Turbine circulation structure optimization method based on bionic blade design

Abstract

The invention provides a turbine circulation structure optimization method based on bionic blade design, which comprises the following steps: acquiring airfoil profile parameters of bird wings in a cruising state, and extracting front edge arc radius, mean camber line curvature distribution and rear edge thickness characteristics; a bionic airfoil profile structure of the turbine moving blade is designed based on the airfoil profile parameters, so that the front edge of the blade is of a variable-curvature arc structure, a mean camber line is distributed in a nonlinear curvature mode, and the flow characteristic of steam on the surface of the blade is optimized; according to the bionic wing-shaped structure, the inlet and outlet angles and the sectional area of a steam turbine through-flow channel are adjusted, so that the steam incident angle is matched with the front edge of a blade, and steam flow velocity distribution in the channel is optimized; a micron-sized concave-convex texture structure is machined on the surface of the blade through a laser engraving technology, so that the steam adhesiveness is enhanced, and boundary layer separation is restrained. Boundary layer separation of steam on the blade surface can be effectively restrained, the steam flowing efficiency is improved, the adaptability of a steam turbine under different load working conditions is enhanced, and energy loss is reduced.

Description

Technical Field

[0001] This invention belongs to the field of steam turbine flow structure optimization technology, specifically relating to a steam turbine flow structure optimization method based on biomimetic blade design. Background Technology

[0002] During the operation of thermal power plants, the steam turbine, as the core power equipment, directly affects the power generation efficiency and energy consumption level of the entire power plant due to the efficiency of its flow path structure. Currently, traditional steam turbine blade designs mostly adopt symmetrical arc or linear airfoil structures, and the design approach mainly relies on numerical simulations and empirical parameter selection using fluid dynamics software, without fully considering the efficient motion characteristics of natural organisms in fluid environments.

[0003] Existing technologies suffer from two major problems: First, the airflow boundary layer on the blade surface is prone to separation, especially under high-load conditions. The velocity difference between the pressure and suction surfaces of the steam creates eddies, leading to energy loss. Industry data shows that the steam flow efficiency of traditional blades is generally below 85%. Second, the matching degree between the inlet and outlet airflow angles and the flow channel is insufficient. Steam is prone to impact losses when entering and exiting the blades, further reducing the turbine's flow efficiency. Furthermore, traditional blade designs have poor adaptability to different operating conditions. When the unit load fluctuates, the aerodynamic performance of the blades deteriorates significantly, making it difficult to meet the high-efficiency operation requirements under both high and low loads. While there have been attempts in the industry to smooth the blade surface or improve local structures, these have not addressed the issue from a biomimetic optimization perspective of the overall airfoil morphology, and therefore cannot fundamentally solve the problem of low steam flow efficiency. Summary of the Invention

[0004] The present invention aims to at least partially solve one of the technical problems in the related art.

[0005] Therefore, the first objective of this invention is to propose a method for optimizing the flow structure of a steam turbine based on biomimetic blade design.

[0006] The main objective of this invention is to provide a method for optimizing the flow path structure of a steam turbine based on biomimetic blade design. By drawing on the biological characteristics of birds' wings moving efficiently in the air, the airfoil structure of the steam turbine blades is optimized to improve steam flow efficiency and reduce energy loss.

[0007] The second objective of this invention is to propose a turbine flow structure optimization device based on biomimetic blade design.

[0008] The third objective of this invention is to provide a computer device.

[0009] A fourth objective of this invention is to provide a non-transitory computer-readable storage medium.

[0010] To achieve the above objectives, a first aspect of the present invention proposes a method for optimizing the flow structure of a steam turbine based on biomimetic blade design, comprising: S1, obtain the airfoil profile parameters of the bird's wing in cruise mode, and extract the leading edge radius, mid-arc curvature distribution and trailing edge thickness features; S2. Based on the airfoil profile parameters, design the biomimetic airfoil structure of the turbine blade, so that the leading edge of the blade adopts a variable curvature circular arc structure and the middle arc adopts a nonlinear curvature distribution to optimize the flow characteristics of steam on the blade surface. S3, adjust the inlet and outlet angles and cross-sectional areas of the turbine flow passage according to the biomimetic airfoil structure, so that the steam incident angle matches the leading edge of the blade, and optimize the steam velocity distribution in the passage; S4 uses laser engraving technology to process micron-level textured structures on the blade surface to enhance steam adhesion and suppress boundary layer separation.

[0011] In one embodiment of the present invention, S1 includes: S11 uses high-speed camera technology to capture the dynamic deformation process of bird wings during cruising, and obtains airfoil profile data at different angles of attack; S12 uses a three-dimensional scanning device to perform non-contact measurements on bird wing samples, extracting a set of three-dimensional coordinate points for the leading edge radius, the mid-arc curvature distribution, and the trailing edge thickness.

[0012] In one embodiment of the present invention, S2 includes: S21 adjusts the position of the maximum curvature point of the mid-curvature line from 50% chord length in the traditional airfoil to 38% chord length, thereby improving steam flow efficiency. S22, using a nonlinear function Describe the curvature distribution of the arc, where The value range is the biomimetic curvature index. .

