Performance of a turboalternator gas-bearing system at steady-state conditions
Roman Kruchowy, James C. Wood, Joseph S. Curreri, Lewis Research Center, United States. National Aeronautics and Space Administration
National Aeronautics and Space Administration, 1969 - Technology & Engineering - 30 pages
Turboalternator gas-bearing system performance at steady state conditions.
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33 kilowatts electric 8.9 kilowatts alternator output alternator speed anti-drive-end anti-drive-end bearing argon Average pad clearance bearing clearance bearing pad bearing-rotor system capacitance probe coolant temperature copper losses deflection design conditions design value disassembled for inspection drive-end journal drive-end-bearing clearance exchangers and support Figure 17 film thickness variation gas bearings gas coolant flow gas flow gas temperature heat exchangers heat-exchanger oil flow hydrodynamic hydrostatic jacking gas journal bearing journal clearance journal orbit journal-bearing clearance Lewis Research Center load conditions Main thrust load NASA oil coolant flow oil flow rate output power pad motions pad or shaft pad pivot power output pressure ratio psia resonance reverse-thrust-bearing film thickness roll motions rotation rotor Schematic drawing short circuit shown in figure startup stator STEADY-STATE CONDITIONS support ring thermocouples thrust bearing thrust load value Turbine inlet pressure turbine inlet temperature Turbine weight flow valve variation at 7200 Varying Power Factor