Patent ID: 12196115

DETAILED DESCRIPTION OF THE DISCLOSURE

The foregoing summary, as well as the following detailed description of certain embodiments will be better understood when read in conjunction with the appended drawings. As used herein, an element or step recited in the singular and preceded by the word “a” or “an” should be understood as not necessarily excluding the plural of the elements or steps. Further, references to “one embodiment” are not intended to be interpreted as excluding the existence of additional embodiments that also incorporate the recited features. Moreover, unless explicitly stated to the contrary, embodiments “comprising” or “having” an element or a plurality of elements having a particular condition can include additional elements not having that condition.

In certain smaller vehicles, such as certain unmanned aerial vehicles (UAVs), or for configurations where a separate liner is not practical, a solution integral to the underlying structure is needed. As a result, there is a need for an integrated propulsion flow path in which acoustic treatments can be incorporated directly into the propulsion flow path structure, in contrast to be being separately secured to the structure.

Certain embodiments of the subject disclosure provide a quiet propulsion flow path duct system that includes a base having a flow surface, a plurality of supports joined together to define a plurality of cavities isolated from each other, and a backing surface. The supports are between the base and the backing surface. The base defines a plurality of perforations. An underlying cavity is in fluid communication with an internal volume of a duct via one or more perforations. In at least one embodiment, the base, supports, and backing surface together form a monolithic, load bearing structure.

In at least one embodiment, instead of separately forming portions, the flow path duct system is integrally formed as a monolithic structure. For example, the flow path duct system is integrally molded and formed as a single, monolithic piece (instead of having separate components formed and secured together). As another example, the flow path duct system, including all component parts, is integrally formed through additive manufacturing.

In at least one embodiment, the plurality of cavities and the perforations together form a plurality of Helmholtz resonators for sound attenuation. In at least one embodiment, the plurality of cavities define a distribution of shapes including triangles, diamonds, circles, hexagons (honeycomb), or a combination thereof. Further, in at least one embodiment, the plurality of cavities can define a distribution of diamond shapes. In some ducts, the perforations can be ellipses, circles, squares, rounded squares, diamonds, rounded diamonds, rectangles, rounded rectangles, parallelograms, rounded parallelograms, or a combination thereof. In at least one embodiment, the perforations can be circles. For some embodiments, the perforations can define a flow surface porosity. The porosity can range from 20% to 4%, for example. In some ducts, the perforations can define a flow surface porosity, the porosity ranging from 10% to 6%, for example.

In at least one embodiment, the depth of the plurality of cavities can define a continuous distribution, a constant distribution, or a step distribution with at least one step. In at least one embodiment, the depth of the plurality of cavities can define a constant distribution or a step distribution with at least one step. In at least one embodiment, the duct can be formed of titanium, titanium alloys, aluminum, aluminum alloys, stainless steel, or polymer. For some ducts, the duct can include a polymer. For some duct embodiments, the duct can be a variable geometry with at least one high aspect ratio inlet or exit.

FIG.1illustrates a perspective top view of an aircraft100, such as an unmanned aerial vehicle (UAV), according to an embodiment of the subject disclosure. In at least one embodiment, the UAV100includes a main body or fuselage101, wings102, and canards103. The main body101defines an inlet110. The inlet110leads into a flow path duct system of a propulsion system. The flow path duct system extends into and through at least a portion of the UAV100. The flow path duct system is described herein.

Optionally, the UAV100can be sized, shaped, and configured differently than shown inFIG.1. For example, the UAV100may not include canards. As another example, the wings102can be disposed at locations that are forward from the wings102as shown. As another example, the UAV100may not include wings. Instead, the UAV100can include one or more helicopter-like rotors, for example.

FIG.2illustrates a front perspective view of an aircraft100, according to an embodiment of the subject disclosure. The aircraft100includes a propulsion system212that includes two engines202, for example, such as two turbofan or turbojet engines. Optionally, the propulsion system212may include more engines202than shown. The engines202are carried by wings216of the aircraft100. In other embodiments, the engines202are carried by a fuselage218and/or an empennage220. The empennage220may also support horizontal stabilizers222and a vertical stabilizer224. The fuselage218of the aircraft100defines an internal cabin, including a flight deck. The engines202include flow path duct systems, such as described herein.

The aircraft100can be sized, shaped, and configured differently than shown inFIG.2. The aircraft100shown inFIG.1is merely an example.