[0013] In one embodiment of the present invention, S3 further includes: S31, the inlet angle of the flow channel Adjusted to Export angle Adjusted to ,in and For traditional blade inlet and outlet angles; S32 optimizes the steam velocity distribution using fluid dynamics simulation software, reducing the velocity gradient in the blade region. satisfy .

[0014] In one embodiment of the present invention, S4 includes: S41, using pulse width Laser processing is used to refine textures, increasing the processing precision of individual textures. ; S42, controls texture depth Spacing The ratio satisfies ,in , .

[0015] To achieve the above objectives, a second aspect of the present invention provides a turbine flow structure optimization device based on biomimetic blade design, comprising: The airfoil parameter acquisition module acquires the airfoil profile parameters of a bird's wing in cruise mode, and extracts the leading edge radius, mid-arc curvature distribution, and trailing edge thickness features. The biomimetic airfoil design module designs the biomimetic airfoil structure of the turbine blade based on the airfoil profile parameters, so that the leading edge of the blade adopts a variable curvature circular arc structure and the middle arc adopts a nonlinear curvature distribution to optimize the flow characteristics of steam on the blade surface. The flow channel adjustment module adjusts the inlet and outlet angles and cross-sectional areas of the turbine flow channel according to the biomimetic airfoil structure, so that the steam incident angle matches the leading edge of the blade and optimizes the steam velocity distribution in the channel. The surface texture processing module uses laser engraving technology to process micron-level concave and convex texture structures on the blade surface to enhance steam adhesion and suppress boundary layer separation.

[0016] This invention discloses a method and apparatus for optimizing the flow structure of a steam turbine based on biomimetic blade design. Through biomimetic design, the steam flow efficiency of the turbine's moving blades is increased to over 92%, which is more than 7% higher than that of traditional blades. At the same time, the optimized flow structure has significantly enhanced adaptability to load fluctuations. Within the load range of 50%-100%, the steam flow efficiency decay rate is less than 3%, which can effectively improve the operating economy of the steam turbine under varying operating conditions.

[0017] To achieve the above objectives, a third aspect of this application provides a computer device, including a processor and a memory; wherein the processor runs a program corresponding to the executable program code by reading executable program code stored in the memory, for implementing the turbine flow structure optimization method based on biomimetic blade design as described in the first aspect embodiment.

[0018] To achieve the above objectives, a fourth aspect of this application provides a non-transitory computer-readable storage medium storing a computer program thereon, which, when executed by a processor, implements the turbine flow structure optimization method based on biomimetic blade design as described in the first aspect embodiment.

[0019] Additional aspects and advantages of the invention will be set forth in part in the description which follows, and in part will be obvious from the description, or may be learned by practice of the invention. Attached Figure Description

[0020] The above and / or additional aspects and advantages of the present invention will become apparent and readily understood from the following description of the embodiments taken in conjunction with the accompanying drawings, wherein: Figure 1 This is a flowchart of a method for optimizing the flow structure of a steam turbine based on biomimetic blade design according to an embodiment of the present invention; Figure 2 This is a schematic diagram of a bird's wing cross-section according to an embodiment of the present invention; Figure 3 This is a design drawing of a steam turbine biomimetic blade according to an embodiment of the present invention; Figure 4 This is a schematic diagram of a steam turbine biomimetic blade design according to an embodiment of the present invention; Figure 5 This is a structural diagram of a turbine flow structure optimization device based on biomimetic blade design according to an embodiment of the present invention; Figure 6 It is a computer device according to an embodiment of the present invention. Detailed Implementation

[0021] It should be noted that, unless otherwise specified, the embodiments and features described in the present invention can be combined with each other. The present invention will now be described in detail with reference to the accompanying drawings and embodiments.

[0022] To enable those skilled in the art to better understand the present invention, the technical solutions of the present invention will be clearly and completely described below with reference to the accompanying drawings of the embodiments of the present invention. Obviously, the described embodiments are only some embodiments of the present invention, and not all embodiments. Based on the embodiments of the present invention, all other embodiments obtained by those skilled in the art without creative effort should fall within the scope of protection of the present invention.

[0023] The following description, with reference to the accompanying drawings, describes a method and apparatus for optimizing the flow structure of a steam turbine based on biomimetic blade design, according to an embodiment of the present invention.

[0024] Example 1 Figure 1 This is a flowchart of a method for optimizing the flow structure of a steam turbine based on biomimetic blade design according to an embodiment of the present invention, such as... Figure 1 As shown, it includes: S1: Obtain the airfoil profile parameters of a bird's wing in cruise mode, and extract the leading edge radius, mid-arc curvature distribution, and trailing edge thickness features.

[0025] In some implementations, this step combines a high-speed camera system with a 3D laser scanning device to capture and model the wing shape of birds in stable flight with high precision. Specifically, a high-speed camera with a frame rate of at least 1000fps records the wing movement trajectory of the bird during flight, and a 3D point cloud scanner (such as Artec Leo or Mitsubishi Electric 3D scanner) is used to collect the geometric contour data of the wing surface, ultimately generating a high-resolution 3D airfoil model.

