Vortex nozzle interaction in solid rocket motors: A scaling law for upstream acoustic response | Zendy

Lionel Hirschberg | Zendy; Steven J. Hulshoff | Zendy; Jean Collinet | Zendy; C. Schram | Zendy; Thierry Schuller | Zendy

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Vortex nozzle interaction in solid rocket motors: A scaling law for upstream acoustic response

Author(s) -

Lionel Hirschberg,

Steven J. Hulshoff,

Jean Collinet,

C. Schram,

Thierry Schuller

Publication year - 2018

Publication title -

the journal of the acoustical society of america

Language(s) - English

Resource type - Journals

SCImago Journal Rank - 0.619

H-Index - 187

eISSN - 1520-8524

pISSN - 0001-4966

DOI - 10.1121/1.5046441

Subject(s) - nozzle , mechanics , scaling , physics , vortex , solid fuel rocket , scaling law , rocket (weapon) , aeroacoustics , amplitude , flow (mathematics) , aerospace engineering , classical mechanics , acoustics , sound pressure , engineering , optics , geometry , thermodynamics , mathematics , propellant

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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