# Introduction turbine blade is the part which makes up the turbine segment of a gas turbine. The blades are responsible for extracting energy from the high temperature, high pressure gas produced by the combustor. The turbine blades are usually the restricting component of gas turbines. To survive in this difficult environment, turbine blades often use exotic materials like super alloys and many different methods of cooling, such as internal air channels, boundary layer cooling, and barrier coatings Blade fatigue is a major source of failure in steam turbines and gas turbines. Fatigue is caused by the stress induced by vibration and resonance within the operating range of machinery. To protect blades from these high dynamic stresses, friction dampers are used. Blades of wind turbines and water turbines are designed to operate in different conditions, which typically involve lower rotational speeds and temperatures. Gas turbine engine, a single turbine segment is comprised of a plate or center point that holds numerous turbine sharp blades. Turbine section is connected to a compressor section via a shaft (or "spool"), and that compressor section can either biaxial or centrifugal .The temperature is then greatly increased by combustion of fuel inside the combustor, which sits between the compressor stages and the Author ? ?: Mechanical Department, G.Naryanamma Institute of Technology & Science, Hyderabad, India. e-mails: yashwanth.megnit@gmail.com, mvrrin@gmail.com Author ?: Mechatronics Department, IcfaiTech Faculty of Science & Technology, Hyderabad India. e-mail: himam.mech@gmail.com turbine stages. The high-temperature and high-pressure exhaust gases then pass through the turbine stages. The stages separate energy from this stream, bringing down the pressure and temperature of the air. This process is very similar to how an axial compressor works, only in reverse. The number of turbine stages varies in different types of engines, with high-bypassratio engines tending to have the most turbine stages. The number of turbine stages can have a great effect on how the turbine blades are designed for each stage. Many gas turbine engines are twin-spool designs. Other gas turbines use three spools, adding an intermediate pressure spool between the high-and low-pressure spool. The high-pressure turbine is exposed to the hottest, highest-pressure air, and the low-pressure turbine is subjected to cooler, lower-pressure air. The difference in conditions leads to the design of highpressure and low-pressure turbine blades that are significantly different in material and cooling choices even though the aerodynamic and thermodynamic principles are the same. Under these severe operating conditions inside the gas and steam turbines, the blades face high temperature, high stresses, and potentially high vibrations. Steam turbine blades are critical components in power plants which convert the linear motion of high-temperature and high-pressure steam flowing down a pressure gradient into a rotary motion of the turbine shaft. The present paper deals with the thermal stresses that arise due to temperature gradient within the blade material. The analysis is carried out under steady state conditions using Ansys software. The study has been conducted with three different materials stainless steel, Titanium alloy, Aluminium alloy. # II. # Literature Review In today's economic climate, cost pressure is a pervasive problem. One way to reduce costs is to carry out repair of single components within assemblies. In some applications, the regeneration can save up to 70 % of the costs compared to the replacement with remanufactured components. Due to the high potential in cost saving, most companies try to keep their knowledge in repair processes for themselves. Much effort is put into the improvement of processes in the maintenance, repair, and overhaul (MRO) of engines. An engine consists of approximately 30,000 components. Their repair takes a significant volume of the engine business with an increasing trend. Furthermore, Rupp indicates that the material costs add up to 50 % in the maintenance costs of engines. The repair or A regeneration of components such as castings, seal fins/labyrinth, and notches is mostly carried out manually. Engine components of particular interest regarding the regeneration process are compressor, and turbine blades and vanes due to their high value. Most available references regarding the regeneration of those components concern the material deposit. Information on the recon touring is even harder to find .Nevertheless; this final shape cutting of a work piece is a crucial step regarding the later workpiece quality. Engine blades are an example for workpieces that have high requirements in accuracy and quality combined with a complex shape and difficult material conditions. The usual procedure for recon touring is characterized by a lot of manual working steps. This includes, e. g., manual grinding in the area of interfering contour. Achieving the final contour and a suitable surface topography is the most important aim. In order to limit the variety of occurring damages, Carter classifies these into basic groups. Any damage can be reduced to at least one of the three main causes: thermal influence, mechanical influence, or chemical influence. This paper in the following gives a literature review about regeneration processes related to the aviation industry. Moreover, it collects and generalizes detailed information on the machining point of view. The scientific basics extracted from the references can be transferred to other mechanical engineering sectors. # III. Modelling of Slap and Slider for Friction Surface For Designing and analyzing an engineer must be familiar with the cause, which the manufacturing and thermal analysis done on the materials. Slap and slider are designed individually and assembled in order to obtain the final shape of the turbine blade. The slap and slider of the blade are designed as per the design standards using CATIA software as shown below: # Result and Discussion After the conduction of the thermal analysis on turbine blade is done using Ansys software. The results that are obtained with the rise in Temperature and Heat Flux by Temperature rise from 100 to 1000°C for different alloys is mentioned in the following table below: From the above graphs, it is found that temperature has significant effect of the thermal stresses induced in the Turbine Blade of different alloys. Moreover the temperature is high for Aluminium alloy and the heat flux is also high. ![He describes and lists common failure mechanisms occurring at engine blades. Damage types are Micro structural changes: due to high variations in temperature Oxidation: due to chemical reactions of the workpiece material with the ambient air Cracks: through high tensile stresses caused by thermal fatigue Abrasion: through sand or small particles Deformation: due to the impact of foreign objects or creep Entire breakages: through foreign objects or thermo mechanical cracks or creep.](image-2.png "") 1![Fig. 1: Pad Tool for Base Locker](image-3.png "Fig. 1 :") 3![Fig. 3: Temperature and Radiation the Steady-State Thermal After the thermal boundary conditions are applied, it is now important to analyze the behavior of the model with respect to the boundary conditions applied. The analysis that is carried out for different materials is shown in following figures For Stainless Steel](image-4.png "Fig. 3 :") 1![Temperatures and Heat Flux by Temperature Rise from 100 To1000°C The graphical representation for rise in Temperature and Heat Flux from 100°C to 1000°C for different alloys are shown below Graph 1: Heat Flux W/Mm2 Graph 2: Temperature C](image-5.png "Table 1 :") ![](image-6.png "") ![](image-7.png "") © 2020 Global Journals * Flight Operations Briefing Notes -Supplementary Techniques: Handling Engine Malfunctions PDF).Airbus * Propulseur par réaction sur l'air MaximeGuillaume May 1921. January 1922 534 13 * Chasing the Sun -Frank Whittle PBS Retrieved2010-03-26 * History -Frank Whittle BBC. Retrieved 1907 -1996. 2010-03-26 * Improvements relating to the propulsion of aircraft and other vehicles FrankWhittle January 1930 16 * The History of the Jet Engine -Sir Frank Whittle -Hans Von Ohain said thahe had not read Whittle's patent and Whittle believed him * THE FIRST JET PILOT -The Story of German Test Pilot ErichWarsitz LutzWarsitz 2009 Pen and Sword Books Ltd 125 England * Ch10-3". Hq.nasa.gov. Retrieved 2010-03-26 * Elements of Propulsion: Gas Turbines and Rockets JackDMattingly AIAA Education Series 2006 American Institute of Aeronautics and Astronautics * Trent XWB info graphic Retrieved2015-10-15 * Hill & Peterson 1992. 2006 Mattingly * Fundamentals of Jet Propulsion with Applications. Cambridge Aerospace Series *Flack RonaldD 2005 Cambridge University Press 16 New York, NY