent optical thickness of the model are obtained; the model size under two different working conditions is set and the model size ratio is defined; by adjusting the model size ratio under two different working conditions, the radiation equivalent optical thickness under two different working conditions is changed, and the Boltzmann number of the cooling structure is matched; and by adjusting the pressure data of the model under two different working conditions, the Bouguer number of the cooling structure is matched.

[0100] The radiation equivalent optical thickness is adjusted to match the Boltzmann number so that the radiation intensity characteristics between high and low working conditions are relatively consistent; in matching pressure data, the pressure spectrum absorption coefficient is adjusted to match it with the Bouguer number of high temperature conditions.

[0101] In step S1, a comprehensive cooling efficiency expression is obtained, including the following steps:

[0102] Assuming that the wall of the cooling structure is one-dimensional heat conduction and has no internal heat source, its heat conduction control equation is:

[0103]

[0104] The boundary conditions of the cooling structure on the cold air side and the gas side are:

[0105]

[0106]

[0107] The comprehensive cooling effect expression is:

[0108]

[0109] in, represents the solid thermal conductivity of the cooling structure, δ represents the wall thickness of the cooling structure, and represent the wall convection heat transfer coefficients on the cold air side and the gas side of the cooling structure, respectively. The equivalent convection heat transfer coefficient representing the radiation heat transfer of the cooling structure, Indicates the temperature of the cooling air at the entrance of the air film hole of the cooling structure, represents the mainstream gas temperature of the cooling structure, T w represents the wall temperature of the cooling structure, represents the adiabatic wall temperature of the cooling structure, represents the temperature of the cooling structure at the cold air side boundary condition, Represents the temperature of the cooling structure at the gas side boundary condition.

[0110] After dimensionless processing, the one-dimensional comprehensive cooling effect expression is obtained:

[0111]

[0112] in, is the temperature rise coefficient of the secondary flow from inlet to outlet, is the adiabatic cooling efficiency, is the mainstream side Biot number of the cooling structure.

[0113] In step S2, the comprehensive cooling efficiency expression is decomposed, including the following steps:

[0114] The obtained one-dimensional comprehensive cooling effect expression is decomposed into the temperature rise coefficient of the secondary flow from the inlet to the outlet , Adiabatic Cooling Efficiency , mainstream side Biot number , heat transfer coefficient ratio between mainstream side and cold air side , radiation equivalent heat transfer coefficient ratio ,in:

[0115]

[0116]

[0117]

[0118] in, Indicates the temperature of the cold air at the outlet of the air film hole. Indicates the thickness of the air film plate, k Represents the thermal conductivity of the air film plate.

[0119] Obtaining the adiabatic cooling efficiency and comprehensive cooling efficiency expression of the matched cooling structure includes the following steps:

[0120] Use Boltzmann number and Bouguer number to match the radiation equivalent heat transfer coefficient ratio in the radiation term ,in:

[0121] The Boltzmann number characterizes the gas radiation intensity, and the Bouguer number characterizes the gas radiation characteristics. The expressions of the Boltzmann number and the Bouguer number are as follows:

[0122]

[0123]

[0124] The numerator and denominator of the Boltzmann number are multiplied by the mainstream gas temperature T After that, the expression characterizes the ratio of radiation heat flux to convection heat flux, and we get:

[0125]

[0126] According to the convection heat transfer coefficient:

[0127]

[0128] Radiation equivalent heat transfer coefficient:

[0129]

[0130] The expressions of adiabatic cooling efficiency and comprehensive cooling efficiency are as follows:

[0131] ,

[0132] in, Bo 1 represents the actual high temperature working condition Boltzmann number, Bo 2 represents the Boltzmann number under laboratory low temperature conditions, q h represents the convective heat transfer, q r represents the radiation heat transfer, is the mainstream gas temperature of the cooling structure, is the coupled wall temperature, is the adiabatic wall temperature, is the secondary flow temperature.

[0133] Obtaining the pressure and radiation equivalent optical thickness of the model includes the following steps:

[0134] According to the convective heat transfer coefficient, radiation equivalent heat transfer coefficient ratio, adiabatic cooling efficiency and comprehensive cooling efficiency expression, we get:

[0135]

[0136] Combining the ratio of radiation heat flux density to convection heat flux density, when the Boltzmann number has matched, we have:

[0137]

[0138] Adiabatic Cooling Efficiency It is matched according to the mainstream Reynolds number and momentum ratio, that is, , obtained through the Boltzmann number B o The obtained Boltzmann number and Bouguer number match the radiation equivalent heat transfer coefficient ratio in the radiation term. is reliable;

[0139] The ratio of the radiation equivalent heat transfer coefficient in the radiation term is matched by the Boltzmann number and the Bouguer number. The matching principle is:

[0140]

[0141]

[0142] in, is the pressure absorption coefficient, is the channel pressure, is the radiation equivalent optical thickness.

