Rotor design optimization methods, devices, computer equipment and storage media

Abstract

This invention relates to the field of aircraft rotor blade design technology, and discloses a rotor design optimization method, apparatus, computer equipment, and storage medium. The method includes: obtaining initial design parameters of the rotor; determining the vortex interference position of the rotor based on the initial design parameters; constructing a rotor model based on the chord length characteristics of the rotor within a set range of the vortex interference position, the rotor model being used to characterize the rotor's external dimensions; and performing computational fluid dynamics iterative simulation on the rotor based on the rotor's external dimensions to obtain a target rotor size whose noise calculation results conform to a set noise range. This allows for the rapid extraction of effective rotor features, and by using rotor noise as the optimization target for computational fluid dynamics iterative simulation of the rotor's design parameters, rapid noise reduction optimization is achieved, significantly shortening the iterative update cycle of design parameters, effectively improving rotor design efficiency, and significantly enhancing the noise reduction optimization effect.

Description

Technical Field

[0001] This invention relates to the field of aircraft rotor blade design technology, specifically to rotor design optimization methods, devices, computer equipment, and storage media. Background Technology

[0002] Due to limitations in materials, usage scenarios, and design methods, the size design of traditional aircraft rotors is significantly restricted. The overall rotor and blade tip shapes are relatively conventional, and the design optimization iteration speed is slow, failing to effectively optimize design parameters. Currently, most aircraft rotors adopt conventional chord characteristics, resulting in high rotor noise during operation. Therefore, how to quickly and effectively optimize aircraft rotor parameters has become an urgent technical problem to be solved. Summary of the Invention

[0003] In view of this, the present invention provides a rotor design optimization method, apparatus, computer equipment and storage medium to solve the urgent technical problem of how to quickly and effectively optimize the design of aircraft rotor parameters.

[0004] In a first aspect, the present invention provides a rotor design optimization method, the method comprising:

[0005] Obtain the initial design parameters of the rotor;

[0006] Based on the initial design parameters, the location of the rotor's vortex interference was determined;

[0007] Based on the chord length characteristics of the rotor within the set range of propeller vortex interference position, a rotor model is constructed, which is used to characterize the rotor's external dimensions;

[0008] Based on the rotor's external dimensions, computational fluid dynamics iterative simulations were performed on the rotor to obtain a target rotor size whose noise calculation results meet the set noise range.

[0009] The rotor design optimization method provided in this invention determines the location of vortex interference on the rotor based on the initial design parameters of the rotor. Based on the chord length characteristics of the rotor within a set range of the vortex interference location, a rotor model is constructed to characterize the rotor's external dimensions. Then, based on the rotor's external dimensions, computational fluid dynamics iterative simulation is performed on the rotor to obtain a target rotor size whose noise calculation results meet the set noise range. This rapidly extracts the effective features of the rotor, uses rotor noise as the optimization target, and performs computational fluid dynamics iterative simulation on the rotor's design parameters. This quickly performs noise reduction optimization, significantly shortens the iteration update cycle of the design parameters, effectively improves rotor design efficiency, and significantly enhances the noise reduction optimization effect.

[0010] In one alternative implementation, determining the location of propeller vortex interference based on initial design parameters includes:

[0011] Based on the initial design parameters, computational fluid dynamics simulation of the rotor was performed to obtain the location of vortex interference where the intensity of the vortex interference is within the set range.

[0012] The rotor design optimization method provided in this invention performs computational fluid dynamics simulation on the rotor based on initial design parameters to obtain the location of vortex interference where the intensity of the vortex interference conforms to a set range. Therefore, the computational fluid dynamics simulation method effectively locates the location of vortex interference where the intensity of the vortex interference conforms to a set range.

[0013] In one alternative implementation, computational fluid dynamics simulation of the rotor includes:

[0014] Based on the initial design parameters, calculate the thrust, torque, and efficiency of the rotor at different speeds;

[0015] Based on the thrust, torque, and efficiency, construct three-dimensional flow field diagrams of the rotor at different speeds;

[0016] Determine the location of rotor vortex interference based on the three-dimensional flow field diagram.

[0017] In one alternative implementation, computational fluid dynamics iterative simulation of the rotor includes:

[0018] Based on the rotor's external dimensions, computational fluid dynamics simulations are performed on the rotor to determine the noise calculation results corresponding to the rotor's external dimensions.

[0019] Before the noise calculation results meet the set noise range, adjust the chord length characteristics based on the set rules;

[0020] Based on the rotor shape dimensions corresponding to the adjusted chord length characteristics, computational fluid dynamics simulation of the rotor is performed until the target rotor size, whose noise calculation results meet the set noise range, is obtained.

[0021] The rotor design optimization method provided in this invention performs computational fluid dynamics simulation on the rotor based on its external dimensions to determine the noise calculation results corresponding to those dimensions. Then, by automatically adjusting the chord length characteristics according to set rules, and based on the rotor external dimensions corresponding to the adjusted chord length characteristics, computational fluid dynamics simulation is performed on the rotor until a target rotor size whose noise calculation results meet the set noise range is obtained. By using rotor noise as an effective optimization target and performing computational fluid dynamics simulation on the rotor, automatic iteration of rotor external dimensions is achieved, effectively improving the optimization efficiency of rotor design.

