Propeller design method and system based on dynamic and static blade circulation distribution matching

Abstract

The invention discloses a propeller design method and system based on dynamic and static blade circulation distribution matching. The method comprises the steps that design parameters are obtained; on the basis of the design parameters, the maximum thrust needed by the oblique flow type combined propeller is obtained; based on the maximum thrust, constructing a first moving blade radial circulation distribution model; based on the first moving blade radial circulation distribution model, constructing a moving and static blade circulation distribution matching model along an oblique flow surface; and on the basis of the dynamic and static blade circular rector distribution matching model, geometric parameters of the propeller are obtained. By combining the fluid dynamics theory and experimental data, the method has the advantages that a matching model of dynamic and static blade circulation distribution, collaborative optimization of the dynamic and static blades, a dynamic adjustment mechanism and the like are innovatively constructed.

Description

Technical Field

[0001] The present invention belongs to the field of ship propellers, and particularly relates to a propeller design method and system based on the matching of the circulation distributions of static and moving blades. Background Art

[0002] In order to improve the energy conservation and environmental protection effects of ships and ensure the physical and mental health of crew members, during the design process of ship propellers, the propulsion efficiency should be increased as much as possible, and the abnormal hull vibrations that may be generated by the ship propellers should be controlled. The diagonal-flow combined propeller includes static blades and moving blades, and the above purposes can be achieved through the matching design of the static and moving blades. However, the quality of the design scheme highly depends on the experience accumulated by designers, and usually a large number of simulation simulations are required after the scheme is designed, and even costly physical tests need to be carried out. Therefore, it not only requires the long-term practical accumulation of designers, but also requires a large amount of human and material resources.

[0003] The current ship propeller blade circulation design method mainly realizes the design purpose by controlling the circulation distribution at different radii of the propeller blades, and cannot match the distribution of the velocity circulation of the static and moving blades, which is not conducive to improving the propulsion efficiency and controlling abnormal vibrations of the combined propeller with the structures of the static and moving blades. A large number of simulations and related tests are required for the optimization work after the design, resulting in an increase and waste of time and resources. Summary of the Invention

[0004] In view of the defects existing in the above-mentioned prior art, the present invention provides a propeller design method based on the matching of the circulation distributions of static and moving blades, including the following steps: Step S101, obtaining design parameters; Step S103, based on the design parameters, obtaining the maximum thrust required for the diagonal-flow combined propeller; Step S105, based on the maximum thrust, constructing a first moving blade radial circulation distribution model; Step S107, based on the first moving blade radial circulation distribution model, constructing a static and moving blade circulation distribution matching model along the diagonal-flow surface; Step S109, based on the static and moving blade circulation distribution matching model, obtaining the geometric parameters of the propeller.

[0005] Among them, the design parameters at least include the rated power P, the rated speed n, the maximum speed V, and the moving blade diameter D.

[0006] Among them, the maximum thrust F in the step S103 can be calculated by the following formula: , where P is the power, V is the maximum speed, and 0.7 and 0.9 are efficiency coefficients, respectively considering the mechanical efficiency and the flow efficiency.

[0007] Among them, the step S103 further includes: obtaining the maximum circulation according to the maximum thrust , where the maximum circulation is the sum of the circulations of the stationary and moving blades, represents the water density.

[0008] Among them, the step S105 includes: Step S1051: Based on the maximum thrust, construct a second moving blade radial circulation distribution model; Step S1053: Based on the design parameters, obtain the adjustment term of the moving blade radial circulation distribution model; Step S1055: Based on the second moving blade radial circulation distribution model and the adjustment term of the moving blade radial circulation distribution model, obtain the first moving blade radial circulation distribution model.

[0009] Among them, the matching model of the stationary and moving blade circulation distributions along the diagonal flow surface is calculated using the following formula: , where represents the circulation, i represents a certain diagonal flow surface along the radial direction, is represents a certain diagonal flow surface along the stationary blade radial direction, id represents a certain diagonal flow surface along the moving blade radial direction, where is and id refer to the corresponding diagonal flow surfaces, and g represents the proportionality coefficient, .

[0010] Among them, the step S109 includes: Based on the circulation distributions of the stationary and moving blades, and the geometric characteristic quantities of the pitch and camber at their respective radii, the three-dimensional coordinates of the thruster are obtained.

