Abstract

To better understand atomization in a commercial aviation gas turbine combustion environment, we present experimental measurements of the internal fuel flow of a simplex atomizer. Particle Image Velocimetry was used to measure velocity in a plane axial to the flow internal to a standard aerospace fuel atomizer. The geometry studied used a 0.74mm orifice and is typical of a commercial aircraft engine. MIL PRF-7024 was employed as the working fluid and two mass flow rates were studied. Particle Image Velocimetry data on a small simplex atomizer was collected and methods are detailed including the machining of the optically clear spin chamber, which properly replicates atomizer geometry, and challenges associated with seeding MIL PRF-7024. The method of data collection is discussed for future application to other geometries. Flow fields showed the majority of mass flowrate around the air core. In addition to increased understanding of this complex flow, this data may be used to support and validate computational analyses of gas turbine fuel injection.

Library of Congress Subject Headings

Atomization; Fluid dynamics; Particle image velocimetry; Airplanes--Motors

Publication Date

5-2016

Document Type

Thesis

Student Type

Graduate

Degree Name

Mechanical Engineering (MS)

Department, Program, or Center

Mechanical Engineering (KGCOE)

Advisor

Steven W. Day

Advisor/Committee Member

Jason Kolodziej

Advisor/Committee Member

Michael Schertzer

Comments

Physical copy available from RIT's Wallace Library at TC173 .T45 2016

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AThistleSupplement.zip (1631 kB)

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RIT – Main Campus

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