EP2570341A1 - Tuyère d'hélice - Google Patents

Tuyère d'hélice Download PDF

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Publication number
EP2570341A1
EP2570341A1 EP12184282A EP12184282A EP2570341A1 EP 2570341 A1 EP2570341 A1 EP 2570341A1 EP 12184282 A EP12184282 A EP 12184282A EP 12184282 A EP12184282 A EP 12184282A EP 2570341 A1 EP2570341 A1 EP 2570341A1
Authority
EP
European Patent Office
Prior art keywords
propeller
nozzle
flow
gap
wall
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Granted
Application number
EP12184282A
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German (de)
English (en)
Other versions
EP2570341B1 (fr
Inventor
Dr. Reinhard Schulze
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Becker Marine Systems GmbH and Co KG
Original Assignee
Becker Marine Systems GmbH and Co KG
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by Becker Marine Systems GmbH and Co KG filed Critical Becker Marine Systems GmbH and Co KG
Priority to PL12184282T priority Critical patent/PL2570341T3/pl
Publication of EP2570341A1 publication Critical patent/EP2570341A1/fr
Application granted granted Critical
Publication of EP2570341B1 publication Critical patent/EP2570341B1/fr
Priority to HRP20170432TT priority patent/HRP20170432T1/hr
Active legal-status Critical Current
Anticipated expiration legal-status Critical

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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B63—SHIPS OR OTHER WATERBORNE VESSELS; RELATED EQUIPMENT
    • B63H—MARINE PROPULSION OR STEERING
    • B63H5/00—Arrangements on vessels of propulsion elements directly acting on water
    • B63H5/07—Arrangements on vessels of propulsion elements directly acting on water of propellers
    • B63H5/14—Arrangements on vessels of propulsion elements directly acting on water of propellers characterised by being mounted in non-rotating ducts or rings, e.g. adjustable for steering purpose
    • B63H5/15—Nozzles, e.g. Kort-type
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B63—SHIPS OR OTHER WATERBORNE VESSELS; RELATED EQUIPMENT
    • B63H—MARINE PROPULSION OR STEERING
    • B63H5/00—Arrangements on vessels of propulsion elements directly acting on water
    • B63H5/07—Arrangements on vessels of propulsion elements directly acting on water of propellers
    • B63H5/14—Arrangements on vessels of propulsion elements directly acting on water of propellers characterised by being mounted in non-rotating ducts or rings, e.g. adjustable for steering purpose

