Rotor design optimization method and device, computer equipment and storage medium

Abstract

The invention relates to the technical field of aircraft blade design, and discloses a rotor design optimization method and device, computer equipment and a storage medium, and the method comprises the steps: obtaining initial design parameters of a rotor; based on the initial design parameters, determining a vortex interference position of the rotor; based on the chord length characteristics of the rotor in the set range of the blade vortex interference position, constructing a rotor model which is used for representing the overall dimension of the rotor; and performing computational fluid dynamics iterative simulation on the rotor based on the outline dimension of the rotor to obtain a target rotor dimension of which a noise calculation result accords with a set noise range. Therefore, the effective features of the rotor wing are rapidly extracted, the design parameters of the rotor wing are subjected to computational fluid dynamics iterative simulation with the noise of the rotor wing as the optimization target, noise reduction optimization is rapidly carried out, the iterative update period of the design parameters is remarkably shortened, the design efficiency of the rotor wing is effectively improved, and meanwhile the noise reduction optimization effect is remarkably improved.

Description

Technical Field

[0001] The present invention relates to the technical field of aircraft blade design, and in particular to a rotor design optimization method, device, computer equipment and storage medium. Background Art

[0002] Due to the limitations of materials, usage scenarios, and design methods, the size design of traditional aircraft rotors is greatly restricted. The entire rotor and blade tip shape design is relatively conventional, and the design optimization iteration speed is slow, and the optimization design of design parameters has not been effectively carried out. Currently, most equipment rotors use conventional chord length characteristics, and the rotors are noisy during operation. Therefore, how to quickly and effectively optimize the design of aircraft rotor parameters has become a technical problem that needs to be solved urgently. Summary of the invention

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

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

[0005] Obtaining initial design parameters of the rotor;

[0006] Based on the initial design parameters, determine the vortex interference position of the rotor;

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

[0008] Based on the rotor dimensions, computational fluid dynamics iterative simulation is performed on the rotor, and the noise calculation results are in line with the target rotor dimensions within the set noise range.

[0009] The rotor design optimization method provided by the embodiment of the present invention determines the vortex interference position of the rotor based on the initial design parameters of the rotor, and constructs a rotor model for characterizing the rotor's external dimensions based on the chord length characteristics of the rotor within the set range of the vortex interference position, and then performs computational fluid dynamics iterative simulation on the rotor based on the rotor's external dimensions to obtain a target rotor size whose noise calculation result meets the set noise range. Thus, the effective features of the rotor are quickly extracted, and computational fluid dynamics iterative simulation is performed on the rotor's design parameters with the rotor's noise as the optimization target, and noise reduction optimization is quickly performed, which significantly shortens the iterative update cycle of the design parameters, effectively improves the rotor design efficiency, and significantly improves the noise reduction optimization effect.

[0010] In an optional implementation, determining the propeller vortex interference position based on the initial design parameters includes:

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

[0012] The rotor design optimization method provided by the embodiment of the present invention performs computational fluid dynamics simulation on the rotor based on the initial design parameters to obtain the propeller vortex interference position where the propeller vortex interference intensity meets the set intensity range. Thus, the propeller vortex interference position where the propeller vortex interference intensity meets the set intensity range is effectively located by using the computational fluid dynamics simulation method.

[0013] In an optional embodiment, performing computational fluid dynamics simulation on the rotor includes:

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

[0015] Construct a three-dimensional diagram of the flow field of the rotor at different speeds based on thrust, torque and efficiency;

[0016] According to the three-dimensional flow field diagram, the position of the rotor vortex interference is determined.

[0017] In an optional embodiment, performing computational fluid dynamics iterative simulation on the rotor includes:

[0018] Based on the rotor dimensions, computational fluid dynamics simulation is performed on the rotor to determine the noise calculation results corresponding to the rotor dimensions;

[0019] Before the noise calculation result meets the set noise range, the chord length characteristics are adjusted based on the set rules;

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

[0021] The rotor design optimization method provided by the embodiment of the present invention performs computational fluid dynamics simulation on the rotor based on the rotor external dimensions to determine the noise calculation results corresponding to the rotor external dimensions; thus, the chord length feature is automatically adjusted based on the set rules, and the rotor external dimensions corresponding to the adjusted chord length feature are subjected to computational fluid dynamics simulation until the target rotor dimensions whose noise calculation results meet the set noise range are obtained. With the rotor noise as an effective optimization target, computational fluid dynamics simulation is performed on the rotor to achieve automatic iteration of the rotor external dimensions, effectively improving the optimization efficiency of the rotor design.

