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Experimental Characterization of Thermal Cavitation Effects on Space Rocket Axial Inducers

[+] Author Affiliations
Angelo Pasini, Lucio Torre, Angelo Cervone

Alta S.p.A., Pisa, Italy

Luca d’Agostino

University of Pisa, Pisa, Italy

Paper No. AJK2011-06043, pp. 223-234; 12 pages
doi:10.1115/AJK2011-06043
From:
  • ASME-JSME-KSME 2011 Joint Fluids Engineering Conference
  • ASME-JSME-KSME 2011 Joint Fluids Engineering Conference: Volume 1, Symposia – Parts A, B, C, and D
  • Hamamatsu, Japan, July 24–29, 2011
  • Conference Sponsors: Fluids Engineering Division
  • ISBN: 978-0-7918-4440-3
  • Copyright © 2011 by ASME

abstract

The paper shows the results of an experimental campaign conducted in the CPRTF (Cavitating Pump Rotordynamic Test Facility) at ALTA S.p.A., aimed at characterizing the cavitation thermal effects on two tapered-hub, variable-pitch inducers, designated as DAPAMITO. The semi-empirical method proposed by Ruggeri and Moore for scaling the thermal cavitation effects has been successfully applied and, consequently, a further validation of this method has been provided. The influence of the temperature on the intensity of the performance degradation associated with the attached cavitation instability has been identified as a new typology of cavitation thermal effects. In this case, the inhibition of the bubble growth due to thermal effects can be detected by the reduction of the performance degradation usually associated with this type of instability.

Copyright © 2011 by ASME

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