Definitions

  • the present invention relates to a propeller nozzle, in particular for watercraft, such as ships.
  • propeller nozzles Drive units of watercraft, in particular of ships, are referred to as propeller nozzles, which comprise a propeller which is surrounded or encased by a nozzle ring or a nozzle.
  • Some embodiments of such nozzle rings or nozzles are also called "Kortdüsen”.
  • the arranged inside the nozzle propeller is normally fixed in Kortdüsen, d. h.,
  • the propeller is rotatable only about the drive or propeller axis.
  • the propeller via a rotatable, but not pivotable, along the propeller axis extending rigidly mounted propeller shaft is connected to the hull.
  • the propeller shaft is driven by a drive arranged in the hull.
  • the propeller is therefore not (horizontally or vertically) swiveled.
  • the nozzle is designed to be pivotable around the fixed propeller.
  • the Kortdüse be used to control the vessel.
  • additional maneuvering systems such as rudders, can be replaced or made superfluous.
  • pivotable is to be understood in the present case that the nozzle is pivotable from its starting position to starboard as well as to port by a predetermined angle.
  • Controllable Kortdüsen are usually not rotatable by a full 360 °.
  • propeller nozzles designed as rudder nozzles are those rudder nozzles in which the nozzle is fixed relative to the propeller, but the entire rudder nozzle, including nozzle and propeller, can be pivoted through 360 °.
  • Such propeller nozzles are sometimes referred to as nozzle-jacketed rudder propeller.
  • the nozzle or Kortdüse is normally an externally approximately tapered, preferably rotationally symmetrical trained pipe which forms the wall of the propeller nozzle.
  • the propeller nozzles can transfer an extra thrust to the vessel without increasing workload. In addition to propulsion-enhancing properties, this also reduces ramming movements in rough seas, which can reduce speed losses and increase course stability in heavy seas. Since the drag of the propeller nozzle or a Kortdüse increases approximately quadratically with increasing ship speed, its advantages are particularly effective for slow ships that need to produce a large propeller thrust (eg, tugs, fishing vessels, etc.).
  • the propellers arranged in the interior of the propeller nozzle comprise at least one, preferably a plurality of propeller blades (for example 3, 4 or 5 pieces).
  • the individual propeller blades protrude radially from the propeller hub located on the propeller shaft to the outside and are generally shaped identically and distributed at regular intervals around the propeller hub. By turning around the propeller shaft spreads the propeller blades on a propeller surface. This applies both to catchy screws, ie propeller nozzles with only one propeller blade, as well as variants with several propeller blades, in which case the several propeller blades together span the propeller surface.
  • this is a generally circular surface with the outer edge of the circular surface resting against the respective end portions of the propeller blades and outer propeller blade tips, respectively, and centered on the propeller shaft.
  • the propeller blade end regions correspondingly form the free end of each propeller blade, which in the radial direction is that part of the propeller blade that has the furthest distance from the propeller hub.
  • a propeller nozzle has both a flow inlet region and a flow outlet region, which together define a flow direction through which the water flows through the nozzle of the propeller nozzle when the (water) vehicle moves forwards.
  • the in the inner edge region of the nozzle d. H.
  • edge flow water flowing along, which in the course of its flow path through the propeller nozzle through the gap between Propellerhofflend Schemeen and inner wall of the nozzle, is referred to herein as edge flow. Since the gap in order to ensure functioning of the propeller nozzle, must be formed circumferentially around the propeller, the edge flow is also distributed circumferentially over the entire inner jacket of the nozzle.
  • the flow directors are configured to redirect at least a portion of the edge flow away from the normal flow path away from the gap and onto the propeller surface.
  • the fluids may direct at least a portion of the edge flow away from the interior wall of the nozzle and onto the propeller surface. This achieves that part of the edge flow that normally flows around the propeller blade end regions is instead directed to the propeller surface, where it is caught by the propeller blades and flows out as propeller nozzle outflow from the propeller nozzle, thus reducing vortex formation in the propeller nozzle.
  • the flow directing means are configured to divert at least a portion of the edge flow from its normal flow path along the inner wall of the nozzle and to the propeller surface, ie the propeller itself.
  • the edge flow is deflected by the flow guiding means from the edge or nozzle inner wall region.
  • this is the flow rate of the edge flow, the flows through the gap, reduced.
  • This leads to reduced turbulence in the region behind the propeller blade end region in the direction of flow and thereby to an improvement in the overall performance of the propeller nozzle.
  • the amount of water flowing through the gap between the end portion of the propeller blade and the nozzle inner wall in a defined period of time is therefore reduced by the flow-guiding means.
