CN116384005A - Method and device for determining aerodynamic performance of deformed blade and electronic equipment - Google Patents
Method and device for determining aerodynamic performance of deformed blade and electronic equipment Download PDFInfo
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Abstract
The disclosure provides a method and a device for determining aerodynamic performance of a deformed blade, and electronic equipment, wherein the method comprises the following steps: obtaining a target blade geometrical parameter of the deformed blade; inputting the geometric parameters of the target blade into a force source item volumetric force prediction model to obtain a characteristic curve of the volumetric force of the target distributed force source item; simulating the flow field characteristics of the deformed blade by taking the characteristic curve of the volume force of the target distributed force source item as a known condition to obtain target flow field information of the deformed blade; the aerodynamic performance of the deformed blade is determined based on the target flow field information of the deformed blade. The method provided by the disclosure can realize the rapid prediction of the aerodynamic performance of the deformed blade while guaranteeing the spatial resolution of the flow field, and provides a reference for the optimization design of the blade profile of the deformed blade, thereby improving the design efficiency of the deformed blade.
Description
Technical Field
The disclosure relates to the technical field of computers, and in particular relates to a method and a device for determining aerodynamic performance of a deformed blade and electronic equipment.
Background
The compressor is one of the core components of an aeroengine and plays a decisive role in the performance and stability of the engine. In the working process of the compressor in a wide working condition range, the blades deform to different degrees, and the aerodynamic performance of the blades is changed, so that the acquisition of the aerodynamic performance of the deformed blades is very important to the optimal design of the blades.
In the related art, the aerodynamic performance of the blade can be simulated by a conventional computational fluid dynamics (Computational Fluid Dynamics, abbreviated as CFD), but the simulation scale is increased due to the rotation of the blade, and meanwhile, the number of to-be-simulated examples is greatly increased due to the remarkable increase of the degree of freedom of deformation, so that the conventional CFD technology has huge workload and takes a long time, and the aerodynamic performance change generated by the rapid simulation of the deformation is difficult to realize. On the basis, the existing blade pneumatic performance rapid prediction tool mainly comprises a through-flow program and a volume force, wherein the through-flow program and the volume force are two types, the problem of low spatial resolution exists in the former, the problem that the pneumatic performance of the deformed blade cannot be predicted rapidly exists in the latter, and the requirement of the pneumatic performance of the deformed blade cannot be met.
Disclosure of Invention
According to an aspect of the present disclosure, there is provided a method for determining aerodynamic performance of a deformed blade, including:
obtaining a target blade geometrical parameter of the deformed blade;
inputting the geometric parameters of the target blade into a force source item volumetric force prediction model to obtain a characteristic curve of the volumetric force of the target distributed force source item;
simulating the flow field characteristics of the deformed blade by taking the characteristic curve of the volume force of the target distributed force source item as a known condition to obtain target flow field information of the deformed blade;
The aerodynamic performance of the deformed blade is determined based on the target flow field information of the deformed blade.
According to another aspect of the present disclosure, there is provided a determining apparatus of aerodynamic performance of a deformed blade, including:
the acquisition module is used for acquiring the geometric parameters of the target blade of the deformed blade;
the acquisition module is also used for inputting the geometric parameters of the target blade into the force source item volumetric force prediction model to acquire a characteristic curve of the target distributed force source item volumetric force;
the acquisition module is also used for simulating the flow field characteristics of the deformed blade by taking the characteristic curve of the volume force of the target distributed force source item as a known condition to acquire target flow field information of the deformed blade;
and the determining module is used for determining the aerodynamic performance of the deformed blade based on the target flow field information of the deformed blade.
According to another aspect of the present disclosure, there is provided an electronic device including:
a processor; the method comprises the steps of,
a memory storing a program;
wherein the program comprises instructions which, when executed by a processor, cause the processor to perform a method according to an exemplary embodiment of the present disclosure.
According to another aspect of the present disclosure, there is provided a non-transitory computer-readable storage medium storing computer instructions for causing a computer to perform a method according to an exemplary embodiment of the present disclosure.
According to one or more technical schemes provided by the exemplary embodiments of the present disclosure, a target blade geometry parameter of a deformed blade may be obtained, the target blade geometry parameter is input into a force source item volumetric force prediction model, and a characteristic curve of a target distributed force source item volumetric force is obtained; then, taking a characteristic curve of the volume force of the target distributed force source item as a known condition, simulating the flow field characteristics of the deformed blade to obtain target flow field information of the deformed blade; the aerodynamic performance of the deformed blade is determined based on the target flow field information of the deformed blade. Therefore, the method of the exemplary embodiment of the present disclosure can determine the aerodynamic performance of the deformed blade corresponding to the geometric parameter of the target blade by using the volume force of the target distributed force source item, so as to implement rapid prediction of the aerodynamic performance of the deformed blade, and provide a reference for the optimization design of the blade profile of the deformed blade, thereby improving the design efficiency of the deformed blade; meanwhile, as the target distributed force source item volume force is a three-dimensional volume force, the spatial resolution of the target flow field information of the deformed blade determined based on the target distributed force source item volume force is ensured, and the problem that the flow field result has low spatial resolution due to flow sequence calculation in the prior art is avoided.