FIG.3illustrates a lateral perspective view of an engine202, according to an embodiment of the subject disclosure. In at least one embodiment, the engine202is a turbofan or turbojet engine having a case300that includes an engine inlet314, which leads into a flow path duct system, as described herein. The engine inlet314may include a leading edge316and an inner barrel section320located aft of the leading edge316of the engine inlet314. The inner barrel section320can provide a boundary surface or wall for directing airflow (not shown) entering the engine inlet314and passing through the engine202. The inner barrel section320can be located in relatively close proximity to one or more fan blades (not shown inFIG.3). In at least one embodiment, the inner barrel section320can also be configured to serve as an acoustic structure having a plurality of perforations in an inner face sheet of the inner barrel section320for absorbing noise generated by the rotating fan blades and/or noise generated by the airflow entering the engine inlet314and passing through the engine202. In at least one embodiment, the inner barrel section320includes, and or can be configured as, a flow path duct system, as described herein.

FIG.4illustrates a perspective internal view of a flow path duct system400, according to an embodiment of the subject disclosure.FIG.5illustrates a perspective external view of the flow path duct system400with a backing surface removed to expose supports and resulting cavities, according to an embodiment of the subject disclosure.

Referring toFIGS.4and5, in at least one embodiment, the flow path duct system400is within the UAV100shown inFIG.1. For example, the inlet110, shown inFIG.1, leads into, or forms an inlet of, the flow path duct system400. In at least one other embodiment, the flow path duct system400is within the engine202shown inFIGS.2and3. For example, the engine inlet314, shown inFIG.3, leads into, or forms an inlet of, the flow path duct system400.

The flow path duct system400provides a quiet propulsion flow path system. The flow path duct system400includes an internal surface428, which defines a flow surface410. For example, a base426includes the internal surface428that defines the flow surface410. Fluid, for example, air, travels over and along the flow surface410. Supports420extend opposite from the base426, such as at edges422and an external surface. The supports420can include frames, beams, ribs, fins, walls, or the like.

The supports420define a plurality of cavities421. For example, a cavity421ais defined between a first support420aand a second support420b. A cavity421bis defined between the second support420band a third support420c. The supports420can be sized and shaped the same. The supports420can be upstanding fins, walls, beams, ribs, and/or or the like.

The flow path duct system400also includes a backing surface430and a plurality of perforations440. For example, the backing surface430is disposed over external portions of the supports420, the cavities421, and/or the perforations440. The perforations440can be formed in the base426, for example. As an example, the supports420extend from the base426, which provides the flow surface410. In at least one embodiment, the supports420are or otherwise include fins427that extend from the base426. The cavities421are defined between the base426and the fins427. The perforations440are formed into and/or through the base426. As such, a fluid flow path extends between the cavities421, the perforations440, and the internal volume435of the flow path duct system400. The backing surface430can be a sheet, skin, or the like, disposed over the supports420and the cavities421.

The cavities421extend from external surfaces of the base426, opposite from the flow surface410, thereby extending away from the internal volume435. The perforations440are formed in the base426and are in fluid communication with the internal volume435. As such, the fluid flow path extends from the cavities421, through the perforations440in the base426, and into the internal volume435.

In at least one embodiment, the depth423of the cavities421is constant throughout the flow path duct system400. That is, the distribution of depths423of the cavities421can be the same throughout the flow path duct system400. Optionally, the depths of certain cavities421can differ. In at least one embodiment, the flow path duct system400shown inFIGS.4and5provides a monolithic, complex geometry inlet structure that provides sound attenuation.

In at least one embodiment, as shown inFIG.5, the supports420include intersecting, beams, ribs, panels, walls, or fins427that intersect to form a plurality of repeating cavities421. The supports420define outer boundaries for the cavities421, which can have various shapes and sizes.

In at least one embodiment, the flow path duct system400is for a propulsion system of an aircraft. The flow path duct system400includes the base426defining the flow surface410(such as on an internal surface428). The base426includes the internal surface428and an external surface432. A plurality of perforations440are formed through the base426between the internal surface428and the external surface432. The supports420define the cavities421. The supports420extend outwardly from the external surface432of the of the base426. One or more of the plurality of cavities421are in fluid communication with the one or more of the plurality of perforations440. The backing surface430is secured to the plurality of supports420. The supports420are disposed between the base426and the backing surface430. One or more of the plurality of cavities421are in fluid communication with an internal volume435defined by the internal surface428of the base426through one or more of the plurality of perforations440.