[0026] This step focuses on acquiring three key features: the leading-edge radius, the mid-curve curvature distribution, and the trailing-edge thickness. The leading-edge radius is obtained by fitting the curvature variation curve of the wing's leading edge, typically using the least squares method to ensure its aerodynamic adaptability at different angles of attack. The mid-curve curvature distribution is calculated by determining the curvature function of the airfoil's mid-curve. ,in This indicates the coordinate position along the chord length. The maximum curvature typically occurs in the 35%-45% region of the chord length; this distribution guides the design of the blade's nonlinear arc. Trailing edge thickness. By measuring the chordal thickness at the airfoil tip and considering the aerodynamic stability requirements of a bird's wing during cruise, the optimal value within the range of 2mm-5mm was determined.

[0027] Furthermore, the parameters extracted in this step will serve as a benchmark for the airfoil design of turbine blades, used to optimize the aerodynamic performance of the blades. By mapping the fluid adaptability characteristics of bird wings to turbine blades, the flow characteristics of steam on the blade surface can be effectively improved, boundary layer separation and eddy current losses can be reduced, thereby increasing flow efficiency. This method demonstrates good adaptability under both high and partial load conditions, providing data support for subsequent flow channel matching optimization, and has significant engineering application value.

[0028] Furthermore, S1 includes: S11 uses high-speed camera technology to capture the dynamic deformation process of bird wings during cruising, and obtains airfoil profile data at different angles of attack.

[0029] In some implementations, this step relies on the combined application of a high-speed imaging system and 3D scanning technology to achieve high-precision dynamic modeling of the airfoil profile during bird flight. Specifically, high-speed camera equipment with a frame rate of at least 1000 frames per second (such as the Phantom high-speed camera series) is used to film birds from multiple angles in natural or simulated flight environments to ensure the capture of their true airfoil deformation at different angles of attack. During filming, the ambient light intensity must be controlled above 5000 lux to ensure image clarity and contrast. Simultaneously, a background calibration board and stereo vision calibration technology are used to reconstruct the 3D spatial coordinates.

[0030] Furthermore, image processing algorithms (such as OpenCV or MATLAB image recognition modules) are used to perform edge detection and contour extraction on high-speed camera images to obtain key geometric parameters of bird wings in cruise mode, such as the leading-edge radius, mid-curvature curvature distribution, and trailing-edge thickness. These parameters will serve as biomimetic benchmarks for turbine blade airfoil design, guiding the geometric reconstruction of the leading, mid-curvature, and trailing edges of the blades. For example, the leading-edge radius of a bird's wing is typically in the range of 10-15 mm, while the maximum curvature point of the mid-curvature is often located in the 35%-45% range of the airfoil chord length. These data provide important references for blade aerodynamic optimization.

[0031] S12 uses a three-dimensional scanning device to perform non-contact measurements on bird wing samples, extracting a set of three-dimensional coordinate points for the leading edge radius, the mid-arc curvature distribution, and the trailing edge thickness.

[0032] In some implementations, this step involves non-contact measurement of bird wing samples using a high-precision 3D optical scanner (such as a laser triangulation scanner or a structured light scanning system). Scanning devices typically possess sub-millimeter spatial resolution (e.g., 0.1 mm) and high sampling frequencies (e.g., 1000 Hz), enabling them to capture the geometric features of the bird's wing at different spanwise positions. During scanning, the sample must be fixed to a rotating platform to ensure complete 3D point cloud data is acquired at different angles. Point cloud data processing software (such as Geomagic, CloudCompare, or MATLAB Point Cloud Toolbox) is then used to denoise, register, and fit surfaces to extract the radius of the leading edge arc of the bird's wing. The curvature distribution function of the middle arc and trailing edge thickness A set of three-dimensional coordinate points.

[0033] Specifically, the radius of the leading edge arc The range is typically between 3mm and 15mm, depending on the bird species and flight pattern; mid-curve curvature distribution With string length The independent variable is used to describe the curvature variation along the span, with the maximum curvature point typically located in the 35%-45% range of the airfoil chord length; trailing edge thickness. It is typically between 1mm and 5mm in diameter and has a tapering characteristic to meet the requirements of airflow separation control.

[0034] S2. Based on the airfoil profile parameters, design the biomimetic airfoil structure of the turbine blade, so that the leading edge of the blade adopts a variable curvature circular arc structure and the middle arc adopts a nonlinear curvature distribution to optimize the flow characteristics of steam on the blade surface.

[0035] In some implementations, the variable curvature arc structure of the blade leading edge is derived from the geometric features of the leading edge of a bird's wing using biomimetic methods and mapped onto the leading edge design of the turbine blade. The radius of this arc is not a fixed value but varies non-linearly along the chord to adapt to the flow characteristics of steam at different angles of attack. For example, in this embodiment, the leading edge arc radius varies from the inlet end... Gradually transitioning to the trailing edge This creates a continuous curvature change, effectively reducing the local pressure gradient during steam impact and delaying boundary layer separation.

