30 results about "Thrust coefficient" patented technology

The invention discloses a ship maneuverability prediction method, a ship maneuverability prediction system and a ship maneuverability prediction device taking propeller performance changes into regular waves. The method comprises the following steps: firstly, calculating the motion response, the second-order wave drift force and the drift moment of a ship body under different regular wave conditions based on a potential flow theory, establishing a wave force fitting equation taking the wave direction and the navigational speed as variables, and performing ship manipulation motion numerical simulation in regular waves based on an obtained calculation result; acquiring an input parameter range of the propeller in a manipulating motion state; establishing a CFD numerical model of ship propeller performance in regular waves, simulating heaving and pitching motion of the propeller under motion response, determining the range of the heaving and pitching motion, and calculating propeller thrust data under different wave conditions and input parameters; and carrying out regression analysis on the propeller thrust data, and fitting to obtain a prediction formula of the propeller thrust coefficient in the regular waves. The formula couples the wavelength-to-length ratio, the advance speed coefficient and the wave direction angle, and quantifies the dynamic influence of the wave on the propeller thrust.

This invention relates to the field of marine propulsion device manufacturing, specifically a design method for a fully azimuth-controlled adjustable-pitch ducted propeller. This method extracts the basic parameters of the ship's main engine and existing rudder propeller, and establishes an integrated arrangement scheme to replace the fixed-pitch propeller with an adjustable-pitch propeller while maintaining the original power parameters unchanged. Based on the theoretical diagram of the fixed-pitch ducted propeller, a hydrodynamic calculation program is executed, introducing correction factors for increased shell diameter ratio and slightly reduced disk area ratio, and forcibly lowering the theoretical thrust coefficient by 5%, to obtain the corrected target open-water characteristic curve. The overall rotational characteristics of the fully azimuth-controlled rudder propeller are utilized to provide thrust for reversing and steering, strictly limiting the pitch adjustment authority to adaptability requirements for low-speed navigation and providing maximum drag under multiple operating conditions. A single-crank slider mechanism is configured inside the propeller hub as the core rotor component, and a three-dimensional spatial layout is completed. An electro-hydraulic integrated servo control system, dominated by a PLC and incorporating a dual-pump parallel architecture and a built-in hydraulic lock, is established. This significantly reduces the frequency and physical amplitude of the propeller blade rotation angle.

The invention belongs to the technical field of aero-engines, and particularly relates to an air film cooling two-dimensional nozzle thrust coefficient loss rapid calculation method which comprises the steps that the total flow of a nozzle is determined, and the total flow comprises the inner culvert flow, the flow flowing through an air film plate, the flow flowing through an impact-air film plate and the outer culvert leakage flow; based on the gas film hole inclination angle and the local loss factor, the speed v of the gas flow passing through the gas film plate is determined; based on the sectional area of the cooling channel and the hole area of the baffle, the speed v25 of the airflow passing through the baffle is determined; calculating the energy loss of the air flow passing through the impact-air film plate, and determining the speed v3 of the air flow passing through the impact-air film plate based on the inclination angle of the impact-air film hole; and substituting each airflow velocity into a thrust coefficient calculation formula to calculate the thrust coefficient loss.

This invention discloses an aerodynamic optimization design method for scaled-down model blades of large vertical axis wind turbines based on DMST theory. The method includes: determining scaled-down parameters according to wind tunnel similarity criteria; selecting an optimized airfoil for aerodynamic characteristic matching at low Reynolds numbers based on the lift-to-drag ratio characteristics of the prototype blades; constructing an aerodynamic performance model based on dual-disk multi-flow theory, calculating and verifying the theoretical thrust coefficients of the prototype and optimized airfoils; conducting force-pressure tests in a wind tunnel, extracting the pure thrust of the blades by subtracting the total thrust of the turbine from the tower thrust vector; and comparing the measured thrust coefficients with the theoretical thrust coefficients to verify the aerodynamic load matching degree. This invention effectively eliminates the Reynolds number effect in scaled-down tests by combining airfoil optimization, DMST theory verification, and wind tunnel test verification, achieving high-precision matching of aerodynamic loads on scaled-down model blades of vertical axis wind turbines and improving the reliability of wind tunnel test data.