[0022] In one alternative implementation, the chord length features include the number, size, and position of protrusions on the rotor blades within the vortex interference position setting range.

[0023] The rotor design optimization method provided in this invention includes chord features such as the number, size, and position of protrusions on the rotor blades within a set range of vortex interference locations. Therefore, a rotor model can be constructed based on the number, size, and position of protrusions on the rotor blades within the set range of vortex interference locations. Further computational fluid dynamics iterative simulation of the rotor can then be performed to obtain a target rotor size whose noise calculation results conform to a set noise range. This fully utilizes the energy dissipated by vortex entanglement between the protrusion features designed on the rotor blades, thereby reducing the rotor's noise level.

[0024] In one alternative implementation, the number of protrusions is 1;

[0025] The target rotor dimensions include: the distance between the protrusion position and the rotor center position in the initial design dimensions is a first set multiple of the rotor blade radius; the protrusion size is a second set multiple of the chord length dimension in the initial design dimensions.

[0026] In one optional implementation, obtaining a target rotor size whose noise calculation results conform to a set noise range includes:

[0027] Based on the number, size, and location of the protrusions, the target rotor size is obtained using a piecewise cubic Hermite interpolation polynomial.

[0028] Secondly, the present invention provides a rotor design optimization device, the device comprising:

[0029] The acquisition module is used to obtain the initial design parameters of the rotor.

[0030] The position determination module is used to determine the location of rotor vortex interference based on the initial design parameters;

[0031] The construction module is used to build a rotor model based on the chord length characteristics of the rotor within a set range of propeller vortex interference positions. The rotor model is used to characterize the rotor's external dimensions.

[0032] The simulation module is used to perform computational fluid dynamics iterative simulation of the rotor based on its external dimensions, and obtain the target rotor size whose noise calculation results meet the set noise range.

[0033] Thirdly, the present invention provides a computer device, comprising: a memory and a processor, the memory and the processor being communicatively connected to each other, the memory storing computer instructions, and the processor executing the computer instructions to perform the rotor design optimization method of the first aspect or any corresponding embodiment described above.

[0034] Fourthly, the present invention provides a computer-readable storage medium storing computer instructions for causing a computer to perform the rotor design optimization method of the first aspect or any corresponding embodiment described above. Attached Figure Description

[0035] To more clearly illustrate the specific embodiments of the present invention or the technical solutions in the prior art, the drawings used in the description of the specific embodiments or the prior art will be briefly introduced below. Obviously, the drawings described below are some embodiments of the present invention. For those skilled in the art, other drawings can be obtained from these drawings without creative effort.

[0036] Figure 1 This is a schematic flowchart of a rotor design optimization method according to an embodiment of the present invention;

[0037] Figure 2 This is a flowchart illustrating another rotor design optimization method according to an embodiment of the present invention;

[0038] Figure 3 This is a flowchart illustrating a specific application example of the rotor design optimization method according to an embodiment of the present invention;

[0039] Figure 4 This is a flowchart of another rotor design optimization method according to an embodiment of the present invention;

[0040] Figure 5 This is a flowchart illustrating a specific application example of the rotor design optimization method according to an embodiment of the present invention;

[0041] Figure 6 This is a schematic diagram of the shape of a single-protrusion rotor obtained from a specific application example of the rotor design optimization method of the present invention;

[0042] Figure 7 This diagram illustrates the location of propeller vortex interference in CFD simulation of the rotor shape corresponding to the initial design parameters in a specific application example of this invention.

[0043] Figure 8 This diagram illustrates the position of propeller vortex interference in a CFD simulation of a rotor shape with a single protrusion, as shown in a specific application example of an embodiment of the present invention.

[0044] Figure 9 This diagram illustrates the location of propeller vortex interference in a CFD simulation of a rotor with multiple protrusions, as shown in a specific application example of an embodiment of the present invention.

[0045] Figure 10This is a schematic diagram of the noise calculation results obtained from computational fluid dynamics simulation based on initial design parameters, target rotor size with a single protrusion, and target rotor size with multiple protrusions in a specific application example of the rotor design optimization method of this invention.

[0046] Figure 11 This is a schematic diagram of the noise detection results obtained by performing actual noise detection based on initial design parameters, the target rotor size with a single protrusion, and the target rotor size with multiple protrusions in a specific application example of the rotor design optimization method of this invention.

[0047] Figure 12 This is a structural block diagram of a rotor design optimization device according to an embodiment of the present invention;

[0048] Figure 13 This is a schematic diagram of the hardware structure of a computer device according to an embodiment of the present invention. Detailed Implementation

[0049] To make the objectives, technical solutions, and advantages of the embodiments of the present invention clearer, the technical solutions of the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only some embodiments of the present invention, not all embodiments. Based on the embodiments of the present invention, all other embodiments obtained by those skilled in the art without creative effort are within the scope of protection of the present invention.

[0050] With the development of vehicle technology, flying car technology has also developed rapidly. Rotor design is a crucial component of flying cars, especially the rotor blade design, which significantly impacts important parameters such as rotor noise. Rotor noise directly affects user experience; therefore, optimizing rotor design to effectively reduce noise generated during flying car operation has become a pressing technical problem.