[0036] Furthermore, the mid-curvature adopts a nonlinear curvature distribution, with the maximum curvature point set at 38% of the airfoil chord length. Compared to the 50% position of the traditional linear mid-curvature, this better matches the lift distribution characteristics of a bird's wing during cruise. This nonlinear curvature distribution can be modeled using spline interpolation or Bézier curves to ensure a smoother steam flow path on the blade surface, reducing flow drag and energy loss.

[0037] At the parameter level, parameters such as the leading edge radius, the position of the mid-curve curvature distribution, and the trailing edge thickness of the blade all need to be determined based on the turbine operating conditions (such as steam pressure). ,temperature Adjustments need to be made to adapt the design. For example, the trailing edge thickness. Compared to traditional leaves The reduction in size significantly helps improve the aerodynamic performance of the blades and reduce their structural weight.

[0038] Furthermore, S2 includes: S21 adjusts the position of the maximum curvature point of the mid-curvature line from 50% chord length in the traditional airfoil to 38% chord length, thereby improving steam flow efficiency.

[0039] The specific technical implementation includes: First, based on the three-dimensional scanning data of a bird's wing in cruise mode, the nonlinear curvature distribution characteristics of its arc are extracted. In particular, the location of the maximum curvature point is usually located in the forward region of the wingspan, at approximately 38% of the chord length. This location is further forward than the 50% chord length of traditional blades, which helps to form a more reasonable pressure gradient when steam enters the blade area, allowing the airflow to maintain a smoother flow state between the suction and pressure surfaces. Furthermore, through CAD modeling and CFD (Computational Fluid Dynamics) simulation, this biomimetic feature is mapped to the mid-curvature design of the turbine blade, ensuring its structural strength and aerodynamic performance under high-temperature and high-pressure steam environments.

[0040] Specifically, the adjustment of the position of the point of maximum curvature of the arc in this step must meet the following requirements. The requirement for improved steam flow efficiency. In this embodiment, the location is precisely set at 38% chord length, in conjunction with the leading edge radius. With trailing edge thickness These parameters together form the geometric reference of the biomimetic airfoil. The effectiveness of this parameter combination in reducing flow losses was verified through fluid dynamics simulations under conditions of 16.7 MPa steam pressure and 538°C steam temperature.

[0041] S22, using a nonlinear function Describe the curvature distribution of the arc, where The value range is the biomimetic curvature index. .

[0042] In some implementations, this invention employs a nonlinear function. To describe the curvature distribution of the arc in the turbine blades, where Indicates the coordinate position along the chord length of the blade. The chord length of the leaf blade. This represents the maximum curvature value at the leading edge of the blade. The value range of the biomimetic curvature index is limited to 1. The function is derived from the fitting analysis of the mid-curvature distribution of bird wings in cruise mode, which can effectively simulate the lift characteristics generated by natural airfoils in fluid, thereby optimizing the steam flow behavior on the blade surface.

[0043] This nonlinear curvature function is passed through parameters The curvature decay rate of the mid-curvature curve is controlled to ensure a higher curvature at the leading edge of the blade, gradually flattening out at the trailing edge. This design helps to create a more reasonable pressure gradient when steam enters the blade region, thereby suppressing boundary layer separation. In practice, high-speed photography and 3D scanning technology can be used to acquire mid-curvature data of a bird's wing, and the optimal curve can be fitted using least squares or spline interpolation methods. The value is then applied to the CAD modeling and CNC machining of the blades.

[0044] Specifically, The value needs to be adjusted according to the blade geometry and steam conditions (such as pressure and temperature), and is usually within... Within the range. The choice of value directly affects the aerodynamic performance of the blades. An excessively large value results in an overly gentle mid-curve, affecting lift distribution; an excessively small value may cause an overly steep local pressure gradient, leading to flow separation. Therefore, this invention limits... exist This is to ensure good flow stability under different load conditions.

[0045] S3. Adjust the inlet and outlet angles and cross-sectional areas of the turbine flow passage according to the biomimetic airfoil structure to match the steam incident angle with the leading edge of the blade and optimize the steam velocity distribution in the passage.

[0046] In some implementations, the core technical principle of this step lies in matching geometric parameters to ensure that the flow direction of steam entering and exiting the blades is consistent with the aerodynamic characteristics of the blade leading edge, thereby reducing impact losses and boundary layer separation. Specifically, this process is based on the variable curvature arc structure of the leading edge and the nonlinear curvature characteristics of the mid-arc of a bird's wing, extracting its key geometric parameters, such as the radius of the leading edge arc, the position of the maximum curvature of the mid-arc, and the thickness of the trailing edge, and mapping them to the flow channel design of the turbine blades.

[0047] Specifically, the inlet angle of the flow channel of a traditional blade Export angle This invention, through biomimetic optimization, adjusts the inlet angle to... The export angle was adjusted to This allows the deviation between the steam incident angle and the airflow angle at the leading edge of the blade to be controlled within a certain range. This effectively reduces airflow impact losses. Simultaneously, to optimize the steam velocity distribution within the channel, the inlet cross-sectional area is... Expand by 5%, export cross-sectional area The speed gradient is reduced by 3% to achieve a more uniform velocity gradient and reduce eddies and energy losses caused by local acceleration or deceleration.

