Thin Layered Damping Treatments for Turbo Machinery

Award Information
Agency: Department of Defense
Branch: Navy
Contract: N68335-02-C-3113
Agency Tracking Number: N01-168-01
Amount: $69,200.00
Phase: Phase I
Program: SBIR
Awards Year: 2002
Solicitation Year: N/A
Solicitation Topic Code: N/A
Solicitation Number: N/A
Small Business Information
P.O. Box 329, Free Union, VA, 22940
DUNS: 036500804
HUBZone Owned: N
Woman Owned: N
Socially and Economically Disadvantaged: N
Principal Investigator
 Douglas Queheillalt
 Chief Finiacial Officer
 (804) 825-1345
Business Contact
 Derek Hass
Title: Chief Technology Officer
Phone: (804) 825-6938
Research Institution
"Rotors, such as for gas turbine engines and the like, are typically subjected to high stresses and high temperatures. Extensive efforts have been made over the years to develop new alloys, new fabrication techniques, and new component designs which permitoperation of these rotors at higher operating temperatures and/or which lead to lighter weight, longer lived components. State-of-the-art designs of compressor and turbine rotors for aircraft gas turbine engines are using integrally bladed rotor (IBR)technologies (rotor and blades are one piece - continuous structure). The advantage of this one-piece construction is weight savings and reduced losses from cavity flows inherent with a bladed disk. The disadvantage comes from the reduction of overalldamping provided by the friction interface at the blade/disk attachment. The first approach we will pursue using the DVD process will make use of a porous columnar Ni- or Ti- alloy to perform the bulk of the energy conversion. Another approach will pursueusing the DVD process will make use of a cellular NiTi shape memory alloy (SMA) to perform the bulk of the energy conversion. The coatings will consist of a compliant bondcoat, porous columnar or cellular SMA and constraining layer. Development of a costeffective vapor deposition method for the production of multi-layered damping structures."

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

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