EP0894066A1 - Blade for ship propellers - Google Patents

Blade for ship propellers

Info

Publication number
EP0894066A1
EP0894066A1 EP97923737A EP97923737A EP0894066A1 EP 0894066 A1 EP0894066 A1 EP 0894066A1 EP 97923737 A EP97923737 A EP 97923737A EP 97923737 A EP97923737 A EP 97923737A EP 0894066 A1 EP0894066 A1 EP 0894066A1
Authority
EP
European Patent Office
Prior art keywords
propeller blade
blade
ribs
ship propellers
induced
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.)
Withdrawn
Application number
EP97923737A
Other languages
German (de)
French (fr)
Inventor
Dirk JÜRGENS
Christian Thieme
Heinz-Günter Ehluss
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.)
Blohm and Voss International GmbH
Original Assignee
Blohm and Voss International GmbH
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 Blohm and Voss International GmbH filed Critical Blohm and Voss International GmbH
Publication of EP0894066A1 publication Critical patent/EP0894066A1/en
Withdrawn legal-status Critical Current

Links

Classifications

    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B63—SHIPS OR OTHER WATERBORNE VESSELS; RELATED EQUIPMENT
    • B63H—MARINE PROPULSION OR STEERING
    • B63H1/00—Propulsive elements directly acting on water
    • B63H1/02—Propulsive elements directly acting on water of rotary type
    • B63H1/12—Propulsive elements directly acting on water of rotary type with rotation axis substantially in propulsive direction
    • B63H1/14—Propellers
    • B63H1/26—Blades
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C11/00—Propellers, e.g. of ducted type; Features common to propellers and rotors for rotorcraft
    • B64C11/16—Blades
    • B64C11/18—Aerodynamic features

Definitions

  • the invention relates to a propeller blade of ship propellers with the features specified in the preamble of claim 1
  • the outer leaf end is provided with a disk or with wing segments which are almost axially, perpendicular to the sheet surface and project in the direction of the suction or pressure side This makes it possible to reduce the pressure equalization or the flow around the end of the blade and thus the eddy losses.
  • Modifications of this principle are so-called tip-fin propellers, in which the blade end bulges up to over 90 ° in the axial direction and thus an end disk effect is achieved.
  • a major disadvantage of the known devices is the disproportionately high manufacturing effort. Due to the friction on the additional surfaces, the moment also increases, so that the overall gain in efficiency is relatively small
  • the invention has for its object to overcome this deficiency and accordingly to further develop the device according to the preamble of claim 1 in such a way that a significant gain in efficiency can be achieved with comparatively little technological effort.
  • This object is achieved according to the invention in that several ribs run approximately parallel to the generatrix of the propeller blade, which project radially freely outwards from the end of the propeller blade.
  • the device according to the invention is illustrated in the drawings with the aid of a few sketches, structural details having been omitted
  • FIG. 1 sectional view of the propeller blade with ribs
  • Fig. 2 top view of the propeller blade with ribs
  • Fig. 3 top view of the propeller blade with ribs and slot
  • the device according to the invention makes it possible to reduce the vortex losses.
  • the screw surface of a propeller is formed by a straight line which rotates about a fixed axis and progresses along this axis at a constant speed.
  • the generating line is also referred to as generator 1. Due to the ribs R1-R4 arranged approximately parallel to the generating 1, the energy loss of the free vertebra is significantly reduced. The energy of the vortex is approximately proportional to the third power of its radius. This results in accordance with the geometry of the edge to be flowed around.
  • the ribs additionally generate buoyancy.
  • the development of the boundary layer and the pressure distribution through slots 3 can be positively influenced.
  • the ribs can be produced technologically simply by milling out the thicker leaf end area or by attaching a prefabricated rib cap.