[0143] When the mainstream Reynolds number matches = When , the matching of the Boltzmann number is transformed into:

[0144]

[0145] in, and They represent the dynamic viscosity and specific heat capacity of high temperature fuel gas respectively. and Specifically indicates the dynamic viscosity and specific heat capacity of the fuel gas at constant pressure under low temperature conditions.

[0146] In step S2, the comprehensive cooling efficiency expression is decomposed to include the temperature rise coefficient of the secondary flow from the inlet to the outlet, the ratio of the inside and outside heat transfer coefficients, and the Biot number on the mainstream side.

[0147] Specifically, matching the temperature rise coefficient of the secondary flow from the inlet to the outlet, the ratio of the inside and outside heat transfer coefficients, and the Biot number on the main flow side includes the following steps:

[0148] Match the adiabatic cooling efficiency of the models under different working conditions;

[0149] When the adiabatic cooling efficiency meets the requirements, the momentum ratio is used to match the ratio of the inside and outside heat transfer coefficients, and the ratio of the thermal conductivity of the fluid and the solid is used to match the Biot number on the mainstream side.

[0150] When the inner and outer heat transfer coefficients and the mainstream side Biot number meet the conditions, the radiation equivalent heat transfer coefficient ratio is matched.

[0151] In step S3, the Bouguer number of the cooling structure is matched, including the following steps:

[0152] Define the model size ratio as:

[0153]

[0154]

[0155] in, is the model size ratio under two different working conditions, L 1 and L 2 is the model under two different working conditions; is the radiation equivalent optical thickness, V is the volume of the gas bag wall, A is the surface area of ​​the gas envelope wall, and 0.9 and 4 are reference coefficients.

[0156] By adjusting the model size ratio , changing the radiation equivalent optical thickness under the two working conditions , to match the Boltzmann number; and by varying the pressure, to match the Bouguer number.

[0157] The present invention also proposes a cooling structure comprehensive cooling effect modeling matching system, comprising:

[0158] A comprehensive cooling efficiency acquisition module is used to obtain a comprehensive cooling efficiency expression according to the cooling process of the hot end components of the cooling structure under the influence of radiation;

[0159] Comprehensive cooling efficiency decomposition module, used to decompose the comprehensive cooling efficiency expression to obtain adiabatic cooling efficiency and radiation equivalent heat transfer coefficient ratio;

[0160] The model matching module is used to match the radiation term by using the Boltzmann number and the Bouguer number according to the adiabatic cooling efficiency and the radiation equivalent heat transfer coefficient ratio, transform the radiation equivalent heat transfer coefficient ratio, and obtain the adiabatic cooling efficiency and comprehensive cooling efficiency expression of the matched cooling structure; obtain the pressure and radiation equivalent optical thickness of the model according to the adiabatic cooling efficiency and comprehensive cooling efficiency expression of the matched cooling structure; define the model size ratio under two different working conditions and adjust the size, and match the Boltzmann number of the cooling structure by changing the radiation equivalent optical thickness under two different working conditions; match the Bouguer number of the cooling structure by adjusting the pressure data of the model under two different working conditions.

[0161] The present invention further provides a computer device, the computer device comprising a memory and a processor, the memory storing a computer program, and when the computer program is executed by the processor, the processor executes the following steps:

[0162] According to the cooling process of the hot end components of the cooling structure under the influence of radiation, the comprehensive cooling effect expression is obtained;

[0163] The comprehensive cooling efficiency expression is decomposed to obtain the adiabatic cooling efficiency and the radiation equivalent heat transfer coefficient ratio;

[0164] According to the adiabatic cooling efficiency and the radiation equivalent heat transfer coefficient ratio, the Boltzmann number and the Bouguer number are used to match the radiation term, and the radiation equivalent heat transfer coefficient ratio is transformed to obtain the adiabatic cooling efficiency and comprehensive cooling efficiency expression of the matched cooling structure.

[0165] According to the adiabatic cooling efficiency and comprehensive cooling effect expression of the matched cooling structure, the pressure and radiation equivalent optical thickness of the model are obtained; the model size ratio under two different working conditions is defined and the size is adjusted, and the Boltzmann number of the cooling structure is matched by changing the radiation equivalent optical thickness under two different working conditions; the Bouguer number of the cooling structure is matched by adjusting the pressure data of the model under two different working conditions.

[0166] The present invention further provides a computer-readable storage medium, wherein the computer-readable storage medium stores a computer program. When the computer program is executed by a processor, the processor executes the following steps:

[0167] According to the cooling process of the hot end components of the cooling structure under the influence of radiation, the comprehensive cooling effect expression is obtained;

[0168] The comprehensive cooling efficiency expression is decomposed to obtain the adiabatic cooling efficiency and the radiation equivalent heat transfer coefficient ratio;

[0169] According to the adiabatic cooling efficiency and the radiation equivalent heat transfer coefficient ratio, the Boltzmann number and the Bouguer number are used to match the radiation term, and the radiation equivalent heat transfer coefficient ratio is transformed to obtain the adiabatic cooling efficiency and comprehensive cooling efficiency expression of the matched cooling structure.

