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Abstract:
Gas turbine engine operating temperatures have been increasing over the years, thus improving their efficiency and power density. As this trend continues, the currently used metallic components (titanium-based and nickel-based superalloys) will no longer be usable due to their limited temperature capabilities. This provides an opportunity for 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 more powerful engines. 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 of oxide-oxide CMCs under an engine relevant environment. Flat oxide-oxide CMC panels were cyclically exposed to temperatures up to 1150 °C, within 240 m/s (~0.3 M) gas flows and hot sand impingement. Front and backside surface temperatures were monitored by a single-wavelength pyrometer and thermocouple. Nondestructive evaluation was used to evaluate all specimens before and after thermal exposure.
Gas turbine engine operating temperatures have been increasing over the years, thus improving their efficiency and power density. As this trend continues, the currently used metallic components (titanium-based and nickel-based superalloys) will no longer be usable due to their limited temperature capabilities. This provides an opportunity for 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 more powerful engines. 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 of oxide-oxide CMCs under an engine relevant environment. Flat oxide-oxide CMC panels were cyclically exposed to temperatures up to 1150 °C, within 240 m/s (~0.3 M) gas flows and hot sand impingement. Front and backside surface temperatures were monitored by a single-wavelength pyrometer and thermocouple. Nondestructive evaluation was used to evaluate all specimens before and after thermal exposure.
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Biography:
Merna Salama is currently a Materials & Process Engineer at Boeing, working in the Research & Technology division of the Extreme Environment Materials Group. She mainly works with Ceramic Matrix Composites (CMCs). She received her B.S. in Chemical Engineering and M.S. in Materials Science & Engineering from the University of California, Irvine. In her free time, she likes to bake sourdough bread and go on adventures. |
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