EP3508415B1 - Hélice à plaque d'extrémité de type diffuseur - Google Patents

Hélice à plaque d'extrémité de type diffuseur Download PDF

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Publication number
EP3508415B1
EP3508415B1 EP18179727.5A EP18179727A EP3508415B1 EP 3508415 B1 EP3508415 B1 EP 3508415B1 EP 18179727 A EP18179727 A EP 18179727A EP 3508415 B1 EP3508415 B1 EP 3508415B1
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EP
European Patent Office
Prior art keywords
endplate
propeller
diffuser
type
angle
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.)
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Application number
EP18179727.5A
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German (de)
English (en)
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EP3508415A1 (fr
Inventor
Young-Zehr Kehr
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.)
Hung Shen Propeller Co Ltd
National Taiwan Ocean University NTOU
Original Assignee
Hung Shen Propeller Co Ltd
National Taiwan Ocean University NTOU
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Priority claimed from US15/860,685 external-priority patent/US10155575B2/en
Application filed by Hung Shen Propeller Co Ltd, National Taiwan Ocean University NTOU filed Critical Hung Shen Propeller Co Ltd
Publication of EP3508415A1 publication Critical patent/EP3508415A1/fr
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    • 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
    • B63H1/15—Propellers having vibration damping means
    • 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
    • B63H1/18—Propellers with means for diminishing cavitation, e.g. supercavitation
    • 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
    • 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
    • B63H1/28—Other means for improving propeller efficiency

