Aircraft propulsion system with turbine engine and exhaust condenser

An aircraft propulsion system is provided that includes a turbine engine and an exhaust gas condenser. The exhaust gas condenser includes a housing, a nozzle, a plurality of air scoops, and a plurality of exhaust gas conduit banks. The housing has an interior cavity, a bottom side, and first and second lateral sides. The exhaust gas conduit banks are disposed in the interior cavity of the housing and are configured to form an interior bypass air chamber. Each exhaust gas conduit bank includes alternating exhaust gas conduits and bypass air passages. The exhaust gas conduits extend axially between the forward and aft ends, and are configured to conduct exhaust gases to the nozzle. The bypass air passages are configured to receive bypass air from the air scoops and direct the bypass air between the exhaust gas conduits and into the interior bypass air chamber.

BACKGROUND OF THE INVENTION

1. Technical Field

This disclosure relates to an aircraft in general, and to a turbine engine system for an aircraft in particular.

2. Background Information

There is interest in alternative fuels for gas turbine engines. There is interest, for example, in fueling a gas turbine engine with a non-hydrocarbon fuel (e.g., hydrogen) rather than a traditional hydrocarbon fuel such as kerosine to reduce greenhouse emissions. Various systems and methods are known in the art for fueling a gas turbine engine with hydrogen. While these known systems and methods have various advantages, there is still room in the art for improvement.

SUMMARY

According to an aspect of the present disclosure, an aircraft propulsion system is provided that includes a turbine engine and an exhaust gas condenser. The turbine engine is configured to exhaust gases during combustion of a fuel, wherein the exhaust gases include water vapor. The exhaust gas condenser extends lengthwise along a central axis and includes a housing, a nozzle, a plurality of air scoops, and a plurality of exhaust gas conduit banks. The housing extends lengthwise between a forward end and an aft end. The housing has an interior cavity, a top side, a bottom side opposite the top side, a first lateral side, and a second lateral side opposite the first lateral side. The first and second lateral sides extend between the top side and the bottom side. The nozzle is in communication with the housing and is disposed at the aft end. The air scoops are attached to the housing. The exhaust gas conduit banks are disposed in the interior cavity of the housing. The exhaust gas conduit banks are configured to form an interior bypass air chamber within the housing interior cavity. Each exhaust gas conduit bank includes a plurality of exhaust gas conduits and a plurality of bypass air passages. The exhaust gas conduits and the bypass air passages are disposed relative to one another in an alternating configuration. The exhaust gas conduits extend axially between the forward end and the aft end, and are open at the forward end to receive the exhaust gases from the turbine engine and are open at the nozzle. The bypass air passages are configured to receive bypass air from the plurality of air scoops and direct the bypass air between the exhaust gas conduits and into the interior bypass air chamber. The interior bypass air chamber is in fluid communication with the nozzle.

In any of the aspects or embodiments described above and herein, the exhaust gas condenser may be configured to keep the exhaust gases separate from the bypass air.

In any of the aspects or embodiments described above and herein, the nozzle may include an exhaust gas portion and a bypass air portion, and the exhaust gas conduits may be in communication with the exhaust gas portion of the nozzle and the exhaust gas nozzle portion may be configured to maintain the exhaust gases separate from the bypass air, and the interior bypass air chamber may be in communication with the bypass air portion of the nozzle and the bypass air portion may be configured to maintain the bypass air separate from the exhaust gases.

In any of the aspects or embodiments described above and herein, the plurality of exhaust gas conduit banks may include a first lateral side bank of exhaust gas conduits disposed adjacent to the first lateral side of the housing, a second lateral side bank of exhaust gas conduits disposed adjacent to the second lateral side of the housing, and a bottom side bank of exhaust gas conduits disposed adjacent to the bottom side of the housing, and the plurality of air scoops may include a first lateral side air scoop attached to the first lateral side of the housing, a second lateral side air scoop attached to the second lateral side of the housing, and a bottom side air scoop attached to the bottom side of the housing.

In any of the aspects or embodiments described above and herein, the exhaust gas conduits within the first lateral side bank of exhaust gas conduits and the second lateral side bank of exhaust gas conduits may be lateral side (LS) exhaust gas conduits and the bypass air passages disposed alternating with the LS exhaust gas conduits may be LS bypass air passages, and the LS exhaust gas conduits may extend laterally, and the LS bypass air passages of the first lateral side bank of exhaust gas conduits may be configured to provide fluid communication between the first lateral side air scoop and the interior bypass air chamber, and the LS bypass air passages of the second lateral side bank of exhaust gas conduits may be configured to provide fluid communication between the second lateral side air scoop and the interior bypass air chamber.