[0022] In an optional embodiment, the chord length feature includes the number, size and position of protrusions of the blades of the rotor within a set range of the blade vortex interference position.

[0023] In the rotor design optimization method provided by the embodiment of the present invention, the chord length feature includes the number of protrusions, the size of the protrusions, and the position of the protrusions on the rotor blades within the set range of the vortex interference position. Therefore, based on the number of protrusions, the size of the protrusions, and the position of the protrusions on the rotor blades within the set range of the vortex interference position, a rotor model can be constructed, and the rotor can be further subjected to computational fluid dynamics iterative simulation to obtain a target rotor size whose noise calculation result meets the set noise range, thereby making full use of the vortex entanglement dissipation energy between the protrusion features designed on the rotor blades and reducing the noise level of the rotor.

[0024] In an optional embodiment, 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 dimension is a first set multiple of the rotor blade radius; the protrusion dimension is a second set multiple of the chord length dimension in the initial design dimension.

[0026] In an optional embodiment, obtaining a target rotor size whose noise calculation result meets a set noise range includes:

[0027] Based on the number, size and position of the bumps, the target rotor size is obtained by using piecewise cubic Hermite interpolation polynomial.

[0028] In a second aspect, the present invention provides a rotor design optimization device, the device comprising:

[0029] An acquisition module, used to obtain initial design parameters of the rotor;

[0030] A position determination module, used for determining a vortex interference position of the rotor based on initial design parameters;

[0031] A construction module is used to construct a rotor model based on the chord length characteristics of the rotor within the set range of the blade vortex interference position, and the rotor model is used to characterize the rotor shape size;

[0032] The simulation module is used to perform computational fluid dynamics iterative simulation on the rotor based on the rotor's external dimensions, and obtain a target rotor dimension whose noise calculation result meets the set noise range.

[0033] In a third aspect, 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 rotor design optimization method of the first aspect or any corresponding embodiment thereof by executing the computer instructions.

[0034] In a fourth aspect, the present invention provides a computer-readable storage medium having computer instructions stored thereon, the computer instructions being used to enable a computer to execute the rotor design optimization method of the first aspect or any corresponding embodiment thereof. BRIEF DESCRIPTION OF THE DRAWINGS

[0035] In order to more clearly illustrate the specific implementation methods of the present invention or the technical solutions in the prior art, the drawings required for use in the specific implementation methods or the description of the prior art will be briefly introduced below. Obviously, the drawings described below are some implementation methods of the present invention. For ordinary technicians in this field, other drawings can be obtained based on these drawings without paying creative work.

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

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

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

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

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

[0041] Figure 6 is a schematic diagram of a single-protrusion rotor shape obtained by a specific application example of the rotor design optimization method according to an embodiment of the present invention;

[0042] Figure 7 A schematic diagram of the CFD simulation of the vortex interference position of the rotor shape corresponding to the initial design parameters in a specific application example of an embodiment of the present invention is shown;

[0043] Figure 8 A schematic diagram of the CFD simulation of the vortex interference position of a rotor with a single protrusion in a specific application example of an embodiment of the present invention is shown;

[0044] Fig. 9 A schematic diagram of the CFD simulation of the vortex interference position of a rotor shape with multiple protrusions in a specific application example of an embodiment of the present invention is shown;

[0045] Fig.10It is a schematic diagram of noise calculation results obtained by performing computational fluid dynamics simulation based on initial design parameters, single-protrusion target rotor size, and multi-protrusion target rotor size in a specific application example of the rotor design optimization method according to an embodiment of the present invention;

[0046] Fig.11 It is a schematic diagram of noise detection results obtained by performing actual noise detection based on initial design parameters, a single-protrusion target rotor size, and a multi-protrusion target rotor size in a specific application example of the rotor design optimization method according to an embodiment of the present invention;

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

[0048] Fig.13 It is a schematic diagram of the hardware structure of a computer device according to an embodiment of the present invention. DETAILED DESCRIPTION

[0049] In order to make the purpose, technical solution and advantages of the embodiments of the present invention clearer, the technical solution in the embodiments of the present invention will be clearly and completely described below in conjunction with the drawings in the embodiments of the present invention. Obviously, the described embodiments are part of the embodiments of the present invention, not all of the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by those skilled in the art without creative work are within the scope of protection of the present invention.

[0050] With the development of vehicle technology, flying car technology has also developed rapidly. The rotor design is an important part of the flying car, especially the rotor blade design has a great influence on important parameters such as rotor noise. The rotor noise index directly affects the user experience. Therefore, how to optimize the rotor design to effectively reduce the noise generated by the rotor during the operation of the flying car has become a technical problem that needs to be solved urgently.