[0051] It should be noted that the above is a specific application scenario of the rotor design optimization method of the present invention. In actual application, the rotor design optimization method of the present invention can also be applied to other rotor design processes.

[0052] This invention provides a rotor design optimization method, apparatus, computer equipment, and storage medium. Based on the initial design parameters of the rotor, the location of vortex interference is determined. Based on the chord length characteristics of the rotor within a set range of the vortex interference location, a rotor model is constructed to characterize the rotor's external dimensions. Then, based on the rotor's external dimensions, computational fluid dynamics iterative simulation is performed on the rotor to obtain a target rotor size whose noise calculation results meet the set noise range. This rapidly extracts the effective features of the rotor, uses rotor noise as the optimization target, and performs computational fluid dynamics iterative simulation on the rotor's design parameters, quickly performing noise reduction optimization. This significantly shortens the iteration update cycle of the design parameters, effectively improving rotor design efficiency while significantly enhancing noise reduction optimization results. Effectively solving the problem of how to quickly and effectively optimize aircraft rotor parameters is a pressing technical issue.

[0053] According to an embodiment of the present invention, a rotor design optimization method embodiment is provided. It should be noted that the steps shown in the flowchart in the accompanying drawings can be executed in a computer system such as a set of computer-executable instructions. Furthermore, although a logical order is shown in the flowchart, in some cases, the steps shown or described may be executed in a different order than that shown here.

[0054] This embodiment provides a rotor design optimization method, which can be used in computing devices such as computers to design rotors for flying cars. Figure 1 This is a flowchart of a rotor design optimization method according to an embodiment of the present invention, such as... Figure 1 As shown, the process includes the following steps:

[0055] Step S101: Obtain the initial design parameters of the rotor.

[0056] The initial design parameters mainly take into account various factors such as material selection, structural design and aerodynamic performance, and are designed to meet the initial design parameters of the rotor application scenario.

[0057] In some alternative implementations, initial design parameters may include: rotor geometry CAD, different section chord lengths, installation angle, airfoil, etc.

[0058] Step S102: Based on the initial design parameters, determine the location of the rotor's vortex interference.

[0059] In some alternative implementations, CFD (Computational Fluid Dynamics) simulation technology can be used to calculate the thrust, torque, efficiency, and three-dimensional flow field of the rotor at different speeds, and the location of rotor vortex interference can be determined by the three-dimensional flow field diagram.

[0060] Specifically, during rotor rotation, the vortex interference effect is a disturbance effect caused by the interaction of the free vortex of the leading blade colliding with or approaching the following blade, resulting in a rapid change in the local aerodynamic load on the following blade. The vortex interference location refers to the specific location where the interference effect occurs. The vortex interference location can be defined as a range, a point at the blade tip, or a set number of points on the blades. In practical applications, it can also be set according to the needs of the actual simulation calculation.

[0061] Step S103: Based on the chord length characteristics of the rotor within the set range of the propeller vortex interference position, construct a rotor model. The rotor model is used to characterize the rotor's external dimensions.

[0062] In one alternative implementation, the chord length features include the number, size, and position of protrusions on the rotor blades within the vortex interference position setting range.

[0063] Specifically, to ensure the optimization effect of rotor design parameters while reducing the amount of simulation calculations and improving optimization efficiency, a rotor model can be constructed based on the chord length characteristics of the rotor within a defined range of vortex interference locations. Specifically, CAD modeling can be used to parameterize the chord length characteristics of the rotor within the defined range of vortex interference locations. The chord length characteristics are mainly iterated based on three parameters: the number of protrusions (Num), the scale (Len), and the position (Pos).

[0064] For example, Figure 2 A schematic diagram of the rotor blade design with multiple protrusions in an embodiment of the present invention is shown. For example... Figure 2 As shown, the number of raised features, Num, has a value of 4. The scale of the raised feature, Len, can refer to the chord length between multiple pairs of points on the raised feature, such as L1, L2, L3...Ln. The position of the raised feature, Pos, can be defined based on the position with the longest chord length on the raised feature. For example, the position Pos of the nth raised feature can be defined as: the distance Rn from the rotor center point to the line connecting the pair of points with the longest chord length among multiple pairs of points on that raised feature. Specifically, it can be the length of the perpendicular distance from the rotor center point to the line connecting the pair of points.

[0065] Figure 3 A schematic diagram of the blade design of a single-protrusion rotor in an embodiment of the present invention is shown. Figure 3 The value of the number of protrusions Num is 1.

[0066] The rotor design optimization method provided in this invention includes chord features such as the number, size, and position of protrusions on the rotor blades within a set range of vortex interference locations. Therefore, a rotor model can be constructed based on the number, size, and position of protrusions on the rotor blades within the set range of vortex interference locations. Further computational fluid dynamics iterative simulation of the rotor can then be performed to obtain a target rotor size whose noise calculation results conform to a set noise range. This fully utilizes the energy dissipated by vortex entanglement between the protrusion features designed on the rotor blades, thereby reducing the rotor's noise level.

[0067] Step S104: Based on the rotor's external dimensions, perform computational fluid dynamics iterative simulation on the rotor to obtain a target rotor size whose noise calculation results meet the set noise range.

