Redistribution of transient shock waves using shock dividers

Bhavraj S. Thethy, Mohammad Rezay Haghdoost, Christian Oliver Paschereit, Damon Honnery, Daniel Edgington-Mitchell, Kilian Oberleithner

Research output: Chapter in Book/Report/Conference proceedingConference PaperOther

1 Citation (Scopus)


The exhaust of a pulse-detonation combustor is characterised by the emission of a high-amplitude primary shock wave and a trailing transient supersonic jet. Attenuation of this shock wave is of importance to the development of pulse-detonation combustors for use in gas turbines. One method of attenuation is to diffuse and redistribute the energy of the shock wave through the use of a shock divider, which splits the leading shock into multiple separate shocks. This paper presents an experimental investigation of three different shock divider designs. High-speed schlieren images are shown along with pressure measurements from within the divider. Static pressure is measured upstream and downstream of the divider and total pressure is measured inside the divider using a high-frequency total-pressure probe. The separation between the split shocks increases as the divider design is varied. The largest temporal separation produced at the exit of the divider was 0.06 ms. The efficiency of each design is evaluated using a metric based on pressure measurements, and was found to be 76%, 86% and 90% of the reference measurement without a divider respectively.

Original languageEnglish
Title of host publicationAIAA Scitech 2020 Forum
PublisherAmerican Institute of Aeronautics and Astronautics
Number of pages16
ISBN (Print)9781624105951
Publication statusPublished - 2020
EventAIAA Scitech Forum 2020 - Orlando, United States of America
Duration: 6 Jan 202010 Jan 2020

Publication series

NameAIAA Scitech 2020 Forum
Volume1 PartF


ConferenceAIAA Scitech Forum 2020
Country/TerritoryUnited States of America

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