Definitions

  • the present invention generally relates to a propeller, and more particularly, to a diffuser-type endplate propeller.
  • tip vortex free (TVF) propeller and contracted loaded tip (CLT) propeller.
  • TVF tip vortex free
  • CLT contracted loaded tip
  • the endplate thereof is tangential to the cylindrical surface of the propeller blade-tip. That is during the rotation of the propeller, the endplate becomes a portion of the cylindrical surface to reduce the viscous resistance of the endplate.
  • the successive developers further make the endplate contracted by design, i.e., for the new designed CLT propeller, the leading edge radius of the endplate is greater than the radius of the trailing edge.
  • both the TVF propeller and the CLT propeller are able to effectively prevent the fluid at the high-pressure side-surfaces of the propeller blades from flowing to the low-pressure side-surfaces so as to keep the loads of the blade-tips and suppress the intensity of the tip vortex. Accordingly, a quite portion of the thrust produced by the above-mentioned TVF propeller or CLT propeller is provided by the high-pressure side-surfaces of the propeller blades, which reduces the probability for the low-pressure side-surface of the propeller to produce cavitation.
  • Another more serious trouble is that if a CLT propeller is applied to a hull based on the inclined-shaft design, for example, a speedboat, the CLT propeller under an inclined-shaft inflow condition has a more serious cavitation phenomenon occurred at the endplate of a blade when the blade turns to the upper-vertical position.
  • US 2014/363298 A1 discloses a diffuser-type endplate propeller for driving a hull.
  • the diffuser-type endplate propeller includes a propeller hub and a plurality of blades.
  • the propeller hub is connected to a transmission shaft of the hull.
  • Each of blades respectively has a blade-body and an endplate connected to each other, wherein each of the blade-bodies is connected to the propeller hub and extends outward from the propeller hub to the corresponding endplate, each the endplate bends from the corresponding blade-body to extend towards a stern of the hull, each of the endplates has a leading edge and a trailing edge, each the leading edge keeps a first distance from an axis of the propeller hub, each the trailing edge keeps a second distance from the axis of the propeller hub, and the first distance is less than the second distance.
  • JP S53 66696 A discloses a blade designed for boats or ship propellers.
  • the secondary blade has a slot which is located normal to the blade surface and on the outside edge of the blade. The effect of the slot is to reduce the propeller diameter and to increase its pitch.
  • the slot is covered with an aerofoil section along the leading edge of the propeller blade. The blade extends beyond the ends of the slot, which spans only the central portion of the propeller blade.
  • JP S56 167590 A discloses a propeller in which the blades of propeller have blade tip plates provided in parallel to the thrust shaft core or in an angle close to it, to diffuse tip eddies, to decrease inductive resistance of the propeller, and thereby to increase efficiency, and to prevent generation of cavitation.
  • the present invention is directed to a diffuser-type endplate propeller under an inclined-shaft inflow condition which can largely reduce even eliminate the sheet cavitation phenomenon produced by the endplate itself regardless of the propeller blades turning to any angle positions.
  • An embodiment of the present invention provides a diffuser-type endplate propeller, according to claim 1.
  • An embodiment of the present invention provides a diffuser-type endplate propeller, according to claim 4.
  • the endplate propeller of the invention is a diffuser-type endplate propeller, i.e., when the diffuser-type endplate propeller is rotating, it does not produce sheet cavitation phenomenon at the endplates themselves, so that the invention improves the efficiency of the endplate propeller and reduces the hull vibration and noise.
  • FIG. 1 is a schematic partial diagram showing a diffuser-type endplate propeller connected to a hull in an embodiment of the disclosure, not forming part of the invention
  • FIG. 2 is a three-dimensional diagram of the diffuser-type endplate propeller of FIG. 1
  • FIG. 3A is a front-view diagram of the diffuser-type endplate propeller in FIG. 1 in the angle of view towards the stern of the hull
  • FIG. 3B is a cross-sectional view along the section line I-I' of the diffuser-type endplate propeller in FIG. 3A .
  • a diffuser-type endplate propeller 100 of the embodiment is able to drive a hull 20, and the diffuser-type endplate propeller 100 includes a propeller hub 110 and a plurality of blades 120.
  • the propeller hub 110 is connected to a transmission shaft 22 of the hull 20.
