SURFACE COATING FOR REDUCTION OF AERODYNAMIC NOISE AND VIBRATIONS

Abstract

A coating apparatus for the reduction of aerodynamic noise and vibrations. The coating apparatus is configured to include a group of fibrillar structures, wherein each fibrillar structure is configured with a diverging tip so that the coating reduces the size of and shifts downstream, a separation bubble, and modulates large-scale recirculating motion. Each fibrillar structure can be configured as a cylindrical micropillar. The group of fibrillar structures can be configured as a group of uniformly distributed cylindrical micropillars (e.g., one or more micropillar arrays). The surface coating is effective in reducing the separation bubble and displacing the separation bubble downstream. The coating facilitates a reduction in noise (e.g., aerodynamic noise) and vibrations due to the reduction in the size of the separation bubble.

Description

STATEMENT OF GOVERNMENT RIGHTS

The invention described in this patent application was made with Government support under Contract Number NSF/ONR CBET-1512393 awarded by the Office of Naval Research and the National Science Foundation. The Government has certain rights in the invention.

TECHNICAL FIELD

Embodiments are related to the field of flow separation in fluid mechanics and devices, systems and techniques for reducing flow separation. Embodiments also relate to surface coatings for reducing the amount of drag produced in turbulent flow. Embodiments further relate to surface coatings that facilitate the reduction of aerodynamic noise and vibrations.

BACKGROUND

Flow separation is a fluid mechanic phenomenon that results in increased drag and loading on structures, causing reduced energy efficiency and possibly compromising structural integrity. As an object travels through a fluid, the velocity of the fluid in contact with the object slows down because of the viscosity of the fluid and the friction applied by the object's surface. This interaction between the fluid and the surface of the object is referred to as the boundary layer, which can be categorized as either laminar or turbulent flow by calculating the Reynolds number (i.e., a ratio of inertial force to viscous force). Low Reynolds numbers are attributed to larger viscous forces, which result in laminar flow (e.g., constant, orderly fluid motion). As the Reynolds number increases because of large inertial forces, the flow becomes disorderly (e.g., producing eddies and vortices) and transitions into turbulent flow.

With respect to aerodynamics, the boundary layer profile begins as laminar and transitions to turbulent as the velocity profile thickens—disrupting the smooth flow and producing skin-friction drag. At greater downstream distances of an object traveling through a fluid, the boundary layer and the pressure differential (e.g., front-to-back of object) increase—eventually resulting in a separation bubble that reverses the flow at the surface. When the flow reverses, the boundary layer essentially separates from the surface, creating a drag force that requires more energy to overcome and in some cases causes a plane to stall.

In addition to turbulent flow, an object's surface roughness has demonstrated an ability to increase the skin-friction drag and potentially play a role in flow separation. To overcome this issue, researchers have been investigating the use of coating on surfaces to reduce the amount of drag produced in turbulent flow.

BRIEF SUMMARY

The following summary is provided to facilitate an understanding of some of the innovative features unique to the disclosed embodiments and is not intended to be a full description. A full appreciation of the various aspects of the embodiments disclosed herein can be gained by taking the entire specification, claims, drawings, and abstract as a whole.

It is therefore one aspect of the disclosed embodiments to provide for methods and devices for reducing flow separation.

It is another aspect of the disclosed embodiments to provide for methods and devices that reduce the amount of drag produced in a turbulent flow.

It is yet another aspect of the disclosed embodiments to provide for a surface coating for the reduction of noise and vibrations due to a reduction in the size of a separation bubble.

It is also an aspect of the disclosed embodiments to provide for a micro-scale fibrillar coating that reduces flow separation by reducing the size of a separation bubble and pushing the separation point further downstream.

The aforementioned aspects and other objectives and advantages can now be achieved as described herein. A surface coating is disclosed for the reduction of aerodynamic noise and vibrations. In an example embodiment, a coating apparatus can be configured, which includes a group of fibrillar structures, wherein each fibrillar structure is configured with a diverging tip so that the coating reduces the size of and shifts downstream, a separation bubble, and modulates large-scale recirculating motion. In some example embodiments, each fibrillar structure can be configured as a cylindrical micropillar. Such a group of fibrillar structures can be configured as a group of uniformly distributed cylindrical micropillars.

The coating is configured to function under dry or wet conditions and mitigates flow separation without a noticeable increase in the production of TKE (Turblent Kinetic Energy). The coating can be configured as a microsurface coating that shifts the separation point downstream and reduces the area of negative flow. The coating can also be configured to rely on the generation of distributed wall-normal perturbations.

BRIEF DESCRIPTION OF THE DRAWINGS

The accompanying figures, in which like reference numerals refer to identical or functionally-similar elements throughout the separate views and which are incorporated in and form a part of the specification, further illustrate the disclosed embodiments and, together with the detailed description of the disclosed embodiments, serve to explain the principles of the present invention.