In any of the aspects or embodiments described above and herein, the exhaust gas conduits within the bottom side bank of exhaust gas conduits may be bottom side (BS) exhaust gas conduits and the bypass air passages disposed alternating with the BS exhaust gas conduits may be BS bypass air passages, and the BS exhaust gas conduits may extend heightwise, and the BS bypass air passages of the bottom side bank of exhaust gas conduits may be configured to provide fluid communication between the bottom side air scoop and the interior bypass air chamber.

In any of the aspects or embodiments described above and herein, the exhaust gas condenser may further include a first collection channel and a second collection channel. The first collection channel may be disposed at a first interface between the first lateral side bank of exhaust gas conduits and the bottom side bank of exhaust gas conduits, wherein the first collection channel may be configured to receive bypass air from at least some of the LS bypass air passages within the first lateral side bank of exhaust gas conduits and direct the bypass air to the interior bypass air chamber. The second collection channel may be disposed at a second interface between the second lateral side bank of exhaust gas conduits and the bottom side bank of exhaust gas conduits, and the second collection channel may be configured to receive bypass air from at least some of the LS bypass air passages within the second lateral side bank of exhaust gas conduits and direct the bypass air to the interior bypass air chamber.

In any of the aspects or embodiments described above and herein, a flow area of the interior bypass chamber may increase in the axial direction from the forward end to the aft end.

In any of the aspects or embodiments described above and herein, the housing has a length, a width, and a height, and the first and second lateral side air scoops may each have an opening disposed at the forward end, and each of the first and second lateral side air scoops may taper inwardly in a direction from the forward end to the aft end.

In any of the aspects or embodiments described above and herein, the first and lateral side air scoop and the second lateral side air scoop extend the length of the housing.

In any of the aspects or embodiments described above and herein, the first and second lateral side air scoops may extend the height of the housing.

In any of the aspects or embodiments described above and herein, the housing has a length, a width, and a height, and the bottom side air scoop may have an opening disposed at the forward end, and the bottom side air scoop may taper inwardly in a direction from the forward end to the aft end.

In any of the aspects or embodiments described above and herein, the bottom side air scoop may extend the length of the housing.

In any of the aspects or embodiments described above and herein, the bottom side air scoop may extend the width of the housing.

In any of the aspects or embodiments described above and herein, the system may include a water recovery system in communication with the exhaust gas condenser, the water recovery system configured to recover liquid water from the exhaust gas condenser.

According to an aspect of the present disclosure, an exhaust gas condenser for an aircraft turbine engine is provided that extends lengthwise along a central axis. The exhaust gas condenser includes a housing, a nozzle, a plurality of air scoops, and a plurality of exhaust gas conduit banks. The housing is configured to receive exhaust gases from an aircraft turbine engine. The housing extends lengthwise between a forward end and an aft end, and has an interior cavity, a top side, a bottom side opposite the top side, a first lateral side, and a second lateral side opposite the first lateral side. The first and second lateral sides extend between the top and bottom sides. The nozzle is in communication with the housing and disposed at the aft end. The plurality of air scoops are attached to the housing. The exhaust gas conduit banks are disposed in the interior cavity of the housing. The exhaust gas conduit banks are configured to form an interior bypass air chamber within the housing interior cavity. Each exhaust gas conduit bank includes a plurality of exhaust gas conduits and a plurality of bypass air passages. The exhaust gas conduits and the bypass air passages are disposed relative to one another in an alternating configuration. The exhaust gas conduits extend axially between the forward end and the aft end, and are open at the forward end to receive the exhaust gases from the turbine engine and are open at the nozzle. The bypass air passages are configured to receive bypass air from the plurality of air scoops and direct the bypass air between the exhaust gas conduits and into the interior bypass air chamber. The interior bypass air chamber is in fluid communication with the nozzle.

The foregoing features and elements may be combined in various combinations without exclusivity, unless expressly indicated otherwise. For example, aspects and/or embodiments of the present disclosure may include any one or more of the individual features or elements disclosed above and/or below alone or in any combination thereof. These features and elements as well as the operation thereof will become more apparent in light of the following description and the accompanying drawings. It should be understood, however, the following description and drawings are intended to be exemplary in nature and non-limiting.

