Rotating detonation rocket engine nozzles

The research activity will focus on the design and The research activity will focus on the design and optimization of supersonic nozzles for rotating detonation rocket engines, with particular emphasis on the interaction between the combustion chamber and the nozzle and its impact on propulsion system performance. The research will address the main fluid-dynamic and thermochemical challenges associated with combustion-product expansion, nozzle adaptation to different operating conditions, and the influence of nozzle geometry on engine performance. The activity will be carried out using in-house numerical simulation tools based on both high-fidelity and reduced-order models to develop efficient analysis and optimization methodologies. The research may also include parametric investigations, sensitivity analyses, and comparative assessments of alternative design configurations

Selection process

Qualifications and Interview evaluationin order to get more information and how to apply, please download the announcement, the application form and attached files at link https://web.uniroma1.it/trasparenza/dettaglio_bando_albo/246533 Interview Topics: Space propulsion, with a primary focus on chemical propulsion systems and rotating detonation engines; Unsteady gas dynamics and fluid dynamics of compressible reacting flows; Combustion instabilities in rocket engines; Numerical simulation methods and modeling of reacting flows; Use of high-fidelity and reduced-order models for the analysis and optimization of propulsion systems; Design and analysis of supersonic nozzles for space propulsion applications up to 60 points for the relevance and significance of qualifications, publications (max 5) and scientific and professional curriculum vitae - up to 40 points for the interview REQUIREMENT: Master's Degree in Space and Astronautical Engineering PREFERRED SKILLS: The candidate shall have a solid background in rocket propulsion, with particular emphasis on chemical rocket propulsion systems and their underlying physical and design challenges. Demonstrated knowledge of unsteady gas dynamics, reacting compressible flows, and thermoacoustic instability phenomena in rocket engines is required. The candidate shall also have experience with numerical methods for the solution of the governing equations of reacting compressible flows, together with proven expertise in the numerical modeling of rotating detonation propulsion systems and the numerical simulation of rocket engine thrust chambers

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