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Durability Challenges for Next Generation of Gas Turbine Engine MaterialsAggressive fuel burn and carbon dioxide emission reduction goals for future gas turbine engines will require higher overall pressure ratio, and a significant increase in turbine inlet temperature. These goals can be achieved by increasing temperature capability of turbine engine hot section materials and decreasing weight of fan section of the engine. NASA is currently developing several advanced hot section materials for increasing temperature capability of future gas turbine engines. The materials of interest include ceramic matrix composites with 1482 - 1648 C temperature capability, advanced disk alloys with 815 C capability, and low conductivity thermal barrier coatings with erosion resistance. The presentation will provide an overview of durability challenges with emphasis on the environmental factors affecting durability for the next generation of gas turbine engine materials. The environmental factors include gaseous atmosphere in gas turbine engines, molten salt and glass deposits from airborne contaminants, impact from foreign object damage, and erosion from ingestion of small particles.
Document ID
Acquisition Source
Glenn Research Center
Document Type
Conference Paper
Misra, Ajay K.
(NASA Glenn Research Center Cleveland, OH, United States)
Date Acquired
August 27, 2013
Publication Date
October 15, 2012
Subject Category
Composite Materials
Meeting Information
Meeting: AVT Symposium on Design, Modelling, Lifting and Validation of Advanced Materials in Extreme Military Environments
Location: Biarritz
Country: France
Start Date: October 15, 2012
End Date: October 18, 2012
Funding Number(s)
WBS: WBS 561581.
Distribution Limits
Work of the US Gov. Public Use Permitted.
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