International Research Journal of Engineering and Technology (IRJET)
e-ISSN: 2395 -0056
Volume: 04 Issue: 05 | May -2017
p-ISSN: 2395-0072
www.irjet.net
Structural Analysis of Gas Turbine Blade P.R.Surve1, R.V.Shitole1, D.R.Shirdhankar1, S.N.Shigwan1, V. S.Bagade2 Finolex Academy of Management and Technology, Ratnagiri, Maharashtra, India Professor, Finolex Academy of Management and Technology, Ratnagiri, Maharashtra, India ---------------------------------------------------------------------***--------------------------------------------------------------------2. LITERATURE REVIEW Abstract –Blades of gas turbine are responsible for 1
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extracting energy from the high temperature and high pressure gases.Gas turbine blade operated at high temperature provides better efficiency and maximum work output. The present paper deals with structural analysis of gas turbine blade. The analysis was carried out to know the mechanical stresses and deformation experienced by the gas turbine rotor blade. Solid model of turbine blade is created by using SOLIDWORKS20 software. The turbine blade is analyzed for its’ structural performance due to the loading condition using ANSYS 16.2 software to study the variation of stresses on gas turbine blade for aluminium alloy, titanium alloy and magnesium alloy material. Among this three materials Titanium alloy has maximum equivalent stress 7.53×105 N/m2 and minimum deformation of 2.33×10-5 m. Key Words: Gas turbine blade, Mechanical stresses, Deformations, Materials, Structural Analysis.
1. INTRODUCTION The gas turbine obtains its power by utilizing the energy from burnt gases which is at the high temperature and pressure. Power was obtained by expanding them through the several rings of fixed and moving blades. The turbine is responsible for driving the compressor so it is coupled to the turbine shaft. After compression, the working fluid was expanded in a turbine. Then it was assumed that there were no losses in both component and the power developed by the turbine can be increased by increasing the volume of working fluid at constant pressure or alternatively increasing the pressure at constant volume. Else it may be done by adding heat so that the temperature of the working fluid is increased after compression. For getting higher combustion, chamber is required where combustion of air and fuel takes place and giving temperature rise to the working fluid. The turbine escapes energy from the exhaust gas. Work deals with structural analysis of gas turbine blade. The analysis was carried out to understand the mechanical stresses and deformation. This was experienced by the gas turbine rotor blade and includes the parameters such as the gas forces which are assumed to be distributed evenly. The tangential and axial force acts through the centroid of the blade and the centrifugal force acts through the centroid of the blade in radial direction.
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V. NagaBhushana et.al[1] worked on the turbine blade under evaluation belongs to the first stage rotor blade of a two stage gas turbine. The turbine blade data was obtained by using CMM. 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. Maximum stresses are observed near the root of the turbine blade and maximum temperatures are observed at the blade tip sections. Also minimum temperature is observed at the root of blade. P. V. Krishnakanth et.al.[2] specified how the program makes effective use of the ANSYS pre-processor to analyze the complex turbine blade geometries and then apply boundary conditions to know steady state thermal & structural performance of the turbine blade for N 155, Hastealloy x & Inconel 625 material. Inconel 625 has better thermal properties. V. Nagabhushan Rao, et.al.[3] generated profile by using CATIA V5R21software. The turbine blade is analysed 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 which indicates the elongation of the blade is within the safe limit. The stresses induced in the turbine blade which is to be made up of super alloy and Nimonic 80A alloy are within the safe limits. Theju V. et.al [4] made an attempt to investigate the effect of temperature and induced stresses on the turbine blade. A thermal analysis has been carried out to investigate the direction of the temperature flow which has been developed due to the thermal loading. A structural analysis has been carried out to know the stresses and displacements of the turbine blade. An attempt is also made to suggest the best material for a turbine blade by comparing the results obtained for two materials i.e. Inconel 718 and titanium T6. Inconel 718 is considered as a best material after analysis. S. Alka et.al[5] designed blade in such a way that it produce maximum rotational energy by directing the flow of the gas along its surface. The blades are made at specific angles to incorporate the net flow of gas over it. Catia is the standard 3D product design, featuring industry-leading productivity tool that promote best practices in design. Over a static structural analysis silicon carbide is better material for gas turbine blade. Mehdi Tofighi Naeem et.al[6]carried out microstructural analysis of all elements that had great influence on the failure initiation. The failure analysis of a gas turbine with first and second stage blades made up of nickel-based alloy was checked. Accumulated service time of these blades is more than 10 years. This investigation was carried out by mechanical as well as metallurgical analysis. ISO 9001:2008 Certified Journal
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