Annular propeller modeling method and device, modeling equipment and storage medium

Abstract

The invention relates to an annular propeller modeling method and device, modeling equipment and a storage medium, and belongs to the technical field of ship propellors.The annular propeller modeling method comprises the steps that a water flow direction serves as a first coordinate axis, and the radial direction of a first blade serves as a second coordinate axis; a propeller hub center under a corresponding first coordinate axis coordinate when the transition section of the first propeller blade and the second propeller blade reaches the maximum radius of the propeller is used as an original point, a third coordinate axis is determined based on a right-hand rule, a three-dimensional coordinate system is established, and the first propeller blade and the second propeller blade are two different propeller blades; under the three-dimensional coordinate system, the thickness angle of each paddle is determined based on the rotating shaft of the two-dimensional airfoil profile of each paddle, and the inflow angle of each paddle is determined based on the thickness angle of each paddle; and modeling the annular propeller based on the thickness angle and the inflow angle of each blade. According to the method, tip smooth transition and section geometric parameter control of the annular propeller are realized on the premise of relatively low calculation complexity.

Description

Technical Field

[0001] The present invention relates to the technical field of ship propellers, and in particular, to a method, device, modeling equipment and storage medium for modeling an annular propeller. Background Art

[0002] When a propeller works underwater, due to the leakage of the tip vortices of the propeller, serious hydrodynamic noise will be generated. In recent years, a new type of annular propeller has received wide attention due to its good tip vortex suppression ability. The annular propeller has a smooth transition at the blade tip through an annular structure, reduces the flow from the pressure surface to the suction surface of the propeller, thereby suppressing the generation of tip vortices, reducing flow noise, and improving the propulsion efficiency. It has certain significance in noise reduction, energy conservation and improving the stealth ability of underwater vehicles.

[0003] Since the annular propeller has a more complex shape than the conventional propeller, there is less research on its geometric mathematical modeling method at the present stage. When applying the conventional propeller modeling scheme to the annular propeller, the computational complexity is relatively high, and it is difficult to achieve smooth transition at the tip of the annular propeller and control of the sectional geometric parameters. Summary of the Invention

[0004] In view of this, it is necessary to provide a method, device, modeling equipment and storage medium for modeling an annular propeller to solve the problems that when the conventional propeller modeling scheme is applied to the annular propeller, the computational complexity is relatively high, and it is difficult to achieve smooth transition at the tip of the annular propeller and control of the sectional geometric parameters.

[0005] To solve the above problems, in a first aspect, the present invention provides a method for modeling an annular propeller, including: Taking the water flow direction as the first coordinate axis, the radial direction of the first blade as the second coordinate axis, and the hub center at the coordinate of the first coordinate axis corresponding to the transition section of the first blade and the second blade reaching the maximum radius of the propeller as the origin, determining the third coordinate axis based on the right-hand rule, and establishing a three-dimensional coordinate system, where the first blade and the second blade are two different blades; In the three-dimensional coordinate system, based on the rotation axis of the two-dimensional airfoil section of each blade, determining the thickness angle of each blade, and based on the thickness angle of each blade, determining the inflow angle of each blade; Based on the thickness angle and inflow angle of each blade, perform modeling of the annular propeller.

[0006] In a possible implementation manner, the determining the thickness angle of each blade based on the rotation axis of the two-dimensional airfoil section of each blade includes: Determine the angle between the rotation axis and the two-dimensional airfoil section of each blade as the thickness angle of each blade, and determine the thickness angle vector of each blade based on the coordinate difference between the three-dimensional coordinate points of the leading edge and the trailing edge of the two-dimensional airfoil section of each blade.

[0007] In a possible implementation manner, the determining the inflow angle of each blade based on the thickness angle of each blade includes: Determine the coordinate difference between the three-dimensional coordinate point corresponding to the upper surface point at 0.5 times the chord length and the three-dimensional coordinate point corresponding to the lower surface point at 0.5 times the chord length in the two-dimensional airfoil section of each blade as the mid-section vector of each blade; Perform a vector product operation on the thickness angle vector and the mid-section vector of each blade to obtain the inflow angle vector of each blade.

[0008] In a possible implementation manner, the method further includes: Before performing the annular propeller modeling based on the thickness angle and the inflow angle of each blade, determine the chord midpoint of the two-dimensional airfoil section of each blade as the blade surface reference point of each blade, and determine the preset discrete points of each blade on the chord of the two-dimensional airfoil section of each blade based on the preset parameters and the blade surface reference point of each blade; Determine the control points of each blade based on the preset discrete points of each blade.

