Keywords

Propulsion, Detonations, Liquid Injection

Abstract

The Ongoing effort to advance the Technology Readiness Level (TRL) of Rotating Detonation Engines (RDEs) has faced significant challenges with respect to the development of accurate analytical models for the performance of liquid fueled detonations. A key issue lies in the lack of comprehensive experimental data to validate and refine these models. To address this gap, the present study seeks to provide detailed characterization data on a specific Liquid Rotating Detonation Rocket Engine (LRDRE) injector, which can be leveraged to improve simulation accuracy and predictive capabilities. This investigation is divided into two primary phases. The first phase focuses on the macroscopic analysis of liquid spray formation, specifically examining the influence of varying liquid fuel temperatures on injector behavior. By analyzing parameters such as beta angle and average frame intensity, this phase aims to determine whether fuel temperature plays a significant role in spray development and liquid atomization. The second phase delves into the microscopic characteristics of the liquid spray, employing a Phase Doppler Interferometer (PDI) to generate parameter maps detailing mean droplet diameter (D10), Sauter Mean Diameter (D32 or SMD), and mean velocity at multiple distinct locations within the spray. These measurements provide crucial insights into the droplet dynamics and their dependence on operating conditions, ultimately contributing to a more refined understanding of injector performance and aiding in the development of more reliable liquid-fueled RDE models.

Completion Date

2025

Semester

Spring

Committee Chair

Ahmed, Kareem

Degree

Master of Science in Aerospace Engineering (M.S.A.E.)

College

College of Engineering and Computer Science

Department

Mechanical and Aerospace Engineering

Identifier

DP0029388

Document Type

Dissertation/Thesis

Campus Location

Orlando (Main) Campus

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