Drawings
Further details, features and advantages of the present disclosure are disclosed in the following description of exemplary embodiments, with reference to the following drawings, wherein:
FIG. 1 illustrates a flow chart of a method of determining aerodynamic performance of a deformed blade according to an exemplary embodiment of the present disclosure;
FIG. 2A illustrates a schematic view of a deformed blade of an exemplary embodiment of the present disclosure;
FIG. 2B illustrates an exemplary schematic view of a blade height section contained by a deformed blade according to an exemplary embodiment of the present disclosure;
fig. 3 illustrates a flow chart of acquisition of target flow field information in an exemplary embodiment of the present disclosure;
FIG. 4 illustrates a block schematic diagram of a determination device of aerodynamic performance of a deformed blade according to an exemplary embodiment of the present disclosure;
FIG. 5 shows a schematic block diagram of a chip of an exemplary embodiment of the present disclosure;
fig. 6 illustrates a block diagram of an exemplary electronic device that can be used to implement embodiments of the present disclosure.
Detailed Description
Embodiments of the present disclosure will be described in more detail below with reference to the accompanying drawings. While certain embodiments of the present disclosure have been shown in the accompanying drawings, it is to be understood that the present disclosure may be embodied in various forms and should not be construed as limited to the embodiments set forth herein, but are provided to provide a more thorough and complete understanding of the present disclosure. It should be understood that the drawings and embodiments of the present disclosure are for illustration purposes only and are not intended to limit the scope of the present disclosure.
It should be understood that the various steps recited in the method embodiments of the present disclosure may be performed in a different order and/or performed in parallel. Furthermore, method embodiments may include additional steps and/or omit performing the illustrated steps. The scope of the present disclosure is not limited in this respect.
The term "including" and variations thereof as used herein are intended to be open-ended, i.e., including, but not limited to. The term "based on" is based at least in part on. The term "one embodiment" means "at least one embodiment"; the term "another embodiment" means "at least one additional embodiment"; the term "some embodiments" means "at least some embodiments. Related definitions of other terms will be given in the description below. It should be noted that the terms "first," "second," and the like in this disclosure are merely used to distinguish between different devices, modules, or units and are not used to define an order or interdependence of functions performed by the devices, modules, or units.
It should be noted that references to "one", "a plurality" and "a plurality" in this disclosure are intended to be illustrative rather than limiting, and those of ordinary skill in the art will appreciate that "one or more" is intended to be understood as "one or more" unless the context clearly indicates otherwise.
The names of messages or information interacted between the various devices in the embodiments of the present disclosure are for illustrative purposes only and are not intended to limit the scope of such messages or information.
Before describing embodiments of the present disclosure, the following definitions are first provided for the relative terms involved in the embodiments of the present disclosure:
computational fluid dynamics (Computational Fluid Dynamics, abbreviated as CFD) is an emerging intersection subject of mutual fusion of fluid mechanics and computer science, and is based on a calculation method, and the approximate solution of a fluid control equation is obtained by using the rapid calculation capability of a computer.
Latin hypercube sampling (Latin hypercube sampling, abbreviated LHS) is a method of approximately random sampling from a multivariate parameter distribution, belongs to a hierarchical sampling technique, and is commonly used in computer experiments or Monte Carlo integration, etc. The Latin hypercube sampling method can ensure the full coverage of each variable range by maximally distributing and layering each edge, and realize the efficient sampling in the variable distribution interval.
In the related art, the conventional technology such as the static blade adjustable technology is difficult to support the requirements of synchronous adjustment of the future full speed domain large flow, the bypass ratio/supercharging ratio and the like of the aeroengine. For this bottleneck, the concept of a controllably deforming fan is proposed. The concept fundamentally breaks through the restriction that the pneumatic geometrical shape of the blade is not adjustable, can realize the decoupling adjustment of the circulation capacity and the supercharging capacity, and further improves the limit capacity of pneumatic matching adjustment. The aerodynamic performance of the deformable blade is an important reference in the optimal design of the deformable blade.
At present, the aerodynamic performance of the blade is simulated by a conventional computational fluid dynamics (Computational Fluid Dynamics, abbreviated as CFD), but the simulation scale is increased due to the rotation of the blade, and meanwhile, the number of to-be-simulated examples is greatly increased due to the remarkably increased degree of freedom of deformation, so that the conventional CFD technology has huge workload and takes a long time, and the aerodynamic performance change generated by rapid simulation of the deformation is difficult to realize.
On the basis, the existing blade aerodynamic performance rapid prediction tool mainly comprises a through-flow program and a volume force, wherein the two-dimensional volume force is adopted in calculation, so that a flow field calculation result has the problem of low spatial resolution, and the problem that the flow field calculation result cannot be suitable for deformed blades is solved, and the requirement of rapid prediction of the aerodynamic performance of the deformed blades cannot be met.
In view of the above problems, the exemplary embodiments of the present disclosure provide a method for determining aerodynamic performance of a deformed blade, which may determine aerodynamic performance of a deformed blade corresponding to a target blade geometry parameter by using a target distributed force source item volumetric force, and implement rapid prediction of aerodynamic performance of the deformed blade while guaranteeing spatial resolution of a flow field, thereby providing a reference for optimization design of a blade profile of the deformed blade, and improving design efficiency of the deformed blade.
The method of determining blade deformation simulation parameters of exemplary embodiments of the present disclosure may be performed by an electronic device having one or more modeling software installed, which may be stored in a computer readable storage medium, including but not limited to: UG, CAD, SPCS, PKPM-PC, revit, navisworks, bentley Navigator, tekla Structures and ArchiCAD, etc. The electronic device may include, but is not limited to, a desktop computer, a notebook computer, a tablet computer, and the like.
FIG. 1 illustrates a flow chart of a method of determining aerodynamic performance of a deformed blade according to an exemplary embodiment of the present disclosure. As shown in fig. 1, a method for determining aerodynamic performance of a deformed blade according to an exemplary embodiment of the present disclosure may include:
step 101: and obtaining the target blade geometric parameters of the deformed blade.
