WO2014109670A2 - Procédé et appareil permettant d'obtenir un écoulement laminaire de gaz ou de liquide à proximité d'arêtes - Google Patents
Procédé et appareil permettant d'obtenir un écoulement laminaire de gaz ou de liquide à proximité d'arêtes Download PDFInfo
- Publication number
- WO2014109670A2 WO2014109670A2 PCT/RU2013/001035 RU2013001035W WO2014109670A2 WO 2014109670 A2 WO2014109670 A2 WO 2014109670A2 RU 2013001035 W RU2013001035 W RU 2013001035W WO 2014109670 A2 WO2014109670 A2 WO 2014109670A2
- Authority
- WO
- WIPO (PCT)
- Prior art keywords
- point
- cutting edge
- term
- true
- aerodynamic
- Prior art date
Links
- 239000007788 liquid Substances 0.000 title abstract description 8
- 238000000034 method Methods 0.000 title description 2
- 238000000926 separation method Methods 0.000 abstract description 11
- 238000010276 construction Methods 0.000 abstract description 6
- 241000272517 Anseriformes Species 0.000 abstract description 2
- 239000000969 carrier Substances 0.000 abstract description 2
- 230000006872 improvement Effects 0.000 abstract description 2
- 230000009467 reduction Effects 0.000 abstract description 2
- 230000003111 delayed effect Effects 0.000 description 3
- 239000012530 fluid Substances 0.000 description 3
- 230000008901 benefit Effects 0.000 description 1
- 230000008859 change Effects 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 239000007787 solid Substances 0.000 description 1
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C21/00—Influencing air flow over aircraft surfaces by affecting boundary layer flow
- B64C21/10—Influencing air flow over aircraft surfaces by affecting boundary layer flow using other surface properties, e.g. roughness
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F03—MACHINES OR ENGINES FOR LIQUIDS; WIND, SPRING, OR WEIGHT MOTORS; PRODUCING MECHANICAL POWER OR A REACTIVE PROPULSIVE THRUST, NOT OTHERWISE PROVIDED FOR
- F03D—WIND MOTORS
- F03D1/00—Wind motors with rotation axis substantially parallel to the air flow entering the rotor
- F03D1/06—Rotors
- F03D1/0608—Rotors characterised by their aerodynamic shape
- F03D1/0633—Rotors characterised by their aerodynamic shape of the blades
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F15—FLUID-PRESSURE ACTUATORS; HYDRAULICS OR PNEUMATICS IN GENERAL
- F15D—FLUID DYNAMICS, i.e. METHODS OR MEANS FOR INFLUENCING THE FLOW OF GASES OR LIQUIDS
- F15D1/00—Influencing flow of fluids
- F15D1/10—Influencing flow of fluids around bodies of solid material
- F15D1/12—Influencing flow of fluids around bodies of solid material by influencing the boundary layer
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B63—SHIPS OR OTHER WATERBORNE VESSELS; RELATED EQUIPMENT
- B63B—SHIPS OR OTHER WATERBORNE VESSELS; EQUIPMENT FOR SHIPPING
- B63B1/00—Hydrodynamic or hydrostatic features of hulls or of hydrofoils
- B63B1/02—Hydrodynamic or hydrostatic features of hulls or of hydrofoils deriving lift mainly from water displacement
- B63B1/04—Hydrodynamic or hydrostatic features of hulls or of hydrofoils deriving lift mainly from water displacement with single hull
- B63B1/06—Shape of fore part
- B63B1/063—Bulbous bows
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B63—SHIPS OR OTHER WATERBORNE VESSELS; RELATED EQUIPMENT
- B63B—SHIPS OR OTHER WATERBORNE VESSELS; EQUIPMENT FOR SHIPPING
- B63B1/00—Hydrodynamic or hydrostatic features of hulls or of hydrofoils
- B63B1/32—Other means for varying the inherent hydrodynamic characteristics of hulls
- B63B1/34—Other means for varying the inherent hydrodynamic characteristics of hulls by reducing surface friction
- B63B1/36—Other means for varying the inherent hydrodynamic characteristics of hulls by reducing surface friction using mechanical means
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C2230/00—Boundary layer controls
