The present invention relates to a closure assembly configured to be mounted to a container.

Closure assemblies are known with a plastic cap that is releasably attached to a neck of a spout fitted on a collapsible pouch container. Furthermore it is known that such plastic caps are provided with a pair of wings extending from the skirt on opposing sides of the cap.

The wings of such a closure assembly can aid in opening the closure assembly mounted on the container by allowing a user to manually apply a force upon these wings and thus generating a torque on the cap. Some of these wings might even be provided with, or comprise, an integrated strap as shown in W02020/221801. However, the provision of such a pair of wings requires the use of additional plastic material for the production of the cap of the closure assembly. Especially since the size of the wings is, in many cases, also determined to be of such size that they prevent the cap of the closure assembly from being accidentally swallowed.

It is desirable to use as little plastic material as possible during the production process of the closure assemblies. Simply reducing the thickness of the wings and thus the amount of material used for the wings while retaining their practical size would result in a reduction of the stiffness of the wings and may cause problems during injection molding and/or during handling of the cap, e.g. during opening of the closure assembly.

In an effort to optimize the required plastic material whilst providing sufficient stiffness of the wings several designs are known, for instance from WO2018/194454.

A problem with current state of the art is that the industry is now approaching a limit in the amount of material that can be removed from the thickness of the wings without the wings losing so much stiffness that they cannot properly perform their initial function of receiving a force and transferring this as a torque to the cap of the closure assembly.

The object of this invention is to provide a novel approach to improving the stiffness of the wings.

An additional benefit or secondary objective is that the necessary amount of plastic material can be further reduced. The invention provides a closure assembly according to claim 1.

According to the invention an increase in the ability of the wings to convert a force acting perpendicularly upon the sides of the wings by a user into a torque acting upon the cap of the closure assembly is achieved by means of providing each wing with a center portion that includes at least one corrugation. This corrugated center portion adjoins the skirt of the cap and is located between the base portion and the top portion of the wing.

From prior art document US5188250 a twist off closure is known having a cap with wings. The wings may include wing portions that are horizontally rippled for increased strength. These ripples are provide over the entire height of the wing.

According to the invention, the base portion and the top portion are substantially flat. For example, the flat base portion and top portion are located in a common vertical plane.

This lifting or sinking of the corrugations with respect to the substantially flat base portion and substantially flat top portion is beneficial e.g. for production purposes, ease of use, stiffness, storage etc.

The flat base and top portions of the wings have a technical role during the injection moulding. During injection moulding the molten plastic is injected under high pressure into the mould. In order to assure that no leakage between the mold halves occurs a high closing force is required. When edges of the moulded product would be positioned under an angle, as is the case with corrugations extending to the periphery of the wing, such as e.g. in prior art document US5188250, the mold halves have to be aligned very precise and tolerances are very strict.

The mold halves normally used during production of these caps contain a large number of cavities such that a large number of caps is produced during each production cycle.

The slightest misalignment between the mold halves would result in leakage and formation of burrs. Aligning flat surfaces, in particular the flat top and base portions of the wings according to the present invention, is easier than aligning multiple angles surfaces. Hence, according to the invention, the tolerances during injection moulding are alleviated and the chances of leakage are reduced when the flat top and base portion is present. The at least one corrugation extends along the length of the wing, preferably over a majority of the length, e.g. at least 75% of the length, and forms a groove on each of the sides of the wing. In a sideways view onto the wing, e.g. a sideways cross-sectional view, the corrugation forms an alternating waveform, e.g. a sinusoidal shape.

In a practical embodiment, seen in a view from above, the at least one corrugation in the center portion of the wing tapers off towards the tip of the wing. So, the depth of the grooves associated with the corrugation reduces gradually in direction from the skirt towards the tip of the wing. In an embodiment, the tapering corrugation merges towards to tip of the wing with the substantially flat base portion and substantially flat top portion of the wing, e.g. in a smooth transition. For example, the corrugation tapers into a tip of the wing that is substantially flat.

In a practical embodiment, the at least one corrugation is substantially parallel to the lateral extending direction of the wings.

In a practical embodiment, the one or more corrugations are perpendicular to the vertical main axis of the tubular neck at least in a closed configuration of the closure assembly.

In a practical embodiment, the at least one corrugation extends at an angle with respect to the lateral extension of the wings, e.g. of less than 60 degrees, e.g. of less than 45 degrees.