  • the flow guide means may have any structural configuration suitable for diverting a portion of the edge flow away from the normal flow path away from the gap and onto the propeller surface.
  • the flow-guiding means are preferably formed by a suitable design of the contour of the nozzle inner wall.
  • the flow directing means are adapted to direct a good portion of the edge flow, for example more than half, more than 60% or more than 75% of the edge flow, to the propeller surface.
  • the flow directors do not influence the dimensions of the gap or the gap dimension.
  • the gap expediently also in the present invention always at least the minimum gap required for the respective size of the propeller nozzle.
  • the gap has a thickness, d. H. a distance between the propeller blade end region and the inner wall of the nozzle, from 1% to 2% of the propeller diameter, preferably from 1.2% to 1.8%, on. Since the individual propeller blades are generally set in relation to the direction of flow of the propeller nozzle, the gap runs in the flow direction over the entire depth of the employed propeller blade.
  • the present propeller nozzle according to the invention can be executed both as a controllable variant (rudder nozzle) and as a fixed variant with a fixed, non-pivotable nozzle.
  • the controllable propeller nozzle may be formed, for example, as a controllable Kortdüse or as a 360 ° pivoting rudder nozzle.
  • the invention Advantages of lower circulation losses.
  • the propeller is preferably arranged in the propeller nozzle according to the invention in the flow direction between the center of the nozzle and the flow outlet region of the nozzle. Particularly preferred is an arrangement of the propeller between 50% and 70% of the nozzle length relative to the inlet edge of the nozzle in the flow inlet region.
  • rotationally symmetrical nozzles of the propeller is arranged with its propeller axis concentric to the nozzle axis, so that there is a circumferential gap of constant width ,
  • the present invention is applicable to both propeller blade fixed propeller blades and variable pitch propeller blades.
  • the propeller nozzle is used in water vehicles, such as ships.
  • the propeller nozzle according to the invention is not limited to this application and there are also other fields of use, such as e.g. in aviation, possible.
  • the propeller nozzle has at least one propeller blade. In principle, however, variants with several propeller blades, for example with 3, 4 or 5 propeller blades, are preferred.
  • the flow-guiding means are designed such that they either guide the edge flow away from the inner wall of the nozzle in the direction of the nozzle center and thus onto the propeller surface, or they make it possible to introduce or introduce the propeller surface into the region of the edge flow.
  • the flow directing means allows the propeller blade end portions to be expanded further outward, ie, to use a larger propeller, in comparison to prior art propeller nozzles of the same dimensions. Moving the propeller or propeller surface further outwards, part of the edge flow that would normally flow through the gap in propeller nozzles known in the art is directed onto the propeller surface without the edge flow from its normal flow path or their normal flow path must be distracted.
  • the power of the propeller nozzle is further increased by the enlargement of the propeller.
  • the deflection of the flow from the inner wall of the nozzle by the flow guide according to the first alternative described above is to be understood such that the flow is in particular derived obliquely away from the edge.
  • the flow-guiding means are arranged in the region of the propeller blade end regions or in the immediate vicinity of the gap or to the propeller blade end regions.
  • the term "immediate proximity to the gap" is to be understood in the present case such that the flow-guiding means can be arranged in the gap, upstream of the gap and / or downstream of the gap in the flow direction. That is, the flow guiding means may basically extend from a position immediately before the nip, through the nip, to a position directly behind the nip. If the fluids are arranged in front of and / or behind the gap, they are to be arranged adjacent to one another or at a distance such that they can still influence the edge flow in such a way that they are conducted at least partially onto the propeller surface.
  • the flow guide can basically be attached as separate components on the inner wall of the nozzle or in the wall or inner wall of the nozzle (integrally) be formed.
  • the flow-guiding means can be arranged only in one region or several separate regions of the nozzle.
  • the flow-guiding means are circumferentially formed in the circumferential direction of the nozzle in the sense of a ring. This will ensure that the entire edge flow into each area of the nozzle is influenced by the flow guide. As a result, the performance of the propeller nozzle is further improved.
  • these can also be formed only in the two portside or starboard-side lateral areas of the propeller nozzle, in particular in the case of controllable propeller nozzles, since the gap increases in these areas as a result of the pivoting of the propeller nozzle and thus increased turbulence can occur there.
  • the flow guiding means comprise one or more recesses in the inner wall or the wall of the nozzle.
  • the term "confiscation" in the present context a directed into the interior of the nozzle shell or the nozzle wall tapering of the nozzle in longitudinal section view or reduction of the nozzle thickness to understand, which differs from the profile profile of conventional nozzles.