[0170] According to the adiabatic cooling efficiency and comprehensive cooling effect expression of the matched cooling structure, the pressure and radiation equivalent optical thickness of the model are obtained; the model size ratio under two different working conditions is defined and the size is adjusted, and the Boltzmann number of the cooling structure is matched by changing the radiation equivalent optical thickness under two different working conditions; the Bouguer number of the cooling structure is matched by adjusting the pressure data of the model under two different working conditions.

[0171] By setting the boundary conditions of the wall, cold air side and gas side of the cooling structure, this method can analyze the heat transfer of the entire cooling structure from a theoretical level, and provide basic theoretical support for the one-dimensional expression of the comprehensive cooling efficiency. The comprehensive cooling efficiency expression is decomposed to obtain the adiabatic cooling efficiency and the radiation equivalent heat transfer coefficient ratio. The radiation equivalent heat transfer coefficient ratio is a specific manifestation of the participation of radiation in the entire heat exchange process, which is more in line with the actual situation with radiation participation. The Boltzmann number and the Bouguer number are used to match the radiation terms. When the matching of each item in the comprehensive cooling efficiency expression is met, it can be considered that it has the corresponding high-temperature working condition wall temperature prediction capability. By adjusting the radiation equivalent optical thickness, the Boltzmann number is matched, so that the radiation intensity characteristics between the high and low working conditions are relatively consistent; by adjusting the pressure spectrum absorption coefficient in the pressure data, it is matched with the Bouguer number of the high temperature working condition. This method can deeply reflect the heat transfer mechanism under the real radiation-convection coupling and improve the matching accuracy.

[0172] Embodiment 1

[0173] like Figure 3 As shown, the first embodiment of the present invention uses the impact divergence cooling structure as a common cooling structure in high-temperature components of aircraft engines, and conducts numerical simulation research based on the structure.

[0174] The boundary conditions are set as follows: Figure 3 As shown, the upper end surface of the model is set as a symmetrical surface, and the left and right sides are set as periodic surfaces. For the mainstream fluid, the inlet boundary uses a mass flow inlet and a uniform total temperature inlet, and the outlet boundary uses a pressure outlet; for the cold air fluid, a uniform total temperature and mass flow inlet is used. Previous studies have shown that the SST model is more suitable for complex flows. Therefore, the turbulence model of the present invention selects The model is numerically simulated; boundary layers are set at the coupling surface and the wall of the air film hole to ensure that the boundary layer grid The value meets the requirements of the turbulence model; the discrete method uses the COUPLE algorithm, and the structural size of the model is as follows Figure 4 shown.

[0175] The numerical simulation domain used includes the fluid domain and the solid domain. The solid domain material in the model is uniformly set to nickel, and the fluid domain medium is a high-temperature mixed ideal gas and a low-temperature cooling ideal gas, and their thermal conductivity varies with temperature. At the same time, the high-temperature fuel gas and cooling gas are in a high-pressure and high-speed environment, and the compressibility effect of the gas needs to be considered. Its viscosity is determined using the Sutherland formula.

[0176] In order to study the radiation effect of radiation, two groups of typical gas components were used in the calculation.

[0177] The engine oil-to-gas ratio will change accordingly during the process from takeoff to cruising and landing. When it is in a high thrust state, the aircraft engine speed increases rapidly and the oil-to-gas ratio increases dramatically. The gas state at this time is taken as one group; when the aircraft is in a cruising state, its oil-to-gas ratio is in the most economical state. The gas state at this time is taken as another group.

[0178] The gas state is different, and the gas components and The content of the gas is different, and its gas state component coefficient is listed in Table 1. The number H in Table 1 indicates the value of the gas. and The content is relatively large; the code is L, indicating and The content is low. The convective heat transfer and radiation heat transfer characteristics are different for different gas components.

[0179] Table 1 Gas composition coefficient table

[0180]

[0181] According to traditional research, when the temperature ratio of high and low temperature conditions matches, the adiabatic cooling efficiency, the ratio of the inside and outside heat transfer coefficients, etc. are easier to match.

[0182] In order to fully verify the effectiveness of the matching method proposed in the present invention, the several groups of verification conditions used in the present invention are all established under conditions with different temperature ratios. As shown in Table 2, the detailed operating parameters of two groups of cases are shown, where case A is used to represent the actual engine operating condition; case C is a medium-temperature laboratory operating condition with a mainstream temperature of 850K; and all operating conditions are set with non-radiation control groups case A-norad and case C-norad.

[0183] Table 2. Table of matching verification conditions between numerical simulation laboratory conditions and actual engine conditions

[0184]

[0185] like Figure 5As shown in the figure, the comprehensive cooling effect cloud diagram of high temperature and medium temperature conditions without radiation conditions is shown. Figure 5 (a) and Figure 5 (b) When there is no radiation involved, the matching result between the two is better, which also proves the reliability of the simulation research of previous scholars. Figure 5 (c) and Figure 5 (d) When radiation is involved, the results presented by the two are almost the same, and it is difficult to see where the error lies. Figure 5 The cloud map results with / without radiation participation are shown in the figure, and the span-wise average comprehensive cooling effect line diagram is made, such as Figure 6 shown.