The depth of the grooves associated with a corrugation is related to the increase in robustness and/or stiffness of the wing. In practical embodiments, the depth is the greatest where the corrugation adjoins the skirt of the cap and then gradually reduces towards the tip of the wing.

Not only the depth of the grooves defined by the corrugation plays a role, but also the height of the grooves is of influence.

The stability achieved by the provision of the corrugation can be predicted by appropriate finite element calculations and/or by the testing of prototypes.

In embodiments, the largest height of the one or more corrugations is less than 80% of the largest height of the wing, e.g. 80% of the largest sum of the height of the base portion, the center portion, and the top portion of the wing. For example, the largest depth and/or height of the grooves of the at least one corrugation is between 2 mm and 5 mm.

When multiple corrugations are present in the center portion of the wing, the corrugations may be identical in geometry. In other embodiments, they are not identical, e.g. they differ in view of the largest depth and/or largest height of their associated grooves and/or in view of the extension along the length of the wing.

In embodiments, the center portion of the wing is larger than the top portion and/or of the base portion of the respective wing, e.g. the height of the center portion being larger, e.g. larger than the combined maximum height of the top portion and base portion.

In embodiments, the center part of the wing comprises at least two corrugations, wherein these corrugations are formed in opposite directions with respect to a main surface of the wing.

In embodiments, the center part of the wing comprises at least two corrugations.

In embodiments, the center part of the wing comprises corrugations formed in opposite directions, wherein the corrugations are offset from a main surface of the wing such that one of the two sides of the wing does not have any protrusions past its surface as a result of the corrugations.

In embodiments, the increase in stability/stiffness achieved by the provision of the one or more corrugations is most prevalent in the bending stiffness in a direction perpendicular to the opening direction of the cap.

In embodiments, the one or more corrugations as seen from the side of the wing have a sinusoidal shape.

In embodiments, the corrugations as seen from the side of the wing have a shape substantially similar to a square wave.

In embodiments, the tapering of the one or more grooves formed by the corrugation is achieved by decreasing the amplitude of the wave form shape along the length of the wing. In embodiments, the one or more grooves form an alternating waveform along the length of the groove centered around the main surface of the wing, e.g. incorporating two perpendicularly oriented waveforms over the surface of the wing.

In an embodiment, the alternating waveform along the length of the groove decreases in amplitude along the length of the wing.

The invention will now be explained in more detail with reference to the appended drawings.

In the drawings:

Fig. 1 shows a schematic of a closure assembly with a winged cap,

Fig. 2 shows a schematic of a closure assembly with an illustrated corrugation in the wings, Fig. 3a, 3b and 3c show a schematic cross-sectional sideview of a wing of a closure assembly,

Fig. 3d shows a schematic view of a wing without tapering of the corrugation towards the tip of the wing,

Fig. 3e and 3f show a schematic view of a wing with illustrated tapering of the corrugation, Fig. 4a shows a schematic cross-sectional sideview of a wing with multiple corrugations, Fig. 4b. shows a schematic view of a wing with multiple corrugations,

Fig. 5a, 5b and 5c show schematic cross-sectional side views of wings of a closure assembly,

Fig. 6a and 6b show schematic cross-sectional side views of wings of a closure assembly comprising corrugations with variable heights,

Figs. 7a, 7b, 7c, 7d, 7e, 7f and 7g show several schematic cross-sectional side views of wings illustrating various corrugation forms,

Fig 8. shows a first practical embodiment of a closure assembly comprising corrugated wings,

Fig 9. shows a second practical embodiment of a closure assembly comprising corrugated wings,

Fig 10. shows a third practical embodiment of a closure assembly comprising corrugated wings.

Figure 1 shows a schematic figure of a closure assembly with a winged cap 2.

The closure assembly comprises a spout 1 (mostly hidden by the cap 2). The spout 1 has spout body that is injection moulded of plastic material. The figure shows an attachment portion 3 of the spout body that is sealed to a container 4.

Not visible is the tubular neck above the portion 3 as it is hidden under the cap. As known in the art, a product passage extends through the attachment portion and the neck of the spout. The tubular neck has a vertical main axis and forms a mouth at a top end of the product passage allowing to dispense a product from the container 4. The neck has an exterior side.

The cap 2 is a rotational cap that is injection moulded of plastic material and that illustrated in a position secured on the neck of the spout in a closed position of the cap 2 on the neck such that the cap seals the product passage. The cap 2, for removal of the cap from the neck of the spout by a user to open the product passage, is adapted to be manually rotated from the closed position in an opening direction.

