Experimental Identification of Fluid Thin Film Dynamic Coefficients for Space Propulsion Turbo Pumps
Résumé
Through an application example, a test rig dedicated to the measurement of rotordynamic coefficients for thin fluid film components, as encountered in liquid Rocket Engine Turbopump, is presented. Low viscosity fluids (as cryogenic fluids), leads to thin film flows with high Reynolds number. Tests are performed with a Reynolds similitude, using warm water and a component's nominal diameter about ten times larger than the prototype (for bearings and seals). Typical results are presented for a front shrouded centrifugal pump impeller, using various kinds of eye-packing seals and a vaned diffuser. All the tests have been operated with a centered position of the rotor. For various rotor speeds, experimental data (displacements, forces, pressures, flowrate, temperatures, torque) have been recorded for steady-state static case and dynamic excitations (frequency range from to Hz in Hz increments). First, the performance curves are discussed. en, the identified dynamic coefficients are presented.
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