Prediction of Glass Formation in High-Temperature Environmental Barrier Coating Systems

Award Information
Agency:
Department of Defense
Branch
Air Force
Amount:
$99,999.00
Award Year:
2009
Program:
SBIR
Phase:
Phase I
Contract:
FA8650-09-M-5212
Agency Tracking Number:
F083-070-0420
Solicitation Year:
2008
Solicitation Topic Code:
AF083-070
Solicitation Number:
2008.3
Small Business Information
Infoscitex Corporation
303 Bear Hill Road, Waltham, MA, 02451
Hubzone Owned:
N
Socially and Economically Disadvantaged:
N
Woman Owned:
N
Duns:
004627316
Principal Investigator:
Robert Woodman
Senior Engineer
(781) 890-1338
rwoodman@infoscitex.com
Business Contact:
William Thompson
Contracts Manager
(781) 890-1338
bthompson@infoscitex.com
Research Institution:
n/a
Abstract
Further improvement in gas-turbine engine performance requires development of hot-section structural materials capable of functioning at unprecedentedly high temperatures. SiC fiber-reinforced SiC ceramic-matrix composites (CMCs) have high melting points, but are thermodynamically unstable in combustion environments. Environmental barrier coatings (EBCs) have been developed to protect the substrate from the combustion gases. It is unknown whether current EBCs are capable of protecting CMCs over their intended design life of approximately 2000 h. Physical models that make it possible to predict the effects of the service environment on the materials would enable design decisions without resorting to full-scale testing. In the proposed Phase I SBIR program, Infoscitex will develop a thermodynamic model for a simplified system that will lay the foundation for modelling full-scale parts in realistic combustion environments. Infoscitex will develop a database of thermodynamic data. A range of temperatures and coating systems will be investigated during the Phase I program. This model will be tailored to facilitate incorporation of additional EBC components in later phases. BENEFIT: The proposed modelling technology will allow optimization of high-temperature engine parts while minimizing costly experimentation. This technology will be applicable across the aerospace propulsion industry. The successful model will enable next-generation performance turbine engines. The model may also have applications beyond the aerospace propulsion industry, such as in glass manufacturing.

* information listed above is at the time of submission.

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