ELIA PUCCINELLI; ANGELO PASINI

DOI Number: 10.13009/EUCASS2023-042

The present work represents the first step toward a new layout for the nuclear propulsion systems. The regenerative cooled nozzle present in the historic configuration is eliminated from the system and replaced with several small er nozzles shaped inside each core’s coolant channels. The focus of this study is the determination of the channel’s optimum geometry for a general fuel element and the corresponding power density distribution. These outputs are achieved by implementing a new methodology for solving the ID steady viscous and non-adiabatic duct flow equations by imposing the Mach number and the wall outer temperature profiles as boundary conditions.

Read the full paper here

In Categories: 1. Aerospace Europe Conference 2023, 1.Events, 18. Testing in Aerospace
Email
Print
LinkedIn
The paper above was part of  proceedings of a CEAS event and as such the author has signed a publication agreement to have their paper published in the repository. In the case this paper is found somewhere else CEAS always links to the other source.  CEAS takes great care in making the correct content available to the reader. If any mistakes are found  in the listings please contact us directly at papers@aerospacerepository.org and we will correct the listing promptly.  CEAS cannot be held liable either for mistakes in editorial or technical aspects, nor for omissions, nor for the correctness of the content. In particular, CEAS does not guarantee completeness or correctness of information contained in external websites which can be accessed via links from CEAS’s websites. Despite accurate research on the content of such linked external websites, CEAS cannot be held liable for their content. Only the content providers of such external sites are liable for their content. Should you notice any mistake in technical or editorial aspects of the CEAS site, please do not hesitate to inform us.