Understanding and avoidance of thermoacoustic instabilities is of crucial importance in the design and operation of both gas turbine combustors as well as rocket engines. Despite apparent methodological and phenomenological overlaps, two almost entirely separated research networks have evolved around both industries, which have developed their own research strategies and methodologies. The strong overlap is currently further increasing due to the recently growing interest of the gas turbine community in acoustically non-compact high frequency oscillations. The aim of this symposium is to bring together researchers from industry and academia and to provide a forum on which synergies between rocket and gas turbine research can be exploited.
The symposium’s framework consists of three and a half days, divided in multiple sessions with different topics on combustion dynamics. Each session will start with a 45 minute invited talk from an expert from either industry or academia. Papers presented at the symposium may be resubmitted for review and publication in a special issue of the "International Journal of Spray and Combustion Dynamics".
Specific topics related to thermoacoustic oscillations in gas turbine and rocket engines to be covered are:
Please notice that due to the large amount of received and accepted abstracts, we will not be able to facilitate the originally planned tutorial sessions on high-frequency thermoacoustic analysis and modeling methods.