This invention belongs to the field of electronic digital data processing and discloses a propulsion modeling method for FPSOs based on Modelica, comprising the following steps: S1: Modeling the propulsion coefficient model of the propeller, including calculating the following parameters: thrust coefficient, thrust torque coefficient, thrust gain coefficient, and thrust torque gain coefficient; S2: Modeling the propeller performance model, including calculating the following parameters: wake coefficient, advance number, thrust loss coefficient, and relative rotational efficiency; S3: Based on the results of steps S1 and S2, outputting the thrust and thrust torque of the propeller, thereby obtaining the propulsion efficiency of the propeller. This method can comprehensively simulate the thrust and torque variation characteristics of the propeller under different operating conditions through a discrete dynamic modeling approach, thus providing accurate simulation support for the dynamic response of FPSO systems in complex marine environments.

The invention belongs to the technical field of aero-engine double-duct nozzle thrust coefficient determination, and particularly relates to an aero-engine double-duct nozzle thrust coefficient determination method which comprises the following steps: step 1, constructing a double-duct nozzle calculation model; 2, setting an air inlet condition and outlet back pressure of the double-duct spray pipe, and calculating to obtain flow field distribution and inlet and outlet parameters of the double-duct spray pipe according to a calculation model of the double-duct spray pipe; 3, based on the inlet and outlet parameters of the double-duct spray pipe, the theoretical thrust of the inner duct spray pipe and the theoretical thrust of the outer duct spray pipe are obtained through calculation; step 4, based on the theoretical thrust of the inner duct spray pipe, the theoretical thrust of the outer duct spray pipe and the real thrust of the double-duct spray pipe; 5, on the basis of the inlet and outlet parameters of the double-duct spray pipe, the one-dimensional isentropic complete expansion thrust of the double-duct spray pipe is calculated; and 6, calculating the thrust coefficient of the double-duct nozzle based on the real thrust and the one-dimensional isentropic complete expansion thrust of the double-duct nozzle.

The present application belongs to the field of aero-engine nozzle aerodynamic optimization, and discloses a discrete-adjoint nozzle thrust coefficient surface sensitivity calculation method and system. The surface sensitivity algorithm and system capture the response of the flow field to the nozzle thrust coefficient through the discrete-adjoint equation, take the spatial sensitivity as an intermediate bridge to separate the geometric direct effect and the flow field indirect effect, combine the radial basis function RBF-transfinite interpolation TFI to calculate the mapping derivative, and transfer the nozzle spatial structure grid deformation, so that the whole solving process is independent of the number of design variables, and high-precision and high-efficiency sensitivity calculation of the nozzle thrust coefficient to the surface parameters is realized. The surface sensitivity algorithm and system solve the problems of low optimization efficiency, poor precision and weak adaptability of the nozzle, realize accurate and efficient analysis of the influence of the nozzle thrust coefficient on the surface parameter sensitivity, provide key technical support for improving the nozzle thrust coefficient, and have engineering practical value.

The invention discloses a wind turbine generator group wake flow optimization method and system suitable for generating power synergy. The method comprises the following steps: establishing an engineering wake flow model considering wake flow delay; in the wake flow area, the equivalent wind speed of the downstream wind turbine generator is calculated; acquiring a sensitivity coefficient of the wind speed with respect to the thrust coefficient based on an engineering wake flow model; acquiring a wind speed sensitivity coefficient according to the fact that the equivalent wind speed is a polynomial about an upstream unit thrust coefficient, namely a multivariate nonlinear function about a tip speed ratio and a pitch angle; establishing a wind turbine generator group increment state-space equation based on the wind speed sensitivity coefficient; establishing an optimization target for improving the generated power; and based on the wind turbine generator group increment state equation of the wind speed sensitivity coefficient, an optimization value is solved, and an optimization instruction of the optimized active power and the pitch angle is sent to a wind turbine generator controller.

