Method for analyzing quick coupling heat transfer performance of turbine blade laminate cooling structure

Abstract

The present disclosure relates to a turbine blade laminate cooling structure rapid coupling heat exchange performance analysis method, the turbine blade laminate cooling structure has internal cooling and external cooling, the turbine blade laminate cooling structure rapid coupling heat exchange performance analysis method, comprising: analyzing the internal cooling to obtain the outflow state parameter of cold gas at the outlet of the film hole; by the outflow state parameter, the external cooling is simplified as the third type boundary condition, the third type boundary condition includes the heat transfer coefficient of convection and the temperature of adiabatic wall; in combination with the third type boundary condition, the internal cooling is calculated to obtain the temperature distribution and cooling efficiency distribution of the outer surface of the turbine blade laminate; set the first threshold value, compare the absolute value of the variation of the outer surface temperature distribution with the first threshold value;When the absolute value of the variation of the outer surface temperature distribution is less than or equal to the first threshold value, the outer surface temperature distribution and the outer surface cooling efficiency distribution are the heat exchange performance of the turbine blade laminate cooling structure.

Description

TECHNICAL FIELD

[0001] The present disclosure relates to the technical field of aero-engine manufacturing, and particularly relates to a method for rapidly coupling and analyzing heat exchange performance of a turbine blade panel cooling structure. BACKGROUND

[0002] At present, in the technical field of aero-engine manufacturing, in the analysis of heat exchange performance of a traditional turbine blade panel cooling structure, a numerical method is usually used to analyze the flow and heat transfer of the panel cooling structure containing a solid domain and a fluid domain, so as to obtain the comprehensive performance under the coupling of internal cooling and external cooling. In this numerical simulation process, the flow of cooling gas before entering the panel cooling structure, the flow and heat exchange of cooling gas inside the panel, and the flow and heat exchange of high-temperature gas and cooling gas outside the panel are usually simulated.

[0003] However, in the analysis of the flow and heat exchange of high-temperature gas and cooling gas outside the panel, due to the interaction between the cooling gas jet and the cross flow of high-temperature gas, a horseshoe vortex is generated in front of the cooling gas jet, a trailing vortex is generated behind the cooling gas jet, a jet shear layer vortex is generated at the interface between the cooling gas jet and the high-temperature gas, and a kidney-shaped vortex pair that dominates the flow is formed behind the interface.

[0004] This series of complex vortexes makes it necessary to use a large number of fine grids to simulate the mixing of the external high-temperature gas and the cooling gas jet in the heat exchange performance analysis using the traditional analysis method, which results in low efficiency and high cost of the heat exchange performance analysis. At the same time, the traditional analysis method is difficult to accurately capture the flow field and heat exchange of the external high-temperature gas and the cooling gas jet outside the panel when using the numerical simulation method to analyze the heat exchange performance, which results in low accuracy of the analysis results.

[0005] It should be noted that the information disclosed in the above background section is only used to strengthen the understanding of the background of the present disclosure, and therefore can include information that does not constitute prior art known to those of ordinary skill in the art. SUMMARY

[0006] The present disclosure aims to provide a method for rapidly coupling and analyzing heat exchange performance of a turbine blade panel cooling structure, which can greatly improve the efficiency and accuracy of analyzing the heat exchange performance of the turbine blade panel cooling structure, and can also save the cost and time of analysis.

[0007] The present disclosure provides a method for rapidly coupling and analyzing heat exchange performance of a turbine blade panel cooling structure, the turbine blade panel cooling structure having internal cooling and external cooling, the internal cooling including impingement cooling and flow around cooling, and the external cooling including film cooling, the method comprising:

[0008] analyzing the internal cooling to obtain an outflow state parameter of the cooling air at the exit of the film hole;

[0009] simplifying the external cooling into a third type of boundary condition including a convective heat transfer coefficient and an adiabatic wall temperature by the outflow state parameter;

[0010] calculating the internal cooling in combination with the third type of boundary condition to obtain an external surface temperature distribution and an external surface cooling efficiency distribution of the turbine blade panel;

[0011] setting a first threshold value, comparing an absolute value of a variation of the external surface temperature distribution with the first threshold value; when the absolute value of the variation of the external surface temperature distribution is less than or equal to the first threshold value, the external surface temperature distribution and the external surface cooling efficiency distribution are heat exchange performance of the turbine blade panel cooling structure.

[0012] In an exemplary embodiment of the present disclosure, the analyzing the internal cooling to obtain an outflow state parameter of the cooling air at the exit of the film hole comprises:

[0013] setting a cooling inlet boundary condition of the internal cooling;

[0014] calculating a flow field structure and heat exchange condition of the internal cooling according to the cooling inlet boundary condition of the internal cooling to obtain the outflow state parameter of the cooling air at the exit of the film hole.

