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-rw-r--r--background.tex11
-rw-r--r--dissertation_main.aux65
-rw-r--r--dissertation_main.bbl36
-rw-r--r--dissertation_main.blg67
-rw-r--r--dissertation_main.fdb_latexmk101
-rw-r--r--dissertation_main.fls202
-rw-r--r--dissertation_main.lof7
-rw-r--r--dissertation_main.log564
-rw-r--r--dissertation_main.pdfbin2905539 -> 3292105 bytes
-rw-r--r--dissertation_main.synctex.gzbin0 -> 60135 bytes
-rw-r--r--dissertation_main.toc36
-rw-r--r--img/faaturbofan.pngbin0 -> 490809 bytes
-rw-r--r--references.bib7
13 files changed, 705 insertions, 391 deletions
diff --git a/background.tex b/background.tex
index dbba796..8eb4cbf 100644
--- a/background.tex
+++ b/background.tex
@@ -24,9 +24,16 @@ The combustor, as illustrated in figure \ref{EoPturbojet} between station number
The turbine section of the engine, denoted by station numbers 4 through 5, is responsible for taking the energy generated in the combustion chamber and turning it into shaft horsepower to drive the compressor stages and external loads. Almost 75 percent of the energy generated from the combustion process is required to drive the compressor alone.\cite{EoPGTR2}The axial-flow turbine is similar to the axial compressor, and is likewise comprised of a series of stages of rotors and stators. However, the turbine has the opposite effect of the compressor: it turns the energy contained within flow into shaft rotation. The stage quantity of the turbine section of a given turbine engine is typically lower than that of its compressor, as the flow is expanding rather than compressing. Axial turbines are either impulse design, which maintain flow velocity across their rotor and decrease pressure across their stator, whereas reaction stages increase pressure across their rotor blades and direct flow within their stator. Most turbines use a combination of these two stage designs, and must be dual or split commensurately with the design of the compressor.
\par
The final stage of the turbine engine, the exhaust nozzle, denoted by station numbers 5 through 9, is responsible for increasing the velocity of the exhaust gas before discharge such that ample thrust can be generated by the engine. Ideally, the exit pressure of the flow leaving the nozzle should equal ambient pressure, otherwise the engine will operate less efficiently than it is capable. Nozzles are typically either convergent, or convergent-divergent, meaning a convergent duct followed by a divergent duct. Simple convergent ducts are used in the case where the ratio of turbine exit pressure to nozzle exit pressure is less than 2. The convergent-divergent duct is employed in instances where this nozzle pressure ratio is in excess of 2. Such ducts incorporate more sophisticated aerodynamic features and variable geometry in certain applications.\cite{EoPGTR2}
+\par
+Gas turbine engines fall into four categories: turbofan, turboprop, and turboshaft, and turbojet. Turbojets make use of a propelling nozzle to create thrust by allowing the heated exhaust created by a gas turbine to expand, without extracting rotational power from the engine. \cite{nasa_turbojet}
+Turbofans make use of a front mounted fan to extract as much as 80 percent of thrust from the engine, significantly more than their turbojet counterparts. The inlets of turbofans differ from other topologies by virtue of their inlet design, as can be visualized in figure \ref{faaturbofan}.
+The air driven by the fan will generally bypass the core, the amount of which contributes to the engine's bypass ratio. This ratio is simply the amount of flow through the engine bypass ducts over the flow through its core. The turboprop engine, that which is employed in this paper, drives a propeller through a reduction gearbox.
-Gas turbine engines fall into four categories: turbofan, turboprop, and turboshaft, and turbojet. Turbojets make use of a propelling nozzle to create thrust by allowing the heated exhaust created by a gas turbine to expand. \cite{nasa_turbojet}
-
+\begin{figure}[h]
+ \centering
+ \includegraphics[width=\textwidth]{img/faaturbofan.png}
+ \caption{\label{faaturbofan}Turbofan Engine Cross Section}
+\end{figure}
\begin{figure}[h]
\centering
\includegraphics[width=\textwidth]{img/tp100cutaway.png}
diff --git a/dissertation_main.aux b/dissertation_main.aux
index fdcf281..4f269c6 100644
--- a/dissertation_main.aux
+++ b/dissertation_main.aux
@@ -16,46 +16,49 @@
\citation{EoPGTR2}
\citation{EoPGTR2}
\citation{nasa_turbojet}
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\citation{*}
\bibstyle{osustyle.bst}
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\bibdata{references.bib}
\bibcite{tp100technical}{1}
\bibcite{doi:10.2514/6.2018-4984}{2}
\bibcite{TurboelectricAS}{3}
-\bibcite{nasa_prop_overview}{4}
-\bibcite{CessnaASME}{5}
-\bibcite{EoPGTR2}{6}
-\bibcite{MelvinThesis}{7}
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-\bibcite{hybrid_trends}{9}
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+\bibcite{faa_engines}{4}
+\bibcite{nasa_prop_overview}{5}
+\bibcite{CessnaASME}{6}
+\bibcite{EoPGTR2}{7}
+\bibcite{MelvinThesis}{8}
+\bibcite{nasa_turbojet}{9}
+\bibcite{hybrid_trends}{10}
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diff --git a/dissertation_main.bbl b/dissertation_main.bbl
index 8cdfd83..8d78e22 100644
--- a/dissertation_main.bbl
+++ b/dissertation_main.bbl
@@ -5,49 +5,37 @@
\href{http://www.ams.org/mathscinet-getitem?mr=#1}{#2}
}
\providecommand{\href}[2]{#2}
-\begin{thebibliography}{1}
+\begin{thebibliography}{10}
\interlinepenalty=10000
\bibitem{tp100technical}
-PBS Aerospace, \emph{Basic technical information turboprop engine tp100}, April
- 2015.