  • Each of the blades 120 respectively has a blade-body 122 and a endplate 124 connected to each other, in which each blade-body 122 is connected to the propeller hub 110 and extends outward from the propeller hub 110 to the corresponding endplate 124, and each endplate 124 bends from the corresponding blade-body 122 to extend towards a stern 24 of the hull.
  • Each endplate 124 has a leading edge 124a and a trailing edge 124b, in which the leading edge 124a keeps a first distance D1 from an axis L of the propeller hub 110, the trailing edge 124b keeps a second distance D2 from the axis L of the propeller hub 110, and the first distance D1 is shorter than the second distance D2.
  • the endplate 124 is parallel to the axis L, as shown in FIG. 3B .
  • the diffuser-type endplate propeller 100 of the embodiment is installed, for example, at the bottom of the hull 20 and operated under an inclined-shaft condition or a horizontal shaft condition.
  • the diffuser-type endplate propeller 100 is described as operated under an inclined-shaft condition for illustration purpose.
  • the diffuser-type endplate propeller 100 is connected to an end of the transmission shaft 22 through the propeller hub 110, while another end of the transmission shaft 22 is connected to the engine in the hull 20 (not shown).
  • the transmission shaft 22 When the engine is running, the transmission shaft 22 is driven to rotate the diffuser-type endplate propeller 100, and, by means of the rotating of the blades 120, the water flow is back pushed towards the stern 24 so as to produce a forward reaction for driving the hull 20 to proceed in a sailing direction A2, in which the axis L of the propeller hub 110 is not parallel to the sailing direction A2.
  • the quantity of the blades 120 is three to seven. In the embodiment, there are, for example, four blades 120, which are disposed and radially arranged on the propeller hub 110.
  • the diffuser-type endplate propeller 100 is fabricated in, for example, casting process by using metallic material or composite materials. In other words, the propeller hub 110 and the blades 120 can be integrally molded to have better rigidity to withstand the pressure of the water flow.
  • the blade-body 122 of a blade 120 can further include a high-pressure side-surface towards the stern 24 and a low-pressure side-surface back from the stern 24, in which the most portion of the thrust produced by the diffuser-type endplate propeller 100 is provided by the high-pressure side-surface.
  • the diffuser-type endplate propeller 100 in the embodiment rotates clockwise and the endplates 124 can prevent the water flow moved by the rotations of the blades 120 from flowing to the low-pressure side-surfaces at the blade-tips so as to ensure the diffuser-type endplate propeller 100 having good efficiency and effectively suppress the tip vortex.
  • the leading edge 124a is, for example, for guiding the water flow of the high-pressure side-surface of the propeller to flow to the trailing edge 124b along the inner-side of the endplate 124, and then, guiding the water flow out of the high-pressure side-surface through the trailing edge 124b.
  • the endplate 124 of the embodiment chordwise extends to the trailing edge 124b from the leading edge 124a, in which the leading edge 124a keeps a first distance D1 from the axis L, the trailing edge 124b keeps a second distance D2 from the axis L, and the first distance D1 is shorter than the second distance D2, and further thus, the endplate 124 has a diffused shape chordwise.
  • FIG. 4A is a diagram showing the diffuser-type endplate propeller of FIG. 2 in clockwise rotating
  • FIG. 4B is a partial enlarged view diagram of a region A of the diffuser-type endplate propeller of FIG. 4A
  • FIG. 4C is a partial enlarged view diagram of the region A of the diffuser-type endplate propeller of FIG. 4A in view along an axis of the propeller from a high pressure side.
  • the diffuser-type endplate propeller 100 rotates clockwise, the rotating track of the leading edge 124a forms a cylindrical surface S1, and a negative angle of attack of endplate (the diffuser angle) ⁇ may present at the leading edge 124a of each endplate 124.
  • the negative angle of attack of endplate may be determined at other appropriate positions on the endplate 124 in other embodiments. More specifically, in the present embodiment, the leading edge 124a and the cylindrical surface S1 has a boundary line I, the endplate 124 has a first tangent plane C1 which is located at the boundary line I and along the chord of the endplate 124, while the cylindrical surface S1 has a second tangent plane C2 on the boundary line I, the included angle of the first tangent plane C1 and the second tangent plane C2 is the angle of attack of endplate ⁇ . In the embodiment, the angle of attack of endplate ⁇ is, for example, smaller than 0° and greater than or equal to -1°, which means the endplate 124 of the embodiment has a negative angle of attack.