Landscapes

  • Engineering & Computer Science (AREA)
  • Physics & Mathematics (AREA)
  • Fluid Mechanics (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • Ocean & Marine Engineering (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
  • Wind Motors (AREA)

Abstract

A blade for ship propellers is provided in the area of its outer radius with means for reducing the induced turbulence. The means for reducing the induced turbulence consist of several ribs spaced apart and arranged next to each other in an approximately parallel direction to the generatrix of the propeller blade. The ribs project freely outwards in the radial direction from the end of the propeller blade.

Description

Propellerblatt von SchiffspropellernPropeller blade from ship propellers
Die Erfindung betrifft ein Propellerblatt von Schiffspropellem mit den im Oberbegriff des Anspruchs 1 angegebenen MerkmalenThe invention relates to a propeller blade of ship propellers with the features specified in the preamble of claim 1
Durch die unterschiedlichen Druckverhältnisse an der Saug- bzw. Druckseite eines Propeller¬ blattes kommt es zu einer Umstromung des äußeren Blattendes Dabei wird ein sogenannter Spitzenwirbel induziert. Je hoher der Propeller belastet wird, um so großer wird der Druckgra¬ dient zwischen Saug- und Druckseite und damit die Energie des induzierten Wirbels. In Ab¬ hängigkeit vom Belastungsgrad betragen die durch Wirbelinduktion verursachten Wirkungs¬ gradverluste bis zu 15%. Bisher bekannt gewordene Einrichtungen mit den im Oberbegriff des Anspruchs 1 angegebenen Merkmalen basieren auf dem Wirkprinzip von Flügelendscheiben Das äußere Blattende wird mit einer Scheibe oder mit Flugelsegmenten versehen, welche na¬ hezu axial, senkrecht zur Blattflache stehen und in Richtung der Saug- bzw Druckseite ragen Damit ist es möglich, den Druckausgleich bzw. die Umstromung am Blattende und damit die Wirbelverluste zu verringern. Modifikationen dieses Prinzips sind sogenannte Tip-Fin-Propel- ler, bei denen das Blattende bis über 90° in die axiale Richtung verwolbt und somit eine End¬ scheibenwirkung erzielt wird. Ein wesentlicher Nachteil der bekannten Einrichtungen ist der unverhältnismäßig hohe Fertigungsaufwand. Auf Grund der Reibung an den zusätzlichen Fla¬ chen erhöht sich zudem das Moment, so daß der Gesamtwirkungsgradgewinn relativ gering ausfalltThe different pressure conditions on the suction or pressure side of a propeller blade result in a flow around the outer blade end. A so-called tip vortex is induced. The higher the propeller is loaded, the greater the pressure gradient between suction and pressure side and thus the energy of the induced vortex. Depending on the degree of loading, the efficiency losses caused by vortex induction are up to 15%. Devices which have become known to date have the features specified in the preamble of claim 1 and are based on the principle of operation of wing end disks. The outer leaf end is provided with a disk or with wing segments which are almost axially, perpendicular to the sheet surface and project in the direction of the suction or pressure side This makes it possible to reduce the pressure equalization or the flow around the end of the blade and thus the eddy losses. Modifications of this principle are so-called tip-fin propellers, in which the blade end bulges up to over 90 ° in the axial direction and thus an end disk effect is achieved. A major disadvantage of the known devices is the disproportionately high manufacturing effort. Due to the friction on the additional surfaces, the moment also increases, so that the overall gain in efficiency is relatively small
