Protective Coating for Restoring the Operability of Gas Turbine Engine Blades with Allowance for Their Service-Induced Damage
摘要
Abstract
The causes of destruction of a thermal barrier coating on gas turbine engine turbine blades are studied, and the mechanism of its destruction has been revealed. A method for inhibiting the mechanism of oxide film growth at the ceramic layer–metal sublayer interface decomposition is presented. An improved metallic sublayer is proposed for the restoration of gas turbine engine turbine blades with allowance for their operational damage. The results of comparative studies of the heat resistances and thermophysical properties of various coatings are presented.