Francis turbine electrohydraulic inlet guide vane control by artificial neural network 2 degree-of-freedom PID controller with actuator fault

2020 ◽  
pp. 095965182097379
Author(s):  
Vinod J ◽  
Bikash Kumar Sarkar
Keyword(s):  
Neural Network ◽  
Mathematical Model ◽  
Guide Vane ◽  
Francis Turbine ◽  
Inlet Guide Vane ◽  
Power Demand ◽  
Proportional Integral Derivative ◽  
Proportional Integral Derivative Controller ◽  
Piston Seal ◽  
Controller Performance

Hydropower system has great attention due to the cheapest and simplest renewable power generation, available potential and environmental concern. Francis turbine has wide operating range compare to other hydro turbine runner. Electrohydraulic Francis turbine inlet guide vane system has advantages like, high power density, self-lubrication property, very good controllability and rugged. Francis turbine inlet guide vane system consists of inlet guide vane actuation system, ring inlet guide blade arrangement, and controller. The main challenges with the electrohydraulically actuated inlet guide vane system are nonlinear characteristic, parametric uncertainty, and external disturbances. Further with respect to the real-life application of the electrohydraulic actuator piston seal damage may occur due to fitting problem of the seal, impurities in the hydraulic oil, high temperature of the hydraulic oil and so on. Recently some researchers are reported on modelling accuracy, accurate controller design and stability analysis. In the present study mathematical model of the Francis turbine has been developed based on velocity diagram to capture effect of water flow dynamics on turbine power generation with the consideration of Euler’s equation of turbo machinery. Detailed mathematical model of the inlet guide vane actuating system has been integrated with Francis turbine model. Artificial neural network 2 degree-of-freedom proportional integral derivative controller has been developed for Francis turbine power/speed control. The controller performance has been studied with the consideration of actuator piston seal damage. The controller performance has been studied with 30%, 60%, and 90% step increase of power demand. The controller performance also has been studied with 0.005 and 0.05 Hz frequency sinusoidal power demand. The proposed controller performance has been compared with conventional proportional integral derivative controller through various performance indexes. The proposed controller performances also have been compared with recently reported work due to step increase of torque and step decreases of power demand.

System modeling and instability control of wind turbine blade based on hydraulic pitch system and radial basic function neural network proportional–integral–derivative controller

2018 ◽  
Vol 232 (10) ◽  
pp. 1412-1428 ◽  
Author(s):  
Tingrui Liu
Keyword(s):  
Neural Network ◽  
Wind Turbine ◽  
Turbine Blade ◽  
System Modeling ◽  
Basic Function ◽  
Wind Turbine Blade ◽  
Proportional Integral Derivative ◽  
Proportional Integral Derivative Controller ◽  
Thin Walled ◽  
Pitch System

System modeling and aeroservoelastic control for divergent instability of stall-induced composite wind turbine blade modeled as thin-walled symmetric layup beam analysis have been investigated based on hydraulic pitch system and radial basic function neural network control. The blade is modeled as single-cell thin-walled beam structure with the circumferentially asymmetric stiffness design, exhibiting flap/lead-lag bending coupling deformation. The stall flutter and aeroservoelastic control of composite blade are investigated based on dynamic stall Beddoes–Leishman aerodynamic model and radial basic function neural network proportional–integral–derivative controller, with pitch actuator performed by hydraulic system. The system motion equations consist of the aeroelastic equations and the six-order pitch equation. The nonlinear aeroelastic responses, including both flap/lead-lag responses and pitch angle responses under different parameters, are solved by Galerkin method and the nonlinear time integration scheme with nonlinear residual analysis. To verify the effectiveness of the control scheme and realize visualized display of large thin-walled blade in the laboratory, experimental platform based on hardware-in-the-loop simulation is built to realize real-time control and virtual simulation. The platform structure consists of PLC hardware, monitoring interface in configuration software, and simulation environment that is connected by the OPC server with PLC system. The platform lays the foundation for vibrational behavior research on visualization of large wind turbine blade under divergent stall situation and verifies the real-time feasibility of the control algorithm proposed.

