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Improved Turbine Engine Bearing Materials And Processes

Award Information
Agency: Department of Defense
Branch: Air Force
Contract: FA8650-05-M-2572
Agency Tracking Number: F051-181-0828
Amount: $100,000.00
Phase: Phase I
Program: SBIR
Solicitation Topic Code: AF05-181
Solicitation Number: 2005.1
Solicitation Year: 2005
Award Year: 2005
Award Start Date (Proposal Award Date): 2005-03-23
Award End Date (Contract End Date): 2006-03-23
Small Business Information
4415 Euclid Avenue, Suite 500
Cleveland, OH 44103
United States
DUNS: 557510336
HUBZone Owned: No
Woman Owned: No
Socially and Economically Disadvantaged: No
Principal Investigator
 Greg Shaw
 Director, Microdevices & Smart Mat.
 (216) 649-0399
Business Contact
 Joseph Snyder II
Title: Vice President, Administration
Phone: (216) 649-0399
Research Institution

The VAATE program and other advanced turbine engines require improved bearing materials for better resistance to fatigue, wear and corrosion. Orbital Research proposes a combination of two processing methods to ensure the optimum properties. Starting with a high strength stainless steel (Pyrowear 675) to ensure corrosion resistance, a novel heat treating method will be used that dramatically increases the surface hardness and compressive stresses relative to standard methods. The core properties are not diminished, and may be improved. The part is then coated with titanium nitride to provide enhanced wear resistance. The coating is applied using another novel method that dramatically improves adhesion so that it can withstand the high load, high speed conditions present in advanced turbine engines. In Phase I the improvement in material properties and performance characteristics will be demonstrated, and the process designed for a prototype turbine engine bearing. Properties to be measured include strength, toughness, hardness, wear resistance and fatigue resistance. In Phase II prototype bearings will be fabricated and tested. Initial testing will be completed on high speed, high load bearing test rigs. Subsequent testing will be performed in a turbine engine test stand.

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

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