JPH0826186A - Propeller with blade tip plate - Google Patents
Propeller with blade tip plateInfo
- Publication number
- JPH0826186A JPH0826186A JP6161624A JP16162494A JPH0826186A JP H0826186 A JPH0826186 A JP H0826186A JP 6161624 A JP6161624 A JP 6161624A JP 16162494 A JP16162494 A JP 16162494A JP H0826186 A JPH0826186 A JP H0826186A
- Authority
- JP
- Japan
- Prior art keywords
- blade
- propeller
- tip
- wing
- blades
- 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.)
- Pending
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
- B63H1/18—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
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)
Abstract
Description
【０００１】[0001]
【産業上の利用分野】本発明は、船舶に使用されるとこ
ろの、複数の翼の各翼端に軸方向に張り出した翼端板を
付けた翼端板付きプロペラに関するものである。BACKGROUND OF THE INVENTION 1. Field of the Invention The present invention relates to a propeller with a wing tip plate, which is used in a ship, in which a wing tip plate extending in the axial direction is attached to each wing tip of a plurality of blades.
【０００２】[0002]
【従来の技術】従来、船舶に使用されるプロペラにおい
ては、プロペラ効率の向上や燃料消費量の節減を図るた
めに、翼端に付属物を設けたプロペラが知られている。
この種のプロペラにおいては、翼端まで大きい幅を持た
せることにより、翼端部にも大きい荷重を分担させて翼
面荷重分布をラジアル方向に均一化させており、各翼端
に軸方向に張り出した翼端板を設けている。2. Description of the Related Art Conventionally, as a propeller used in a ship, a propeller provided with an accessory at a wing tip is known in order to improve propeller efficiency and reduce fuel consumption.
In this type of propeller, by giving a large width to the blade tip, a large load is also shared by the blade tip to even out the blade surface load distribution in the radial direction, and each blade tip is axially distributed in the axial direction. It has a wing tip plate overhanging.
【０００３】この翼端板は、翼後面（高圧面）の翼先端
部に水を封じ込めて、翼先端部においても高い水圧を発
生させるためのものである。換言すれば、もしこの翼端
板がないと、翼端部の幅を大きくしても、翼後面（高圧
面）の翼端部における圧力が翼前面（低圧面）に抜けて
しまうために、幅を大きくした翼端部に高い水圧を維持
させることができなくなる。すなわち、翼端部にも大き
い荷重を負担させて翼面分布荷重をラジアル方向に均一
化させるという目的が達成できないことになり、従っ
て、プロペラ効率を向上させることができない。This blade tip plate is for confining water in the blade tip portion on the rear surface (high pressure surface) of the blade and for generating high water pressure also in the blade tip portion. In other words, without this blade tip, even if the width of the blade tip is increased, the pressure at the blade tip of the blade rear surface (high pressure surface) escapes to the blade front surface (low pressure surface). It becomes impossible to maintain a high water pressure at the blade tip with the increased width. That is, it is impossible to achieve the purpose of uniformizing the blade surface distributed load in the radial direction by applying a large load to the blade tip portion, and therefore it is not possible to improve the propeller efficiency.
【０００４】上述のことを図３〜図４に基づいてより具
体的に説明する。図３に示す通常のプロペラ１５におい
ては、翼端における荷重をゼロにするような翼面荷重分
布とするために、翼端部１６において翼幅が漸減され、
翼端１７において幅がゼロ（点）となされている。これ
に対して、図４に示す翼端板付きプロペラ２１において
は、翼端部２２をも大きい翼幅となし、翼端部２２にお
いても荷重を受けられるようにしている。このプロペラ
２１が期待通りに作動すれば、翼面荷重分布がラジアル
方向において均一化されるので、プロペラ効率が高くな
り、プロペラ寸法を小さくすることができる。一方で、
翼端部２２をも大きい翼幅とした場合には、翼端２３に
も荷重がかかり、翼先端にも高圧が発生し、翼端２３に
おける翼後面（高圧面）２４から翼前面（低圧面）２５
へ向けた流れが生起して圧力喪失および翼端渦の発生
（即ちキャビテーションの発生）を必然的に招くことに
なるので、この弊害を防止するために、各翼端２３の後
面側に全幅にわたって軸方向に張り出した翼端板２６を
設けている。The above will be described more specifically with reference to FIGS. In the normal propeller 15 shown in FIG. 3, the blade width is gradually reduced at the blade tip 16 in order to obtain a blade surface load distribution that makes the load at the blade tip zero.