Generally, the plastic cap 2 comprises a top wall 2a and a downward depending skirt 2b. The skirt has an interior side, an exterior side, and a lower edge remote from the top wall 2a. For example, a tamper-evident structure is provided at the lower edge of the skirt.

The cap 2 has two wings 5, so a single pair of wings 5. It is illustrated, as preferred, that - in view from above - the two wings 5 of the cap 2 are generally aligned with a top edge of the pouch 4 when the cap is closed, e.g. before first time opening of the closure.

The wings 5 are integrally moulded of plastic material with the rest of the cap 2. The wings 5 extend generally vertically and outward in a lateral direction over a wing length in substantially opposite directions from an inner end to a tip of the wing that is remote from the skirt.

In figure 2 the same schematic figure of a closure assembly is shown with the addition of a schematic illustration of a single corrugation 6 according to the invention in a center portion of the wing. The wings 5 are shown to each further include a flat top portion 10a and a flat base portion 10b, respectively above and below the center portion with the corrugation.

In figure 2, the flat top portion 10a and a flat base portion 10b extend in a common vertical plane.

The point where the wing 5 connects with the skirt cap is referred to as the inner end or junction 7 of the wing. The end of the wing furthest away from the skirt 2b cap is referred to as the tip 8 of the wing 5. It is illustrated that the wing tip is a flat wing tip 11 that adjoins the ends of the portion 10a, 10b to form a flat contour along the top, tip, and bottom delineation of the corrugated center portion.

Furthermore a cross sectional indication line X is shown illustrating a cross section location used for further clarification of the corrugation.

Figures 3a, 3b and 3c show side views of three different embodiments of a wing of the closure assembly, seen in direction of arrow III in figure 2.

The side view 3a illustrates a corrugation 12 in the wing 5 of the closure assembly with an alternating waveform, here a sinusoidal shape, wherein the corrugation 12 does not taper to the edges and the tip of the wing 5. So, both the depth “d” and the height “h” of the grooves 12a, 12b associated with the single corrugation 12 are constant over the length of the corrugation.

In figure 3a the flat top portion 10a, and flat bottom portion 10b extend in a common vertical plane.

In figure 3a, the corrugation 12 extends in sinusoidal form relative to a vertical plane.

Figure 3b shows a corrugation 12’ that tapers off towards the tip 11 of the wing 5. This tapering can be recognized by several cross sections X1 , X2 and X3 shown in figure 3b, which correspond to various positions along the length of the wing 5 such that a reduced amplitude of the sinusoidal shape at each cross section towards the tip of the wing becomes apparent. As preferred, the greatest depth of the grooves 12a, b is where the center portion adjoins the skirt 2b of the cap.

In figure 3c a corrugation 12’ is illustrated that not only tapers towards the tip 11 of the wing 5 but simultaneously tapers towards a lengthwise axis of the wing 5. In the illustrated embodiment, this tapering occurs towards an axis along the middle of the wing in lengthwise direction but an axis under an angle or an axis translated over the width of the wing can be envisioned as alternative embodiments. It is illustrated in the cross-sections X4,X5, X6 that both the depth and the height of the grooves associated with the corrugation reduces from the inner end of the wing 5 towards the tip of the wing. Figures 3d, 3e and 3f each show a schematic 3-dimensional representation of an embodiment of a corrugated wing according to the invention.

Figure 3d matches with figure 3a, wherein the sinusoidal shape of the corrugation 12 does not taper off towards the tip of the wing 5.

Figure 3e matches with figure 3b, wherein the sinusoidal shape of the corrugation 12’ can be seen to taper off towards the tip of the wing 5 by a diminishing amplitude of the sinusoidal shape towards the tip of the wing.

Figure 3f matches with figure 3c, wherein the sinusoidal shape of the corrugation can be seen to taper off towards the tip of the wing as well as towards an axis M along the length of the wing.

From the schematic 3-dimensional representations of the wing embodiments in figures 3d, 3e and 3f it can also be seen that the wing 5 comprises, in addition to the corrugation 12 or 12’, the flat portions 10a, 10b above and below the center portion with the corrugation 12 or 12’.

A tip zone 11 located at the tip of the wing which can, but not necessarily is, substantially flat.

