Corrosion/Erosion Resistant Coatings for Turbine Compression Systems

Award Information
Agency:
Department of Defense
Branch
Navy
Amount:
$102,986.00
Award Year:
2002
Program:
SBIR
Phase:
Phase I
Contract:
N00421-02-C-3034
Award Id:
59346
Agency Tracking Number:
N01-165-03
Solicitation Year:
n/a
Solicitation Topic Code:
n/a
Solicitation Number:
n/a
Small Business Information
121 Tennessee Avenue, N.E., Washington, DC, 20002
Hubzone Owned:
N
Minority Owned:
N
Woman Owned:
N
Duns:
044754575
Principal Investigator:
MarcioDuffles
Aerospace Engineer
(202) 546-7442
dufflesm@bellatlantic.net
Business Contact:
MarcioDuffles
President
(202) 546-7442
dufflesm@bellatlantic.net
Research Institute:
n/a
Abstract
"The proposed Corrosion/Erosion Resistant (C/ER) coating is amulti-layered "Titanium-Nitride" coating that is applied todifferent compressor airfoils via a Cathodic-Arc PhysicalVapor Deposition process.The C/ER coating has been applied to over 2000 Russianmanufactured TV2-117 turboshaft engines and demonstratedsignificant operational savings due to decreasedrejection of compressor airfoils, decreased fuelconsumption and increased operational hours beforeengine overhaul. In addition, the C/ER coatingrecently completed a successful Foreign Comparative Test(FCT) test & evaluation program for application on aGE T64-419 turboshaft engine.The C/ER Coating process and composition can be optimizedfor different gas turbine engine compressor systems andsubsystems. For example, the coating composition can beenhanced to provide greater corrosion protection and maintainerosion protection, and the coating application can beoptimized for application on single compressor airfoils, vanesegments, blisk rotors and centrifugal compressors. The anticipated benefits of the C/ER Caoting includes decreased totalownership cost to the operator via: a reduced number of compressor airfoilsubsystems rejected due to corrosion or erosion; increased engineperformance due to decreased compressor degradation, increased mean-timebetween engine repair and increased engine time-on-wing.These anticipated benefits can be realized for gas turbine compressionsystems and s

* information listed above is at the time of submission.

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