The width at the blade tip 17 is zero (point). On the other hand, in the propeller 21 with a wing tip plate shown in FIG. 4, the wing tip 22 also has a large wing width so that the wing tip 22 can also receive a load. If the propeller 21 operates as expected, the blade surface load distribution is made uniform in the radial direction, so that the propeller efficiency is increased and the propeller size can be reduced. On the other hand,
When the blade tip 22 also has a large blade width, a load is also applied to the blade tip 23 and high pressure is generated at the blade tip, and the blade rear surface (high pressure surface) 24 at the blade tip 23 is changed to the blade front surface (low pressure surface). ) 25
Since a flow toward the blades inevitably causes pressure loss and generation of blade tip vortices (that is, cavitation), in order to prevent this adverse effect, the entire width is applied to the rear surface side of each blade tip 23. A wing tip plate 26 that projects in the axial direction is provided.
【０００５】[0005]
【発明が解決しようとする課題】上記した構成におい
て、翼端板２６は、翼後面（高圧面）２４の先端部に水
を封じ込めて翼先端部に高い水圧を維持させるが、他
方、翼後面（高圧面）２４の先端部においても圧力が大
きいために、高圧部と低圧部の境界域、すなわち翼先端
部の前縁と後縁のそれぞれの翼前面と後面の境界部分に
おいて、翼面上に形成される水の境界層の一部が、局部
的に高圧側から低圧側に急激に変化する。このことによ
り、流れの状態によっては、翼先端部の前縁と後縁の翼
前面（低圧面）側で、局所的に境界層の剥離（通常、そ
の剥離領域は小さいものであるが）を生ずる可能性があ
り、もし境界層の剥離が生ずると、剥離に伴って生ずる
渦によって翼の抵抗が増加するという問題があった。In the above structure, the blade tip plate 26 confines water at the tip of the blade rear surface (high pressure surface) 24 to maintain a high water pressure at the blade tip, while the blade rear plate 26 Since the pressure is large even at the tip of the (high pressure surface) 24, on the blade surface at the boundary region between the high pressure portion and the low pressure portion, that is, at the boundary portion between the front surface and the rear surface of the leading edge and the trailing edge of the blade tip, respectively. A part of the boundary layer of water formed locally changes rapidly from the high pressure side to the low pressure side. Due to this, depending on the flow conditions, the boundary layer is locally separated (usually the separation area is small) locally on the blade front surface (low pressure surface) side of the leading edge and trailing edge of the blade tip. If there is separation of the boundary layer, there is a problem that the resistance of the blade increases due to the vortex that accompanies the separation.
【０００６】翼表面に形成される境界層が翼前面（低圧
面）の先端部で剥離を生ずる場合、前縁部では層流層の
剥離、後縁部では層流から乱流に遷移しての乱流層の剥
離となることが実験で確かめられた（何れも、剥離領域
は小さいものではある）。When the boundary layer formed on the blade surface causes separation at the tip of the blade front surface (low pressure surface), separation of the laminar flow layer occurs at the leading edge and transition from laminar flow to turbulent flow occurs at the trailing edge. It was confirmed by experiments that the turbulent flow layer was separated (in both cases, the separation region was small).
【０００７】境界層が層流から乱流に変ると、その層は
厚くなって摩擦抵抗が多少増加するが、一方で、乱流へ
の変化は、境界層を剥離し難くするとともに、その発生
点をずらせて剥離領域を小さくするので、全体として、
抵抗は層流剥離に比べて著しく小さいものである。従っ
て、翼端板付きプロペラにおいては、翼前面（低圧面）
の先端部の前縁と後縁における水の境界層の剥離のう
ち、前縁部で発生する可能性のある層流剥離を抑制する
ことにより、最も効果的に翼端板付きプロペラの抵抗を
減少させ得ることが判った。When the boundary layer changes from laminar flow to turbulent flow, the layer becomes thicker and frictional resistance increases to some extent. On the other hand, the change to turbulent flow makes it difficult for the boundary layer to separate and at the same time occurs. Since the peeling area is made smaller by shifting the points, overall,
The resistance is significantly smaller than that of laminar separation. Therefore, in a propeller with a wing tip plate, the wing front surface (low pressure surface)
Among the separation of the boundary layer of water at the leading and trailing edges of the blade tip, by suppressing the laminar flow separation that may occur at the leading edge, the resistance of the propeller with tip plate is most effectively reduced. It turned out that it can be reduced.
【０００８】本発明は、翼先端部での翼面高負荷特性を
本質的に損うことなくして、流れの状態によっては発生
する可能性のある翼前面（低圧面）先端部の前縁での境
界層剥離を抑制し、プロペラ抵抗を最小にする翼端板付
きプロペラを提供することを目的とする。According to the present invention, the leading edge of the front surface (low pressure surface) of the blade, which may occur depending on the flow condition, is generated without essentially impairing the high load characteristic of the blade surface at the blade tip. An object of the present invention is to provide a propeller with a wing tip plate that suppresses the separation of the boundary layer of the propeller and minimizes propeller resistance.
