<abstract xmlns="http://www.w3.org/1999/xhtml"><p>Injecting a liquid into a gas-filled vessel while in weightlessness can result in at least two conditions–a droplet attached to the wall around the injection orifice and a geyser in which the liquid propagates away from the orifice in a continuous jet. The need to design injection of liquid to accomplish one condition or the other shows up in both zero-<italic>g</italic> fluids research geometries and spaceflight systems. Previous experiments by others assumed the rim of the injection orifice to be sharp. Liquid flow out of orifices with chamfered and rounded rims during the weightlessness of parabolic aircraft flight are studied in this work. When compared to previous work, results indicate that chamfered and rounded rims have little effect on the value of Weber number dividing the wall-bound droplet and geyser behaviors. Because any manufactured orifice will have finite bluntness, this conclusion is useful for both research and spaceflight systems.</p></abstract>

Injecting a liquid into a gas-filled vessel while in weightlessness can result in at least two conditions–a droplet attached to the wall around the injection orifice and a geyser in which the liquid propagates away from the orifice in a continuous jet. The need to design injection of liquid to accomplish one condition or the other shows up in both zero-g fluids research geometries and spaceflight systems. Previous experiments by others assumed the rim of the injection orifice to be sharp. Liquid flow out of orifices with chamfered and rounded rims during the weightlessness of parabolic aircraft flight are studied in this work. When compared to previous work, results indicate that chamfered and rounded rims have little effect on the value of Weber number dividing the wall-bound droplet and geyser behaviors. Because any manufactured orifice will have finite bluntness, this conclusion is useful for both research and spaceflight systems.