[0068] In some optional implementations, the chord length characteristics of the rotor within the set range of the propeller vortex interference position can be parameterized in step S103. Here, based on the rotor's external dimensions, the process of performing computational fluid dynamics iterative simulation on the rotor involves using multiple parameters of the rotor's external dimensions as variables, and using the noise calculation results obtained from the computational fluid dynamics simulation as the optimization target. When the noise calculation results meet the set noise range, the values ​​of multiple parameters corresponding to the rotor's external dimensions are recorded, thereby determining the main parameters of the rotor blades as the target rotor size. For example, the chord length between multiple point pairs of the rotor blades and the radius of the blades are R.

[0069] For example, a genetic algorithm can be used to iteratively update the rotor shape based on three parameters: the number of protrusions (Num), the scale (Len), and the position (Pos). A new rotor shape is generated based on each set of parameter values, and then CFD simulation is performed based on these dimensions to obtain the corresponding rotor noise simulation results. The noise range can be set to be less than a noise threshold, for example, a noise threshold of 60 dBa (decibels).

[0070] Return to reference again Figure 3 , Figure 3 The diagram also illustrates the rotor shape during multiple iterations of simulation using different line types. It should be noted that... Figure 3 The image only shows a schematic diagram of the rotor shape obtained by designing a single protrusion feature on the rotor based on the location of vortex interference, and performing computational fluid dynamics iterative simulation on the rotor by changing the scale (Len) of the protrusion feature. In practical applications, the position of the protrusion feature can be adjusted within a set range of the vortex interference location to perform computational fluid dynamics iterative simulation on the rotor. Therefore, by configuring the parameter iteration rules in the simulation process according to the design requirements in advance, a target rotor size whose noise calculation results meet the set noise range can be obtained.

[0071] The rotor design optimization method provided in this invention determines the location of vortex interference on the rotor based on the initial design parameters of the rotor. Based on the chord length characteristics of the rotor within a set range of the vortex interference location, a rotor model is constructed to characterize the rotor's external dimensions. Then, based on the rotor's external dimensions, computational fluid dynamics iterative simulation is performed on the rotor to obtain a target rotor size whose noise calculation results meet the set noise range. This rapidly extracts the effective features of the rotor, uses rotor noise as the optimization target, and performs computational fluid dynamics iterative simulation on the rotor's design parameters. This quickly performs noise reduction optimization, significantly shortens the iteration update cycle of the design parameters, effectively improves rotor design efficiency, and significantly enhances the noise reduction optimization effect.

[0072] This embodiment provides a rotor design optimization method, which can be used in computing devices such as computers to design rotors for flying cars. Figure 4 This is a flowchart of another rotor design optimization method according to an embodiment of the present invention, such as... Figure 4 As shown, the process includes the following steps:

[0073] Step S401: Obtain the initial design parameters of the rotor.

[0074] Please see details Figure 1 Step S102 of the illustrated embodiment will not be described again here.

[0075] Step S402: Based on the initial design parameters, determine the location of the rotor's vortex interference.

[0076] Specifically, step S402 may include:

[0077] Step S4021: Based on the initial design parameters, perform computational fluid dynamics simulation on the rotor to obtain the location of vortex interference where the intensity of the vortex interference meets the set intensity range.

[0078] The rotor design optimization method provided in this invention performs computational fluid dynamics simulation on the rotor based on initial design parameters to obtain the location of vortex interference where the intensity of the vortex interference conforms to a set range. Therefore, the computational fluid dynamics simulation method effectively locates the location of vortex interference where the intensity of the vortex interference conforms to a set range.

[0079] In an optional implementation, the process of performing computational fluid dynamics simulation on the rotor in step S S4021 may include:

[0080] Step a1: Based on the initial design parameters, calculate the thrust, torque, and efficiency of the rotor at different speeds.

[0081] Here, CFD simulation based on the initial design parameters of the rotor can directly yield parameters such as thrust, torque, and efficiency at different speeds. The CFD simulation process can directly call the scripts of the CFD simulation software.

[0082] Step a2 involves constructing three-dimensional flow field diagrams of the rotor at different speeds based on the thrust, torque, and efficiency. These three-dimensional flow field diagrams are conventional three-dimensional flow field models generated during data processing using computational fluid dynamics simulation algorithms. Here, the three-dimensional flow field diagrams are used to visually represent the noise simulation results of the rotor.

[0083] Step a3: Determine the location of rotor vortex interference based on the three-dimensional flow field diagram.

[0084] Step S403: Based on the chord length characteristics of the rotor within the set range of propeller vortex interference position, construct a rotor model. The rotor model is used to characterize the rotor's external dimensions.

[0085] Please see details Figure 1 Step S103 of the illustrated embodiment will not be described again here.

[0086] Step S404: Based on the rotor's external dimensions, perform computational fluid dynamics iterative simulation on the rotor to obtain a target rotor size whose noise calculation results meet the set noise range.

[0087] Specifically, step S404 may include:

[0088] Step S4041: Based on the rotor's external dimensions, perform computational fluid dynamics simulation on the rotor to determine the noise calculation results corresponding to the rotor's external dimensions.

[0089] Step S4042: Before the noise calculation result meets the set noise range, adjust the chord length feature based on the set rules.

[0090] Step S4043: Based on the rotor shape dimensions corresponding to the adjusted chord length characteristics, perform computational fluid dynamics simulation on the rotor until the noise calculation results meet the target rotor size within the set noise range.