【０００９】[0009]
【課題を解決するための手段】上記した課題を解決する
ために、本発明の翼端板付きプロペラは、プロペラボス
にラジアル方向に延びる複数葉の翼を設け、各翼の翼端
を円弧形状に形成するとともに、各翼の後面側に軸方向
に張り出す翼端板を翼端に沿って設けた翼端板付きプロ
ペラであって、プロペラの回転方向において翼端板の前
縁をなす端板前縁が翼の前縁をなす翼前縁より適当距離
だけ後退して位置する構成としたものである。In order to solve the above-mentioned problems, a propeller with a wing tip plate according to the present invention is provided with a plurality of blades extending in a radial direction in a propeller boss, and each wing tip has an arc shape. A propeller with a wing tip plate formed on the rear surface side of each wing and extending in the axial direction along the wing tip, the end forming the leading edge of the wing tip plate in the rotation direction of the propeller. The plate leading edge is arranged so as to be set back by an appropriate distance from the blade leading edge forming the leading edge of the blade.
【００１０】[0010]
【作用】上記した構成により、プロペラの翼の回転によ
り、流れが翼の後面（高圧面）を通過するとき、翼先端
部における流れが翼端板によって翼後面（高圧面）上に
封じ込められ、高圧側である翼後面の翼先端部から低圧
側である翼前面の翼先端部に逸流する（すなわち、圧力
が低下する）ことが阻止される。このことから、翼後面
（高圧面）の側において、翼先端部にまで圧力（すなわ
ち推力）を分布させ得、翼面の荷重分布がラジアル方向
に均一化される。With the above structure, when the flow of the propeller blade rotates and the flow passes through the rear surface (high pressure surface) of the blade, the flow at the blade tip is confined on the rear surface (high pressure surface) of the blade by the blade end plate. It is prevented that the blade tip on the rear surface of the blade on the high pressure side flows to the blade tip on the front surface of the blade on the low pressure side (that is, the pressure decreases). From this, on the rear surface (high pressure surface) side of the blade, pressure (that is, thrust) can be distributed to the tip of the blade, and the load distribution on the blade surface is made uniform in the radial direction.
【００１１】これにより、推力がプロペラボスから翼先
端部まで連続的に増加するような分布とすることがで
き、以って高いプロペラ効率が得られ、プロペラ寸法も
小さくすることができる。この際、翼端板の前縁が翼の
前縁よりも後退して位置していることから、この後退部
分については局所的に翼表面上への水の封じ込めがな
い。すなわち、翼後面（高圧面）先端部前縁の部分は局
所的に、翼端板が存在する部分に比べて圧力が低い。従
って、この翼先端部前縁の部分での翼後面（高圧面）の
側から翼前面（低圧面）の側への急激な圧力変化がな
く、このため翼前面（低圧面）の先端前縁の部分におけ
る水の翼面境界層の層流剥離の発生、すなわち剥離渦の
発生が避けられ、剥離渦によるプロペラ抵抗の増加が避
けられる。Thus, the thrust can be distributed so as to continuously increase from the propeller boss to the tip of the blade, whereby high propeller efficiency can be obtained and the propeller size can be reduced. At this time, since the leading edge of the wing tip plate is located receding from the leading edge of the wing, there is no local containment of water on the wing surface in this receding portion. That is, the pressure is locally lower at the front edge portion of the blade rear surface (high pressure surface) than at the portion where the blade is present. Therefore, there is no abrupt pressure change from the blade rear surface (high pressure surface) side to the blade front surface (low pressure surface) side at the blade tip front edge portion, and therefore the blade front surface (low pressure surface) tip front edge It is possible to avoid the occurrence of laminar flow separation of the blade surface boundary layer of water in the area, that is, the generation of separation vortices, and the increase in propeller resistance due to the separation vortices.
【００１２】他方、翼端板の後退部分における局所的な
翼面圧力の減少は、後退部分を有さない翼端板付きプロ
ペラの場合に比べて、翼先端部における荷重負担能力を
若干減少させるもののその量は僅かであり、翼端板の後
退部分がない場合において翼先端前縁部に生じる水の翼
面境界層の剥離によるプロペラ抵抗の増大の方がはるか
に影響が大きい。On the other hand, the local reduction of the blade surface pressure at the retreat portion of the blade tip plate slightly reduces the load bearing capacity at the blade tip as compared with the case of the propeller with the blade tip plate having no retreat portion. However, the amount is small, and the increase of the propeller resistance due to the separation of the blade boundary layer of water that occurs at the leading edge of the blade in the absence of the receding portion of the blade is much more significant.