- B64C2230/26—Boundary layer controls by using rib lets or hydrophobic surfaces
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05B—INDEXING SCHEME RELATING TO WIND, SPRING, WEIGHT, INERTIA OR LIKE MOTORS, TO MACHINES OR ENGINES FOR LIQUIDS COVERED BY SUBCLASSES F03B, F03D AND F03G
- F05B2250/00—Geometry
- F05B2250/60—Structure; Surface texture
- F05B2250/61—Structure; Surface texture corrugated
- F05B2250/611—Structure; Surface texture corrugated undulated
-
- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02E—REDUCTION OF GREENHOUSE GAS [GHG] EMISSIONS, RELATED TO ENERGY GENERATION, TRANSMISSION OR DISTRIBUTION
- Y02E10/00—Energy generation through renewable energy sources
- Y02E10/70—Wind energy
- Y02E10/72—Wind turbines with rotation axis in wind direction
-
- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T50/00—Aeronautics or air transport
- Y02T50/10—Drag reduction
-
- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T70/00—Maritime or waterways transport
- Y02T70/10—Measures concerning design or construction of watercraft hulls
Definitions
- the invention relates to an apparatus for reducing turbulent drag, especially in aircraft and watercraft.
- the forms of surfaces are described, which delay or prevent boundary layer separation without creating an undesirable drag penalty.
- These forms jean be used for turbulent drag reduction of surfaces in a flow of gas or liquid, for example, for inner surface of a tube.
- This invention relates to aerodynamic and hydrodynamic components having leading edge devices for the improvement of performance, for example, for construction of bulbous bows for bulk carriers.
- aerodynamic and hydrodynamic component is used herein to encompass structures having an airfoil or hydrofoil section and leading edge. This term
- wings is intended to include wings, fins, tailplanes, canards, engine components such as turbine and compressor blades, propeller blades, helicopter rotor blades, and similar items.
- the ideal fluid model can be used as model of flow of gas or liquid in some distance from surfaces of solid bodies. Near these surfaces the boundary layer lays,
- the ideal fluid model has no solutions for nfinite velocity. So the appearance of vortexes and the separation of the boundary layer in these cases are impossible or delayed near the cutting edges. As a result the flow is steady there and the turbulent drag is absent.
- This effect can be used not only for any edge of construction, but for reducing the turbulent drag on the surfaces of bodies as well. For example, for reducing the turbulent drag on the surfaces of aircraft or watercraft units, or on the inner surface of tube. For this purpose we need to create the shape of these surfaces characterized by an array of spaced cutting edges, near which the separation of the boundary layer is delayed or prevented, so the average value of turbulent drag will be reduced.
- Fig.l, Fig.2, Fig.3 are three different views of surface, for which the claim 1.1 is true in point P.
- Fig.4 are surfaces, for which the claim 1.2.1 is true in crossing line between points D and E.
- Fig.5 are surfaces, for which the claim 1.2 is true. In crossing line between points F, G and between points G, H the claim 1.2.1 is true. In the point G the claim 1.2.2 is true.
- Fig.6 and Fig.7 are examples of surface, which has array of spaced cutting edges, for which claim 1.2.1 is true.
- Fig.8 is example of surface, which has array of spaced cutting edges, for which the-claim 2 is true: in any point of cutting edge, where flat elements do not touch, the claim ⁇ .2 ⁇ is true; in points, where flat elements do touch, the claim 1.2.2 s true.
- Fig.9 is profile of few crossed surfaces, which can be modified for achieving laminarity of flow of gas or liquid near point P as Fig.10, Fig.l 1 show.
