A propeller design method and system based on the matching of the annular distribution of dynamic and static blades

Abstract

The present invention discloses a propeller design method and system based on matching the circulation distribution of moving and stationary blades. The method comprises: obtaining design parameters; obtaining the maximum thrust required for a diagonal flow type combined propeller based on the design parameters; constructing a first moving blade radial circulation distribution model based on the maximum thrust; constructing a matching model for the circulation distribution of moving and stationary blades along the diagonal flow surface based on the first moving blade radial circulation distribution model; and obtaining the propeller geometric parameters based on the matching model for the circulation distribution of moving and stationary blades. By combining fluid dynamics theory with experimental data, the present invention innovatively constructs a matching model for the circulation distribution of moving and stationary blades, achieves coordinated optimization of moving and stationary blades, and provides a dynamic adjustment mechanism.

Description

Technical Field

[0001] The present invention belongs to the field of ship propulsion, and in particular relates to a propeller design method and system based on the matching of the circulation distribution of dynamic and static blades. Background Art

[0002] To improve ship energy conservation and environmental protection, and safeguard the health of crew members, the design process for ship propulsion systems should prioritize propulsion efficiency and control any abnormal hull vibrations that may be generated by the propulsion system. Diagonal flow combined propulsion systems, which incorporate both stationary and rotating blades, achieve this goal through a well-matched design. However, the quality of a design depends heavily on the designer's accumulated experience, and often requires extensive simulations and even costly physical testing. This requires not only extensive practical experience but also significant human and material resources.

[0003] The current design method of the circulation of ship propeller blades mainly achieves the design purpose by controlling the circulation distribution at different radii of the propeller blades. It is unable to match the distribution of the velocity circulation of the moving and static blades. It is not conducive to improving the propulsion efficiency and controlling abnormal vibration of the combined propeller with moving and static blades. The post-design optimization work requires a large number of simulations and related experiments, resulting in an increase and waste of time and resources. Summary of the Invention

[0004] In view of the above-mentioned defects in the prior art, the present invention provides a propeller design method based on the matching of the circulation distribution of the moving and stationary blades, comprising the following steps:

[0005] Step S101, obtaining design parameters;

[0006] Step S103: obtaining the maximum thrust required by the diagonal flow combined propeller based on the design parameters;

[0007] Step S105: constructing a radial circulation distribution model of the first rotor blade based on the maximum thrust;

[0008] Step S107: constructing a matching model for the circulation distribution of moving and stationary blades along the oblique flow surface based on the first moving blade radial circulation distribution model;

[0009] Step S109: obtaining the propeller geometric parameters based on the dynamic and static blade circulation distribution matching model.

[0010] The design parameters include at least rated power P, rated speed n, maximum speed V and rotor blade diameter D.

[0011] The maximum thrust F in step S103 can be calculated using the following formula:

[0012] , where P is power, V is maximum speed, and 0.7 and 0.9 are efficiency coefficients, which take into account mechanical efficiency and flow efficiency, respectively.

[0013] 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 moving and stationary blades, Indicates the density of water.

[0014] Wherein, the step S105 includes:

[0015] Step S1051: constructing a radial circulation distribution model of the second rotor blade based on the maximum thrust;

[0016] Step S1053: obtaining an adjustment item of a rotor blade radial circulation distribution model based on the design parameters;

[0017] Step S1055: Obtain a first rotor blade radial circulation distribution model based on the second rotor blade radial circulation distribution model and the rotor blade radial circulation distribution model adjustment item.

[0018] The matching model of the circulation distribution of the moving and stationary blades along the oblique flow surface is calculated using the following formula:

[0019] ,in Indicates the amount of circulation, i indicates a certain oblique flow surface along the radial direction, is indicates a certain oblique flow surface along the radial direction of the stationary blade, and id indicates a certain oblique flow surface along the radial direction of the moving blade, where is and id refer to the corresponding oblique flow surfaces. represents the proportionality coefficient, .

[0020] Wherein, the step S109 includes: obtaining the three-dimensional coordinates of the propeller based on the circulation distribution of the moving and stationary blades and the geometric characteristics of the pitch and camber of the moving and stationary blades at their respective radii.

[0021] The method also includes using numerical methods to perform grid discretization, numerical design and numerical solution according to the operating conditions requirements in the geometric parameters and design parameters of the oblique flow combined propeller, thereby performing propeller simulation.

[0022] The method further includes returning to step S101 or step S105 to make improvements if the propeller design does not meet the requirements until it meets the requirements.

[0023] The present invention also proposes a propeller design method based on the matching of the circulation distribution of the moving and stationary blades, comprising:

[0024] A design parameter acquisition module, which is used to obtain design parameters;

[0025] a maximum thrust calculation module, configured to obtain the maximum thrust required by the diagonal flow combined thruster based on the design parameters;

[0026] a first rotor blade radial circulation distribution model construction module, configured to construct a first rotor blade radial circulation distribution model based on the maximum thrust;

[0027] a moving blade and stationary blade circulation distribution matching model construction module, which is used to construct a moving blade and stationary blade circulation distribution matching model along the oblique flow surface based on the first moving blade radial circulation distribution model;

[0028] A propeller geometric parameter estimation module is used to obtain the propeller geometric parameters based on the dynamic and static blade annular distribution matching model.

[0029] Compared with the prior art, the present invention has the following advantages:

[0030] By combining fluid dynamics theory with experimental data, an innovative matching model for the distribution of the annular mass of the moving and stationary blades was constructed. This approach ensures the scientific and practical nature of the design and improves the accuracy of the model.

[0031] Emphasizing the synergy between the rotor and stator blades, rather than optimizing each individually, this systematic approach makes the design more comprehensive, taking into account both the thrust characteristics of the rotor blades and the flow guidance capabilities of the stator blades.

[0032] A dynamic adjustment mechanism is introduced to adjust the design parameters of the stator blades in real time based on real-time flow field changes and performance feedback. This adaptive design improves the performance stability of the propeller under different operating conditions.

[0033] Accurate simulations using advanced computational fluid dynamics (CFD) tools enable prediction of flow characteristics and performance during the design phase. This innovation significantly reduces testing costs and time.

[0034] By optimizing the design of the stationary blades, an innovative vibration suppression strategy was introduced to reduce the vibration amplitude of the moving blades and improve the reliability and service life of the propeller.

[0035] A multi-objective optimization approach was employed to simultaneously improve propulsion efficiency, reduce pulsation, and suppress vibration. This innovative approach resulted in a more comprehensive design objective and enhanced the overall performance of the thruster.

[0036] By establishing a verification and feedback mechanism, a closed loop is achieved between design and actual performance. This mechanism can continuously optimize the design process and ensure the efficiency and reliability of the thruster in actual application. BRIEF DESCRIPTION OF THE DRAWINGS

[0037] The above and other objects, features and advantages of the exemplary embodiments of the present disclosure will become readily understood by reading the following detailed description with reference to the accompanying drawings. In the accompanying drawings, several embodiments of the present disclosure are shown in an illustrative and non-limiting manner, and the same or corresponding reference numerals represent the same or corresponding parts, wherein:

[0038] Figure 1 It is a flowchart of a method for matching the velocity circulation distribution of moving and stationary blades of an oblique flow combined propeller provided by an embodiment of the present invention.

[0039] Figure 2 It is a schematic diagram of an oblique flow combined propeller provided by an embodiment of the present invention.

[0040] Figure 3 It is a schematic diagram of the oblique flow surface at a certain radius of an oblique flow type combined propeller provided by an embodiment of the present invention.

[0041] Figure 4 The figure is a schematic cross-sectional view of moving and stationary blades on an oblique flow surface at a certain radius of an oblique flow type combined propeller provided by one embodiment of the present invention.

[0042] Among them, 1-stationary blade, 2-moving blade, 3-hub, 4-oblique flow surface on the hub surface, 5-oblique flow surface at a certain radius, 6-stationary blade cross section on the oblique flow surface at a certain radius, 7-moving blade cross section on the oblique flow surface at a certain radius. DETAILED DESCRIPTION

[0043] To make the objectives, technical solutions, and advantages of the present invention more apparent, the present invention will be further described in detail below with reference to the accompanying drawings. It is apparent that the embodiments described are only some, not all, of the present invention. All other embodiments derived by persons of ordinary skill in the art based on the embodiments of the present invention without creative effort are intended to fall within the scope of protection of the present invention.

[0044] The terms used in the embodiments of the present invention are for the purpose of describing specific embodiments only and are not intended to limit the present invention. The singular forms "a," "an," "the," and "the" used in the embodiments of the present invention and the appended claims are also intended to include plural forms, and unless the context clearly indicates otherwise, "a plurality" generally includes at least two.