The invention belongs to the technical field of aero-engine exhaust nozzle pneumatic optimization, and discloses an exhaust nozzle thrust coefficient surface sensitivity algorithm and system based on discrete accompanying. According to the surface sensitivity algorithm and system, response of a flow field to a thrust coefficient of the exhaust nozzle is captured through a discrete adjoint equation, a geometric direct effect and a flow field indirect effect are separated by taking space sensitivity as an intermediate bridge, and grid deformation of a mapping derivative transfer exhaust nozzle space structure is calculated in combination with a radial basis function (RBF)-over-limit interpolation (TFI); the whole solving process is irrelevant to the number of design variables, and high-precision, high-efficiency and high-sensitivity calculation of the thrust coefficient of the exhaust nozzle on the surface parameters is achieved. According to the surface sensitivity algorithm and system, the problems of low optimization efficiency, poor precision and weak adaptability of the exhaust nozzle are solved, accurate and efficient analysis of the influence of the thrust coefficient of the exhaust nozzle on the surface parameter sensitivity is realized, key technical support is provided for improvement of the thrust coefficient of the exhaust nozzle, and the surface sensitivity algorithm and system have engineering practical value.

This application belongs to the field of aero-engine testing technology, specifically relating to a method for estimating the thrust correction coefficient of an aero-engine indoor test stand, including: Step 1, determining the performance and structural parameters of the target aero-engine; Step 2, finding a reference aero-engine, wherein the performance and structural parameters of the reference aero-engine are of the same order of magnitude as those of the target aero-engine, and the thrust coefficient on the target test stand is already known; Step 3, calculating the ratio of the impulse of the target aero-engine to that of the reference aero-engine; Step 4, correcting the thrust correction coefficient of the reference aero-engine using the ratio of the impulse of the target aero-engine to that of the reference aero-engine, thereby obtaining the thrust correction coefficient of the target aero-engine.

This invention discloses a method for monitoring the comprehensive performance of ships, including: a speed performance monitoring process and a cost-effectiveness monitoring process. The speed performance monitoring process includes: constructing the ship's total resistance, torque coefficient, and thrust coefficient using three sets of polynomials containing unknowns to be identified; dividing the value ranges of the three sets of unknowns into several value intervals; using an improved genetic algorithm, finding the optimal solution in each value interval of the unknowns, and taking the smallest optimal solution as the final solution; calculating the ship's real-time parameters in the ship's mathematical model based on the values ​​of the three sets of unknowns corresponding to the final solution, thus completing the ship's speed performance monitoring; the cost-effectiveness monitoring process includes: calculating cost-effectiveness based on the degree of change in naval coefficients, the degree of change in monitoring system functional indicators, and the cost of the monitoring system. This invention can better obtain ship speed performance indicators and more accurately and dynamically obtain cost-effectiveness.

The application relates to the technical field of wind turbine wake calculation, in particular to a wind farm full-field full-domain wake analysis method based on yaw control, which comprises the following steps: acquiring wind turbine parameters and terrain and inflow parameters of an operating environment in a wind farm, including the position of the wind turbine, the rotor diameter, the hub height, the yaw angle and the thrust coefficient, the flat terrain inflow wind speed, the complex terrain inflow wind speed and the turbulence intensity; calculating the lateral offset of the wake generated by the yaw of the wind turbine based on the law of conservation of momentum and the law of conservation of mass; calculating the wake width downstream of the wind turbine based on the inflow parameters and the lateral offset of the wake, and determining the range of the wake area; calculating the initial speed loss of the full-field full-domain wake based on the law of conservation of mass and the cosine distribution function; and obtaining the full-field full-domain wake speed of the wind farm based on the inflow speed and the wake speed loss at the complex terrain. Through comprehensive consideration of factors such as complex terrain, wake yaw and wake interaction, high-precision prediction of the wake speed of the wind farm is realized.