[0011] Among them, the method further includes performing grid discretization, numerical design, and numerical solution using numerical methods according to the geometric parameters of the diagonal flow type combined thruster and the operating condition requirements in the design parameters, so as to perform thruster simulation.

[0012] Among them, the method further includes returning to step S101 or step S105 for improvement if the thruster design does not meet the requirements until it meets the requirements.

[0013] The present invention also proposes a thruster design method based on the matching of the stationary and moving blade circulation distributions, including: A design parameter acquisition module, which is used to acquire design parameters; A maximum thrust calculation module, which is used to obtain the required maximum thrust of the diagonal flow type combined thruster based on the design parameters; A first moving blade radial circulation distribution model construction module, which is used to construct a first moving blade radial circulation distribution model based on the maximum thrust; A matching model construction module for the static and moving blade circulation distributions, which is used to construct a matching model for the static and moving blade circulation distributions along the diagonal flow surface based on the first moving blade radial circulation distribution model; A thruster geometric parameter estimation module, which is used to obtain the thruster geometric parameters based on the matching model for the static and moving blade circulation distributions.

[0014] Compared with the prior art, the present invention has the following advantages: By combining fluid dynamics theory with experimental data, a matching model for the static and moving blade circulation distributions is innovatively constructed. This method ensures the scientificity and practicality of the design and improves the accuracy of the model.

[0015] Emphasize the synergistic effect of the static and moving blades rather than individual optimization. This systematic thinking makes the design more comprehensive and can consider the thrust characteristics of the moving blade and the flow guiding ability of the static blade simultaneously.

[0016] Introduce a dynamic adjustment mechanism to adjust the design parameters of the static blade in real time according to the real-time flow field changes and performance feedback. This adaptive design improves the performance stability of the thruster under different working conditions.

[0017] Use advanced computational fluid dynamics (CFD) tools for accurate simulation, which can predict the flow characteristics and performance at the design stage. This innovation significantly reduces the test cost and time.

[0018] By optimizing the static blade design, a vibration suppression strategy is innovatively introduced, reducing the vibration amplitude of the moving blade and improving the reliability and service life of the thruster.

[0019] Adopt a multi-objective optimization method to simultaneously improve the propulsion efficiency, reduce pulsation, and suppress vibration. This innovative idea makes the design objectives more comprehensive and enhances the overall performance of the thruster.

[0020] By establishing a verification and feedback mechanism, a closed-loop between the design and the actual performance is achieved. This mechanism can continuously optimize the design process and ensure the high efficiency and reliability of the thruster in actual applications. Description of the Drawings

[0021] By referring to the accompanying drawings and reading the following detailed description, the above and other objects, features, and advantages of the exemplary embodiments of the present disclosure will become easily understood. In the drawings, several embodiments of the present disclosure are shown in an exemplary and non-limiting manner, and the same or corresponding reference numerals represent the same or corresponding parts, wherein: Figure 1 It is a flowchart of the method for matching the velocity circulation distributions of the static and moving blades of an diagonal flow type combined thruster provided by an embodiment of the present invention.

[0022] Figure 2Schematic diagram of an axial - flow type combined thruster provided by an embodiment of the present invention.

[0023] Figure 3 Schematic diagram of an axial - flow surface at a certain radius of the axial - flow type combined thruster provided by an embodiment of the present invention.

[0024] Figure 4 Schematic diagram of the profiles of stationary and moving blades on the axial - flow surface at a certain radius of the axial - flow type combined thruster provided by an embodiment of the present invention.

[0025] Wherein, 1 - stationary blade, 2 - moving blade, 3 - hub, 4 - axial - flow surface on the hub surface, 5 - axial - flow surface at a certain radius, 6 - profile of the stationary blade on the axial - flow surface at a certain radius, 7 - profile of the moving blade on the axial - flow surface at a certain radius. Detailed implementation manners

[0026] In order to make the objectives, technical solutions and advantages of the present invention clearer, the present invention will be further described in detail below with reference to the accompanying drawings. Obviously, the described embodiments are only a part of the embodiments of the present invention, rather than all of them. Based on the embodiments of the present invention, all other embodiments obtained by those of ordinary skill in the art without creative efforts shall fall within the scope of protection of the present invention.

