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CHAPTER 1 INTRODUCTION Chapter 1 Introduction For turbine components located in the hot section of engines, their fabrication procedure is highly demanding because they have to endure the flow of hot gas which often leads to problems such as corrosion and oxidation. Furthermore, turbine components also have to endure the impact of high velocity objects such as sand particles. Due to the continuous improvement of engineering skills, the engine could be improved in different ways such as the turbine design, increasing the combustion temperature, and the use of materials. Since reducing the emission of carbon dioxide has been one of the important considerations of advanced engine design, and along with the increasing price of fossil fuel, demand for the increase of fuel efficiency became one of the most important issues for the future work of engine design. According to these motives, increasing the operation temperature was an obvious trend over the past 50 years [1]. For the state-of-the-art engine, the operating temperature in the combustion chamber is more than 1500 °C [2], which is much higher than the melting point of nickel-based superalloy (1320 - 1450 °C [3]) [4], the material which is used in the substrate material in engine turbine. Besides, compared with older generations of Page 14PDF Image | Volcanic Ash Degradation on Thermal Barrier Coatings
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