It will be appreciated that the target blade geometry described above may be used to determine a target deformation for a deformed blade. The target blade geometry of the deformed blade may include the geometry and position parameters of the plurality of blade high sections contained by the deformed blade. Wherein, for each high section of the blade, the geometric parameter can determine the shape of the high section of the blade, and the position parameter can determine the position of the high section of the blade in the deformed blade.
For example, the geometric parameters of each of the lobe high sections in exemplary embodiments of the present disclosure may include a camber line parameter of the lobe high section and a thickness parameter of the lobe high section, and the position parameter of each of the lobe high sections may include coordinates of a geometric center of the lobe high section determined based on the geometric parameters of the lobe high section.
Fig. 2A shows a schematic view of a deformed blade of an exemplary embodiment of the present disclosure. As shown in FIG. 2A, the deformed blade 200 includes a plurality of blade height sections 210. FIG. 2B illustrates an exemplary schematic view of a blade height section contained by a deformed blade according to an exemplary embodiment of the present disclosure. As shown in fig. 2B, exemplary embodiments of the present disclosure may determine a mean camber line of each high-leaf section 210 by using a polynomial fitting method, a mean camber line parameter of the high-leaf section 210 may be a polynomial coefficient corresponding to the mean camber line of the high-leaf section 210, and a thickness parameter of the high-leaf section may be a set of thicknesses of the deformed blade at various points on the mean camber line along a direction perpendicular to the mean camber line; meanwhile, the position parameter of the high-leaf cross section 210 may be coordinates of a centroid of a mean camber line of the high-leaf cross section 210. Based on this, exemplary embodiments of the present disclosure may also fit a curve to the line of the centroids of the individual blade high sections contained in deformed blade 200, resulting in parametric modeling of deformed blade 200.
As can be seen, exemplary embodiments of the present disclosure may parameterize a target deformation produced by a deformed blade with target blade geometry such that the deformed blade may be simulated to produce a corresponding deformation by adjusting the target blade geometry.
Step 102: and inputting the geometric parameters of the target blade into a force source item volumetric force prediction model to obtain a characteristic curve of the target distributed force source item volumetric force.
The force source term volumetric force prediction model may be a neural network model after training according to an exemplary embodiment of the disclosure, and a characteristic curve of a target distributed force source term volumetric force corresponding to a target blade geometric parameter may be determined based on the force source term volumetric force prediction model. The characteristic curve of the target distributed force source item volume force is substantially a characteristic curve fitted by the distributed force sources Xiang Tiji force in a plurality of deformation states, and the characteristic curve can reflect the change rule of the distributed force source item volume force of the compressor in a normal working range.
The characteristic curve of the target distributed force source term volumetric force may be a characteristic curve of the distributed force source term volumetric force of each blade high section. The distributed force source Xiang Tiji force for any deformation state on the characteristic curve, which is essentially a volumetric force distributed in three dimensions, may include volumetric forces in the axial direction, volumetric forces in the circumferential direction, and volumetric forces in the radial direction. On the basis, in the method of the exemplary embodiment of the disclosure, because the target distributed force source item volume force is a three-dimensional volume force, when the target flow field information of the deformed blade is determined based on the target distributed force source item volume force, the obtained target flow field information has higher spatial resolution, and the problem that in the prior art, the flow field calculation result has low spatial resolution due to the adoption of a two-dimensional control equation in calculation is solved.
Step 103: and simulating the flow field characteristics of the deformed blade by taking the characteristic curve of the volume force of the target distributed force source item as a known condition to obtain the target flow field information of the deformed blade.
It should be appreciated that the target flow field information described above may include stably converging flow field information obtained by the deformed blade after the target deformation has been generated. According to the exemplary embodiment of the disclosure, the target distributed force source Xiang Tiji force in a plurality of deformation states can be selected from the characteristic curves of the target distributed force source volume force, and the flow field characteristics of the deformed blade are simulated based on the target distributed force source Xiang Tiji force in the plurality of deformation states to obtain the target flow field information of the deformed blade.
Step 104: the aerodynamic performance of the deformed blade is determined based on the flow field information of the deformed blade.
The aerodynamic properties of the deformable vanes may include one or more of boost ratio, efficiency, and flow rate. According to the method and the device for determining the aerodynamic performance of the deformed blade, the relevant parameters of the aerodynamic performance to be determined can be extracted from the flow field information of the deformed blade, and the extracted relevant parameters of the aerodynamic performance to be determined are substituted into corresponding calculation formulas, so that the aerodynamic performance of the corresponding deformed blade can be obtained. Determining aerodynamic performance of the deformed blade based on flow field information of the deformed blade is a conventional calculation means in the art, and a calculation formula is a conventional calculation formula in the art, and is not described herein.
Therefore, the method of the exemplary embodiment of the present disclosure can determine the aerodynamic performance of the deformed blade corresponding to the geometric parameter of the target blade by using the volume force of the target distributed force source item, so as to implement rapid prediction of the aerodynamic performance of the deformed blade, and provide a reference for the optimization design of the blade profile of the deformed blade, thereby improving the design efficiency of the deformed blade; meanwhile, as the target distributed force source item volume force is a three-dimensional volume force, the spatial resolution of the target flow field information of the deformed blade determined based on the target distributed force source item volume force is ensured, and the problem that the flow field result has low spatial resolution due to flow sequence calculation in the prior art is avoided.
In an alternative manner, the training sample of the force source item volumetric force prediction model of the exemplary embodiments of the present disclosure during the training phase may include: a plurality of blade geometric parameters of the deformed blade in different deformation states and corresponding distributed force source item volume forces.