- Fig.10 and Fig.l 1 are two variants of modification of profile Fig.9 for achieving laminarity of flow of gas or liquid near point P, where the claim 1.1 is true.
- Fig.12 is scheme of bulk carrier with bulbous bow.
- Fig.13 is prototype of bulbous bow for bulk carrier, in which the claim 1.1 is true in point A, as Fig.l, Fig.2, Fig.3 show, and the claim 2 is true in the region marked by letter C, where it can be used for surfaces such as in Fig 6, Fig.7 arid Fig.8.
- Fig.14 is scheme of wind power plant.
- Fig.15 is prototype of the blade of wind power plant, where for the leading and trailing edges the claim 1.2.1 is true. These edges are marked by letter B.
- Fig.16 and Fig.17 are two views of part of the blade from Fig.15.
- Fig.18 is scheme of aircraft showing the regions, where the claims of invention can be used: regions marked by letter A are for the use of claim 1.1; regions marked by letter B are for the use of claim 1.2; regions marked by letter C are for the use of claim 2.
- Fig.19 and Fig.20 are two views of the part of prototype for wing of an aircraft with leading-edge slat, where claim 1.2.1 is true for the leading and trailing edges.
- the claim 1.1 is true in point P. It can be used, for example, as part of the bulbous bow Fig.13 in point A of bulk carrier shown in Fig.12. In region, marked by letter C in Fig.13, where the initial boundary layer separation is possible, the profiles Fig.6, Fig.7, Fig.8 of surface can be used. For profiles Fig.6, Fig.7 and Fig.8 of surface the claim 2 is true. The average value of turbulent drag reduces near these surfaces.
- the variant of blade shown in Fig.15, Fig.16 and Fig 17 can be used.
- the leading and trailing cutting edges of the blade marked by letter B in Fig.15, that are shown in Fig.16 and Fig.17, the claim 1.2.1 is true.
- This profile with the cutting edge is an alternative to the profile of smooth surface, in which the drag of laminar flow near leading cutting edge is generally lower.
- the trailing cutting edge for which the claim 1.2 is true, is also preferred to the profile of smooth surface or traditional trailing cutting edge with profile of a wedge, because the appearance of vortex near this cutting edge is delayed or prevented.
- Fig.18 there is possibility for the use the invention in the regions, marked by letters A, B, C.
- the claim 1.1 can be used.
- the variants for this use are shown in Fig.l, Fig.2, Fig.3 and in Fig.10, Fig.l 1 as well.
- initial profile of surface is shown in Fig.9 .
- the variant with solitary point as cutting edge is preferred, the achieving of laminarity of flow near some point on the line of cutting edge or the crossing of cutting edges, as shown in Fig.9 in point P, is also possible. In this case
- claim 2 can be used for reducing the extent of turbulent drag by delaying or preventing the separation of the boundary layer there.
- Fig.6, Fig.7 and Fig.8 are showing some of possible profiles of such surfaces, for which the claim 2 is true.
- the profile in Fig.8 is more suitable for places, where the flow can change direction.
- the claim 2 and surfaces Fig.6, Fig.7, Fig.8 can be used for reducing the turbulent 4rag of the surfaces of tubes or underwater constructions.
- the best mode for carrying out the invention includes full realization of claims conditions in part of surface near a cutting edge.
- the best mode is the embodiment of the surface, which touches the cones with different aperture angles in maximum possible number of tangent rays in the point of cutting edge.
- the best mode is the embodiment, when one of crossing surface is plane.
- the best mode is the embodiment, where an array of spaced cutting edges lays in the regions, where the initial separation of the boundary layer is possible.