[0186] from Figure 6 From the line graph in , the matching results between the high temperature condition and the medium temperature condition under radiation-convection coupling are good, and the error is close to the error between the high and low conditions in the non-radiation control group.

[0187] Embodiment 2

[0188] like Figure 7 The calculation domain model and boundary conditions are shown in Figure 1. The model is taken from a cascade segment in the full-cycle model, with a cascade channel height of 28 mm and a blade pitch of 25 mm, where:

[0189] The main inlet and secondary inlet are both mass flow inlets, and the outlet is a pressure outlet. The end wall and the bottom of the impact duct use adiabatic wall surfaces, and periodic boundary conditions are used on both sides of the blade fluid channel. The translation period is extended along the y direction to both sides to reduce the amount of numerical simulation calculations. The solid outer side of the blade is in contact with the high-temperature gas, and the outer surface in contact with the high-temperature gas is set as a coupled heat exchange boundary to ensure the rationality and continuity of the heat flux density and temperature calculations.

[0190] like Figure 8 As shown, the geometric model of the turbine guide vane of the present invention is a simplified turbine guide vane of a certain type, the blade chord length C = 33.25 mm, the internal structure is formed by an impact duct and a support column, the impact holes are distributed on the impact duct, the aperture D1 = 0.5 mm, and the aperture of the air film hole on the outer surface is D = 0.4 mm.

[0191] The fluid domain mesh near the guide vane is encrypted and the boundary layer mesh is set. The first layer mesh is ensured by mesh independence check. The value of about 1 meets the requirements of the turbulence model. The DO model is used in the radiation calculation example. When considering the gas radiation, the gas spectrum radiation model needs to be added. This paper uses the WSGG model for calculation.

[0192] In order to explore the comprehensive cooling effect modeling matching method under the turbine blade model, a group of calculation case examples were designed and analyzed and verified from different angles. The specific parameters are shown in Table 3.

[0193] Table 3 Turbine blade laboratory operating conditions and actual engine operating conditions matching table

[0194]

[0195] According to traditional research, the momentum ratio parameter plays an important role in the simulation study without radiation participation. When the temperature ratio does not match, the results can be corrected by matching the momentum ratio. However, the radiation modeling is not taken into account in the traditional research results. Therefore, in order to explore whether the matching momentum ratio parameter under radiation-convection coupling can also correct the results, and to explore the applicability of the comprehensive cooling effect modeling matching method under complex flow factors in the turbine blade structure, this embodiment uses two groups of working conditions, case 1-a and case 2-a, to explore the comprehensive cooling effect modeling matching results.

[0196] like Fig. 9 As shown, they are the cloud diagrams of the combined cooling effect distribution of the suction surface and pressure surface of the blade under high and low temperature conditions (momentum ratio I=1).

[0197] contrast Fig. 9 (a) and Fig. 9 (c) It can be seen that there are differences in the comprehensive cooling effect in the downstream area of ​​the suction surface. Fig. 9 (b) and Fig. 9 As can be seen in (d), the distribution of the comprehensive cooling effect between the second and third rows of holes on the pressure surface is slightly different. Overall, the distribution of the comprehensive cooling effect of case 1-a and case 2-a is very similar, and the matching effect is good. This group of working conditions happens to be working conditions with the same temperature ratio, so the good matching result is not without the positive influence of the temperature ratio matching. The relevant analysis of the temperature ratio will be mentioned below.

[0198] like Fig.10 As shown, the high temperature condition and momentum ratio are shown I =1 The spanwise average diagram of the comprehensive cooling effect of the low-temperature condition. From the line diagram in 10, it can be seen that the distribution patterns of the two conditions on the entire blade surface are similar, and the overall matching error of the suction surface is small, while the area with large errors exists between the second and third rows of holes on the pressure surface. From a numerical point of view, the comprehensive cooling effect results of the low-temperature condition in the area with large errors on the pressure surface are on average about 0.02 higher than those of the high-temperature condition, and the matching results in other areas of the pressure surface are similar.

[0199] By analyzing Example 1 and Example 2, the present invention explores the comprehensive cooling efficiency matching of the fully coupled heat exchange of the cooling structure under high and low working conditions under laboratory conditions. The simulation experimental results show that the method proposed in the present invention can deeply reflect the heat transfer mechanism under the real radiation convection coupling and improve the matching accuracy. The model matching simulation can provide an important reference basis for the thermal protection design of hot end components such as turbine guide vanes to a certain extent.

[0200] The above description is only a preferred specific implementation manner of the present invention, but the protection scope of the present invention is not limited thereto. Any technician familiar with the technical field can make equivalent replacements or changes according to the technical scheme and inventive concept of the present invention within the technical scope disclosed by the present invention, which should be covered by the protection scope of the present invention.

[0201] In addition, unless otherwise specified, all technical and scientific terms used in the present invention have the same meanings as commonly understood by those skilled in the art to which the present invention belongs. All documents mentioned in this specification are incorporated by reference to disclose and describe the methods related to the documents. In the event of any conflict with any incorporated document, the content of this specification shall prevail.

