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The Role of Radial Clearance on the Performance of Foil Air BearingsLoad capacity tests were conducted to determine how radial clearance variations affect the load capacity coefficient of foil air bearings. Two Generation III foil air bearings with the same design but possessing different initial radial clearances were tested at room temperature against an as-ground PS304 coated journal operating at 30,000 rpm. Increases in radial clearance were accomplished by reducing the journal's outside diameter via an in-place grinding system. From each load capacity test the bearing load capacity coefficient was calculated from the rule-of-thumb (ROT) model developed for foil air bearings. The test results indicate that, in terms of the load capacity coefficient, radial clearance has a direct impact on the performance of the foil air bearing. Each test bearing exhibited an optimum radial clearance that resulted in a maximum load capacity coefficient. Relative to this optimum value are two separate operating regimes that are governed by different modes of failure. Bearings operating with radial clearances less than the optimum exhibit load capacity coefficients that are a strong function of radial clearance and are prone to a thermal runaway failure mechanism and bearing seizure. Conversely, a bearing operating with a radial clearance twice the optimum suffered only a 20 percent decline in its maximum load capacity coefficient and did not experience any thermal management problems. However, it is unknown to what degree these changes in radial clearance had on other performance parameters, such as the stiffness and damping properties of the bearings.
Document ID
20020081114
Acquisition Source
Glenn Research Center
Document Type
Technical Memorandum (TM)
Authors
Radil, Kevin
(Army Research Lab. Cleveland, OH United States)
Howard, Samuel
(NASA Glenn Research Center Cleveland, OH United States)
Dykas, Brian
(Ohio Aerospace Inst. Brook Park, OH United States)
Date Acquired
August 20, 2013
Publication Date
July 1, 2002
Subject Category
Aircraft Propulsion And Power
Report/Patent Number
NAS 1.15:211705
E-13450
ARL-TR-2769
NASA/TM-2002-211705
Report Number: NAS 1.15:211705
Report Number: E-13450
Report Number: ARL-TR-2769
Report Number: NASA/TM-2002-211705
Meeting Information
Meeting: International Joint Tribology Conference
Location: Cancun
Country: Mexico
Start Date: October 27, 2002
End Date: October 30, 2002
Sponsors: Society of Tribologists and Lubrication Engineers, American Society of Mechanical Engineers
Funding Number(s)
PROJECT: RTOP 708-18-13
PROJECT: DA Proj. 1L1-61102-AH-45
Distribution Limits
Public
Copyright
Public Use Permitted.
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