+PBS Aerospace, \emph{Basic technical information turboprop engine tp100}, April 2015.
\bibitem{doi:10.2514/6.2018-4984}
-Cheryl~L. Bowman, Ty~V. Marien, and James~L. Felder, \emph{Turbo- and
- hybrid-electrified aircraft propulsion for commercial transport}, 2018.
+Cheryl~L. Bowman, Ty~V. Marien, and James~L. Felder, \emph{Turbo- and hybrid-electrified aircraft propulsion for commercial transport}, 2018.
\bibitem{TurboelectricAS}
-Johnathan Burgess, Timothy Runnels, Joshua Johnsen, Joshua Drake, and Kurt
- Rouser, \emph{Experimental comparison of direct and active throttle control
- of a 7 kw turboelectric power system for unmanned aircraft}, Applied Sciences
- \textbf{11} (2021), no.~22.
+Johnathan Burgess, Timothy Runnels, Joshua Johnsen, Joshua Drake, and Kurt Rouser, \emph{Experimental comparison of direct and active throttle control of a 7 kw turboelectric power system for unmanned aircraft}, Applied Sciences \textbf{11} (2021), no.~22.
+
+\bibitem{faa_engines}
+FAA, \emph{Aircraft engines}, Federal Aviation Administration, 2024.
\bibitem{nasa_prop_overview}
-Ralph Jansen, \emph{Overview of nasa electrified aircraft propulsion
- activities}, NASA Glenn Research Center, 2017.
+Ralph Jansen, \emph{Overview of nasa electrified aircraft propulsion activities}, NASA Glenn Research Center, 2017.
\bibitem{CessnaASME}
-Joshua Johnsen, Joshua Melvin, Joshua Drake, Muwanika Jdiobe, and Kurt Rouser,
- \emph{Experimental evaluation of an electric powertrain designed for a 180-kw
- turboelectric aircraft ground test rig}, Journal of Engineering for Gas
- Turbines and Power \textbf{146} (2024).
+Joshua Johnsen, Joshua Melvin, Joshua Drake, Muwanika Jdiobe, and Kurt Rouser, \emph{Experimental evaluation of an electric powertrain designed for a 180-kw turboelectric aircraft ground test rig}, Journal of Engineering for Gas Turbines and Power \textbf{146} (2024).
\bibitem{EoPGTR2}
-Jack Mattingly and Hans von Obain, \emph{Elements of propulsion: Gas turbines
- and rockets 2nd edition}, AIAA, 2016.
+Jack Mattingly and Hans von Obain, \emph{Elements of propulsion: Gas turbines and rockets 2nd edition}, AIAA, 2016.
\bibitem{MelvinThesis}
-Joshua Melvin, \emph{Integration and evaluation of a 180-kw turboprop engine
- with a turboelectric ground test rig}, Master's thesis, OKLAHOMA STATE
- UNIVERSITY, May 2021.
+Joshua Melvin, \emph{Integration and evaluation of a 180-kw turboprop engine with a turboelectric ground test rig}, Master's thesis, OKLAHOMA STATE UNIVERSITY, May 2021.
\bibitem{nasa_turbojet}
NASA, \emph{Turbojet engine}, NASA Glenn Research Center, 2017.
\bibitem{hybrid_trends}
-Manuel Rendón, Carlos Sánchez, Josselyn Gallo~Muñoz, and Alexandre Anzai,
- \emph{Aircraft hybrid-electric propulsion: Development trends, challenges and
- opportunities (https://rdcu.be/cmg4u)}, Sba Controle \& Automação Sociedade
- Brasileira de Automatica (2021).
+Manuel Rendón, Carlos Sánchez, Josselyn Gallo~Muñoz, and Alexandre Anzai, \emph{Aircraft hybrid-electric propulsion: Development trends, challenges and opportunities (https://rdcu.be/cmg4u)}, Sba Controle \& Automação Sociedade Brasileira de Automatica (2021).