【００１３】[0013]
【実施例】以下、本発明の一実施例を図面に基づいて説
明する。図１〜図２において、翼端板付きプロペラ１の
翼２は、必要なピッチと曲面形状をもって各々が得られ
るようにする。すなわち翼２は、プロペラボス３からラ
ジアル方向に延び、その翼幅は、プロペラボス３からラ
ジアル方向に進むにつれて漸増し、最大幅部を経てから
漸減するか、あるいは翼端４まで漸増し続ける。いずれ
にせよ、その翼端４に至っても十分な幅を有する。An embodiment of the present invention will be described below with reference to the drawings. 1 to 2, the blades 2 of the propeller 1 with a blade end plate are each obtained with a required pitch and curved surface shape. That is, the blade 2 extends from the propeller boss 3 in the radial direction, and its blade width gradually increases as it advances from the propeller boss 3 in the radial direction, and then gradually decreases after reaching the maximum width portion or continues to increase to the blade tip 4. In any case, even if it reaches the blade tip 4, it has a sufficient width.
【００１４】各々の翼端４は円弧形状をなしており、各
翼２の翼先端弧の外周には、翼先端弧の先端形状に一致
する翼端板５を、翼後面６の側に軸方向に張り出して一
体に設けている。この翼端板５は、プロペラ１の回転方
向において翼端板５の前縁をなす端板前縁５ａが翼２の
前縁をなす翼前縁２ａより適当距離だけ後退して位置す
るような形状をなしており、端板前縁５ａは抵抗の小さ
い適当な形状に仕上げている。この端板前縁５ａの後退
量は条件により異なるが、一般的に翼先端弧の弧長さの
１０〜２０％程度とする。Each wing tip 4 has an arc shape, and a wing tip plate 5 matching the tip shape of the wing tip arc is provided on the outer periphery of the wing tip arc of each wing 2 on the rear surface 6 side of the wing. It projects in the direction and is integrated. The wing tip plate 5 has a shape such that the end plate front edge 5a forming the front edge of the wing end plate 5 is located at a proper distance from the wing front edge 2a forming the front edge of the wing 2 in the rotational direction of the propeller 1. The front edge 5a of the end plate is finished in an appropriate shape with low resistance. Although the amount of retreat of the front edge 5a of the end plate varies depending on the conditions, it is generally about 10 to 20% of the arc length of the blade tip arc.
【００１５】尚、翼端板５と翼２との間の角度は、翼端
板５の軸方向長さが相対的に極めて小さいために性能に
はほとんど影響を及ぼさない。以下、上記構成における
作用を説明する。プロペラの翼２の回転により、流れが
翼２の後面（高圧面）６を通過するとき、翼先端部にお
ける流れが翼端板５によって翼後面（高圧面）６上に封
じ込められ、高圧側である翼後面６の翼先端部から低圧
側である翼前面の翼先端部に逸流する（すなわち、圧力
が低下する）ことが阻止される。このことから、翼後面
（高圧面）６の側において、翼先端部までも圧力（すな
わち推力）を分布させ得、翼面の荷重分布がラジアル方
向に均一化される。これにより、推力がプロペラボス３
から翼先端部まで連続的に増加するような分布とするこ
とができ、以って高いプロペラ効率が得られ、プロペラ
寸法も小さくすることができる。この際、翼端板５の前
縁が翼２の前縁よりも後退して位置していることから、
この後退部分については局所的に翼表面上への水の封じ
込めがない。すなわち、翼後面（高圧面）６の先端部前
縁の部分は局所的に、翼端板５が存在する部分に比べて
圧力が低い。従って、この翼後面（高圧面）６の先端部
前縁の部分での翼後面（高圧面）６の側から翼前面（低
圧面）の側への急激な圧力変化がなく、このため翼前面
（低圧面）の先端前縁の部分における水の翼面境界層の
層流剥離の発生、すなわち剥離渦の発生が避けられ、剥
離渦によるプロペラ抵抗の増加が避けられる。The angle between the wing tip plate 5 and the wing 2 has little effect on the performance because the axial length of the wing tip plate 5 is relatively small. The operation of the above configuration will be described below. When the flow passes through the rear surface (high pressure surface) 6 of the blade 2 due to the rotation of the propeller blade 2, the flow at the tip of the blade is confined on the rear surface (high pressure surface) 6 of the blade by the blade end plate 5, and at the high pressure side. It is prevented that the blade tip portion of a certain blade rear surface 6 leaks to the blade tip portion of the blade front surface on the low pressure side (that is, the pressure is reduced). From this, on the blade rear surface (high pressure surface) 6 side, pressure (that is, thrust) can be distributed even to the blade tip portion, and the load distribution on the blade surface is made uniform in the radial direction. As a result, the thrust is propeller boss 3
The distribution can be continuously increased from to the tip of the blade, whereby high propeller efficiency can be obtained and the propeller size can be reduced. At this time, since the leading edge of the wing tip plate 5 is located rearward of the leading edge of the wing 2,
There is no local containment of water on the wing surface for this receding part. That is, the pressure at the tip front edge portion of the blade rear surface (high pressure surface) 6 is locally lower than that at the portion where the blade end plate 5 is present. Therefore, there is no abrupt pressure change from the blade rear surface (high pressure surface) 6 side to the blade front surface (low pressure surface) side at the tip front edge portion of this blade rear surface (high pressure surface) 6, and therefore the blade front surface The occurrence of laminar flow separation of the blade surface boundary layer of water, that is, the generation of separation vortices, is avoided at the leading edge portion of the (low pressure surface), and an increase in propeller resistance due to separation vortices is avoided.