Claims

1. A cooling structure comprehensive cooling effect modeling matching method, characterized in that: The following steps are involved: According to the cooling process of the hot end components of the cooling structure under the influence of radiation, the comprehensive cooling effect expression is obtained; The method of obtaining the comprehensive cooling effect expression comprises the following steps: Assuming that the wall of the cooling structure is one-dimensional heat conduction and has no internal heat source, its heat conduction control equation is: The boundary conditions of the cooling structure on the cold air side and the gas side are: The comprehensive cooling effect expression is: Among them, k s represents the solid thermal conductivity of the cooling structure, δ represents the wall thickness of the cooling structure, and h c and h g are the wall convection heat transfer coefficients on the cold air side and the gas side of the cooling structure, respectively, h r The equivalent convection heat transfer coefficient, T, represents the radiation heat transfer of the cooling structure. c,i represents the temperature of the cooling air at the entrance of the air film hole of the cooling structure, T g represents the mainstream gas temperature of the cooling structure, T w represents the wall temperature of the cooling structure, T aw represents the adiabatic wall temperature of the cooling structure, T z＝0 represents the temperature of the cooling structure at the cold air side boundary condition, T z＝δ Represents the temperature of the cooling structure at the gas side boundary condition; After dimensionless processing, the one-dimensional comprehensive cooling effect expression is obtained: Where χ is the temperature rise coefficient of the secondary flow from the inlet to the outlet, η is the adiabatic cooling efficiency, and Bi is the Biot number on the mainstream side of the cooling structure; The comprehensive cooling efficiency expression is decomposed to obtain the adiabatic cooling efficiency and the radiation equivalent heat transfer coefficient ratio; According to the adiabatic cooling efficiency and the radiation equivalent heat transfer coefficient ratio, the Boltzmann number and the Bouguer number are used to match the radiation term, and the radiation equivalent heat transfer coefficient ratio is transformed to obtain the adiabatic cooling efficiency and comprehensive cooling efficiency expression of the matched cooling structure. According to the adiabatic cooling efficiency and comprehensive cooling efficiency expression of the matched cooling structure, the pressure and radiation equivalent optical thickness of the model are obtained; the model size ratio under two different working conditions is defined and the size is adjusted, and the Boltzmann number of the cooling structure is matched by changing the radiation equivalent optical thickness under two different working conditions; the Bouguer number of the cooling structure is matched by adjusting the pressure data of the model under two different working conditions; The step of decomposing the comprehensive cooling efficiency expression comprises the following steps: The obtained one-dimensional comprehensive cooling efficiency expression is decomposed into the temperature rise coefficient χ of the secondary flow from the inlet to the outlet, the adiabatic cooling efficiency η, the mainstream side Biot number Bi, the ratio of the heat transfer coefficients of the mainstream side and the cold air side Radiation equivalent heat transfer coefficient ratio in: Among them, T c,exit represents the temperature of the cold air at the outlet of the air film hole, δ represents the thickness of the air film plate, and k represents the thermal conductivity of the air film plate; The method of obtaining the adiabatic cooling efficiency and comprehensive cooling efficiency expression of the matched cooling structure comprises the following steps: Use the Boltzmann number and the Bouguer number to match the radiation equivalent heat transfer coefficient ratio h in the radiation term r / h g ,in: The Boltzmann number characterizes the gas radiation intensity, and the Bouguer number characterizes the gas radiation characteristics. The expressions of the Boltzmann number Bo and the Bouguer number Bu are as follows: Bu=α λ,p pL After the numerator and denominator of the Boltzmann number are multiplied by the mainstream gas temperature T, the expression represents the ratio of the radiation heat flux density to the convection heat flux density, and the result is: According to the convection heat transfer coefficient: Radiation equivalent heat transfer coefficient: The expressions of adiabatic cooling efficiency and comprehensive cooling efficiency are as follows: Among them, Bo1 represents the actual high temperature working condition Boltzmann number, Bo2 represents the laboratory low temperature working condition Boltzmann number, q h represents the convective heat transfer, q r represents the radiation heat transfer, T g is the mainstream gas temperature of the cooling structure, T W is the coupled wall temperature, T aw is the adiabatic wall temperature, T c is the secondary flow temperature.