[0015] In an exemplary embodiment of the present disclosure, the simplifying the external cooling into a third type of boundary condition including a convective heat transfer coefficient and an adiabatic wall temperature by the outflow state parameter comprises:

[0016] performing internal-external coupling conjugate heat exchange calculation on the turbine blade panel cooling structure to obtain the convective heat transfer coefficient;

[0017] calculating adiabatic film cooling efficiency of multiple rows of the film holes according to the outflow state parameter;

[0018] obtaining the adiabatic wall temperature according to the adiabatic film cooling efficiency of the multiple rows of the film holes.

[0019] In an exemplary embodiment of the present disclosure, the calculating adiabatic film cooling efficiency of multiple rows of the film holes according to the outflow state parameter comprises:

[0020] calculating adiabatic film cooling efficiency and adiabatic wall temperature of a single film hole according to the outflow state parameter;

[0021] According to the adiabatic wall temperature of each single gas film hole, the adiabatic gas film cooling efficiency of each single gas film hole is recalculated to obtain the adiabatic gas film cooling efficiency of the plurality of rows of gas film holes.

[0022] In an exemplary embodiment of the present disclosure, the outflow state parameters include at least one of flow velocity, temperature, and density.

[0023] In an exemplary embodiment of the present disclosure, the calculating the adiabatic gas film cooling efficiency and the adiabatic wall temperature of each single gas film hole according to the outflow state parameters comprises:

[0024] Substituting the flow velocity of the cold gas at the gas film hole outlet into the first formula to obtain the adiabatic gas film cooling efficiency of each single gas film hole;

[0025] Substituting the temperature of the cold gas at the gas film hole outlet into the second formula to obtain the adiabatic wall temperature of each single gas film hole;

[0026] wherein the first formula is:

[0027]

[0028] wherein η f is the adiabatic gas film cooling efficiency of each single gas film hole; α t is the turbulent thermal diffusion coefficient; x is the cold gas flow direction coordinate value with the center of the gas film hole as the origin; D f is the diameter of the gas film hole; V g is the velocity of the high-temperature gas outside the turbine blade panel cooling structure; y is the lateral coordinate value of the gas film hole; y 1 / 2 is the lateral adiabatic gas film cooling efficiency reduction, which is the lateral distance when the lateral adiabatic gas film cooling efficiency is reduced to half of the adiabatic gas film cooling efficiency at the corresponding position of the centerline of the gas film hole; BR is the blowing ratio, BR = ρ g V g / ρ c V c , ρ g is the density of the high-temperature gas, V g is the flow velocity of the high-temperature gas, ρ c is the density of the cold gas at the gas film hole outlet, V c is the flow velocity of the cold gas at the gas film hole outlet;

[0029] The second formula is:

[0030] T aw = T g - η f (T g -T c ),

[0031] wherein the T aw is the adiabatic wall temperature of a single gas film hole; T g is the high-temperature gas temperature; η f is the adiabatic film cooling effectiveness of a single gas film hole; T c is the temperature of the cooling gas at the outlet of the gas film hole.

[0032] In an exemplary embodiment of the present disclosure, the recalculating the adiabatic film cooling effectiveness of each single gas film hole according to the adiabatic wall temperature of each single gas film hole to obtain the adiabatic film cooling effectiveness of the plurality of rows of gas film holes comprises:

[0033] substituting the adiabatic wall temperature of each single gas film hole into a third formula to re-obtain the adiabatic film cooling effectiveness of each single gas film hole;

[0034] substituting the adiabatic film cooling effectiveness of each single gas film hole into a fourth formula to obtain the adiabatic film cooling effectiveness of the plurality of rows of gas film holes;

[0035] wherein the third formula is:

[0036]

[0037] wherein η f,i is the adiabatic film cooling effectiveness of the i-th gas film hole, T aw,i is the adiabatic wall temperature of the i-th gas film hole, T aw,i-1 is the adiabatic wall temperature of the gas film hole upstream of the i-th gas film hole;

[0038] the fourth formula is:

[0039]

[0040] wherein η f总 is the adiabatic film cooling effectiveness of the plurality of rows of gas film holes.

[0041] In an exemplary embodiment of the present disclosure, the obtaining the adiabatic wall temperature according to the adiabatic film cooling effectiveness of the plurality of rows of gas film holes comprises:

[0042] substituting the adiabatic film cooling effectiveness of the plurality of rows of gas film holes into a fifth formula to obtain the adiabatic wall temperature of the plurality of rows of gas film holes;

[0043] wherein the fifth formula is:

[0044] T aw总 = T g - η f总 (T g - T c),

[0045] wherein, T aw总 is the adiabatic wall temperature of the plurality of rows of the film holes; T g is the high-temperature gas temperature; T c is the temperature of the cold gas at the outlet of the film holes.