[0048] Furthermore, S3 includes: S31, the inlet angle of the flow channel Adjusted to Export angle Adjusted to ,in and This refers to the inlet and outlet angles of traditional blades.

[0049] In some implementations, this step is first based on the inlet and outlet angles of traditional blades. and Fine-tuning was made. Specifically, the import angle... The adjustment range is Export angle The adjustment range is This angle adjustment is achieved through numerical simulation using 3D modeling and fluid dynamics simulation software (such as ANSYS CFX, CFD++, etc.). During the simulation, by setting different angle combinations, the flow characteristics of steam on the blade surface are analyzed, including velocity distribution, pressure gradient, boundary layer thickness, etc., and finally the optimal angle configuration is determined to make the steam flow smoother and reduce eddies and separation losses.

[0050] Specifically, based on specific data, the inlet angle of traditional blades Export angle Optimized blade inlet angle Export angle All are controlled within Within a certain range. This angle adjustment must meet the limitations on airflow angle deviation in turbine design standards (such as ASME, API 612, etc.) to ensure that good aerodynamic performance can still be maintained under different load conditions (such as 50%-100% load).

[0051] S32 optimizes the steam velocity distribution using fluid dynamics simulation software, reducing the velocity gradient in the blade region. satisfy .

[0052] In some implementations, this step employs CFD (Computational Fluid Dynamics) simulation software, such as ANSYS Fluent or COMSOL Multiphysics, to establish a three-dimensional geometric model of the turbine blades and their flow passages. The geometric parameters of the blades in the model have been determined through a biomimetic airfoil profile design process, including the leading-edge radius, mid-curvature distribution, and trailing-edge thickness. During the simulation, the steam inlet boundary condition is set as a mass flow inlet, and the outlet as a pressure outlet, using Realizable... The turbulence model simulates boundary layer separation and turbulence characteristics. The velocity field distribution within the blade region is obtained by iteratively solving the Navier-Stokes equations.

[0053] Specifically, the core control index for this step is the velocity gradient in the blade region. Its modulus must satisfy This index reflects the local velocity change rate of steam flowing on the blade surface. An excessively large gradient can lead to boundary layer instability, resulting in separation and energy loss. In the simulation, the inlet and outlet angles of the flow channel (e.g., ...) are adjusted. , ) and cross-sectional area (e.g., import cross-sectional area) Expand by 5%, export cross-sectional area (Reducing the size by 3%) to achieve precise control of the velocity gradient. In addition, the simulation also requires setting the physical properties of the steam, such as temperature. ,pressure This is to ensure that the simulation results are consistent with the actual working conditions.

[0054] S4 uses laser engraving technology to process micron-level textured structures on the blade surface to enhance steam adhesion and suppress boundary layer separation.

[0055] In some implementations, this step employs a high-precision laser micromachining system. A focused laser beam scans and ablates point-by-point on the blade surface, creating a micron-level textured structure with specific geometric features. The processing accuracy of laser engraving is typically controlled within ±2 μm, and the texture depth... ,spacing This structure mimics the microscopic texture of bird feathers. It significantly enhances steam adhesion to the blade surface, thereby delaying boundary layer separation and reducing eddy current losses in the flow separation region.

[0056] Furthermore, the laser engraving process parameters need to be optimized based on the characteristics of the blade material (such as stainless steel or titanium alloy). For example, the laser power is typically set in the range of 10~30 W, the scanning speed is controlled at 1~5 mm / s, and the pulse frequency is 10~50 kHz to ensure the stability of the texture structure and the surface roughness is between Ra 0.5~2.0 μm. This combination of parameters can effectively avoid problems such as excessive material ablation or structural discontinuity, ensuring the durability and stability of the blade surface under high temperature and high pressure steam environment.

[0057] Furthermore, S4 includes: S41, using pulse width Laser processing is used to refine textures, increasing the processing precision of individual textures. .

[0058] In some implementations, this step employs ultra-short pulse laser micromachining (UPL) technology. Its core lies in using a laser beam with nanosecond-level pulse widths to perform high-precision microstructural engraving on the blade surface. During laser processing, non-contact, high-resolution processing of the blade surface is achieved by controlling parameters such as laser power density, scanning speed, pulse frequency, and focused spot size. The laser beam ablates the blade surface point-by-point according to a pre-set texture pattern, forming a deep... ,spacing The structure features a periodic microstructure. This structure can effectively alter the flow boundary conditions between steam and the blade surface, enhancing the ability of surface roughness to control the flow.

[0059] Specifically, laser pulse width Controlled to This process is designed to ensure high-precision machining without damaging the blade substrate. Machining accuracy. No more than This meets the high aerodynamic performance requirements of the microstructure on the surface of turbine blades. Furthermore, the periodicity and directionality of the texture structure must be consistent with the airflow direction on the blade surface to maximize its control effect on the boundary layer.