[0027] The terms used in the embodiments of the present invention are only for the purpose of describing specific embodiments, and are not intended to limit the present invention. The singular forms of "a", "the" and "said" used in the embodiments of the present invention and the appended claims are also intended to include the plural forms, unless the context clearly indicates otherwise. "Plural" generally includes at least two.

[0028] It should be understood that although the terms first, second, third, etc. may be used in the embodiments of the present invention to describe..., these... should not be limited to these terms. These terms are only used to distinguish.... For example, without departing from the scope of the embodiments of the present invention, the first... may also be referred to as the second..., and similarly, the second... may also be referred to as the first....

[0029] It should be understood that the term " / " used herein is only a description of the association relationship between associated objects, indicating that there can be three relationships. For example, A and / or B can represent: A exists alone, A and B exist simultaneously, and B exists alone. In addition, the character " / " herein generally represents an "or" relationship between the associated objects before and after.

[0030] Depending on the context, as used herein, the words "if" and "when" may be interpreted as "when" or "while" or "in response to determining" or "in response to detecting". Similarly, depending on the context, the phrase "if determined" or "if detecting (stated condition or event)" may be interpreted as "when determined" or "in response to determining" or "when detecting (stated condition or event)" or "in response to detecting (stated condition or event)".

[0031] It should also be noted that the term "comprising", "including" or any other variant thereof is intended to cover non-exclusive inclusion, such that a commodity or device comprising a series of elements includes not only those elements but also other elements not expressly listed, or elements inherent to such commodity or device. Without further limitation, an element defined by the statement "comprising an..." does not exclude the presence of additional identical elements in the commodity or device comprising said element.

[0032] The optional embodiments of the present invention will be described in detail below with reference to the accompanying drawings.

[0033] Embodiment 1 As Figure 1 shown, the present invention discloses a propeller design method based on the matching of the circumferential velocity distribution of moving and static blades, comprising the following steps: Step S101, obtaining design parameters; Step S103, based on the design parameters, obtaining the maximum thrust required for an axial-flow type combined propeller; Step S105, based on the maximum thrust, constructing a first radial circumferential velocity distribution model of the moving blade; Step S107, based on the first radial circumferential velocity distribution model of the moving blade, constructing a matching model of the circumferential velocity distribution of moving and static blades along the axial-flow surface; Step S109, based on the matching model of the circumferential velocity distribution of moving and static blades, obtaining the geometric parameters of the propeller.

[0034] Embodiment 2 A propeller design method based on the matching of the circumferential velocity distribution of moving and static blades proposed by the present invention, comprising the following steps: Step S101, obtaining design parameters; Step S103, based on the design parameters, obtaining the maximum thrust required for an axial-flow type combined propeller; Step S105, based on the maximum thrust, constructing a first radial circumferential velocity distribution model of the moving blade; Step S107, based on the first radial circumferential velocity distribution model of the moving blade, constructing a matching model of the circumferential velocity distribution of moving and static blades along the axial-flow surface; Step S109: Based on the static and dynamic blade circulation distribution matching model, obtain the geometric parameters of the thruster.

[0035] Among them, the design parameters at least include the rated power P, the rated speed n, the maximum speed V, and the diameter D of the moving blade.

[0036] The design parameters also include the spatial layout size, which refers to the overall size configuration of the thruster, including the relative positions and diameters of the static and moving blades, etc. It affects the flow characteristics of the fluid in the thruster and the overall performance.

[0037] Among them, the maximum thrust F in step S103 can be calculated by the following formula: , where P is the power, V is the maximum speed, and 0.7 and 0.9 are efficiency coefficients, which respectively consider the mechanical efficiency and the flow efficiency.

[0038] Among them, step S103 also includes: obtaining the maximum circulation according to the maximum thrust , where the maximum circulation is the sum of the circulations of the static and moving blades, represents the water density.

[0039] Among them, step S105 includes: Step S1051: Based on the maximum thrust, construct the second radial circulation distribution model of the moving blade; Step S1053: Based on the design parameters, obtain the adjustment term of the radial circulation distribution model of the moving blade; Step S1055: Based on the second radial circulation distribution model of the moving blade and the adjustment term of the radial circulation distribution model of the moving blade, obtain the first radial circulation distribution model of the moving blade.