Der Erfindung liegt die Aufgabe zugrunde, diese Mangel zu überwinden und demgemäß die Einrichtung nach dem Oberbegriff des Anspruchs 1 derart weiterzuentwickein, daß mit ver¬ gleichsweise geringem technologischem Aufwand ein deutlicher Wirkungsgradgewinn erzielt werden kann. Diese Aufgabe wird erfindungsgemaß dadurch gelöst, daß mehrere Rippen na- herungsweise parallel zur Erzeugenden des Propellerblattes verlaufen, die vom Propellerblatt¬ ende radial frei nach außen ragen In den Zeichnungen ist die erfindungsgemaße Einrichtung anhand einiger Skizzen veranschau¬ licht, wobei konstruktive Einzelheiten fortgelassen sindThe invention has for its object to overcome this deficiency and accordingly to further develop the device according to the preamble of claim 1 in such a way that a significant gain in efficiency can be achieved with comparatively little technological effort. This object is achieved according to the invention in that several ribs run approximately parallel to the generatrix of the propeller blade, which project radially freely outwards from the end of the propeller blade The device according to the invention is illustrated in the drawings with the aid of a few sketches, structural details having been omitted
Es zeigenShow it
Fig 1 Schnittdarstellung des Propellerblattes mit RippenFig. 1 sectional view of the propeller blade with ribs
Fig 2 Draufsicht des Propellerblattes mit RippenFig. 2 top view of the propeller blade with ribs
Fig 3 Draufsicht des Propellerblattes mit Rippen und SchlitzFig. 3 top view of the propeller blade with ribs and slot
Durch die erfindungsgemaße Einrichtung ist es möglich, die Wirbelverluste zu senken Die Schraubenflache eines Propellers wird von einer Geraden gebildet, die sich um eine feste Ach¬ se dreht und mit konstanter Geschwindigkeit längs dieser Achse fortschreitet Die erzeugende Gerade wird auch als Erzeugende 1 bezeichnet. Durch die naherungsweise parallel zur Erzeu¬ genden 1 angeordneten Rippen R1-R4 wird die Verlustenergie des freien Wirbels deutlich her¬ abgesetzt. Die Energie des Wirbels ist naherungsweise proportional der dritten Potenz seines Radius. Dieser ergibt sich entsprechend der Geometrie der zu umströmenden Kante Durch die Unteπeilung der Kontur des Propellerblattes 2 am äußeren Ende in mehrere Rippen R1-R4 werden an Stelle eines freien Wirbels mehrere kleine Wirbel entsprechend der Anzahl und der Spaltabstande der Rippen induziert Wird beispielsweise von einem Einzelwirbel mit dem Ra¬ dius 1 0 ( r=l) ausgegangen, so laßt sich die Verlustenergie bei vier Teilwirbeln mit dem Radi¬ us 0 25 (4*0.253=0 0625) auf ca 6-7% reduzieren. Durch die Ausrichtung der Rippen R1-R4 entsprechend der Blattkontur und der Erzeugenden 1 erzeugen die Rippen zusatzlich Auftrieb Dabei kann die Entwicklung der Grenzschicht und der Druckverteilung durch Schlitze 3 posi¬ tiv beeinflußt werden. Die Rippen lassen sich technologisch einfach durch Ausfrasen des dicker ausgelegten Blattendbereiches herstellen, bzw durch Aufsetzen einer vorgefertigten Rippenkappe. The device according to the invention makes it possible to reduce the vortex losses. The screw surface of a propeller is formed by a straight line which rotates about a fixed axis and progresses along this axis at a constant speed. The generating line is also referred to as generator 1. Due to the ribs R1-R4 arranged approximately parallel to the generating 1, the energy loss of the free vertebra is significantly reduced. The energy of the vortex is approximately proportional to the third power of its radius. This results in accordance with the geometry of the edge to be flowed around. By dividing the contour of the propeller blade 2 at the outer end into a plurality of ribs R1-R4, instead of a free vortex, several small vortices are induced in accordance with the number and spacing of the ribs. For example, from a single vortex assuming the radius 1 0 (r = 1), the loss energy in four partial vertebrae can be reduced to approx. 6-7% with the radius 0 25 (4 * 0.25 3 = 0 0625). By aligning the ribs R1-R4 in accordance with the blade contour and the generatrix 1, the ribs additionally generate buoyancy. The development of the boundary layer and the pressure distribution through slots 3 can be positively influenced. The ribs can be produced technologically simply by milling out the thicker leaf end area or by attaching a prefabricated rib cap.