<div xmlns="http://www.w3.org/1999/xhtml"><sec id="j_gsr-2017-0003_s_001_w2aab3b7c22b1b6b1ab1aAa"><div>INTRODUCTION</div><p>Several drop tower experiments in the first two decades of U.S. spaceflight studied the initial flow of a liquid injected into a gas-filled vessel. It was recognized early (<a ref-type="bibr" href="#j_gsr-2017-0003_ref_004_w2aab3b7c22b1b6b1ab2b1b4Aa">Symons et al., 1968</a>) that in the absence of gravity, the relative magnitudes of the momentum of the liquid flow and the capillary pressure difference across the free surface, described now as a Weber number, determine whether the liquid forms a droplet attached to the wall or if the liquid travels out into the vessel as a “geyser.” The droplet and geyser conditions are sketched in <a ref-type="fig" href="#j_gsr-2017-0003_fig_001_w2aab3b7c22b1b6b1ab1ab2Aa">Figure 1</a> and sample images from flight-test videos are presented in <a ref-type="fig" href="#j_gsr-2017-0003_fig_002_w2aab3b7c22b1b6b1ab1ab3Aa">Figure 2</a>. The droplet is the lower momentum result and the geyser the higher momentum result. The division between these two results is of interest. Presumably, a significant additional increase in liquid momentum could result in a spray of the liquid but such high speeds are not of interest here.</p><figure id="j_gsr-2017-0003_fig_001_w2aab3b7c22b1b6b1ab1ab2Aa" position="float" fig-type="figure"><h2>Figure 1</h2><figCaption><p>Droplet and geyser geometries – light gray is the liquid, dark gray is the solid. White background is the air. Sharp orifice rims are shown here; see below for the bluntness types examined in the present research.</p></figCaption><img xmlns:xlink="http://www.w3.org/1999/xlink" xlink:href="graphic/j_gsr-2017-0003_fig_001.jpg" src="https://sciendo-parsed.s3.eu-central-1.amazonaws.com/6471e254215d2f6c89db3f28/j_gsr-2017-0003_fig_001.jpg?X-Amz-Algorithm=AWS4-HMAC-SHA256&amp;X-Amz-Date=20240520T211331Z&amp;X-Amz-SignedHeaders=host&amp;X-Amz-Expires=18000&amp;X-Amz-Credential=AKIA6AP2G7AKP25APDM2%2F20240520%2Feu-central-1%2Fs3%2Faws4_request&amp;X-Amz-Signature=056caa7b6afddd9923968022d1eeb246763e05d6bcd67f4d0c07bab2d1318b45" class="mw-100"/></figure><figure id="j_gsr-2017-0003_fig_002_w2aab3b7c22b1b6b1ab1ab3Aa" position="float" fig-type="figure"><h2>Figure 2</h2><figCaption><p>Droplet (left) and geyser (right) images from flight test of 0.48 cm diameter orifices (the two images are presented at the same scale). The small droplets in the foreground of the right image are residues of a test during a previous parabola and are in the fields of view but are not interacting with the hole or the jet.</p></figCaption><img xmlns:xlink="http://www.w3.org/1999/xlink" xlink:href="graphic/j_gsr-2017-0003_fig_002.jpg" src="https://sciendo-parsed.s3.eu-central-1.amazonaws.com/6471e254215d2f6c89db3f28/j_gsr-2017-0003_fig_002.jpg?X-Amz-Algorithm=AWS4-HMAC-SHA256&amp;X-Amz-Date=20240520T211331Z&amp;X-Amz-SignedHeaders=host&amp;X-Amz-Expires=18000&amp;X-Amz-Credential=AKIA6AP2G7AKP25APDM2%2F20240520%2Feu-central-1%2Fs3%2Faws4_request&amp;X-Amz-Signature=d2fe936bc040b4779d87485024c5d8f62616119134cf0db7f0eb5fa6bfc85fc1" class="mw-100"/></figure><p>Early work was apparently motivated by spacecraft systems, with liquid injected into vessels representing propellant tanks (<a ref-type="bibr" href="#j_gsr-2017-0003_ref_004_w2aab3b7c22b1b6b1ab2b1b4Aa">Symons et al., 1968</a>; <a ref-type="bibr" href="#j_gsr-2017-0003_ref_005_w2aab3b7c22b1b6b1ab2b1b5Aa">Symons and Nussle, 1969</a>) including non-zero low gravity (<a ref-type="bibr" href="#j_gsr-2017-0003_ref_003_w2aab3b7c22b1b6b1ab2b1b3Aa">Spuckler, 1972</a>). Note that the droplet versus geyser question does not limit tank filling rates; subsequent research explored a solution or two for how to fill a tank rapidly without geysering (<a ref-type="bibr" href="#j_gsr-2017-0003_ref_001_w2aab3b7c22b1b6b1ab2b1b1Aa">Abdalla and Andracchio, 1968</a>; <a ref-type="bibr" href="#j_gsr-2017-0003_ref_002_w2aab3b7c22b1b6b1ab2b1b2Aa">Labus et al., 1972</a>). In fluids research, the droplet versus geyser question remains relevant, e.g., recent creative drop tower experiments depend on the existence of a geyser formation at the exit of a miniature nozzle (<a ref-type="bibr" href="#j_gsr-2017-0003_ref_008_w2aab3b7c22b1b6b1ab2b1b8Aa">Wollman et al., 2016</a>). Many drop tower and flight experiments depend on injecting a volume of liquid that remains a droplet and wets the wall around an orifice.</p><p>The earlier drop tower experiments examined the flow of a liquid injected out of an orifice with what is described as a “sharp” rim. Yet there must have been some finite, albeit small, bluntness of some form at the rim of the orifice as it is not possible to manufacture a hole, especially in acrylic, with a mathematically sharp rim. Just how sharp a hole could be considered sharp and what effect larger bluntness on the rim would have on the division between droplet and geyser formation (without regard to specific applications) are the focus of the experiments in this work.</p></sec><sec id="j_gsr-2017-0003_s_002_w2aab3b7c22b1b6b1ab1b1Aa"><div>MATERIALS AND METHODS</div><p>The relative influence of liquid momentum and capillary pressure difference across the free surface, such as in the droplet sketch and image of <a ref-type="fig" href="#j_gsr-2017-0003_fig_001_w2aab3b7c22b1b6b1ab1ab2Aa">Figures 1</a> and <a ref-type="fig" href="#j_gsr-2017-0003_fig_002_w2aab3b7c22b1b6b1ab1ab3Aa">2</a>, respectively, is quantified by a Weber number,
<disp-formula id="j_gsr-2017-0003_ueq_001_w2aab3b7c22b1b6b1ab1b1b1b5Aa"><alternatives><graphic xmlns:xlink="http://www.w3.org/1999/xlink" xlink:href="graphic/j_gsr-2017-0003_ueq_001.png"></graphic><math xmlns:mml="http://www.w3.org/1998/Math/MathML"><mrow><mi>We</mi><mo>=</mo><mfrac><mrow><mi>ρ</mi><msup><mi>V</mi><mn>2</mn></msup><mi>R</mi></mrow><mi>σ</mi></mfrac></mrow></math><tex-math>We = {{\rho {V^2}R} \over \sigma}</tex-math></alternatives></disp-formula>