[0046] In an exemplary embodiment of the present disclosure, the calculation of the internal cooling, in combination with the third type of boundary condition, to obtain the external surface temperature distribution and the external surface cooling efficiency distribution of the turbine blade laminate includes:

[0047] establishing a model of the turbine blade laminate and dividing a grid for the model of the turbine blade laminate;

[0048] calculating the external surface temperature and the external surface cooling efficiency in each of the grids by using the method of computational fluid dynamics in combination with the third type of boundary condition;

[0049] integrating the external surface temperature and the external surface cooling efficiency in each of the grids to obtain the external surface distribution and the external surface cooling efficiency distribution of the turbine blade laminate.

[0050] In an exemplary embodiment of the present disclosure, the turbine blade laminate cooling structure rapid coupling heat exchange performance analysis method further includes:

[0051] when the absolute value of the variation of the external surface temperature distribution is greater than a first threshold value, re-executing the analysis of the internal cooling to obtain the outflow state parameter of the cold gas at the outlet of the film holes to correct the outflow state parameter of the cold gas at the outlet of the film holes;

[0052] substituting the corrected outflow state parameter into the subsequent steps until the absolute value of the variation of the final external surface temperature distribution is less than or equal to the first threshold value, at which time the obtained external surface temperature distribution and external surface cooling efficiency distribution are the heat exchange performance of the turbine blade laminate cooling structure.

[0053] The technical solution provided by the present disclosure can achieve the following beneficial effects:

[0054] The turbine blade laminate cooling structure rapid coupling heat exchange performance analysis method provided by the present disclosure can obtain the outflow state parameter of the cold gas at the outlet of the film holes by analyzing the internal cooling. The external cooling can be simplified as the third type of boundary condition by using the outflow state parameter, and the internal cooling of the turbine blade laminate can be calculated in combination with the third type of boundary condition, so as to obtain the external surface temperature distribution and the external surface cooling efficiency distribution of the turbine blade.

[0055] Therefore, in the analysis of the external cooling, the external cooling is simplified as the third type of boundary condition, so that the problem of a series of complex vortexes caused by the mixing of the high-temperature gas outside the layer plate and the cooling gas at the gas film hole is no longer considered. Therefore, the mixing of the external high-temperature gas and the cooling gas jet does not need to be simulated by using a large number of fine grids, so that the analysis efficiency of the heat exchange performance can be greatly improved, and the cost and time of the analysis and calculation can be greatly reduced.

[0056] Meanwhile, by simplifying the external cooling as the third type of boundary condition, the problem that the flow field structure and the heat exchange condition of the external high-temperature gas and the cooling gas jet outside the layer plate need to be accurately captured in the conventional analysis method can be avoided, so that the accuracy of the analysis result can be greatly improved.

[0057] In addition, the first threshold value is set, and the absolute value of the change amount of the outer surface temperature distribution is compared with the first threshold value. Only when the absolute value of the change amount of the outer surface temperature distribution is less than or equal to the first threshold value, the obtained outer surface temperature distribution and the outer surface cooling efficiency distribution can be considered as the final analysis result of the heat exchange performance of the turbine blade layer plate cooling structure. Therefore, by this method, the preliminary analysis result obtained in the previous step can be verified, so that the accuracy of the analysis result obtained by the present disclosure can be further improved.

[0058] It should be understood that the above general description and the following detailed description are only exemplary and explanatory, and cannot limit the present disclosure. BRIEF DESCRIPTION OF DRAWINGS

[0059] The drawings incorporated into the specification and forming a part thereof show embodiments consistent with the present disclosure and, together with the specification, serve to explain the principles of the present disclosure. Obviously, the drawings in the following description are only some embodiments of the present disclosure, and other drawings can be obtained from these drawings without creative labor for those skilled in the art.

[0060] Figure 1 A flowchart of a rapid coupling heat exchange performance analysis method of a turbine blade layer plate cooling structure according to an exemplary embodiment of the present disclosure is shown;

[0061] Figure 2 A cross-sectional structure schematic diagram of a turbine blade layer plate according to an exemplary embodiment of the present disclosure is shown;

[0062] Figure 3 A flowchart of a rapid coupling heat exchange performance analysis method of a turbine blade layer plate cooling structure according to another exemplary embodiment of the present disclosure is shown.

[0063] LEGEND OF REFERENCE NUMBERS:

[0064] 1. Turbine blade layered cooling structure; 11. Inner layer; 12. Outer layer; 13. Baffle column; 14. Impact hole; 15. Film cooling hole;

[0065] 2. Air conditioning;

[0066] 3. High-temperature gas. Detailed Implementation

[0067] Exemplary embodiments will now be described more fully with reference to the accompanying drawings. However, these exemplary embodiments can be implemented in many forms and should not be construed as limited to the embodiments set forth herein; rather, they are provided so that this disclosure will be thorough and complete, and will fully convey the concept of the exemplary embodiments to those skilled in the art. The same reference numerals in the drawings denote the same or similar structures, and therefore their detailed description will be omitted.

