From dd6ab15fa7b08a3aea6ab613ad0fa046d7b27c82 Mon Sep 17 00:00:00 2001
From: Joshua Drake <joshua.ellis.drake@gmail.com>
Date: Fri, 25 Oct 2024 11:55:24 -0500
Subject: Restarted repo because it was somehow borked.

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+\begingroup
+\clearpage% Manually insert \clearpage
+\let\clearpage\relax% Remove \clearpage functionality
+\vspace*{-16pt}% Insert needed vertical retraction
+\chapter[BACKGROUND]{BACKGROUND}
+\endgroup
+
+
+%\section{Advanced Air Mobility}
+\section{Turbine Engines}
+A cursory understanding of turbine engines is necessarry to contextualize this work, as their improved power to weight ratio and performance at altitude when compared to piston engines make them an ideal choice for use in hybrid electric aircraft. The following is a description of how a general jet engine with a single inlet and exhuast functions. This description corresponds to the station numbering found in \ref{EoPturbojet} and is applicable to the subcategories of turbine engines discuessed later.
+\begin{figure}[h]
+	\centering
+	\includegraphics[width=\textwidth]{img/EoPturbojet.png}
+	\caption{\label{EoPturbojet}Ideal Turbojet with station numbering}
+\end{figure}
+\par
+The Inlet is the first section of the gas turbine engine, denoted by station numbers 0-2, and its operation and design are described in terms of the efficiency of the compression process, the external drag of the inlet, and the mass flow into the inlet. \cite{EoPGTR2} Inlet design is most heavily influenced by whether the air entering it is subsonic or supersonic. Subsonic inlet design is simple, and typically involves selecting an operating velocity at which air compression is most efficient at the expense of performance at other velocities. Supersonic inlets must take the shockwaves endemic to supersonic flow into account for optimal performace. This is accomplished by adjusting inlet geometry to reduce flow velocity while adding as little weight to the system as possible. Variable inlet geometry will allow for increased efficiency accross many velocities.
+\par
+Compressors, denoted by station numbers 2-3, increase the pressure of the flow obtained by the inlet such that the combustion and exhaust processes can be conducted more efficiently. Increasing the pressure of an initial volume of air results in the reduction of its volume, allowing for the combustion of the air/fuel mixture to occur within a smaller volume than it would otherwise. Turbine engines most commonly employ centrifugal or axial compressors. Figure \ref{EoPturbojet} appropriately depicts an axial compressor in the makeup of the common turbine engine by virtue of their superiority. However, centrifugal compressors find use in smaller, less expensive engines due to their simple design. Centrifugal compressors are comprised of an impeller, which serves to increase flow velocity through rotation; a diffuser, which decreases the velocity of the flow thereby increasing its pressure; and a manifold which directs the compressed air into the combustor. Axial compressors are made of a series of stator vanes and rotor blades that are concentric to the axis of rotation. Each set of these stators and rotors is referred to as a stage. ''The flow path in an axial compressor decreases in cross-sectional area in the direction of flow." \cite{EoPturbojet} Each stage of the compressor results in an increase in air density. Thus, multiple stages are used in the design of high compression ratio turbine engines. Many turbines, including that which is depicted in figure \ref{EoPturbojet}, are equiped with dual axial compressors. Dual axial compressors allow for a more uniform loading of compressor stages, as well as for improved flexibility in the balancing between the initial and later stages.
+
+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/tp100cutaway.png}
+	\caption{\label{tp100cutaway}PBS TP100 Cutaway}
+\end{figure}
+\section{Generator Theory}
+\section{Battery Theory}
+\section{Turboelectric Theory}
+\begin{figure}[h]
+	\centering
+	\includegraphics[width=\textwidth]{img/turbosystems.png}
+	\caption{\label{turboarch}Turboelectric Architectures}
+\end{figure}
+\begin{figure}[h]
+	\centering
+	\includegraphics[width=.6\textwidth]{img/turboseriesparallel.png}
+	\caption{\label{turboseriesparallel}Parallel Turboelectric Design}
+\end{figure}
+\section{Previous Work}
+
+
+
+% \begin{figure}[!h]
+%  \centering
+%  \includegraphics[width=3in]{osu}
+%  \caption{\label{fig:2-1}Here is a figure.}
+% \end{figure}
+
+% Below is another table.
+
+% \begin{table}[!h]
+%   \centering
+%     \begin{tabular}{| l c r |}
+%     \hline
+%     1 & 2 & 3 \\
+%     4 & 5 & 6 \\
+%     7 & 8 & 9 \\
+%     \hline
+%     \end{tabular}
+%   \caption{A third table}
+% \end{table}
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