where the liquid density is <italic>ρ</italic> (gas density is assumed negligible), the mean velocity of the liquid in the hole is <italic>V</italic>, orifice radius is <italic>R</italic>, and surface tension is <italic>σ</italic>. Deionized water is the test liquid, with ambient cabin pressure approximately the atmospheric pressure at 2,400 m altitude (75 kPa) and the ambient temperature varied between 17 and 22°C. Weber number can be viewed as the ratio of the dynamic pressure of the liquid flow to the capillary pressure difference for a hemisphere of radius equal to the orifice radius, with a factor of 4 dropped from the denominator. A spherical cap is the zero-<italic>g</italic> solution for a static liquid on the rim of the orifice, and the maximum capillary pressure difference is at minimum radius for the spherical cap, which is equal to the radius of the hole.</p><p>When the Weber number is large, the flow is dominated by liquid momentum, likely resulting in a geyser. When the Weber number is small, capillary effects dominate, and should cause a droplet to form on the wall. The question addressed in earlier work and this one is: what value of the Weber number separates the two behaviors?</p><p>To test the behavior of injected liquid through orifices of differing geometries on the rim, as shown in <a ref-type="fig" href="#j_gsr-2017-0003_fig_003_w2aab3b7c22b1b6b1ab1b1b4Aa">Figure 3</a>, experimental apparatus was designed for parabolic aircraft flight testing. Three types of rims on the orifices are explored–sharp, chamfered, and rounded. “Sharp” cannot be interpreted literally. In this case is the label refers to rim bluntness as fine as can be machined on the transparent acrylic plates. The sharp orifice for which results are reported here has a rounding with a radius of no more than 0.04 cm. The small orifices have diameter of 0.48 cm and large orifices are 0.64 cm diameter. Chamfer on the small and large orifices enlarges the holes to 0.70 cm and 0.95 cm diameter, respectively, at the surface of the plate. The rounded rim on the large hole is a radius of approximately 0.16 cm.</p><figure id="j_gsr-2017-0003_fig_003_w2aab3b7c22b1b6b1ab1b1b4Aa" position="float" fig-type="figure"><h2>Figure 3</h2><figCaption><p>Injection hole edge conditions. In this geometry, the liquid flow, when present, was upwards from the hole.</p></figCaption><img xmlns:xlink="http://www.w3.org/1999/xlink" xlink:href="graphic/j_gsr-2017-0003_fig_003.jpg" src="https://sciendo-parsed.s3.eu-central-1.amazonaws.com/6471e254215d2f6c89db3f28/j_gsr-2017-0003_fig_003.jpg?X-Amz-Algorithm=AWS4-HMAC-SHA256&amp;X-Amz-Date=20240520T211331Z&amp;X-Amz-SignedHeaders=host&amp;X-Amz-Expires=18000&amp;X-Amz-Credential=AKIA6AP2G7AKP25APDM2%2F20240520%2Feu-central-1%2Fs3%2Faws4_request&amp;X-Amz-Signature=c4bb2999193022e3cedef9fbcc08e9325e1a2b07529a550e703659ef5f9b5a4b" class="mw-100"/></figure><p>Two flights of thirty parabolas each in January, 2009 were provided by the (now defunct) NASA Reduced Gravity Student Flight Opportunity Program. Each day tested three orifices in parallel with various controlled flow rates of water. Three video camcorders (640 × 480 resolution, 30 fps) recorded the water as it exited the orifice. One camera failed during the flights, and thus, there are data from only four orifices analyzed in this paper. A wide range of Weber numbers were created during the first flight and results permitted adjustment of the testing plan for the second day. On the second day, the range of Weber numbers were reduced so that more experiments were conducted closer to the values of Weber numbers dividing the droplet from the geyser results.</p><p>The major components of the experiment apparatus are sketched in <a ref-type="fig" href="#j_gsr-2017-0003_fig_004_w2aab3b7c22b1b6b1ab1b1b7Aa">Figure 4</a>. Operation for each parabola began when the nominally weightless period of the flight started and the stepper motor actuated the three pistons that pushed additional water into the plenums under the orifices causing water to flow through and out of the orifices for several seconds. Motor control was calibrated before flight to produce the desired water flow speeds through the orifices. When the viewing window is occluded by droplets, the plunger is used to wipe the window clean without breaking the double containment of the liquid. The face of the plate is, in general, partially wetted because it is found in flight that it is impractical to actuate the plunger before every parabola. A testing plan that scheduled the desired flow velocities was prepared and followed for each flight.</p><figure id="j_gsr-2017-0003_fig_004_w2aab3b7c22b1b6b1ab1b1b7Aa" position="float" fig-type="figure"><h2>Figure 4</h2><figCaption><p>Photograph of experiment bolted to the floor on board the 727 of the Zero-G Corporation. The transparent box in the left half of the frame is the second level of containment around the test sections.</p></figCaption><img xmlns:xlink="http://www.w3.org/1999/xlink" xlink:href="graphic/j_gsr-2017-0003_fig_004.jpg" src="https://sciendo-parsed.s3.eu-central-1.amazonaws.com/6471e254215d2f6c89db3f28/j_gsr-2017-0003_fig_004.jpg?X-Amz-Algorithm=AWS4-HMAC-SHA256&amp;X-Amz-Date=20240520T211331Z&amp;X-Amz-SignedHeaders=host&amp;X-Amz-Expires=18000&amp;X-Amz-Credential=AKIA6AP2G7AKP25APDM2%2F20240520%2Feu-central-1%2Fs3%2Faws4_request&amp;X-Amz-Signature=0d63411e33a0cc4fbe5879b8733095386f0ae24696b7906bb27f3ce03161427e" class="mw-100"/></figure><p>The video data were analyzed after the flights. For each parabola, the state of the injected fluid was assessed as a droplet, a geyser, or an indeterminate case. An indeterminate result included situations like a wall-bound drop with a satellite drop ejected out the end of the main drop, a droplet shearing off to the side, or similar, which are caused by the g-jitter of the flight.