2. The cooling structure comprehensive cooling effect modeling matching method according to claim 1 is characterized in that: The method of obtaining the pressure and radiation equivalent optical thickness of the model comprises the following steps: According to the convective heat transfer coefficient, radiation equivalent heat transfer coefficient ratio, adiabatic cooling efficiency and comprehensive cooling efficiency expression, we get: Combining the ratio of radiation heat flux density to convection heat flux density, when the Boltzmann number has matched, we have: The adiabatic cooling efficiency η is matched according to the mainstream Reynolds number and momentum ratio, that is, η1=η2, and the Boltzmann number B is obtained. o The obtained Boltzmann number and Bouguer number match the radiation equivalent heat transfer coefficient ratio h in the radiation term. r / h g is reliable; The Boltzmann number and the Bouguer number jointly match the radiation equivalent heat transfer coefficient ratio h in the radiation term r / h g The matching principle is: Bu1=a λ,p1 p1L1=a λ,p2 p2L2=Bu2 Among them, α λ,p is the pressure absorption coefficient, p is the channel pressure, and L is the radiation equivalent optical thickness; When the mainstream Reynolds number matches Re1 = Re2, the matching of the Boltzmann number is converted to: Among them, μ1 and C P1 They represent the dynamic viscosity and constant pressure specific heat of high temperature working gas, μ2 and C respectively. P2 Specifically indicates the dynamic viscosity and specific heat capacity of the fuel gas at constant pressure under low temperature conditions.

3. The cooling structure comprehensive cooling effect modeling matching method according to claim 2 is characterized in that: The decomposition of the comprehensive cooling efficiency expression also includes the temperature rise coefficient of the secondary flow from the inlet to the outlet, the ratio of the internal and external heat transfer coefficients and the mainstream side Biot number, and also includes matching the temperature rise coefficient of the secondary flow from the inlet to the outlet, the ratio of the internal and external heat transfer coefficients and the mainstream side Biot number, including the following steps: Match the adiabatic cooling efficiency of the models under different working conditions; When the adiabatic cooling efficiency meets the requirements, the momentum ratio is used to match the ratio of the inside and outside heat transfer coefficients, and the ratio of the thermal conductivity of the fluid and the solid is used to match the Biot number on the mainstream side. When the inner and outer heat transfer coefficients and the mainstream side Biot number meet the conditions, the radiation equivalent heat transfer coefficient ratio is matched.

4. The cooling structure comprehensive cooling effect modeling matching method according to claim 3 is characterized in that: The step of matching the Bouguer number of the cooling structure comprises the following steps: Define the model size ratio as: L=0.9*4*V / A in, is the model size ratio under two different working conditions, L1 and L2 are models under two different working conditions; L is the radiation equivalent optical thickness, V is the volume of the gas wall, A is the surface area of ​​the gas wall, 0.9 and 4 are reference coefficients; By adjusting the model size ratio L, the radiation equivalent optical thickness L under the two working conditions is changed to match the Boltzmann number; and by changing the pressure, the Bouguer number is matched.

5. A cooling structure comprehensive cooling effect modeling matching system, characterized in that: include: A comprehensive cooling efficiency acquisition module is used to obtain a comprehensive cooling efficiency expression according to the cooling process of the hot end components of the cooling structure under the influence of radiation; The method of obtaining the comprehensive cooling effect expression comprises the following steps: Assuming that the wall of the cooling structure is one-dimensional heat conduction and has no internal heat source, its heat conduction control equation is: The boundary conditions of the cooling structure on the cold air side and the gas side are: The comprehensive cooling effect expression is: Among them, k s represents the solid thermal conductivity of the cooling structure, δ represents the wall thickness of the cooling structure, and h c and h g are the wall convection heat transfer coefficients on the cold air side and the gas side of the cooling structure, respectively, h r The equivalent convective heat transfer coefficient, T, represents the radiative heat transfer of the cooling structure. c,i represents the temperature of the cooling air at the entrance of the air film hole of the cooling structure, T g represents the mainstream gas temperature of the cooling structure, T w represents the wall temperature of the cooling structure, T aw represents the adiabatic wall temperature of the cooling structure, T z＝0 represents the temperature of the cooling structure at the cold air side boundary condition, T z＝δ Represents the temperature of the cooling structure at the gas side boundary condition; After dimensionless processing, the one-dimensional comprehensive cooling effect expression is obtained: Where χ is the temperature rise coefficient of the secondary flow from the inlet to the outlet, η is the adiabatic cooling efficiency, and Bi is the Biot number on the mainstream side of the cooling structure; Comprehensive cooling efficiency decomposition module, used to decompose the comprehensive cooling efficiency expression to obtain adiabatic cooling efficiency and radiation equivalent heat transfer coefficient ratio; The model matching module is used to match the radiation term by using the Boltzmann number and the Bouguer number according to the adiabatic cooling efficiency and the radiation equivalent heat transfer coefficient ratio, transform the radiation equivalent heat transfer coefficient ratio, and obtain the adiabatic cooling efficiency and comprehensive cooling efficiency expression of the matched cooling structure; obtain the pressure and radiation equivalent optical thickness of the model according to the adiabatic cooling efficiency and comprehensive cooling efficiency expression of the matched cooling structure; define the model size ratio under two different working conditions and adjust the size, and match the Boltzmann number of the cooling structure by changing the radiation equivalent optical thickness under two different working conditions; match the Bouguer number of the cooling structure by adjusting the pressure data of the model under two different working conditions; The step of decomposing the comprehensive cooling efficiency expression comprises the following steps: The obtained one-dimensional comprehensive cooling efficiency expression is decomposed into the temperature rise coefficient χ of the secondary flow from the inlet to the outlet, the adiabatic cooling efficiency η, the mainstream side Biot number Bi, the ratio of the heat transfer coefficients of the mainstream side and the cold air side Radiation equivalent heat transfer coefficient ratio in: Among them, T c,exit represents the temperature of the cold air at the outlet of the air film hole, δ represents the thickness of the air film plate, and k represents the thermal conductivity of the air film plate; The method of obtaining the adiabatic cooling efficiency and comprehensive cooling efficiency expression of the matched cooling structure comprises the following steps: Use the Boltzmann number and the Bouguer number to match the radiation equivalent heat transfer coefficient ratio h in the radiation term r / h g ,in: The Boltzmann number characterizes the gas radiation intensity, and the Bouguer number characterizes the gas radiation characteristics. The expressions of the Boltzmann number Bo and the Bouguer number Bu are as follows: Bu=α λ,p pL After the numerator and denominator of the Boltzmann number are multiplied by the mainstream gas temperature T, the expression represents the ratio of the radiation heat flux density to the convection heat flux density, and the result is: According to the convection heat transfer coefficient: Radiation equivalent heat transfer coefficient: The expressions of adiabatic cooling efficiency and comprehensive cooling efficiency are as follows: Among them, Bo1 represents the actual high temperature working condition Boltzmann number, Bo2 represents the laboratory low temperature working condition Boltzmann number, q h represents the convective heat transfer, q r represents the radiation heat transfer, T g is the mainstream gas temperature of the cooling structure, T W is the coupled wall temperature, T aw is the adiabatic wall temperature, T c is the secondary flow temperature.