FIG. 1 illustrates a pictorial diagram depicting a sample shark denticle and sample microscopy images of micropillar arrays, in accordance with an example embodiment;

FIG. 2 illustrates graphs depicting data indicative of instantaneous normalized velocity for respective smooth and coated cases, and graphs of data indicative of the mean vertical velocity for the smooth and coated cases, respectively, in accordance with an example embodiment;

FIG. 3 illustrates a graph depicting superimposed contour lines for the normalized mean streamwise velocity and graphs with data indicative of velocity profiles, in accordance with an example embodiment;

FIG. 4 illustrates graphs depicting profile data and a schematic diagram demonstrating the physical mechanism by which a group of micropillars modify the flow in the area near the flow, in accordance with an example embodiment;

FIG. 5 illustrates a schematic diagram of the APG test section of a wind-turbine, in accordance with an example embodiment;

FIG. 6 illustrates a schematic diagram depicting a ZPG test section and FIG. 6A illustrates an inset thereof, in accordance with an example embodiment; and

FIG. 7 illustrates a flow chart of operations depicting a method for fiber fabrication in accordance with an example embodiment.

DETAILED DESCRIPTION

The particular values and configurations discussed in these non-limiting examples can be varied and are cited merely to illustrate at least one embodiment and are not intended to limit the scope thereof.

The embodiments will now be described more fully hereinafter with reference to the accompanying drawings, in which illustrative embodiments of the invention are shown. The embodiments disclosed herein can be embodied in many different forms and should not be construed as limited to the embodiments set forth herein; rather, these embodiments are provided so that this disclosure will be thorough and complete, and will fully convey the scope of the invention to those skilled in the art. Like numbers refer to identical, like or similar elements throughout, although such numbers may be referenced in the context of different embodiments. As used herein, the term “and/or” includes any and all combinations of one or more of the associated listed items.

The terminology used herein is for the purpose of describing particular embodiments only and is not intended to be limiting of the invention. As used herein, the singular forms “a”, “an”, and “the” are intended to include the plural forms as well, unless the context clearly indicates otherwise. It will be further understood that the terms “comprises” and/or “comprising,” when used in this specification, specify the presence of stated features, integers, steps, operations, elements, and/or components, but do not preclude the presence or addition of one or more other features, integers, steps, operations, elements, components, and/or groups thereof.

Unless otherwise defined, all terms (including technical and scientific terms) used herein have the same meaning as commonly understood by one of ordinary skill in the art to which this invention belongs. It will be further understood that terms, such as those defined in commonly used dictionaries, should be interpreted as having a meaning that is consistent with their meaning in the context of the relevant art and will not be interpreted in an idealized or overly formal sense unless expressly so defined herein.

Subject matter will now be described more fully hereinafter with reference to the accompanying drawings, which form a part hereof, and which show, by way of illustration, specific example embodiments. Subject matter may, however, be embodied in a variety of different forms and, therefore, covered or claimed subject matter is intended to be construed as not being limited to any example embodiments set forth herein; example embodiments are provided merely to be illustrative. Likewise, a reasonably broad scope for claimed or covered subject matter is intended. Among other things, for example, subject matter may be embodied as methods, devices, components, or systems. The following detailed description is, therefore, not intended to be taken in a limiting sense.

Throughout the specification and claims, terms may have nuanced meanings suggested or implied in context beyond an explicitly stated meaning. Likewise, the phrase “in one embodiment” or “an example embodiment” as used herein does not necessarily refer to the same embodiment and the phrase “in another embodiment” as used herein does not necessarily refer to a different embodiment. It is intended, for example, that claimed subject matter include combinations of example embodiments in whole or in part.

In general, terminology may be understood at least in part from usage in context. For example, terms, such as “and”, “or”, or “and/or,” as used herein may include a variety of meanings that may depend at least in part upon the context in which such terms are used. Typically, “or” if used to associate a list, such as A, B or C, is intended to mean A, B, and C, here used in the inclusive sense, as well as A, B or C, here used in the exclusive sense. In addition, the term “one or more” as used herein, depending at least in part upon context, may be used to describe any feature, structure, or characteristic in a singular sense or may be used to describe combinations of features, structures or characteristics in a plural sense. Similarly, terms, such as “a,” “an,” or “the,” again, may be understood to convey a singular usage or to convey a plural usage, depending at least in part upon context. In addition, the term “based on” may be understood as not necessarily intended to convey an exclusive set of factors and may, instead, allow for existence of additional factors not necessarily expressly described, again, depending at least in part on context.

During the past few decades, considerable effort has been placed on controlling flow separation. This phenomenon is usually responsible for increased vibration and drag on bluff bodies as well as higher energy consumption in vehicles. The drag experienced by a body under subsonic motion mostly embodies viscous and pressure (form) effects. The former is a result of friction induced by the near-wall fluid, and the latter is a result of pressure imbalance around the surface of the body. The separation phenomenon is well exemplified in the canonic case of flow around a foil at a sufficiently high angle of attack. There, the adverse pressure gradient (APG) in the suction side leads to flow deceleration and eventually flow detachment. The direct consequence of this process is a change of the aerodynamic force components, namely lift and drag.