  • the cylindrical surface S1 is an imaginary surface formed by the leading edge 124a while the endplates 124/the diffuser-type endplate propeller 10 is rotated about the axis L of the propeller hub 110
  • the boundary line I is an intersection line between the leading edge 124a and the cylindrical surface S1
  • the boundary line I is located on the cylindrical surface S1 and coincide with the leading edge 124a.
  • the first tangent plane C1 is tangential to the endplate 124 at the leading edge 124a (or the boundary line I). That is, the first tangent plane C1 contains the leading edge 124a and is a tangent plane of the endplate 124.
  • the second tangent plane C2 is tangential to the cylindrical surface S1 at the leading edge 124a. That is, the second tangent plane C2 contains the leading edge 124a and is a tangent plane of the cylindrical surface S1.
  • the angle of attack of endplate ⁇ is defined as the included angle of the first tangent plane C1 and the second tangent plane C2.
  • the absolute value of the included angle is greater than 0° and smaller than or equal to 1°.
  • FIG. 4C is a partial enlarged view diagram of the region A of the diffuser-type endplate propeller of FIG. 4A in view along an axis of the propeller from a high pressure side.
  • the diffuser-type endplate propeller 100 rotates clockwise to drive the hull 20 for proceeding towards the sailing direction A2.
  • the included angle between the first tangent plane C1 and the second tangent plane C2 is measured from the second tangent plane C2 to the first tangent plane C1 in clockwise direction, so the included angle is a negative angle.
  • the included angle is greater than or equal to -1° and smaller than 0°, and thus the angle of attack of endplate ⁇ is also greater than or equal to -1° and smaller than 0°.
  • FIG. 4D is a partial enlarged view diagram of the region A of the diffuser-type endplate propeller of another embodiment of the disclosure, not forming part of the invention, in view along an axis of the propeller from a high pressure side.
  • the diffuser-type endplate propeller 100 rotates counterclockwise to drive the hull 20 for proceeding towards the sailing direction A2.
  • the included angle between the first tangent plane C1 and the second tangent plane C2 is measured from the second tangent plane C2 to the first tangent plane C1 in counterclockwise direction, so the included angle is a positive angle.
  • the included angle is greater than 0° and smaller than or equal to 1°, and thus the angle of attack of endplate ⁇ is also greater than 0° and smaller than or equal to 1°.
  • FIG. 5A is a diagram showing the inflow velocity at the inclined-shaft for the diffuser-type endplate propeller of FIG. 1 .
  • FIG. 5B is a diagram showing the diffuser-type endplate propeller of FIG. 5A in clockwise rotating along the X axis while viewing from the high pressure side.
  • FIG. 5C is a diagram showing the inflow velocity at the cylindrical endplate for a conventional propeller without diffuser-type endplate under an inclined-shaft inflow condition, wherein the propeller turns to the 0°circumferential position.
  • FIG. 5D is a diagram showing the inflow velocity at the endplate for the diffuser-type endplate propeller of FIG. 5A , wherein the propeller turns to the 0°circumferential position.
  • FIG. 5A is a diagram showing the inflow velocity at the inclined-shaft for the diffuser-type endplate propeller of FIG. 1 .
  • FIG. 5E is a diagram showing the inflow velocity at the cylindrical endplate for a conventional propeller under an inclined-shaft inflow condition, wherein the propeller turns to the 180°circumferential position.
  • FIG. 5F is a diagram showing the inflow velocity at the endplate for the diffuser-type endplate propeller of FIG. 5A , wherein the propeller turns to the 180°circumferential position.
  • the endplates 124 and 220 are curved plates and the inflow also flows along the curved plates, the curved plates and the curved inflow are stretched to be flat for better visualization and explanation, so the endplates 124 and 220 are depicted as straight plates. Referring to FIG.
  • the actual experiments prove when the diffuser-type endplate propeller 100 rotates under an inclined-shaft condition, the diffuser-type endplate 124 not only prevents the water flow of the high-pressure side-surface from flowing to the low-pressure side-surface, but also eliminates the sheet cavitation phenomenon produced by the endplates 124 themselves regardless of the propeller blades 120 turning to any angle positions.
  • the axis L of the propeller hub 110 has an inclined-shaft angle ⁇ towards the sailing direction A2 of the hull, in which the inclined-shaft angle ⁇ ranges, for example, between 1° and 12°, and the propeller is suitable for a high-speed boat and ship with transom stern.