The corrugations in the wings of figures 2 and 3a, 3b, 3c, 3d, 3e have a single peak and a single valley in the cross-sectional sinusoidal shape of the corrugation 12 and 12’.

The one or more corrugations of the wing center portion comprise a minimum of a one peak and one valley, e.g. in sinusoidal form.

A corrugated wing can comprise more than a single corrugation, e g. as is shown in figures 4a and 4b.

Depending on the direction from which one sees the embodiment of the wing in figure 4a either two valleys and one peak or two peaks and one valley is shown thus giving 1 ,5 (one and a half) corrugation 12” in the wing of figure 4a. Three grooves 12a”, 12b”, and 12c” are present.

Figure 4b is a 3-dimensional schematic representation of a corrugated wing embodiment similar to the sideways cross-sectional view of 4a with a few notable differences. The first notable difference is the axis C1 along the sinusoidal shape in figure 4a which coincides with the substantially flat portions 20a, b such that the peaks and valleys of the corrugations are on one side of the axis C1. This as opposed to the axis C2 in figure 4b which cuts the corrugation such that the single valley lies below the axis C2 while the two peaks lie above the axis 02 when seen from the direction II along the length of the wing as shown in figure 4b.

From peak to valley and vice versa the corrugations in figure 4b transition through the axis 02 whereas the corrugations of figure 4a do not.

The substantially flat portions 24a, b from figure 4b still coincide with the axis C2 as is the case with the corrugations of figure 4a.

This illustrates that the corrugations can in principle be lifted out of or sunk into the plane defined by the wing 5. This lifting or sinking of the corrugations can in embodiments be beneficial for production purposes, ease of use, stiffness, storage etc.

Secondly, another observable difference between the corrugations of figure 4a and 4b are the smooth transitions 26 from the corrugation center portion to the substantially flat base and top portions 20a, b of the wing. These smooth transitions can in embodiments be omitted or introduced. The introduction or omission of which would serve aesthetics, production purposes, or ease of use.

Figures 5a and 5b again show these differences more clearly by setting the cross sectional view of a single corrugation in figure 5b alternating through a centerline next to a cross sectional view of 1 ,5x corrugations lifted out of the plane such that the corrugations do not cross the line coinciding with the edge zones.

Both corrugations in figures 5a and 5b illustrate the smooth transitions from the corrugations to the edge zones.

In yet another embodiment similar to the corrugations of figure 5a are the 1 ,5x corrugations seen in figure 5c wherein the wing has been curved along the curve 31 such that the edge zones 30 of the wing now smoothly transition into the corrugations without a curvature and help form the peaks of the corrugations.

Figure 5c also illustrates that the valley (or peak depending on the viewing direction) does not need to reach or cross the axis C3. Figures 6a and 6b show that the sinusoidal shape of the corrugations are not required to have equal amplitude and as such can, in embodiments, be varied.

Figures 7a, 7b, 7c, 7d, 7e, 7f and 7g show several schematic cross-sectional side views of wings illustrating various corrugation forms.

Figure 7a is included as reference again since it is similar to the right side of figure 6a wherein the cross section comprises 1.5x corrugations and wherein the amplitude of at least one the peaks (or valleys depending on viewing direction) is different from the others.

In figure 7b a more discretized sinusoidal waveform is shown, wherein the peaks and valleys of the corrugations are now made with straight lines and angles instead of continuous curves as is the case in figure 7a. The valley in between the two peaks of figure 7b also crosses the axis that coincides with the two substantially flat edge zones, but in embodiments this valley can coincide or stay on one side of this axis.

It is then understood that in light of the invention, a sinusoidal waveform is meant to include all types of waveforms such as square waves. More specifically, the term sinusoidal waveform is, in light of the invention, used to describe alternating waveforms.

Figure 7c shows a similar discretized sinusoidal waveform as in figure 7b although here a single corrugation has been used. The corrugation of figure 7c also crosses the axis that coincides with the two substantially flat edge zones as it transitions from a valley to a peak and vice versa.

In figure 7d a combination between the discretized and a normal sinusoidal waveform is introduced and furthermore it is shown that the edge zones are intentionally placed on different heights and no longer share a common coinciding axis.

It is not necessary to combine these two characteristics into the same embodiment, e.g. discretized vs. normal and non-coinciding edge zones axis. These characteristics are shown in the same embodiment to illustrate various options.