  • the thickness or thickness of the nozzle or of the nozzle jacket is thus reduced by a larger factor in the region of the necking than immediately before and / or afterward.
  • the profile thickness of the nozzle in the region of the necking can be reduced by 2% to 50% of the profile nozzle thickness, preferably by 3 to 25%, particularly preferably by 5% to 15%, compared to the profile thickness of an identically dimensioned nozzle without recovery.
  • the length of the collection may be between 5% and 50%, preferably between 10% and 40%, more preferably between 20% and 30% of the total length of the nozzle.
  • the confiscation can only be designed circumferentially or viewed circumferentially of the nozzle. Due to the formation of a recess in the nozzle, it is possible, in the region of the collection or in the direction of flow, shortly after the propeller to be formed enlarged. Much of the edge flow arriving in the area of the recovery will not follow the profile of the nozzle in the area of the recovery, but instead will continue to follow its normal, straight flow path and thus peel off from the nozzle edge in the area of collection. Due to the enlarged design of the propeller In the area of confiscation, the propeller surface is thus introduced into the region of the edge flow, which then flows at least partially, instead of flowing through the now outwardly displaced gap, straight onto the propeller surface, or is detected by the propeller blades.
  • the collection is expediently arranged directly in front of or in the region of the propeller blade end regions or the gap.
  • the inner wall of the nozzle in the region of the necking in a profile view runs relatively quickly outward with respect to the nozzle. That is, the profile thickness of the nozzle decreases relatively quickly in the area of collection. This ensures that only a part of the edge flow follows this inward course and consequently the flow rate in the region of the gap is significantly reduced. Overall, thus results by the confinement of a sealing effect of the edge region of the nozzle or the gap. Further, it becomes possible over the prior art to use a larger diameter propeller, thereby further improving the performance of the propeller nozzle.
  • the necking can be of any shape as long as it reduces the nozzle profile in the area of necking.
  • the formation of the constriction with a curved profile line may be expedient, since then the course of the retraction can be adapted to the pivoting path of the nozzle, that the distance between the nozzle inner wall and Propellerhofflend Scheme, at least up to a certain Swivel angle, as constant as possible (small) remains.
  • the confiscation can go back to the normal profile profile of the nozzle or in any other way, for example in a straight line, continue to the nozzle end. If the nozzle profile behind the gap or the Propellererielend Schemeen viewed in the flow direction increases again, d. H. the nozzle wall thickness increases again, or the nozzle inner diameter decreases, the recovery is formed as a recess.
  • the formation of such a recess is particularly advantageous for pivotable propeller nozzles, as this is kept as small as possible in each of the two pivot directions. This applies to such pivoting angles, in which the propeller blade end region is still located in the region of the depression.
  • the recess results in an improved sealing effect, since the depression in the sense of a labyrinth seal seals the gap area and only an extremely small flow quantity flows through the gap.
  • This sealing effect occurs in particular when the propeller is designed and arranged in such a way that only the minimum distance between the end portion of the propeller blade and the inner wall (at the lowest point of the recess) exists, ie. h., The propeller blade end region is introduced into the region of the depression.
  • the profile of the nozzle wall is narrowed only in regions and thus substantially no or only a slight weakening of the nozzle structure occurs.
  • the recess may be formed in regions or even circumferentially, with a circumferential or closed-loop design results in a kind of closed or circumferential annular groove.
  • the profile of the recess extends in a longitudinal sectional view of the nozzle as a circular arc with the same curvature.
  • the curvature is advantageously matched to the pivoting of the nozzle in such a way that the gap or the distance between the end portion of the propeller blade and the inner wall within the recess is always substantially constant.
  • it may also be desired that the curvature is not formed constant, but in particular flatter toward the flow outlet side of the propeller nozzle runs, since the propellers are often inserted during assembly from this side into the nozzle and must be ensured that enough space for introducing the propeller into the nozzle.
  • the recess is formed as a spherical sphere or spherical. This is particularly advantageous in view of the fact that the propeller blades are usually employed and thus pivot over a certain length away from the depression.
  • the propeller blade end regions prefferably have a shape corresponding to the shape of the flow guiding means or the recess. Accordingly, in this embodiment as well, the propeller blade end region is to be provided with a spherical shape, wherein the sphere of the propeller blade end region should have the same curvature as the sphere of the depression, so that the gap remains constant up to a certain predetermined swivel angle of the nozzle.