DETAILED DESCRIPTION

FIG.1diagrammatically illustrates a propulsion system20for an aircraft. The aircraft may be an airplane, a helicopter, a drone (e.g., an unmanned aerial vehicle (UAV)) or any other manned or unmanned aerial vehicle or system. The propulsion system20shown inFIG.1includes a propulsor rotor22, a turbine engine24, a fuel source26, and an exhaust gas condenser28. Non-limiting examples of a propulsor rotor22include a propeller rotor for a turboprop propulsion system, a rotorcraft rotor (e.g., a main helicopter rotor) for a turboshaft propulsion system, a propfan rotor for a propfan propulsion system, a pusher fan rotor for a pusher fan propulsion system, a fan for a turbofan propulsion system, or the like. Unless otherwise stated herein, the present disclosure is not limited to any particular turbine engine24configuration, or any propulsor rotor22configuration.

The turbine engine24extends axially along an axis30between an upstream, forward end and a downstream, aft end. The turbine engine24includes a compressor section32, a combustor section34, and a turbine section36. A core flow path38extends sequentially through the compressor section32, the combustor section34, and the turbine section36. Air enters the turbine engine24through an airflow inlet40upstream of the compressor section32, passes through the core flow path38, and exits the turbine engine24. Thereafter, the core gas enters the exhaust gas condenser28. As indicated above, the present disclosure is not limited to any particular turbine engine24configuration and the aforesaid description of the core flow path38and engine component positioning is for illustration purposes and is not intended to be limiting.

Embodiments of the present disclosure propulsion system20may include a turbine engine24configured to combust non-hydrocarbon fuels (e.g., hydrogen or “H2”), or hydrocarbon fuels (e.g., aviation fuel), or some mixture thereof. For example, the turbine engine24within a present disclosure system embodiment may be configured to combust a fuel that is 100% non-hydrocarbon (e.g., 100% H2), or a fuel that is 100% hydrocarbon (e.g., 100% aviation fuel), or a mixture thereof (e.g., a mixture of H2and aviation fuel). The present disclosure is not limited to any combusting any particular fuel. In those embodiments wherein the present disclosure system20combusts hydrogen, the fuel source26may be configured to store the hydrogen in liquid form and the present disclosure system20may be configured to process the hydrogen to a form (e.g., phase change to a gaseous phase) acceptable for combustion.

The combustion products generated by the combustion of the fuel-air mixture within the combustor section34include water (H2O) vapor. The water vapor may be a product of the combustion of a non-hydrocarbon fuel, or the product of water injected into the engine that is vaporized during operation, or any combination thereof. As will be detailed herein, the exhaust gas condenser28portion of the present disclosure system20is configured to recover at least some of the water vapor produced by the combustion of the fuel-air mixture within the combustor section34.

FIG.2diagrammatically illustrates a present disclosure aircraft propulsion system20with a turbine engine24enclosed within a housing that is disposed forward of an aircraft exhaust gas condenser28.FIG.3is a diagrammatic perspective view representation of a present disclosure exhaust gas condenser28.FIG.4is a diagrammatic top view representation of a present disclosure exhaust gas condenser28.FIG.5is a diagrammatic end view perspective representation of a present disclosure exhaust gas condenser28, wherein the view is in the direction forward to aft.

Referring toFIGS.3-5, the exhaust gas condenser28extends along a central axis30(e.g., coincident with the engine axis30) between an exhaust gas inlet42and a nozzle44. The exhaust gas condenser28includes a housing46, an interior cavity48, a first lateral side air scoop50, a second lateral side air scoop52, a bottom side air scoop54, a first lateral side bank of exhaust gas conduits56, a second lateral side bank of exhaust gas conduits58, and a bottom side bank of exhaust gas conduits60. The exhaust gas inlet42is disposed at a forward end62of the housing46and the nozzle44is disposed at an aft end64of the housing46.

In the embodiment shown inFIGS.3-5, the exhaust gas condenser housing46has a generally rectangular configuration having a width (X-axis), a height (Y-axis), and a length (Z-axis). The cross-section geometry of the condenser housing46(e.g., in the X-Y plane) is generally square. In this configuration, the condenser housing46may be described as having a bottom side66and a top side68opposite one another, and a first lateral side70and a second lateral side72opposite one another. The interior cavity48is defined by the bottom, top, first lateral, and second lateral sides66,68,70,72. The housing46includes a top side panel that extends lengthwise between the forward and aft ends62,64, and widthwise between the first and second lateral sides70,72. In some embodiments, the condenser housing46may include lateral side panels that allow bypass air passage therethrough (e.g., via one or more apertures) and that provide structural support. In similar fashion, the condenser housing46may include a bottom side panel that allows bypass air passage therethrough (e.g., via one or more apertures) and that provides structural support. The condenser housing46does not require lateral side panels or a bottom side panel.

