Abstract

The purpose of this research was to design and modify a combustor to study the combustion of aviation fuels and air at elevated pressures within the experimental facility. The fuels of interest are to be heated, atomized, and injected into the facility, where they are ignited in the recirculation zone of a bluff body flame holder. A converging nozzle is attached at the exit of the facility. The ignition of the fuel/air mixture chokes the flow at the nozzle exit, creating interior pressures up to 5atm. This increased temperature and pressure better represent conditions within combustors used in typical jet engines or gas turbines. A series of tests was completed, varying the pressure and equivalence ratio by adjusting the mass flow rates of the air and fuel into the facility. Several fuels including JP-8 and JP-5 have been successfully ignited for this experiment over the full range of desired pressures.

Thesis Completion

2020

Semester

Spring

Thesis Chair

Ahmed, Kareem

Degree

Bachelor Science in Aerospace Engineering (B.S.A.E.)

College

College of Engineering and Computer Science

Department

Mechanical and Aerospace Engineering

Degree Program

Aerospace Engineering

Language

English

Access Status

Campus Access

Length of Campus-only Access

5 years

Release Date

5-1-2025

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