The invention relates to a wind speed fine correction method and system based on a physical effect. The method comprises the steps that a double-Gaussian wake flow model is constructed, model parameters are determined based on a thrust coefficient and turbulence intensity of a wind turbine, and wake flow velocity loss distribution is represented by adopting a double-Gaussian function. The method comprises the steps that a CFD field machine integrated simulation model is established, a flow field model is established based on large vortex simulation, a wind turbine is modeled to be an actuator disc capable of being dynamically adjusted, and dynamic operation of the turbine is simulated by sensing local wind speed and wind direction in real time and updating aerodynamic loads and yaw angles. And inputting the speed loss output by the double-Gaussian wake flow model as a correction value into the CFD field-machine integrated simulation model for flow field solution, and obtaining corrected wind speed distribution. According to the method, wake flow velocity loss distribution characteristics are accurately described through the double-Gaussian wake flow model, and accurate prediction of wind speed distribution and power output of the wind power plant under complex terrains and dynamic working conditions is realized in combination with a dynamic response mechanism of CFD field machine integrated simulation.

The application discloses a large vertical axis fan wind tunnel scale model blade aerodynamic optimization design method based on a DMST theory, and comprises the following steps: determining scale parameters according to wind tunnel test similarity criteria; selecting an optimized airfoil with matched aerodynamic characteristics under low Reynolds number based on the lift-drag ratio characteristics of a prototype blade; constructing an aerodynamic performance model based on a double disk multi-flow management theory, calculating the theoretical thrust coefficient of the prototype and the optimized airfoil, and performing matching verification; carrying out a force-measuring and pressure-measuring test in a wind tunnel, stripping the pure thrust of the blade by subtracting the total thrust of the whole machine from the thrust vector of the tower column; and comparing and verifying the aerodynamic load matching degree by comparing the measured thrust coefficient with the theoretical thrust coefficient. The application combines airfoil optimization, DMST theory verification and wind tunnel test stripping verification, effectively eliminates the Reynolds number effect in the scale test, realizes high-precision matching of the aerodynamic load of the vertical axis fan scale model blade, and improves the reliability of the wind tunnel test data.

The invention relates to the technical field of aerodynamic design of helicopter rotors, and discloses a coaxial rotor blade aerodynamic configuration optimization design method, which comprises the following steps of: determining an optimization state and an optimization target: determining that a flight state needing to be calculated and analyzed is a hovering state, and correspondingly analyzing and evaluating the optimization target as hovering efficiency and a maximum tension coefficient; a reference model of the rotor wing type of the coaxial rotor aircraft is selected, and the datum blade aerodynamic configuration is constructed based on reference model parameters; determining an optimization parameter range and an optimization strategy: setting the optimization parameter range and the optimization strategy according to the aerodynamic configuration of the reference blade; and differential optimization of the aerodynamic configuration of the blade: based on a Kriging model, performing differential optimization on the aerodynamic configuration of the reference blade by adopting an NSGA-II multi-target genetic algorithm. The hovering efficiency of the coaxial rotor wings can be effectively improved, the influence of aerodynamic interference between the upper rotor wings and the lower rotor wings is avoided or reduced, and then the performance of the aircraft is improved.

The invention provides an ejector nozzle wind tunnel test thrust measuring and calculating method under engine body streaming interference, and belongs to the technical field of nozzle wind tunnel tests. The method comprises the steps that a main jet flow air inlet channel and a secondary flow air inlet channel of an ejector nozzle are constructed, different main flow drop-pressure ratio and secondary flow drop-pressure ratio conditions of the injection spray pipe are simulated by adjusting main flow inlet conditions and secondary flow inlet conditions entering a main flow inlet channel and a secondary flow inlet channel of the injection spray pipe; the total pressure and the total temperature at an inlet of a main spray pipe of the injection spray pipe, the total pressure and the total temperature at an inlet of a secondary flow channel and the total pressure and the static pressure at an outlet of the injection spray pipe are obtained, and the actual thrust of the injection spray pipe in a given test state is calculated based on test measurement data of the total pressure and the static pressure at the outlet of the injection spray pipe; the ideal thrust of the injection nozzle in a given test state is calculated based on the total pressure and total temperature test measurement data at the inlet of the injection nozzle, and finally the thrust coefficient of the injection nozzle is obtained by calculating the ratio of the actual thrust to the ideal thrust of the injection nozzle.

