NASA NTRS · 19900000667
Computing Flows In Turbine End Bearings
Abstract
Computer program implements mathematical model of flow through turbine and bearings of high-pressure-oxygen turbopump of Space Shuttle main engine. Intended to determine rate of flow and margin before vaporization in these bearings for various types of geometries. Effects of hydrostatic damper and/or back-pressure seal included. Modified for application to other turbomachines and fluids other than oxygen.
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Smith, Tyn S.. 1990-12-01. Computing Flows In Turbine End Bearings. https://ntrs.nasa.gov/citations/19900000667
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