Topic 16 – CMC Application in aeronautic engines
Silicon carbide fibers reinforced silicon carbide based-matrix composites (SiC/SiC CMCs) and oxide fibers reinforced oxide based-matrix composites (Oxide/Oxide CMCs) are probably becoming a major leading alternative for the design and manufacturing of the next gas turbine engines hot parts as airfoils, shroud, combustion chambers and exhaust nozzle. These materials offer higher temperature capability than the current state-of-the-art metallic superalloys and tougher than the corresponding monolithic ceramics. The growing interest in CMC technologies development is directly linked to the new short-term engine design constraints in the context of booming air travel, namely : a drastic decrease of admitted noise and air polluting emissions and a specific fuel consumption decrease.
Building on past materials development efforts in the fields of space launchers and of military aircraft engines, major CMC actors continue to enhance CMC technologies for commercial aircraft engines. Considering this new target, one of the key issues related to this emerging technology is to develop and industrialize materials offering high thermomechanical design allowances and stable lifetime properties, in representative environment. To reach these goals, an important work has been done, in the implementation of thermomechanical behavior and modeling of CMC sub-element and engine CMC part tests.
Keywords:
SiC/SiC CMC, Oxide/Oxide CMC, Thermomechanical behavior, Design allowance, Burner rig testing, Ground engine testing, Flight engine testing
Sub-topics:
- Recent CMC Technological Improvements for aero gas Turbine Applications
- CMC Thermomechanical Behavior and Modeling: Design allowance
- CMC sub-element Testing in realistic environment and Life Duration approach
- Ground and Flight engine CMC parts tests experiments
- Integration and Attachment between CMC parts and metallic parts: Design and testing methodology
Scientific Committee :
- J. Douglas Kiser, NASA Glenn Research Center
- Jay Lane, Rolls-Royce
- Andrew Lazur, Pratt & Whitney
- David Shifler, Office of Naval Research
- James Steibel, GE Aviation
- Hagen Klemm, Fraunhofer IKTS
- Benedikt Albert, MTU
- Imanari Kuniyuki, IHI
- Michel Dessaulty, Safran Aircraft Engine
- Philippe Gomez, French MOD
Points of contact:
Michael Cinibulk, US Air Force Research Labs, USA
E-mail: michael.cinibulk@us.af.mil
Eric Bouillon, Safran Ceramics, France
E-mail: eric.bouillon@safrangroup.com