Keywords

hypersonic injector accumulator plumbing performance atomization

Abstract

Accumulators are an alternative solution to pumps as they do not require energy in flight. This means power generated does not have to be diverted to an accumulator, boosting overall efficiency. Additionally, accumulators do not have pressure oscillations or cavitation risks typically associated with pump-driven systems. Further, they are lightweight systems with lower points of failure than traditional pumps. This makes them an interesting candidate for use in hypersonic flight. However, prior to flight data, accumulator-based systems should be tested statically on the ground to determine its feasibility. In this study, a piston accumulator is used in a plumbing system as a form of fluid battery that delivers fuel to injectors. The spray pattern and droplet kinematic characteristics from the injector under static conditions is measured optically using Mie Scattering and Shadowgraph techniques. This will help demonstrate injector performance compared to other plumbing-based systems in the future. Observing the drag induced on the droplets under static conditions will help understand mixing performance in future flight applications, as maintaining a stable equivalence ratio is critical for successful sustainment of ODW Engines.

The plumbing system is powered by a piston accumulator. Kerosene is delivered to the injectors to help simulate real world flight conditions. 0.007” and 0.022” circular injectors are used to also help simulate the typical setup of flight conditions. Accumulator pressures of 500, 750, 1000, and 1250 psi are used to monitor spray pattern formations. Special observation is taken of the line pressures during operation. Combining qualitative characteristics from Shadowgraph in imaging and quantitative spray size and spray angle from Mie Scattering help to determine feasibility of the concept. Study lays the groundwork for using accumulators in flight conditions to save on weight and improve performance.

Completion Date

2025

Semester

Fall

Committee Chair

Kareem Ahmed

Degree

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

College

College of Engineering and Computer Science

Department

Mechanical and Aerospace Engineering

Format

PDF

Identifier

DP0029827

Document Type

Thesis

Campus Location

Orlando (Main) Campus

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