Abstract:For pursuing higher performance, extremely high inlet temperature is given for prior gas turbine design. This results in a relatively high level of thermal load to the hot component beyond the thermal limit of the nickel-base super-alloy. The ceramic matrix composite (CMC) with low density and high thermal resistance, is always regarded as the potential thermal structure material for the state of art gas turbine and aero-engine. Nowadays, many studies concerning the endwall adiabatic film cooling have been per… Show more
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