  • the propeller blade end regions or the recesses are designed to correspond to one another in such a way that a corresponding formation is ensured even when the propeller blade blades are adjusted (adjustment of the angle of attack) or if the gap remains constant.
  • the flow guidance means comprise one or more projection bodies projecting from the inner wall of the nozzle.
  • the projection body (s) are expediently arranged in the immediate vicinity, in particular at least in the flow direction, before the gap, and designed such that they divert the edge flow or at least part of the edge flow away from the nozzle wall in the direction of the nozzle center or propeller surface.
  • the projection bodies may be formed as a circumferential bead in the circumferential direction of the nozzle. Such a bead would be aligned approximately parallel to the gap.
  • an additional bead can be arranged behind the gap. Alternatively, you can the contour of the nozzle inner wall viewed behind the gap in the longitudinal direction of the nozzle continues straight or without a projection body.
  • the projection body may be provided with a curvature, so that the gap remains as constant as possible (small) up to a certain pivot angle even when pivoting the nozzle.
  • the formation of the projection body is preferably adapted to the flow such that no or only little turbulence is generated by the projection body.
  • the protrusion bodies project into the interior of the nozzle and are designed to conduct the edge flow.
  • the design of the flow guide and the configuration of the Propellerhofflend Suitee are coordinated so that the gap up to a tilt angle of the nozzle of 5 °, preferably up to 10 °, more preferably up to 20 °, is substantially constant , Conveniently, all propeller blades are the same shape. In other words, the thickness of the gap remains in a given pivot angle range, ie. H. the distance between the end of the propeller blade and the inner wall of the nozzle is the same.
  • a pivotable propeller nozzle 100 is shown.
  • the propeller nozzle 100 comprises a nozzle 10, in the interior of which a propeller 20 is arranged.
  • the propeller 20 comprises a propeller hub 21 which lies centrally on the propeller axis 24. From the propeller hub 21 are in the radial direction four propeller blades 22 before (see Fig. 4 ).
  • the sectional views of the Fig. 1 to 3 For the sake of clarity, only two propeller blades 22 are shown.
  • the nozzle 10 is flowed through in the main flow direction 30 from the nozzle start 13 to the nozzle end 14 with water.
  • reference numerals 31 and 32 designate the flow inlet region or the flow outlet region of the nozzle 10.
  • a recess 15 is arranged. From a recess beginning 151 reduces the cross-section or the thickness of the nozzle profile to a lowest point of the recess 15, from which the cross-section or the thickness of the nozzle 10 increases again to a recess end 152. After the recess end 152 goes to Inner wall 12 back into the normal nozzle profile over. The deepest point of the recess 15 is located on the middle between the recess beginning 151 and the recess end 152. The recess 15 is circumferentially formed around the nozzle 10 circumferentially and therefore results in an annular groove.
  • the recess 15 is formed as a circular arc-shaped course in the surface of the inner wall 12 of the nozzle 10 and has a relatively flat curvature. As by the in the Fig. 1 . 2 and 3 drawn circle 16 can be seen, the recess 15 over the entire circumference of the nozzle 10 to a constant curvature.
  • the individual propeller blades 22 are inclined relative to a radial axis.
  • the propeller blade end region 23, ie the free end of the propeller blades 22, is likewise circular-arc-shaped or spherically shaped, the sphere or circular arc having the same curvature as the depression 15, so that the shape of the propeller blade end region 23 corresponds to the shape of the depression 15.
  • the curvature of the arc extends from the beginning 231 of the Propellererielend Schemees to the end 232 of the Propellerhoffend Schemees 23. Since the propeller blades 22 in, ie about its longitudinal axis, twisted or twisted, resulting in a spherical configuration of the Propellerhoffler Anlagenlend Symposium
  • the propeller nozzle 100 in the Fig. 1 is in the zero position, ie, it is not pivoted. In a ship mounted state, the ship would therefore be in straight ahead.
  • the nozzle axis 11, which extends centrally through the nozzle in the longitudinal direction, ie in the flow direction 30, and the propeller axis 24 lie on one another.
  • the nozzle 10 is pivoted in each case by a pivot angle ⁇ about the propeller axis 24.
  • the swivel angle ⁇ is 5 ° and in Fig. 3 10 °.
  • the propeller blade end regions 23 are located at a 10 ° -Verschwenkung opposite to the recess beginning 151 or well end 152. In other words, with a pivoting of more than 10 °, the propeller blade end regions 23 are located outside the recess 15. By contrast, up to a pivoting angle ⁇ of 10 °, the propeller blade end regions 23 are located within the recess 15. Due to the spherical configuration of the recess 15 and the propeller blade end regions 23 having the same curvature, the distance between the propeller blade end region 23 and the inner wall of the nozzle 12 and the thickness, respectively of the gap 40 in each case the same size and unchanged (constant).
  • Fig. 1A In the presentation of the Fig. 1A are shown with the reference numeral 33 provided arrows representing the course of the edge flow.