[0009] In a possible implementation manner, the determining the preset discrete points of each blade on the chord of the two-dimensional airfoil section of each blade based on the preset parameters and the blade surface reference point of each blade includes: Determine the two-dimensional coordinates of the preset discrete points of each blade on the two-dimensional airfoil section based on the preset parameters and the two-dimensional coordinates of the blade surface reference point of each blade on the two-dimensional airfoil section; The determining the control points of each blade based on the preset discrete points of each blade includes: Determine the two-dimensional coordinates of the control points of each blade on the two-dimensional airfoil section based on the two-dimensional coordinates of the preset discrete points of each blade on the two-dimensional airfoil section; Convert the two-dimensional coordinates of the control points of each blade on the two-dimensional airfoil section into three-dimensional coordinates based on the skew angle corresponding to the control points of each blade in the three-dimensional coordinate system.

[0010] In a possible implementation manner, the converting the two-dimensional coordinates of the control points of each blade on the two-dimensional airfoil section into three-dimensional coordinates based on the skew angle corresponding to the control points of each blade in the three-dimensional coordinate system includes: Convert the two-dimensional coordinates of the control points of each blade on the two-dimensional airfoil section into three-dimensional coordinates based on the skew angle corresponding to the control points of each blade in the three-dimensional coordinate system and the ordinate of the control points of each blade on the two-dimensional airfoil section.

[0011] In a possible implementation, the annular propeller modeling based on the thickness angle and the inflow angle of each blade includes: Determine a first set of three-dimensional point coordinates based on the control point coordinates of each blade and the Rodriguez rotation matrix corresponding to the thickness angle of each blade; Determine a second set of three-dimensional point coordinates based on the first set of three-dimensional point coordinates and the Rodriguez rotation matrix corresponding to the inflow angle of each blade; Perform annular propeller modeling based on the second set of three-dimensional point coordinates.

[0012] On the other hand, the present invention also provides an annular propeller modeling device, including: A building module, which uses the water flow direction as the first coordinate axis, the radial direction of the first blade as the second coordinate axis, and the hub center at the coordinate of the first coordinate axis corresponding to the transition section of the first blade and the second blade reaching the maximum radius of the propeller as the origin, and determines the third coordinate axis based on the right-hand rule to establish a three-dimensional coordinate system, where the first blade and the second blade are two different blades; A determination module, which, under the three-dimensional coordinate system, determines the thickness angle of each blade based on the rotation axis of the two-dimensional airfoil section of each blade, and determines the inflow angle of each blade based on the thickness angle of each blade; A modeling module, which performs annular propeller modeling based on the thickness angle and the inflow angle of each blade.

[0013] In a second aspect, the present invention also provides a modeling device, including a memory and a processor, where The memory is used to store a program; The processor is coupled to the memory and is used to execute the program stored in the memory to implement the steps in the annular propeller modeling method described in any of the above implementations.

[0014] In a third aspect, the present invention also provides a computer-readable storage medium for storing computer-readable programs or instructions, and when the programs or instructions are executed by a processor, they can implement the steps in the annular propeller modeling method described in any of the above implementations.

[0015] The beneficial effects of the present invention are as follows: The annular propeller modeling method, device, modeling equipment, and storage medium provided by the present invention first establish a three-dimensional coordinate system different from that in conventional propeller modeling to ensure the continuity of modeling. Then, the specific thickness at the tip of the blade during transition is determined by the thickness angle, and the ability of the blade to rotate around the vertical axis of the profile at the tip is enhanced by the inflow angle. Finally, based on the thickness angle and inflow angle of each blade, annular propeller modeling is carried out, avoiding complex calculations during the annular propeller modeling process. The present invention realizes smooth transition at the tip of the annular propeller and control of profile geometric parameters under the premise of low computational complexity. BRIEF DESCRIPTION OF THE DRAWINGS

[0016] Figure 1 Schematic flowchart of an embodiment of the annular propeller modeling method provided by the present invention; Figure 2 Schematic flowchart of an embodiment of the annular propeller modeling process provided by the present invention; Figure 3 Schematic diagram of an embodiment of the three-dimensional parameter definition of the annular propeller provided by the present invention; Figure 4 Schematic diagram of an embodiment of the two-dimensional airfoil profile parameter definition of the annular propeller provided by the present invention; Figure 5 Schematic diagram of an embodiment of the airfoil profile parameter definition of the front and rear blades of the annular propeller provided by the present invention; Figure 6 Schematic diagram of an embodiment of the blade stagger angle definition of the annular propeller provided by the present invention; Figure 7 Schematic diagram of an embodiment of the axis distance definition of the annular propeller provided by the present invention; Figure 8 Schematic diagram of an embodiment of the profile control point definition provided by the present invention; Figure 9 Schematic diagram of an embodiment of the thickness angle definition provided by the present invention; Figure 10 Schematic diagram of an embodiment of the inflow angle definition provided by the present invention; Figure 11 Schematic structural diagram of an embodiment of the annular propeller modeling device provided by the present invention; Figure 12 Schematic structural diagram of an embodiment of the modeling equipment provided by the present invention. DETAILED DESCRIPTION OF THE EMBODIMENTS

[0017] Next, the technical solutions in the embodiments of the present invention will be clearly and completely described in conjunction with the accompanying drawings in the embodiments of the present invention. Obviously, the described embodiments are only a part of the embodiments of the present invention, rather than all of the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by those skilled in the art without creative efforts fall within the protection scope of the present invention.

