Experimental and numerical study of oxygen-hydrogen rocket flame response to transverse acoustic excitation

Scott K. Beinke, Justin S. Hardi, Michael Oschwald, Daniel T. Banuti, Sebastian Karl, Bassam B. Dally

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

Abstract

The response of an oxygen-hydrogen flame to transverse acoustic velocity forcing is investigated using a combination of experimental analysis and numerical modelling. An experimental rocket combustor is used to study the response of oxygen-hydrogen flames to acoustic forcing representative of high frequency combustion instabilities. Optical datasets were analysed to identify the response of the flame to a transverse acoustic velocity disturbance using a multi-variable DMD method. As the optical access only allows for 2D imaging, CFD modelling of a representative single injector under forcing are emploiyed to gain insight into the three-dimensional features of the flow field. The numerical results successfully captured the exponential reduction in LOX core length as a function of the transverse acoustic amplitude that was observed experimentally. The CFD result show the excited LOX jet develops into a flattened and widened structure normal to the imposed disturbance. The complementary numerical and experimental analyses provide further insight into the transverse flame response.
Original languageEnglish (US)
Title of host publication2018 Joint Propulsion Conference
PublisherAmerican Institute of Aeronautics and Astronautics Inc, AIAA
ISBN (Print)9781624105708
DOIs
StatePublished - Jan 1 2018
Externally publishedYes

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