  • the hull 20 in sailing produces a propeller inflow VI, in which the propeller inflow V1 enters the diffuser-type endplate propeller 100 in a direction opposite to the sailing direction A2, and the propeller inflow V1 has an included angle towards the axis L, i.e. the inclined-shaft angle ⁇ .
  • the propeller inflow V1 can be resolved into a first inflow component V1cos ⁇ parallel to the axis L and a second inflow component V1sin ⁇ vertical to the axis L.
  • the second inflow component V1sin ⁇ enables the endplate 124 turning to the 0°circumferential position to increase the actual angle of attack of endplate or to the 180°circumferential position to decrease the actual angle of attack of endplate.
  • the diffuser-type endplate propeller 100 rotates in a peripheral velocity ⁇ R around the X axis, wherein the peripheral velocity coR produces an opposite cylindrical tangential inflow velocity ⁇ R1 and the peripheral velocity ⁇ R is equal to the cylindrical tangential inflow velocity ⁇ R1.
  • the cylindrical tangential inflow velocity ⁇ R1 and the second inflow component V1sin ⁇ together form a first actual angle of attack of endplate ⁇ 1 produced by the inclined-shaft inflow at the diffuser-type endplate 124 (as shown in FIG. 5D ).
  • the differential angle between the first cylindrical endplate angle of attack ⁇ 11 and the first actual angle of attack of endplate ⁇ 1 is ⁇
  • the angle ⁇ is a diffusing angle of the diffused endplate at the leading edge of the diffused endplate.
  • the outer-surface 220d and the inner-surface 220c of the conventional endplate 220 are shown in FIGs. 5C and 5E , the conventional endplate 220 is not contracted type and is also not diffused type.
  • the geometry of the diffused endplate has a negative angle ⁇ , the first actual angle of attack of endplate ⁇ 1 is significantly smaller than the first cylindrical endplate angle of attack ⁇ 11.
  • the sheet cavitation of the endplate can be reduced or eliminated.
  • the cylindrical tangential inflow velocity ⁇ R1 and the second inflow component V1sin ⁇ together form a second actual angle of attack of endplate ⁇ 2 produced by the inclined-shaft inflow at the endplate 124 (as shown in FIG. 5F ).
  • the cylindrical tangential inflow velocity ⁇ R1 and the second inflow component V1sin ⁇ together form a second cylindrical endplate angle of attack ⁇ 22 produced by the inclined-shaft inflow at the cylindrical endplate 220, in which the second cylindrical endplate angle of attack ⁇ 22 is negative.
  • the first cylindrical endplate angle of attack ⁇ 11 and the second cylindrical endplate angle of attack ⁇ 22 have the same absolute values but they are positive and negative, respectively. Since, in the diffuser-type endplate propeller 100 the angle of attack of endplate ⁇ of the endplate 124 of the blade 120 has a negative value by design, so that when the blade 120 turns to the 0°circumferential position, the first actual angle of attack of endplate ⁇ 1 of the endplate 124 is less than the first cylindrical endplate angle of attack of endplate ⁇ 11 by an absolute value of the angle of attack of endplate ⁇ , and the decreased actual angle of attack of the endplate 124 reduces the sheet cavitation phenomenon produced at the low-pressure side-surface (the outer-surface 124d of the endplate 124).
  • the inner-surface 124c of the endplate 124 contacts the high-pressure side-surface of the blades of the propeller and the immerged depth of the endplate 124 at the 180°circumferential position is deeper, therefore, no cavitation phenomenon occurs which thus suppresses the vibration and noise induced by the propeller.
  • the angle of attack of endplate ⁇ is an angle of attack of the endplate by design and determined based on the geometry of the endplate.
  • the first actual angle of attack of endplate ⁇ 1, the first cylindrical endplate angle of attack ⁇ 11, the second actual angle of attack of endplate ⁇ 2, and the second cylindrical endplate angle of attack ⁇ 22 are determined based on the relative position between the endplate and the flow.
  • the endplate 124 is stretched to be flat in FIGs. 5D and 5F for better visualization and explanation.
  • the actual shape of the endplate 124 and the inflow velocity at the leading edge 124a of the endplate 124 are shown in FIGs. 5G , 5H, and 5I hereinafter.
  • FIG. 5G is a diagram showing the diffuser-type endplate propeller of FIG. 5A in clockwise rotating along the X axis while viewing from the high pressure side.
  • the diffuser-type endplate propeller 100 turns to a position that the leading edge 124a of the endplate 124 of one of the propeller blades 120 is located at 0°circumferential position, as depicted in a region B, and the leading edge 124a of the endplate 124 of another one of the propeller blades 120 is located at 180°circumferential position, as depicted in a region C.
  • FIG. 5H is a partial enlarged view diagram of the region B showing the inflow velocity at the leading edge of the endplate of FIG. 5G for the diffuser-type endplate propeller of FIG. 5A , wherein the leading edge of the endplate is at the 0°circumferential position.
