Vortex nozzle interaction in solid rocket motors

A scaling law for upstream acoustic response

Journal article (2018)

Authors

L. Hirschberg Université Paris-Saclay, von Karman Institute for Fluid Dynamics
S.J. Hulshoff Aerodynamics - Aerospace Engineering
J. Collinet von Karman Institute for Fluid Dynamics
Christophe Schram von Karman Institute for Fluid Dynamics
T. Schuller Université Paris-Saclay
Research Group
Aerodynamics (Aerospace Engineering) (TU Delft)
Copyright: © 2018 L. Hirschberg, S.J. Hulshoff, J. Collinet, C. Schram, T. Schuller
DOI: https://doi.org/10.1121/1.5046441
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Published Date

01-07-2018

Language

English

Reuse Rights

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Faculty

Aerospace Engineering

Department

Flow Physics and Technology

Research Group

Aerodynamics

Abstract

In solid rocket motors, vortex nozzle interactions can be a source of large-amplitude pressure pulsations. Using a two-dimensional frictionless flow model, a scaling law is deduced, which describes the magnitude of a pressure pulsation as being proportional to the product of the dynamic pressure of the upstream main flow and of vortex circulation. The scaling law was found to be valid for both an integrated nozzle with surrounding cavity and a nozzle geometry without surrounding cavity that forms a right angle with the combustion chamber side wall. Deviations from the scaling law only occur when unrealistically strong circulations are considered.

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