Cavitation-Induced Vibrations in a Two-Bladed Rocket Engine Inducer
Abstract
Experimental investigation of cavitation induced vibrations in a 2-bladed water model inducer was performed for inlet flowrates ranging from 70% to 120% of the design flowrate and over a range of inlet cavitation numbers representative of a typical rocket engine operation. Dynamic (high frequency) pressure transducers were used to record fluctuating pressures along inducer housing (stationary reference frame) up to 2500 Hz, i.e. about 30 times the shaft speed. Data were obtained in two axial planes: one 0.08 diameters upstream and one 0.37 diameters downstream relative to the inducer blade leading edge tip plane. Flow visualization data at conditions typical of tip vortex instabilities at high cavitation number and sheet cavitation are presented and correlated to dynamic signature. Dynamic spectrum of the 2-bladed inducer is compared to data representative of the environment in a 4-bladed rocket engine inducer. The differences in the dynamic characteristics between the 2-bladed and 4-bladed inducers and the potential implications to inducer design decisions for lowering the impact of cavitation induced vibrations in turbomachinery are discussed.
Document Details
- Document Type
- Technical Report
- Publication Date
- Feb 01, 2008
- Accession Number
- ADA480749
Entities
People
- Kevin Burton
- Maria Subbaraman
- Mark Nadolski
- Robert Hibbs
Organizations
- Aerojet Rocketdyne Holdings