Surface roughness plays a significant role in the turbulence dynamics near the wall and, in particular, in the separation regions. Evidence suggests that randomly distributed roughness, e.g., sand grain roughness, may move the separation point against the flow direction in the case of foils; this shift results in drag increase and lift decrease. Experiments have shown an upstream shift of the separation point in a channel expansion with rough walls. However, various studies have shown that triggering transition to turbulence may reduce separation. These findings have motivated the use of flow control strategies such as vortex generators and synthetic jets to effectively delay flow separation. Unfortunately, these methods increase the production of TKE (Turbulent Kinetic Energy), which, in turn, increases viscous losses and thus energy dissipation near the wall region. This viscous loss suggests that the control of flow separation without turbulence penalty is an ideal way to control form drag.

Recent efforts have focused on passive control via bio-inspired surfaces. The morphology of some natural organisms such as the lotus leaf and shark skin suggests that this daunting task might be achieved through textured coatings. Synthetic microscale structures similar to those found in the lotus leaf have been effective in reducing viscous drag by creating a slip velocity with trapped air between the wall and the water flow. The surface, however, eventually wets, losing functionality over tim. Denticles found on the skin of sharks have also shown drag reducing properties. While not completely understood, these structures appear to inhibit the formation and evolution of near-wall coherent motions. However, the physical mechanism responsible for this phenomenon is still under debate.

FIG. 1 illustrates a pictorial diagram depicting a sample shark denticle 10 and sample microscopy images 14 and 16 of micropillar arrays, in accordance with an example embodiment. The example shark denticle 10 shown in FIG. 1 demonstrates a divergent shape with an asymmetry in the wall-normal and streamwise directions. The example microscopy images 14 and 16 of such micropillar arrays have a similar asymmetric shape (e.g., note—scale bars: 100 μm). Note that in the example images 14 and 16, the height and tip diameter of each element are 85 μm and 75 μm, whereas the salk diameter is 40 μm. The center-to-center distance between the pillars is 120 μm. Note that throughout the specification, example parameters such as those depicted in the figures and described herein, should not be considered limiting features of the disclosed embodiments but are discussed and illustrated for exemplary purposes only.

A feature of shark denticles as illustrated in FIG. 1 is the aforementioned asymmetric geometry. The pillars shown in images 14 and 16, for example, are axisymmetric but take other elements of the denticles, including divergence and height. They are packed in a Cartesian layout and feature a “spatula” shape with stalk and tip diameters of 40 μm and 75 μm, respectively, a height of 85 μm (defined here as the roughness height, k), and a center-to-center distance between pillars of 120 μm. Another key difference is that the pillars do not include the channel-like indentations that denticles have on their top surfaces. Note that the pillars shown in the images 14 and 16 can be arranged in a square packing with aligned rows and columns, but naturally occurring denticles overlap and are randomly aligned. Synthetic denticles have been successfully tested in Cartesian arrays without overlap. One of the objectives of the disclosed embodiments is to demonstrate that this unique, engineered microsurface is capable of mitigating flow separation. The pillars' simple manufacturing and cost-effective fabrication process may lead to a large impact in a wide range of energy applications.

Despite some success fabricating shark-inspired synthetic surfaces, such fabrication methods rely on 3D printing, making it difficult to replicate denticles in their original size. Some experiments have scaled the structures by a factor of 12.4 to satisfactorily replicate geometric features. However, because every denticle must be 3D printed, this method may be slow and expensive. The approach described and presented herein instead relies on a series of etching and casting steps. While the initial step includes a complicated process composed of deep reactive ion etching, the subsequent steps allow for replication of the desired surface using simple casting methods. Once a mold is made, it can be used almost indefinitely. This reusability allows for reproduction and scaleup of these engineered microsurfaces in a cost-effective manner, using a variety of materials capable of satisfying application-specific requirements. Furthermore, the structures can be casted directly on the surface to be coated, thus simplifying the installation process.

FIG. 2 illustrates graphs 22, 24 depicting data indicative of instantaneous normalized velocity u/U_∞ for respective smooth and coated cases, and graphs 26 and 28 depicting data indicative of the mean vertical velocity V/U_∞, for the smooth and coated cases, respectively, in accordance with an example embodiment. Graphs 22 and 24 demonstrate that the smooth case has significantly more reverse flow, which is associated with separated flow. In addition, graphs 26 and 28 demonstrate the area of flow moving away from the wall (upward velocity), which is linked to separation.

The data contained in the various graphs shown herein (e.g., FIGS. 2, 3, 4) is based on measurements that were performed in a refractive-index—matching (RIM) facility at the University of Illinois at Urbana—Champaign with a diverging cross-section (e.g., see image 16 in FIG. 1) at Re_θ≈1,200. As discussed previously, such measurements or parameters are not to be considered limiting features of the disclosed embodiments, but are provided herein for exemplary purposes only.

The RIM allowed measurement of the velocity very near the wall, down to y⁺≈3.6 for the selected interrogation window. The flow field and turbulence statistics were compared with a smooth counterpart. The calculated uncertainty of the velocity measurement is 0.5% of U_∞. Details of the experiments are described in the section “Materials and Methods” herein. The resulting velocity fields reveal significant differences between the flows over the smooth and coated walls.