[0091] In one optional implementation, obtaining the target rotor size whose noise calculation results conform to a set noise range includes: obtaining the target rotor size using a piecewise cubic Hermite interpolation polynomial based on the number of protrusions, the size of the protrusions, and the position of the protrusions.

[0092] Specifically, in step S4042, before the noise calculation result meets the set noise range, the chord length features are adjusted based on the set rules. The chord length features include the number, size, and position of protrusions on the rotor blades within the set range of the vortex interference position. Therefore, when the noise calculation result meets the set noise range, the obtained information is the chord length features of multiple point pairs corresponding to the protrusion features. Here, the rotor shape needs to be fitted based on the chord length features of multiple point pairs to obtain lines that can characterize the rotor blade shape, for example, it can be shown in a CAD format file. The fitting method here can be a piecewise cubic Hermitian interpolation polynomial, or other applicable fitting methods can be used; this invention does not specifically limit this.

[0093] The rotor design optimization method provided in this invention performs computational fluid dynamics (CFD) simulations on the rotor based on its external dimensions to determine the noise calculation results corresponding to those dimensions. Then, by automatically adjusting the chord length characteristics according to set rules, and based on the rotor external dimensions corresponding to the adjusted chord length characteristics, CFD simulations are performed on the rotor until a target rotor size with noise calculation results meeting a set noise range is obtained. By using rotor noise as an effective optimization target, CFD simulations are performed on the rotor, enabling automatic iteration of rotor external dimensions and effectively improving the optimization efficiency of rotor design.

[0094] This embodiment provides a rotor design optimization method, which can be used in computing devices such as computers to design rotors for flying cars. Figure 5 This is a flowchart illustrating a specific application example of the rotor design optimization method according to an embodiment of the present invention, such as... Figure 5 As shown, the process includes the following steps:

[0095] Step S501: Obtain the initial design parameters of the rotor.

[0096] Step S502: Based on the initial design parameters, perform CFD simulation calculations to determine the location of rotor vortex interference.

[0097] Step S503: Based on the chord length characteristics of the rotor within the set range of the propeller vortex interference position, construct a rotor model. The rotor model is used to characterize the rotor's external dimensions.

[0098] Specifically, the chord length characteristic of the propeller vortex interference location can be parameterized.

[0099] For example, by setting the position Pos of the protrusion feature, the number of protrusion features Num, and the scale Len of the protrusion feature, the rotor shape and size can be parametrically modeled.

[0100] Step S504: Based on the rotor's external dimensions, execute the CAD script to obtain the rotor CAD model.

[0101] Here, the rotor CAD model is a CAD model used to represent the geometric shape of the rotor.

[0102] Step S505: Execute the CFD script to obtain the rotor CFD model.

[0103] For example, an interface for calling CFD scripts can be configured here, enabling the invocation of CFD scripts. Here, the rotor CFD model represents the features used to characterize different points on the rotor.

[0104] Step S506: For the rotor shape dimensions corresponding to the given protrusion feature position Pos, the number of protrusion features Num, and the scale Len of the protrusion feature, automatically perform CFD simulation calculations to obtain noise calculation results.

[0105] Step S507: Determine whether the noise calculation result meets the set noise range. If the noise calculation result meets the set noise range, proceed to step S509. If the noise calculation result does not meet the set noise range, proceed to step S508.

[0106] Step S508: Adjust the position Pos of the raised feature, the number of raised features Num, and the scale Len of the raised feature.

[0107] For example, refer back to the reference. Figure 2 and Figure 3 The text explains the location Pos of the raised feature, the number of raised features Num, and the scale Len of the raised feature. The values ​​of L1, L2...Ln, and Rn can be adjusted.

[0108] Therefore, through steps S503 to S508, computational fluid dynamics iterative simulation of the rotor is achieved based on the rotor's external dimensions in the rotor CFD model.

[0109] Step 509: When the noise calculation result meets the set noise range, output the target rotor size.

[0110] In one alternative implementation, the number of protrusions is 1. The target rotor size may include the following parameters: the distance between the protrusion location and the rotor center location in the initial design size is a first predetermined multiple of the rotor blade radius, and the protrusion size is a second predetermined multiple of the chord length dimension in the initial design size.

[0111] In one optional implementation, obtaining a target rotor size whose noise calculation results conform to a set noise range includes:

[0112] Based on the number, size, and location of the protrusions, the target rotor size is obtained using a piecewise cubic Hermite interpolation polynomial.