[0040] Among them, the second radial circulation distribution model of the moving blade is calculated by the following formula: , where is a normalization coefficient to ensure that the sum of the circulation distributions of the moving blade within the entire radius range is equal to the maximum circulation, represents the circulation of the moving blade at the radius r, C(r) represents the conventional term that is a polynomial relationship with the radius of the moving blade of the thruster, and its form is , c i is the polynomial coefficient; m is the highest power of the polynomial; k is the conventional coefficient, and its value range is from -256 to 256; n is the exponent, and its value range is from -10 to 10. According to specific design requirements and flow characteristics, select appropriate values of k and n to ensure that the circulation distribution of the moving blade meets the performance requirements.

[0041] Among them, the adjustment term of the radial circulation distribution model of the moving blade is calculated by the following formula : , where a represents the normal vector at a radius r, b represents the normal vector of an adjacent point, and f is an adjustment coefficient with a range from -1 to 1. According to the magnitude of A(r), the value of f is adjusted. If the result of A(r) is large, then f should be close to 0; if the result of A(r) is small, then f should be close to -1 or 1.

[0042] The first moving blade radial circulation distribution model is calculated using the following formula: .

[0043] Among them, the stator-rotor blade circulation distribution matching model along the diagonal flow surface is calculated using the following formula: , where represents the circulation, i represents a certain diagonal flow surface along the radial direction, is represents a certain diagonal flow surface along the stator blade radial direction, id represents a certain diagonal flow surface along the moving blade radial direction, where is and id refer to the corresponding diagonal flow surfaces, and g represents the proportionality coefficient. .

[0044] Among them, the step S109 includes: based on the circulation distribution of the stator and rotor blades, the geometric characteristic quantities of the pitch and camber at their respective radii, so as to obtain the three-dimensional coordinates of the thruster.

[0045] In a certain embodiment, according to the circulation distribution of the stator and rotor blades, the pitch can be calculated by the ship speed V and the rotational speed n , where V is the ship speed and n is the rotational speed.

[0046] The camber can be deduced from the geometric shape of the blade and the circulation distribution, usually involving the boundary conditions and physical properties of the flow.

[0047] Through the above calculations, the geometric characteristic quantities of the thruster at each radius can be obtained, including the pitch P, camber, blade thickness, and blade width.

[0048] According to the calculated geometric characteristic quantities, a three-dimensional coordinate system of the thruster can be established. The specific steps are as follows: Select a reference plane to determine the installation plane or reference plane of the thruster.

[0049] Establish a coordinate system and set the origin, x, y, and z axis directions of the three-dimensional coordinate system.

[0050] Draw the blades and draw the contours of the stator and rotor blades in the coordinate system according to the calculated pitch and camber.

[0051] Wherein, the method further includes performing grid discretization, numerical design, and numerical solution using numerical methods according to the operating condition requirements in the geometric parameters and design parameters of the diagonal flow type combined propeller, so as to perform propeller simulation.

[0052] In one embodiment, the geometric parameters include the diameter, number of blades, pitch, camber, blade thickness, etc. of the propeller. These parameters are the basis for designing the propeller.

[0053] The design parameters relate to the operating conditions, such as the ship speed, rotational speed, properties of the working fluid (such as density and viscosity), etc.

[0054] Grid discretization: In numerical simulation, the computational domain is divided into multiple small units (grids) for numerical calculation. The quality of the grid directly affects the accuracy and convergence of the calculation results. Structured grids or unstructured grids can be selected, depending on the geometry and complexity of the propeller.

[0055] Among them, numerical design includes selecting numerical methods. Select appropriate numerical methods to solve the hydrodynamic equations. Commonly used methods include the finite difference method, the finite element method, and the computational fluid dynamics (CFD) method. Select an appropriate physical model (such as a laminar or turbulent model) according to the flow characteristics to describe the fluid behavior.

[0056] Among them, in numerical solution, the Navier-Stokes equations are solved by numerical methods to calculate the flow characteristics of the fluid around the propeller. Set reasonable boundary conditions (such as the no-slip condition, inlet and outlet conditions) to ensure the accuracy of the calculation.