[0018] In the description of the embodiments of the present invention, unless otherwise specified, the meaning of "a plurality" is two or more. "And / or" describes the association relationship of associated objects, indicating that there can be three relationships, for example: A and / or B can represent three situations: A exists alone, A and B exist simultaneously, and B exists alone.

[0019] The descriptions such as "first" and "second" involved in the embodiments of the present invention are only for descriptive purposes, and cannot be understood as indicating or implying their relative importance or implicitly indicating the quantity of the indicated technical features. Therefore, the technical features defined with "first" and "second" may explicitly or implicitly include at least one such feature.

[0020] Referring to "embodiments" herein means that the specific features, structures, or characteristics described in connection with the embodiments may be included in at least one embodiment of the present invention. The phrase appears in various places in the specification does not necessarily refer to the same embodiment, nor is it an independent or alternative embodiment mutually exclusive with other embodiments. Those skilled in the art explicitly and implicitly understand that the embodiments described herein may be combined with other embodiments.

[0021] Before presenting the embodiments, the following terms are explained first.

[0022] Annular propeller: The blades of the annular propeller are connected in a ring shape to form a closed structure, thereby reducing the eddy currents and turbulence at the blade tips and reducing energy losses. Eddy currents are generated at the blade tips of traditional propellers, resulting in energy losses and noise. The annular design improves efficiency by eliminating these tip eddy currents.

[0023] The following explains some parameters of the annular propeller.

[0024] Blade diameter: The distance from the blade tip to the center of rotation.

[0025] Number of blades: The total number of blades on the propeller.

[0026] Hub diameter: The diameter of the central part where the blades are connected.

[0027] Chord length: The straight-line distance from the leading edge to the trailing edge of the airfoil in the two-dimensional airfoil section of the propeller.

[0028] Thickness: The maximum vertical distance between the upper and lower surfaces of the airfoil in the two-dimensional airfoil section of the propeller.

[0029] Camber: The maximum height of the mean camber line of the airfoil in the two-dimensional airfoil section of the propeller, reflecting the degree of curvature.

[0030] Pitch angle: When the propeller rotates, the angle between the airfoil section and the rotation plane.

[0031] Skew angle: The lateral inclination angle of the airfoil section relative to the rotation axis.

[0032] Dip angle: The longitudinal inclination angle of the airfoil section relative to the rotation axis.

[0033] The present invention provides a method, device, modeling equipment and storage medium for annular propeller modeling, which will be described separately below.

[0034] Figure 1 It is a schematic flowchart of an embodiment of the annular propeller modeling method provided by the present invention. As Figure 1 shown, the annular propeller modeling method includes: S101. Taking the water flow direction as the first coordinate axis, the radial direction of the first blade as the second coordinate axis, and the hub center at the corresponding first coordinate axis coordinate when the transition section of the first blade and the second blade reaches the maximum radius of the propeller as the origin, determining the third coordinate axis based on the right-hand rule, and establishing a three-dimensional coordinate system. The first blade and the second blade are two different blades.

[0035] It should be noted that: in addition to taking the water flow direction as the first coordinate axis, it can also be the air flow direction (for example, when modeling the annular propeller in a ground environment) as the first coordinate axis. The present invention will be described below by taking the modeling of a ship annular propeller as an example. The first coordinate axis, the second coordinate axis and the third coordinate axis respectively correspond to the x-axis, y-axis and z-axis in the three-dimensional coordinate system. The transition section of the blade refers to the part where the cross-sectional shape of the blade gradually changes from the root to the tip. By establishing a three-dimensional coordinate system different from that in conventional propeller modeling, the present invention ensures the continuity of modeling.

[0036] S102. Under the three-dimensional coordinate system, based on the rotation axis of the two-dimensional airfoil section of each blade, determining the thickness angle of each blade, and based on the thickness angle of each blade, determining the inflow angle of each blade.