Exemplary embodiments of the present disclosure may determine a plurality of blade geometry parameters for a deformed blade at different deformation states based on a hierarchical sampling method. The layered sampling method can sample from the distribution interval of the independent variables, so that the obtained geometric parameters of the blade can ensure the full coverage of each variable range, and the sampling efficiency of the geometric parameters of the blade is improved. The hierarchical sampling method may be a Latin hypercube sampling method (English: latin hypercube sampling, abbreviated as LHS), which is a method of approximately random sampling from a multivariate parameter distribution, and is commonly used in computer experiments or Monte Carlo integration, etc.
The method of determining the force of the distributed force source Xiang Tiji of the exemplary embodiments of the present disclosure may include: determining flow field information corresponding to the geometric parameters of the corresponding blades by utilizing a Reynolds average NS equation; and determining a characteristic curve of the volume force of the distributed force source item corresponding to the blade geometric parameters based on the flow field information. That is, according to the exemplary embodiment of the disclosure, after the blade geometric parameters of the deformed blade are determined, the blade geometric parameters can be substituted into the reynolds average NS equation to solve, so as to obtain flow field information corresponding to the corresponding blade geometric parameters; and then determining a characteristic curve of the volume force of the distributed force source item corresponding to the geometrical parameters of the corresponding blade based on the flow field information.
Based on the above, according to the exemplary embodiment of the disclosure, the plurality of blade geometric parameters of the deformed blade in different deformation states and the corresponding distributed force source item volume force are used as training samples, so that the force source item volume force prediction model obtained through training can directly determine the characteristic curve of the corresponding target distributed force source item volume force based on the target blade geometric parameters in the reasoning stage, and the steady Reynolds average calculation is prevented from being performed again after the blade geometric parameters are changed, thereby improving the acquisition efficiency of the characteristic curve of the target distributed force source item volume force.
In an alternative manner, the model architecture of the force source item volumetric force prediction model of the exemplary embodiments of the present disclosure may include an input layer, an hidden layer, and an output layer. The input layer is used for acquiring a plurality of blade geometric parameters of the input deformed blade in different deformation states; the hidden layer is used for extracting feature vectors based on a plurality of blade geometric parameters of different deformation states; the output layer outputs characteristic curves of the volume force of the distributed force source items corresponding to the geometric parameters of the blades in different deformation states.
The number of the hidden layers is multiple, each hidden layer can comprise an activation function, and the activation function is used for enhancing the nonlinear relation between the geometric parameters of the blade and the corresponding volume force of the distributed force source item, so that the force source item volume force prediction model obtained after training has the capability of predicting complex problems. The activation function may comprise one of a sigmod function, a hyperbolic tangent activation function, and the like. It should be noted that the specific number of hidden layers, the number of nodes of each layer of neurons, and the specific form of the activation function may be adjusted by using the super parameters in the actual use situation, so as to obtain a good fitting effect.
In an alternative manner, fig. 3 illustrates a flow chart of acquisition of target flow field information in an exemplary embodiment of the present disclosure. As shown in fig. 3, in the method according to the exemplary embodiment of the present disclosure, with a characteristic curve of a volumetric force of a target distributed force source term as a known condition, flow field characteristics of a deformed blade are simulated, and target flow field information of the deformed blade is obtained, which may include:
Step 301: and determining the target distributed force source term volumetric force based on the characteristic curve of the target distributed force source term volumetric force.
According to the exemplary embodiment of the disclosure, the target distributed force source Xiang Tiji force corresponding to the deformed blade in a certain deformation state can be determined from the characteristic curve of the target distributed force source item volumetric force based on initial flow field information, and the initial flow field information can be determined according to the local flow field information of the computing unit. The target distributed force sourceThe term volume force can be applied by F body Representing the volume force of the target distributed force source item along the equal axial direction by F body,z Representing the volume force of the target distributed force source item along the circumferential direction by F body,θ Representing the volumetric force of the target distributed force source item along the radial direction by F body,r And (3) representing. Wherein F is body,z 、F body,θ And F body,r The calculation formulas of (a) are respectively as follows:
wherein p is the pressure, ρ is the average density, r is the radius, z is the axial coordinate,
for the axial average speed>
Is the circumferential average speed +.>
For radial average speed, λ is the blade blockage factor, +.>
Represents the pressure after circumferential averaging.
In practical application, the exemplary embodiment of the disclosure may adopt a user-defined function module (User Defined Function, abbreviated as UDF) of the Fluent software to compile, and introduce the value of the target distributed force source item volume force in the characteristic curve of the target distributed force source item volume force determined by the force source item volume force prediction model into the Fluent software.
Step 302: inputting the volume force of the target distributed force source item into a blade flow field control equation to solve, and obtaining flow field information of the deformed blade.
The blade flow field control equation solving process can be carried out by adopting fluid mechanics commercial software Fluent, solving is carried out under an absolute coordinate system in the calculating process, the calculating grid is a Cartesian orthogonal grid, the inlet condition is given total temperature total pressure, the axial air inlet condition is given static pressure, and the outlet condition is given static pressure.
By way of example, the vane flow field control equations of the exemplary embodiments of the present disclosure may include euler equations, which may take the form of cylindrical coordinates, as shown in the following equation:
wherein F is body,z For the volume force of the target distributed force source item volume force along the equal axial direction, F body,θ A volume force along the circumferential direction for the volume force of the target distributed force source item, F body,r The radial volume force of the target distributed force source item is represented by phi, the control energy source item is represented by t, t is represented by time, r is represented by radius, lambda is represented by a blade blocking coefficient, p is represented by pressure, ρ is represented by density, and V Z For axial speed, V θ For circumferential velocity, V r The radial velocity, h is the total enthalpy and e is the internal energy.
