Durable Solution for Compressor Airfoil Leading Edges in Gas Turbine Engines

Award Information
Agency:
Department of Defense
Branch
n/a
Amount:
$79,678.00
Award Year:
2012
Program:
SBIR
Phase:
Phase I
Contract:
N68335-12-C-0275
Award Id:
n/a
Agency Tracking Number:
N121-039-1087
Solicitation Year:
2012
Solicitation Topic Code:
N121-039
Solicitation Number:
2012.1
Small Business Information
780 Eden Road, Lancaster, PA, -
Hubzone Owned:
N
Minority Owned:
N
Woman Owned:
N
Duns:
055625685
Principal Investigator:
James Marder
Vice President - Mats. an
(412) 382-7150
j.m.marder@thermacore.com
Business Contact:
Nelson Gernert
Vice President - Engineer
(717) 569-6551
n.j.gernert@thermacore.com
Research Institution:
Stub




Abstract
In austere environments, erosion and corrosion seriously degrade the performance of airfoils in fan and compressor sections of gas turbine engines. To prevent damage to titanium airfoils, a powder metallurgy approach will be taken that produces a hard, erosion resistant leading edge. The leading edge should be strongly bonded to the blade body, have similar resonant characteristics (elastic modulus driven) as well as sufficiently similar to the chemistry of the blade body so as not to set up galvanic corrosion cells. The body of the blade will be fabricated using conventional powder to maintain the overall toughness of the blade in the event of large body ballistic impact. The approach that will be taken will be that of cryo-milling titanium alloy powder similar to that used in conventional blades, and using powder metallurgy techniques, such as HIP and CIP/HIP to assure that the hard, strong cryo-milled powder becomes an integral part of the leading edge of the blade. After milled and unmilled powders are placed so that the cryomilled powder will become the leading edge, consolidation will be followed by forging to obtain the proper airfoil shape.

* information listed above is at the time of submission.

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