[0037] It should be noted that: in order to achieve the smooth transition of the tip of the annular propeller and the control of the sectional geometric parameters, the present invention first determines the thickness angle of each blade through the rotation axis of the two-dimensional airfoil section of each blade, so as to determine the specific thickness when the blade makes a transition at the tip. Then, the inflow angle of each blade is determined through the thickness angle of each blade to enhance the ability of the blade to rotate along the vertical axis of the section at the tip.

[0038] S103. Perform annular propeller modeling based on the thickness angle and inflow angle of each blade.

[0039] It should be noted that: after determining the thickness angle and inflow angle of each blade, the three-dimensional point coordinate set of the annular propeller blade can be determined according to the thickness angle and inflow angle of each blade, and then used for annular propeller modeling. For example, the three-dimensional point coordinate set of the annular propeller blade can be exported as a.dat file, and then imported into UG software for three-dimensional modeling. Spline curves are generated through points, and then surface patches of the annular propeller are generated according to the curve grid. Then, a closed surface is established at the front and rear blade roots, and after being stitched into a solid as a whole, all blades are arrayed along the x-axis according to the defined number of blades, and the hub solid is imported, and the output is a three-dimensional solid file of the annular propeller. It can be understood that in addition to performing three-dimensional modeling through UG software, other software can also be used for modeling.

[0040] In summary, the annular propeller modeling method provided by the embodiments of the present invention first establishes a three-dimensional coordinate system different from that in conventional propeller modeling to ensure the continuity of modeling. Then, the specific thickness of the blade during the transition at the tip is determined through the thickness angle, and the ability of the blade to rotate along the vertical direction of the section at the tip is enhanced through the inflow angle. Finally, annular propeller modeling is performed according to the thickness angle and inflow angle of each blade, avoiding complex operations in the process of annular propeller modeling. The present invention realizes the smooth transition of the tip of the annular propeller and the control of sectional geometric parameters on the premise of relatively low computational complexity.

[0041] In some embodiments of the present invention, in combination with Figure 2 viewed, the modeling process of the annular propeller mainly includes a mathematical calculation process and a modeling process. The technical solution of the present invention mainly aims at the mathematical calculation process, and this process includes: 1. Determination of three-dimensional geometric parameters of the annular propeller.

[0042] The annular propeller is divided into front and rear double blades (i.e., the first blade and the second blade, which will not be elaborated later) for modeling, and the three-dimensional parameters of the annular propeller are determined respectively. In combination with Figure 3 viewed, the three-dimensional geometric parameters of the annular propeller include blade diameter , number of blades , hub diameter .

[0043] 2. Determination of two-dimensional blade section parameters of the annular propeller.

[0044] Determine the specific parameters of the two-dimensional airfoil section of the front propeller and the rear propeller. In combination with Figure 4 viewed, the two-dimensional blade section parameters of the annular propeller include chord length , thickness , camber , pitch angle , skew angle , trim angle , trim value , skew value .

[0045] Among them, the relationship between the trim value and the trim angle is: ; the relationship between the skew value and the skew angle is: ; is the radius amplitude of this section.

[0046] The thickness of the blade section is divided into the back thickness and the face thickness , and the relationship with the thickness and camber is: , .

[0047] 3. Calculation of the three-dimensional point sets of the front and rear blades of the annular propeller.

[0048] (1) Considering Figure 5 , the three-dimensional coordinates of a conventional propeller are defined with the hub center as the coordinate origin, the flow direction of the propeller as the x-axis, the radial direction of the first blade as the y-axis, and the z-axis determined by the right-hand rule. The coordinate origin definition of the present invention is different from that of the conventional propeller. The coordinate origin of the annular propeller is located at the hub center corresponding to the same x-coordinate when the transition section between the front and rear blades of the annular propeller reaches the maximum radius of the propeller. According to this definition, the skew angle and trim angle of the front blade section of the annular propeller and those of the rear blade section are one positive and one negative, and the skew angle and trim angle of the blade tip sections of the front and rear blades are both 0.

[0049] (2) Considering Figure 6 , the stagger angle of the annular propeller is defined as the absolute value of the maximum difference between the skew angles of the front and rear blades, and the expression is: .

[0050] Considering Figure 7 , the shaft pitch of the annular propeller is defined as the sum of the trim values calculated from the trim angles of the root sections of the front and rear blades, and the expression is: .

[0051] (3) In some embodiments of the present invention, the method further includes: Before performing annular propeller modeling based on the thickness angle and inflow angle of each blade, the midpoint of the chord line of the two-dimensional airfoil section of each blade is determined as the blade surface reference point of each blade, and based on the preset parameters and the blade surface reference point of each blade, preset discrete points of each blade are determined on the chord line of the two-dimensional airfoil section of each blade; Based on the preset discrete points of each blade, the control points of each blade are determined.