Instantaneous velocity contours with superimposed mean streamlines (i.e., see graphs 22 and 24 in FIG. 2) illustrate a large region with reverse flow in the smooth case. In contrast, the divergent pillars induce a smaller separation bubble. Further, the reverse flow (blue) region is considerably smaller in the coated case.

FIG. 3 illustrates a graph 32 depicting superimposed contour lines for the normalized mean streamwise velocity <U>/U_∞ and graphs 34 and 36 with data indicative of velocity profiles, in accordance with an example embodiment. In graph 32, solid lines represent “smooth” and dashed lines represent “coated”. The smooth case shown an approximately 60% larger area with negative flow (black level). Graphs 34 and 36 respectively show velocity profiles for <U>/U_∞ and <V>/U_∞, respectively, smooth and coated. Note that in graph 34, the inset 37 shows the region near the wall for <U>/U_∞, where a larger negative portion in the smooth case can be observed. Error bars represent SE (=u_rms√{square root over (N)}, where N is the number of samples). For U, the error bars (not shown) are smaller than the symbol site).

The reduced flow separation is confirmed by the mean streamwise velocity contours, which are shown superimposed for both cases (see graph 32 in FIG. 3A). The contours for the smooth case (solid lines) recover farther away from the wall, and the reverse flow (black contour) is considerably larger over the smooth surface. The area with reverse flow is reduced by approximately 60% in the presence of the microscale coating. Our data also reveal a downstream shift in the separation point of ˜0.46δ₀, where δ₀ is the boundary layer thickness at the inlet of the expansion. The effect of the coating is also observed in the mean vertical velocity field. When the flow is attached, this velocity component should remain negative in this particular configuration. However, as observed in some cases, a higher upward velocity occurs in the smooth case, which is characteristic evidence that the boundary layer has detached from the wall (i.e., it is separated).

Despite lift and drag measurements not being performed for this particular study, previous wind-tunnel experiments carried out on a coated S809 airfoil have shown a 25-40% increase in the lift coefficient at angles between 8° and 16°. These results provide complementary evidence of the functionality of pillars (such as shown, for example, in the images 14 and 16) in reducing flow separation. This apparent functionality (lift coefficient increase) in wind-tunnel experiments implies that the coating also works in air. This supports the hypothesis that the mechanism by which the surface coating reduces flow separation does not rely on hydrophobicity.

The differences between the two cases are highlighted in the selected mean velocity profiles at x/δ₀=18.5 (see graphs 34 and 36 in FIG. 3). This is consistent with reduced blockage from a smaller recirculation bubble. The streamwise velocity in the coated case is higher near the wall (approximately 10% of the local average) than in the baseline. The effect of the coating is most noticeable from the wall up to y/δ≈0.6. The inset 37 in graph 34 of FIG. 3 shows a closer view near the wall, where the area with negative velocity, i.e., below the dashed line, is larger over the smooth surface. The difference larger, reaching almost 50% increase in the coated case around y/δ≈0.3. It is also worth noting that the vertical velocity does not recover completely at the edge of the boundary layer. This effect is due to the separation bubble preventing the flow from moving downward along the wall.

When adding texture to a wall, there is a risk of increasing the production of turbulent kinetic energy, which is related to viscous losses. The data discussed herein demonstrates differences in the TKE production between the two cases that are within the measurement uncertainty, suggesting that the pillars have minor effect on the turbulence production. This result is expected for “hydrodynamically smooth” walls.

While the results from the APG experiments show that the separation bubble is reduced and displaced downstream, the physical mechanism responsible for these phenomena is not evident from the data. To shed light on this mechanism, additional high-resolution experiments were carried out over a flat plate coated with the same engineered diverging pillars at Re_θ≈3,600 (see details in the “Materials and Methods” section herein). For these measurements, the interrogation window was placed as close as y⁺≈1. This setup was chosen to avoid the unsteadiness of the separation bubble in the APG flow. It should be noted that given the thickness of the laser sheet (e.g., approximately 1 mm), we inherently probe the flow over several rows of pillars, which creates an averaging effect in the transverse direction.

FIG. 4 illustrates graphs 42 and 44 depicting profile data and a schematic diagram 51 depicting the physical mechanism by which a group of micropillars 48, 50, 52 modify the flow in the area near the flow, in accordance with an example embodiment. Graph 42 shown in FIG. 4 plots data indicative of a wall-normal profile over someth and coated plates at x=2,100 mm. The coated case demonstrates a negative velocity in the vicinity of the wall, which is a result of suction between pillars (e.g., such as between micropillars 48, 50, and/or 52). Graph 44 depicts data indicative of wall-normal Reynolds stress. The velocity fluctuation shows a marked increase in the area adjacent to the pillar canopy edge, which suggests that oscillations are induced by the pillars in the flow in the interface of the pillary canopy.

The schematic diagram 51 illustrates the physical mechanism by which the micropillars modify the flow in the area near the flow. Note that in the schematic diagram 51, flow is indicated by the arrow 46. That is, areas of low and high pressure create high- and low-velocity areas, respectively. They also create ejection and suction events as represented by the thick black arrows 53 and 55 shown in FIG. 4, which increase the wall-normal velocity fluctuations. The schematic diagram 51 also demonstrates three distinct regions that arise in the flow: an inertia-dominated region, a viscous-dominated region, and an interface region between these two layers.

