IJERT-Steady State Structural Analysis of High pressure Gas Turbine Blade (original) (raw)
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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.
IJERT-Comparative Stress Analysis of Gas Turbine Blades
International Journal of Engineering Research and Technology (IJERT), 2021
https://www.ijert.org/comparative-stress-analysis-of-gas-turbine-blades https://www.ijert.org/research/comparative-stress-analysis-of-gas-turbine-blades-IJERTCONV9IS11061.pdf In turbomachinery, the turbine blades play an important role. While operating these blades rotate at high speed and as a result, are subjected to high centrifugal force. The gas turbine transforms the natural gas into mechanical energy, and then the mechanical energy generated by the turbine exit shaft is then transferred through a gearbox to the generator shaft. Due to high rotation speed, the centrifugal stresses act on the blade. Then, due to the presence of different blade material, along with the temperature dependency, thermal stress and deformation are developed. So, this paper is a review of various factors affecting the turbine blade.
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...
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.
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...
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
Gas Turbines Blades — a Critical Review of Failure on First and Second Stages
2014
Gas turbine blades have numerous applications in the aerospace industry. In this study, the stresses and deformations of a turbine were studied. The goal was to highlight the stress and deformation distribution to assist in the design of a blades. The stresses and deformations developed as a result of the blade operating conditions at high rotational speeds and thermal gradients were evaluated using two types of heat transfer modes-conduction and convection, taking into consideration the material behavior at elevated temperatures. The greatest stresses in the blades result from the thermal load caused by conduction, and they are located between the blades and disc. In addition an analytical method was used to evaluated and predict the stresses along the blades it gave a good estimate of the stress values compared to the finite element. It is important to design for as high temperatures gas as possible in order to attain a high thermal efficiency in gas turbines. In the case of power...
Mechanical Analysis of 1 st Stage Marine Gas Turbine Blade
Turbine blades of a gas turbine are responsible for extracting energy from the high temperature, high pressure gases. These blades are operated at elevated temperatures in aggressive environments and are subjected to large centrifugal forces. As many as 42 percent of the failures in gas turbine engines were only due to blading problems and the failures in these turbine blades can have dramatic effect on the safety and performance of the gas turbine engine. In this research paper, an attempt has been made to analyze the failure of gas turbine blade through Mechanical analysis. The blade under investigation belongs to a 30 MW gas turbine engines used in marine applications and is made of Nickel-Base superalloys. Before failure, the turbine blade was operated for about 10000 hours while its service life was expected to be around 15000 hours. Mechanical analysis has been carried out assuming that there might be failure in the blade material due to blade operation at elevated temperature and subjected to large centrifugal forces. The gas turbine blade model profile is generated by using CATIA V5R21software. The turbine blade is analyzed for its thermal as well as structural performance. It was observed that there was no evidence of rubbing marks on the tip section of turbine blade indicating the elongation of the blade is within the safe limit. Maximum stresses and strains are observed near to the root of the turbine blade and upper surface along the blade roots. Maximum temperatures are observed at the blade tip sections and minimum temperature at the root of the blade. Temperature distribution is decreasing from the tip to the root of the blade section. The temperatures observed are below the melting temperature of blade material.