Effect of two inner-ring oil-flow distribution schemes on the operating characteristics of a 35-millimeter-bore ball bearing to 2.5 million DN
Fredrick T. Schuller, Stanley I. Pinel, Hans R. Signer, United States. National Aeronautics and Space Administration. Scientific and Technical Information Branch
National Aeronautics and Space Administration, Scientific and Technical Information Branch, 1985 - Technology & Engineering - 11 pages
8 pages matching thrust load in this book
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2.5 million DN 25 percent flowed 50-percent flow axial grooves bearing bore bearing operating bearing power loss cm3/min cmVmin 0.20 gal/min combined load contact angle cool the inner cooling oil flow Cooling the outer double-inner-land-guided cage equal inner flow to inner-ring heat rejection increased with increasing increasing shaft speed inner ring flowed inner-ring temperature Lewis Research Center load conditions load of 667 loss as obtained Lubricant flow rate lubricated the bearing maximum cage slip N(lb NASA oil flow rates oil flow supplied oil-flow distribution schemes oil-inlet temperature Outer ring cooled Outer-ring cooling oil outer-ring temperature Parametric tests percent cage slip percent flowed axially radial holes radial load rate to inner rate to test ring flowed radially ring on bearing speed and lubricant speed of 72 split-inner-ring ball bearing strain gage test bearing temperature test machine tests 50 percent thermocouple thrust and 222 thrust load torque measurements total oil flow