Design of a shock tube facility to investigate droplet aerobreakup

Document Type

Conference Proceeding

Publication Date

1-1-2020

Abstract

The interaction between a propagating shock wave with fuel droplets forms a fundamental process occurring in several propulsion applications. The ensuing processes including droplet aerobreakup, ignition, and combustion, are strongly influenced by the droplet-shock wave interaction. This study documents the design of a shock tube facility to study droplet-shock wave interaction under controlled conditions using non-intrusive diagnostic techniques. A shock tube capable of operating up to Mach 6 using Helium as the driver gas and air as the driven gas is designed. The various dimensions of the shock tube sections including lengths, diameters, and wall thicknesses are determined. Stress analysis using FEA is conducted to ensure a minimum factor of safety requirement. Numerical simulations are also carried out to study the breakup, vaporization, and combustion processes for iso-octane droplets. Comparisons are made to study the effect of shock Mach number on the interaction processes.

Publication Source (Journal or Book title)

AIAA Propulsion and Energy 2020 Forum

First Page

1

Last Page

16

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