[0052] Specifically, the midpoint of the profile chord line is the blade surface reference point, and the three-dimensional connection line of all blade surface reference points of the propeller is the blade surface reference line. The calculation of the control points is based on the relative positions of the blade surface reference points. According to the preset parameters, discrete points are taken at equal intervals along the chord line of the two-dimensional planar airfoil section, and perpendicular lines to the chord line are made to intersect with the airfoil surface to obtain the control points of the corresponding airfoil.

[0053] In some embodiments of the present invention, the determining the preset discrete points of each blade on the chord line of the two-dimensional airfoil section of each blade based on the preset parameters and the blade surface reference point of each blade includes: Based on the preset parameters and the two-dimensional coordinates of the blade surface reference point of each blade on the two-dimensional airfoil section, the two-dimensional coordinates of the preset discrete points of each blade on the two-dimensional airfoil section are determined; The determining the control points of each blade based on the preset discrete points of each blade includes: Based on the two-dimensional coordinates of the preset discrete points of each blade on the two-dimensional airfoil section, the two-dimensional coordinates of the control points of each blade on the two-dimensional airfoil section are determined; Based on the skew angle corresponding to the control points of each blade in the three-dimensional coordinate system, the two-dimensional coordinates of the control points of each blade on the two-dimensional airfoil section are converted into three-dimensional coordinates.

[0054] Specifically, combined with Figure 8 to see, assuming is the blade surface reference point of a certain radius section of the propeller, is the discrete point on the chord line, and the distance is 0.25C, is the blade back control point of the section.

[0055] Through coordinates calculate to obtain coordinates , and then calculate to obtain coordinates , and then convert the planar coordinates into three-dimensional coordinates.

[0056] In some embodiments of the present invention, converting the two-dimensional coordinates of the control point of each blade on the two-dimensional airfoil section into three-dimensional coordinates based on the skew angle corresponding to the control point of each blade in the three-dimensional coordinate system includes: Converting the two-dimensional coordinates of the control point of each blade on the two-dimensional airfoil section into three-dimensional coordinates based on the skew angle corresponding to the control point of each blade in the three-dimensional coordinate system and the vertical coordinate of the control point of each blade on the two-dimensional airfoil section.

[0057] Specifically, when converting the two-dimensional coordinates of the control point of each blade on the two-dimensional airfoil section into three-dimensional coordinates, first calculate the skew angle corresponding to the control point in the three-dimensional coordinate system, and then convert the two-dimensional coordinates of the control point on the two-dimensional airfoil section into three-dimensional coordinates according to the vertical coordinate of the control point on the two-dimensional airfoil section.

[0058] Taking the above control point as an example:

[0059]

[0060]

[0061]

[0062] That is, the three-dimensional coordinates of the control point are .

[0063] In some embodiments of the present invention, determining the thickness angle of each blade based on the rotation axis of the two-dimensional airfoil section of each blade includes: Determining the angle between the rotation axis of the two-dimensional airfoil section of each blade and the two-dimensional airfoil section as the thickness angle of each blade, and determining the thickness angle vector of each blade based on the coordinate difference between the three-dimensional coordinate point of the leading edge and the three-dimensional coordinate point of the trailing edge of the two-dimensional airfoil section of each blade.

[0064] Specifically, in combination with Figure 9 it can be seen that in order to achieve the rotation of the tip section and thus achieve the geometric modeling of the annular propeller tip with thickness through mathematical methods, the present invention defines the thickness angle vector of each section as the difference between the three-dimensional coordinate point of the leading edge and the three-dimensional coordinate point of the trailing edge of the section, which is the rotation axis of the section. To achieve smooth thickness transition at the tip, the thickness angle of the front propeller tip section is defined as 90°, the thickness angle near the tip rapidly increases from 0° to 90°, and for the rear propeller, due to the different rotation directions, it is the negative value of the thickness angle of the front propeller, thus ensuring the smoothness of the propeller.

[0065] In some embodiments of the present invention, determining the inflow angle of each blade based on the thickness angle of each blade includes: In the two-dimensional airfoil section of each blade, the coordinate difference between the three-dimensional coordinate point corresponding to the upper surface point at 0.5 times the chord length and the three-dimensional coordinate point corresponding to the lower surface point at 0.5 times the chord length is determined as the mid-section vector of each blade; Perform a vector product operation on the thickness angle vector and the mid-section vector of each blade to obtain the inflow angle vector of each blade.

