Lumped model for vortex sound in large solid rocket motors

Lionel Hirschberg, Thierry Schuller, Christophe F. Schram, Jean Collinet

Research output: Chapter in Book/Report/Conference proceedingConference contributionAcademicpeer-review

3 Citations (Scopus)

Abstract

Vortex driven sustained pressure pulsations in large solid rocket motors (SRMs) present an analytical modeling challenge, particularly when finite limit cycle amplitudes predictions are aimed for. The need for analytical models of these pulsations in SRMs is discussed. Two modelling strategies are reviewed: the energy balance and Culick’s lumped model approach. The lumped model has the advantage that it allows a prediction of the pulsation frequency, while this frequency is an input to the energy balance. A detailed derivation of a lumped model using a Vortex Sound Analogy is given. The analogy is similar to Howe’s vortex sound analogy. However, it contains an extra source term, which proves essential to find the correct acoustic radiation losses at the nozzle. When a volume integral is neglected one recovers a result very similar to the expected results. For a cylindrical combustion chamber this approximation is accurate both for axial and radial gas injection into the combustion chamber. For arbitrary combustion chamber geometry and actual combustion, the accuracy of the approximation has still to be established.

Original languageEnglish
Title of host publication2018 AIAA/CEAS Aeroacoustics Conference
PublisherAmerican Institute of Aeronautics and Astronautics
ISBN (Print)9781624105609
DOIs
Publication statusPublished - 2018
Externally publishedYes
Event24th AIAA/CEAS Aeroacoustics Conference 2018 - Atlanta, United States
Duration: 25 Jun 201829 Jun 2018
Conference number: 24

Conference

Conference24th AIAA/CEAS Aeroacoustics Conference 2018
Abbreviated titleAeroacoustics 2018
Country/TerritoryUnited States
CityAtlanta
Period25/06/1829/06/18

Keywords

  • n/a OA procedure

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