Design Study of Shaft Face Seal with Self-acting Lift Augmentation: Force balance / by Lawrence P. Ludwig, John Zuk and Robert L. Johnson, Volume 4
National Aeronautics and Space Administration, 1972 - Aircraft - 27 pages
A method for predicting the operating film thickness of self-acting seals is described. The analysis considers a 16.76-cm mean diameter seal that is typical of large gas turbines for aircraft. Four design points were selected to cover a wide range of operation for advanced engines. This operating range covered sliding speeds of 61 to 153 m/sec, sealed pressures of 45 to 217 N/sq cm abs, and gas temperatures of 311 to 977 K. The force balance analysis revealed that the seal operated without contact over the operating range with gas film thicknesses ranging between 0.00046 to 0.00119 cm, and with gas leakage rates between 0.01 to 0.39 scmm.
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2-milliradian analysis area ratio axial force centimeter closing force due Compressible Flow described in reference due to sealed effects of nonparallel equilibrium film thickness face deformation force balance indicator forces acting four design points gas film thickness gas leakage inside diameter labyrinth seal Lawrence leakage flow leakage rates Lewis Research Center lift force Ludwig mathematical model Mean film thickness NASA TN noncontact operation nonparallel faces nutation operating film thickness operating points parallel faces piston ring pneumatic closing force pressure balance pressure gradient pressure profile primary ring assembly primary seal faces primary seal opening range of operation rubbing contact scfm seal design seal force balance seal opening force Seal with Self-Acting sealed air Sealing Dam seat face runout secondary seal Self-Acting Lift Augmentation self-acting pad self-acting seals Shaft Face Seal shown in figure sliding speed Study of Shaft Takeoff total closing force total opening force