6. A computer device, characterized in that: The computer device includes a memory and a processor, wherein the memory stores a computer program, and when the computer program is executed by the processor, the processor performs the following steps: According to the cooling process of the hot end components of the cooling structure under the influence of radiation, the comprehensive cooling effect expression is obtained; The method of obtaining the comprehensive cooling effect expression comprises the following steps: Assuming that the wall of the cooling structure is one-dimensional heat conduction and has no internal heat source, its heat conduction control equation is: The boundary conditions of the cooling structure on the cold air side and the gas side are: The comprehensive cooling effect expression is: Among them, k s represents the solid thermal conductivity of the cooling structure, δ represents the wall thickness of the cooling structure, and h c and h g are the wall convection heat transfer coefficients on the cold air side and the gas side of the cooling structure, respectively, h r The equivalent convection heat transfer coefficient, T, represents the radiation heat transfer of the cooling structure. c,i represents the temperature of the cooling air at the entrance of the air film hole of the cooling structure, T g represents the mainstream gas temperature of the cooling structure, T w represents the wall temperature of the cooling structure, T aw represents the adiabatic wall temperature of the cooling structure, T z＝0 represents the temperature of the cooling structure at the cold air side boundary condition, T z＝δ Represents the temperature of the cooling structure at the gas side boundary condition; After dimensionless processing, the one-dimensional comprehensive cooling effect expression is obtained: Where χ is the temperature rise coefficient of the secondary flow from the inlet to the outlet, η is the adiabatic cooling efficiency, and Bi is the Biot number on the mainstream side of the cooling structure; The comprehensive cooling efficiency expression is decomposed to obtain the adiabatic cooling efficiency and the radiation equivalent heat transfer coefficient ratio; According to the adiabatic cooling efficiency and the radiation equivalent heat transfer coefficient ratio, the Boltzmann number and the Bouguer number are used to match the radiation term, and the radiation equivalent heat transfer coefficient ratio is transformed to obtain the adiabatic cooling efficiency and comprehensive cooling efficiency expression of the matched cooling structure. According to the adiabatic cooling efficiency and comprehensive cooling efficiency expression of the matched cooling structure, the pressure and radiation equivalent optical thickness of the model are obtained; the model size ratio under two different working conditions is defined and the size is adjusted, and the Boltzmann number of the cooling structure is matched by changing the radiation equivalent optical thickness under two different working conditions; the Bouguer number of the cooling structure is matched by adjusting the pressure data of the model under two different working conditions; The step of decomposing the comprehensive cooling efficiency expression comprises the following steps: The obtained one-dimensional comprehensive cooling efficiency expression is decomposed into the temperature rise coefficient χ of the secondary flow from the inlet to the outlet, the adiabatic cooling efficiency η, the mainstream side Biot number Bi, the ratio of the heat transfer coefficients of the mainstream side and the cold air side Radiation equivalent heat transfer coefficient ratio in: Among them, T c,exit represents the temperature of the cold air at the outlet of the air film hole, δ represents the thickness of the air film plate, and k represents the thermal conductivity of the air film plate; The method of obtaining the adiabatic cooling efficiency and comprehensive cooling efficiency expression of the matched cooling structure comprises the following steps: Use the Boltzmann number and the Bouguer number to match the radiation equivalent heat transfer coefficient ratio h in the radiation term r h g ,in: The Boltzmann number characterizes the gas radiation intensity, and the Bouguer number characterizes the gas radiation characteristics. The expressions of the Boltzmann number Bo and the Bouguer number Bu are as follows: Bu=α λ,p pL After the numerator and denominator of the Boltzmann number are multiplied by the mainstream gas temperature T, the expression represents the ratio of the radiation heat flux density to the convection heat flux density, and the result is: According to the convection heat transfer coefficient: Radiation equivalent heat transfer coefficient: The expressions of adiabatic cooling efficiency and comprehensive cooling efficiency are as follows: Among them, Bo1 represents the actual high temperature working condition Boltzmann number, Bo2 represents the laboratory low temperature working condition Boltzmann number, q h represents the convective heat transfer, q r represents the radiation heat transfer, T g is the mainstream gas temperature of the cooling structure, T W is the coupled wall temperature, T aw is the adiabatic wall temperature, T c is the secondary flow temperature.