</p></sec><sec id="j_gsr-2017-0003_s_003_w2aab3b7c22b1b6b1ab1b2Aa"><div>RESULTS</div><p>All droplet, geyser, and indeterminate results from the four orifices with video records are presented versus their respective Weber number in <a ref-type="fig" href="#j_gsr-2017-0003_fig_006_w2aab3b7c22b1b6b1ab1b2b3Aa">Figure 6</a>. Uncertainty in the Weber number is primarily from uncertainty in the surface tension of the water in the testing environment several hours after being loaded into the experiment. As a result, uncertainty in Weber number is estimated to be approximately ± 0.08. Density of 1 g cm<sup>−3</sup>, surface tension of 70 dyne cm<sup>−1</sup>, and the orifice radius are used in computing the Weber numbers. Uncertainty in classification, which is represented in the vertical direction in <a ref-type="fig" href="#j_gsr-2017-0003_fig_006_w2aab3b7c22b1b6b1ab1b2b3Aa">Figure 6</a>, is absent because of the use of the indeterminate classification for collecting all of the uncertain results. Also shown in <a ref-type="fig" href="#j_gsr-2017-0003_fig_006_w2aab3b7c22b1b6b1ab1b2b3Aa">Figure 6</a> is a vertical dotted line for the previous result of <italic>We</italic> = 1.3 (<a ref-type="bibr" href="#j_gsr-2017-0003_ref_004_w2aab3b7c22b1b6b1ab2b1b4Aa">Symons et al., 1968</a>; <a ref-type="bibr" href="#j_gsr-2017-0003_ref_006_w2aab3b7c22b1b6b1ab2b1b6Aa">Symons, 1970</a>).</p><figure id="j_gsr-2017-0003_fig_005_w2aab3b7c22b1b6b1ab1b2b2Aa" position="float" fig-type="figure"><h2>Figure 5</h2><figCaption><p>Experiment components, initial condition. One fluid system is shown in this view; there are two additional systems, identical except for the orifice size or rim shape, behind this system.</p></figCaption><img xmlns:xlink="http://www.w3.org/1999/xlink" xlink:href="graphic/j_gsr-2017-0003_fig_005.jpg" src="https://sciendo-parsed.s3.eu-central-1.amazonaws.com/6471e254215d2f6c89db3f28/j_gsr-2017-0003_fig_005.jpg?X-Amz-Algorithm=AWS4-HMAC-SHA256&amp;X-Amz-Date=20240520T211331Z&amp;X-Amz-SignedHeaders=host&amp;X-Amz-Expires=18000&amp;X-Amz-Credential=AKIA6AP2G7AKP25APDM2%2F20240520%2Feu-central-1%2Fs3%2Faws4_request&amp;X-Amz-Signature=677891964fffe15142dec7e6fff4e405eb8ebe56d3991dddf8c26d5a21e8c738" class="mw-100"/></figure><figure id="j_gsr-2017-0003_fig_006_w2aab3b7c22b1b6b1ab1b2b3Aa" position="float" fig-type="figure"><h2>Figure 6</h2><figCaption><p>All of the data from four holes over two flights.</p></figCaption><img xmlns:xlink="http://www.w3.org/1999/xlink" xlink:href="graphic/j_gsr-2017-0003_fig_006.jpg" src="https://sciendo-parsed.s3.eu-central-1.amazonaws.com/6471e254215d2f6c89db3f28/j_gsr-2017-0003_fig_006.jpg?X-Amz-Algorithm=AWS4-HMAC-SHA256&amp;X-Amz-Date=20240520T211331Z&amp;X-Amz-SignedHeaders=host&amp;X-Amz-Expires=18000&amp;X-Amz-Credential=AKIA6AP2G7AKP25APDM2%2F20240520%2Feu-central-1%2Fs3%2Faws4_request&amp;X-Amz-Signature=692fb52ffd0a6f621a555553d4ecf5a020f5854999af92bf99d20a567ebe9076" class="mw-100"/></figure></sec><sec id="j_gsr-2017-0003_s_004_w2aab3b7c22b1b6b1ab1b3Aa"><div>DISCUSSION</div><p>The maximum Weber number for dependable droplet formation is shown to be 1.25. This is consistent with the previous result of 1.3, given the uncertainty in Weber number. The minimum Weber number for dependable geyser formation is 2.0. Intermediate values of Weber number produce all three classes of results, for all four orifices. This may be the effect of g-jitter of the aircraft, a residual droplet from the preceding parabola, or other phenomena. This indeterminate condition in 1.25 &lt; <italic>We</italic> &lt; 2 is not inconsistent with the earlier drop tower work in which conditions are described as “unstable” above <italic>We</italic> = 1.3.</p><p>The indeterminate result at <italic>We</italic> = 0.25 stands out as unique. This case could not be classified completely as a droplet. <italic>G</italic>-jitter of the flight or a sticky spot for the piston driving this flow may have influenced this result. Many things can affect the droplet formation event. For example, it has even been shown that a reduction in draining rate can cause ejection of droplets (<a ref-type="bibr" href="#j_gsr-2017-0003_ref_007_w2aab3b7c22b1b6b1ab2b1b7Aa">Symons, 1974</a>).</p><p>Note that the chamfered and rounded rims are found to have no clear impact on the Weber numbers below which the droplet is formed or above which the geyser is formed. This intolerance of the results to condition of the rim of the orifice does simplify design and fabrication requirements for propellant tanks and fluids experiments alike, absent increasing importance of other phenomena.</p><p>It appears that the determination of the Weber number separating droplet and geyser production from parabolic flight experiments is found to be less precise than in experiments in drop towers. The more quiescent <italic>g</italic>-environment and the opportunity to clean the apparatus before each drop are the likely causes of lower ambiguity. This ambiguity may be of little consequence because in designing either a fluids experiment or a propellant transfer system, one would design to create a Weber number a safe distance away from the transition Weber number range.</p><p>Note that only a drop tower with the ability to drop frequently each day can produce data as rapidly as parabolic flight testing, such as would be beneficial for investigating larger chamfer sizes and rounding radii on droplet and geyser formation. In spite of the increased uncertainty compared to drop tower testing, the data in this paper from the investigation of different orifice rim geometries are new.</p></sec></div>