[0045] It should be understood that although the terms "first," "second," "third," etc. may be used to describe "...," these "..." should not be limited to these terms. These terms are merely used to distinguish "...." For example, "first..." could also be referred to as "second...", and similarly, "second..." could also be referred to as "first..." without departing from the scope of the present invention.

[0046] It should be understood that the term "and / or" as used herein is merely a description of the relationship between associated objects, indicating that three possible relationships exist. For example, "A and / or B" can represent: A exists alone, A and B exist simultaneously, or B exists alone. Furthermore, the character " / " in this document generally indicates that the associated objects are in an "or" relationship.

[0047] As used herein, the words "if" and "if" may be interpreted as "at the time of" or "when" or "in response to determining" or "in response to detecting," depending on the context. Similarly, the phrases "if it is determined" or "if (stated condition or event) is detected" may be interpreted as "when it is determined" or "in response to the determination" or "when detecting (stated condition or event)" or "in response to detecting (stated condition or event)," depending on the context.

[0048] It should also be noted that the terms "include," "comprises," or any other variations thereof are intended to encompass non-exclusive inclusion, such that a product or device comprising a series of elements includes not only those elements but also other elements not explicitly listed, or elements inherent to such product or device. In the absence of further limitations, an element defined by the phrase "comprises a..." does not exclude the presence of other identical elements in the product or device comprising the element.

[0049] The optional embodiments of the present invention are described in detail below with reference to the accompanying drawings.

[0050] Example 1

[0051] like Figure 1 As shown, the present invention discloses a propeller design method based on the matching of the circulation distribution of the moving and stationary blades, comprising the following steps:

[0052] Step S101, obtaining design parameters;

[0053] Step S103: obtaining the maximum thrust required by the diagonal flow combined propeller based on the design parameters;

[0054] Step S105: constructing a radial circulation distribution model of the first rotor blade based on the maximum thrust;

[0055] Step S107: constructing a matching model for the circulation distribution of moving and stationary blades along the oblique flow surface based on the first moving blade radial circulation distribution model;

[0056] Step S109: obtaining the propeller geometric parameters based on the dynamic and static blade circulation distribution matching model.

[0057] Example 2

[0058] The present invention proposes a propeller design method based on the matching of the circulation distribution of the moving and stationary blades, comprising the following steps:

[0059] Step S101, obtaining design parameters;

[0060] Step S103: obtaining the maximum thrust required by the diagonal flow combined propeller based on the design parameters;

[0061] Step S105: constructing a radial circulation distribution model of the first rotor blade based on the maximum thrust;

[0062] Step S107: constructing a matching model for the circulation distribution of moving and stationary blades along the oblique flow surface based on the first moving blade radial circulation distribution model;

[0063] Step S109: obtaining the propeller geometric parameters based on the dynamic and static blade circulation distribution matching model.

[0064] The design parameters include at least rated power P, rated speed n, maximum speed V and rotor blade diameter D.

[0065] The design parameters also include spatial arrangement size, which refers to the overall size configuration of the propeller, including the relative position and diameter of the moving and stationary blades, etc. It affects the flow characteristics of the fluid in the propeller and the overall performance.

[0066] The maximum thrust F in step S103 can be calculated using the following formula:

[0067] , where P is power, V is maximum speed, and 0.7 and 0.9 are efficiency coefficients, which take into account mechanical efficiency and flow efficiency, respectively.

[0068] 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 moving and stationary blades, Indicates the density of water.

[0069] Wherein, the step S105 includes:

[0070] Step S1051: constructing a radial circulation distribution model of the second rotor blade based on the maximum thrust;

[0071] Step S1053: obtaining an adjustment item of a rotor blade radial circulation distribution model based on the design parameters;

[0072] Step S1055: Obtain a first rotor blade radial circulation distribution model based on the second rotor blade radial circulation distribution model and the rotor blade radial circulation distribution model adjustment item.

