CN111611661A - Transverse V-shaped groove structure based on stable vortex string resistance reduction and application thereof - Google Patents

Transverse V-shaped groove structure based on stable vortex string resistance reduction and application thereof Download PDF

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CN111611661A
CN111611661A CN202010457823.2A CN202010457823A CN111611661A CN 111611661 A CN111611661 A CN 111611661A CN 202010457823 A CN202010457823 A CN 202010457823A CN 111611661 A CN111611661 A CN 111611661A
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groove
vortex
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shaped groove
groove structure
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CN111611661B (en
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李志平
潘天宇
贺龙
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Beihang University
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Abstract

The invention provides a transverse V-shaped groove structure based on stabilized vortex string resistance reduction, which is formed by combining a plurality of V-shaped grooves, wherein the arrangement direction of the V-shaped grooves is vertical to the flow direction of fluid, and the width of each V-shaped groove is W; the height of the V-shaped groove is H; the width-to-height ratio W/H of the V-shaped groove is 2. When the structure disclosed by the invention is used, stable boundary vortex can be generated in the V-shaped groove, so that the resistance reduction effect is obviously improved.

Description

Transverse V-shaped groove structure based on stable vortex string resistance reduction and application thereof
Technical Field
The disclosure relates to the technical field of airflow drag reduction, in particular to a transverse V-shaped groove structure based on stable vortex-string drag reduction and application thereof.
Background
In the aerospace field of wings, compressor blades, revolved bodies and the like, resistance is generated when fluid passes through the structure. Current drag reduction approaches typically employ additional control mechanisms or inject additional substances to achieve drag reduction. Therefore, the existing drag reduction technology needs additional injected substances, consumes additional energy, or is difficult to manufacture, high in cost and unstable in drag reduction effect.
Disclosure of Invention
In order to solve at least one of the above technical problems, the present disclosure provides a lateral V-groove structure based on stable vortex-string drag reduction, which utilizes a specific groove structure to form vortices in the groove, so that a flowing vortex-string boundary replaces a solid-wall boundary, thereby generating an efficient drag reduction effect.
According to one aspect of the disclosure, a transverse V-shaped groove structure based on stable vortex string resistance reduction is formed by combining a plurality of V-shaped grooves, the arrangement direction of the V-shaped grooves is perpendicular to the flow direction of fluid, and the width of each V-shaped groove is W; the height of the V-shaped groove is H; the width-to-height ratio W/H of the V-shaped groove is 2.
According to at least one embodiment of the present disclosure, the V-groove apex angle is 90 °.
According to at least one embodiment of the present disclosure, the height H of the V-groove is such that the fluid generates a stable vortex within the groove.
According to at least one embodiment of the present disclosure, the V-groove height H is determined by the fluid flow rate U and the fluid kinematic viscosity V, and:
Figure BDA0002509938440000011
wherein: the height of the V-shaped groove is H, and the unit of H is m; the flow rate of the fluid is U, and the unit of U is m/s; the kinematic viscosity of the fluid is upsilon, which is expressed in m2S; re represents the Reynolds number,
Figure BDA0002509938440000021
wherein L represents the characteristic length.
The present disclosure also provides a stable vortex string drag reduction-based wing with a transverse V-groove structure, wherein all or part of the surface of the wing has the above stable vortex string drag reduction-based transverse V-groove structure.
The present disclosure also provides a compressor blade of a transverse V-groove structure based on stabilized vortex-cluster drag reduction, wherein all or part of the surface of the compressor blade has the transverse V-groove structure based on stabilized vortex-cluster drag reduction as described above.
The present disclosure also provides a rotor of a transverse V-groove structure based on stabilized vortex-cluster drag reduction, wherein all or part of the surface of the rotor is the transverse V-groove structure based on stabilized vortex-cluster drag reduction as described above.
Drawings
The accompanying drawings, which are included to provide a further understanding of the disclosure and are incorporated in and constitute a part of this specification, illustrate exemplary embodiments of the disclosure and together with the description serve to explain the principles of the disclosure.
Fig. 1 is a schematic structural diagram in accordance with at least one embodiment of the present disclosure.