The vertical velocity profile (see graph 42 in FIG. 4) for the coated case shows a downward (negative) flow near the wall. The inventors believe that this downward flow may be due to a misalignment between the pillar rows and the bulk flow, creating a localized spanwise flow. The mechanism by which the pillars reduce flow separation can be gleaned from graph 44 in FIG. 4. The pillars generate oscillations in the inner layer, which are reflected as a large peak in the wall-normal component of the Reynolds stresses near the edge of the pillar canopy. Complementary insight is illustrated in the schematic diagram 51 of FIG. 4. The pillars reduce the crosssectional area, accelerating the fluid passing between them along the streamwise direction (red area). This acceleration decreases the pressure and generates suction. Additionally, pillars 48, 50 and/or 52 create a stagnation point by blocking some of the fluid. This increases the pressure and pushes fluid up, inducing fluid ejection.

Instead of the typical nonslip condition in canonical smooth walls, at the top of the pillars (y=k), the fluid velocity is not zero between the pillars. Instead, an “interlayer” is created above the pillars (see schematic diagram 51). In this layer a connection exists between the boundary layer (flow above the pillars 48, 50, 52) and the inner flow (i.e., within the canopy). Recalling the boundary layer momentum equation in the wall-normal direction,

$\begin{array}{cc}\frac{1}{\rho }\frac{\partial 〈P〉}{\partial y}=\frac{\partial 〈v^2〉}{\partial y}+\frac{\partial 〈v^{\mathrm{″2}}〉}{\partial y},& \left[1\right]\end{array}$

it is clear that v² and P are directly related; here • represents the time-averaging operator and v^″2 is a dispersive stress arising from the spatial averaging in the x (streamwise) and z (spanwise) directions. Integrating Eq. 1 from the top of the diverging pillars to a point y above the surface, it follows that

(P_oi−P)/ρ=v²−v_oi²+v^″2−v_oi^″2,  [2]

where P_oi is the static pressure at the edge of the canopy; that is, y_oi=k=85 μm Note that for the case of the smooth surface v_oi²=0, but in the coated case v_oi²≠0, as seen in the lower portion of graph 44 in FIG. 4.

The flow regime is significantly different within the micropillar layer, however. It has a Re_k less than or approximately equal to 1, based on the geometry and the estimated friction velocity; thus, it is viscous dominated and governed by pressure gradient, i.e., Stokes flow. Equation 1 can be used accordingly, recognizing that the gradient of the wall-normal Reynolds stress approaches zero. Therefore, P_ω≈P_oi within the pillar canopy, and the changes in the wall-normal Reynolds stress are proportional to the pressure difference between the static pressure at the wall, (P_ω), and the local pressure across the boundary layer. Consequently, it follows that

v_oi²=v²+v^″2−v_oi^″2−(P_ω−P)/τ  [3]

This relation implies that the changes observed in the inner region for (v²) are likely due to suction and blowing events between the diverging pillars and along the high-momentum flow region. Despite the fact that these changes exist mainly below the buffer layer, significant variations are observed in the outer layer, where the bubble resides. Consequently, this microscale surface passively modulates the small scales of the flow in the wall region, which in turn affects the large scales in the outer flow. Given the size of the pillars, this result is surprising, but is consistent with observed findings of the propagation of the pressure perturbation over 35 times the pillar height.

The pressure modulation generated by the pillars can be described as small-scale weak jetting events that may reenergize the boundary layer and delay separation; however, the pillars passively induce small-scale perturbations over the entire surface. In the case of the divergent pillars, the contraction in the cross-sectional area is greater, amplifying the flow acceleration between the pillars. The regions of ejections and suctions are increased in the viscous sublayer. For the smooth case, this increase occurs in the buffer layer, suggesting evidence of an interlayer above the pillar, which is consistent with Equation 3.

The combined results from such experiments indicate that it is through pressure changes at the interlayer, between viscous-dominated flow within the canopy and the inertia-dominated flow above the pillars, that the large scales of the flow are affected. Thus, the wall normal Reynolds stress at the interface, v², modulates the flow between the diverging pillars (suction and blowing) by interacting with the pressure difference, P_ω−(P), across the roughness interlayer. It must be stressed that the diameter of the pillar is the largest at the interlayer between the roughness canopy and the boundary layer, and therefore its effect is largest precisely in this region of the flow.

The pillars 48, 50 and 50 shown in the schematic diagram 51 in FIG. 4 are thus examples of a type of bio-inspired fibrillar structure. They have the demonstrated the ability to reduce the drag by more than 10%. The disclosed embodiments are based on studies of the effects of such fibrillar structures on flow separation. The inventors have discovered that the micro-scale fibrillar coating significantly reduced flow separation by reducing the size of the separation bubble and pushing the separation point further downstream. The inventors have accomplished this without increasing the turbulent kinetic energy (which is by-product of texturizing a surface). These results starkly oppose the notion that rough surfaces facilitate flow separation. The configuration and makeup of the surface coating in the disclosed embodiments demonstrate how and why the surface coating is so effective in reducing the separation bubble and displacing the separation bubble downstream.