[0060] S42, controls texture depth Spacing The ratio satisfies ,in , .

[0061] In some implementations, this step simulates the microscopic morphology of bird feathers by fabricating micron-scale textured structures on the blade surface. The texturing process typically employs laser micromachining techniques, such as femtosecond or nanosecond laser etching, achieving sub-micron level precision and ensuring accurate control over texture depth and spacing. In some implementations, the textured structure can take the form of periodically arranged micropillars or microgrooves, with a depth... Spacing The ratio directly affects the flow characteristics of steam on the blade surface. When If the ratio is too small, the texture's disturbance effect on the airflow is insufficient, making it difficult to effectively enhance adhesion; while if the ratio is too large, it may increase steam flow resistance, thus reducing efficiency. Therefore, the ratio should be controlled within a certain range. Within this range, it can enhance adhesion while avoiding unnecessary flow loss.

[0062] Specifically, in this invention, the texture depth is set. ,spacing The ratio is The parameters fall within the recommended range. This parameter combination, verified through fluid dynamics simulation and experiments, effectively improves the flow stability of steam on the blade surface and reduces the probability of boundary layer separation. Furthermore, the fabrication of this microstructure must meet the surface roughness and geometric accuracy requirements of ISO 10360 to ensure its structural stability and durability under high-temperature, high-pressure steam conditions.

[0063] An embodiment of the present invention provides a method for optimizing the flow structure of a steam turbine based on biomimetic blade design, which can effectively suppress boundary layer separation of steam on the blade surface, improve steam flow efficiency to over 92%, enhance the adaptability of the steam turbine under different load conditions, and significantly reduce energy loss.

[0064] Example 2 The following describes in detail, with reference to the accompanying drawings, a method for optimizing the flow structure of a steam turbine based on biomimetic blade design, according to an embodiment of the present invention.

[0065] The core objective of this invention is to provide a method for optimizing the flow path structure of a steam turbine based on biomimetic blade design, drawing inspiration from bird wings (such as...). Figure 2 The biological characteristics of efficient movement in the air are used to optimize the airfoil structure of turbine blades in order to improve steam flow efficiency and reduce energy loss.

[0066] The specific technical solution includes the following key components: Bionic Airfoil Profile Design: High-speed photography and 3D scanning technology are used to acquire airfoil profile data of a bird's wing in cruise mode. Key parameters such as the leading-edge radius, mid-curvature, and trailing-edge thickness are extracted and transformed into airfoil design benchmarks for turbine blades. Specifically, the blade's leading edge adopts a variable-curvature arc structure consistent with the leading edge of a bird's wing, which reduces boundary layer separation during steam impact compared to a traditional fixed-curvature leading edge. The mid-curvature of the blade employs a nonlinear curvature design to simulate the aerodynamic lift characteristics of a bird's wing, resulting in smoother steam flow on the blade surface. Flow Channel Matching Optimization: Based on the airfoil parameters of the bionic blade, the inlet and outlet angles and cross-sectional areas of the turbine's flow channels are adjusted to control the deviation between the steam flow angle entering the blade and the incident angle at the blade's leading edge within ±3°, avoiding impact losses. Simultaneously, fluid dynamics simulation software is used to optimize the steam velocity distribution within the flow channels, ensuring a uniform velocity gradient as the steam flows through the blade region and reducing eddy current generation.

[0067] Surface microstructure improvement: Drawing inspiration from the micro-texture characteristics of bird feathers, a micron-level concave-convex texture structure is designed on the blade surface. This structure can enhance the adhesion of steam to the blade surface, further suppress boundary layer separation, and improve the stability of steam flow.

[0068] like Figure 3 and Figure 4 As shown, an embodiment of the present invention provides a biomimetic blade design as follows: The leading edge of the blade adopts a variable curvature arc structure consistent with the leading edge of a bird's wing, which can reduce boundary layer separation during steam impact compared to the traditional fixed curvature leading edge. The arc in the blade adopts a non-linear curvature design to simulate the aerodynamic lift characteristics of a bird's wing, making the flow of steam on the blade surface smoother.

[0069] Based on the airfoil parameters of the biomimetic blades, the inlet and outlet angles and cross-sectional areas of the turbine flow passage are adjusted to avoid impact losses. At the same time, the steam velocity distribution in the flow passage is optimized using fluid dynamics simulation software to ensure that the steam maintains a uniform velocity gradient when flowing through the blade area, thereby reducing the generation of eddies.

[0070] By designing a micron-level textured structure on the blade surface, the adhesion of steam to the blade surface can be enhanced, further suppressing boundary layer separation and improving the stability of steam flow.

[0071] Based on the above method, there are also the following specific embodiments: This embodiment focuses on the high-pressure cylinder turbine blades of a 300MW thermal power unit as the optimization target.

[0072] The original parameters of the conventional moving blades of this unit were obtained as follows: leading edge radius R0 = 8 mm, mid-arc line is a linear structure, trailing edge thickness T0 = 5 mm, inlet angle α0 = 15°, outlet angle β0 = 25°; leading edge radius Rb = 12 mm, the maximum curvature point of the mid-arc line is located at 40% of the airfoil chord length, and trailing edge thickness Tb = 3 mm.