  • the second inflow component V1sin ⁇ , the cylindrical tangential inflow velocity ⁇ R1, the first cylindrical endplate angle of attack ⁇ 11, and a total inflow velocity VR vector which is a sum of the second inflow component V1sin ⁇ vector and the cylindrical tangential inflow velocity ⁇ R1 vector of the inflow at the leading edge 124a of the endplate 124 are shown in FIG. 5H .
  • the first cylindrical endplate angle of attack ⁇ 11 is magnified for clear purpose, and the notations of the first actual angle of attack of endplate ⁇ 1 and the angle ⁇ as shown in FIG. 5D are omitted.
  • FIG. 5I is a partial enlarged view diagram of the region C showing the inflow velocity at the leading edge of the endplate of FIG. 5G for the diffuser-type endplate propeller of FIG. 5A , wherein the leading edge of the endplate is at the 180°circumferential position.
  • the second inflow component V1sin ⁇ , the cylindrical tangential inflow velocity ⁇ R1, the second cylindrical endplate angle of attack ⁇ 22, and the total inflow velocity VR vector of the inflow at the leading edge 124a of the endplate 124 are shown in FIG. 5I .
  • the second cylindrical endplate angle of attack ⁇ 22 is magnified for clear purpose, and the notations of the second actual angle of attack of endplate ⁇ 2 and the angle ⁇ as shown in FIG. 5F are omitted.
  • FIG. 6A is a partial enlarged view diagram of endplate having angle of attack of -1° when turning to the 0°circumferential position in one embodiment of the disclosure, not forming part of the invention
  • FIG. 6B is a partial enlarged view diagram of endplate having angle of attack of 0° when turning to the 0°circumferential position in conventional technology
  • FIG. 6C is a partial enlarged view diagram of endplate having angle of attack of 1° when turning to the 0°circumferential position in conventional technology.
  • the rotating track of the leading edge 124a forms the cylindrical surface S1 having radius R1 from the centre O of the diffuser-type endplate propeller.
  • the angle of attack of the endplate 124 is equal to -1°, the leading edge 124a of the endplate 124 is located on the cylindrical surface S1 and the trailing edge 124b of the endplate 124 is located outside of the cylindrical surface S1.
  • the rotating track of the leading edge 124a' forms the cylindrical surface S1' having radius R1' from the centre O' of the endplate propeller.
  • the angle of attack of the endplate 124' is equal to 0°
  • the leading edge 124a' and the trailing edge 124b' of the endplate 124' are located on the cylindrical surface S1'.
  • the rotating track of the leading edge 124a" forms the cylindrical surface S1" having radius R1" from the centre O" of the endplate propeller.
  • the angle of attack of the endplate 124" is equal to 1°
  • the leading edge 124a" of the endplate 124" is located on the cylindrical surface S1"
  • the trailing edge 124b" of the endplate 124" is located inside of the cylindrical surface S1".
  • FIG. 7A is a partial enlarged view diagram of endplate having a positive camber distribution near the leading edge of the endplate compared with a cylindrical surface when turning to the 0°circumferential position in another embodiment of the invention.
  • the endplate 324 has a first portion 326 and a second portion 328, the leading edge 324a is located at the first portion 326, and the trailing edge 324b is located at the second portion 328.
  • the distance from the leading edge 324a to the centre O of the diffuser-type endplate propeller is equal to the distance from the trailing edge 324b to the centre O of the diffuser-type endplate propeller and is represented as R2.
  • the leading edge 324a and the trailing edge 324b are both located on the cylindrical surface S2 which has centre O and radius R2.
  • the curvature of the first portion 326 is greater than the curvature of the second portion 328, so the angle of attack of the endplate 324 at the leading edge 324a is greater than or equal to -1° and smaller than 0° by the designed geometry.
  • the length of the first portion 326 is equal to the length of the second portion 328 and equal to a half of the length of the endplate 324, and the first portion 326 has a positive camber distribution.
  • the ratio of the length of the first portion 326 to the total length of the endplate 324 may be greater than zero and smaller than or equal to 1, as long as the angle of attack of the endplate 324 at the leading edge 324a is greater than or equal to -1° and smaller than 0°.
  • FIG. 7B is a partial enlarged view diagram of endplate having a positive camber distribution on the endplate compared with the cylindrical surface when turning to the 0° circumferential position in another embodiment of the disclosure, not forming part of the invention.
