A water test facility for liquid rocket engine turbopump cavitation testing

Abstract

Improved understanding of the physics of turbopump cavitation and its relation to engine design parameters is needed to enhance propulsion system reliability and reduce development costs. A program to investigate cavitation phenomena in liquid rocket turbopumps has been initiated at The Aerospace Corporation to improve capability to predict the phenomena. This paper presents the methodology for the design of a new water-flow cavitation test facility capable of testing a variety of rocket turbopumps over a wide range of operating conditions to simulate the thermal characteristics of cryogenic propellants. This new cavitation test facility is now operational and qualification testing is in progress. Future experiments conducted in the facility will provide valuable data for the characterization of turbopump cavitation phenomena as well as evaluation, development, and validation of cavitation models.