Date of Award

5-2026

Degree Type

Capstone Project

First Advisor

Professor Bahram Nassersharif

Abstract

The Centrifugal Nuclear Thermal Rocket (CNTR) is an advanced propulsion concept whose performance is strongly influenced by the efficiency and continuity of its propellant flow path. This project focuses on improving the geometric integrity and analytical fidelity of the CNTR fuel tube inlet and manifolds, which are critical subsystems governing pressure losses and downstream performance. In prior designs, these parts consisted of multiple components assembled using adhesive, introducing geometric discontinuities that increased head losses and limited the reliability of computational analysis.

In this work, the inlet and manifold were successfully redesigned as single, integrated components. This redesign represents a key advancement, as it eliminates discontinuities associated with bonded interfaces, reduces flow separation, and enables direct and accurate Computational Fluid Dynamics (CFD) analysis. The unified geometries allow for improved simulation capability in ANSYS Fluent, providing more reliable predictions of pressure drop, velocity distribution, and flow development within the system.

SolidWorks was used to develop revised geometry, and preliminary CFD simulations were conducted to evaluate flow behavior and identify remaining areas for refinement. Results indicate improved flow continuity and reduced head loss relative to prior configurations, establishing a stronger foundation for future optimization. This improved fluid flow also improved the heat transfer of the system. COMSOL was used to develop the updated heat transfer model. This work significantly improves both the experimental and analytical framework of the CNTR test apparatus and enables higher-fidelity design decisions in subsequent project phases.

Comments

Team Name: Team 10

Document Reference: URI-MCE-2026-FDR-010

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