[0051] It should be noted here that the above is a specific application scenario description of the rotor design optimization method of an embodiment 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] The embodiments of the present invention provide a rotor design optimization method, device, computer equipment and storage medium. Based on the initial design parameters of the rotor, the blade vortex interference position of the rotor is determined, and based on the chord length characteristics of the rotor within the set range of the blade vortex interference position, a rotor model for characterizing the rotor's external dimensions is constructed. 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 result meets the set noise range. Thus, the effective characteristics of the rotor are quickly extracted, and computational fluid dynamics iterative simulation is performed on the rotor's design parameters with the rotor's noise as the optimization target, and noise reduction optimization is quickly performed, which significantly shortens the iterative update cycle of the design parameters, effectively improves the rotor design efficiency, and significantly improves the noise reduction optimization effect. Effectively solving how to quickly and effectively optimize the design of aircraft rotor parameters has become a technical problem that needs to be solved urgently.

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

[0054] In this embodiment, a rotor design optimization method is provided, which can be used in a computing device such as a computer for designing a flying car rotor. Figure 1 is a flow chart of a rotor design optimization method according to an embodiment of the present invention. Figure 1 As shown, the process includes the following steps:

[0055] Step S101, obtaining initial design parameters of the rotor.

[0056] The initial design parameters mainly consider various factors such as material selection, structural design and aerodynamic performance, and design initial design parameters that meet the rotor usage scenarios.

[0057] In some optional embodiments, the initial design parameters may include: the geometric shape CAD of the rotor, different section chord lengths, installation angle, airfoil, etc.

[0058] Step S102, determining the vortex interference position of the rotor based on the initial design parameters.

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

[0060] Specifically, when the rotor rotates, the moment the free vortex of the leading blade collides with or approaches the succeeding blade, the interaction of the vortices causes a local and drastic change in the aerodynamic load on the succeeding blade. The vortex interference position refers to the specific location where the interference effect occurs. The vortex interference position can be defined as a range, a point at the blade tip, or a set number of points on the blade. In practical applications, it can also be set according to the needs of actual simulation calculations.

[0061] Step S103, constructing a rotor model based on the chord length characteristics of the rotor within the set range of the blade-vortex interference position, where the rotor model is used to characterize the rotor's external dimensions.

[0062] In an optional embodiment, the chord length feature includes the number, size and position of protrusions of the blades of the rotor within a set range of the blade vortex interference position.

[0063] Specifically, in order to ensure the optimization effect of the rotor design parameters, reduce the amount of simulation calculations in the design optimization process, and improve the optimization efficiency, a rotor model can be constructed here for the chord length characteristics of the rotor within the vortex interference position setting range. Specifically, the chord length characteristics of the rotor within the vortex interference position setting range can be parameterized by CAD modeling, and the chord length characteristics are mainly based on the three parameters of the number of raised features Num, the scale of the raised features Len, and the position of the raised features Pos.

[0064] For example, Figure 2 FIG. 2 shows a schematic diagram of the design appearance of a rotor blade with multiple protrusions in an embodiment of the present invention. Figure 2 As shown, the value of the number of raised features Num is 4, the scale Len of the raised feature may refer to the chord length between multiple point pairs on the raised feature, such as L1, L2, L3...Ln, and the position Pos of the raised feature may 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 may be defined as: the distance Rn from the rotor center point to the line connecting the point pair with the longest chord length between multiple point pairs on the raised feature, and specifically, the length of the vertical distance from the rotor center point to the line connecting the point pair may be taken.

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

[0066] In the rotor design optimization method provided by the embodiment of the present invention, the chord length feature includes the number of protrusions, the size of the protrusions, and the position of the protrusions on the rotor blades within the set range of the vortex interference position. Therefore, based on the number of protrusions, the size of the protrusions, and the position of the protrusions on the rotor blades within the set range of the vortex interference position, a rotor model can be constructed, and the rotor can be further subjected to computational fluid dynamics iterative simulation to obtain a target rotor size whose noise calculation result meets the set noise range, thereby making full use of the vortex entanglement dissipation energy between the protrusion features designed on the rotor blades and reducing the noise level of the rotor.

[0067] Step S104, based on the rotor outer dimensions, computational fluid dynamics iterative simulation is performed on the rotor to obtain a target rotor dimension whose noise calculation result meets the set noise range.

