CN116911182A - Recommendation method for turbine blade leading edge air film cooling structure parameters - Google Patents
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Abstract
A recommendation method for turbine blade leading edge air film cooling structure parameters relates to the field of aircraft engine turbine blade design, solves the problems that the existing turbine blade leading edge air film cooling design lacks consideration of main flow RTDF inlet, and simultaneously has large single calculation amount, long iteration period, more repeatability flow, and a plurality of software involved, complicated manual operation, low overall design efficiency and the like in the design process. The method is realized by a gas RTDF inlet temperature preprocessing module, a gas film hole flow prediction module, a solid temperature calculation module, a structural parameter optimizing module and a gas RTDF inlet correction module. The invention can greatly save manpower and material resources and lighten the burden of design personnel.
Description
Technical Field
The invention relates to the field of design of turbine blades of aeroengines, in particular to a recommendation method for parameters of a turbine blade leading edge air film cooling structure.
Background
Film cooling is the most main and effective external cooling mode in the high-temperature turbine blade of the modern aero-engine, and can well protect the blade from being ablated by high-temperature gas. Therefore, in the design process of turbine blades, the design of the structure and arrangement of the air film holes is an extremely important ring. In the whole turbine blade, the working condition of the front edge is the worst, and the front edge is the part which is firstly contacted with high-temperature fuel gas to strike and is the most upstream of the whole blade, so that the air film formed by the outflow of the front edge can cause the front edge to be ablated once the air film is insufficiently cooled. However, the existing air film cooling design technology aiming at the front edge mainly considers the curvature of the blade along the flow direction and the main flow condition to carry out air film design, neglects that the gas at the inlet of the turbine blade has a radial temperature distribution coefficient (RTDF inlet) under the actual condition, namely the gas temperature is not uniform in the radial direction perpendicular to the flow direction, and therefore the air film structure of the air film is designed to be suitable for the RTDF inlet of the gas in the radial direction of the blade. Meanwhile, for the designed cooling structure, the existing design method is to perform geometric modeling on the front edge with the cooling structure based on three-dimensional modeling software (such as UG, solidWorks and the like), then perform discrete screening on the geometric model through grid division software (such as ANSYS ICEM and the like), and finally perform gas-heat coupling numerical simulation solving on the grid model through three-dimensional numerical simulation software (such as ANSYS FLUENT and CFX and the like), so that the front edge temperature under the cooling design is obtained. Because of the large structural curvature of the leading edge, the main flow is complex, and the grid quantity is required to be large enough and the quality is required to be good enough for obtaining accurate numerical simulation results. Furthermore, the design of the front edge air film cooling is difficult, the structural parameters are modified very frequently, so that geometric modeling, meshing and numerical simulation are required to be started from the beginning each time, and the flow is repeated in a large number. Summarizing, the existing turbine blade leading edge air film cooling design technology lacks consideration on the main stream RTDF inlet, and has the advantages of large single calculation amount, long iteration period, more repeated processes, and complex manual operation due to the fact that a plurality of software are involved in the design process, and therefore the overall design efficiency is low.
Therefore, how to consider the inlet characteristics of high-temperature gas RTDF when developing the gas film cooling design of turbine blades, and establish a high-efficiency and rapid design method, avoid complex and time-consuming three-dimensional numerical simulation, thereby improving the effect and efficiency of the leading edge gas film cooling design, and being a technical problem to be solved urgently.
Disclosure of Invention
The invention provides a recommendation method for parameters of a turbine blade leading edge air film cooling structure, which aims to solve the problems that the existing turbine blade leading edge air film cooling design lacks consideration of a main flow RTDF inlet, and simultaneously has large single calculation amount, long iteration period, more repeatability flow, more software, complicated manual operation, low overall design efficiency and the like in the design process.