  • the leading edge 324a and the trailing edge 324b are still located on the cylindrical surface S2
  • the first portion 326 has a positive camber distribution
  • the length of the first portion 326 is equal to the total length of the endplate 324.
  • the ratio of the length of the first portion 326 to the total length of the endplate 324 is equal to 1.0. That is to say, the geometry of the endplate 324 is a camber in comparison with the cylindrical surface S2.
  • the camber 324 can provide the same effect of the diffused type endplate. To be more specific, the camber 324 can also largely reduce and even eliminate the serious extent of cavitation on the outer side of the camber 324 itself when operating at inclined-shaft condition or a horizontal shaft condition.
  • FIG. 8 is a top view showing experimental result of a conventional CLT propeller.
  • the endplate is contracted type, the angle of attack of the endplate is +0.1°, the inclined shaft angle is 10°, the cavitation number is 1.5, and the sheet cavitation phenomenon produced at the outer-sides of the endplate when the blade turns to the 0° circumferential position is very serious.
  • FIG. 9A is a top view showing experimental result of a first diffuser-type endplate propeller of the disclosure.
  • the endplate is diffused type, the angle of attack of the endplate is -0.1°, the inclined shaft angle is 8°, the cavitation number is 1.0, and the sheet cavitation phenomenon produced at the outer-sides of the endplate is reduced.
  • FIG. 9B is a top view showing experimental result of a second diffuser-type endplate propeller of the disclosure.
  • the endplate is diffused type, the angle of attack of the endplate is -1°, the inclined shaft angle is 8°, the cavitation number is 1.0, and the sheet cavitation phenomenon produced at the outer-sides of the endplate is greatly reduced.
  • FIG. 9C is a top view showing experimental result of a third diffuser-type endplate propeller of the disclosure.
  • the endplate is also diffused type, the angle of attack of the endplate is -0.8°, the inclined shaft angle is 8°, the cavitation number is 1.0, and the sheet cavitation phenomenon produced at the outer-sides of the endplate is further reduced compared to the first diffuser-type endplate propeller.
  • the first, the second, and the third diffuser-type endplate propellers are similar and the only difference is the angle of attack of the endplate.
  • Each of the first, the second, and the third diffuser-type endplate propellers has four blades and developed area ratio of 0.8.
  • FIG. 9D is a top view showing experimental result of a fourth diffuser-type endplate propeller of the disclosure.
  • the endplate is also diffused type, the developed area ratio is 1.0, the angle of attack of the endplate is -1°, the inclined shaft angle is 8°, the cavitation number is 1.0, and the sheet cavitation phenomenon produced at the outer-sides of the endplate is eliminated.
  • FIG. 9E is a top view showing experimental result of a fifth diffuser-type endplate propeller of the disclosure.
  • the endplate is also diffused type, the developed area ratio is 1.0, the angle of attack of the endplate is -1°, the inclined shaft angle is 8°, the cavitation number is 0.75, and the sheet cavitation phenomenon produced at the outer-sides of the endplate is also eliminated. Therefore, the greater the developed area ratio is, the more effective/the greater the sheet cavitation is reduced.
  • FIG. 9F is a top view showing experimental result of a sixth diffuser-type endplate propeller with five blades of the disclosure.
  • the endplate is also diffused type, the developed area ratio is 1.0, the angle of attack of the endplate is -0.8°, the inclined shaft angle is 10°, the cavitation number is 1.0, and the sheet cavitation phenomenon produced at the outer-sides of the endplate is also eliminated.
  • FIG. 9G is a top view showing experimental result of a seventh diffuser-type endplate propeller with four blades of the disclosure.
  • the endplate is also diffused type, the developed area ratio is 1.0, the angle of attack of the endplate is -0.8°, the inclined shaft angle is 10°, the cavitation number is 1.0, and the sheet cavitation phenomenon produced at the outer-sides of the endplate is also eliminated.
  • the above-mentioned experiments are conducted at the cavitation tunnel of the National Taiwan Ocean University, Keelung, Taiwan.
  • the diffuser-type endplate propeller of the invention prevent the flow at the high-pressure side-surface from back-flowing to the low-pressure side-surface
  • the diffuser-type endplate propeller of the invention can also largely reduce and even eliminate the serious extent of cavitation on the outer side of the endplate itself when operating at inclined-shaft condition.
  • the invention can significantly improve the efficiency of the propeller and largely reduce the vibration and noise produced by the propeller.

