Overview of CMC (Ceramic Matrix Composite) Research at the NASA Glenn Research CenterIn support of NASAs Aeronautics Research Mission, the Glenn Research Center has developed and assessed various constituents for a high temperature (2700F) SiCSiC CMC system for turbine engine applications. Combinations of highly creep-resistant SiC fibers, advanced 3D weaves, durable environmental barrier coatings (EBCs), and a 2700F-capable hybrid SiC matrix are being developed evaluated. The resulting improvements in CMC mechanical properties and durability will be summarized. The development and validation of models for predicting the effects of the environment on the durability of CMCs and EBCs and other operating-environment challenges including the effect of CMAS (calcium magnesium aluminosilicate) degradation of EBCs will be discussed. Progress toward the development of CMC joining technology for 2400F joint applications will also be reviewed.
Document ID
20160014907
Acquisition Source
Glenn Research Center
Document Type
Presentation
Authors
Kiser, J. Douglas (NASA Glenn Research Center Cleveland, OH United States)
Grady, Joseph E. (NASA Glenn Research Center Cleveland, OH United States)
Bhatt, Ramakrishna T. (Ohio Aerospace Inst. Cleveland, OH, United States)
Wiesner, Valerie L. (NASA Glenn Research Center Cleveland, OH United States)
Zhu, Dongming (NASA Glenn Research Center Cleveland, OH United States)