Thermal Barrier Coating Environmental Durability Enhancement (CMAS)

Award Information
Agency: Department of Defense
Branch: Navy
Contract: N68335-06-C-0265
Agency Tracking Number: N061-032-0286
Amount: $149,829.00
Phase: Phase I
Program: SBIR
Awards Year: 2006
Solicitation Year: 2006
Solicitation Topic Code: N06-032
Solicitation Number: 2006.1
Small Business Information
2 Boar's Head Lane, Charlottesville, VA, 22903
DUNS: 036500804
HUBZone Owned: N
Woman Owned: N
Socially and Economically Disadvantaged: N
Principal Investigator
 Derek Hass
 Dir. of Research and Deve
 (434) 977-1405
Business Contact
 Harry Burns
Title: President and CEO
Phone: (434) 977-1405
Research Institution
Advanced thermal barrier coating systems are desired for naval gas turbine engines. These coatings will increase the durability of hot-section engine components to significantly improve the time “on-wing”, safety and readiness of these engines. In this work, we will use novel coating synthesis techniques that enable the deposition of advanced compositions and microstructures to achieve a comprehensive thermal barrier coating system that provides vastly improved resistance to damage from CMAS. A low cost, high throughput processing approach for the application of this TBC system is also envisioned. The proposed Phase I effort will identify CMAS protection concepts that are anticipated to meet the performance goals at both current and future engine operating temperatures and demonstrate the feasibility of applying these concepts using our advanced processing techniques. The successful completion of the Phase I work will lead to a follow-on Phase II program focused on down-selecting candidate approaches for optimization and applying the new coating onto real aircraft components. Success in this objective will offer the military a pathway toward production implementation of these advanced coatings and the new deposition processing capabilities required for applying coatings of this type onto engine components.BENEFITS: This research is anticipated to result in a thermal barrier coating system that provides unprecedented protection from CMAS induced failures. This will help enable the realization of many advanced gas turbine engine designs leading to thrust improvement or specific fuel consumption reduction for current turbine engines. These advances will not only benefit military engines, but also commercial and industrial gas turbines. In addition, the innovative approach proposed here will reduce the time and expense for refurbishing and repairing blades during engine overhauls, thus improving military readiness and reducing the cost of maintaining commercial aircraft.

* Information listed above is at the time of submission. *

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