[0068] In some optional embodiments, the chord length characteristics of the rotor within the set range of the vortex interference position may be parameterized in step S103. Here, based on the rotor outer dimensions, the process of performing computational fluid dynamics iterative simulation on the rotor is to use multiple parameters of the rotor outer dimensions as variables, and the noise calculation results obtained by performing computational fluid dynamics simulation on the rotor are used as optimization targets. When the noise calculation results meet the set noise range, the values ​​of multiple parameters corresponding to the rotor outer dimensions are recorded, and then the main parameters of the rotor blades are determined as the target rotor dimensions, 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 three parameters of the number of raised features Num, the scale of the raised features Len, and the position of the raised features Pos. A new rotor shape dimension is generated based on each set of parameter values ​​of these three parameters, and then a CFD simulation is performed based on the rotor shape dimension to obtain the corresponding rotor noise simulation result. The noise range can be set to be less than the noise threshold, for example, the noise threshold is 60dBa (decibel).

[0070] Return for further reference Figure 3 , Figure 3 The figure also shows the schematic diagram of the rotor shape during multiple iterations of simulation through different line types. Figure 3 The figure only shows a schematic diagram of the rotor shape obtained by designing a single raised feature on the rotor based on the vortex interference position, and performing computational fluid dynamics iterative simulation on the rotor by changing the scale Len of the raised feature. In actual application, the position of the raised feature can also be adjusted within the set range of the vortex interference position to perform computational fluid dynamics iterative simulation on the rotor. Thus, according to the design requirements, the parameter iteration rules in the simulation process are configured in advance to obtain the target rotor size whose noise calculation results meet the set noise range.

[0071] The rotor design optimization method provided by the embodiment of the present invention determines the vortex interference position of the rotor based on the initial design parameters of the rotor, and constructs a rotor model for characterizing the rotor's external dimensions based on the chord length characteristics of the rotor within the set range of the vortex interference position, and then performs computational fluid dynamics iterative simulation on the rotor based on the rotor's external dimensions to obtain a target rotor size whose noise calculation result meets the set noise range. Thus, the effective features of the rotor are quickly extracted, and computational fluid dynamics iterative simulation is performed on the rotor's design parameters with the rotor's noise as the optimization target, and noise reduction optimization is quickly performed, which significantly shortens the iterative update cycle of the design parameters, effectively improves the rotor design efficiency, and significantly improves the noise reduction optimization effect.

[0072] In this embodiment, a rotor design optimization method is provided, which can be used in a computing device such as a computer for designing a flying car rotor. Figure 4 is a flow chart of another rotor design optimization method according to an embodiment of the present invention. Figure 4 As shown, the process includes the following steps:

[0073] Step S401, obtaining initial design parameters of the rotor.

[0074] For details, please see Figure 1 Step S102 of the illustrated embodiment will not be described in detail here.

[0075] Step S402, determining the vortex interference position of the rotor based on the initial design parameters.

[0076] Specifically, step S402 may include:

[0077] Step S4021, based on the initial design parameters, a computational fluid dynamics simulation is performed on the rotor to obtain a vortex interference position where the vortex interference intensity meets a set intensity range.

[0078] The rotor design optimization method provided by the embodiment of the present invention performs computational fluid dynamics simulation on the rotor based on the initial design parameters to obtain the propeller vortex interference position where the propeller vortex interference intensity meets the set intensity range. Thus, the propeller vortex interference position where the propeller vortex interference intensity meets the set intensity range is effectively located by using the computational fluid dynamics simulation method.

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

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

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

[0082] Step a2, constructing a three-dimensional flow field diagram of the rotor at different speeds based on the pulling force, torque and efficiency. The three-dimensional flow field diagram is a conventional three-dimensional flow field model generated during data processing using a computational fluid dynamics simulation algorithm. Here, the three-dimensional flow field diagram is used to intuitively represent the noise simulation results of the rotor.

[0083] Step a3, judging the rotor vortex interference position according to the three-dimensional flow field diagram.

[0084] Step S403, constructing a rotor model based on the chord length characteristics of the rotor within the set range of the vortex interference position, where the rotor model is used to characterize the rotor's external dimensions.

[0085] For details, please see Figure 1 Step S103 of the illustrated embodiment will not be described in detail here.

[0086] Step S404, based on the rotor outer dimensions, computational fluid dynamics iterative simulation is performed on the rotor to obtain a target rotor dimension whose noise calculation result meets the set noise range.

[0087] Specifically, step S404 may include:

[0088] Step S4041, based on the rotor dimensions, perform computational fluid dynamics simulation on the rotor to determine the noise calculation results corresponding to the rotor dimensions.

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

[0090] Step S4043, based on the rotor outer dimensions corresponding to the adjusted chord length characteristics, computational fluid dynamics simulation is performed on the rotor until a noise calculation result is obtained that meets the target rotor dimensions within a set noise range.

[0091] In an optional embodiment, obtaining a target rotor size whose noise calculation result meets a set noise range includes: obtaining the target rotor size based on the number of protrusions, the protrusion size and the protrusion position using a piecewise cubic Hermite interpolation polynomial.

[0092] Specifically, in step S4042, before the noise calculation result meets the set noise range, the chord length feature is adjusted based on the set rules. The chord length feature includes the number of protrusions, the size of the protrusions and the position of the protrusions on the blades of the rotor within the set range of the vortex interference position. Therefore, when the noise calculation result meets the set noise range, the information obtained is also 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 shape of the rotor blades, for example: it can be shown in a CAD format file. The fitting method here can use a piecewise cubic Hermite interpolation polynomial. Of course, other applicable fitting methods can also be used. The present invention does not make specific limitations on this.

[0093] The rotor design optimization method provided by the embodiment of the present invention performs computational fluid dynamics simulation on the rotor based on the rotor outer dimensions to determine the noise calculation results corresponding to the rotor outer dimensions. Thus, by automatically adjusting the chord length characteristics based on the set rules, and based on the rotor outer dimensions corresponding to the adjusted chord length characteristics, computational fluid dynamics simulation is performed on the rotor until the target rotor dimensions whose noise calculation results meet the set noise range are obtained. With the rotor noise as an effective optimization target, computational fluid dynamics simulation is performed on the rotor to achieve automatic iteration of the rotor outer dimensions, effectively improving the optimization efficiency of the rotor design.

[0094] In this embodiment, a rotor design optimization method is provided, which can be used in a computing device such as a computer for designing a flying car rotor. Figure 5 is a flow chart of a specific application example of the rotor design optimization method according to an embodiment of the present invention. Figure 5 As shown, the process includes the following steps:

[0095] Step S501, obtaining initial design parameters of the rotor.

[0096] Step S502, based on the initial design parameters, CFD simulation calculation is performed to determine the vortex interference position of the rotor.

[0097] Step S503, constructing a rotor model based on the chord length characteristics of the rotor within the set range of the vortex interference position, where the rotor model is used to characterize the rotor's external dimensions.

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

[0099] For example, the position Pos of the raised feature, the number Num of the raised features and the scale Len of the raised features are set, and based on these three parameters, the rotor shape dimensions are parametrically modeled.

[0100] Step S504, executing the CAD script based on the rotor's external dimensions to obtain a rotor CAD model.

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

[0102] Step S505, executing the CFD script to obtain the rotor CFD model.

[0103] For example, an interface for calling a CFD script can be configured here to implement the calling of the CFD script. Here, the rotor CFD model is used to characterize the features of different points on the rotor.

[0104] Step S506, automatically performing CFD simulation calculation for the rotor outer dimensions corresponding to the given convex feature position Pos, the convex feature number Num and the convex feature scale Len to obtain the noise calculation result.

[0105] Step S507, determining whether the noise calculation result meets the set noise range. If the noise calculation result meets the set noise range, executing step S509. If the noise calculation result does not meet the set noise range, executing step S508.

[0106] Step S508, adjusting the position Pos of the convex feature, the number Num of the convex features, and the value of the size Len of the convex feature.

[0107] For example, return to reference Figure 2 and Figure 3 The explanation of the position Pos of the raised feature, the number Num of the raised features and the size Len of the raised features. The values ​​of L1, L2...Ln, the value of Rn, etc. can be adjusted.

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

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

[0110] In an optional embodiment, the number of protrusions is 1. The target rotor size may include the following parameters: the distance between the protrusion position and the rotor center position in the initial design size is a first set multiple of the rotor blade radius, and the protrusion size is a second set multiple of the chord length dimension in the initial design size.

[0111] In an optional embodiment, obtaining a target rotor size whose noise calculation result meets a set noise range includes:

[0112] Based on the number, size and position of the bumps, the target rotor size is obtained by using piecewise cubic Hermite interpolation polynomial.

