Design and Analysis of Titanium Alloy Turbine Blade Using ANSYS (original) (raw)

2024, IJRAME PUBLICATIONS

This paper presents a detailed design and analysis of a turbine blade made from titanium alloy using ANSYS, a robust finite element analysis (FEA) tool. Turbine blades operate under extreme mechanical and thermal conditions, necessitating materials with exceptional properties. Titanium alloys are favoured for their high strength-to-weight ratio, corrosion resistance, and good thermal properties. This study investigates the structural integrity, stress distribution, deformation, and thermal behaviour of titanium alloy turbine blades under operational conditions. The results provide valuable insights for optimizing turbine blade design for improved performance and durability.

IJERT-Structural Design and Analysis of Gas Turbine Blade using CAE tools

International Journal of Engineering Research and Technology (IJERT), 2014

https://www.ijert.org/structural-design-and-analysis-of-gas-turbine-blade-using-cae-tools https://www.ijert.org/research/structural-design-and-analysis-of-gas-turbine-blade-using-cae-tools-IJERTV3IS100482.pdf In today's industrial scenario, gas turbine is one of the most important parts of a power plant. In order to maximize the overall performance and efficiency of all modern turbines, it should operate at high temperatures and speeds. Due to high operating temperatures and speeds, failure of the turbine blades is inevitable. Hence there is a pressing need for analysis of turbine blades. The steady state thermal and static structural analysis of turbine blade is carried out using ANSYS 14.0 for different titanium alloys. In the analysis, it is observed that the bottom trailing edge of the blade section has higher stress value than the tip of the blade. The value of Von-Mises stress and deformation is obtained and it is seen that at 1000 0 C, Alloy 685 and at 2000 0 C, Ti 6242S exhibits least amount of stress and undergoes less deformation for a constant turbine speed of 10000 rpm with a pressure of 3.06 MPa.

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Static and Fatigue Analysis of a Steam Turbine Blade

Steam turbine is one of the most important prime movers for generating electricity. This falls under the category of power producing turbo-machines. Single unit of steam turbine can develop power ranging from 1 MW to 1000 MW. The purpose of turbine technology is to extract the maximum quantity of energy from the working fluid, to convert it into useful work with maximum efficiency, by means of a plant having maximum reliability, minimum cost, minimum supervision and minimum starting time. This present work explores the finite element analysis of a steam turbine blade using ANSYS software. Life cycle assessment of steam turbines is essential to improve their design and maintenance plans, since they should operate more than 20 years with minimum interruptions and without failures. Important element of this turbine is the blades and rotor due to their size, mass and cyclic stresses with relatively high frequencies and amplitude. To cope up with this we are using titanium alloy as a material. Different types of loads acting on steam turbine blade and consequential stresses develops in blade are studied. Fatigue stresses are developed on the steam turbine blade due to change in steam speed. The maximum steam speed range (from cut-in to cut-out steam speed) is considered for design of blade as well as predicting the fatigue life of the blade.

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Numerical and Thermal Finite Element Analysis (FEA) of Idealized Gas Turbine Engine Blade

International Journal of Mechanical and Aerospace Engineering, 2020

The turbine blades are responsible for extracting energy from the high temperature gas produced from the combustor of a gas turbine. To obtain a better efficiency and maximum work output from the gas turbine, it is operated at elevated temperature. The blades are required to withstand elevated temperature. The need for the blades to operate effectively and survive in an aggressive environment without failure required an exotic material for the design of the blades. In this paper, the blade under study is made of titanium and it was subjected to a temperature of 1200°c to 1650°c. The thermal finite thermal element analysis was done with the aid of ABAQUS software. A 3-dimensional model of the blade was developed by the software and also to predict the thermal behavior of the blade at different elevated temperature with an interval of 50°c. The simulation result shows that the temperature gradient along the blade length is 49°c/mm.

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Comparative Thermal and Structural Analysis of High-Pressure Gas Turbine Blade using Finite Element Method

INTERNATIONAL JOURNAL OF INNOVATIVE RESEARCH IN TECHNOLOGY, 2017

A turbine blade is a component which complete the turbine section of a gas turbine or steam turbine. The blades of turbine are responsible for withdrawing energy from the high pressure, high temperature gas produced in the combustor. The turbine blades are very often the limiting and critical component of gas turbines. In this paper three most widely used materials are selected such as titanium alloy, IN738 and high strength alloy. For thermal and structural analysis, a 3 D FEM model was created using Creo 2.0 and velocity diagram was prepared for the actual working diagram of the gas turbine. The important parameters are considered for this analysis such as temperature of gas, forces through velocity diagram and ambient temperature and pressure conditions. After FEM analysis using ANSYS workbench 15.0 was analyzed for stress induced due to thermal and structural loading, form the FEM analysis it is found that Titanium alloy is found most promising material for the turbine blade in gas power plants.