[0073] Based on the extracted bird wing parameters and the working environment of the steam turbine blade (steam pressure 16.7 MPa, temperature 538°C), the airfoil parameters were adapted and adjusted: the leading edge radius of the blade was set to R1=10 mm, the maximum curvature point of the mid-arc line was adjusted to 38% of the chord length, and the trailing edge thickness was set to T1=4 mm; micron-level textures were processed on the blade surface using laser engraving technology, with a texture depth h=8 μm and a spacing d=25 μm.

[0074] Based on the biomimetic blade parameters, the inlet and outlet angles of the flow channel are adjusted: inlet angle α1=17°, outlet angle β1=23°, so that the steam incident angle matches the leading edge of the blade; at the same time, the inlet cross-sectional area S1 of the flow channel is increased by 5% and the outlet cross-sectional area S2 is reduced by 3% to optimize the steam velocity distribution.

[0075] The optimized biomimetic blades and flow path structure were applied to the high-pressure cylinder of the 300MW unit, and performance tests were conducted under full load (300MW) and partial load (150MW). The results showed that at full load, the steam flow efficiency reached 93.2%, an improvement of 8.1% compared to the traditional structure; at 150MW load, the steam flow efficiency was 91.5%, with a decay rate of only 1.8%, significantly better than the 5.2% decay rate of the traditional blades, verifying the effectiveness and practicality of the invention.

[0076] Example 3 To achieve the above embodiments, such as Figure 5 As shown, this embodiment also provides a turbine flow structure optimization device 10 based on biomimetic blade design. The device 10 includes an airfoil parameter acquisition module 100, a biomimetic airfoil design module 200, a flow channel adjustment module 300, and a surface texture processing module 400.

[0077] The airfoil parameter acquisition module 100 acquires the airfoil profile parameters of a bird's wing in cruise mode, and extracts the leading edge radius, mid-arc curvature distribution, and trailing edge thickness features. The biomimetic airfoil design module 200 designs the biomimetic airfoil structure of the turbine blade based on the airfoil profile parameters, so that the leading edge of the blade adopts a variable curvature circular arc structure and the middle arc adopts a nonlinear curvature distribution to optimize the flow characteristics of steam on the blade surface. The flow channel adjustment module 300 adjusts the inlet and outlet angles and cross-sectional areas of the turbine flow channel according to the biomimetic airfoil structure, so that the steam incident angle matches the leading edge of the blade and optimizes the steam velocity distribution in the channel. The surface texture processing module 400 uses laser engraving technology to process micron-level concave and convex texture structures on the blade surface to enhance steam adhesion and suppress boundary layer separation.

[0078] Furthermore, the airfoil parameter acquisition module 100 is also used for: S11 uses high-speed camera technology to capture the dynamic deformation process of bird wings during cruising, and obtains airfoil profile data at different angles of attack; S12 uses a three-dimensional scanning device to perform non-contact measurements on bird wing samples, extracting a set of three-dimensional coordinate points for the leading edge radius, the mid-arc curvature distribution, and the trailing edge thickness.

[0079] Furthermore, the aforementioned biomimetic airfoil design module 200 is also used for: S21 adjusts the position of the maximum curvature point of the mid-curvature line from 50% chord length in the traditional airfoil to 38% chord length, thereby improving steam flow efficiency. S22, using a nonlinear function Describe the curvature distribution of the arc, where The value range is the biomimetic curvature index. .

[0080] Furthermore, the aforementioned flow channel adjustment module 300 is also used for: S31, the inlet angle of the flow channel Adjusted to Export angle Adjusted to ,in and For traditional blade inlet and outlet angles; S32 optimizes the steam velocity distribution using fluid dynamics simulation software, reducing the velocity gradient in the blade region. satisfy .

[0081] Furthermore, the surface texture processing module 400 described above is also used for: S41, using pulse width Laser processing is used to refine textures, increasing the processing precision of individual textures. ; S42, controls texture depth Spacing The ratio satisfies ,in , .

[0082] An embodiment of the present invention provides a turbine flow structure optimization device based on biomimetic blade design, which can effectively suppress boundary layer separation of steam on the blade surface, improve steam flow efficiency to over 92%, enhance the adaptability of the turbine under different load conditions, and significantly reduce energy loss.

[0083] To implement the methods of the above embodiments, the present invention also provides a computer device, such as... Figure 6 As shown, the computer device 600 includes a memory 601 and a processor 602; wherein, the processor 602 reads executable program code stored in the memory 601 to run a program corresponding to the executable program code, so as to implement the various steps of the method described above.

[0084] To implement the above embodiments, this application also proposes a non-transitory computer-readable storage medium storing a computer program thereon, which, when executed by a processor, implements the method described in the foregoing embodiments.