This invention relates to an aerodynamic optimization design method for propellers of multi-condition unmanned aerial vehicles (UAVs), and more particularly to an optimization design method for propellers of low Reynolds number and small advance ratio UAVs based on genetic algorithms and sheet theory. It belongs to the field of aerodynamic performance technology for micro fixed-wing UAVs. The method optimizes the thrust coefficient, hovering and cruise efficiency of the propellers of UAVs with low Reynolds number and small advance ratio under hovering and cruise conditions. The chord length and twist angle of the corresponding propeller blades are obtained through the optimized thrust coefficient, hovering and cruise efficiency, and the UAV propeller configuration is designed based on the chord length and twist angle of the propeller blades.

The invention discloses a fan cut-out control method and system based on air density and wind speed real-time fusion. The control method comprises the following steps of multi-source data real-time collection, air density and wind speed data processing, thrust coefficient matching, real-time load calculation and threshold value comparison and cut-out decision making. The control system comprises a sensor module, a data processing module, a storage module, a control module and a communication module. According to the control method and system, the safety of the unit can be guaranteed, and meanwhile the power generation efficiency is improved.

The application belongs to the technical field of the inclined shaft TBM anti-falling support, and particularly relates to an ABS support device suitable for a large-inclination-angle inclined shaft TBM and a structural optimization method thereof, which comprises the following steps: taking the center of a supporting shoe of the ABS support device as an origin to establish a coordinate system; establishing a thrust equation required by a hydraulic cylinder and a connecting rod of the ABS support device to provide a thrust; deriving a thrust coefficient and an integral value of the thrust coefficient according to the obtained thrust equation, and constructing a structural optimization function of the ABS support device; and taking a horizontal distance between the supporting shoe of the ABS support device and a rack and a ratio of the thrust coefficients of the hydraulic cylinder and the connecting rod as constraint conditions to solve optimal structural sizes of the ABS support device. The optimal structural sizes of the ABS support device are obtained by taking the horizontal distance between the supporting shoe of the ABS support device and the rack of a TBM main machine as a constraint condition, the anti-falling support capability of the ABS support device can be improved, the falling risk of the inclined shaft TBM can be reduced, and thus serious personnel casualties and property losses can be avoided.

The invention relates to determining a reduced thrust coefficient mode of operation for a wind turbine The invention includes retrieving a baseline mode of operation of the wind turbine, defined as a baseline optimal pitch curve having a baseline optimal TSR value. The invention includes retrieving a thrust coefficient table and a power coefficient table. The invention includes defining a maximum thrust coefficient value that is less than a thrust coefficient value of the baseline optimal TSR value in the thrust coefficient table. The invention includes determining, based on the coefficient tables, a maximum thrust coefficient pitch curve that maximises power coefficient value against a constraint that the maximum thrust coefficient value is not exceeded. The invention includes determining the reduced thrust coefficient mode of operation, defined as a reduced thrust coefficient optimal pitch curve determined by modifying the baseline optimal pitch curve using the maximum thrust coefficient pitch curve.

The present application relates to a spacecraft maneuvering acceleration estimation method for sparse data, and aims to solve the problem that the existing method cannot predict the flight trajectory of a target star in real time for some special cases, resulting in a low success rate of the interception process. The process is as follows: I. The interceptor measures and records the measurement data of the target star, i.e. the position and speed of the target star; when the number of measurement data of the target star obtained by the interceptor is greater than or equal to N, execute II; II. Establish a linear relative motion equation of the target star relative to the reference orbit; III. Derive a relative state analytical prediction expression of the target star relative to the reference orbit; IV. Establish a target star measurement equation about the thrust coefficient; V. Solve the target star measurement equation by the weighted least squares method to obtain the thrust coefficient, thereby obtaining the estimated value of the target star maneuvering acceleration. The present application is used in the field of spacecraft maneuvering acceleration estimation.