[0113] Figure 6 The figure shows the schematic diagram of the single-protrusion rotor shape obtained by a specific application example of the rotor design optimization method according to the embodiment of the present invention. Figure 6 The rotor shape shown is the target rotor size of a single protrusion obtained in a specific application example of an embodiment of the present invention. Among them, the distance between the protrusion position and the rotor center position in the initial design size is 0.9 times the radius of the rotor blade, and the protrusion size is 1.227 times the chord length scale in the initial design size. That is, the above-mentioned first setting multiple is 0.9R, and the above-mentioned second setting multiple is 1.227. Specifically, on the blade of a single-protrusion rotor, L2 is used to characterize the scale Len of the protrusion feature, specifically refers to the position with the longest chord length between multiple point pairs on the protrusion feature, and the chord length is L2. Figure 6 The relatively smoother dotted line position without a protrusion shown in the middle dotted line is used to characterize the rotor shape corresponding to the initial design parameters of the rotor. For the protrusion after the rotor optimization design relative to the initial design parameters, each point pair of the protrusion feature has an original point pair. Therefore, L2 and Figure 6 The chord length L shown by the point pair in the initial design parameters corresponding to the middle dashed line 2原 (Because it coincides with L2, Figure 6 The relationship (not shown) is L2 = 1.227*L 2原 The position Pos of the raised feature can be identified based on the blade radius of the rotor. For example, if the blade radius of the rotor is R, the position Pos of the raised feature is a position on the rotor blade that is 0.9R away from the center point of the rotor.

[0114] It should be noted that the values ​​of the first set multiple and the second set multiple can be adjusted according to actual simulation results.

[0115] Figure 7 The schematic diagram of the CFD simulation of the rotor vortex interference position corresponding to the initial design parameters in the specific application example of the embodiment of the present invention is shown. Figure 8 The figure shows a schematic diagram of the CFD simulation of the vortex interference position of the rotor shape with a single protrusion in a specific application example of the embodiment of the present invention. Fig. 9 The schematic diagram of the CFD simulation of the vortex interference position of the rotor shape with multiple protrusions in the specific application example of the embodiment of the present invention is shown. Figure 7 to Figure 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 similar to 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 semicircle-like line and the relatively thick straight line in the middle. It can be clearly seen from the tip vortex that the newly added convex feature divides the tip vortex into multiple distinct ones, such as Figure 7 to Figure 9The visualization of the tip vortex of the same scale in the figure clearly shows that the raised feature adds multiple tip vortices, which is beneficial to reducing the vortex intensity and improving the blade noise.

[0116] Fig.10 FIG. 2 shows a schematic diagram of noise calculation results obtained by computational fluid dynamics simulation based on initial design parameters, single-protrusion target rotor size, and multi-protrusion target rotor size in a specific application example of an embodiment of the present invention. The target rotor size of a single protrusion can be as follows: Figure 6 The single-protrusion rotor shape is shown. The target rotor size of multiple protrusions can be the target rotor size obtained by using the rotor design optimization method provided by the embodiment of the present invention.

[0117] refer to Fig.10 , V3 represents the noise calculation result obtained by computational fluid dynamics simulation based on the target rotor size of a single protrusion. V4 represents the noise calculation result obtained by computational fluid dynamics simulation based on the target rotor size of multiple protrusions. base represents the noise calculation result obtained by computational fluid dynamics simulation based on the initial design parameters. Fig.10 It can be seen that, whether it is a target rotor size based on a single protrusion or a target rotor size based on multiple protrusions, the blade noise after optimization using the rotor design provided by the embodiment of the present 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 21.4dBA relative to the reference blade corresponding to base, and the target rotor shape corresponding to V4 has an average noise reduction of 15.9dBA relative to the reference blade corresponding to base.

[0118] Furthermore, through experimental test analysis and simulation comparison, the noise simulation results obtained by computational fluid dynamics simulation are more accurate for noise calculation within 2000Hz, which can be referred to as above Fig.10 The noise simulation results are shown in FIG. 1 . For noise data above 2000 Hz, the specific application examples of the embodiments of the present invention provide the following Fig.11 The noise detection results obtained by the actual noise detection are shown. Specifically, the target rotor shape corresponding to V3 obtained by the rotor design optimization method provided by the embodiment of the present invention has an average noise reduction of 5.0dBA relative to the reference blade corresponding to base, and the target rotor shape corresponding to V4 has an average noise reduction of 4.9dBA relative to the reference blade corresponding to base.

[0119] The rotor design optimization method provided in an embodiment of the present invention can add a raised feature to the blade tip of a large-sized rotor, and through the blade tip profile plane design, utilize the blade tip vortex coupling or winding dissipation principle formed by the raised feature to significantly reduce the noise level.

[0120] In this embodiment, a rotor design optimization device is also provided, which is used to implement the above-mentioned embodiments and preferred implementation modes, and the descriptions that have been made will not be repeated. As used below, the term "module" can be a combination of software and / or hardware that implements a predetermined function. Although the devices described in the following embodiments are preferably implemented in software, the implementation of hardware, or a combination of software and hardware, is also possible and conceivable.