In at least one embodiment, the base426, the supports420, and the backing surface430are integrally formed together as a monolithic, load-bearing structure. For example, the base426, the supports420, and the backing surface430are additively manufactured together. That is, the flow path duct system400, including the components thereof, are integrally formed through an additive manufacturing process.

In at least one embodiment, each of the cavities421is in fluid communication with at least one the perforations440, and/or vice versa. In at least one embodiment, cavities421and the perforations440cooperate to provide a plurality of Helmholtz resonators.

FIG.6illustrates a transverse partial cross-sectional view of the flow path duct system400having constant depth cavities, according to an embodiment of the subject disclosure. As shown inFIG.6, the flow path duct system400can be an inlet401. The depth (or height)423of the cavities421can be constant along a length460of the flow path duct system400.

FIG.7illustrates a transverse partial cross-sectional view of the flow path duct system400having constant depth cavities421, according to an embodiment of the subject disclosure. As shown inFIG.7, the flow path duct system400can be an outlet nozzle403. Again, the depth (or height)423of the cavities421can be constant along a length462of the flow path duct system400.

Referring toFIGS.6and7, while the depths423of the cavities421can be the same throughout the flow path duct system400, the widths429can differ. For example, a first set of cavities421can have a first width that differs from a second set of cavities421. Optionally, the width429of the cavities421can be the same throughout.

FIG.8illustrates transverse partial cross-sectional view of a flow path duct system400having cavities421cand421dwith a single step distribution in depth423, or two constant depths, according to an embodiment of the subject disclosure. For example, a first set of cavities421chas a depth423that differs from a depth423of a second set of cavities421d. A step425defines a transition between the first set of cavities421cand the second set of cavities421d. As shown, the depth423of the first set of cavities421cis greater than the depth423of the second set of cavities421d. Optionally, the depth423of the second set of cavities421dcan be greater than the depth423of the first set of cavities421c.

FIG.9illustrates a transverse partial cross-sectional view of a flow path duct system400having cavities421e,421f, and421gwith a double step distribution in depth, or three constant depths, according to an embodiment of the subject disclosure. For example, a first set of cavities421ehas a depth423that differs from a depth423of a second set of cavities421f, which differs from a depth423of a third set of cavities421g. A step431defines a transition between the first set of cavities421eand the second set of cavities421f. A step433defines a transition between the second set of cavities421fand the third set of cavities421g. As shown, the depth423of the first set of cavities421eis greater than the depth423of the second set of cavities421f. Further, the depth423of the second set of cavities421gis greater than the depth423of the third set of cavities421g. Optionally, the depth423of the second set of cavities421fcan be greater than the depth423of the first set of cavities421e, and/or the depth423of the third set of cavities421gcan be greater than the depth423of the second set of cavities421f.

Referring toFIGS.4-9, certain embodiments provide a flow path duct system400, and a method of making the flow path duct system400. In at least one embodiment, the method includes additively manufacturing a duct geometry as a monolithic structure, in which the geometry includes the flow surface410, the supports420defining the plurality of cavities421isolated from each other, and the backing surface430. In at least one embodiment, the supports420are between the flow surface410and the backing surface430.

In at least one embodiment, the flow path duct system400, and the method of forming the flow patch duct400, also includes the plurality of perforations440. The perforations440are in fluid communication with one or more cavities421. In at least one embodiment, the plurality of perforations440can be added to the flow surface410, as opposed to adding them during an additive manufacturing step.

As noted, the supports420are between the base426and the backing surface430. In at least one embodiment, the supports420can be joined together. For example, the supports420can be fastened together. In at least one embodiment, the flow surface410, the supports420, and the backing surface430define the cavities421, which are internal to the flow path duct system400. The cavities421are isolated from one another. In at least one embodiment, the base426, the supports420, and the backing surface430together form a monolithic, load bearing structure. In at least one embodiment, the monolithic structure can be additively manufactured. In at least one embodiment, the flow path duct system400can be a primary load bearing structure, thereby resulting in an integrated design with reduced part count and reduced complexity.