Landscapes
- Engineering & Computer Science (AREA)
- Physics & Mathematics (AREA)
- Fluid Mechanics (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Life Sciences & Earth Sciences (AREA)
- Aviation & Aerospace Engineering (AREA)
- Sustainable Development (AREA)
- Sustainable Energy (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
- Wind Motors (AREA)
Abstract
L'invention concerne un appareil permettant de réduire la traînée turbulente, en particulier dans des aéronefs et des véhicules marins. Sont décrites les formes de surfaces qui ralentissent ou empêchent le décollement de la couche limite sans affecter la traînée de manière indésirable. Ces formes peuvent être utilisées pour réduire la traînée turbulente de surfaces dans un écoulement de gaz ou de liquide, par exemple, pour la surface intérieure d'un tube. L'invention concerne des composants aérodynamiques et hydrodynamiques présentant des dispositifs de bord d'attaque pour l'amélioration des performances, par exemple, pour la construction d'étraves à bulbe destinées à des vraquiers. Le terme "composant aérodynamique et hydrodynamique" désigne ici des structures présentant une surface portante ou une section de profil d'aubes et un bord d'attaque. Ce terme englobe des ailes, ailettes, empennages horizontaux, empennages canards, composants de moteur, tels que des aubes de turbine et de compresseur, des pales d'hélice, des pales de rotor d'hélicoptère, et des articles similaires.
Priority Applications (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
PCT/RU2013/001035 WO2014109670A2 (fr) | 2013-11-19 | 2013-11-19 | Procédé et appareil permettant d'obtenir un écoulement laminaire de gaz ou de liquide à proximité d'arêtes |
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
PCT/RU2013/001035 WO2014109670A2 (fr) | 2013-11-19 | 2013-11-19 | Procédé et appareil permettant d'obtenir un écoulement laminaire de gaz ou de liquide à proximité d'arêtes |
Publications (2)
Publication Number | Publication Date |
---|---|
WO2014109670A2 true WO2014109670A2 (fr) | 2014-07-17 |
WO2014109670A3 WO2014109670A3 (fr) | 2014-10-23 |
Family
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PCT/RU2013/001035 WO2014109670A2 (fr) | 2013-11-19 | 2013-11-19 | Procédé et appareil permettant d'obtenir un écoulement laminaire de gaz ou de liquide à proximité d'arêtes |
Country Status (1)
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WO (1) | WO2014109670A2 (fr) |
Cited By (1)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
CN112977713A (zh) * | 2021-04-07 | 2021-06-18 | 浙江海洋大学 | 一种用于螺旋桨式船舶的涡流发生器及船舶 |
Citations (3)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
WO1992005341A1 (fr) * | 1990-09-14 | 1992-04-02 | Josef Moser | Rotor |
DE4208751A1 (de) * | 1992-02-27 | 1993-11-11 | Fritz Karl Hausser | Gezahnte Fronten, Kanten oder Ränder als Verfahren zur Verringerung des Widerstandes von gasförmige und flüssige Gegenstände |
RU2294300C2 (ru) * | 2005-03-22 | 2007-02-27 | Институт теоретической и прикладной механики СО РАН (ИТПМ СО РАН) | Несущая поверхность |
-
2013
- 2013-11-19 WO PCT/RU2013/001035 patent/WO2014109670A2/fr active Application Filing
Patent Citations (3)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
WO1992005341A1 (fr) * | 1990-09-14 | 1992-04-02 | Josef Moser | Rotor |
DE4208751A1 (de) * | 1992-02-27 | 1993-11-11 | Fritz Karl Hausser | Gezahnte Fronten, Kanten oder Ränder als Verfahren zur Verringerung des Widerstandes von gasförmige und flüssige Gegenstände |
RU2294300C2 (ru) * | 2005-03-22 | 2007-02-27 | Институт теоретической и прикладной механики СО РАН (ИТПМ СО РАН) | Несущая поверхность |
Cited By (1)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
CN112977713A (zh) * | 2021-04-07 | 2021-06-18 | 浙江海洋大学 | 一种用于螺旋桨式船舶的涡流发生器及船舶 |
Also Published As
Publication number | Publication date |
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WO2014109670A3 (fr) | 2014-10-23 |
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