Fig. 2 is a schematic view of a stabilized vortex in accordance with at least one embodiment of the present disclosure.
Fig. 3 is a kinetic model of in-groove vortex stabilization according to at least one embodiment of the present disclosure.
Fig. 4 is a schematic illustration of vortex-string drag reduction according to at least one embodiment of the present disclosure.
Fig. 5 is a numerical experimental validation of vortex stabilization according to at least one embodiment of the present disclosure.
Figure 6 is an experimental verification of drag reduction characteristics according to the present disclosure.
Detailed Description
The present disclosure will be described in further detail with reference to the drawings and embodiments. It is to be understood that the specific embodiments described herein are for purposes of illustration only and are not to be construed as limitations of the present disclosure. It should be further noted that, for the convenience of description, only the portions relevant to the present disclosure are shown in the drawings.
It should be noted that the embodiments and features of the embodiments in the present disclosure may be combined with each other without conflict. The present disclosure will be described in detail below with reference to the accompanying drawings in conjunction with embodiments.
Examples
As shown in fig. 1, the present disclosure provides a transverse V-groove structure 100 based on stable vortex-induced drag reduction, the structure is formed by combining a plurality of V-grooves 1, the arrangement direction of the V-grooves is perpendicular to the flow direction of fluid, the direction indicated by arrows in fig. 1 is the flow direction of fluid, and the width of the V-grooves is W; setting the height of the V-shaped groove to be H, wherein the height H of the V-shaped groove is the height which enables the fluid to generate stable vortex in the groove; the width-to-height ratio W/H of the V-shaped groove is 2, and the vertex angle of the V-shaped groove is 90 degrees. As shown in fig. 2, the present disclosure realizes the formation of "vortex boundary" between fluid and solid by generating stable vortex in the groove through a specific transverse V-groove configuration, thereby reducing frictional resistance and realizing efficient drag reduction function, wherein the uppermost 2 transverse arrows in fig. 2 represent the flow direction of the fluid; the 3 clockwise arrows in the V-groove represent the in-groove swirl.
According to at least one embodiment of the present disclosure, the V-groove height H is determined by the fluid flow rate U and the fluid kinematic viscosity V, and:
Figure BDA0002509938440000031
wherein: the height of the V-shaped groove is H, and the unit of H is m; the flow rate of the fluid is U, and the unit of U is m/s; the kinematic viscosity of the fluid is upsilon, which is expressed in m2S; re represents the Reynolds number,
Figure BDA0002509938440000032
wherein L represents the characteristic length. The method simultaneously gives out the change rule of the control parameters along with the incoming flow, and achieves the optimal resistance reduction effect through the formula according to different incoming flow working conditions.
The transverse V-shaped groove adopted by the present disclosure is characterized by special geometrical characteristics: i.e. an aspect ratio of 2, ensures that the vortex is stable in the tank. The drag reduction principle of the present disclosure is: when the fluid vertically flows through the transverse V-shaped groove, a plurality of vortexes are formed in the V-shaped groove, and the vortexes are combined into a series of vortex strings. When the in-groove vortex stabilizes inside the V-groove, it turns the flow-solid boundary into a flow-flow slip boundary similar to a "fluid ball bearing", which will greatly reduce frictional resistance. As shown in fig. 3, from the viewpoint of vortex dynamics, the fixed wall acts on the in-groove vortex like two mirror-image vortices (1 and 2 in fig. 3) having equal and opposite vortex volumes, and the mirror-image vortex generates an induced velocity on the in-groove vortex. As shown in FIG. 3, U13Representing the induced velocity, U, of the mirror vortex 1 to the in-groove vortex 323Representing the velocity induced by the mirror vortex 2 to the in-groove vortex 3. U shapemRepresenting the combined induction of the mirror image vortexes 1 and 2 at the vortex core in the grooveVelocity, representing the migration velocity of the in-groove vortex at the in-groove vortex core,
Figure BDA0002509938440000041
representing the magnitude of the velocity of the migration flow at the slip plane. From the viewpoint of vortex dynamics, only when the induced velocity of the mirror vortex and the migration velocity of the migration flow to the vortex in the groove are superimposed to 0 at the vortex core in the groove, that is, in the figure
Figure BDA0002509938440000042
In the meantime, the vortex in the V-groove remains stable. In the present disclosure, a V-groove width-to-height ratio of 2 ensures
Figure BDA0002509938440000043