\end{thebibliography}
diff --git a/dissertation_main.blg b/dissertation_main.blg
index 0d2b2e1..1e6bceb 100644
--- a/dissertation_main.blg
+++ b/dissertation_main.blg
@@ -1,4 +1,4 @@
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+This is BibTeX, Version 0.99d (TeX Live 2024)
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Warning--missing chapter and pages in doi:10.2514/6.2018-4984
Warning--missing publisher in doi:10.2514/6.2018-4984
Warning--missing pages in TurboelectricAS
+Warning--missing booktitle in faa_engines
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diff --git a/dissertation_main.pdf b/dissertation_main.pdf
index 8549122..b478169 100644
--- a/dissertation_main.pdf
+++ b/dissertation_main.pdf
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diff --git a/dissertation_main.synctex.gz b/dissertation_main.synctex.gz
new file mode 100644
index 0000000..6e03f48
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diff --git a/dissertation_main.toc b/dissertation_main.toc
index e7650fa..648e28d 100644
--- a/dissertation_main.toc
+++ b/dissertation_main.toc
@@ -2,21 +2,21 @@
\contentsline {chapter}{\numberline {I}INTRODUCTION}{1}{}%
\contentsline {chapter}{\numberline {II}BACKGROUND}{2}{}%
\contentsline {section}{\numberline {2.1}Turbine Engines}{2}{}%
-\contentsline {section}{\numberline {2.2}Generator Theory}{5}{}%
-\contentsline {section}{\numberline {2.3}Battery Theory}{5}{}%
-\contentsline {section}{\numberline {2.4}Turboelectric Theory}{5}{}%
-\contentsline {section}{\numberline {2.5}Previous Work}{5}{}%
-\contentsline {chapter}{\numberline {III}METHODOLOGY}{7}{}%
-\contentsline {section}{\numberline {3.1}General Aircraft System}{7}{}%
-\contentsline {section}{\numberline {3.2}Configuration One}{7}{}%
-\contentsline {subsection}{\numberline {3.2.1}Data Acquisition}{7}{}%
-\contentsline {subsection}{\numberline {3.2.2}Experimental Procedure}{7}{}%
-\contentsline {section}{\numberline {3.3}Configuration Two}{7}{}%
-\contentsline {subsection}{\numberline {3.3.1}Data Acquisition}{7}{}%
-\contentsline {subsection}{\numberline {3.3.2}Experimental Procedure}{7}{}%
-\contentsline {chapter}{\numberline {IV}RESULTS}{8}{}%
-\contentsline {section}{\numberline {4.1}Configuration One}{8}{}%
-\contentsline {section}{\numberline {4.2}Configuration Two}{8}{}%
-\contentsline {chapter}{\numberline {V}CONCLUSION, RECOMMENDATIONS, AND FUTURE WORK}{9}{}%
-\contentsline {chapter}{REFERENCES}{10}{}%
-\contentsline {chapter}{APPENDICES}{11}{}%
+\contentsline {section}{\numberline {2.2}Generator Theory}{6}{}%
+\contentsline {section}{\numberline {2.3}Battery Theory}{6}{}%
+\contentsline {section}{\numberline {2.4}Turboelectric Theory}{6}{}%
+\contentsline {section}{\numberline {2.5}Previous Work}{6}{}%
+\contentsline {chapter}{\numberline {III}METHODOLOGY}{8}{}%
+\contentsline {section}{\numberline {3.1}General Aircraft System}{8}{}%
+\contentsline {section}{\numberline {3.2}Configuration One}{8}{}%
+\contentsline {subsection}{\numberline {3.2.1}Data Acquisition}{8}{}%
+\contentsline {subsection}{\numberline {3.2.2}Experimental Procedure}{8}{}%
+\contentsline {section}{\numberline {3.3}Configuration Two}{8}{}%
+\contentsline {subsection}{\numberline {3.3.1}Data Acquisition}{8}{}%
+\contentsline {subsection}{\numberline {3.3.2}Experimental Procedure}{8}{}%
+\contentsline {chapter}{\numberline {IV}RESULTS}{9}{}%
+\contentsline {section}{\numberline {4.1}Configuration One}{9}{}%
+\contentsline {section}{\numberline {4.2}Configuration Two}{9}{}%
+\contentsline {chapter}{\numberline {V}CONCLUSION, RECOMMENDATIONS, AND FUTURE WORK}{10}{}%
+\contentsline {chapter}{REFERENCES}{11}{}%
+\contentsline {chapter}{APPENDICES}{13}{}%
diff --git a/img/faaturbofan.png b/img/faaturbofan.png
new file mode 100644
index 0000000..7020868
--- /dev/null
+++ b/img/faaturbofan.png
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diff --git a/references.bib b/references.bib
index 19c9c85..b13eba2 100644
--- a/references.bib
+++ b/references.bib
@@ -86,3 +86,10 @@ doi = {10.1007/s40313-021-00740-x}
author = {Mattingly, Jack and von Obain, Hans},
publisher = {AIAA},
}
+@inproceedings{faa_engines,
+ author = {FAA},
+ year = {2024},
+ URL = {https://www.faa.gov/sites/faa.gov/files/03_amtp_ch1.pdf},
+ organization = {Federal Aviation Administration},
+ title = {Aircraft Engines},
+}