The invention discloses an air-drop object assembly and a dropping method thereof, and relates to the field of aviation air-drop. Comprising a plurality of air-dropped objects arranged on a flight carrier; at least part of the air-dropped object is provided with a left-handed rotor wing and / or a right-handed rotor wing; at least one pair of the one or more pairs of air-dropped objects which are symmetrically distributed meets one of preset conditions, and the preset conditions comprise that the rotation directions of the rotors arranged on the two air-dropped objects are opposite; one of the two air-dropped objects is not provided with a rotor wing; the two air-dropped objects are provided with rotor wings which are the same in rotation direction and different in rotor wing tension coefficient. The problem that efficiency and economical efficiency are difficult to consider at the cost of sacrificing the load capacity or increasing the system complexity when air-dropped object distribution is achieved in the prior art is solved, and repeated back-and-forth flight is avoided.

The application discloses an integrated design method of an INVELOX wind turbine device and belongs to the technical field of wind power generation. The application constructs a volume force model of the wind turbine, equivalently converts axial momentum action of the turbine on airflow into a continuously distributed axial volume force source term, and obtains an optimal thrust coefficient by taking wind energy available for turbine theory as an optimization target to optimize, thereby determining a feasible region of one-dimensional design parameters of the turbine, sequentially completing forward aerodynamic design of the turbine, three-dimensional modeling of blades and single-channel performance verification, and finally realizing integrated matching verification of a flow channel and the turbine. The application greatly improves the applicability of turbine design to the INVELOX internal flow condition, reduces design calculation cost and period, significantly improves the wind energy utilization coefficient and turbine aerodynamic efficiency of the device, and can be widely applied to the design and optimization of wind power gathering type wind power generation devices.

The present application relates to a kind of vertical axis tidal current energy turbine multi-parameter coupling experiment and intelligent model collaborative optimization method, the method includes: based on orthogonal experimental design and response surface method to construct the multi-level interaction working condition of blade key geometric parameters, obtain power and thrust coefficient performance curve, introduce global optimization of genetic algorithm and obtain optimal geometric configuration;Using variable pitch mechanism, determine the optimal variable pitch strategy considering power improvement and load fluctuation suppression;Introduce turbulence intensity correction coefficient, represent the performance degradation law of turbine under complex inflow, construct robust prediction model;Phase-locked PIV flow field measurement is executed under different working conditions, establish the quantitative correlation model of flow field characteristics and instantaneous load fluctuation, and feedback optimal parameter combination back to experimental design.Relative to the prior art, the present application has disclosed the multi-parameter nonlinear coupling mechanism of turbine energy trapping efficiency and operating stability, provides physical basis for its optimization design and the like advantages.

A method is described for estimating the pitch angle (γ) of the blades (25) of a rotor (10, 10') of an aircraft (1) capable of hovering comprising a motor member (16) with a stator (14) and an output shaft (18) rotatable about the stator (14); a hub (19) rotatable about the axis (B) and operatively connected with the output shaft (18) so as to be rotatable with an angular velocity (ω) about the axis (B); at least two blades (25) rotatable about the axis (B) and about corresponding second axes (D) of extension of the blades (25), so as to adjust the pitch angles (γ) of the blades (25) between a first value (α) and a second value (β) different from each other; the method comprises the steps of: i) computing a third value associated with the torque (τEM) generated by the motor (16); ii) computing a fourth value associated with the torque (τtr) required, in use, by the rotor (10, 10'); iii) computing a fifth value associated with the thrust coefficient (CP) and a sixth value associated with the thrust coefficient (CT) of the rotor (10, 10'), also based on the fourth value; iv) comparing the fifth and sixth values with seventh and eighth threshold values (ThP, ThT); and v) estimating a ninth value of the pitch angle (γ), based on the result of step iv). (Figure 2)