[0113] Figure 6 The diagram shows a schematic representation of a single-protrusion rotor obtained through a specific application example of the rotor design optimization method according to an embodiment of the present invention. Figure 6 The rotor shape shown is the target rotor size with a single protrusion obtained from a specific application example of this invention. The distance between the protrusion location and the rotor center location in the initial design size is 0.9 times the rotor blade radius, and the protrusion size is 1.227 times the chord length in the initial design size. That is, the first set multiple is 0.9R, and the second set multiple is 1.227. Specifically, on the blade of the single-protrusion rotor, L2 is used to characterize the scale Len of the protrusion feature, specifically referring to the position with the longest chord length among multiple point pairs on the protrusion feature, where the chord length is L2. Figure 6 The dashed lines, representing smoother, non-protruding sections, characterize the rotor shape corresponding to the initial design parameters. For the protrusions after rotor optimization relative to the initial design parameters, each pair of points in the protrusion feature has an original pair of points. Therefore, L2 and... Figure 6 The chord length L is shown by the pair of points in the initial design parameters corresponding to the dashed line. 2原 (Because it overlaps with L2, Figure 6 The relationship (not shown in the diagram) is L2 = 1.227 * L 2原 The position Pos of the protrusion feature can be identified based on the rotor blade radius. For example, if the rotor blade radius is R, the position Pos of the protrusion feature is the location on the rotor blade at a distance of 0.9R from the rotor center point.

[0114] It should be noted that the values ​​of the first and second set multiples can be adjusted based on the actual simulation results.

[0115] Figure 7 This diagram illustrates the location of propeller vortex interference in CFD simulation of the rotor shape corresponding to the initial design parameters in a specific application example of this invention. Figure 8 This diagram illustrates the location of propeller vortex interference in a CFD simulation of a rotor shape with a single protrusion, as shown in a specific application example of an embodiment of the present invention. Figure 9 This diagram illustrates the location of propeller vortex interference in a CFD simulation of a rotor with multiple protrusions, as shown in a specific application example of an embodiment of the present invention. Based on Figures 7-9 By comparison, it can be seen that in the CFD simulation results of the rotor shape corresponding to the initial design parameters, each blade has only one tip vortex, which is the line resembling two semicircles in the figure. With the convex rotor shape, each blade forms multiple vortices, which are the convex lines near the connection between the semicircular lines and the relatively thicker straight line in the figure. The newly added convex features clearly divide the tip vortex into several distinct segments, such as... Figures 7-9Visualizing the same scale of the propeller tip vortex clearly shows that the convex features increase the number of tip vortices, which helps to reduce vortex intensity and improve blade noise.

[0116] Figure 10 The diagram illustrates the noise calculation results obtained from computational fluid dynamics simulation based on initial design parameters, the target rotor size with a single convexity, and the target rotor size with multiple convexities, in a specific application example of an embodiment of the present invention. The target rotor size with a single convexity can be as follows: Figure 6 The single-protrusion rotor shape is shown. The target rotor size with multiple protrusions can be the target rotor size obtained using the rotor design optimization method provided in the embodiments of the present invention.

[0117] refer to Figure 10 V3 represents the noise calculation results obtained from computational fluid dynamics simulation based on the target rotor size with a single protrusion. V4 represents the noise calculation results obtained from computational fluid dynamics simulation based on the target rotor size with multiple protrusions. base represents the noise calculation results obtained from computational fluid dynamics simulation based on the initial design parameters. Figure 10 It can be seen that, regardless of whether the target rotor size is based on a single protrusion or a multi-protrusion target rotor size, the blade noise optimized using the rotor design provided in this embodiment of the invention is significantly lower than the blade noise of the reference blade with the initial design parameters. Specifically, the target rotor shape corresponding to V3 has an average noise reduction of 21.4 dBA compared to the reference blade corresponding to base, and the target rotor shape corresponding to V4 has an average noise reduction of 15.9 dBA compared to the reference blade corresponding to base.

[0118] Furthermore, through experimental testing and analysis, and simulation comparison, the noise simulation results obtained using computational fluid dynamics simulation are more accurate for noise calculations below 2000Hz, as can be referenced above. Figure 10 The noise simulation results are shown. For noise data above 2000Hz, specific application examples of this invention provide, as shown... Figure 11 The noise detection results shown are from actual noise detection. Specifically, the target rotor shape corresponding to V3 obtained by the rotor design optimization method provided in this embodiment of the invention has an average noise reduction of 5.0 dBA compared to the reference blade corresponding to base, and the target rotor shape corresponding to V4 has an average noise reduction of 4.9 dBA compared to the reference blade corresponding to base.

[0119] The rotor design optimization method provided in this invention can add protruding features to the tip of a large rotor. By designing an irregular plane at the tip, the method utilizes the tip vortex coupling or entanglement dissipation principle formed by the protruding features to significantly reduce the noise level.

[0120] This embodiment also provides a rotor design optimization device for implementing the above embodiments and preferred embodiments; details already described will not be repeated. As used below, the term "module" can refer to a combination of software and / or hardware that performs a predetermined function. Although the device described in the following embodiments is preferably implemented in software, hardware implementation, or a combination of software and hardware, is also possible and contemplated.

[0121] This embodiment provides a rotor design optimization device, such as... Figure 12 As shown, it includes:

[0122] The acquisition module 1201 is used to obtain the initial design parameters of the rotor;

[0123] The position determination module 1202 is used to determine the position of the rotor's vortex interference based on the initial design parameters;

[0124] Module 1203 is used to construct a rotor model based on the chord length characteristics of the rotor within a set range of propeller vortex interference position. The rotor model is used to characterize the rotor's external dimensions.

[0125] Simulation module 1204 is used to perform computational fluid dynamics iterative simulation of the rotor based on the rotor's external dimensions, and obtain the target rotor size whose noise calculation results meet the set noise range.