[0068] Although relative terms such as "up" and "down" are used in this specification to describe the relative relationship of one component of an icon to another, these terms are used only for convenience, such as according to the orientation of the examples shown in the accompanying drawings. It is understood that if the device of the icon is flipped upside down, the component described as "up" will become the component described as "down." When a structure is "up" of another structure, it may mean that the structure is integrally formed on the other structure, or that the structure is "directly" mounted on the other structure, or that the structure is "indirectly" mounted on the other structure through another structure.

[0069] The terms “a,” “one,” “the,” and “the” are used to indicate the existence of one or more elements / components / etc.; the terms “including” and “having” are used to indicate an open-ended inclusion meaning and that there may be other elements / components / etc. in addition to the listed elements / components / etc.; the terms “first” and “second” are used only as markers and are not a limitation on the number of objects.

[0070] like Figure 1 As shown, this disclosure first provides a rapid coupled heat transfer performance analysis method for a turbine blade laminate cooling structure 1. This rapid coupled heat transfer performance analysis method for a turbine blade laminate cooling structure 1 can significantly improve the efficiency and accuracy of analyzing the heat transfer performance of the turbine blade laminate cooling structure 1, and can also save analysis costs and time.

[0071] In one embodiment of this disclosure, such as Figure 2As shown, the turbine blade layer plate cooling structure 1 can include: an inner layer plate 11, an outer layer plate 12, a spoiler column 13, an impingement hole 14 and a film hole 15. Among them, the inner layer plate 11 and the outer layer plate 12 can be oppositely arranged, and there is a containing cavity between the inner layer plate 11 and the outer layer plate 12. The spoiler column 13 can be located in the containing cavity, and both ends of the spoiler column 13 can be connected with the inner layer plate 11 and the outer layer plate 12. The impingement hole 14 can be located on the inner layer plate 11 and can be in communication with the containing cavity. The film hole 15 can be located on the outer layer plate 12 and can be in communication with the containing cavity.

[0072] The cold gas 2 (cooling gas) can enter the impingement hole 14 from the side of the inner layer plate 11 away from the outer layer plate 12, and after passing through the impingement hole 14, a cold gas 2 jet is formed to impinge into the containing cavity. In the containing cavity, the cold gas 2 jet can flow around and can accelerate out through the film hole 15 after bypassing each spoiler column 13, and finally form a cooling gas film on the side of the outer layer plate 12 away from the inner layer plate 11 (i.e. the outer surface of the turbine blade), so as to isolate the high-temperature gas 3 located on the side of the outer layer plate 12 away from the inner layer plate 11 from the turbine blade, thereby being able to reduce the temperature of the turbine blade surface.

[0073] Therefore, the turbine blade layer plate can be subjected to impingement cooling through the impingement hole 14, bypass flow cooling through the spoiler column 13, and film cooling through the film hole 15. Thus, the turbine blade layer plate cooling is a process of internal-external coupled cooling, and therefore the cooling of the turbine blade layer plate cooling structure 1 can be divided into internal cooling and external cooling. Among them, the internal cooling can include: impingement cooling and bypass flow cooling; the external cooling can include: film cooling.

[0074] In an embodiment of the present disclosure, the high-temperature gas 3 can be high-temperature combustion gas, but is not limited thereto, and the type of the high-temperature gas 3 can also not be limited to high-temperature combustion gas, for example, the high-temperature gas 3 can also be high-temperature air, etc., and the present disclosure does not limit this, which can be selected as needed, and this is within the protection scope of the present disclosure.

[0075] As shown in the above, Figure 1 The rapid coupling heat transfer performance analysis method of the turbine blade layer plate cooling structure 1 can include:

[0076] Step S10, analyzing the internal cooling to obtain the outflow state parameters of the cold gas 2 at the outlet of the film hole 15.

[0077] Step S20, simplifying the external cooling into a third type of boundary condition through the outflow state parameters, and the third type of boundary condition includes a convective heat transfer coefficient and an adiabatic wall temperature.

[0078] Step S30, in combination with the third type of boundary condition, the internal cooling is calculated to obtain the outer surface temperature distribution and the outer surface cooling efficiency distribution of the turbine blade laminate.

[0079] Step S40, a first threshold value is set, and the absolute value of the variation of the outer surface temperature distribution is compared with the first threshold value; when the absolute value of the variation of the outer surface temperature distribution is less than or equal to the first threshold value, the outer surface temperature distribution and the outer surface cooling efficiency distribution are the heat exchange performance of the turbine blade laminate cooling structure 1.