The invention relates to a method for calibrating a wind turbine rotor model comprising several blade sections, from measurements (Mes) and input curves, in which at least the following steps are carried out: a) from the measurements taken, a speed ratio and a blade orientation angle are associated (Ass) with certain wind speeds; b) modification curves of the lift coefficient (C1_port) and drag coefficient (C1_train) are constructed (Cons) and power coefficient (Cart_P) maps (Cart_T) are determined for different sets (Jp) of parameters; c) comparative curves of the power coefficient (C1_P) and thrust coefficient (C1_T) are generated; d) the modification parameter sets allowing a predefined function to be minimized are retained as final modification parameters (Jp_opt); e) the aerodynamic characteristics of the rotor model are calibrated (Cal1). Figure 1 to be published

This application discloses a method for identifying aerodynamic parameters of a tail-saddle unmanned aerial vehicle (UAV) and applying it to a data processing device. The method includes: obtaining a propeller thrust coefficient function; obtaining steady-state flight data collected by airborne sensors when the tail-saddle UAV is in steady-state flight at different pitch and sideslip angles; calculating propeller thrust based on the steady-state flight data and the propeller thrust coefficient function; calculating aerodynamic forces by combining dynamic equations and decomposing them into lift, drag, and sideslip forces; calculating aerodynamic coefficients at different angles of attack and sideslip angles; and obtaining the aerodynamic coefficient function based on a polynomial model and least squares fitting. This application does not require specialized equipment such as wind tunnels, but only relies on low-cost airborne sensors to complete aerodynamic identification covering the entire flight envelope in a real flight environment, reducing the cost of engineering applications.

The application discloses a fan mechanism modeling and optimization method and system based on a neural network, and the method comprises the following steps: a model of a wind energy utilization coefficient and a thrust coefficient of a fan is established, and steady-state simulation is performed to obtain a two-dimensional relationship table model of the wind energy utilization coefficient and the thrust coefficient, and a fan aerodynamics model is established based on the two-dimensional relationship table model; a fan transmission chain system model and a fan blade and tower coupling model are respectively established based on nonlinear aerodynamic torque T r and nonlinear air thrust F t in the fan aerodynamics model, so that a complete fan mechanism model is obtained; actual operation data of the fan are collected, deviations of the fan mechanism model and the actual operation data of the fan are analyzed based on a neural network, and correction is performed through the neural network, so that an optimized fan mechanism model is obtained. The application can improve the precision of fan modeling.

The application relates to a blade reconstruction method of a floating vertical axis fan model for a scale-down test, the aerodynamic parameters of a full-scale fan including an actual thrust coefficient and an actual side force coefficient, and the blade reconstruction method comprising the steps of: determining a scale-down ratio of the fan model according to test conditions; calculating initial blade chord length c0 and torsion angle beta0 of the fan model according to the Froude similarity law; calculating a Reynolds number of the fan model blade, and selecting a low Reynolds number airfoil; determining a thrust coefficient calculation expression C T (c, beta) of the fan model and a side force coefficient calculation expression C S (c, beta) of the fan model; at (c0, beta0), Taylor expansion formulae are used to expand C T (c, beta) and C S (c, beta) to obtain a binary first-order equation group by taking the actual thrust coefficient and the actual side force coefficient as target values and inputting the expanded expressions; and target chord length and target torsion angle of the fan model blade are solved to realize effective blade reconstruction and accurately simulate double-degree-of-freedom aerodynamic loads suffered by the fan.

The application provides a kind of intelligent speed regulation method and system of thermal power station fan, method includes: based on the extraction of time-frequency characteristics of multi-modal data, based on the extraction of dynamic working condition characteristics of boiler working condition parameters, fusion is obtained joint state vector;Based on the generation of fan continuous action instruction of joint state vector;With non-dominated sorting genetic algorithm based on the optimization of continuous action instruction of boiler working condition parameters, generate optimized control solution set and execute speed regulation.The application realizes real-time sensing of operating state by multi-modal data fusion and dynamic working condition adaptive optimization mechanism, first extracts features to generate joint state vector, then provides model support by combining online updating aerodynamic knowledge base;Finally, through working condition adaptive optimization algorithm, dynamically adjust the weight coefficient of wind energy efficiency and mechanical load, impose exponential penalty on thrust coefficient constraint, generate optimized control solution set that matches boiler load demand, coal quality characteristics and meets safety boundary, solve the control mismatch problem of traditional method.