In the embodiment shown inFIGS.3and4, the first and second lateral side air scoops50,52and the bottom side air scoop54each extend lengthwise for substantially the entire length of the condenser housing46.FIGS.3-5show first and second lateral side air scoops50,52and a bottom side air scoop54each having a generally rectangular cross-sectional configuration, defined by a pair of side panels74and an outer panel76. The present disclosure is not limited to air scoops50,52,54with a rectangular configuration; e.g., the air scoops50,52,54may be arcuately shaped. The first and second lateral side air scoops50,52and the bottom side air scoop54each include an opening78disposed at the forward end62of the condenser housing46. The opening78may be defined by a plane that extends between the housing46(e.g., a lateral side70,72of the housing46for a respective lateral side air scoop50,52or the bottom side66of the housing46for the bottom side air scoop54) and the side and outer panel74,76of the respective air scoop50,52,54; e.g., the planes are disposed in the X-Y plane. The present disclosure is not limited to the aforesaid scoop opening78orientation. Each of the first and second lateral side air scoops50,52and the bottom side air scoop54taper inwardly toward the central axis30of the condenser28in the direction from forward to aft. In this manner, the cross-sectional flow area of the scoops50,52,54decrease in the direction from forward to aft. In the embodiment shown inFIGS.3-5, the outer panel76of the respective air scoops50,52,54is shown extending linearly in the direction from forward to aft. Alternatively, the outer panel76of the respective air scoops50,52,54may taper inwardly along an arcuate line. As stated above, in the embodiment shown inFIGS.3and4the first and second lateral side air scoops50,52and the bottom side air scoop54each extend lengthwise for substantially the entire length of the condenser housing46and are shown enclosing the entire respective side of the condenser housing46. The present disclosure is not limited to this embodiment. For example, one or more of the first and second lateral side air scoops50,52and the bottom side air scoop54may extend lengthwise for less than the entire length of the condenser housing46and/or may enclose less that the entire respective side of the condenser housing46.

Each bank of exhaust gas conduits56,58,60is disposed within the interior cavity48of the condenser housing46. The first and second lateral side (LS) banks of exhaust gas conduits56,58include a plurality of planar LS exhaust gas conduits80that extend axially (e.g., along the Z-axis; seeFIGS.6and7) between the forward and aft ends62,64of the housing46, and laterally within the housing46between the housing lateral sides70,72. The LS exhaust gas conduits80are open at the forward end62to receive turbine engine exhaust gas. At the aft end, the LS exhaust gas conduits80are in fluid communication with a manifold86that directs the exhaust gas to an exhaust gas portion44A of the nozzle44. As will be detailed herein, the manifold86is in communication with a water recovery system84.

The LS exhaust gas conduits80are spaced apart from one another such that a passage (e.g., an “LS bypass air passage82” as will be described below) is disposed between each adjacent pair of LS exhaust gas conduits80. The LS exhaust gas conduits80are closed and thereby provide an enclosed passage for exhaust gas axially between the forward and aft ends of the condenser28. As will be detailed herein, the closed LS exhaust gas conduits80keep the exhaust gas separate from (i.e., fluidly isolated from) bypass air traveling through the LS bypass air passages82disposed between adjacent LS exhaust gas conduits80. The bottom side (BS) bank of exhaust gas conduits60includes a plurality of planar BS exhaust gas conduits88that extend axially (e.g., along the Z-axis) between the forward and aft ends62,64of the housing46, and heightwise (along the Y-axis) within the housing46between the housing bottom and top sides66,68. The BS exhaust gas conduits88are spaced apart from one another such that a passage (e.g., a “BS bypass air passage90” as will be described below) is disposed between each adjacent pair of BS exhaust gas conduits88. The BS exhaust gas conduits88are closed and thereby provide an enclosed passage for exhaust gas axially between the forward and aft ends of the condenser46. As will be detailed herein, the closed BS exhaust gas conduits88keep the exhaust gas separate from (i.e., fluidly isolated from) bypass air traveling through the BS bypass air passages90disposed between adjacent BS exhaust gas conduits88.FIG.6is a diagrammatic end view showing the LS exhaust gas passages80, the LS bypass air passages82, the BS exhaust gas passages88, and the BS bypass air passages90disposed relative to one another in alternating fashion.FIG.7is a diagrammatic side view showing the LS exhaust gas passages80and the LS bypass air passages82extending axially, disposed relative to one another.