Flow separation on moving bodies has a negative effect on energy efficiency. Reducing recirculating regions is a key in the design of energy-efficient systems. Efficient design decreases fuel consumption and pollutant emissions, including the systems' carbon footprint. The engineered bio-inspired coating presented herein aims to contribute in that direction. The relative ease of manufacturing and installation and its cost effectiveness, as well as its functionality under both wet and dry conditions, make it a versatile solution of potentially high impact in a broad range of applications, including transportation, wind power, and underwater vehicles.

Conclusions and Outlook

We have tested the flow control properties of an engineered bio-inspired surface coating. Our results confirm the functionality of the coating, which mitigated flow separation without a noticeable increase in the production of the turbulent kinetic energy. The microscale surface coating shifts the separation point downstream and significantly reduces the area of negative flow. The coating can be manufactured and installed with relative ease and is cost-effective in comparison with other solutions manufactured using 3D printing. The physical mechanism by which the coating works does not rely on (super)hydrophobicity. Instead, it relies on the generation of distributed wall-normal perturbations, giving it the versatility to work in liquid and gas media. These results have important implications in flow control, with applications in both power generation, e.g., wind turbines, and energy-efficient transport vehicles. These capabilities considerably increase the potential impact of the engineered coating.

While our results demonstrate the functionality and describe the working mechanism of the micropillars, it is necessary to test the surface coating under other flow conditions and different geometric configurations, e.g., spacing and height. Adapting the micropillar coating to a diverse array of applications will maximize the impact of this engineered surface on energy and transport systems.

Materials and Methods

FIG. 5 illustrates a schematic diagram 60 of the APG test section of a wind-turbine, in accordance with an example embodiment. In the experiments associated with the schematic diagram 60, the boundary layer develops in an approach channel of height H=45 mm and a length L=1,250 mm. The origin of the coordinate system (x=0, y=0) is set at the bottom wall of the channel at the beginning of the expansion. The micropillar coating (shaded area) was applied from x=−50 mm, and the X835 section is 370 mm long.

FIG. 6 illustrates a schematic diagram 80 depicting a ZPG test section and FIG. 6A illustrates an inset thereof, in accordance with an example embodiment. The boundary layer develops over a smooth region of 1,650 mm followed by a coated plate of 550 mm length (R_θ3,600), using the same diverging pillar geometry (e.g., shape, size, and spacing) as in the APG experiments. Careful alignment of the plates was performed by using 20-μm shims. In FIG. 6, example pillars 84 and 86 are shown in the inset 82 in FIG. 6A.

The experiments were performed in a RIM flume of a 112.5×112.5 mm² test section at the University of Illinois (laboratory of L.P.C.). The working fluid was a sodium iodide solution (63% by weight) with a kinematic viscosity v=1.1×10⁻⁶ m²/s and a density ρ=1,800 kg/m³. The minimum reflection from the wall allowed measurements within the viscous sublayer (y⁺≈3.6). The facility was adapted with a diverging wall (see FIG. 5) to induce adverse pressure gradient and flow separation. The experiments were performed at a Reynolds number Re_H=U₀H_1/2/v=4,600 (or in terms of the momentum thickness, Re_θ≈560) measured right upstream of the expansion (x=0), where U_o=0.225 m/s is the centerline velocity and H_1/2=H/2. The boundary layer thickness at the inlet δ_o=16:2 mm, and the normalized roughness height k⁺≅1 is estimated with c_f=0.026/Re_x^1/7. The inlet velocity profile for both cases differed by less than or equal to 1%. In the FOV (Field of View) shown in FIG. 2, for example, δ≈27.5 mm and Re_θ≈1,200.

Flat-plate [zero pressure gradient (ZPG)], high-resolution experiments were carried out in the RIM flume described above to assess the changes in the velocity field near the wall. For this set of experiments, the cross-section (112.5 mm×112.5 mm) was unobstructed. As illustrated in FIG. 6, the bottom wall was coated over a 550-mm span past a 1,650-mm smooth development region. The height of the coated plate was adjusted to minimize disturbances. Furthermore, to reduce misalignment effects, the flow was probed 500 mm into the coated section. The mean free stream velocity U_∞=0.8 m/s, equivalent to a momentum-based Reynolds number Re_θ=3,600. For these experiments, the field of view was considerably smaller than in the APG experiments, allowing us to resolve the viscous sublayer, down to a y⁺≈1.

Regarding particle image velocimetry, planar (two-dimension, two-component) particle image velocimetry (PIV) was used to measure the velocity field in a vertical plane at the axis of the diverging flume. An 11-MP camera (e.g., 2,700×4,000 pixels²) and a pulsed, dual-head Nd:YAG laser were used for image capture. The APG experiments had a resolution of 46 μm/pixel, resulting in a field of view of approximately 182×123 mm². Each experimental run involved 4,000 PIV realizations. The data processing was performed with a final interrogation window of 16×16 pixels² with 50% overlap, resulting in a vector separation Δx=Δy=365 μm.