The flow field information of the deformed blade determined based on the solution of the blade flow field control equation can comprise p as pressure, ρ as density and V Z For axial speed, V θ For circumferential velocity, V r The radial velocity, h is the total enthalpy and e is the internal energy.
Step 303: judging whether the flow field information of the deformed blade meets the iteration termination condition.
The iteration termination condition may include that a global residual of flow field information of the deformed blade obtained by two adjacent iterations is smaller than or equal to a preset threshold. If the flow field information of the deformed blade meets the iteration termination condition, the flow field information of the deformed blade obtained at present is proved to be converged stably, and at this time, step 304 is executed; if the flow field information of the deformed blade does not meet the iteration termination condition, it indicates that the flow field information of the deformed blade obtained currently has not been converged stably, and at this time, step 305 is performed.
Step 304: if the flow field information of the deformed blade meets the iteration termination condition, determining the target flow field information of the deformed blade as the flow field information of the deformed blade.
If the flow field information of the deformed blade meets the iteration termination condition, the flow field information of the deformed blade obtained at present is proved to be stable and converged, and at the moment, the target flow field information of the deformed blade is determined to be the flow field information of the deformed blade.
Step 305: and if the flow field information of the deformed blade does not meet the iteration termination condition, re-determining the target distributed force source term volumetric force from the characteristic curve of the target distributed force source term volumetric force based on the flow field information of the deformed blade.
If the flow field information of the deformed blade does not meet the iteration termination condition, the flow field information of the deformed blade obtained at present is not stably converged, at this time, the target distributed force source Xiang Tiji force is redetermined from the characteristic curve of the target distributed force source term volumetric force based on the flow field information of the deformed blade, and then the next iteration is executed.
Therefore, the method of the exemplary embodiment of the disclosure can select the target distributed force source Xiang Tiji forces in a plurality of deformation states from the characteristic curves of the target distributed force source item volumetric force determined by the force source item volumetric force prediction model to substitute the target distributed force source Xiang Tiji forces into the blade flow field control equation for iterative solution, simulate the flow field characteristics of the deformed blade, and thus obtain stably converged target flow field information, so as to determine the aerodynamic performance of the deformed blade based on the target flow field information, realize rapid prediction of the aerodynamic performance of the deformed blade, provide references for optimization design of the blade profile of the deformed blade, and improve the design efficiency of the deformed blade.
According to one or more technical schemes provided by the exemplary embodiments of the present disclosure, a target blade geometry parameter of a deformed blade may be obtained, the target blade geometry parameter is input into a force source item volumetric force prediction model, and a characteristic curve of a target distributed force source item volumetric force is obtained; then, taking a characteristic curve of the volume force of the target distributed force source item as a known condition, simulating the flow field characteristics of the deformed blade to obtain target flow field information of the deformed blade; the aerodynamic performance of the deformed blade is determined based on the target flow field information of the deformed blade. Therefore, the method of the exemplary embodiment of the present disclosure can determine the aerodynamic performance of the deformed blade corresponding to the geometric parameter of the target blade by using the volume force of the target distributed force source item, so as to implement rapid prediction of the aerodynamic performance of the deformed blade, and provide a reference for the optimization design of the blade profile of the deformed blade, thereby improving the design efficiency of the deformed blade; meanwhile, as the target distributed force source item volume force is a three-dimensional volume force, the spatial resolution of the target flow field information of the deformed blade determined based on the target distributed force source item volume force is ensured, and the problem that the flow field result has low spatial resolution due to flow sequence calculation in the prior art is avoided.
The foregoing has been mainly presented in terms of the teachings of the presently disclosed embodiments. It will be appreciated that, in order to achieve the above-described functions, the electronic device includes corresponding hardware structures and/or software modules that perform the respective functions. Those of skill in the art will readily appreciate that the various illustrative elements and algorithm steps described in connection with the embodiments disclosed herein may be implemented as hardware or combinations of hardware and computer software. Whether a function is implemented as hardware or computer software driven hardware depends upon the particular application and design constraints imposed on the solution. Skilled artisans may implement the described functionality in varying ways for each particular application, but such implementation decisions should not be interpreted as causing a departure from the scope of the present disclosure.
The embodiment of the disclosure may divide the functional units of the electronic device according to the above method example, for example, each functional module may be divided corresponding to each function, or two or more functions may be integrated into one processing module. The integrated modules may be implemented in hardware or in software functional modules. It should be noted that, in the embodiment of the present disclosure, the division of the modules is merely a logic function division, and other division manners may be implemented in actual practice.
In the case of dividing each functional module by corresponding each function, exemplary embodiments of the present disclosure provide a determination apparatus of a blade deformation simulation parameter, which may be an electronic device or a chip applied to the electronic device. FIG. 4 illustrates a block schematic diagram of a determination device of aerodynamic performance of a deformed blade according to an exemplary embodiment of the present disclosure. As shown in fig. 4, the apparatus 400 includes:
an acquisition module 401 for acquiring target blade geometry parameters of the deformed blade;
the obtaining module 401 is further configured to input the geometric parameter of the target blade into a force source term volumetric force prediction model, and obtain a characteristic curve of the volumetric force of the target distributed force source term;
the obtaining module 401 is further configured to simulate flow field characteristics of the deformed blade with a characteristic curve of a volumetric force of a target distributed force source term as a known condition, so as to obtain target flow field information of the deformed blade;
a determination module 402 is configured to determine aerodynamic properties of the deformed blade based on the target flow field information of the deformed blade.