[0080] The above steps are explained in detail as follows:

[0081] In the above step S10, the internal cooling of the turbine blade laminate can be analyzed to obtain the outflow state parameters of the cooling gas 2 at the outlet of the film hole 15. Specifically, the cooling inlet boundary condition of the internal cooling can be set. According to the cooling inlet boundary condition of the internal cooling, the flow field and heat exchange of the internal cooling are calculated to obtain the outflow state parameters at the outlet of the film hole 15.

[0082] For example, the cooling inlet boundary condition of the internal cooling can be set specifically; according to the set cooling inlet boundary condition, the numerical simulation method is used to calculate the internal cooling flow field structure and heat exchange of the laminate under the given cooling inlet boundary condition, so that the outflow state parameters of the cooling gas 2 at the outlet of the film hole 15 under the action of the internal cooling can be obtained.

[0083] In an embodiment of the present disclosure, the outflow state parameters can include at least one of flow velocity, temperature and density, but are not limited thereto, and can be adjusted and selected according to actual needs, which are all within the protection scope of the present disclosure.

[0084] In the above step S20, the external cooling can be simplified to the third type of boundary condition through the outflow state parameters. The third type of boundary condition can include the convective heat transfer coefficient and the adiabatic wall temperature.

[0085] Therefore, when analyzing the external cooling, the technical scheme of the present disclosure simplifies the external cooling to the third type of boundary condition, so that the problem of a series of complex vortexes caused by the mixing of the high-temperature gas 3 outside the laminate and the cooling gas at the film hole 15 is no longer considered. Therefore, the present disclosure no longer needs to use a large number of fine grids to simulate the mixing of the external high-temperature gas 3 and the cooling gas jet, so that the heat exchange performance analysis efficiency can be greatly improved, and the analysis and calculation cost and time can be greatly reduced.

[0086] Meanwhile, the disclosure can also avoid the problem of needing to accurately capture the flow field structure and heat exchange of the external high-temperature gas 3 and the jet of the cooling gas 2 on the outside of the panel in the conventional analysis method by simplifying the external cooling to the third type of boundary condition, thereby greatly improving the accuracy of the analysis results.

[0087] In one embodiment of the disclosure, the internal and external coupling conjugate heat exchange calculation of the turbine blade panel cooling structure 1 can be performed to obtain the convective heat exchange coefficient. Specifically, the external high-temperature gas 3, impingement cooling and flow-by cooling can be coupled and calculated together in the manner of CFD (Computational Fluid Dynamics), thereby obtaining the convective heat exchange coefficient. However, this is not limited thereto, and the internal and external coupling conjugate calculation can also be performed in the manner of CFD, for example, the empirical formula calculation and the like can also be used to obtain the same, which is within the protection scope of the disclosure.

[0088] Further, when the internal and external coupling conjugate calculation is performed in the manner of CFD, the CFD software can be used to improve the calculation speed and efficiency.

[0089] Further, the adiabatic film cooling efficiency of the multiple rows of gas film holes 15 can be calculated according to the outflow state parameters. Specifically, the adiabatic film cooling efficiency of the single gas film hole 15 and the adiabatic wall temperature of the single gas film hole 15 can be calculated according to the outflow state parameters.

[0090] In the embodiment, the flow velocity of the cooling gas 2 at the outlet of the gas film hole 15 can be substituted into the first formula to obtain the adiabatic film cooling efficiency of the single gas film hole 15, and the temperature of the cooling gas 2 at the outlet of the gas film hole 15 can be substituted into the second formula to obtain the adiabatic wall temperature of the single gas film hole 15.

[0091] The above first formula can be:

[0092]

[0093] wherein, η f is the adiabatic film cooling efficiency of the single gas film hole 15; α t is the turbulent thermal diffusion coefficient; x is the flow direction coordinate value of the cooling gas 2 with the center of the gas film hole 15 as the origin; D f is the diameter of the gas film hole 15; V g is the velocity of the high-temperature gas 3 outside the turbine blade panel cooling structure 1; y is the lateral coordinate value of the gas film hole 15; y 1 / 2 is the lateral adiabatic film cooling efficiency, and BR is the blowing ratio, BR = ρ g V g / ρc V c , p g is the density of the hot gas 3, V g is the flow velocity of the hot gas 3, p c is the density of the cold gas 2 at the outlet of the film hole 15, V c is the flow velocity of the cold gas 2 at the outlet of the film hole 15.

[0094] The second formula can be:

[0095] T aw = T g - η f (T g -T c ),

[0096] wherein T aw is the adiabatic wall temperature of the single film hole 15, T g is the temperature of the hot gas 3, η f is the adiabatic film cooling effectiveness of the single film hole 15, and T c is the temperature of the cold gas 2 at the outlet of the film hole 15.