The base426includes a plurality of perforations440. One or more cavities421are in fluid communication with an internal volume435of the flow path duct system400through the perforations440. The perforations440provide an acoustic flow path to the underlying isolated cavities421to effectively attenuate sound energy. In at least one embodiment, the cavities421and the perforations440together form a plurality of Helmholtz resonators that are configured to attenuate sound.

The perforations440can have a variety of sizes and shapes. For example, the perforations440can be formed as ellipses, circles, squares, rounded squares, diamonds, rounded diamonds, rectangles, rounded rectangles, parallelograms, rounded parallelograms, or a combination thereof. A rounded perforation440has junctions, edges, and the like that are filleted to provide a smooth transition. In at least one embodiment, the perforations440can be circular.

In at least one embodiment, the number of size of the perforations440(for example, a surface area and volume of perforation) defines a porosity of the flow surface410. For example, the porosity (that is, the total volume of open space within the flow path duct system400), as defined by the perforations440, ranges from about 20% (for example, between 18%-22%), about 15% (for example, between 13%-17%), about 10% (for example, between 8%-12%), about 8% (for example, between 6%-10%), about 6% (for example, between 4%-8%), or about 5% (for example, between 3%-7%), to about 4% (for example, between 2%-5%), or any combination thereof. In at least one embodiment, the porosity ranges from about 10% to about 6%, or about 8%, for example.

In at least one embodiment, the plurality of cavities421define a distribution of shapes including triangles, diamonds, circles, hexagons (honeycomb), or a combination thereof. For example, as shown inFIG.5, the cavities421have shapes490in the form of diamonds. In at least one embodiment, the cavities421define a distribution of diamond shapes, as shown inFIG.5, for example. The supports420define the outer envelopes of the shapes of the cavities421. As such, the supports420provide load transmission and structural support for the flow path duct systems400, and define the envelopes of the cavities421.

In at least one embodiment, the size and spacing of the perforations440and the cavities421is tuned for tailored frequency attenuation using methods known in the art, for example noise propagation codes (one example being ACoustic TRANsmission (ACTRAN®)), or theoretical methods described in Wu et al., Noise Attenuation Performance of a Helmholtz Resonator Array Consist of Several Periodic Parts, 17 Sensors 2029 (2017). In at least one embodiment, the depth of cavities can be varied for sound attenuation optimization. In some embodiments, the depths423of the cavities421define a continuous distribution, a constant distribution, a step distribution with at one step for example, one step, two steps, or more).

In at least one embodiment, the material of the flow path duct system400can vary depending on actual use and environmental conditions. For example, the flow path duct system400is formed of titanium, titanium alloys, aluminum, aluminum alloys, stainless steel, one or more polymers, and/or the like.

In at least one embodiment, the flow path duct system400includes a variable geometry. For example, the flow patch duct system400includes an inlet flow path, an exit, a nozzle, a partial flow path, and/or a complete flow path. In at least one embodiment, at least one of the inlet (such as the inlet401shown inFIG.6) or the exit (such as the nozzle outlet403shown inFIG.7) includes a high aspect ratio. The aspect ratio is defined as a ratio of width/height of the flow path duct system400, with an aspect ratio greater than two (that is, the width being at least twice the height) being a high aspect ratio for a flow path duct system400. In at least one embodiment, both the inlet401and nozzle outlet402have high aspect ratios.

While the fluid path duct systems400described herein can be monolithic in terms of the construction of the acoustic treatment and the load bearing structure, the complete assembled flow path duct systems400as integrated into a vehicle (such as an aircraft) can include several different monolithic duct geometry sections (for example, inlet, nozzle, upper half, lower half) as opposed to one large section due to additive manufacturing and installation constraints.

In at least one embodiment, instead of additively manufacturing the flow surface410with a plurality of perforations440, different methods can be used to form the perforations440. For example, the perforations440can be formed through drilling cutting, laser cutting, vaporization, ablation, chemical treatment, and/or the like.

As described herein, certain embodiments of the subject disclosure provide a quiet propulsion flow path duct system400, which includes the flow surface410, a plurality of supports420defining a plurality of cavities421isolated from each other, and a backing surface430. The supports420are between the flow surface410and the backing surface430. For example, the supports420are sandwiched between the flow surface410and the backing surface430. The base426having the flow surface410includes a plurality of perforations440, such that at least one underlying cavity421is in fluid communication with the internal volume435through the perforations440. In at least one embodiment, the flow surface410, the supports420, and the backing surface430together form a monolithic, load bearing structure.