  • the flow flows from different directions into the region of the edge, ie, into the region close to or adjacent to the nozzle inner wall 12.
  • the edge flow 33 flows along the The majority of the edge flow 33 then no longer follows the course of the inner wall 12 into the depression 15, but continues to flow in a laminar fashion straight on and impinges on the propeller blade 22.
  • the Fig. 5 . 5A and 6 show a further embodiment of the invention, namely a non-pivoting propeller nozzle 200.
  • the propeller 20 and the nozzle 10 of the propeller nozzle 200 are substantially similar to the propeller nozzle 100 of the Fig. 1 to 4 educated. With respect to the nozzle 10, there is a difference in that the depression 15 in the propeller nozzle 200 also has an arcuate course, but the arc curve has a much greater curvature than in the case of the propeller nozzle 100.
  • the depression 15 in the flow direction 30 is very large shorter, ie, the distance between the recess start 151 and recess end 152 is much lower in the case of the propeller nozzle 200 than in the case of the propeller nozzle 100.
  • This recess 15 is also designed as a circumferential annular groove (see FIG Fig. 6 ).
  • the Propellererielend Scheme 23 of the propeller blades 22 has a circular arc in the views of Fig. 5 and 5A on, wherein the curvature of the circular arc approximately corresponds to the course of the recess 15, that is, also here Propellerhoffledend Schemee 23 and recess 15 are formed corresponding to each other.
  • the Propellererielend Scheme 23 can taper much sharper, ie be formed narrower than that at the propeller blades from the propeller nozzle 100. Similar to the propeller 100 also flows in the propeller nozzle 200 a Most of the edge flow 33 is not through the gap 40, but is detected in the region of the recess start 151 by the propeller blade 22 (see Fig. 5A ).
  • the propeller blade end portions are inserted into the recess 10 so deeply that they protrude outwardly beyond the inner wall portion before the recess beginning 151 and after the recess end 152, respectively.
  • a further embodiment of a pivotable propeller nozzle is shown, wherein only a portion of a propeller blade 22 and a section through the nozzle 10 are shown.
  • pivotable propeller nozzle is not provided with a recess in the inner wall 12 of the nozzle 10.
  • a projection body is provided, which is designed as a front bead 17.
  • the bead 17 extends circumferentially along the nozzle inner wall 12 along and thus forms an annular bead.
  • the outer edge of the front bead 17 is approximately arcuate.
  • the edge flow 33 which flows along the nozzle inner wall 12, is deflected from the front bead 17, at least partially, inwards into the nozzle interior and thus directed onto the propeller blade 22. Accordingly, the edge flow 33 is, at least partially, directed away from the gap 40 between the propeller blade end region 23 and the nozzle inner wall 12.
  • the front bead 17 is dimensioned uniformly over its entire circumference.
  • the curved design of the bead in cross-sectional view with a constant radius of curvature produces little or no turbulence in the deflection of the edge flow 33. It also ensures that pivoting of the propeller 22 remains possible and this is not blocked by the front bead 17 during pivoting, which through the partially illustrated circle in the Fig. 7A is indicated. Also, by this shape of the front bead 17, the gap 40 between Propellerhofflend Scheme 23 and nozzle inner wall 12 in all pivot positions between the zero position and the front bead 17 as small as possible.
  • a rear bead 18 is provided in which compared to the embodiment of the Fig. 7A in a pivotable propeller in addition to the front bead 17, a rear bead 18 is provided.
  • the rear bead 18 is arranged at the untwisted nozzle 10 in the flow direction behind the propeller blades 22.
  • the rear bead 18 is formed substantially similar to the front bead 17, that is also as circumferentially circumferential annular bead. Due to the additional arrangement of Butt bead 18 results in an increased sealing effect in the manner of a labyrinth seal.
  • the representation in the Fig. 8A and 8B each show a non-pivoting propeller nozzle, wherein in the illustration of Fig. 8A a front bead 17 and in the execution of the Fig. 8B In addition, a rear bead 18 are provided. Since the propeller nozzle is non-pivotable, the beads 17 and 18 are arranged at a smaller distance from the propeller blade 22, as compared to the beads 17, 18 of the pivotable propeller nozzle from the Fig. 7A and 7B the case is. Also, the height of the beads 17, 18 from the Fig. 8A and 8B larger than that at the beads 17, 18 from the Fig. 7A and 7B the case is. The outer contour of the beads 17, 18 from the Fig. 8A .
  • the edge flow 33 is derived by the front bead 17 from the nozzle inner wall 12 inwardly onto the propeller blade 22.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • Combustion & Propulsion (AREA)
  • Ocean & Marine Engineering (AREA)
  • Chemical & Material Sciences (AREA)
  • General Engineering & Computer Science (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
  • Nozzles (AREA)
  • Fuel-Injection Apparatus (AREA)
  • Particle Formation And Scattering Control In Inkjet Printers (AREA)
  • Percussion Or Vibration Massage (AREA)
  • Hydraulic Turbines (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Infusion, Injection, And Reservoir Apparatuses (AREA)
EP12184282.7A 2011-09-14 2012-09-13 Tuyère d'hélice Active EP2570341B1 (fr)