[0121] This embodiment provides a rotor design optimization device, such as Fig.12 As shown, including:

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

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

[0124] A construction module 1203 is used to construct a rotor model based on the chord length characteristics of the rotor within the set range of the blade-vortex interference position, and the rotor model is used to characterize the rotor's external dimensions;

[0125] The simulation module 1204 is used to perform computational fluid dynamics iterative simulation on the rotor based on the rotor's external dimensions, and obtain a target rotor dimension whose noise calculation result meets the set noise range.

[0126] In an 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 initial design parameters to obtain a propeller vortex interference position where the propeller vortex interference intensity meets a set intensity range.

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

[0129] A calculation subunit, used to calculate the thrust, torque and efficiency of the rotor at different rotation speeds based on the initial design parameters;

[0130] A three-dimensional construction subunit is used to construct a three-dimensional flow field diagram of the rotor at different speeds according to the thrust, torque and efficiency;

[0131] The judgment subunit is used to judge the vortex interference position of the rotor according to the three-dimensional flow field diagram.

[0132] In an optional implementation, the simulation module 1204 includes:

[0133] A noise unit is used to perform computational fluid dynamics simulation on the rotor based on the rotor dimensions to determine the noise calculation results corresponding to the rotor dimensions;

[0134] An adjustment unit, used for adjusting the chord length characteristic based on a set rule 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 size corresponding to the adjusted chord length feature, until the noise calculation result is obtained to meet the target rotor size within the set noise range.

[0136] In an optional embodiment, the chord length feature includes the number, size and position of protrusions of the blades of the rotor within a set range of the blade vortex interference position.

[0137] In an optional embodiment, 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 dimension is a first set multiple of the rotor blade radius; the protrusion dimension is a second set multiple of the chord length dimension in the initial design dimension.

[0139] In an optional embodiment, obtaining a target rotor size whose noise calculation result meets a set noise range includes:

[0140] Based on the number, size and position of the bumps, the target rotor size is obtained by using piecewise cubic Hermite interpolation polynomial.

[0141] The further functional description of each of the above modules and units is the same as that of the above corresponding embodiments and will not be repeated here.

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

[0143] The embodiment of the present invention also provides a computer device having the above Fig.12 The rotor design optimization device shown.

[0144] See also Fig.13 , Fig.13 is a schematic diagram of the structure of a computer device provided by an optional embodiment of the present invention, such as Fig.13As shown, the computer device includes: one or more processors 10, a memory 20, and interfaces for connecting various components, including high-speed interfaces and low-speed interfaces. Various components are connected to each other using different buses for communication, and can be installed on a common mainboard or installed in other ways as needed. The processor can process the instructions executed in the computer device, including instructions stored in or on the memory to display the graphical information of the GUI on an external input / output device (such as, a display device coupled to the interface). In some optional embodiments, if necessary, multiple processors and / or multiple buses can be used together with multiple memories and multiple memories. Similarly, multiple computer devices can be connected, and each device provides some necessary operations (for example, as a server array, a group of blade servers, or a multi-processor system). Fig.13 A processor 10 is taken as an example.

[0145] The processor 10 may be a central processing unit, a network processor or a combination thereof. The processor 10 may further include a hardware chip. The hardware chip may be a dedicated integrated circuit, a programmable logic device or a combination thereof. The programmable logic device may be a complex programmable logic device, a field programmable gate array, a general purpose array logic or any combination thereof.

[0146] The memory 20 stores instructions executable by at least one processor 10, so that at least one processor 10 executes the method shown in the above embodiment.

[0147] The memory 20 may include a program storage area and a data storage area, wherein the program storage area may store an operating system, an application required for at least one function; the data storage area may store data created according to the use of the computer device, etc. In addition, the memory 20 may include a high-speed random access memory, and may also include a non-transient memory, such as at least one disk storage device, a flash memory device, or other non-transient solid-state storage device. In some optional embodiments, the memory 20 may optionally include a memory remotely arranged relative to the processor 10, and these remote memories may be connected to the computer device via a network. Examples of the above-mentioned network include, but are not limited to, the Internet, an intranet, a local area network, a mobile communication network, and combinations thereof.

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

[0149] The computer device further comprises a communication interface 30 for the computer device to communicate with other devices or a communication network.