Position Control of the Hydraulically Actuated Francis Turbine Inlet Guide Vane

2017 ◽  
Author(s):  
Paladugu Venkaiah ◽  
Bikash Kr. Sarkar
Keyword(s):  
Fossil Fuels ◽  
Position Control ◽  
Guide Vane ◽  
Low Cost ◽  
Francis Turbine ◽  
Inlet Guide Vane ◽  
Hydro Power ◽  
Renewable Source ◽  
Area Of Interest ◽  
Arbitrary Position

Development of the renewable source of energy has become an area of interest due to increasing power demand and fixed fossil fuels in the universe. To increase efficiency of the renewable source of energy like, hydro power become important. In the present work, adaptive feedforward fuzzy PID controller has been developed for position control of the electrohydraulic actuation turbine IGV system. Electrohydraulic turbine governing systems are superior to the electromechanical governing system due to the high power availability, very good controllability, self lubrication property etc. NACA 0012 aerofoil blade configuration has been considered for the turbine IGV system due to the less lift force which lead to the less effort required to governing action. Low cost proportional valve control electrohydraulic system configuration has been considered. Simulation study has been carried in Matlab Simulink environment. The system IGV position control has been studied for step, sinusoidal and arbitrary position demand.

scholarly journals Motion Control and Implementation for an AC Servomotor System

2007 ◽  
Vol 2007 ◽  
pp. 1-6 ◽  
Author(s):  
L. Canan Dülger ◽  
Ali Kireçci
Keyword(s):  
Mathematical Model ◽  
Dynamic Behavior ◽  
Motion Control ◽  
Trajectory Tracking ◽  
Pid Controller ◽  
Experimental Validation ◽  
Experimental Setup ◽  
Tracking Problem ◽  
Proportional Integral Derivative ◽  
Proportional Integral Derivative Controller

This paper presents a study on trajectory tracking problem for an AC synchronous servomotor. A mathematical model for the system including AC synchronous servomotor, gearbox, and a load is developed to examine the systems dynamic behavior. The system is controlled by a traditional PID (proportional + integral + derivative) controller. The required values for the controller settings are found experimentally. Different motion profiles are designed, and trapezoidal ones are implemented. Thus, the experimental validation of the model is achieved using the experimental setup. The simulation and experimental results are presented. The tracking performance of an AC servomotor system is illustrated with proposed PID controller.

scholarly journals A New Processing Method Combined with BP Neural Network for Francis Turbine Synthetic Characteristic Curve Research

2017 ◽  
Vol 2017 ◽  
pp. 1-11 ◽  
Author(s):  
Junyi Li ◽  
Canfeng Han ◽  
Fei Yu
Keyword(s):  
Neural Network ◽  
High Efficiency ◽  
Guide Vane ◽  
Characteristic Curve ◽  
Flow Characteristics ◽  
Transition Process ◽  
Francis Turbine ◽  
Operation Conditions ◽  
New Perspective ◽  
New Processing

A BP (backpropagation) neural network method is employed to solve the problems existing in the synthetic characteristic curve processing of hydroturbine at present that most studies are only concerned with data in the high efficiency and large guide vane opening area, which can hardly meet the research requirements of transition process especially in large fluctuation situation. The principle of the proposed method is to convert the nonlinear characteristics of turbine to torque and flow characteristics, which can be used for real-time simulation directly based on neural network. Results show that obtained sample data can be extended successfully to cover working areas wider under different operation conditions. Another major contribution of this paper is the resampling technique proposed in the paper to overcome the limitation to sample period simulation. In addition, a detailed analysis for improvements of iteration convergence of the pressure loop is proposed, leading to a better iterative convergence during the head pressure calculation. Actual applications verify that methods proposed in this paper have better simulation results which are closer to the field and provide a new perspective for hydroturbine synthetic characteristic curve fitting and modeling.