The method is realized by a gas RTDF inlet temperature preprocessing module, a gas film hole flow prediction module, a solid temperature calculation module, a structural parameter optimizing module and a gas RTDF inlet correction module: the method comprises the following specific steps:
fitting gas inlet temperatures at different positions in the radial direction of a turbine blade by a gas RTDF inlet temperature preprocessing module to obtain a continuous radial temperature distribution function, and then obtaining a highest temperature value and a lowest temperature value and position coordinates corresponding to the highest temperature value and the lowest temperature value in the radial direction according to the radial temperature distribution function;
the air film hole flow prediction module is used for establishing a neural network model taking structural parameters and working condition parameters as input and taking cold air flow as output, so as to realize cold air flow prediction of different air film structures under different conditions;
step three, the solid temperature calculation module is used for establishing a third type boundary condition neural network prediction model of the inner and outer surfaces of the turbine blade and predicting the inner and outer boundary conditions of the blades with different air film structures; the method comprises the following steps:
taking the structural parameter, the working condition parameter and the cold air flow predicted in the second step as inputs of the prediction model, and taking the heat exchange coefficient and the heat insulation wall temperature of the third type of boundary conditions of the inner surface and the outer surface of the blade as outputs of the prediction model; then calculating a leading edge solid temperature field based on a solid heat conduction differential equation to obtain the temperature of the blade;
step four, the structural parameter optimizing module performs optimal parameter setting on each air film parameter to be designed, establishes a comprehensive merit evaluation function of the air film cooling structure based on flow heat exchange, and then performs automatic iterative optimization by adopting a genetic algorithm according to the cold air flow prediction module established in the step two and the blade temperature calculation module established in the step three, and respectively determines two groups of optimal structural parameter combinations which are smaller than the highest temperature value of the blade obtained in the step one and have the lowest cold air flow and are smaller than the lowest temperature value of the blade obtained in the step one and have the lowest cold air flow;
and fifthly, the gas RTDF inlet correction module takes the two groups of optimal structural parameters obtained in the step four as anchor points to carry out interpolation correction so as to determine the gas film structure parameter distribution of the front edge in the radial direction of the whole blade, and finally, the designed gas RTDF inlet front edge gas film cooling structure is obtained.
The invention has the beneficial effects that:
1. according to the invention, the front edge cooling design problem is disassembled into the flow heat exchange prediction problem and the structural parameter optimizing problem, and the high-calculation-amount numerical simulation process and the reciprocating manual iterative modification process in the prior art are replaced by combining a machine learning algorithm, so that the front edge air film cooling design efficiency is greatly improved.
2. The invention fully considers the problem of the turbine blade gas RTDF inlet under the actual condition, designs according to the highest temperature and the lowest temperature point respectively, and then carries out parameter interpolation correction based on the change gradient.
3. According to the invention, all functional modules are integrated through a main program, a GUI interface is developed, and a user only needs to input working condition and design indexes according to guidance and import a radial distribution value file of gas temperature. Compared with the prior art, the invention can greatly save manpower and material resources, lighten the burden of designers, get rid of the limitation of the commercial software and improve the autonomy of design tools.
Drawings
FIG. 1 is a flow chart of a method for recommending turbine blade leading edge film cooling structural parameters according to the present invention.
Detailed Description
Referring to fig. 1, the present embodiment is described as a method for recommending parameters of a gas film cooling structure at a leading edge of a turbine blade, where the recommended output of the parameters of the gas film cooling structure at the leading edge is automatically achieved by an algorithm under the conditions of known radial temperature distribution and pressure distribution of a main stream inlet, and known temperature and pressure of a cold air inlet at the leading edge of the blade. The method comprises a gas RTDF inlet temperature preprocessing module, a gas film hole flow prediction module, a solid temperature calculation module, a structural parameter optimizing module and a gas RTDF inlet correction module, wherein the whole algorithm frame is shown in figure 1:
s1, for the temperature of the gas at the inlet of the turbine blade under the actual condition, the temperature of the gas has obvious non-uniformity in the radial direction, and the gas is distributed at the two sides of the middle part, so that the temperature of the middle part of the turbine blade without a cooling structure is higher, and the temperature of the blade root and the blade top is lower. Therefore, in order to adjust the cooling structure according to different inlet conditions of the gas RTDF later, the gas inlet temperatures at different positions in the radial direction need to be fitted through the gas RTDF inlet temperature preprocessing module to obtain a continuous radial temperature distribution function, and then the highest temperature and the lowest temperature value and the positions of the highest temperature and the lowest temperature value respectively are obtained according to the radial temperature distribution function.
S2, for the front edge of the turbine blade, a basic scene is that a high-temperature main flow is arranged on the outer side of the outer wall, low-temperature cold air is introduced into the inner cavity, and the cold air is sprayed out through the air film holes and is formed on the outer surface to cover the outer surface, so that cooling is realized. Since flow determines heat transfer, the effectiveness of film cooling is directly dependent on the blended flow conditions of the cold and gas. The factors influencing the flowing state are mainly air film hole structure parameters (such as air film aperture, angle, length-diameter ratio and the like) and working condition parameters (such as pressure difference, density ratio, turbulence and the like), so that a neural network model taking the structure parameters and the working condition parameters as input and the cold air flow as output is established through the air film hole flow prediction module, and the rapid prediction of the cold air flow of different air film structures under different conditions is realized.
