Abstract
Abstract In order to prevent these undesirable effects of the high temperatures, two methods are used for protecting the gas turbine blades: cooling of the blades with air from the compressor of turboengine and application of a ceramic thermal barrier coating. The paper analyzes the influence of air flow holes and of the thermal barrier coat on distribution of stresses in a HP stage blade of a turboengine. Blade with and without cooling air holes and thermal barrier coating is considered. The reference model is the blade from HP stage of the EJ 200 turbofun engine, which equips the military aircraft Eurofighter Typhoon. The finite element analysis was done made using the ANSYS 13 program. The ceramic material for thermal barrier coating is ZrO2/20%Y2O3.
Published Version
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