7. A computer-readable storage medium, characterized in that: The computer readable storage medium stores a computer program, and when the computer program is executed by a processor, the processor performs the following steps: According to the cooling process of the hot end components of the cooling structure under the influence of radiation, the comprehensive cooling effect expression is obtained; The method of obtaining the comprehensive cooling effect expression comprises the following steps: Assuming that the wall of the cooling structure is one-dimensional heat conduction and has no internal heat source, its heat conduction control equation is: The boundary conditions of the cooling structure on the cold air side and the gas side are: The comprehensive cooling effect expression is: Among them, k s represents the solid thermal conductivity of the cooling structure, δ represents the wall thickness of the cooling structure, and h c and h g are the wall convection heat transfer coefficients on the cold air side and the gas side of the cooling structure, respectively, h r The equivalent convective heat transfer coefficient, T, represents the radiative heat transfer of the cooling structure. c,i represents the temperature of the cooling air at the entrance of the air film hole of the cooling structure, T g represents the mainstream gas temperature of the cooling structure, T w represents the wall temperature of the cooling structure, T aw represents the adiabatic wall temperature of the cooling structure, T z＝0 represents the temperature of the cooling structure at the cold air side boundary condition, T z＝δ Represents the temperature of the cooling structure at the gas side boundary condition; After dimensionless processing, the one-dimensional comprehensive cooling effect expression is obtained: Where χ is the temperature rise coefficient of the secondary flow from the inlet to the outlet, η is the adiabatic cooling efficiency, and Bi is the Biot number on the mainstream side of the cooling structure; The comprehensive cooling efficiency expression is decomposed to obtain the adiabatic cooling efficiency and the radiation equivalent heat transfer coefficient ratio; According to the adiabatic cooling efficiency and the radiation equivalent heat transfer coefficient ratio, the Boltzmann number and the Bouguer number are used to match the radiation term, and the radiation equivalent heat transfer coefficient ratio is transformed to obtain the adiabatic cooling efficiency and comprehensive cooling efficiency expression of the matched cooling structure. According to the adiabatic cooling efficiency and comprehensive cooling efficiency expression of the matched cooling structure, the pressure and radiation equivalent optical thickness of the model are obtained; the model size ratio under two different working conditions is defined and the size is adjusted, and the Boltzmann number of the cooling structure is matched by changing the radiation equivalent optical thickness under two different working conditions; the Bouguer number of the cooling structure is matched by adjusting the pressure data of the model under two different working conditions; The step of decomposing the comprehensive cooling efficiency expression comprises the following steps: The obtained one-dimensional comprehensive cooling efficiency expression is decomposed into the temperature rise coefficient χ of the secondary flow from the inlet to the outlet, the adiabatic cooling efficiency η, the mainstream side Biot number Bi, the ratio of the heat transfer coefficients of the mainstream side and the cold air side Radiation equivalent heat transfer coefficient ratio in: Among them, T c,exit represents the temperature of the cold air at the outlet of the air film hole, δ represents the thickness of the air film plate, and k represents the thermal conductivity of the air film plate; The method of obtaining the adiabatic cooling efficiency and comprehensive cooling efficiency expression of the matched cooling structure comprises the following steps: Use the Boltzmann number and the Bouguer number to match the radiation equivalent heat transfer coefficient ratio h in the radiation term r h g ,in: The Boltzmann number characterizes the gas radiation intensity, and the Bouguer number characterizes the gas radiation characteristics. The expressions of the Boltzmann number Bo and the Bouguer number Bu are as follows: Bu=α λ,p pL After the numerator and denominator of the Boltzmann number are multiplied by the mainstream gas temperature T, the expression represents the ratio of the radiation heat flux density to the convection heat flux density, and the result is: According to the convection heat transfer coefficient: Radiation equivalent heat transfer coefficient: The expressions of adiabatic cooling efficiency and comprehensive cooling efficiency are as follows: Among them, Bo1 represents the actual high temperature working condition Boltzmann number, Bo2 represents the laboratory low temperature working condition Boltzmann number, q h represents the convective heat transfer, q r represents the radiation heat transfer, T g is the mainstream gas temperature of the cooling structure, T W is the coupled wall temperature, T aw is the adiabatic wall temperature, T c is the secondary flow temperature.

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