The ZPG experiments used the same imaging system described above, but with higher resolution and a different processing algorithm. The optical field of view for these experiments was 26 mm×17.4 mm. A PIV plus PTV (particle tracking velocimetry) processing (LaVision) was used to obtain the velocity field. The algorithm performed two PIV passes, 32×32 pixels and 16×16 pixels, with a final PTV pass. The mean velocity field was calculated from 2,000 samples with a vector separation of 6.5 μm.

FIG. 7 illustrates a flow chart of operations depicting a method 100 for fiber fabrication in accordance with an example embodiment. The method 100 shown in FIG. 7 can be utilized to configure the disclosed diverging pillar array described herein, which is composed of a group of uniformly distributed cylindrical micropillars. Fiber fabrication (e.g., fabrication of a group of fibrillar structures) can involve the fabrication of the disclosed microscale coating using a method composed of photolithography, micromolding, and diptransfer printing.

As shown at block 102, a step or operation can be implemented in which a master template of cylindrical fibers is first fabricated using photolithography from photoresist (e.g., SU-8 2100; MicroChem). Next, as shown at block 104, a step or operation can be implemented in which a shape-complementary mold, which features the negative of cylindrical fibers, is manufactured by casting the cylindrical master with silicone rubber (e.g., Mold Max 27T; Smooth-On). Then, as depicted at block 106, a step or operation can be implemented in which the complementary mold is then cast with polyurethane (e.g., ST 3180; BJB Enterprises) to manufacture cylindrical fibers, which are an exact replica of the master fibers.

The second step of the fabrication forms the divergent tip, a feature similar to the shark denticle. As indicated at block 108, a step or operation can be implemented in which the polyurethane cylindrical fibers are placed onto a very thin film of liquid polyurethane, formed by spin coating the liquid polyurethane on a polystyrene substrate, using a spinner (e.g., WS-650 MS; Laurell Technologies). Next, as depicted at block 110, a step or operation can be implemented to remove the cylindrical fibers from the thin liquid film. Note that when the cylindrical fibers are removed from the thin liquid film, they retain some of the liquid polymer on the tip of each individual fiber.

Immediately after this step, as shown at block 112, a step or operation can be implemented in which the fiber array is placed onto a low-surface-energy dipping surface, a polypropylene substrate, allowing the liquid polymer to spread and morph into the desired shape. Thereafter, as illustrated at block 114, a step or operation can be implemented in which the pillars with divergent tips are obtained by removing the fibers from the dipping surface after the liquid polymer on the tips of the fibers cures. This step creates the master template for the fiber array, the result of which is indicated by block 116. As shown next at block 118, a step or operation can be implemented in which a complementary mold is fabricated by casting the fibers with silicone rubber. Then, as described at block 120, a step or operation is implemented, which this mold is cast with a rigid polyurethane (e.g., Crystal Clear 200; Smooth-On) on an acrylic backing to obtain diverging pillar arrays such as those utilized in the disclosed experimental embodiments.

It is understood that the specific order or hierarchy of steps, operations, or instructions in method 100 is an illustration of an exemplary process. Based upon design preferences, it is understood that the specific order or hierarchy of such steps, operation or instructions in such a process as discussed and illustrated herein may be rearranged. The accompanying claims, for example, present elements of various steps, operations or instructions in a sample order, and are not meant to be limited to the specific order or hierarchy presented.

Flow separation and vortex shedding are some of the most common phenomena experienced by bluff bodies under relative motion with the surrounding medium. They often result in a recirculation bubble in regions with adverse pressure gradient, which typically reduces efficiency in vehicles and increases loading on structures. As discussed herein, the ability of an engineered coating to manipulate the large-scale recirculation region was tested in a separated flow at moderate momentum thickness Reynolds number, Re_θ=1,200. The disclosed embodiments demonstrate that the coating, composed of uniformly distributed cylindrical pillars with diverging tips, successfully reduces the size of, and shifts downstream, the separation bubble. Despite the so-called roughness parameter, k⁺≈1, falling within the hydrodynamic smooth regime, the coating is able to modulate the large-scale recirculating motion. Remarkably, this modulation does not induce noticeable changes in the near-wall turbulence levels. Supported with experimental data and theoretical arguments based on the averaged equations of motion, the inventors suggest that the inherent mechanism responsible for the bubble modulation is essentially unsteady suction and blowing controlled by the increasing cross-section of the tips. The coating can be easily fabricated and installed and works under dry and wet conditions, increasing its potential impact on a diverse range of applications.

It should be appreciated that the disclosed coating offers a number of advantages. For example, in addition to facilitating a reducing in noise and vibrations due to the disclosed reduction in the size of the separation bubble, such a coating also facilitates a reduction in drag (i.e., recall that the coating can be implemented in dry or wet conditions). One particular area where the disclosed coating offers an advantage is the field of biofouling. Biofouling or biological fouling involves the accumulation of microorganisms, plants, algae, or animals on wetted surfaces. Such accumulation is referred to as epibiosis when the host surface is another organism and the relationship is not parasitic.