Under the necessary condition, the in-groove vortex is stabilized in the V-shaped groove, the resistance reduction schematic diagram is shown in fig. 4(a), a stable vortex is generated in the groove, the effect of the vortex on the boundary layer is similar to that of a sliding boundary, the fluid velocity is fuller, and the frictional resistance of the fluid is reduced; further, as shown in fig. 4(b) and 4(c), the V-groove aspect ratio is not 2, and the in-groove vortex left offset and the in-groove vortex right offset are respectively illustrated; the vortex is displaced with the fluid or is offset left and right in the groove, so that a stable sliding boundary cannot be formed, and a 'vortex locking' function cannot be realized, so that the optimal drag reduction effect cannot be achieved.
Effect verification vortex stability numerical experiment
According to the method, the two-dimensional flat plate is respectively provided with the transverse V-shaped grooves with the width-height ratio of more than 2, equal to 2 and less than 2, numerical experiments are carried out on the transverse V-shaped grooves, and the stability and the resistance reduction performance of the vortex are observed. As shown in fig. 5, which is a vorticity cloud chart of a numerical experiment, fig. 5(a) represents the movement of a vortex (as indicated by an arrow in fig. 5 (a)) when the width-to-height ratio of the transverse V-groove is greater than 2, and it can be seen that the vortex oscillates in the groove with the passage of time (74T to 80T). Fig. 5(c) represents a case where the width-to-height ratio of the transverse V-groove is less than 2, in which the vortex (indicated by an arrow in fig. 5 (c)) is mainly influenced by the mirror vortex, migrates along the solid wall in the groove, and migrates downstream by the migration flow. Fig. 5(b) represents a case where the width-to-height ratio of the transverse V-groove is equal to 2, where the vortex (indicated by the arrow in fig. 5 (b)) is very stably settled in the groove.
As shown in FIG. 6, a velocity vs. drag reduction ratio is given, where 0.1-0.2 represents a height of 0.1mm and a width of 0.2 mm. It can be seen that the aspect ratio of 2 (i.e., 0.1-0.2 for the transverse V-groove in the figure) is best at all operating conditions. This is because the vortex is stably stopped in the groove, so that a stable slip surface is formed, and efficient drag reduction is realized.
By adopting the scheme, the vortex can be stably stopped in the V-shaped groove, and the optimal resistance reduction effect is realized. For example: under the condition that the working condition of the incoming flow is 10m/s, compared with a transverse V-shaped groove with the width-height ratio of 1, the drag reduction rate is increased by more than 24.6%, and the drag reduction effect is obvious. It can be seen that boundary vortexes can be formed inside the transverse grooves, but only the transverse grooves with the shapes disclosed in the present disclosure can stabilize the boundary vortexes inside the V-grooves, so that stable sliding boundaries are formed, and efficient drag reduction is achieved.
The number of the V-shaped grooves is not limited, and the V-shaped grooves can be arranged in any length; no additional control device and injection of additional substances are required; the processing is simple, and the material is not limited; the method has wide application range and can be applied to the field of aerospace (wings, compressor blades and revolved bodies).
In the description herein, reference to the description of the terms "one embodiment/mode," "some embodiments/modes," "example," "specific example," or "some examples," etc., means that a particular feature, structure, material, or characteristic described in connection with the embodiment/mode or example is included in at least one embodiment/mode or example of the application. In this specification, the schematic representations of the terms used above are not necessarily intended to be the same embodiment/mode or example. Furthermore, the particular features, structures, materials, or characteristics described may be combined in any suitable manner in any one or more embodiments/modes or examples. Furthermore, the various embodiments/aspects or examples and features of the various embodiments/aspects or examples described in this specification can be combined and combined by one skilled in the art without conflicting therewith.
Furthermore, the terms "first", "second" and "first" are used for descriptive purposes only and are not to be construed as indicating or implying relative importance or implicitly indicating the number of technical features indicated. Thus, a feature defined as "first" or "second" may explicitly or implicitly include at least one such feature. In the description of the present application, "plurality" means at least two, e.g., two, three, etc., unless specifically limited otherwise.
It will be understood by those skilled in the art that the foregoing embodiments are merely for clarity of illustration of the disclosure and are not intended to limit the scope of the disclosure. Other variations or modifications may occur to those skilled in the art, based on the foregoing disclosure, and are still within the scope of the present disclosure.