The first and second lateral side banks of exhaust gas conduits56,58and the bottom side bank of exhaust gas conduits60have tapered configurations that collectively define an interior bypass air chamber92. A first collection channel94is disposed at the interface between the first lateral side (LS) bank of exhaust gas conduits56and the bottom side (BS) bank of exhaust gas conduits60and a second collection channel96is disposed at the interface between the second lateral side (LS) bank of exhaust gas conduits58and the bottom side (BS) bank of exhaust gas conduits60. The first and second collection channels94,96are configured to receive bypass air from respective LS bypass air passages82and BS bypass air passages90and direct that air into the interior bypass air chamber92.FIGS.8-8Bare diagrammatic sections at different axial positions of the condenser46(seeFIG.4) to illustrate the tapered configurations of the first and second lateral side (LS) banks of exhaust gas conduits56,58and the bottom side (BS) bank of exhaust gas conduits60and the corresponding increasingly larger interior bypass air chamber92. It should be noted that the forward end of the condenser46is configured to block turbine engine exhaust gas from entering the interior bypass air chamber92. The increasingly larger interior bypass air chamber92may be described as the axial flow area of the interior bypass air chamber92increasing in the axial direction from forward to aft.FIG.4diagrammatically illustrates the positions where the diagrammatic sections ofFIGS.8-8Bmay be axially positioned. The diagrammatic section ofFIG.8is at an axial position adjacent to the forward end62of the housing46. The diagrammatic section ofFIG.8Ais at an axial position in the middle region of the housing46. The diagrammatic section ofFIG.8Bis at an axial position adjacent to the aft end64of the housing46. The interior bypass air chamber92is in communication with a bypass air portion44B of the nozzle44.FIGS.5-8Bdiagrammatically illustrate the exhaust conduits80of the first and second lateral side banks56,58and exhaust conduits88of the bottom side bank60as extending along straight lines (e.g., straight lines along the orthogonal axes X, Y, and Z). The present disclosure is not limited to these configurations (e.g., portions of the exhaust conduits80,88may extend arcuately and therefore not coincident with respective orthogonal axes) and may be modified according to specific applications.

As stated above, the combustion products generated by the combustion of the fuel-air mixture within the combustor section34of the turbine engine24may include water (H2O) vapor and/or water vapor may be present as a result of water injection. The exhaust gas condenser28is configured to utilize bypass air to cool the exhaust gas to a degree that causes at least some of the water vapor in the exhaust gas to change from a gaseous phase to a liquid phase. The liquid water is subsequently recovered and may be used for a variety of different purposes, including injection into turbine engine24sections including the compressor section32, the combustor section34, and the turbine section36, and/or for use in the aircraft cabin. Various uses for water (in liquid or gaseous form) in a turbine engine24or aircraft are known in the art, and the present disclosure is not limited to any particular one thereof.