S3, for the front edge cooling design, the fact that the temperature of the blade cannot exceed the design index is considered, and therefore the solid temperature calculation module is required to establish a calculation model of the temperature of the blade. For the solid heat conduction problem, a definite solution exists after the boundary conditions inside and outside the solid are determined. In the air film cooling problem, the inside and the outside of the blade are third type boundary conditions, so that a third type boundary condition neural network prediction model of the inside and the outside surfaces needs to be established, the structural parameters, the working condition parameters and the cold air flow are taken as input, and the heat exchange coefficient and the heat insulation wall temperature are taken as output. And on the basis of the third type of boundary conditions, calculating the temperature of the solid based on a solid heat conduction differential equation, thereby obtaining the temperature of the blade.
S4, the structural parameter optimizing module is adopted to normalize the air film parameters to be designed and the optimizing range, a comprehensive quality evaluation criterion of the air film cooling structure based on flow heat exchange is provided, and a mathematical function frame is established to quantitatively express. And then, based on the calculation of the cold air flow and the blade temperature by the previous module and the automatic iterative optimization of the maximum temperature and the minimum temperature of the blade without cooling according to a genetic algorithm, determining and outputting the combination of the optimal structural parameters of the minimum cold air flow and the maximum temperature and the minimum temperature which are not exceeded respectively.
And S5, the function of the gas RTDF inlet correction module is to conduct interpolation correction by taking the structural parameters output by the structural parameter optimizing module at the highest temperature and the lowest temperature as anchor points to determine the gas film structural parameter distribution of the front edge in the whole radial direction, so that the design of the front edge gas film cooling structure suitable for the gas RTDF inlet is obtained. In engineering practice, the gas temperature at the inlet of the turbine blade is necessarily high in the middle and low in the two sides in the radial direction, so that the highest temperature is necessarily in the blade, the lowest temperature is necessarily in the blade top and the blade root, and the structural parameters respectively recommended according to the highest temperature and the lowest temperature are necessarily parameters in the blade, the gas film parameter distribution from the blade top to the blade root in the blade can be obtained by interpolation according to the recommended structural parameters of the highest temperature and the lowest temperature, namely the gas film structural parameters from the blade root to the blade top of the whole front edge are obtained, and the design of the gas film cooling structural parameters of the front edge suitable for the inlet of the gas RTDF is completed.
The second embodiment is a specific example of the method for recommending the turbine blade leading edge air film cooling structural parameter according to the first embodiment. In the embodiment, a gas RTDF inlet temperature preprocessing module, a gas film hole flow prediction module, a solid temperature calculation module, a structural parameter optimizing module and a gas RTDF inlet correction module are integrated through a self-programming main program, a GUI interface is developed to guide a user to input working condition conditions and guide gas radial temperature values, and the whole calculation flow is as follows:
the designer inputs parameters such as main stream and cold air temperature and pressure conditions, cold air flow design value, cold efficiency index requirement, material physical property and the like of the current turbine blade front edge air film cooling design task through a GUI interface, and introduces a temperature radial distribution value file of a high-temperature gas inlet (generally in the form of denser temperature values at different radial positions in engineering practice). The main program reads various parameters input in the GUI interface and stores the parameters in a classified mode as input parameters for optimizing and recommending a subsequent solid temperature calculation module and structural parameters; and reading an imported gas radial temperature distribution file, automatically fitting a temperature distribution function through the gas RTDF inlet temperature preprocessing module to obtain radial continuous temperature values, and obtaining the values of the highest temperature and the lowest temperature and the coordinates of the position in the radial direction.
The gas film hole flow prediction module takes the working condition input by the gas RTDF inlet temperature preprocessing module and the gas film structure parameter as input and the cold air flow as output, establishes an artificial neural network model, accumulates cold air flow values under different conditions and different structures through a numerical simulation method, and trains the neural network, so that the gas film hole flow prediction module can be directly called to rapidly predict the cold air flow during design.