[0057] Analyze information such as flow characteristics, pressure distribution, and velocity field from the flow field data obtained by numerical solution. Calculate the thrust, efficiency, and other performance indicators of the propeller to evaluate its performance under given conditions. According to the simulation results, adjust the geometric parameters and design parameters, perform multiple iterative optimizations to improve the performance of the propeller. Compare the numerical simulation results with the experimental data to verify the accuracy and reliability of the numerical model.

[0058] Wherein, the method further includes returning to step S101 or step S105 for improvement if the propeller design does not meet the requirements until it meets the requirements.

[0059] Here, according to the requirements of indicators such as rapidity and acoustics preset in the early stage, compare the simulation results with the indicator requirements to judge whether the performance indicator design of the propeller meets the standards; If the requirements are not met, return and adjust the design parameters or adjust the dynamic blade radial circulation distribution model.

[0060] Embodiment 3 The present invention also provides a thruster design system based on the matching of the circulation distributions of the moving and static blades, including: a design parameter acquisition module configured to acquire design parameters; a maximum thrust calculation module configured to obtain the maximum thrust required for a diagonal flow combined thruster based on the design parameters; a first moving blade radial circulation distribution model construction module configured to construct a first moving blade radial circulation distribution model based on the maximum thrust; a moving and static blade circulation distribution matching model construction module configured to construct a moving and static blade circulation distribution matching model along the diagonal flow surface based on the first moving blade radial circulation distribution model; a thruster geometric parameter estimation module configured to obtain the geometric parameters of the thruster based on the moving and static blade circulation distribution matching model.

[0061] Example 4 An embodiment of the present disclosure provides a non-volatile computer storage medium storing computer-executable instructions that can execute the method steps as described in the above embodiments.

[0062] It should be noted that the above computer-readable medium in the present disclosure may be a computer-readable signal medium, a computer-readable storage medium, or any combination of the two. A computer-readable storage medium may be, for example, but not limited to, an electrical, magnetic, optical, electromagnetic, infrared, or semiconductor system, apparatus, or device, or any combination of the above. More specific examples of the computer-readable storage medium may include, but are not limited to: an electrical connection having one or more wires, a portable computer disk, a hard disk, a random access memory (RAM), a read-only memory (ROM), an erasable programmable read-only memory (EPROM or flash memory), an optical fiber, a portable compact disk read-only memory (CD-ROM), an optical storage device, a magnetic storage device, or any suitable combination of the above. In the present disclosure, the computer-readable storage medium may be any tangible medium that contains or stores a program, which can be used by or in conjunction with an instruction execution system, apparatus, or device. In the present disclosure, the computer-readable signal medium may include a data signal propagated in a baseband or as part of a carrier wave, which carries computer-readable program code. Such a propagated data signal may take various forms, including but not limited to electromagnetic signals, optical signals, or any suitable combination of the above. The computer-readable signal medium may also be any computer-readable medium other than the computer-readable storage medium, which can send, propagate, or transmit a program for use by or in conjunction with an instruction execution system, apparatus, or device. The program code contained on the computer-readable medium may be transmitted using any appropriate medium, including but not limited to: wires, optical cables, RF (radio frequency), etc., or any suitable combination of the above.

[0063] The above computer-readable medium may be included in the above electronic device; or it may exist separately without being assembled into the electronic device.

[0064] The computer program code for performing the operations of the present disclosure may be written in one or more programming languages or combinations thereof. The above programming languages include object-oriented programming languages such as Java, Smalltalk, C++, and also include conventional procedural programming languages such as the "C" language or similar programming languages. The program code may be executed entirely on the user's computer, partially on the user's computer, executed as an independent software package, partially on the user's computer and partially on a remote computer, or entirely on a remote computer or server. In the case of a remote computer, the remote computer may be connected to the user's computer through any type of network, including a local area network (LAN) or a wide area network (WAN), or it may be connected to an external computer (for example, by using an Internet service provider to connect through the Internet).