[0066] Specifically, combined with Figure 10 Looking at it, in order to enhance the ability of the blade to rotate about the vertical axis of the section at the tip, the inflow angle is introduced. First, the mid-section vector is determined, which is the vector obtained by subtracting the three-dimensional coordinates corresponding to the lower surface point at 0.5 times the chord length from the three-dimensional coordinates corresponding to the upper surface point at 0.5 times the chord length of each section. Then, the thickness angle vector is cross-multiplied with the mid-section vector to obtain the inflow angle vector. Its physical meaning is perpendicular to the above two vectors, that is, the inflow angle vector is a vector perpendicular to the section. The rotation of the three-dimensional point coordinates of the section around this vector realizes different inflow angles at the tip of the annular propeller. To ensure smoothness, the inflow angle of the front blade tip section is defined as the maximum value, and for the rear blade, due to the different rotation directions, it is the negative value of the inflow angle of the front blade. This parameter realizes the lateral rotation of the tip section along the propeller, changes the inflow angle at the tip during the rotation of the propeller, and increases the flexibility of the annular propeller modeling.

[0067] In some embodiments of the present invention, the modeling of the annular propeller based on the thickness angle and the inflow angle of each blade includes: Determine the first set of three-dimensional point coordinates based on the control point coordinates of each blade and the Rodriguez rotation matrix corresponding to the thickness angle of each blade; Determine the second set of three-dimensional point coordinates based on the first set of three-dimensional point coordinates and the Rodriguez rotation matrix corresponding to the inflow angle of each blade; Perform annular propeller modeling based on the second set of three-dimensional point coordinates.

[0068] Specifically, first, the three-dimensional point coordinate set 1 can be obtained according to the control point coordinates of each blade, and then the three-dimensional point coordinate set 1 is multiplied by the Rodriguez rotation matrix corresponding to the thickness angle of each blade through matrix multiplication operation to obtain the three-dimensional coordinate point set 2 (i.e., the first set of three-dimensional point coordinates). The specific calculation formula is as follows:

[0069] Among them, represents the thickness angle, and the corresponding thickness angle vector is .

[0070] Perform matrix multiplication on the three-dimensional point coordinate set 2 and the Rodriguez rotation matrix corresponding to the inflow angle of each blade to obtain the three-dimensional coordinate point set 3 (i.e., the second three-dimensional point coordinate set). The specific calculation formula is as follows:

[0071] Wherein, represents the inflow angle, and the corresponding thickness angle vector is .

[0072] Use the three-dimensional point coordinate set 3 as the final three-dimensional point coordinate set of the annular propeller for subsequent annular propeller modeling.

[0073] Based on the modeling method of the conventional propeller, using the propeller geometric parameters defined by the conventional propeller, and further introducing the thickness angle and the inflow angle to achieve smooth transition at the tip of the annular propeller and control of the profile geometric parameters. As an optimization of the conventional propeller modeling method, the mathematical derivation is simpler and easier to understand, and the computational complexity is lower.

[0074] In order to better implement the annular propeller modeling method in the embodiments of the present invention, correspondingly, on the basis of the annular propeller modeling method, as Figure 11 shown, the embodiments of the present invention also provide an annular propeller modeling device. The annular propeller modeling device 1100 includes: A building module 1101, configured to establish a three-dimensional coordinate system with the water flow direction as the first coordinate axis, the radial direction of the first blade as the second coordinate axis, and the hub center at the coordinate of the first coordinate axis when the transition profile of the first blade and the second blade reaches the maximum radius of the propeller as the origin, and determine the third coordinate axis based on the right-hand rule. The first blade and the second blade are two different blades; A determination module 1102, configured to determine the thickness angle of each blade based on the rotation axis of the two-dimensional airfoil profile of each blade in the three-dimensional coordinate system, and determine the inflow angle of each blade based on the thickness angle of each blade; A modeling module 1103, configured to perform annular propeller modeling based on the thickness angle and the inflow angle of each blade.

[0075] The above-described annular propeller modeling device 1100 provided in the above embodiments can implement the technical solutions described in the above embodiments of the annular propeller modeling method. The specific implementation principles of the above modules or units can be referred to the corresponding content in the above embodiments of the annular propeller modeling method, and will not be elaborated here.

[0076] As Figure 12 shown, the present invention also correspondingly provides a modeling device 1200. The modeling device 1200 includes a processor 1201, a memory 1202, and a display 1203. Figure 12Only some components of the modeling device 1200 are shown, but it should be understood that it is not necessary to implement all the shown components, and more or fewer components can be alternatively implemented.

[0077] In some embodiments, the processor 1201 can be a central processing unit (CPU), a microprocessor, or other data processing chips, which are used to run the program code stored in the memory 1202 or process data, such as the magnetic resonance image optimization method in the present invention.