[0097] In the present embodiment, the adiabatic film cooling effectiveness of each single film hole 15 can be recalculated according to the adiabatic wall temperature of each single film hole 15 to obtain the adiabatic film cooling effectiveness of the multiple rows of film holes 15.

[0098] Specifically, the adiabatic wall temperature of each single film hole 15 can be substituted into the third formula to obtain the adiabatic film cooling effectiveness of each single film hole 15. And the adiabatic film cooling effectiveness of each single film hole 15 can be substituted into the fourth formula to obtain the adiabatic film cooling effectiveness of the multiple rows of film holes 15.

[0099] wherein the third formula can be:

[0100]

[0101] wherein η f,i is the adiabatic film cooling effectiveness of the i-th film hole 15, T aw,i is the adiabatic wall temperature of the i-th film hole 15, and T aw,i-1 is the adiabatic wall temperature of the film hole 15 upstream of the i-th film hole 15.

[0102] The fourth formula can be:

[0103]

[0104] wherein η f总The adiabatic film cooling efficiency of the plurality of rows of the film holes 15.

[0105] Further, the adiabatic wall temperature of the plurality of rows of the film holes 15 can be obtained according to the adiabatic film cooling efficiency of the plurality of rows of the film holes 15. The adiabatic wall temperature of the plurality of rows of the film holes 15 can be the adiabatic wall temperature in the third type of boundary condition.

[0106] Specifically, the adiabatic film cooling efficiency of the plurality of rows of the film holes 15 can be substituted into the fifth formula to obtain the adiabatic wall temperature of the plurality of rows of the film holes 15.

[0107] The fifth formula can be:

[0108] T aw总 = T g - η f总 (T g - T c ),

[0109] wherein T aw总 is the adiabatic wall temperature of the plurality of rows of the film holes 15; T g is the high-temperature gas 3 temperature; and T c is the temperature of the cold gas 2 at the outlet of the film hole 15.

[0110] Therefore, by using the above formulas and calculation methods, the convection heat transfer coefficient and the adiabatic wall temperature can be accurately and simply obtained, the heat transfer performance analysis efficiency can be further improved, and the analysis and calculation cost and time can be further reduced.

[0111] In step S30, the internal cooling can be calculated in combination with the third type of boundary condition to obtain the outer surface temperature distribution and the outer surface cooling efficiency distribution of the turbine blade panel.

[0112] Specifically, a model of the turbine blade panel can be established, and the model of the turbine blade panel can be meshed. Meanwhile, the outer surface temperature and the outer surface cooling efficiency in each grid can be calculated by using the computational fluid dynamics method in combination with the third type of boundary condition, and the outer surface temperature and the outer surface cooling efficiency in each grid can be integrated to obtain the outer surface distribution and the outer surface cooling efficiency distribution of the turbine blade panel.

[0113] Similarly, it should be noted that when the internal cooling is calculated by using the CFD method to obtain the outer surface temperature distribution and the outer surface cooling efficiency distribution of the turbine blade panel, the CFD software can be used to improve the calculation speed and efficiency.

[0114] Therefore, the disclosure can realize decoupling of the external cooling and the internal cooling of the turbine blade laminate cooling structure 1 through the steps S20 and S30, can independently calculate the external cooling and the internal cooling, and can reduce the complexity of numerical calculation, so as to effectively improve the calculation efficiency.

[0115] In the step S40, the first threshold value can be set, and the absolute value of the change amount of the outer surface temperature distribution can be compared with the first threshold value; when the absolute value of the change amount of the outer surface temperature distribution is less than or equal to the first threshold value, the outer surface temperature distribution and the outer surface cooling efficiency distribution are the heat exchange performance of the turbine blade laminate cooling structure 1.

[0116] Therefore, the disclosure sets the first threshold value, and compares the absolute value of the change amount of the outer surface temperature distribution with the first threshold value. Only when the absolute value of the change amount of the outer surface temperature distribution is less than or equal to the first threshold value, the obtained outer surface temperature distribution and the outer surface cooling efficiency distribution can be considered as the final heat exchange performance analysis result of the turbine blade laminate cooling structure 1. Therefore, the disclosure can verify the preliminary analysis result obtained in the previous step in this way, so as to further improve the accuracy of the analysis result obtained.

[0117] In an embodiment of the disclosure, the first threshold value can be set first, which can be the error tolerance of the analysis result. The disclosure does not limit the specific value of the first threshold value, which can be selected and set according to actual needs, which is within the protection scope of the disclosure.