[0126] In one optional implementation, the location determination module 1202 includes:

[0127] The first simulation unit is used to perform computational fluid dynamics simulation on the rotor based on the initial design parameters to obtain the location of vortex interference where the intensity of the vortex interference is within the set range.

[0128] In one optional implementation, the first simulation unit includes:

[0129] The calculation sub-unit is used to calculate the thrust, torque, and efficiency of the rotor at different speeds based on the initial design parameters;

[0130] The three-dimensional construction sub-unit is used to construct three-dimensional flow field diagrams of the rotor at different speeds based on tension, torque, and efficiency;

[0131] The judgment sub-unit is used to determine the location of rotor vortex interference based on the three-dimensional flow field diagram.

[0132] In one alternative implementation, the simulation module 1204 includes:

[0133] The noise unit is used to perform computational fluid dynamics simulation on the rotor based on its external dimensions, and to determine the noise calculation results corresponding to the rotor's external dimensions.

[0134] The adjustment unit is used to adjust the chord length feature based on set rules before the noise calculation result meets the set noise range;

[0135] The simulation subunit is used to perform computational fluid dynamics simulation on the rotor based on the rotor shape dimensions corresponding to the adjusted chord length characteristics, until the target rotor size with noise calculation results that meet the set noise range is obtained.

[0136] In one alternative implementation, the chord length features include the number, size, and position of protrusions on the rotor blades within the vortex interference position setting range.

[0137] In one alternative implementation, the number of protrusions is 1;

[0138] The target rotor dimensions include: the distance between the protrusion position and the rotor center position in the initial design dimensions is a first set multiple of the rotor blade radius; the protrusion size is a second set multiple of the chord length dimension in the initial design dimensions.

[0139] In one optional implementation, obtaining a target rotor size whose noise calculation results conform to a set noise range includes:

[0140] Based on the number, size, and location of the protrusions, the target rotor size is obtained using a piecewise cubic Hermite interpolation polynomial.

[0141] Further functional descriptions of the above modules and units are the same as those in the corresponding embodiments described above, and will not be repeated here.

[0142] In this embodiment, the rotor design optimization device is presented in the form of a functional unit. Here, a unit refers to an ASIC (Application Specific Integrated Circuit) circuit, a processor and memory that execute one or more software or fixed programs, and / or other devices that can provide the above functions.

[0143] This invention also provides a computer device having the above-described features. Figure 12 The rotor design optimization device shown.

[0144] Please see Figure 13 , Figure 13 This is a schematic diagram of the structure of a computer device provided in an optional embodiment of the present invention, such as... Figure 13As shown, the computer device includes one or more processors 10, memory 20, and interfaces for connecting the components, including high-speed interfaces and low-speed interfaces. The components communicate with each other via different buses and can be mounted on a common motherboard or otherwise installed as needed. The processors can process instructions executed within the computer device, including instructions stored in or on memory to display graphical information of a GUI on external input / output devices (such as display devices coupled to the interfaces). In some alternative implementations, multiple processors and / or multiple buses can be used with multiple memories and multiple memory modules, if desired. Similarly, multiple computer devices can be connected, each providing some of the necessary operations (e.g., as a server array, a group of blade servers, or a multiprocessor system). Figure 13 Take a processor 10 as an example.

[0145] Processor 10 may be a central processing unit, a network processor, or a combination thereof. Processor 10 may further include a hardware chip. The hardware chip may be an application-specific integrated circuit (ASIC), a programmable logic device (PLD), or a combination thereof. The programmable logic device may be a complex programmable logic device (CAMP), a field-programmable gate array (FPGA), a general-purpose array logic (GDA), or any combination thereof.

[0146] The memory 20 stores instructions executable by at least one processor 10 to cause at least one processor 10 to perform the method shown in the above embodiments.

[0147] The memory 20 may include a program storage area and a data storage area. The program storage area may store the operating system and applications required for at least one function; the data storage area may store data created based on the use of the computer device. Furthermore, the memory 20 may include high-speed random access memory and may also include non-transitory memory, such as at least one disk storage device, flash memory device, or other non-transitory solid-state storage device. In some alternative embodiments, the memory 20 may optionally include memory remotely located relative to the processor 10, and these remote memories may be connected to the computer device via a network. Examples of such networks include, but are not limited to, the Internet, intranets, local area networks, mobile communication networks, and combinations thereof.

[0148] The memory 20 may include volatile memory, such as random access memory; the memory may also include non-volatile memory, such as flash memory, hard disk or solid-state drive; the memory 20 may also include a combination of the above types of memory.

[0149] The computer device also includes a communication interface 30 for communicating with other devices or communication networks.

[0150] This invention also provides a computer-readable storage medium. The methods described above according to embodiments of the invention can be implemented in hardware or firmware, or implemented as computer code that can be recorded on a storage medium, or implemented as computer code downloaded via a network and originally stored on a remote storage medium or a non-transitory machine-readable storage medium and then stored on a local storage medium. Thus, the methods described herein can be processed by software stored on a storage medium using a general-purpose computer, a dedicated processor, or programmable or dedicated hardware. The storage medium can be a magnetic disk, optical disk, read-only memory, random access memory, flash memory, hard disk, or solid-state drive, etc.; further, the storage medium can also include combinations of the above types of memory. It is understood that computers, processors, microprocessor controllers, or programmable hardware include storage components capable of storing or receiving software or computer code, which, when accessed and executed by the computer, processor, or hardware, implements the methods shown in the above embodiments.