PERANCANGAN UJI SIRIP ROKET BAGIAN AILERON DENGAN MENGGUNAKAN KONTROL PID

2018 ◽  
Vol 14 (1) ◽  
pp. 1-11
Author(s):  
Galih Irfan Firdaus
Keyword(s):  
Proportional Integral Derivative ◽  
Accelerometer Sensor ◽  
Proportional Integral Derivative Controller ◽  
Proportional Integral

Roket merupakan sebuah peluru kendali atau suatu kendaraan terbang yang mendapatkan dorongan melalui reaksi roket secara cepat dengan bahan fluida dari keluaran mesin roket. Sistem Kendali Sirip Roket berbasis Mikrokontroller ATmega8 berguna untuk mengendalikan sirip roket khususnya bagian aileron.  Dibutuhkan komponen – komponen pendukung berupa Sensor Accelerometer, Sensor Gyroscope, ATmega8 dan Motor Servo. Alat pengendali sirip roket ini dapat digunakan untuk mengendalikan sirip roket bagian aileron pada saat posisi roket tidak stabil atau terjadi gerakan naik turun pada saat setelah diluncurkan, sehingga dapat menghasilkan penerbangan yang maksimal dalam mencapai sasaran.Perancangan yang  digunakan adalah jenis pengendalian dengan kontrol PID. PID (Proportional Integral Derivative controller) merupakan kontroller untuk menentukan presisi suatu sistem instrumentasi dengan karakteristik adanya umpan balik pada sistem tesebut. Pengontrol PID adalah pengontrol konvensional yang banyak dipakai dalam dunia industri. Karakteristik pengontrol PID sangat dipengaruhi oleh kontribusi besar dari ketiga parameter P, I dan D. Pemilihan konstanta Kp, Ki dan Kd akan mengakibatkan penonjolan sifat dari masing-masing elemen. Dalam perancangan sebuah sistem kendali menggunakan kontroller PID pada motor servo yang diharapkan mampu menggerakkan sirip naik dan sirip turun pada roket sehingga mampu menjaga kestabilan roket saat diluncurkan. Prosentase error pada proyek akhir ini adalah 0,5 %.Roket merupakan sebuah peluru kendali atau suatu kendaraan terbang yang mendapatkan dorongan melalui reaksi roket secara cepat dengan bahan fluida dari keluaran mesin roket. Sistem Kendali Sirip Roket berbasis Mikrokontroller ATmega8 berguna untuk mengendalikan sirip roket khususnya bagian aileron.  Dibutuhkan komponen – komponen pendukung berupa Sensor Accelerometer, Sensor Gyroscope, ATmega8 dan Motor Servo. Alat pengendali sirip roket ini dapat digunakan untuk mengendalikan sirip roket bagian aileron pada saat posisi roket tidak stabil atau terjadi gerakan naik turun pada saat setelah diluncurkan, sehingga dapat menghasilkan penerbangan yang maksimal dalam mencapai sasaran.Perancangan yang  digunakan adalah jenis pengendalian dengan kontrol PID. PID (Proportional Integral Derivative controller) merupakan kontroller untuk menentukan presisi suatu sistem instrumentasi dengan karakteristik adanya umpan balik pada sistem tesebut. Pengontrol PID adalah pengontrol konvensional yang banyak dipakai dalam dunia industri. Karakteristik pengontrol PID sangat dipengaruhi oleh kontribusi besar dari ketiga parameter P, I dan D. Pemilihan konstanta Kp, Ki dan Kd akan mengakibatkan penonjolan sifat dari masing-masing elemen. Dalam perancangan sebuah sistem kendali menggunakan kontroller PID pada motor servo yang diharapkan mampu menggerakkan sirip naik dan sirip turun pada roket sehingga mampu menjaga kestabilan roket saat diluncurkan. Prosentase error pada proyek akhir ini adalah 0,5 %.

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