[0150] The embodiment of the present invention also provides a computer-readable storage medium. The method according to the embodiment of the present invention can be implemented in hardware, firmware, or can be implemented as a computer code that can be recorded in a storage medium, or can be implemented as a computer code that is originally stored in a remote storage medium or a non-temporary machine-readable storage medium and will be stored in a local storage medium through a network download, so that the method described herein can be stored in such software processing on a storage medium using a general-purpose computer, a dedicated processor, or programmable or dedicated hardware. Among them, the storage medium can be a magnetic disk, an optical disk, a read-only storage memory, a random access memory, a flash memory, a hard disk or a solid-state hard disk, etc.; further, the storage medium can also include a combination of the above types of memories. It can be understood that a computer, a processor, a microprocessor controller, or programmable hardware includes a storage component that can store or receive software or computer code. When the software or computer code is accessed and executed by a computer, a processor, or hardware, the method shown in the above embodiment is implemented.

[0151] A part of the present invention may be applied as a computer program product, such as a computer program instruction, which, when executed by a computer, can call or provide the method and / or technical solution according to the present invention through the operation of the computer. Those skilled in the art should understand that the existence of the computer program instruction in a computer-readable medium includes, but is not limited to, a source file, an executable file, an installation package file, etc., and accordingly, the way in which the computer program instruction is executed by the computer includes, but is not limited to: the computer directly executes the instruction, or the computer compiles the instruction and then executes the corresponding compiled program, or the computer reads and executes the instruction, or the computer reads and installs the instruction and then executes the corresponding installed program. Here, the computer-readable medium may be any available computer-readable storage medium or communication medium accessible to the computer.

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

Claims

1. A rotor design optimization method, characterized in that: The method comprises: Obtaining initial design parameters of the rotor; Based on the initial design parameters, determining a vortex interference position of the rotor; Based on the chord length characteristics of the rotor within the set range of the blade vortex interference position, a rotor model is constructed, wherein the rotor model is used to characterize the rotor shape dimensions; Based on the rotor outer dimensions, computational fluid dynamics iterative simulation is performed on the rotor to obtain a target rotor dimension whose noise calculation result meets the set noise range.

2. The method according to claim 1, characterized in that The step of determining the propeller-vortex interference position based on the initial design parameters includes: Based on the initial design parameters, computational fluid dynamics simulation is performed on the rotor to obtain a blade vortex interference position where the blade vortex interference intensity meets a set intensity range.

3. The method according to claim 1, characterized in that The performing computational fluid dynamics simulation on the rotor comprises: Based on the initial design parameters, calculating the thrust, torque and efficiency of the rotor at different rotation speeds; Constructing a three-dimensional flow field diagram of the rotor at different speeds according to the pulling force, the torque and the efficiency; The vortex interference position of the rotor is determined according to the three-dimensional flow field diagram.

4. The method according to claim 1, characterized in that: The performing computational fluid dynamics iterative simulation on the rotor comprises: Based on the rotor dimensions, performing computational fluid dynamics simulation on the rotor to determine noise calculation results corresponding to the rotor dimensions; Before the noise calculation result meets the set noise range, adjusting the chord length feature based on a set rule; Based on the rotor outer dimensions corresponding to the adjusted chord length characteristics, computational fluid dynamics simulation is performed on the rotor until a target rotor dimension is obtained whose noise calculation result meets the set noise range.

5. The method according to any one of claims 1 to 4, characterized in that The chord length characteristics include the number, size and position of protrusions of the rotor blades within the vortex interference position setting range.

6. The method according to claim 5, characterized in that The number of protrusions is 1; The target rotor size includes: the distance between the protrusion position and the rotor center position in the initial design size is a first set multiple of the rotor blade radius; the protrusion size is a second set multiple of the chord length scale in the initial design size.

7. The method according to claim 5, characterized in that The noise calculation result obtained is consistent with the target rotor size within the set noise range, including: Based on the number of protrusions, the protrusion size and the protrusion position, the target rotor size is obtained by using a piecewise cubic Hermite interpolation polynomial.

8. A rotor design optimization device, characterized in that: The device comprises: An acquisition module, used to obtain initial design parameters of the rotor; A position determination module, used to determine the vortex interference position of the rotor based on the initial design parameters; A construction module, used to construct a rotor model based on the chord length characteristics of the rotor within the set range of the blade vortex interference position, wherein the rotor model is used to characterize the rotor shape size; The simulation module is used to perform computational fluid dynamics iterative simulation on the rotor based on the rotor shape size, so as to obtain a target rotor size whose noise calculation result meets the set noise range.

9. A computer device, characterized in that: include: A memory and a processor, wherein the memory and the processor are communicatively connected to each other, the memory stores computer instructions, and the processor executes the rotor design optimization method according to any one of claims 1 to 7 by executing the computer instructions.

10. A computer-readable storage medium, characterized in that: The computer-readable storage medium stores computer instructions, and the computer instructions are used to enable a computer to execute the rotor design optimization method according to any one of claims 1 to 7.

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