As one possible implementation, the target blade geometry of the deformed blade includes geometry and position parameters of a plurality of blade high sections contained in the deformed blade.
As one possible implementation, the geometric parameters of each blade height section include a camber line parameter of the blade height section and a thickness parameter of the blade height section.
As a possible implementation, the characteristic curve of the target distributed force source term volumetric force is a characteristic curve of the distributed force source term volumetric force of each blade high section.
As one possible implementation, the obtaining module 401 is further configured to determine the target distributed force source Xiang Tiji force based on a characteristic curve of the target distributed force source term volumetric force; inputting the volume force of the target distributed force source item into a blade flow field control equation to solve, and obtaining flow field information of the deformed blade; if the flow field information of the deformed blade meets the iteration termination condition, determining that the target flow field information of the deformed blade is the flow field information of the deformed blade; otherwise, the target distributed force source term volumetric force is redetermined from the characteristic curve of the target distributed force source term volumetric force based on the flow field information of the deformed blade.
As one possible implementation manner, the iteration termination condition includes that the global residual of the flow field information of the deformed blade obtained by two adjacent iterations is smaller than or equal to a preset threshold.
As one possible implementation, the vane flow field control equation includes the euler equation.
As one possible implementation manner, the training sample of the force source item volumetric force prediction model in the training phase includes: and the characteristic curves of the volume force of the corresponding distributed force source items and the geometric parameters of the plurality of blades of the deformed blade in different deformation states.
As a possible implementation manner, the obtaining module 401 is further configured to determine flow field information corresponding to the geometric parameters of the respective blades by using a reynolds average NS equation; and determining a characteristic curve of the volume force of the distributed force source item corresponding to the blade geometric parameters based on the flow field information.
Fig. 5 shows a schematic block diagram of a chip of an exemplary embodiment of the present disclosure. As shown in fig. 5, the chip 500 includes one or more (including two) processors 501 and a communication interface 502. The communication interface 502 may support a server to perform the data transceiving steps of the method described above, and the processor 501 may support the server to perform the data processing steps of the method described above.
Optionally, as shown in fig. 5, the chip 500 further includes a memory 503, where the memory 503 may include a read-only memory and a random access memory, and provides operating instructions and data to the processor. A portion of the memory may also include non-volatile random access memory (non-volatile random access memory, NVRAM).
In some embodiments, as shown in fig. 5, the processor 501 performs the corresponding operation by invoking a memory-stored operating instruction (which may be stored in an operating system). The processor 501 controls the processing operations of any one of the terminal devices, and may also be referred to as a central processing unit (central processing unit, CPU). Memory 503 may include read only memory and random access memory and provides instructions and data to processor 501. A portion of the memory 503 may also include NVRAM. Such as a memory, a communication interface, and a memory coupled together by a bus system that may include a power bus, a control bus, a status signal bus, etc., in addition to a data bus. But for clarity of illustration, the various buses are labeled as bus system 504 in fig. 5.
The method disclosed by the embodiment of the disclosure can be applied to a processor or implemented by the processor. The processor may be an integrated circuit chip having signal processing capabilities. In implementation, the steps of the above method may be performed by integrated logic circuits of hardware in a processor or by instructions in the form of software. The processor may be a general purpose processor, a digital signal processor (digital signal processing, DSP), an ASIC, an off-the-shelf programmable gate array (field-programmable gate array, FPGA) or other programmable logic device, discrete gate or transistor logic device, discrete hardware components. The various methods, steps and logic blocks of the disclosure in the embodiments of the disclosure may be implemented or performed. A general purpose processor may be a microprocessor or the processor may be any conventional processor or the like. The steps of a method disclosed in connection with the embodiments of the present disclosure may be embodied directly in hardware, in a decoded processor, or in a combination of hardware and software modules in a decoded processor. The software modules may be located in a random access memory, flash memory, read only memory, programmable read only memory, or electrically erasable programmable memory, registers, etc. as well known in the art. The storage medium is located in a memory, and the processor reads the information in the memory and, in combination with its hardware, performs the steps of the above method.
The exemplary embodiments of the present disclosure also provide an electronic device including: at least one processor; and a memory communicatively coupled to the at least one processor. The memory stores a computer program executable by the at least one processor for causing the electronic device to perform a method according to embodiments of the present disclosure when executed by the at least one processor.
The present disclosure also provides a non-transitory computer-readable storage medium storing a computer program, wherein the computer program, when executed by a processor of a computer, is for causing the computer to perform a method according to an embodiment of the present disclosure.
The present disclosure also provides a computer program product comprising a computer program, wherein the computer program, when executed by a processor of a computer, is for causing the computer to perform a method according to embodiments of the disclosure.
Referring to fig. 6, a block diagram of an electronic device 600 that may be a server or a client of the present disclosure, which is an example of a hardware device that may be applied to aspects of the present disclosure, will now be described. Electronic devices are intended to represent various forms of digital electronic computer devices, such as laptops, desktops, workstations, personal digital assistants, servers, blade servers, mainframes, and other suitable computers. The electronic device may also represent various forms of mobile devices, such as personal digital processing, cellular telephones, smartphones, wearable devices, and other similar computing devices. The components shown herein, their connections and relationships, and their functions, are meant to be exemplary only, and are not meant to limit implementations of the disclosure described and/or claimed herein.