[0085] In the description of this specification, the references to terms such as "one embodiment," "some embodiments," "example," "specific example," or "some examples," etc., refer to specific features, structures, materials, or characteristics described in connection with that embodiment or example, which are included in at least one embodiment or example of the present invention. In this specification, the illustrative expressions of the above terms do not necessarily refer to the same embodiment or example. Furthermore, the specific features, structures, materials, or characteristics described may be combined in any suitable manner in one or more embodiments or examples. Moreover, without contradiction, those skilled in the art can combine and integrate the different embodiments or examples described in this specification, as well as the features of different embodiments or examples.

[0086] Furthermore, the terms "first" and "second" are used for descriptive purposes only and should not be construed as indicating or implying relative importance or implicitly specifying the number of technical features indicated. Thus, a feature defined as "first" or "second" may explicitly or implicitly include at least one of that feature. In the description of this invention, "a plurality of" means at least two, such as two, three, etc., unless otherwise explicitly specified.

Claims

1. A method for optimizing the flow structure of a steam turbine based on biomimetic blade design, characterized in that, include: S1, obtain the airfoil profile parameters of the bird's wing in cruise mode, and extract the leading edge radius, mid-arc curvature distribution and trailing edge thickness features; S2. Based on the airfoil profile parameters, design the biomimetic airfoil structure of the turbine blade, so that the leading edge of the blade adopts a variable curvature circular arc structure and the middle arc adopts a nonlinear curvature distribution to optimize the flow characteristics of steam on the blade surface. S3, adjust the inlet and outlet angles and cross-sectional areas of the turbine flow passage according to the biomimetic airfoil structure, so that the steam incident angle matches the leading edge of the blade, and optimize the steam velocity distribution in the passage; S4 uses laser engraving technology to process micron-level textured structures on the blade surface to enhance steam adhesion and suppress boundary layer separation.

2. The method as described in claim 1, characterized in that, S1 includes: S11 uses high-speed camera technology to capture the dynamic deformation process of bird wings during cruising, and obtains airfoil profile data at different angles of attack; S12 uses a three-dimensional scanning device to perform non-contact measurements on bird wing samples, extracting a set of three-dimensional coordinate points for the leading edge radius, the mid-arc curvature distribution, and the trailing edge thickness.

3. The method as described in claim 1, characterized in that, The S2 includes: S21 adjusts the position of the maximum curvature point of the mid-curvature line from 50% chord length in the traditional airfoil to 38% chord length, thereby improving steam flow efficiency. S22, using a nonlinear function Describe the curvature distribution of the arc, where The value range is the biomimetic curvature index. .

4. The method as described in claim 1, characterized in that, The S3 further includes: S31, the inlet angle of the flow channel Adjusted to Export angle Adjusted to ,in and For traditional blade inlet and outlet angles; S32 optimizes the steam velocity distribution using fluid dynamics simulation software, reducing the velocity gradient in the blade region. satisfy .

5. The method as described in claim 1, characterized in that, The S4 includes: S41, using pulse width Laser processing is used to refine textures, increasing the processing precision of individual textures. ; S42, controls texture depth Spacing The ratio satisfies ,in , .

6. A turbine flow structure optimization device based on biomimetic blade design, characterized in that, include: The airfoil parameter acquisition module acquires the airfoil profile parameters of a bird's wing in cruise mode, and extracts the leading edge radius, mid-arc curvature distribution, and trailing edge thickness features. The biomimetic airfoil design module designs the biomimetic airfoil structure of the turbine blade based on the airfoil profile parameters, so that the leading edge of the blade adopts a variable curvature circular arc structure and the middle arc adopts a nonlinear curvature distribution to optimize the flow characteristics of steam on the blade surface. The flow channel adjustment module adjusts the inlet and outlet angles and cross-sectional areas of the turbine flow channel according to the biomimetic airfoil structure, so that the steam incident angle matches the leading edge of the blade and optimizes the steam velocity distribution in the channel. The surface texture processing module uses laser engraving technology to process micron-level concave and convex texture structures on the blade surface to enhance steam adhesion and suppress boundary layer separation.

7. The apparatus as claimed in claim 6, characterized in that, The airfoil parameter acquisition module is also used for: By using high-speed camera technology to capture the dynamic deformation process of bird wings during cruising, airfoil profile data at different angles of attack can be obtained. A three-dimensional scanning device was used to perform non-contact measurements on bird wing samples to extract a set of three-dimensional coordinate points for the leading edge radius, the mid-arc curvature distribution, and the trailing edge thickness.

8. The apparatus as claimed in claim 6, characterized in that, The biomimetic airfoil design module is also used for: The location of the maximum curvature point of the mid-curvature line was adjusted from 50% of the chord length in the traditional airfoil to 38% of the chord length, thereby improving the steam flow efficiency. Using nonlinear functions Describe the curvature distribution of the arc, where The value range is the biomimetic curvature index. .

9. A computer device, characterized in that, Including processor and memory; The processor reads executable program code stored in the memory to run a program corresponding to the executable program code, so as to implement the turbine flow structure optimization method based on biomimetic blade design as described in any one of claims 1-5.

10. A non-transitory computer-readable storage medium having a computer program stored thereon, characterized in that, When executed by the processor, the program implements the turbine flow structure optimization method based on biomimetic blade design as described in any one of claims 1-5.

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