In the solid temperature calculation module, the third type of boundary conditions define the heat exchange coefficient h of the object on the boundary and surrounding fluid and the fluid temperature T f Aiming at the surface of the external air film of the blade, the convective heat transfer calculation formula is as follows:
q o ＝h o (T aw -T wo ) (1)
wherein q is o Represents the heat flow of external fuel gas to heat the solid outer wall surface, h o The convection heat exchange coefficient under the condition that the air film is cooled on the outer surface of the blade is shown; t (T) aw Representing the temperature of the insulating wall without film cooling, i.e. the temperature of the fluid surrounding the outer surface, T wo Representing the solid outer wall temperature. Similarly, the calculation formula of convection heat exchange in the blade is as follows:
q i ＝h i (T c -T wi ) (2)
wherein q is i Indicating the heat flow of the cooling air with the solid inner wall facing the inside, h i Representing the convective heat transfer coefficient in the inner surface cavities of the vanes; t (T) c Indicating the temperature of the cold air, i.e. the temperature of the fluid surrounding the inner surface, T wi Representing the temperature of the solid inner wall surface.
For the inside of the blade solid, the steady-state heat conduction process satisfies the heat conduction equation:
wherein lambda is solid heat conductivity coefficient, T is temperature of each point, x, y and z are coordinates of each point in the solid domain. The boundary conditions are expressed by the above formulas (1) and (2), so that the entire front solid temperature field has a definite solution after determining the boundary conditions of the fluid and the solid.
Taking structural parameters, working condition parameters and cold air flow output by the air film hole flow prediction module as input, and the heat exchange coefficient h of the third type of boundary conditions of the inner surface and the outer surface i And h o And the temperature T of the fluid around the outer surface aw For output, constructing an artificial neural network, and accumulating different strips by a numerical simulation methodBoundary condition data under the part is trained, so that the boundary condition can be rapidly predicted by directly calling the training of the artificial neural network in design. And then the whole front edge solid temperature field can be obtained through iterative calculation according to the formula (3).
The structural parameter optimizing module firstly binary codes each parameter to be designed according to the built-in engineering in-actual air film cooling structure range, and then establishes a structural parameter evaluation function with the cold air flow as low as possible and the temperature not exceeding the standard:
T des ＝T aw -η des *(T aw -T c ) (5)
wherein F represents the merits of the structure,the cold air flow representing the structure is obtained by a prediction model of a gas film hole flow prediction module, T represents the temperature of the outer wall surface of the structure, and is calculated by a solid temperature calculation module, P is a punishment factor, and the importance of main balance flow and the outer wall temperature can be determined according to the actual requirements of different design tasks, and T aw Maximum and minimum temperatures eta of the blade surface without cooling obtained by the gas RTDF inlet temperature pretreatment module according to the fitted gas temperature radial distribution function des And the design index of the cooling effect is input for a user of the gas RTDF inlet temperature preprocessing module.
According to the structural parameters to be designed and the merit and inferiority evaluation function, iterative optimization is carried out based on a genetic algorithm, and the structural parameters are respectively subjected to T under the conditions of highest temperature and lowest temperature (namely formula (5) aw Respectively taking the highest temperature and the lowest temperature) to obtain the structural parameter combination with the highest quality value.
The gas RTDF inlet correction module firstly calculates the gradient of change between the highest temperature and the lowest temperature according to a gas temperature radial distribution function fitted in the gas RTDF inlet temperature pretreatment module, then calculates the optimal gas film cooling structure parameter combination under the highest temperature and the lowest temperature output by the structure parameter optimizing module, interpolates each structure parameter according to the calculated gradient of change between radial position coordinates corresponding to the highest temperature and the lowest temperature obtained in the gas RTDF inlet temperature pretreatment module, thereby obtaining the whole radial gas film structure parameter correction value from the blade root to the blade top, and finally outputs the front edge gas film cooling structure parameter which is suitable for the gas RTDF inlet, and the design is completed.
The technical features of the above-described embodiments may be arbitrarily combined, and all possible combinations of the technical features in the above-described embodiments are not described for brevity of description, however, as long as there is no contradiction between the combinations of the technical features, they should be considered as the scope of the description.
The above examples illustrate only a few embodiments of the invention, which are described in detail and are not to be construed as limiting the scope of the invention. It should be noted that it will be apparent to those skilled in the art that several variations and modifications can be made without departing from the spirit of the invention, which are all within the scope of the invention. Accordingly, the scope of protection of the present invention is to be determined by the appended claims.
