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2016•DergiPark (Istanbul University)Open access

Modeling of Residual Stresses in TBC Coated Gas Turbine Blades

Yaşar Kahraman, Sedat İriç, İmdat Taymaz

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Abstract

Ceramic thermal barrier coatings have been developed for advanced gas turbine and diesel engine applications to improve engine reliability and fuel efficiency. Blades and vanes of the high-pressure turbine stages of aero-engines are the most highly stressed parts in engineering components. The blade geometry was objected to airflow at the temperatures about 800°C. These high gas turbine temperatures can only be maintained through advanced cooling techniques like electro-beam physical vapor deposition (EB-PVD) and thermal barrier coatings (TBCs). Such TBCs consist of thin ceramic layers of low thermal conductivity, yttrium stabilized zirconia (YSZ) which are applied on the blade surface. The coating imparts good adhesion of the ceramic to the substrate

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What this paper is about

Ceramic thermal barrier coatings have been developed for advanced gas turbine and diesel engine applications to improve engine reliability and fuel efficiency. Blades and vanes of the high-pressure turbine stages of aero-engines are the most highly stressed parts in engineering components. The blade geometry was objected to airflow at the temperatures about 800°C. These high gas turbine temperatures can only be maintained through advanced cooling techniques like electro-beam physical vapor deposition (EB-PVD) and thermal barrier coatings (TBCs). Such TBCs consist of thin ceramic layers of low thermal conductivity, yttrium stabilized zirconia (YSZ) which are applied on the blade surface. The coating imparts good adhesion of the ceramic to the substrate

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Available abstract

Ceramic thermal barrier coatings have been developed for advanced gas turbine and diesel engine applications to improve engine reliability and fuel efficiency. Blades and vanes of the high-pressure turbine stages of aero-engines are the most highly stressed parts in engineering components. The blade geometry was objected to airflow at the temperatures about 800°C. These high gas turbine temperatures can only be maintained through advanced cooling techniques like electro-beam physical vapor deposition (EB-PVD) and thermal barrier coatings (TBCs). Such TBCs consist of thin ceramic layers of low thermal conductivity, yttrium stabilized zirconia (YSZ) which are applied on the blade surface. The coating imparts good adhesion of the ceramic to the substrate

Key concepts: Residual stress, Gas turbines, Materials science, Residual, Turbine blade, Nuclear engineering, Metallurgy, Composite material

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