[0151] A portion of this invention can be applied as a computer program product, such as computer program instructions, which, when executed by a computer, can invoke or provide the methods and / or technical solutions according to the invention through the operation of the computer. Those skilled in the art will understand that the forms in which computer program instructions exist in a computer-readable medium include, but are not limited to, source files, executable files, installation package files, etc. Correspondingly, the ways in which computer program instructions are executed by a computer include, but are not limited to: the computer directly executing the instructions, or the computer compiling the instructions and then executing the corresponding compiled program, or the computer reading and executing the instructions, or the computer reading and installing the instructions and then executing the corresponding installed program. Here, the computer-readable medium can be any available computer-readable storage medium or communication medium accessible to a computer.

[0152] Although embodiments of the invention have been described in conjunction with the accompanying drawings, those skilled in the art can make various modifications and variations without departing from the spirit and scope of the invention, and such modifications and variations all fall within the scope defined by the appended claims.

Claims

1. A rotor design optimization method, characterized in that, The method includes: Obtain the initial design parameters of the rotor; Based on the initial design parameters, the location of the rotor's vortex interference is determined; Based on the chord length characteristics of the rotor within the set range of the propeller vortex interference position, a rotor model is constructed, which is used to characterize the rotor's external dimensions; Based on the rotor's external dimensions, computational fluid dynamics iterative simulation is performed on the rotor to obtain a target rotor size whose noise calculation results meet the set noise range; The step of determining the rotor vortex interference location based on the initial design parameters includes: Based on the initial design parameters, the thrust, torque, and efficiency of the rotor at different speeds are calculated; Based on the tension, torque, and efficiency, construct three-dimensional flow field diagrams of the rotor at different speeds; Based on the three-dimensional flow field diagram, determine the location of the rotor's vortex interference; The computational fluid dynamics iterative simulation of the rotor includes: Based on the rotor's external dimensions, computational fluid dynamics simulation is performed on the rotor to determine the noise calculation results corresponding to the rotor's external dimensions; Before the noise calculation result meets the set noise range, the chord length feature is adjusted based on the set rules; Based on the rotor shape dimensions corresponding to the adjusted chord length characteristics, computational fluid dynamics simulation is performed on the rotor until the target rotor size that meets the noise calculation results is obtained; The chord length feature includes the number, size, and position of protrusions on the rotor blades within the set range of the propeller vortex interference position.

2. The method according to claim 1, characterized in that, Determining the location of propeller vortex interference based on the initial design parameters includes: Based on the initial design parameters, computational fluid dynamics simulation was performed on the rotor to obtain the location of vortex interference where the intensity of the vortex interference conforms to the set intensity range.

3. The method according to claim 1, characterized in that, The number of protrusions is 1; The target rotor dimensions include: the distance between the protrusion position and the rotor center position in the initial design parameters is a first set multiple of the rotor blade radius; the protrusion size is a second set multiple of the chord length dimension in the initial design parameters.

4. The method according to claim 1, characterized in that, The target rotor size whose noise calculation results conform to the set noise range includes: Based on the number of protrusions, the size of the protrusions, and the position of the protrusions, the target rotor size is obtained using a piecewise cubic Hermite interpolation polynomial.

5. A rotor design optimization device, characterized in that, The device includes: The acquisition module is used to obtain the initial design parameters of the rotor. The position determination module is used to determine the position of the rotor's vortex interference based on the initial design parameters; The construction module is used to construct a rotor model based on the chord length characteristics of the rotor within the set range of the propeller vortex interference position. The rotor model is used to characterize the rotor's external dimensions. The simulation module is used to perform computational fluid dynamics iterative simulation of the rotor based on the rotor's external dimensions, and obtain a target rotor size whose noise calculation results meet the set noise range. The location determination module includes: The calculation subunit is used to calculate the thrust, torque, and efficiency of the rotor at different speeds based on the initial design parameters. A three-dimensional construction subunit is used to construct a three-dimensional flow field diagram of the rotor at different speeds based on the tension, the torque, and the efficiency; The judgment subunit is used to determine the location of the rotor's vortex interference based on the three-dimensional flow field diagram. The simulation module includes: The noise unit is used to perform computational fluid dynamics simulation on the rotor based on the rotor's external dimensions, and to determine the noise calculation results corresponding to the rotor's external dimensions. An adjustment unit is used to adjust the chord length feature based on a set rule before the noise calculation result meets the set noise range. The simulation subunit is used to perform computational fluid dynamics simulation on the rotor based on the rotor shape dimensions corresponding to the adjusted chord length characteristics, until the noise calculation results meet the target rotor size within the set noise range. The chord length feature includes the number, size, and position of protrusions on the rotor blades within the set range of the propeller vortex interference position.

6. A computer device, characterized in that, include: A memory and a processor are interconnected, the memory stores computer instructions, and the processor executes the rotor design optimization method according to any one of claims 1 to 4 by executing the computer instructions.

7. A computer-readable storage medium, characterized in that, The computer-readable storage medium stores computer instructions for causing the computer to execute the rotor design optimization method according to any one of claims 1 to 4.

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