In figure 7e another such characteristic is introduced wherein the period of the waveform (i.e. the length of the wave or how far the wave has been stretched) changes within the waveform such that the peak and the valley of the corrugation are of different widths. We also see from figure 7e that the discretized waveform has been squished more together resulting in a shape more resembling a square wave. Forming this waveform which more resembles a square wave has an added benefit of increasing the angle of attack of the transitioning line 45 between the valley and the peak of the waveform. Changing the angle of attack of the transitioning line does not require a waveform resembling a square wave but can also be achieved by using the regular sinusoidal waveforms.

By increasing the angle of attack of the transitioning line 45 created by the transition between the valley and the peak of a corrugation the stiffness in the direction perpendicular to the surface of the wing can be influenced.

Furthermore the discretized waveform resembling a square wave of figure 7e has been provided with smooth transitions instead of sharp edges, although this too is optional and can be omitted in alternative embodiments.

These characteristics have in figure 7e been combined with different amplitudes of the peak and valley and edge zones without a common coinciding axis.

Figure 7f shows a combination of a rounded regular sinusoidal waveform with a waveform resembling a square wave of different periods with an optional edge zone coinciding axis illustrated by the dotted line.

Figure 7g shows yet another alternating waveform having a triangular or sawtooth shape. Here the waveform comprises 1.5x corrugations wherein the peaks and valleys of the waveform comprise different amplitudes.

For all waveforms, e.g. like the ones described above, more than 1.5x corrugations can be envisioned to be implemented in alternative embodiments. For example, (1 + n x 0.5) corrugations for n >0.

Figure 8 shows a first practical embodiment of a cap 2 of the closure assembly wherein the top and bottom portions 10a, 10b along the lengthwise edge of the wings are formed such that the overall wings create a leaflike resemblance.

One the wings of the closure assembly with its leaflike resemblance can here be seen to comprise an integrally formed strap 40 following a part of the contour of the wing. This strap, and several other embodiments of it, has been previously disclosed in W02020/221801 and is not a necessary or required part of this invention. It is here nonetheless described for the sake of clarity.

The strap 40 is here integral with the wing at or near the top portion 10a at a first attachment point 43.

Starting from the first attachment point 43 at or near the top portion 10a of the wing there is provided a cut-out or slot between the strap 40 and the wing 5 along the contour of the tip of the wing and the bottom portion 10b of the wing.

The strap further comprises a tamper-evident strap part 41 bridging the cut-out towards the wing.

The strap is integrated with a base part 45 of the cap 2 at a second attachment point 44. The base part 45 of the cap 2 is configured to be mounted on the attachment portion 3 of the closure assembly. The base part 45 also comprising tamper evident cap parts 46 connecting the base part 45 of the cap with the skirt of the cap 2b.

The tip of the wing with regards to the implementation of the corrugation on the strapped wing is here considered to be located before the strap.

A part of the tip zone on the strapped wing is here missing as a result of the cut-out 42.

The (single) corrugation tapers off towards the tip as was illustrated schematically in figure 3d.

The tip zone of the wing here is not flat but still contains the trailing edges of the tapering corrugation.

Figure 9 shows a second practical embodiment of a cap 2’ of the closure assembly wherein the top portion 10a of the wing overlaps more with the cap of the closure assembly. This can add stiffness and may also serve aesthetic purposes.

The bottom portions 10b of the wings in figure 9 are, in this embodiment, purely there for aesthetic purposes since they do not add stiffness to the wing when no bridging connection is made with the cap body. Here one of the wings again comprises a strap 40’ following the contour of the second embodiment of the wing. The strapped wing here also comprising a tamper-evident strap part 41 , a cut-out 42, a first attachment point 43 and a second attachment point 44.

The cap 2 comprises a base part 45 and tamper-evident cap parts 46.

Figure 10 shows a third practical embodiment of a cap 2” of the closure assembly wherein the wings have been provided with discretized corrugations similar to as was illustrated schematically in figure 7b.

In the practical embodiment of figure 10 however the corrugations taper off under an angle from the cap to the tip of the wings, similar to that which was described in the text corresponding to figure 3c.

Just as in the previous two embodiments one of the wings comprises a strap 40”. Here following the contour of the third embodiment of the wing. The strapped wing here also comprising a tamper-evident part 41 , a cut-out 42, a first attachment point 43 and a second attachment point 44. The cap 2 comprises a base part 45 and tamper-evident cap parts 46.