Antifouling is the ability of specifically designed materials and coatings such as the coating described herein to remove or prevent biofouling by any number of organisms on wetted surfaces. Since biofouling can occur almost anywhere water is present, biofouling poses risks to a wide variety of objects such as medical devices and membranes, as well as to entire industries, such as paper manufacturing, food processing, underwater construction, and desalination plants. Thus, the disclosed coating can comprise in some alternative example embodiments, an antifouling coating or material.

Based on the foregoing, it can be appreciated that a number of preferred and alternative example embodiments are disclosed herein. For example, in one embodiment a coating apparatus or device can be configured which includes a coating composed of a plurality of fibrillar structures, wherein each fibrillar structure among the plurality of fibrillar structures is configured with a diverging tip so that the coating reduces a size of and shifts downstream, a separation bubble, and modulates large-scale recirculating motion. The coating can facilitate a reduction in noise and vibrations due to the reduction in the size of the separation bubble. The coating also facilitates a reduction in drag. In an example embodiment, the coating can be configured as an antifouling coating.

Each fibrillar structure among the plurality of fibrillar structures comprises a cylindrical micropillar and the plurality of fibrillar structures comprises a plurality of uniformly distributed cylindrical micropillars. In addition, the coating can be configured to function under a dry condition or a wet condition. Additionally, the coating is configured to mitigate flow separation without a noticeable increase in a production of turbulent kinetic energy.

The coating also can be configured in some example embodiments to include a microsurface coating that shifts the separation point downstream and reduces the area of negative flow. In addition, the coating can be configured to rely on the generation of distributed wall-normal perturbations. In another example embodiment, the coating can include a micropillar coating composed of the aforementioned plurality of fibrillar structures.

It will be appreciated that variations of the above-disclosed and other features and functions, or alternatives thereof, may be desirably combined into many other different systems or applications. It will also be appreciated that various presently unforeseen or unanticipated alternatives, modifications, variations or improvements therein may be subsequently made by those skilled in the art, which are also intended to be encompassed by the following claims.

Claims

1. A coating apparatus, comprising

a coating comprising a plurality of fibrillar structures, wherein each fibrillar structure among said plurality of fibrillar structures is configured with a diverging tip so that said coating reduces a size of and shifts downstream, a separation bubble, and modulates large-scale recirculating motion.

2. The apparatus of claim 1 wherein said coating facilitates a reduction in noise and vibrations due to said reduction in said size of said separation bubble.

3. The apparatus of claim 1 wherein said coating facilitates a reduction in drag.

4. The apparatus of claim 1 wherein said coating comprises an antifouling coating.

5. The apparatus of claim 1 wherein each fibrillar structure among said plurality of fibrillar structures comprises a cylindrical micropillar and said plurality of fibrillar structures comprises a plurality of uniformly distributed cylindrical micropillars.

6. The apparatus of claim 1 wherein said coating is configured to function under a dry condition.

7. The apparatus of claim 1 wherein said coating is configured to function under a wet condition.

8. The apparatus of claim 1 wherein said coating mitigates flow separation without a noticeable increase in a production of turbulent kinetic energy.

9. The apparatus of claim 1 wherein said coating comprises a microsurface coating that shifts a separation point downstream and reduces an area of negative flow.

10. The apparatus of claim 1 wherein said coating relies on a generation of distributed wall-normal perturbations.

11. The apparatus of claim 1 wherein said coating comprises a micropillar coating comprising said plurality of fibrillar structures.

12. A coating apparatus, comprising

a coating that facilitates a reduction in noise and vibrations, said coating comprising a plurality of fibrillar structures, wherein each fibrillar structure among said plurality of fibrillar stuctures is configured with a diverging tip so that said coating reduces a size of and shifts downstream, a separation bubble, and modulates large-scale recirculating motion and wherein said each fibrillar structure among said plurality of fibrillar structures comprises a cylindrical micropillar, said plurality of fibrillar structures comprising a plurality of uniformly distributed cylindrical micropillars and wherein said coating facilitates said reduction of said noise and vibrations due to said reduction in said size of said separation bubble.

13. The apparatus of claim 12 wherein said coating further facilitates a reduction in drag.

14. The apparatus of claim 12 wherein said coating further facilitates a prevention of or a reduction in biofouling.

15. The apparatus of claim 12 wherein said coating is configured to function under either wet or dry conditions.

16. The apparatus of claim 12 wherein said coating comprises a bio-inspired surface coating.

17. The apparatus of claim 12 wherein said coating mitigates flow separation without a noticeable increase in a production of turbulent kinetic energy.

18. The apparatus of claim 12 wherein said coating comprises a microsurface coating that shifts a separation point downstream and reduces an area of negative flow.

19. The apparatus of claim 12 wherein said coating relies on a generation of distributed wall-normal perturbations.

20. A method of configuring a coating apparatus, said method comprising:

providing a coating comprising a plurality of fibrillar structures;

configuring each fibrillar structure among said plurality of fibrillar stuctures with a diverging tip so that said coating reduces a size of and shifts downstream, a separation bubble, and modulates large-scale recirculating motion, wherein said coating facilitates a reduction in noise and vibrations due to said reduction in said size of said separation bubble, and further facilitates a reduction in drag.