[0118] The change amount of the outer surface temperature can be calculated through the outer surface temperature distribution obtained in the step S30. The change amount of the outer surface temperature can be compared with the first threshold value, and when the absolute value of the change amount of the outer surface temperature distribution is less than or equal to the first threshold value, it can represent that the outer surface temperature distribution is uniform at this time, and further can represent that the obtained outer surface temperature distribution and the outer surface cooling efficiency distribution at this time are the final heat exchange performance of the turbine blade laminate cooling structure 1.

[0119] In an embodiment of the disclosure, as shown in Figure 3 The turbine blade laminate cooling structure 1 fast coupling heat exchange performance analysis method can further include:

[0120] The step S50, when the absolute value of the change amount of the outer surface temperature distribution is greater than the first threshold value, re-executes the analysis of the internal cooling to obtain the outflow state parameter of the cold gas 2 at the outlet of the film hole 15, and modifies the outflow state parameter of the cold gas 2 at the outlet of the film hole 15.

[0121] Step S60, substituting the corrected outflow state parameter into the subsequent steps until the absolute value of the change in the outer surface temperature distribution is less than or equal to the first threshold value, at which time the obtained outer surface temperature distribution and the outer surface cooling efficiency distribution are the heat exchange performance of the turbine blade panel cooling structure 1.

[0122] It should be noted that the substitution of the corrected outflow state parameter into the subsequent steps in step S60 refers to the substitution of the corrected outflow state parameter into steps S20, S30 and S40. If the absolute value of the change in the outer surface temperature distribution obtained at this time is less than or equal to the first threshold value, the process can be ended, thereby obtaining the final heat exchange performance of the turbine blade panel cooling structure 1. If the absolute value of the change in the outer surface temperature distribution obtained at this time is greater than the first threshold value, steps S50 and S60 need to be continued to be executed to perform iterative calculation again until the absolute value of the change in the outer surface temperature distribution is less than or equal to the first threshold value.

[0123] Thus, the present disclosure can self-check inaccurate analysis and calculation results by setting iterative calculation in the turbine blade panel cooling structure 1 fast coupling heat exchange performance analysis method, thereby optimizing the inaccurate analysis and calculation results, so that the finally formed analysis and calculation results have high accuracy, thereby meeting the requirements of analysis and calculation to further improve the accuracy of the analysis and calculation results.

[0124] In addition, it should be noted that although the steps of the XX turbine blade panel cooling structure 1 fast coupling heat exchange performance analysis method in the present disclosure are described in a specific order in the accompanying drawings, this does not require or imply that these steps must be performed in this specific order, or that all the steps shown must be performed to achieve the desired results. In addition or alternatively, some steps can be omitted, multiple steps can be combined into one step, and / or one step can be divided into multiple steps, etc.

[0125] Other embodiments of the present disclosure will be apparent to those skilled in the art upon consideration of the specification and practice of the present disclosure. The present disclosure is intended to cover any variations, uses or adaptive changes of the present disclosure following the general principles thereof and including those expressly stated or implied herein. The specification and examples are to be regarded as exemplary only, and the true scope and spirit of the present disclosure are indicated by the appended claims.

Claims

1. A method for analyzing the rapid coupling heat transfer performance of a turbine blade laminate cooling structure, characterized in that, The turbine blade laminate cooling structure has internal cooling and external cooling, the internal cooling includes impingement cooling and flow around cooling, the external cooling includes film cooling, the turbine blade laminate cooling structure rapid coupling heat transfer performance analysis method comprises: analyzing the internal cooling to obtain outflow state parameters of the cold air at the film hole outlet; simplifying the external cooling into a third type of boundary condition through the outflow state parameters, the third type of boundary condition includes a convective heat transfer coefficient and an adiabatic wall temperature; calculating the internal cooling in combination with the third type of boundary condition to obtain an outer surface temperature distribution and an outer surface cooling efficiency distribution of the turbine blade laminate; setting a first threshold value, and comparing an absolute value of a variation of the outer surface temperature distribution with the first threshold value; when the absolute value of the variation of the outer surface temperature distribution is greater than the first threshold value, re-executing the step of analyzing the internal cooling to obtain the outflow state parameters of the cold air at the film hole outlet to correct the outflow state parameters of the cold air at the film hole outlet; substituting the corrected outflow state parameters into subsequent steps until the absolute value of the variation of the finally obtained outer surface temperature distribution is less than or equal to the first threshold value, at which time the obtained outer surface temperature distribution and outer surface cooling efficiency distribution are heat transfer performance of the turbine blade laminate cooling structure; wherein the internal cooling is calculated by using a computational fluid dynamics method, and the convective heat transfer coefficient is obtained by performing internal-external coupling conjugate heat transfer calculation on the turbine blade laminate cooling structure.

