Multilayer microlaminated ceramic thermal barrier coating
Agency / Branch:
DOD / USAF
The use of a thermal barrier coating (TBC) can substantially increase the efficiency of gas turbine engines by allowing increased working temperature and/or reduction of cooling airflow. Current TBCs consist of a single ceramic layer, about 10% porous, appliled to the bond coated metallic substrates. The single ceramic layer structure is more susceptible to damage, and it does not greatly restrict the influx of oxygen or other corrosive gases from reaching the bond coat. The multi-layer construction will be more resistant to damage, and the reinforcement layers within the structure can be engineered to function as the diffusion barriers against oxygen and other corrosive gases. By adapting the multi-layer configuration, not only the individual thickness of thermal insulation layer will be restricted to micro- or even nano-scale, their overall thickness will be reduced as well, thus microstructural control is necessary to increase the thermal barrier efficiency. The two technologies for making current TBCs, plasma spray and PVD, are incapable of generating ceramic coating layers with the desired thickness and microstructure demanded by the multi-layer TBC approach. In this Phase I effort, MMI proposes to develop a sol-gel process to apply micro-laminated TBC with an engineered structure, controlled thickness and microstructures.
Small Business Information at Submission:
Principal Investigator:C. Charles Yu Ph.d.
Materials Modification, Inc.
2929-P1 Eskridge Road Fairfax, VA 22031
Number of Employees: