Hesaplamalı akışkan dinamikleri kullanılarak türbin kanatının sürünmesinin modellenmesi ve analizi

The global population is on a steady rise, while our resources are dwindling at an alarming rate. In order to cater to the world's energy demands, it is imperative that we transition to a device that boasts optimal efficiency. The turbine is a well-suited option in this regard, with gas turbines serving as a prime example of such machinery. Creep is a phenomenon characterized by the gradual and time-dependent inelastic deformation that occurs under mechanical loading and elevated temperatures. The phenomenon of creep is often accompanied by various microstructural rearrangements, such as dislocation motion, microstructure aging, and cavitation at grain boundaries. In recent decades, numerous numerical and experimental studies have been conducted to enhance the understanding of creep behavior in structures subjected to elevated temperatures. The three primary subjects under consideration are the creep constitutive relationship, the creep damage evolution equation, and the method for predicting creep life. Previous research has focused on enhancing the efficacy and quality of gas turbines through various methods, including film cooling, coating, and blade curvature. These techniques aim to safeguard the turbine blades from the extreme temperatures of up to 1400°C within the turbine, thereby prolonging their lifespan. However, the impact of these methods on the engine's efficiency has not been a primary consideration in prior research. The objective of this study is to improve the efficiency of gas turbines. The efficacy of the turbine blade can be evaluated based on the temperature applied to the turbine after coating. The present study involves a simulation that utilizes defined values of temperature and pressure to conduct a computational fluid dynamics (CFD) analysis on blade construction. The meshing of the blade will be performed using ANSYS software, and finite element method (FEM) calculations will be conducted. The results obtained from these calculations, pertaining to the temperature and CFD analysis within the gas turbine of varying numbers of blades, will be compared to determine the optimal efficiency point.