Injecting a Liquid in Weightlessness: Droplet or Geyser Formation

Gravitational and Space Research

This work is licensed under the Creative Commons Attribution-NonCommercial-NoDerivatives 3.0 License.

{"article-title":"Injecting a Liquid in Weightlessness: Droplet or Geyser Formation"}

Injecting a liquid into a gas-filled vessel while in weightlessness can result in at least two conditions–a droplet attached to the wall around the injection...

Injecting a Liquid in Weightlessness: Droplet or Geyser Formation

Article Category: Research Article

Published Online: Jul 20, 2020

Page range: 35 - 40

DOI: https://doi.org/10.2478/gsr-2017-0003

Keywords
Droplet Formation, Liquid Injection, Fluid Dynamics

© 2017 Steven H. Collicott et al., published by Sciendo

This work is licensed under the Creative Commons Attribution-NonCommercial-NoDerivatives 3.0 License.

Injecting a Liquid in Weightlessness: Droplet or Geyser Formation

Article Category: Research Article

Published Online: Jul 20, 2020

Page range: 35 - 40

DOI: https://doi.org/10.2478/gsr-2017-0003

KeywordsDroplet Formation, Liquid Injection, Fluid Dynamics

© 2017 Steven H. Collicott et al., published by Sciendo

This work is licensed under the Creative Commons Attribution-NonCommercial-NoDerivatives 3.0 License.

Keywords
Droplet Formation, Liquid Injection, Fluid Dynamics