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Analysis and structural design of various turbine blades under variable conditions: A review

2019

This paper presents a review study for energy-efficient gas turbines (GTs) with cycles which contributes significantly towards sustainable usage. Nonetheless, these progressive engines, operative at turbine inlet temperatures as high as 1600°C, require the employment of highly creep resistant materials for use in hotter section components of gas turbines like combustion chamber and blades. However, the gas turbine obtain its driving power by utilizing the energy of treated gases and air which is at piercing temperature and pushing by expanding through the several rings of steady and vibratory blades. Since the turbine blades works at very high temperature and pressure, high stress concentration are observed on the blades. With the increasing demand of service, to provide adequate efficiency and power within the optimized level, turbine blades are to be made of those materials which can withstand high thermal and working load condition for longer cycle time. This paper depicts the re...

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IJERT-Structural Analysis of Super Alloy Gas Turbine Blade using FEA

International Journal of Engineering Research and Technology (IJERT), 2014

https://www.ijert.org/structural-analysis-of-super-alloy-gas-turbine-blade-using-fea https://www.ijert.org/research/structural-analysis-of-super-alloy-gas-turbine-blade-using-fea-IJERTV3IS11005.pdf Withstanding of gas turbine blades for the elongations is a major consideration in their design because they are subjected to high tangential, axial, centrifugal forces during their working conditions. Several methods have been suggested for the better enhancement of the mechanical properties of blades to withstand these extreme conditions. This project summarizes the design and analysis of Gas turbine blade, on which CATIA V5 R19 is used for deign of solid model of the turbine blade with the help of the spline and extrude options ANSYS 14.5 software is used analysis of F.E. model generated by meshing of the blade using the solid brick element present in the HYPERMESH 10 software and thereby applying the boundary condition.This project specifies how the program makes effective use of the ANSYS pre-processor to analyse the complex turbine blade geometries and apply boundary conditions to examine

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International Journal of Engineering Sciences & Management Research ANALYTICAL COMPARATIVE STUDY OF GAS TURBINE BLADE MATERIALS USED IN MARINE APPLICATIONS USING FEA TECHNIQUES

The turbine blades are responsible for extracting energy from the high temperature gas produced by the combustor. Operating the gas turbine blade at high temperatures would provide better efficiency and maximum work output. These turbine blades are required to withstand large centrifugal forces, elevated temperatures and are operated in aggressive environments. To survive in this difficult environment, turbine blades often made from exotic materials. A key limiting factor in gas turbine engines is the performance of the materials available for the hot section of the engine especially the gas turbine blades. In this paper, three materials such as Nimonic alloy, Super alloy and titanium aluminium have been considered for the purpose of performance analysis. The turbine blade under evaluation belongs to the first stage rotor blade of a two-stage gas turbine. The turbine blade data was obtained using CMM and its 3D solid model is created by using CATIA V5R21software. The turbine blade is analyzed for its thermal and structural performance due to the loading condition and the temperature gradients using ANSYS 14.0 software. The stresses induced in the turbine blade made up of super alloy and Nimonic 80A alloy are well within the safe limits. Finally, it could be concluded that the super alloy which is being used in manufacturing of the turbine blade of marine gas turbine engine as the best suitable material.

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Thermo-Structural Analysis of High-Pressure Turbine Blade

Journal of the Institute of Engineering

Turbine blade tip clearance plays major role in smooth running of axial turbines. The turbine blade clearance contributes 20-40% of total loss in gas turbine. In Rolls Royce MT2 Turbine with 2% tip to span clearance ratio, tip clearance accounts for 40% of total losses. Turbine blade clearance is necessary as the turbine blade operates at very high temperature up to 1700 ºC and very high centrifugal load. Small turbine tip clearance may forbid expansion of turbine blade which will result in turbine tip rubbing with the casing. High pressure turbine blade experiences high thermal and centrifugal stress. The objective of this paper is to study the individual and combined effect of these stress. The material used for analysis is cast based nickel alloy IN-738. The melting range of this alloy is 1230-1315 ºC with thermal expansion coefficient of 15.39E-6 per ºC. The turbine blade geometry with height 120 mm is used for analysis. The Mathematical modelling of above geometry shows that th...

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