Turbine inlet temperatures within future gas turbine engines will be significantly higher temperatures(~ 1800 °C)than current engines(~ 1400 °C)for improved efficiency and power density.As a result,the current set of metallic components(titanium-based and nickel-based superalloys)will be replaced with ceramics and ceramic matrix composites(CMCs).These materials can survive the higher operating temperatures of future engines at a significant weight savings over the current metallic components,i.e.advanced ceramic components will facilitate engines with higher operational energy.While oxide-based CMCs may not be suitable candidates for hot-section components,they may be suitable for structural and/or exhaust components.However,a more thorough understanding of performance under relevant environment of these materials is needed.To this end,this work investigates the high temperature durability of a family oxide-oxide CMCs under an engine relevant environment.Flat oxide-oxide CMC panels were cyclically exposed to temperatures up to 1150 °C(2100 °F),wimin 240 m/s(~0.3 M)gas flows.Front and backside surface temperatures were monitored by a single-wavelength pyrometer and mermocouple,respectively.In addition,an infrared camera was used to evaluate me damage evolution of the samples during testing.Flash thermography was used to elucidate defects present before and after thermal exposure.
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