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Abstract

TBCs are widely used in gas turbines for propulsion and more recently for power generation, for sustaining a desired temperature difference between the load bearing alloy and 1he coating surface. The benefits of these coatings are life extension of the components, reduced cooling air or higher gas temperature, thus contributing to meeting the demands for more efficient, cleaner and with lower life cycle costs gas turbines. Successful use of TBCs and expanded application to more demanding options have required comprehensive understanding of their thermo-mechanical behaviour and testing under realistic, near-service conditions to assess their durability.

This paper describes methodologies developed for evaluating the TBC life under TMF loading. Tests are carried out in a specially designed TMF rig, allowing for a positive temperature gradient across the TBC system and thus simulating the thermomechanical loading cnvironmcl11 at critical locations in gas turbine blades. To identify the failure mechanisms and describe the evolution of microstructure, specimens, after TMI: testing, are examined microstructurally. The observed damage mechanisms are discussed based on the imposed TMI cycles. .

Additional information

Authors: BAUFELD B, JRC, Institute for Advanced Materials, EPC Petten (NL);MLLEJANS H, JRC, Institute for Advanced Materials, EPC Petten (NL);BRESSERS J, JRC, Institute for Advanced Materials, EPC Petten (NL);HHNER P, JRC, Institute for Advanced Materials, EPC Petten (NL);TZIMAS E, JRC, Institute for Advanced Materials, EPC Petten (NL);PETEVES S.D, JRC, Institute for Advanced Materials, EPC Petten (NL)
Bibliographic Reference: An oral report given at: ASME TURBO EXPO 2001. Organised by: American Society of Mechanical Engineers. Held in: New Orleans, 4-6 June 2001
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