2. The method of claim 1, wherein the method is characterized by: The analyzing the internal cooling to obtain outflow state parameters of the cold air at the film hole outlet comprises: setting a cooling inlet boundary condition of the internal cooling; calculating a flow field structure and heat transfer of the internal cooling according to the cooling inlet boundary condition of the internal cooling to obtain the outflow state parameters of the cold air at the film hole outlet.

3. The method of claim 1, wherein the method is characterized by: The simplifying the external cooling into a third type of boundary condition through the outflow state parameters, the third type of boundary condition including a convective heat transfer coefficient and an adiabatic wall temperature, comprises: performing internal-external coupling conjugate heat transfer calculation on the turbine blade laminate cooling structure to obtain the convective heat transfer coefficient; calculating adiabatic film cooling efficiency of multiple rows of the film holes according to the outflow state parameters; obtaining the adiabatic wall temperature according to the adiabatic film cooling efficiency of the multiple rows of the film holes.

4. The method of claim 3, wherein the method is characterized by: The calculating adiabatic film cooling efficiency of multiple rows of the film holes according to the outflow state parameters comprises: calculating adiabatic film cooling efficiency and adiabatic wall temperature of a single film hole according to the outflow state parameters; re-calculating adiabatic film cooling efficiency of each single film hole according to the adiabatic wall temperature of each single film hole to obtain adiabatic film cooling efficiency of multiple rows of the film holes.

5. The method of claim 4, wherein the method further comprises: The outflow state parameters include at least one of flow velocity, temperature and density.

6. The method of claim 5, wherein the method further comprises: The calculating adiabatic film cooling efficiency and adiabatic wall temperature of a single film hole according to the outflow state parameters comprises: substituting the flow velocity of the cold gas at the outlet of the film hole into the first formula to obtain the adiabatic film cooling efficiency of each of the film holes; substituting the temperature of the cold gas at the outlet of the film hole into the second formula to obtain the adiabatic wall temperature of each of the film holes; the first formula is: ， wherein, is an adiabatic film cooling effectiveness of a single film hole; is a turbulent thermal diffusivity; is a coordinate value of a cold air flow direction with the center of the film hole as an origin; is a diameter of the film hole; is a velocity of a high-temperature gas outside the turbine blade laminate cooling structure; is a lateral coordinate value of the film hole; is a lateral adiabatic film cooling effectiveness reduction distance at which the lateral adiabatic film cooling effectiveness is reduced to half of an adiabatic film cooling effectiveness of a centerline corresponding position of the film hole; is a blowing ratio, , is a density of the high-temperature gas, is a flow velocity of the high-temperature gas, is a density of the cold gas at a film hole outlet, is a flow velocity of the cold gas at the film hole outlet; the second formula is: ， wherein the is the adiabatic wall temperature of a single film hole; is the high temperature gas temperature; is the adiabatic film cooling effectiveness of a single film hole; is the temperature of the cooling gas at the exit of the film hole.

7. The method of claim 6, wherein the method further comprises: the adiabatic film cooling efficiency of each of the film holes is recalculated according to the adiabatic wall temperature of each of the film holes to obtain the adiabatic film cooling efficiency of the multiple rows of film holes, including: the adiabatic film cooling efficiency of each of the film holes is recalculated by substituting the adiabatic wall temperature of each of the film holes into the third formula; the adiabatic film cooling efficiency of the multiple rows of film holes is obtained by substituting the adiabatic film cooling efficiency of each of the film holes into the fourth formula; the third formula is: ， wherein, adiabatic film cooling effectiveness of the i-th gas film hole, adiabatic wall temperature of the i-th gas film hole, adiabatic wall temperature of the gas film hole upstream of the i-th gas film hole; the fourth formula is: ， wherein, is the adiabatic film cooling effectiveness for a plurality of rows of the film holes.

8. The method of claim 7, wherein the method further comprises: the adiabatic wall temperature is obtained according to the adiabatic film cooling efficiency of the multiple rows of film holes, including: the adiabatic wall temperature of the multiple rows of film holes is obtained by substituting the adiabatic film cooling efficiency of the multiple rows of film holes into the fifth formula; the fifth formula is: ， wherein, is the adiabatic wall temperature of the gas film hole; is the high temperature gas temperature; is the temperature of the cold gas at the gas film hole exit.

9. The method of claim 1, wherein, the outer surface temperature distribution and the outer surface cooling efficiency distribution of the turbine blade laminate are obtained by combining the third type of boundary condition and calculating the internal cooling, including: a model of the turbine blade laminate is established, and the model of the turbine blade laminate is divided into grids; the outer surface temperature and the outer surface cooling efficiency in each of the grids are calculated by using the method of computational fluid dynamics and combining the third type of boundary condition; the outer surface temperature distribution and the outer surface cooling efficiency distribution of the turbine blade laminate are obtained by integrating the outer surface temperature and the outer surface cooling efficiency in each of the grids.

Images