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The Effects of Inlet Flow Modification on Cavitating Inducer Performance

Del Valle, J. and Braisted, D. M. and Brennen, C. E. (1992) The Effects of Inlet Flow Modification on Cavitating Inducer Performance. Journal of Turbomachinery, 114 (2). pp. 360-365. ISSN 0889-504X.

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This paper explores the effect of inlet flow modification on the cavitating and noncavitating performance of two cavitating inducers, one of simple helical design and the other a model of the low-pressure LOX pump in the Space Shuttle Main Engine. The modifications were generated by sections of honeycomb, both uniform and nonuniform. Significant improvement in the performance over a wide range of flow coefficients resulted from the use of either honeycomb section. Measurements of the axial and swirl velocity profiles of the flows entering the inducers were made in order to try to understand the nature of the inlet flow and the manner in which it is modified by the honeycomb sections.

Item Type:Article
Additional Information:Contributed by the International Gas Turbine Institute for publication in the Journal of Turbomachinery. Manuscript received by the International Gas Turbine Institute September 1991. The authors would like to thank NASA George Marshall Space Flight Center for support of this research under Contracts NAS8-29313, NAS8-29046, and Grant No. NAG8-118.
Issue or Number:2
Record Number:CaltechAUTHORS:DELjot92
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Usage Policy:No commercial reproduction, distribution, display or performance rights in this work are provided.
ID Code:95
Deposited By: Christopher Brennen
Deposited On:05 Oct 2004
Last Modified:02 Oct 2019 22:16

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