[0078] In some embodiments, the processor 1201 can be a single server or a server group. The server group can be centralized or distributed. In some embodiments, the processor 1201 can be local or remote. In some embodiments, the processor 1201 can be implemented on a cloud platform. In one embodiment, the cloud platform can include a private cloud, a public cloud, a hybrid cloud, a community cloud, a distributed cloud, an internal cloud, a multi-cloud, etc., or any combination of the above.

[0079] In some embodiments, the memory 1202 can be an internal storage unit of the modeling device 1200, such as the hard disk or memory of the modeling device 1200. In some other embodiments, the memory 1202 can also be an external storage device of the modeling device 1200, such as a plug-in hard disk, a smart media card (SMC), a secure digital (SD) card, a flash card, etc. equipped on the modeling device 1200.

[0080] Furthermore, the memory 1202 can also include both the internal storage unit and the external storage device of the modeling device 1200. The memory 1202 is used to store the application software installed in the modeling device 1200 and various types of data.

[0081] In some embodiments, the display 1203 can be an LED display, a liquid crystal display, a touch liquid crystal display, an organic light-emitting diode (OLED) toucher, etc. The display 1203 is used to display the information in the modeling device 1200 and to display a visual user interface. The components 1201 - 1203 of the modeling device 1200 communicate with each other through a system bus.

[0082] In one embodiment, when the processor 1201 executes the annular propeller modeling program in the memory 1202, the following steps can be implemented: Taking the water flow direction as the first coordinate axis, the radial direction of the first blade as the second coordinate axis, and the hub center at the coordinate of the first coordinate axis corresponding to the transition section of the first blade and the second blade reaching the maximum radius of the propeller as the origin, the third coordinate axis is determined based on the right-hand rule to establish a three-dimensional coordinate system. The first blade and the second blade are two different blades; Under the three-dimensional coordinate system, based on the rotation axis of the two-dimensional airfoil section of each blade, the thickness angle of each blade is determined, and based on the thickness angle of each blade, the inflow angle of each blade is determined; Based on the thickness angle and the inflow angle of each blade, an annular propeller is modeled.

[0083] It should be understood that when the processor 1201 executes the annular propeller modeling program in the memory 1202, in addition to the above functions, other functions can also be realized. For details, please refer to the description of the corresponding method embodiments above.

[0084] Furthermore, the type of the modeling device 1200 mentioned in the embodiments of the present invention is not specifically limited. The modeling device 1200 can be a portable electronic device such as a mobile phone, a tablet computer, a personal digital assistant (PDA), a wearable device, a laptop computer, etc. Exemplary embodiments of the portable electronic device include, but are not limited to, portable electronic devices equipped with IOS, android, microsoft or other operating systems. The above portable electronic device can also be other portable electronic devices, such as a laptop computer with a touch-sensitive surface (such as a touch panel). It should also be understood that in some other embodiments of the present invention, the modeling device 1200 may not be a portable electronic device, but a desktop computer with a touch-sensitive surface (such as a touch panel).

[0085] Correspondingly, an embodiment of the present application further provides a computer-readable storage medium, which is used to store a computer-readable program or instruction. When the program or instruction is executed by a processor, the steps or functions in the annular propeller modeling method provided by the above method embodiments can be realized.

[0086] Those skilled in the art can understand that all or part of the processes of implementing the methods in the above embodiments can be completed by instructing relevant hardware (such as a processor, a controller, etc.) through a computer program. The computer program can be stored in a computer-readable storage medium. Among them, the computer-readable storage medium is a disk, an optical disc, a read-only memory or a random access memory, etc.

[0087] The above has introduced in detail the annular propeller modeling method, device, modeling equipment and storage medium provided by the present invention. Specific examples are used in this article to elaborate on the principle and implementation manner of the present invention. The description of the above embodiments is only used to help understand the method and its core idea of the present invention; at the same time, for those skilled in the art, according to the idea of the present invention, there will be changes in the specific implementation manner and application scope. In summary, the content of this specification should not be construed as a limitation to the present invention.

Claims

1. A method for modeling an annular propeller, characterized in that: include: The water flow direction is taken as the first coordinate axis, the radial direction of the first blade is taken as the second coordinate axis, the hub center under the coordinate of the first coordinate axis corresponding to when the transition section between the first blade and the second blade reaches the maximum radius of the propeller is taken as the origin, the third coordinate axis is determined based on the right-hand rule, and a three-dimensional coordinate system is established, where the first blade and the second blade are two different blades; In a three-dimensional coordinate system, based on the rotation axis of the two-dimensional airfoil section of each blade, a thickness angle of each blade is determined, and based on the thickness angle of each blade, an inflow angle of each blade is determined; The annular propeller is modeled based on the thickness angle and inflow angle of each blade.

2. The annular propeller modeling method according to claim 1, characterized in that: The step of determining the thickness angle of each blade based on the rotation axis of the two-dimensional airfoil section of each blade comprises: The angle between the rotation axis of the two-dimensional airfoil section of each blade and the two-dimensional airfoil section is determined as the thickness angle of each blade, and the thickness angle vector of each blade is determined based on the coordinate difference between the three-dimensional coordinate point of the leading edge and the three-dimensional coordinate point of the trailing edge of the two-dimensional airfoil section of each blade.

3. The annular propeller modeling method according to claim 2, characterized in that: The step of determining the inflow angle of each blade based on the thickness angle of each blade comprises: The coordinate difference between the three-dimensional coordinate point corresponding to the upper surface point at 0.5 times the chord length and the three-dimensional coordinate point corresponding to the lower surface point at 0.5 times the chord length in the two-dimensional airfoil section of each blade is determined as the mid-section vector of each blade; The vector product operation is performed on the thickness angle vector and the mid-section vector of each blade to obtain the inflow angle vector of each blade.

4. The annular propeller modeling method according to claim 1, characterized in that: The method further comprises: Before modeling the annular propeller based on the thickness angle and the inflow angle of each blade, a midpoint of the chord line of the two-dimensional airfoil section of each blade is determined as a blade surface reference point of each blade, and a preset discrete point of each blade is determined on the chord line of the two-dimensional airfoil section of each blade based on preset parameters and the blade surface reference point of each blade; Based on the preset discrete points of each blade, the control point of each blade is determined.

5. The annular propeller modeling method according to claim 4, characterized in that: The step of determining a preset discrete point of each blade on a chord line of a two-dimensional airfoil section of each blade based on preset parameters and a blade surface reference point of each blade comprises: Based on the preset parameters and the two-dimensional coordinates of the blade surface reference point of each blade on the two-dimensional airfoil section, determine the two-dimensional coordinates of the preset discrete points of each blade on the two-dimensional airfoil section; The step of determining the control point of each blade based on the preset discrete points of each blade includes: Determine the two-dimensional coordinates of the control point of each blade on the two-dimensional airfoil section based on the two-dimensional coordinates of the preset discrete points of each blade on the two-dimensional airfoil section; Based on the side inclination angle corresponding to the control point of each blade in the three-dimensional coordinate system, the two-dimensional coordinates of the control point of each blade on the two-dimensional airfoil section are converted into three-dimensional coordinates.

6. The annular propeller modeling method according to claim 5, characterized in that: The step of converting the two-dimensional coordinates of the control point of each blade on the two-dimensional airfoil section into three-dimensional coordinates based on the side inclination angle corresponding to the control point of each blade in the three-dimensional coordinate system includes: Based on the side inclination angle corresponding to the control point of each blade in the three-dimensional coordinate system and the longitudinal coordinate of the control point of each blade on the two-dimensional airfoil section, the two-dimensional coordinates of the control point of each blade on the two-dimensional airfoil section are converted into three-dimensional coordinates.

7. The annular propeller modeling method according to claim 4, characterized in that: The annular propeller modeling is performed based on the thickness angle and the inflow angle of each blade, including: Determine a first three-dimensional point coordinate set based on the control point coordinates of each blade and the Rodriguez rotation matrix corresponding to the thickness angle of each blade; Determine a second three-dimensional point coordinate set based on the first three-dimensional point coordinate set and the Rodriguez rotation matrix corresponding to the inflow angle of each blade; Based on the second three-dimensional point coordinate set, annular propeller modeling is performed.

8. A ring propeller modeling device, characterized in that: include: Establish a module, which is used to use the water flow direction as the first coordinate axis, the radial direction of the first blade as the second coordinate axis, the hub center under the coordinate of the first coordinate axis corresponding to when the transition section between the first blade and the second blade reaches the maximum radius of the propeller as the origin, determine the third coordinate axis based on the right-hand rule, and establish a three-dimensional coordinate system, where the first blade and the second blade are two different blades; A determination module, for determining a thickness angle of each blade based on a rotation axis of a two-dimensional airfoil section of each blade in a three-dimensional coordinate system, and determining an inflow angle of each blade based on the thickness angle of each blade; Modeling module for modeling annular propellers based on the thickness angle and inflow angle of each blade.

9. A modeling device, characterized in that: comprising a memory and a processor, wherein: The memory is used to store programs; The processor is coupled to the memory and is used to execute the program stored in the memory to implement the steps in the annular propeller modeling method described in any one of claims 1 to 7.

10. A computer-readable storage medium, characterized in that: Used to store computer-readable programs or instructions, which, when executed by a processor, can implement the steps in the annular propeller modeling method described in any one of claims 1 to 7.

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