FIG.10illustrates a flow chart of a method of forming a flow path duct system for a propulsion system of an aircraft, according to an embodiment of the subject disclosure. Referring toFIGS.1-10, the method includes forming, at500, a plurality of perforations440through a base426defining a flow surface410between an internal surface428and an external surface432; extending, at502, a plurality of supports420defining a plurality of cavities421from the external surface432of the of the base426; fluidly coupling, at504, one or more of the plurality of cavities421with one or more of the plurality of perforations440, wherein said fluidly coupling504includes fluidly coupling the one or more of the plurality of cavities421with an internal volume435defined by the internal surface428of the base426through the one or more of the plurality of perforations440; and securing, at506, a backing surface430to the plurality of supports420, wherein said securing506includes disposing the plurality of supports420between the base426and the backing surface430.

In at least one embodiment, the method further includes integrally forming the base426, the plurality of supports420, and the backing surface430together as a monolithic, load-bearing structure. As a further example, said integrally forming includes additively manufacturing the base426, the plurality of supports420, and the backing surface430together.

In at least one embodiment, said fluidly coupling504includes fluidly coupling each of the plurality of cavities421with at least one of the plurality of perforations440.

In at least one embodiment, said forming500includes forming the plurality of perforations440to define a flow surface porosity within the base that ranges from 20% to 4%.

In at least one embodiment, the method includes forming the flow path duct system400as one or both of an inlet or an outlet nozzle having a high aspect ratio.

It has been discovered that the embodiments of the flow path duct systems400described herein reduce acoustic noise, as well as being able to serve as a primary, load-bearing structure.

Further, the disclosure comprises embodiments according to the following clauses:

Clause 1. A flow path duct system for a propulsion system of an aircraft, the flow path duct system comprising:a base defining a flow surface, wherein the base has an internal surface and an external surface, wherein a plurality of perforations are formed through the base between the internal surface and the external surface;a plurality of supports defining a plurality of cavities, wherein the plurality of supports extend outwardly from the external surface of the of the base, and wherein one or more of the plurality of cavities are in fluid communication with one or more of the plurality of perforations; anda backing surface secured to the plurality of supports,wherein the plurality of supports are disposed between the base and the backing surface, andwherein the one or more of the plurality of cavities are in fluid communication with an internal volume defined by the internal surface of the base through the one or more of the plurality of perforations.

Clause 2. The flow path duct system of Clause 1, wherein the base, the plurality of supports, and the backing surface are integrally formed together as a monolithic, load-bearing structure.

Clause 3. The flow path duct system of Clause 2, wherein the base, the plurality of supports, and the backing surface are additively manufactured together.

Clause 4. The flow path duct system of any of Clauses 1-3, wherein each of the plurality of cavities is in fluid communication with at least one of the plurality of perforations.

Clause 5. The flow path duct system of Clause 4, wherein the plurality of cavities and the plurality of perforations cooperate to provide a plurality of Helmholtz resonators.

Clause 6. The flow path duct system of any of Clauses 1-5, wherein the plurality of cavities are shaped as one or more of triangles, diamonds, circles, or hexagons.

Clause 7. The flow path duct system of any of Clauses 1-6, wherein the plurality of perforations are rounded.

Clause 8. The flow path duct system of any of Clauses 1-7, wherein the plurality of perforations define a flow surface porosity within the base that ranges from 20% to 4%.

Clause 9. The flow path duct system of any of Clauses 1-8, wherein a depth of the plurality of cavities is the same.

Clause 10. The flow path duct system of any of Clauses 1-9, wherein a depth of at least two of the plurality of cavities is different.

Clause 11. The flow path duct system of any of Clauses 1-10, further comprising one or both of an inlet or an outlet nozzle having a high aspect ratio.

Clause 12. A method of forming a flow path duct system for a propulsion system of an aircraft, the method comprising:forming a plurality of perforations through a base defining a flow surface between an internal surface and an external surface;extending a plurality of supports defining a plurality of cavities from the external surface of the of the base;fluidly coupling one or more of the plurality of cavities with one or more of the plurality of perforations, wherein said fluidly coupling comprises fluidly coupling the one or more of the plurality of cavities with an internal volume defined by the internal surface of the base through the one or more of the plurality of perforations; andsecuring a backing surface to the plurality of supports, wherein said securing comprises disposing the plurality of supports between the base and the backing surface.