[0065] The flowcharts and block diagrams in the accompanying drawings illustrate the possible architectures, functions, and operations of systems, methods, and computer program products according to various embodiments of the present disclosure. In this regard, each block in the flowchart or block diagram may represent a module, a segment of a program, or a part of code that contains one or more executable instructions for implementing a specified logical function. It should also be noted that in some alternative implementations, the functions denoted in the blocks may occur in an order different from that denoted in the accompanying drawings. For example, two consecutive blocks shown may actually be executed substantially in parallel, or they may sometimes be executed in the reverse order, depending on the functions involved. It should also be noted that each block in the block diagram and / or flowchart, and combinations of blocks in the block diagram and / or flowchart, can be implemented by a dedicated hardware-based system that performs the specified functions or operations, or can be implemented by a combination of dedicated hardware and computer instructions.

[0066] The units described in the embodiments of the present disclosure can be implemented in software or in hardware. In some cases, the name of the unit does not constitute a limitation on the unit itself.

[0067] The preferred embodiments of the present invention are described above to make the spirit of the present invention clearer and easier to understand, and are not intended to limit the present invention. Any modifications, substitutions, and improvements made within the spirit and principles of the present invention shall be included within the protection scope defined by the appended claims of the present invention.

Claims

1. A propeller design method based on the matching of the circulation distribution of static and moving blades, characterized in that, It includes the following steps: Step S101: Obtain design parameters; Step S103: Based on the design parameters, obtain the maximum thrust required for the diagonal flow type combined propeller; Step S105: Based on the maximum thrust, construct the first moving blade radial circulation distribution model; Step S107: Based on the first moving blade radial circulation distribution model, construct the static and moving blade circulation distribution matching model along the diagonal flow surface; Step S109: Based on the static and moving blade circulation distribution matching model, obtain the geometric parameters of the propeller.

2. The method according to claim 1, wherein The design parameters at least include the rated power P, the rated speed n, the maximum speed V, and the moving blade diameter D.

3. The method according to claim 2, wherein In step S103, the maximum thrust F can be calculated by the following formula: , where P is the power, V is the maximum speed, and 0.7 and 0.9 are efficiency coefficients that respectively account for mechanical efficiency and flow efficiency.

4. The method according to claim 3, wherein The step S103 further includes: obtaining the maximum circulation according to the maximum thrust , wherein the maximum circulation is the sum of the circulations of the stationary and moving blades, represents the water density.

5. The method according to claim 1, wherein Step S105 includes: Step S1051: Based on the maximum thrust, construct the second moving blade radial circulation distribution model; Step S1053: Based on the design parameters, obtain the adjustment term of the moving blade radial circulation distribution model; Step S1055: Based on the second moving blade radial circulation distribution model and the adjustment term of the moving blade radial circulation distribution model, obtain the first moving blade radial circulation distribution model.

6. The method according to claim 1, wherein The static and moving blade circulation distribution matching model along the diagonal flow surface is calculated by the following formula: , where represents circulation, i represents a certain diagonal flow surface along the radial direction, is represents a certain diagonal flow surface along the radial direction of the stator blade, id represents a certain diagonal flow surface along the radial direction of the rotor blade, where is and id refer to the corresponding diagonal flow surfaces, and g represents a proportionality coefficient. .

7. The method according to claim 1, wherein Step S109 includes: Based on the circulation distribution of the static and moving blades, the geometric characteristic quantities of the pitch and camber at their respective radii, so as to obtain the three-dimensional coordinates of the propeller.

8. The method according to claim 1, wherein The method further includes performing grid discretization, numerical design, and numerical solution by numerical methods according to the geometric parameters of the diagonal flow type combined propeller and the operating condition requirements in the design parameters, so as to perform propeller simulation.

9. The method according to claim 1, wherein The method further includes if the propeller design does not meet the requirements, then return to step S101 or step S105 for improvement until it meets the requirements.

10. A propeller design system based on the matching of the circulation distributions of static and moving blades, including A design parameter acquisition module, which is used to acquire design parameters; A maximum thrust calculation module, which is used to obtain the maximum thrust required for the diagonal flow type combined propeller based on the design parameters; A first moving blade radial circulation distribution model construction module, which is used to construct the first moving blade radial circulation distribution model based on the maximum thrust; A static and moving blade circulation distribution matching model construction module, which is used to construct the static and moving blade circulation distribution matching model along the diagonal flow surface based on the first moving blade radial circulation distribution model; A propeller geometric parameter estimation module, which is used to obtain the geometric parameters of the propeller based on the static and moving blade circulation distribution matching model.

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