STTR Phase I: Demonstration of Enhanced Corrosion Resistance using a Nano-composite Thermal Barrier Coating

Award Information
Agency:
National Science Foundation
Branch
n/a
Amount:
$149,977.00
Award Year:
2007
Program:
STTR
Phase:
Phase I
Contract:
0637297
Agency Tracking Number:
0637297
Solicitation Year:
n/a
Solicitation Topic Code:
n/a
Solicitation Number:
n/a
Small Business Information
Mainstream Engr Corp
200 Yellow Place, 6745 HOLLISTER AVENUE, Rockledge, FL, 32955
Hubzone Owned:
N
Socially and Economically Disadvantaged:
N
Woman Owned:
N
Duns:
175302579
Principal Investigator:
Michael Cutbirth
Dr
(321) 631-3550
mcutbirth@mainstream-engr.com
Business Contact:
Robert Scaringe
PhD
(321) 631-3550
rps@mainstream-engr.com
Research Institution:
USRA
Randy L VanderWal
10211 Wincopin Circle
Columbia, MD, 21044 3432
(216) 433-9064
Federally funded R&D center (FFRDC)
Abstract
This Small Business Technology Transfer (STTR) Phase I project will experimentally validate the theory that inclusion of nanostructures within the Thermal Barrier Coatings (TBC) will enhance the resistance to hot corrosion by increasing the fracture strength of the ceramic thereby inhibiting grain growth similar to reinforcing concrete with rebar. The grain growth leads to the formation and growth of interconnected cracks needed for wicking of molten salts that result in spallation. The novel nanocomposite coating would find application within fossil energy power generation devices (dirty fuel) and aircraft engines (marine environments). Current technology turbine blades are comprised of single crystal nickel superalloys. Historically, protective TBC have allowed for operation of the turbine while subjected to hot gases exiting the combustor at temperatures exceeding the superalloy melting point. The increase in turbine inlet temperature has yielded improvements in efficiency, power density, and emission quality. However, these protective barriers are susceptible to hot corrosion, an electrochemical reaction between the superalloy and molten salts resulting in spallation or fragmentation of the thermal barrier coating. The reduction of premature spalling will allow for the simultaneous increase of the turbine inlet temperature and the reduction of the turbine coolant air. This combination has the potential to increase efficiency, reduce toxic emissions, and save capital costs.

* information listed above is at the time of submission.

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