Claims (3)
1. A recommendation method for turbine blade leading edge air film cooling structure parameters is characterized by comprising the following steps: the method is realized by a gas RTDF inlet temperature preprocessing module, a gas film hole flow prediction module, a solid temperature calculation module, a structural parameter optimizing module and a gas RTDF inlet correction module: the method comprises the following specific steps:
fitting gas inlet temperatures at different positions of a turbine blade in the radial direction by a gas RTDF inlet temperature preprocessing module to obtain a continuous radial temperature distribution function, and then obtaining a blade maximum temperature value and a blade minimum temperature value and position coordinates corresponding to the maximum temperature value and the minimum temperature value in the radial direction according to the radial temperature distribution function;
the air film hole flow prediction module is used for establishing a neural network model taking structural parameters and working condition parameters as input and taking cold air flow as output, so as to realize cold air flow prediction of different air film structures under different conditions;
step three, the solid temperature calculation module is used for establishing a third type boundary condition neural network prediction model of the inner and outer surfaces of the turbine blade and predicting the inner and outer boundary conditions of the blades with different air film structures; the method comprises the following steps:
taking the structural parameter, the working condition parameter and the cold air flow predicted in the second step as inputs of the prediction model, and taking the heat exchange coefficient and the heat insulation wall temperature of the third type of boundary conditions of the inner surface and the outer surface of the blade as outputs of the prediction model; then calculating a leading edge solid temperature field based on a solid heat conduction differential equation to obtain the temperature of the blade;
step four, the structural parameter optimizing module performs optimal parameter setting on each air film parameter to be designed, establishes a comprehensive merit evaluation function of the air film cooling structure based on flow heat exchange, and then performs automatic iterative optimization by adopting a genetic algorithm according to the cold air flow prediction module established in the step two and the blade temperature calculation module established in the step three, and respectively determines two groups of optimal structural parameter combinations which are smaller than the highest temperature value of the blade obtained in the step one and have the lowest cold air flow and are smaller than the lowest temperature value of the blade obtained in the step one and have the lowest cold air flow;
and fifthly, the gas RTDF inlet correction module takes the two groups of optimal structural parameters obtained in the step four as anchor points to carry out interpolation correction so as to determine the gas film structure parameter distribution of the front edge in the radial direction of the whole blade, and finally, the designed gas RTDF inlet front edge gas film cooling structure is obtained.
2. The method for recommending turbine blade leading edge film cooling structural parameters according to claim 1, wherein: in the third step, the heat exchange coefficient h of the object and the surrounding fluid and the fluid temperature T on the boundary defined by the third type of boundary conditions f For the surface of the air film outside the blade, the convective heat transfer calculation formula is as follows:
q o ＝h o (T aw -T wo ) (1)
wherein q is o Heat flow for heating solid outer wall surface by external fuel gas, h o The convection heat exchange coefficient is the convection heat exchange coefficient under the condition that the air film is cooled on the outer surface of the blade; t (T) aw The adiabatic wall temperature in the absence of film cooling, i.e., the fluid temperature around the outer surface; t (T) wo The temperature of the outer wall surface of the solid;
the calculation formula of the convection heat transfer inside the blade is as follows:
q i ＝h i (T c -T wi ) (2)
wherein q is i Heat flow for cooling the cold air inside the solid inner wall surface, h i Is the convection heat transfer coefficient in the inner surface cavity of the blade; t (T) c Is the cool air temperature, i.e. the temperature of the fluid around the inner surface; t (T) wi The temperature of the solid inner wall surface;
for the inside of the blade solid, the steady-state heat conduction process satisfies the heat conduction equation:
wherein lambda is solid heat conductivity coefficient, T is the temperature of each point, x, y and z are coordinates of each point in the solid domain; the boundary conditions are expressed by the formula (1) and the formula (2), and the whole front solid temperature field is finally determined after the boundary conditions of the fluid and the solid are finally determined.
3. The method for recommending turbine blade leading edge film cooling structural parameters according to claim 1, wherein: in the fourth step, the comprehensive merit evaluation function of the air film cooling structure based on the flow heat exchange is expressed as follows:
R des ＝T aw -η des *(T aw -T c ) (5)
wherein F is the merits of the structureThe value of the sum of the values,for the cold air flow of the structure, p is penalty factor, T aw Maximum and minimum temperatures, eta, of the blade surface without cooling obtained by the gas RTDF inlet temperature pretreatment module according to a fitted gas temperature radial distribution function des And designing indexes for the cooling effect input by a user in the gas RTDF inlet temperature preprocessing module.
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