[0073] The radial circulation distribution model of the second rotor blade is calculated using the following formula: ,in Is a normalization coefficient that ensures that the sum of the circulation distribution of the moving blades within the entire radius is equal to the maximum circulation. represents the circulation of the moving blade at radius r, and C(r) represents the conventional term that is polynomially related to the radius of the propeller moving blade, which is in the form of , c i is the polynomial coefficient; m is the highest power of the polynomial; k is the general coefficient, ranging from -256 to 256; and n is the exponent, ranging from -10 to 10. Based on specific design requirements and flow characteristics, appropriate values ​​of k and n are selected to ensure that the circulation distribution of the rotor blade meets performance requirements.

[0074] The following formula is used to calculate the adjustment item of the radial circulation distribution model of the moving blade: :

[0075] , where a represents the normal vector at radius r, b represents the normal vector of the adjacent point, and f is the adjustment coefficient, ranging from -1 to 1. Adjust the value of f based on the size of A(r). If the result of A(r) is large, f should be close to 0; if the result of A(r) is small, f should be close to -1 or 1.

[0076] The radial circulation distribution model of the first moving blade is calculated using the following formula:

[0077] .

[0078] The matching model of the circulation distribution of the moving and stationary blades along the oblique flow surface is calculated using the following formula:

[0079] ,in Indicates the amount of circulation, i indicates a certain oblique flow surface along the radial direction, is indicates a certain oblique flow surface along the radial direction of the stationary blade, and id indicates a certain oblique flow surface along the radial direction of the moving blade, where is and id refer to the corresponding oblique flow surfaces. represents the proportionality coefficient, .

[0080] Wherein, the step S109 includes: obtaining the three-dimensional coordinates of the propeller based on the circulation distribution of the moving and stationary blades and the geometric characteristics of the pitch and camber of the moving and stationary blades at their respective radii.

[0081] In one embodiment, according to the circulation distribution of the moving and stationary blades, the pitch can be calculated by the speed V and the rotation speed n. , where V is the ship speed and n is the rotation speed.

[0082] The camber can be derived from the blade geometry and the circulation distribution, usually involving the boundary conditions and physical properties of the flow.

[0083] Through the above calculations, the geometric characteristics of the propeller at each radius can be obtained, including pitch P, camber, blade thickness, and blade width.

[0084] Based on the calculated geometric characteristics, the three-dimensional coordinate system of the propeller can be established. The specific steps are as follows:

[0085] Select a datum surface to determine the thruster's mounting surface or datum.

[0086] Establish a coordinate system and set the origin, x, y, and z axis directions of the three-dimensional coordinate system.

[0087] Draw the blades. Based on the calculated pitch and camber, draw the outlines of the dynamic and static blades in the coordinate system.

[0088] The method also includes using numerical methods to perform grid discretization, numerical design and numerical solution according to the operating conditions requirements in the geometric parameters and design parameters of the oblique flow combined propeller, thereby performing propeller simulation.

[0089] In one embodiment, the geometric parameters include the propeller's diameter, number of blades, pitch, camber, blade thickness, etc. These parameters are the basis for designing the propeller.

[0090] Design parameters involve operating conditions, such as speed, rotational speed, and properties of the working fluid (such as density and viscosity).

[0091] Mesh discretization, in numerical simulations, involves dividing the computational domain into multiple small cells (grids) for numerical calculations. The quality of the mesh directly affects the accuracy and convergence of the computational results. Structured or unstructured meshes can be used, depending on the geometry and complexity of the propeller.

[0092] Numerical design involves selecting a numerical method. Choosing an appropriate numerical method to solve the fluid dynamics equations is crucial. Common methods include the finite difference method, the finite element method, and computational fluid dynamics (CFD). Based on the flow characteristics, an appropriate physical model (such as a laminar or turbulent flow model) is selected to describe the fluid behavior.

[0093] The numerical solution involves solving the Navier-Stokes equations numerically to calculate the flow characteristics of the fluid around the propeller. Appropriate boundary conditions (such as no-slip conditions, inlet and outlet conditions) are set to ensure the accuracy of the calculations.

[0094] Using numerically derived flow field data, we analyze flow characteristics, pressure distribution, velocity fields, and other information. We calculate thrust, efficiency, and other performance indicators to evaluate the thruster's performance under given operating conditions. Based on the simulation results, we adjust geometric and design parameters, performing multiple iterations of optimization to improve thruster performance. The numerical simulation results are compared with experimental data to verify the accuracy and reliability of the numerical model.

[0095] The method further includes returning to step S101 or step S105 to make improvements if the propeller design does not meet the requirements until it meets the requirements.

