Date of Award

5-5-2025

Degree Type

Capstone Project

First Advisor

Bahram Nassersharif

Abstract

The group 11 project is focused specifically on the design of the turbine to provide power and torque to drive the rotation of the Centrifugal Fuel Element (CFE) in the Centrifugal Nuclear Thermal Rocket (CNTR). Design focused on optimization of both high speed power and torque and torque at low speed as well. Other design factor considerations include vibration/resonance, thermal management (in theory, not in testing), and inlet/outlet flow conditions. Combining Computational Fluid dynamics with iterative testing and initial turbine theory, the team was able to successfully design a turbine capable of reaching the 10,000 RPM goal, given further testing and iteration. The final turbine design featured a “C-shaped” airfoil paired with inlet nozzles to produce both low speed torque and high speed power, while maintaining flow integrity. While the design was optimized for air at atmospheric pressure, the design, with accompanying calculations, can easily be transitioned to the desired propellant choice, such as hydrogen or ammonia, at a given pressure. Iterations of the turbine were printed using 3D printers and PLA. Through numerous testing, the team converged on 34 blades for the turbine design, with a nozzle diameter of 0.67 in to ensure maximum mass flow rate through choked flow. The team worked closely with Team 12 to improve upon an existing mount for the turbine and supporting hardware. Using this mount, both teams were able to test their respective parts of the project together, and a rotation speed of 8547 RPM was achieved; over 85% of the desired rate. Team 11 tested out over 40 turbines, several nozzle configurations, and various bearings to achieve this rate of rotation. Fluid simulations indicated that the final configuration was capable of achieving the true desired rate of 10,000 RPM with a positive torque to continue acceleration. Additional changes, such as an increased mass flow rate/fluid power source, increasing rotational stability/stiffness, and improved alignment techniques will allow the working model to achieve 10,000 RPM.

Comments

Team Name: Team 11

Company Sponsor: NASASponsor Representative: Michael Houts

Document Reference: URI-MCE-402-011-2025

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