Clause 13. The method of Clause 12, further comprising integrally forming the base, the plurality of supports, and the backing surface together as a monolithic, load-bearing structure.

Clause 14. The method of Clauses 12 or 13, wherein said integrally forming comprises additively manufacturing the base, the plurality of supports, and the backing surface together.

Clause 15. The method of any of Clauses 12-14, wherein said fluidly coupling comprises fluidly coupling each of the plurality of cavities with at least one of the plurality of perforations.

Clause 16. The method of any of Clauses 12-15, wherein said forming comprises forming the plurality of perforations to define a flow surface porosity within the base that ranges from 20% to 4%.

Clause 17. The method of any of Clauses 12-16, further comprising forming the flow path duct system as one or both of an inlet or an outlet nozzle having a high aspect ratio.

Clause 18. An aircraft comprising:a propulsion system including a flow path duct system, the flow path duct system comprising:a base defining a flow surface, wherein the base has an internal surface and an external surface, wherein a plurality of perforations are formed through the base between the internal surface and the external surface;a plurality of supports defining a plurality of cavities, wherein the plurality of supports extend outwardly from the external surface of the of the base, and wherein each of the plurality of cavities is in fluid communication with at least one of the plurality of perforations; anda backing surface secured to the plurality of supports,wherein the plurality of supports are disposed between the base and the backing surface, andwherein the plurality of cavities are in fluid communication with an internal volume defined by the internal surface of the base through the plurality of perforations.

Clause 19. The aircraft of Clause 18, wherein the base, the plurality of supports, and the backing surface are additively manufactured together as a monolithic, load-bearing structure.

Clause 20. The aircraft of Clauses 18 or 19, wherein the plurality of perforations define a flow surface porosity within the base that ranges from 20% to 4%.

As described herein, embodiments of the present disclosure provide systems and methods for efficiently and effectively reducing noise in relation to various components, such as an engine of aircraft. Further, embodiments of the present disclosure provide relatively simple systems and methods for reducing noise with respect to aircraft, for example.

While various spatial and directional terms, such as top, bottom, lower, mid, lateral, horizontal, vertical, front and the like can be used to describe embodiments of the subject disclosure, it is understood that such terms are merely used with respect to the orientations shown in the drawings. The orientations can be inverted, rotated, or otherwise changed, such that an upper portion is a lower portion, and vice versa, horizontal becomes vertical, and the like.

As used herein, a structure, limitation, or element that is “configured to” perform a task or operation is particularly structurally formed, constructed, or adapted in a manner corresponding to the task or operation. For purposes of clarity and the avoidance of doubt, an object that is merely capable of being modified to perform the task or operation is not “configured to” perform the task or operation as used herein.

It is to be understood that the above description is intended to be illustrative, and not restrictive. For example, the above-described embodiments (and/or aspects thereof) can be used in combination with each other. In addition, many modifications can be made to adapt a particular situation or material to the teachings of the various embodiments of the disclosure without departing from their scope. While the dimensions and types of materials described herein are intended to define the parameters of the various embodiments of the disclosure, the embodiments are by no means limiting and are exemplary embodiments. Many other embodiments will be apparent to those of skill in the art upon reviewing the above description. The scope of the various embodiments of the disclosure should, therefore, be determined with reference to the appended claims, along with the full scope of equivalents to which such claims are entitled. In the appended claims and the detailed description herein, the terms “including” and “containing” are used as the plain-English equivalents of the term “comprising” and the term “in which” is used as the plain-English equivalents of the term “wherein.” Moreover, the terms “first,” “second,” and “third,” etc. are used merely as labels, and are not intended to impose numerical requirements on their objects. Further, the limitations of the following claims are not written in means-plus-function format and are not intended to be interpreted based on 35 U.S.C. § 112(f), unless and until such claim limitations expressly use the phrase “means for” followed by a statement of function void of further structure.

This written description uses examples to disclose the various embodiments of the disclosure, including the best mode, and also to enable any person skilled in the art to practice the various embodiments of the disclosure, including making and using any devices or systems and performing any incorporated methods. The patentable scope of the various embodiments of the disclosure is defined by the claims, and can include other examples that occur to those skilled in the art. Such other examples are intended to be within the scope of the claims if the examples have structural elements that do not differ from the literal language of the claims, or if the examples include equivalent structural elements with insubstantial differences from the literal language of the claims.