THE DEFORMATION ABILITY AND THERMAL-CYCLE DURABILITY OF AIRCRAFT HIGH-TEMPERATURE ALLOYS

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THE DEFORMATION ABILITY AND THERMAL-CYCLE DURABILITY OF AIRCRAFT HIGH-TEMPERATURE ALLOYS

Journal Title: Проблеми тертя та зношування - Year 2016, Vol 71, Issue

Abstract

The article deals with consideration of the durability of high-temperature alloys for gas turbine engine components. Durability of high-temperature alloys is determined in critical points tak-ing into account mechanics and kinetics of accumulation of inelastic deformations and damage until the sample fracture under the action of thermo-mechanical stresses in thermo-cyclic loading. The operation conditions of heat resistant material test specimens are considered at extreme operation modes of turbine elements at their critical points, limiting the lifetime and specified life of gas turbine engines. Both the determination of extreme levels of working stresses and temperatures at the critical points and the determination of optimal levels of stresses and temperatures ensuring the maxi-mum thermo-cyclic durability of high-temperature alloys are described in the article.

Authors and Affiliations

B. A. PETRUK

Keywords

thermo-cyclic durability boundary thermo-mechanical stresses boundary gradient of temperature the temperature difference cyclic fatigue deformation and nominal load capac-ity Bauschinger effect accumulation of inelastic deformations damage in critical points of components internal friction and wearing of high-temperature alloys

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EP ID EP191707
DOI -
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