[0096] Here, based on the pre-set requirements for speed, acoustics, and other indicators, the simulation results are compared with the requirements to determine whether the thruster's performance indicators meet the standards.

[0097] If the requirements are not met, return and adjust the design parameters or adjust the radial circulation distribution model of the moving blades.

[0098] Example 3

[0099] The present invention also proposes a propeller design system based on the matching of the circulation distribution of the moving and stationary blades, comprising:

[0100] A design parameter acquisition module, which is used to obtain design parameters;

[0101] a maximum thrust calculation module, configured to obtain the maximum thrust required by the diagonal flow combined thruster based on the design parameters;

[0102] a first rotor blade radial circulation distribution model construction module, configured to construct a first rotor blade radial circulation distribution model based on the maximum thrust;

[0103] a moving blade and stationary blade circulation distribution matching model construction module, which is used to construct a moving blade and stationary blade circulation distribution matching model along the oblique flow surface based on the first moving blade radial circulation distribution model;

[0104] A propeller geometric parameter estimation module is used to obtain the propeller geometric parameters based on the dynamic and static blade annular distribution matching model.

[0105] Example 4

[0106] An embodiment of the present disclosure provides a non-volatile computer storage medium, wherein the computer storage medium stores computer-executable instructions, and the computer-executable instructions can execute the method steps described in the above embodiment.

[0107] It should be noted that the computer-readable medium described above in the present disclosure may be a computer-readable signal medium or a computer-readable storage medium, or any combination thereof. Computer-readable storage media may include, for example, but not limited to, electrical, magnetic, optical, electromagnetic, infrared, or semiconductor systems, devices, or components, or any combination thereof. More specific examples of computer-readable storage media may include, but are not limited to, an electrical connection having one or more conductors, a portable computer disk, a hard disk, random access memory (RAM), read-only memory (ROM), erasable programmable read-only memory (EPROM or flash memory), optical fiber, a portable compact disk read-only memory (CD-ROM), an optical storage device, a magnetic storage device, or any suitable combination thereof. In the present disclosure, a computer-readable storage medium may be any tangible medium containing or storing a program that can be used by or in conjunction with an instruction execution system, apparatus, or device. In the present disclosure, a computer-readable signal medium may include a data signal propagated in baseband or as part of a carrier wave, carrying computer-readable program code. Such a propagated data signal may take a variety of forms, including, but not limited to, electromagnetic signals, optical signals, or any suitable combination thereof. A computer-readable signal medium may also be any computer-readable medium other than a computer-readable storage medium that can transmit, propagate, or transport a program for use by or in connection with an instruction execution system, apparatus, or device. Program code embodied on a computer-readable medium may be transmitted using any suitable medium, including but not limited to wire, optical cable, RF (radio frequency), or any suitable combination thereof.

[0108] The computer-readable medium may be included in the electronic device, or may exist independently without being incorporated into the electronic device.

[0109] Computer program code for performing the operations of the present disclosure may be written in one or more programming languages, or a combination thereof, including object-oriented programming languages ​​such as Java, Smalltalk, C++, and conventional procedural programming languages ​​such as "C" or similar programming languages. The program code may be executed entirely on the user's computer, partially on the user's computer, as a stand-alone software package, partially on the user's computer and partially on a remote computer, or entirely on a remote computer or server. In cases involving a remote computer, the remote computer may be connected to the user's computer via any type of network, including a local area network (LAN) or a wide area network (WAN), or may be connected to an external computer (e.g., via the Internet using an Internet service provider).

[0110] The flowcharts and block diagrams in the accompanying drawings illustrate the possible implementation architecture, functions and operations of the systems, methods and computer program products according to various embodiments of the present disclosure. In this regard, each box in the flowchart or block diagram can represent a module, program segment, or a part of code, and the module, program segment, or a part of code contains one or more executable instructions for realizing the specified logical function. It should also be noted that in some alternative implementations, the functions marked in the box can also occur in a different order than that marked in the accompanying drawings. For example, two boxes represented in succession can actually be executed substantially in parallel, and they can sometimes be executed in the opposite order, depending on the functions involved. It should also be noted that each box in the block diagram and / or flowchart, and the combination of the boxes in the block diagram and / or flowchart, can be implemented with a dedicated hardware-based system that performs the specified function or operation, or can be implemented with a combination of dedicated hardware and computer instructions.

