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CHAPTER 2 LITERATURE REVIEW Chapter 2 Literature review 2.1 ThermalBarrierCoatings For the state-of-the-art jet engine, in order to achieve better thrust output and fuel efficiency, the operation temperature must be increased beyond the melting temperature of nickel-based superalloy and come with severe oxidation and creep in the hot section of turbine blade [1]. Thus, a protective overlay coating is necessary in order to extend the service lifetime of turbine blades. Especially for increasing the operation temperature of engine turbine, thermal barrier coating technology plays a very important role in aircraft engineering. Thermal barrier coating system is a coating system which is mainly for reducing the heat transfer from the hot engine gas to the substrate of turbine blades and also provides the function for mitigating creep and oxidation in engine system. Thus, TBC system not only has to endure the extremely hot operation environment, but also withstands the stress and thousands thermal cycles. For the state-of-the-art TBCs, the structure is composed by three layers which is shown in Figure 2.1; two ceramic layers on the upper layers and one metal layer located in the bottom, which are top coat, thermal grown oxide (TGO), Page 18PDF Image | Volcanic Ash Degradation on Thermal Barrier Coatings
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