Keywords
Ammonia combustion hydrogen chemiluminescence ignition
Subject Categories
Aerospace Engineering | Heat Transfer, Combustion | Mechanical Engineering
Abstract
With energy security and decarbonization concerns, ammonia has become an increasingly viable solution to both. Ammonia has been studied previously and due to its low reactivity and fuel bound nitrogen, it has resulted in low flame stability and unacceptable NOx emissions. Combustion methods have been developed to help alleviate these concerns. Cracking the ammonia molecule into hydrogen and nitrogen vastly improves the reactivity of the fuel before combustion. There is limited research in the use of ammonia as aviation fuel. This research focuses on the development of an ammonia gas turbine testing facility that utilizes a J85 turbojet engine, along with a fuel injection test platform to optimize the fuel delivery system. Ammonia vapor was chosen because of the phase change when cracking the ammonia. The injection test platform utilizes a diffusion swirl burner and will help identify more ideal injection geometries and fuel compositions or treatments before implementation on the turbojet engine. Design considerations for both test sites are examined. Initial results from the fuel injector testing platform including the rich flame stabilization and flame structures, blowout conditions and NH2 chemiluminescence. These initial findings and future combustor modifications for the J85 are discussed.
Completion Date
2026
Semester
Summer
Committee Chair
Subith Vasu
Degree
Doctor of Philosophy (Ph.D.)
College
College of Engineering and Computer Science
Department
mechicanal and aerospace engineering
Format
Document Type
Dissertation
Release Date
8-15-2027
STARS Citation
Loving, Christopher T., "Design And Development Of An Ammonia Gas Turbine Test Facility And Stability Limits Of Rich Cracked Ammonia Flames With Nh2* Chemiluminescence" (2026). Graduate Studies Theses and Dissertations 2026. 301.
https://stars.library.ucf.edu/gradstudies_etd_2026/301
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