Claims

PatentansprücheClaims
1 Propellerblatt von Schiffspropellem das im Bereich des Außenradius mit Mitteln zur1 propeller blade from ship propellers in the area of the outer radius with means for
Vemngerung des induzierten Wirbels ausgestattet ist, gekennzeichnet dadurch. daß die Mittel zur Verringerung des induzierten Wirbels aus mehreren im Abstand ne¬ beneinander angeordneten, naherungsweise parallel zur Erzeugenden ( I ) des Propel¬ lerblattes (2) verlaufenden Rippen (R1-R4) bestehen, die vom Propellerblattende ra¬ dial frei nach außen ragen Propellerblatt nach Anspruch 1 , gekennzeichnet dadurch. daß die Rippen (H1-R4) durch einen oder mehrere Schlitze (3) in tangentialer Rich¬ tung unterteilt werden Reduction of the induced vertebra is characterized by this. that the means for reducing the induced vortex consist of a plurality of ribs (R1-R4) which are arranged next to one another and are approximately parallel to the generatrix (I) of the propeller blade (2) and project radially outward from the end of the propeller blade Propeller blade according to claim 1, characterized in that. that the ribs (H1-R4) are divided by one or more slots (3) in the tangential direction
EP97923737A 1996-04-15 1997-04-10 Blade for ship propellers Withdrawn EP0894066A1 (en)

Applications Claiming Priority (3)

Application Number Priority Date Filing Date Title
DE19614851 1996-04-15
DE19614851 1996-04-15
PCT/DE1997/000733 WO1997038897A1 (en) 1996-04-15 1997-04-10 Blade for ship propellers

Publications (1)

Publication Number Publication Date
EP0894066A1 true EP0894066A1 (en) 1999-02-03

Family

ID=7791326

Family Applications (1)

Application Number Title Priority Date Filing Date
EP97923737A Withdrawn EP0894066A1 (en) 1996-04-15 1997-04-10 Blade for ship propellers

Country Status (6)

Country Link
EP (1) EP0894066A1 (en)
JP (1) JP2000508271A (en)
KR (1) KR20000005416A (en)
CN (1) CN1221379A (en)
DE (1) DE19780302D2 (en)
WO (1) WO1997038897A1 (en)

Families Citing this family (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GR990100151A (en) * 1999-05-06 2001-01-31 Opener of the twisting of whirls
US7049324B1 (en) 1999-11-15 2006-05-23 Ashis Kumar Saha Triazoles as farnesyl transferase inhibitors
CN100406347C (en) * 2006-01-23 2008-07-30 李如忠 Energy-saving screw propeller for ship
KR101225177B1 (en) 2010-07-16 2013-01-22 삼성중공업 주식회사 Propeller and ship including the same
CN105438424B (en) * 2015-11-23 2017-11-21 镇江同舟螺旋桨有限公司 A kind of energy-conservation marine propeller of ending flap

Family Cites Families (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB196410A (en) * 1922-02-01 1923-04-26 William Robert Douglas Shaw Improvements in wings for aerial machines
ES2035127T3 (en) * 1987-03-13 1993-04-16 Gunter Spranger DEFLATED PROFILE DEVICE, ACTING ON A LIQUID OR GASEOUS FLUID THAT FLOWS AROUND IT AND PRESENTS STRIPPED PROFILED FINS TO IMPROVE EFFICIENCY.
DE4202745C2 (en) * 1991-09-04 1995-04-13 Blohm Voss Ag Wing, in particular stabilizer fin for ships

Non-Patent Citations (1)

* Cited by examiner, † Cited by third party
Title
See references of WO9738897A1 *

Also Published As

Publication number Publication date
DE19780302D2 (en) 1999-04-29
WO1997038897A1 (en) 1997-10-23
CN1221379A (en) 1999-06-30
KR20000005416A (en) 2000-01-25
JP2000508271A (en) 2000-07-04

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