Priority Applications (2)

Application Number Priority Date Filing Date Title
PL12184282T PL2570341T3 (pl) 2011-09-14 2012-09-13 Dysza śruby napędowej
HRP20170432TT HRP20170432T1 (hr) 2011-09-14 2017-03-17 Mlaznica propelera

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
DE102011053619A DE102011053619A1 (de) 2011-09-14 2011-09-14 Propellerdüse für Wasserfahrzeuge

Publications (2)

Publication Number Publication Date
EP2570341A1 true EP2570341A1 (fr) 2013-03-20
EP2570341B1 EP2570341B1 (fr) 2016-12-28

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EP12184282.7A Active EP2570341B1 (fr) 2011-09-14 2012-09-13 Tuyère d'hélice

Country Status (13)

Country Link
US (1) US9322290B2 (fr)
EP (1) EP2570341B1 (fr)
JP (1) JP5721675B2 (fr)
KR (1) KR20130029356A (fr)
CN (1) CN102991659B (fr)
CA (1) CA2789906C (fr)
DE (1) DE102011053619A1 (fr)
DK (1) DK2570341T3 (fr)
ES (1) ES2620295T3 (fr)
HR (1) HRP20170432T1 (fr)
PL (1) PL2570341T3 (fr)
SG (1) SG188755A1 (fr)
TW (1) TWI535625B (fr)

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* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE202013101943U1 (de) * 2013-05-06 2013-06-11 Becker Marine Systems Gmbh & Co. Kg Vorrichtung zur Verringerung des Antriebsleistungsbedarfs eines Wasserfahrzeuges
CA2846137C (fr) * 2014-03-14 2015-08-18 Peter Van Diepen Tuyere d'helice a faible tirant d'eau
US20180281916A1 (en) * 2014-11-14 2018-10-04 Christopher Betts An improved airship
US9751593B2 (en) 2015-01-30 2017-09-05 Peter Van Diepen Wave piercing ship hull
CN105217000B (zh) * 2015-10-30 2018-08-03 佛山市神风航空科技有限公司 一种方管螺旋桨船舶推进器
CN105217001B (zh) * 2015-10-30 2018-12-04 孙永锋 一种椭圆管形船舶推进器
CN109515664A (zh) * 2018-11-21 2019-03-26 浙江海洋大学 一种货船用分叶式螺旋桨
FR3111324B1 (fr) * 2020-06-15 2022-07-22 Hy Generation Tuyere de propulseur de fluide a decrochage dynamique

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US3680977A (en) * 1969-07-01 1972-08-01 Denis Rabouyt Framed impeller
US4074652A (en) * 1976-07-26 1978-02-21 Jackson William M Steering and propulsion device for watercraft
DE2916287A1 (de) * 1978-09-28 1980-10-30 Rudolf Dr Wieser Schiffsantrieb
FR2439869A1 (fr) * 1978-10-24 1980-05-23 Gerry Ulrich Convertisseur d'energie tournant utilisant un fluide, notamment pour compresseurs ou turbines pour moteur a turbine a gaz assurant la propulsion de vehicules aeriens ou marins
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SG188755A1 (en) 2013-04-30
DE102011053619A1 (de) 2013-03-14
CA2789906C (fr) 2015-04-14
US9322290B2 (en) 2016-04-26
TW201323279A (zh) 2013-06-16
JP5721675B2 (ja) 2015-05-20
JP2013063768A (ja) 2013-04-11
DK2570341T3 (en) 2017-04-03
KR20130029356A (ko) 2013-03-22
ES2620295T3 (es) 2017-06-28
TWI535625B (zh) 2016-06-01
PL2570341T3 (pl) 2017-06-30
CN102991659B (zh) 2017-04-12
CA2789906A1 (fr) 2013-03-14
CN102991659A (zh) 2013-03-27
EP2570341B1 (fr) 2016-12-28
US20130064652A1 (en) 2013-03-14
HRP20170432T1 (hr) 2017-05-05

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