ABSTRACT The main objectives of this study were to aerodynamically design and optimize a winglet for wind turbine blade by using computational fluid dynamics (CFD) investigate its effect on the power production. For validation as baseline rotor, National Renewable Energy Laboratory Phase VI rotor is used. Reynolds‐averaged Navier–Stokes equations are solved, k–ε Launder–Sharma turbulence model was numerical results have shown considerable agreement with experimental data. genetic algorithm...

AbstractThe main purpose of this paper is to study the aerodynamic effects blade tip tilting on power production horizontal-axis wind turbines by using Computational Fluid Dynamics (CFD). For validation and as a baseline rotor, NREL Phase VI turbine rotor used. The Reynolds-Averaged Navier–Stokes Equations are solved different turbulence models including Spalart–Allmaras, Standard k-ϵ, k-ϵ Yang–Shih SST k–ω used tested. results shown in terms generation at speeds pressure distribution...

In this paper, a new multiploid genetic optimization method handling surrogate models of the CFD solutions is presented and applied for multi-objective turbine blade aerodynamic problem. A fast, efficient, robust, automated design developed to aerodynamically optimize 3D gas blades. The objectives are selected as maximizing adiabatic efficiency torque so reduce weight, size, cost engine. steady Reynolds averaged Navier–Stokes solver coupled with an unstructured grid generation tool. verified...

This study investigates the effect of periodic excitation from individually controlled synthetic jet actuators on dynamics flow within separation and re-attachment regions boundary layer over suction surface a 2D model wing that has S809 airfoil profile. Experiments are performed in METUWIND's C3 open-loop type wind tunnel 1 m × cross-section test section. The array consists three driven by piezoelectric diaphragms located at 28% chord location near mid-span wing. In first part study,...

Anewmethodology isdevelopedto e ndtheoptimalaerodynamicperformanceofaturbinecascade.Aboundarylayer coupled Euler algorithm and a genetic are linked within an automated optimization loop. The multiparameter objective function is based on the blade loading. For given inlet Mach number baseline cascade geometry, ow exit angles, thickness solidity optimized by robust algorithm. First, Sanz subcritical turbine selected asthe cascadeand used for solver validation. Second, parameters modie ed to...

A parallel adaptive Euler flow solution algorithm is developed for 3D applications on distributed memory computers. Significant contribution of this research the development and implementation a grid adaptation scheme together with an explicit cell vertex-based finite volume solver unstructured tetrahedral grids. Parallel grids based grid-regeneration philosophy by using existing serial generation program. Then, general partitioner repartitions grid. An sensor value, which measure to refine...

In this paper, a new multiploid genetic optimization method handling surrogate models of the CFD solutions is presented and applied for single objective turbine blade aerodynamic problem. A fast, efficient, robust, automated design developed to aerodynamically optimize 3D gas blades. The objectives are selected as maximizing adiabatic efficiency torque so reduce weight, size cost engine. 3-Dimensional steady Reynolds Averaged Navier Stokes solver coupled with an unstructured grid generation...

In this paper, a new multiploid genetic optimization method handling surrogate models of the CFD solutions is presented and applied for multi objective turbine blade aerodynamic problem. A fast, efficient, robust, automated design developed to aerodynamically optimize 3D gas blades. The objectives are selected as maximizing adiabatic efficiency torque so reduce weight, size cost engine. 3-Dimensional steady Reynolds Averaged Navier Stokes solver coupled with an unstructured grid generation...

The vapor-liquid, two-phase, inviscid, compressible e ow in a converging-diverging nozzle is computed by high accuracy total-variation-diminishing and Newton‐ Raphson schemes. A homogeneous speed of sound dee nition based on quality void fraction presented, along with some gas dynamic relations. Analytical twophase mass-e expressions are also derived, solutions compared those obtained from the numerical schemes.Thecomputational resultsofvoid-fraction Mach-numberrelation...

This paper describes a fast, efficient, robust, and automated design method used to aerodynamically optimize 3D gas turbine blade shapes implementing artificial intelligence. The objectives are maximizing the aerodynamic efficiency torque so as reduce weight size cost of engine. procedure described here will allow rapid, practical low that answer need industry. A 3-Dimensional steady Reynolds Averaged Navier Stokes solver is coupled with an unstructured grid generation tool. verified using...

A numerical algorithm has been developed for two dimensional rotating and non-rotating airfoil cross-sections. The steady Euler equations in the rotational plane with viscous boundary layer correction have used analysis. effects of layers wakes on inviscid main stream flow are modeled by displacement thickness concept. Both laminar turbulent growth over can be modeled. transition point is input to solution. non-linear Euler-boundary system equation integral conservative form allows correct...

There are different characters of air flow in a conventional gas turbine blade cooling channel. These characters; including high streamline curvature caused from 180 degree bends, sequential separations rib turbulators and pin-fin structures analyzed separately with available commercial software for turbulence models validated against reliable experimental data open literature. Also coupled conjugate heat transfer analyses on NASA C3X vane, which has only radial holes through span cooling,...

This paper proposes a novel and efficient utilization of gas turbine exhaust waste heat recovery (WHR) with the aim generating electrical energy. The WHR is based on an air Brayton cycle its ratio (electrical generation power from input thermal power) analyzed. Proposed auxiliary unit will reduce load most existing propulsion plants increase efficiency range modern hybrid aircrafts. In analysis, secondary mass flow rate, compressor's pressure inlet relative drop across exchangers are numerically

This study investigates how synthetic jet actuators prevent laminar boundary layer separation caused by adverse pressure gradient. Active control experiments were performed over the suction surface of a wing model that has S809 airfoil profile using actuators. The array on consists three individually controlled driven piezoelectric diaphragms and it was located at 28% chord location near mid-span wing. After conducting measurements several low Reynolds numbers, namely, 2.3x10 5 , 3.4x10...

A new methodology is developed to find the optimal steam injection levels in simple and combined cycle gas turbine power plants. When process being applied turbines, it shown offer many benefits, including increased output efficiency as well reduced exhaust emissions. For plants, turbine, significantly decreases amount of flow energy through overall decreased. This study focuses on finding maximum injected turbines. that purpose, thermodynamic analysis a genetic algorithm are linked within...

Numerical solutions of a 2D stator compressor cascade at one inlet Mach number (0.7) and four values incidence (49°, 51°, 53° 55°) are obtained. Reynolds averaged, thin layer, compressible Navier Stokes equations solved by using multi block, parallel algorithm. Finite differencing approach LU - ADI splitting technique used. BaldwinLomax turbulence model is applied. Computational pressure distribution boundary layer results obtained with uniform velocity profiles compared well the available...

DaN itki sınıfında klasik bir turbojet motor performansı ile tamamen yerli konsept olan Pars türbojet motorun ve yakıt