During operation of the present disclosure aircraft propulsion system20, the turbine engine24is operated to combust a fuel/air mixture to produce power. The produced exhaust gases exit the turbine section36and are directed into the exhaust gas inlet42of the exhaust gas condenser28. Some amount of the exhaust gas is received within the LS exhaust gas conduits80within the first and second lateral side banks of exhaust gas conduits56,58, and some amount of the exhaust gas is received within the BS exhaust gas conduits88within the bottom side bank of exhaust gas conduits60. The exhaust gases subsequently travel axially through the respective exhaust gas conduits80,88and enter the manifold86disposed at the aft end of the condenser46. While the aircraft is underway, the ambient air is captured by the lateral side air scoops50,52and the bottom side air scoop54and is directed into the condenser28. The temperature of the ambient air is appreciably lower than the temperature of the exhaust gases and is used within the condenser28as a cooling medium. The ambient air entering the air scoops50,52,54(which may be categorized as “ram air” when the aircraft is underway) in an axial direction is directed by the tapered air scoops50,52,54inwardly where it enters the LS bypass air passages82disposed between adjacent LS exhaust gas conduits80, and the BS bypass air passages90disposed between adjacent BS exhaust gas conduits88. In some embodiments, the condenser46may include features (e.g., ribs or the like) to facilitate air direction through the bypass air passages82,90. In some embodiments, the condenser46may include heat transfer features (e.g., pins, fins, or the like) extending into the bypass air passages82,90and/or the exhaust gas conduits80,88to facilitate heat transfer between the bypass air and the exhaust gases. As the bypass air passes through the LS bypass air passages82and BS bypass air passages90, the bypass air cools the LS exhaust gas conduits80and the BS exhaust gas conduits88prior to entering the interior bypass air chamber92. The cooling of the LS exhaust gas conduits82and the BS exhaust gas conduits90, in turn, causes the LS exhaust gas conduits80and the BS exhaust gas conduits90to cool the exhaust gases traveling axially therethrough. The exhaust gases are cooled sufficiently to cause at least some of the water vapor in the exhaust gases to change from a gaseous phase to a liquid phase. After the bypass air has passed through the LS bypass air passages82and BS bypass air passages90and passed through the interior bypass air chamber92, the bypass air enters and exits the bypass air portion44B of the nozzle44. During portions of the aircraft flight, the bypass air exiting the bypass air portion44B of the nozzle44may produce propulsive thrust for the aircraft. The exhaust gases entering the manifold86disposed at the aft end of the condenser46will include some amount of liquid water as a result of the cooling. The manifold86may be in communication with a water recovery system84(e.g., that may include a pump, filters, valves, and the like) that directs the recovered water for use elsewhere as detailed herein.

The present disclosure aircraft propulsion system20described herein having an exhaust gas condenser28with lateral side air scoops50,52and a bottom side air scoop54is configured for convenient placement under the wing of an aircraft.

While the principles of the disclosure have been described above in connection with specific apparatuses and methods, it is to be clearly understood that this description is made only by way of example and not as limitation on the scope of the disclosure. Specific details are given in the above description to provide a thorough understanding of the embodiments. However, it is understood that the embodiments may be practiced without these specific details. For example, the present disclosure is described herein as having an exhaust gas condenser28that includes exhaust gas conduits and bypass air passages. In alternative embodiments, the present disclosure may include bypass air conduits and exhaust gas passages disposed in the alternating manner described herein.

It is noted that the embodiments may be described as a process which is depicted as a flowchart, a flow diagram, a block diagram, etc. Although any one of these structures may describe the operations as a sequential process, many of the operations can be performed in parallel or concurrently. In addition, the order of the operations may be rearranged. A process may correspond to a method, a function, a procedure, a subroutine, a subprogram, etc. The singular forms “a,” “an,” and “the” refer to one or more than one, unless the context clearly dictates otherwise. For example, the term “comprising a specimen” includes single or plural specimens and is considered equivalent to the phrase “comprising at least one specimen.” The term “or” refers to a single element of stated alternative elements or a combination of two or more elements unless the context clearly indicates otherwise. As used herein, “comprises” means “includes.” Thus, “comprising A or B,” means “including A or B, or A and B,” without excluding additional elements.

While various inventive aspects, concepts and features of the disclosures may be described and illustrated herein as embodied in combination in the exemplary embodiments, these various aspects, concepts, and features may be used in many alternative embodiments, either individually or in various combinations and sub-combinations thereof. Unless expressly excluded herein all such combinations and sub-combinations are intended to be within the scope of the present application. Still further, while various alternative embodiments as to the various aspects, concepts, and features of the disclosures—such as alternative materials, structures, configurations, methods, devices, and components, and so on—may be described herein, such descriptions are not intended to be a complete or exhaustive list of available alternative embodiments, whether presently known or later developed. Those skilled in the art may readily adopt one or more of the inventive aspects, concepts, or features into additional embodiments and uses within the scope of the present application even if such embodiments are not expressly disclosed herein. For example, in the exemplary embodiments described above within the Detailed Description portion of the present specification, elements may be described as individual units and shown as independent of one another to facilitate the description. In alternative embodiments, such elements may be configured as combined elements. It is further noted that various method or process steps for embodiments of the present disclosure are described herein. The description may present method and/or process steps as a particular sequence. However, to the extent that the method or process does not rely on the particular order of steps set forth herein, the method or process should not be limited to the particular sequence of steps described. As one of ordinary skill in the art would appreciate, other sequences of steps may be possible. Therefore, the particular order of the steps set forth in the description should not be construed as a limitation.