Multilayer microlaminated ceramic thermal barrier coating

Award Information
Agency:
Department of Defense
Amount:
$700,000.00
Program:
SBIR
Contract:
N/A
Solitcitation Year:
N/A
Solicitation Number:
N/A
Branch:
Air Force
Award Year:
1997
Phase:
Phase II
Agency Tracking Number:
36691
Solicitation Topic Code:
N/A
Small Business Information
Materials Modification, Inc.
2929-P1 Eskridge Road, Fairfax, VA, 22031
Hubzone Owned:
N
Woman Owned:
N
Socially and Economically Disadvantaged:
N
Duns:
N/A
Principal Investigator
 C. Charles Yu Ph.d.
 (703) 560-1371
Business Contact
Phone: () -
Research Institution
N/A
Abstract
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.

* information listed above is at the time of submission.

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