As shown in fig. 6, the electronic device 600 includes a computing unit 601 that can perform various appropriate actions and processes according to a computer program stored in a Read Only Memory (ROM) 602 or a computer program loaded from a storage unit 608 into a Random Access Memory (RAM) 603. In the RAM 603, various programs and data required for the operation of the device 600 may also be stored. The computing unit 601, ROM 602, and RAM 603 are connected to each other by a bus 604. An input/output (I/O) interface 605 is also connected to bus 604.
A number of components in the electronic device 600 are connected to the I/O interface 605, including: an input unit 606, an output unit 607, a storage unit 606, and a communication unit 609. The input unit 606 may be any type of device capable of inputting information to the electronic device 600, and the input unit 606 may receive input numeric or character information and generate key signal inputs related to user settings and/or function controls of the electronic device. The output unit 607 may be any type of device capable of presenting information and may include, but is not limited to, a display, speakers, video/audio output terminals, vibrators, and/or printers. Storage unit 608 may include, but is not limited to, magnetic disks, optical disks. The communication unit 609 allows the electronic device 600 to exchange information/data with other devices through a computer network, such as the internet, and/or various telecommunications networks, and may include, but is not limited to, modems, network cards, infrared communication devices, wireless communication transceivers and/or chipsets, such as bluetooth (TM) devices, wiFi devices, wiMax devices, cellular communication devices, and/or the like.
As shown in fig. 6, the computing unit 601 may be a variety of general and/or special purpose processing components having processing and computing capabilities. Some examples of computing unit 601 include, but are not limited to, a Central Processing Unit (CPU), a Graphics Processing Unit (GPU), various specialized Artificial Intelligence (AI) computing chips, various computing units running machine learning model algorithms, a Digital Signal Processor (DSP), and any suitable processor, controller, microcontroller, etc. The computing unit 601 performs the various methods and processes described above. For example, in some embodiments, the methods of the exemplary embodiments of the present disclosure may be implemented as a computer software program tangibly embodied on a machine-readable medium, such as storage unit 608. In some embodiments, part or all of the computer program may be loaded and/or installed onto the electronic device 600 via the ROM 602 and/or the communication unit 609. In some embodiments, the computing unit 601 may be configured to perform the method by any other suitable means (e.g., by means of firmware).
Program code for carrying out methods of the present disclosure may be written in any combination of one or more programming languages. These program code may be provided to a processor or controller of a general purpose computer, special purpose computer, or other programmable data processing apparatus such that the program code, when executed by the processor or controller, causes the functions/operations specified in the flowchart and/or block diagram to be implemented. The program code may execute entirely on the machine, partly on the machine, as a stand-alone software package, partly on the machine and partly on a remote machine or entirely on the remote machine or server.
In the context of this disclosure, a machine-readable medium may be a tangible medium that can contain, or store a program for use by or in connection with an instruction execution system, apparatus, or device. The machine-readable medium may be a machine-readable signal medium or a machine-readable storage medium. The machine-readable medium may include, but is not limited to, an electronic, magnetic, optical, electromagnetic, infrared, or semiconductor system, apparatus, or device, or any suitable combination of the foregoing. More specific examples of a machine-readable storage medium would include an electrical connection based on one or more wires, a portable computer diskette, a hard disk, a Random Access Memory (RAM), a read-only memory (ROM), an erasable programmable read-only memory (EPROM or flash memory), an optical fiber, a portable compact disc read-only memory (CD-ROM), an optical storage device, a magnetic storage device, or any suitable combination of the foregoing.
As used in this disclosure, the terms "machine-readable medium" and "computer-readable medium" refer to any computer program product, apparatus, and/or device (e.g., magnetic discs, optical disks, memory, programmable Logic Devices (PLDs)) used to provide machine instructions and/or data to a programmable processor, including a machine-readable medium that receives machine instructions as a machine-readable signal. The term "machine-readable signal" refers to any signal used to provide machine instructions and/or data to a programmable processor.
To provide for interaction with a user, the systems and techniques described here can be implemented on a computer having: a display device (e.g., a CRT (cathode ray tube) or LCD (liquid crystal display) monitor) for displaying information to a user; and a keyboard and pointing device (e.g., a mouse or trackball) by which a user can provide input to the computer. Other kinds of devices may also be used to provide for interaction with a user; for example, feedback provided to the user may be any form of sensory feedback (e.g., visual feedback, auditory feedback, or tactile feedback); and input from the user may be received in any form, including acoustic input, speech input, or tactile input.
The systems and techniques described here can be implemented in a computing system that includes a background component (e.g., as a data server), or that includes a middleware component (e.g., an application server), or that includes a front-end component (e.g., a user computer having a graphical user interface or a web browser through which a user can interact with an implementation of the systems and techniques described here), or any combination of such background, middleware, or front-end components. The components of the system can be interconnected by any form or medium of digital data communication (e.g., a communication network). Examples of communication networks include: local Area Networks (LANs), wide Area Networks (WANs), and the internet.
The computer system may include a client and a server. The client and server are typically remote from each other and typically interact through a communication network. The relationship of client and server arises by virtue of computer programs running on the respective computers and having a client-server relationship to each other.
In the above embodiments, it may be implemented in whole or in part by software, hardware, firmware, or any combination thereof. When implemented in software, may be implemented in whole or in part in the form of a computer program product. The computer program product includes one or more computer programs or instructions. When the computer program or instructions are loaded and executed on a computer, the processes or functions described by the embodiments of the present disclosure are performed in whole or in part. The computer may be a general purpose computer, a special purpose computer, a computer network, a terminal, a user equipment, or other programmable apparatus. The computer program or instructions may be stored in a computer readable storage medium or transmitted from one computer readable storage medium to another computer readable storage medium, for example, the computer program or instructions may be transmitted from one website site, computer, server, or data center to another website site, computer, server, or data center by wired or wireless means. The computer readable storage medium may be any available medium that can be accessed by a computer or a data storage device such as a server, data center, etc. that integrates one or more available media. The usable medium may be a magnetic medium, e.g., floppy disk, hard disk, tape; optical media, such as digital video discs (digital video disc, DVD); but also semiconductor media such as solid state disks (solid state drive, SSD).
Although the present disclosure has been described in connection with specific features and embodiments thereof, it will be apparent that various modifications and combinations thereof can be made without departing from the spirit and scope of the disclosure. Accordingly, the specification and drawings are merely exemplary illustrations of the present disclosure as defined in the appended claims and are considered to cover any and all modifications, variations, combinations, or equivalents within the scope of the disclosure. It will be apparent to those skilled in the art that various modifications and variations can be made to the present disclosure without departing from the spirit or scope of the disclosure. Thus, the present disclosure is intended to include such modifications and alterations insofar as they come within the scope of the appended claims or the equivalents thereof.
Claims (12)
1. A method of determining aerodynamic performance of a deformed blade, the method comprising:
obtaining a target blade geometrical parameter of the deformed blade;
inputting the geometric parameters of the target blade into a force source item volumetric force prediction model to obtain a characteristic curve of the target distributed force source item volumetric force;
simulating the flow field characteristics of the deformed blade by taking the characteristic curve of the volume force of the target distributed force source item as a known condition to obtain target flow field information of the deformed blade;
And determining aerodynamic performance of the deformed blade based on the target flow field information of the deformed blade.
2. The method of claim 1, wherein the target blade geometry of the deformed blade comprises a plurality of blade height section geometry parameters and position parameters contained by the deformed blade.
3. The method of claim 2, wherein the geometric parameters of each of the leaf high sections comprise a camber line parameter of the leaf high section and a thickness parameter of the leaf high section.
4. The method of claim 1, wherein the characteristic of the target distributed source term volumetric force is a characteristic of the distributed source term volumetric force of each of the high sections of the lobes.
5. The method according to claim 1, wherein simulating the flow field characteristics of the deformed blade with the characteristic curve of the volumetric force of the target distributed force source term as a known condition to obtain target flow field information of the deformed blade comprises:
determining a target distributed force source Xiang Tiji force based on a characteristic of the target distributed force source term volumetric force;
inputting the volume force of the target distributed force source item into a blade flow field control equation to solve, and obtaining flow field information of the deformed blade;
If the flow field information of the deformed blade meets the iteration termination condition, determining that the target flow field information of the deformed blade is the flow field information of the deformed blade;
otherwise, the target distributed force source term volumetric force is redetermined from the characteristic curve of the target distributed force source term volumetric force based on the flow field information of the deformed blade.
6. The method of claim 5, wherein the iteration termination condition includes a global residual of flow field information of the deformed blade obtained from two adjacent iterations being less than or equal to a preset threshold.
7. The method of claim 5, wherein the vane flow field control equation comprises an euler equation.
8. The method of any one of claims 1-7, wherein the training sample of the force source term volumetric force prediction model during the training phase comprises: and the characteristic curves of the volume force of the corresponding distributed force source items and the geometric parameters of the plurality of blades of the deformed blade in different deformation states.
9. The method of claim 8, wherein the method of determining the characteristic of the distributed force source term volumetric force comprises:
determining flow field information corresponding to the geometric parameters of the corresponding blades by utilizing a Reynolds average NS equation;
And determining a characteristic curve of the volume force of the distributed force source item corresponding to the blade geometric parameter based on the flow field information.
10. A device for determining aerodynamic properties of a deformed blade, the device comprising:
the acquisition module is used for acquiring the geometric parameters of the target blade of the deformed blade;
the acquisition module is also used for inputting the geometric parameters of the target blade into a force source item volumetric force prediction model to obtain a characteristic curve of the target distributed force source item volumetric force;
the acquisition module is also used for simulating the flow field characteristics of the deformed blade by taking the characteristic curve of the volume force of the target distributed force source item as a known condition to acquire target flow field information of the deformed blade;
and the determining module is used for determining the aerodynamic performance of the deformed blade based on the target flow field information of the deformed blade.
11. An electronic device, comprising:
a processor; the method comprises the steps of,
a memory storing a program;
wherein the program comprises instructions which, when executed by the processor, cause the processor to perform the method according to any one of claims 1 to 9.
12. A non-transitory computer readable storage medium storing computer instructions for causing the computer to perform the method of any one of claims 1-9.
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Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN117313579A (en) * | 2023-10-07 | 2023-12-29 | 中国航空发动机研究院 | Engine compression part flow field prediction method, device, equipment and storage medium |
| CN117744283A (en) * | 2024-02-20 | 2024-03-22 | 陕西空天信息技术有限公司 | Design method, device, equipment and computer storage medium for compressor |
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Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN117313579A (en) * | 2023-10-07 | 2023-12-29 | 中国航空发动机研究院 | Engine compression part flow field prediction method, device, equipment and storage medium |
| CN117313579B (en) * | 2023-10-07 | 2024-04-05 | 中国航空发动机研究院 | Engine compression part flow field prediction method, device, equipment and storage medium |
| CN117744283A (en) * | 2024-02-20 | 2024-03-22 | 陕西空天信息技术有限公司 | Design method, device, equipment and computer storage medium for compressor |
| CN117744283B (en) * | 2024-02-20 | 2024-04-30 | 陕西空天信息技术有限公司 | Design method, device, equipment and computer storage medium for compressor |
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