Claims (6)

1. A transverse V-shaped groove structure based on stable vortex string resistance reduction is characterized in that the structure is formed by combining a plurality of V-shaped grooves, the arrangement direction of the V-shaped grooves is perpendicular to the flow direction of fluid, and the width of each V-shaped groove is W; the height of the V-shaped groove is H; the width-to-height ratio W/H of the V-shaped groove is 2.
2. The V-groove structure of claim 1, wherein the V-groove apex angle is 90 °.
3. The V-groove structure of claim 1 wherein the V-groove height H is determined by the fluid flow rate U and the fluid kinematic viscosity V, and:
Figure FDA0002509938430000011
wherein: the height of the V-shaped groove is H, and the unit of H is m; the flow rate of the fluid is U, and the unit of U is m/s; the kinematic viscosity of the fluid is upsilon, which is expressed in m2S; re represents the Reynolds number,
Figure FDA0002509938430000012
wherein L represents the characteristic length.
4. An airfoil having the stabilized vortex-string drag reduction-based transverse V-groove structure of any one of claims 1 to 3, wherein all or part of the surface of the airfoil has the stabilized vortex-string drag reduction-based transverse V-groove structure of any one of claims 1 to 4.
5. A compressor blade having the stabilized vortex-string drag reduction-based transverse V-groove structure of any one of claims 1 to 3, wherein all or part of the surface of the compressor blade has the stabilized vortex-string drag reduction-based transverse V-groove structure of any one of claims 1 to 4.
6. A rotor having the stabilized vortex-string drag reduction-based transverse V-groove structure of any one of claims 1 to 3, characterized in that all or part of the surface of the rotor has the stabilized vortex-string drag reduction-based transverse V-groove structure of any one of claims 1 to 3.
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Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN112550679A (en) * 2020-12-18 2021-03-26 上海机电工程研究所 Micro-nano resistance reduction structure for high-altitude high-speed environment
CN113158376A (en) * 2021-04-28 2021-07-23 中国人民解放军海军工程大学 Vortex eliminating structure of rectangular groove on inner wall of pump jet propeller guide pipe and design and processing method
CN113833719A (en) * 2021-09-15 2021-12-24 南京理工大学 Electromagnetic-groove composite damping device for marine navigation body

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* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN1479033A (en) * 2002-08-30 2004-03-03 清华大学 Cross texture microstructure surface and its use method on automobile
WO2013134657A1 (en) * 2012-03-08 2013-09-12 The University Of Alabama A passive drag modification system
CN103821801A (en) * 2014-02-23 2014-05-28 中国科学院工程热物理研究所 Resistance reducing rib
CN104613056A (en) * 2015-01-21 2015-05-13 北京超微上达科技有限公司 Bionic drag reduction surface for herringbone structure

Patent Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN1479033A (en) * 2002-08-30 2004-03-03 清华大学 Cross texture microstructure surface and its use method on automobile
WO2013134657A1 (en) * 2012-03-08 2013-09-12 The University Of Alabama A passive drag modification system
CN103821801A (en) * 2014-02-23 2014-05-28 中国科学院工程热物理研究所 Resistance reducing rib
CN104613056A (en) * 2015-01-21 2015-05-13 北京超微上达科技有限公司 Bionic drag reduction surface for herringbone structure

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN112550679A (en) * 2020-12-18 2021-03-26 上海机电工程研究所 Micro-nano resistance reduction structure for high-altitude high-speed environment
CN113158376A (en) * 2021-04-28 2021-07-23 中国人民解放军海军工程大学 Vortex eliminating structure of rectangular groove on inner wall of pump jet propeller guide pipe and design and processing method
CN113833719A (en) * 2021-09-15 2021-12-24 南京理工大学 Electromagnetic-groove composite damping device for marine navigation body

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