10th International Conference on High Temperature Ceramic-Matrix Composites - Register before May 31st!!

Conference Topics > Topic 16 - Aeronautic applications

Topic 16 -  CMC Application in aeronautic engines

Key Words:     SiC/SiC CMC, Oxide/Oxide CMC, Thermomechanical behavior, Design allowance, Burner rig testing, Ground engine testing, Flight engine testing

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.

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

 

 

Points of Contact:

Michael Cinibulk, US Air Force Research Labs, Dayton, OH, USA, michael.cinibulk@wpafb.af.mil

Eric Bouillon, Safran Ceramics, Le Haillan, France, eric.bouillon@safrangroup.com

Scientific Committee :

-       Jim Steibel, GE GRC, Niskayuna, NY, USA

-       Jay Lane, Rolls-Royce, Indianapolis, IN, USA

-       Andrew Lazur, Pratt & Whitney UTRC, East Hartford, CT, USA

-       Michel Desaulty, Safran Aircraft Engines, Villaroche, France

-       Benedikt Albert, MTU, München, Germany

-       Imanari Kuniyuki, IHI Corp., Tokyo, Japan

-       Philippe Gomez, French Ministry of Defense, Toulouse, France

-       Hagen Klemm, Fraunhofer IKTS, Dresden, Germeny

-       David Shifler, Office of Naval Research, Arlington, VA, USA

-       J. Douglas Kiser, NASA Glenn, Cleveland, OH, USA.

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