Landscapes

  • Chemical & Material Sciences (AREA)
  • Engineering & Computer Science (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • Ocean & Marine Engineering (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)

Claims (6)

  1. Hélice avec les bouts des pales de type diffuseur (100), configurée pour entraîner une coque (20) et comportant :
    un moyeu d'hélice (110) ayant un axe (L) de rotation de l'hélice avec les bouts des pales de type diffuseur (100) et connecté à un arbre de transmission (22) de la coque (20) ; et
    une pluralité de pales (120), ayant respectivement un corps de pale (122) et un bout de pale (124), dans laquelle chaque corps de pale (122) est connecté au moyeu d'hélice (110) et s'étend vers l'extérieur du moyeu d'hélice (110) au bout de pale (124) correspondant, dans laquelle il est prévu que le moyeu d'hélice (110) et les pales (120) sont situés en avant d'une poupe (24) de la coque (20) et chaque bout de pale (124) se courbe depuis le corps de pale (122) correspondant pour s'étendre vers la poupe (24) de la coque (20), chaque bout de pale (120) a un bord d'attaque (124a) et un bord de fuite (124b),
    dans laquelle une surface cylindrique (S1) est imaginairement formée par les bords d'attaque (124a) tandis que l' hélice avec les bouts des pales de type diffuseur (100) est tournée autour de l'axe (L),
    dans laquelle chaque bout de pale (124) a un premier plan tangent (C1) à son bord d'attaque (124a), la surface cylindrique (S1) a un deuxième plan tangent (C2) au bord d'attaque (124a), et
    dans laquelle, tout en regardant d'un côté haute pression de l'hélice avec les bouts des pales de type diffuseur (100), l'hélice avec les bouts des pales de type diffuseur (100) tourne dans le sens des aiguilles d'une montre pour entraîner la coque (20) pour se diriger vers une direction de navigation (A2), et un angle inclus (a) entre le premier plan tangent (C 1) et le deuxième plan tangent (C2) est un angle négatif mesuré du deuxième plan tangent (C2) au premier plan tangent (C1), dans lequel l'angle inclus (a) est supérieur ou égal à -1° et inférieur à 0°,
    dans laquelle le bord d'attaque (324a) garde une première distance de l'axe (L) du moyeu d'hélice (110), le bord de fuite (324b) garde une deuxième distance (R2) de l'axe (L) du moyeu d'hélice (110), caractérisée en ce que la première distance est égale à la deuxième distance (R2) ; et
    dans laquelle chaque bout de pale (324) comprend une première partie (326) et une deuxième partie (328), le bord d'attaque (324a) est situé à la première partie (326) et le bord de fuite (324b) est situé à la deuxième partie (328), et une courbure de la première partie (326) est supérieure à une courbure de la deuxième partie (328), les courbures étant mesurées sur la corde du bout de pale (324).
  2. Hélice avec les bouts des pales de type diffuseur (100) selon la revendication 1, dans laquelle l'axe (L) du moyeu d'hélice (110) n'est pas parallèle à la direction de navigation (A2).
  3. Hélice avec les bouts des pales de type diffuseur (100) selon la revendication 1, qui est moulée d'une seule pièce.
  4. Hélice avec les bouts des pales de type diffuseur (100), configurée pour entraîner une coque (20) et comportant :
    un moyeu d'hélice (110) ayant un axe (L) de rotation de l'hélice avec les bouts des pales de type diffuseur (100) et connecté à un arbre de transmission (22) de la coque (20) ; et
    une pluralité de pales (120), ayant respectivement un corps de pale (122) et un bout de pale (124), dans laquelle chaque corps de pale (122) est connecté au moyeu d'hélice (110) et s'étend vers l'extérieur du moyeu d'hélice (110) au bout de pale (124) correspondant, dans laquelle il est prévu que le moyeu d'hélice (110) et les pales (120) sont situés en avant d'une poupe (24) de la coque (20) et chaque bout de pale (124) se courbe depuis le corps de pale (122) correspondant pour s'étendre vers la poupe (24) de la coque (20), chaque bout de pale (124) a un bord d'attaque (124a) et un bord de fuite (124b),
    dans laquelle une surface cylindrique (S1) est imaginairement formée par les bords d'attaque (124a) tandis que l'hélice avec les bouts des pales de type diffuseur (100) est tournée autour de l'axe (L),
    dans laquelle chaque bout de pale (124) a un premier plan tangent (C1) à son bord d'attaque (124a), la surface cylindrique (S1) a un deuxième plan tangent (C2) au bord d'attaque (124a), et
    dans laquelle, tout en regardant d'un côté haute pression de l'hélice avec les bouts des pales de type diffuseur (100), l'hélice avec les bouts des pales de type diffuseur (100) tourne dans le sens inverse des aiguilles d'une montre pour entraîner la coque (20) pour se diriger vers une direction de navigation (A2), et un angle inclus (a) entre le premier plan tangent (C1) et le deuxième plan tangent (C2) est un angle positif mesuré du deuxième plan tangent (C2) au premier plan tangent (C1), dans laquelle l'angle inclus (a) est supérieur à 0° et inférieur ou égal à 1° ;
    dans laquelle le bord d'attaque (324a) garde une première distance de l'axe (L) du moyeu d'hélice (110), le bord de fuite (324b) garde une deuxième distance (R2) de l'axe (L) du moyeu d'hélice (110), caractérisée en ce que la première distance est égale à la deuxième distance (R2) ; et
    dans laquelle chaque bout de pale (324) comprend une première partie (326) et une deuxième partie (328), le bord d'attaque (324a) est situé à la première partie (326) et le bord de fuite (324b) est situé à la deuxième partie (328), et une courbure de la première partie (326) est supérieure à une courbure de la deuxième partie (328), les courbures étant mesurées sur la corde du bout de pale (324).
  5. Hélice avec les bouts des pales de type diffuseur (100) selon la revendication 4, dans laquelle l'axe (L) du moyeu d'hélice (110) n'est pas parallèle à la direction de navigation (A2).
  6. Hélice avec les bouts des pales de type diffuseur (100) selon la revendication 4, qui est moulée d'une seule pièce.
EP18179727.5A 2018-01-03 2018-06-26 Hélice à plaque d'extrémité de type diffuseur Active EP3508415B1 (fr)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
US15/860,685 US10155575B2 (en) 2013-06-07 2018-01-03 Diffuser-type endplate propeller

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EP3508415A1 EP3508415A1 (fr) 2019-07-10
EP3508415B1 true EP3508415B1 (fr) 2021-12-01

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EP18179727.5A Active EP3508415B1 (fr) 2018-01-03 2018-06-26 Hélice à plaque d'extrémité de type diffuseur

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EP (1) EP3508415B1 (fr)
JP (1) JP2019119436A (fr)
DK (1) DK3508415T3 (fr)
ES (1) ES2904871T3 (fr)

Family Cites Families (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
ES444150A1 (es) * 1976-01-08 1977-05-16 Espanoles Astilleros Perfeccionamientos en los propulsores de los buques.
JPS56167590A (en) * 1980-05-26 1981-12-23 Tetsuhiko Matsumura Propeller
TWI515147B (zh) * 2013-06-07 2016-01-01 國立臺灣海洋大學 擴散型端板螺槳

Non-Patent Citations (1)

* Cited by examiner, † Cited by third party
Title
None *

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ES2904871T3 (es) 2022-04-06
EP3508415A1 (fr) 2019-07-10
JP2019119436A (ja) 2019-07-22
DK3508415T3 (da) 2022-02-28

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