[0111] The units involved in the embodiments described in this disclosure may be implemented in software or hardware, wherein the name of a unit does not necessarily limit the unit itself.

[0112] The above introduces the preferred embodiments of the present invention, which is intended to make the spirit of the present invention clearer and easier to understand, and is not intended to limit the present invention. Any modifications, replacements, and improvements made within the spirit and principles of the present invention should be included in the scope of protection outlined by the claims attached to the present invention.

Claims

1. A propeller design method based on the matching of the circulation distribution of dynamic and static blades, characterized in that: The following steps are involved: Step S101: acquiring design parameters, wherein the design parameters include at least rated power P, rated speed n, maximum speed V, and rotor blade diameter D; Step S103: obtaining the maximum thrust required by the diagonal flow combined propeller based on the design parameters; Step S105: constructing a radial circulation distribution model of the first rotor blade based on the maximum thrust; Step S107: constructing a matching model for the circulation distribution of moving and stationary blades along the oblique flow surface based on the first moving blade radial circulation distribution model; Step S109: acquiring the propeller geometric parameters based on the dynamic and static blade annular distribution matching model; The matching model of the dynamic and static blade circulation distribution along the oblique flow surface is calculated using the following formula: ,in Indicates the amount of circulation, i indicates a certain oblique flow surface along the radial direction, is indicates a certain oblique flow surface along the radial direction of the stationary blade, and id indicates a certain oblique flow surface along the radial direction of the moving blade, where is and id refer to the corresponding oblique flow surfaces, g i represents the proportionality coefficient, ; The step S109 includes: obtaining the three-dimensional coordinates of the propeller based on the circulation distribution of the moving and stationary blades and the geometric characteristics of the pitch and camber of the moving and stationary blades at their respective radii.

2. The method according to claim 1, wherein: The maximum thrust F in step S103 can be calculated using the following formula: , where P is power, V is maximum speed, and 0.7 and 0.9 are efficiency coefficients, which take into account mechanical efficiency and flow efficiency, respectively.

3. The method according to claim 2, 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 moving and stationary blades, Indicates the density of water.

4. The method according to claim 1, wherein: The step S105 includes: Step S1051: constructing a radial circulation distribution model of the second rotor blade based on the maximum thrust; Step S1053: obtaining an adjustment item of a rotor blade radial circulation distribution model based on the design parameters; Step S1055: Obtain a first rotor blade radial circulation distribution model based on the second rotor blade radial circulation distribution model and the rotor blade radial circulation distribution model adjustment item.

5. The method according to claim 1, wherein: The method also includes using numerical methods to perform grid discretization, numerical design and numerical solution according to the operating condition requirements in the geometric parameters and design parameters of the oblique flow type combined propeller, thereby performing propeller simulation.

6. The method according to claim 1, wherein: The method further includes returning to step S101 or step S105 to make improvements if the propeller design does not meet the requirements until the requirements are met.

7. A propeller design system based on the matching of the circulation distribution of the moving and stationary blades, including A design parameter acquisition module, which is used to acquire design parameters, wherein the design parameters include at least rated power P, rated speed n, maximum speed V and rotor blade diameter D; a maximum thrust calculation module, configured to obtain the maximum thrust required by the diagonal flow combined thruster based on the design parameters; a first rotor blade radial circulation distribution model construction module, configured to construct a first rotor blade radial circulation distribution model based on the maximum thrust; a moving blade and stationary blade circulation distribution matching model construction module, which is used to construct a moving blade and stationary blade circulation distribution matching model along the oblique flow surface based on the first moving blade radial circulation distribution model; A propeller geometric parameter estimation module, which is used to obtain the propeller geometric parameters based on the dynamic and static blade annular distribution matching model; in, The matching model of the dynamic and static blade circulation distribution along the oblique flow surface is calculated using the following formula: ,in Indicates the amount of circulation, i indicates a certain oblique flow surface along the radial direction, is indicates a certain oblique flow surface along the radial direction of the stationary blade, and id indicates a certain oblique flow surface along the radial direction of the moving blade, where is and id refer to the corresponding oblique flow surfaces, g i represents the proportionality coefficient, ; The propeller geometric parameter estimation module obtains the three-dimensional coordinates of the propeller based on the circulation distribution of the moving and stationary blades and the geometric characteristics of the pitch and camber of the moving and stationary blades at their respective radii.

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