【００１６】他方、翼端板５の後退部分における局所的
な翼面圧力の減少は、後退部分を有さない翼端板付きプ
ロペラの場合に比べて、翼先端部における荷重負担能力
を若干減少させるもののその量は僅かであり、翼端板５
の後退部分がない場合において翼先端前縁部に生じる水
の翼面境界層の剥離によるプロペラ抵抗の増大の方が、
はるかに影響が大きい。On the other hand, the local reduction of the blade surface pressure in the retreat portion of the blade tip plate 5 reduces the load bearing capacity at the blade tip portion slightly as compared with the case of the propeller with the blade tip plate having no retreat portion. However, the amount of the wing tip plate 5 is small.
The increase in propeller resistance due to the separation of the wing surface boundary layer of water that occurs at the leading edge of the blade when there is no receding part of
The impact is much greater.
【００１７】本発明の翼端板付きプロペラ１は、上記の
実施例に限るものではなく、推進器以外のプロペラ、例
えば、バウスラスター、ノズル・プロペラなどのプロペ
ラに適用しても、また、可変ピッチ・プロペラに適用し
ても、同様の作用効果を発揮する。The propeller 1 with wing tip plate according to the present invention is not limited to the above-mentioned embodiment, but can be applied to propellers other than the propeller, for example, propellers such as bow thruster and nozzle propeller. Even if it is applied to a pitch propeller, the same effect is exhibited.
【００１８】[0018]
【発明の効果】以上述べたように本発明によれば、翼端
板の前縁をなす端板前縁が翼の前縁をなす翼前縁より適
当距離だけ後退して位置させることにより、翼面上に、
翼先端部までも十分な推力を分布させ得て、以って高い
プロペラ効率が得られ、プロペラ寸法も小さくし得るう
え、翼端板付きプロペラにおいて水流の状態によっては
起る可能性のあった翼先端前縁部における水の翼面境界
層の剥離渦の発生を抑えられ、以ってプロペラ抵抗を大
幅に減少させ得るなど、卓越した効果を発揮し得る。As described above, according to the present invention, the front edge of the blade, which constitutes the leading edge of the blade, is set back by a proper distance from the leading edge of the blade, which is the leading edge of the blade, and thus the blade is On the surface,
Sufficient thrust can be distributed even to the tip of the blade, resulting in high propeller efficiency and a small propeller size, which may occur depending on the water flow in the propeller with blade end plates. The generation of separation vortices in the water surface boundary layer at the leading edge of the blade can be suppressed, and the propeller resistance can be greatly reduced.
【図１】本発明の一実施例における翼端板付きプロペラ
を示す斜視図である。FIG. 1 is a perspective view showing a propeller with a wing tip plate according to an embodiment of the present invention.
【図２】同実施例におけるＭ部の平面図である。FIG. 2 is a plan view of an M portion in the example.
【図３】通常のプロペラを後方かつ下方から見た外観斜
視図である。FIG. 3 is an external perspective view of a normal propeller as viewed from the rear and from below.
【図４】従来の翼端板付きプロペラを後方かつ下方から
見た外観斜視図である。FIG. 4 is an external perspective view of a conventional propeller with wing end plates as viewed from the rear and from below.
１ 翼端板付きプロペラ ２ 翼 ２ａ 翼前縁 ３ プロペラボス ４ 翼端 ５ 翼端板 ５ａ 端板前縁 ６ 翼後面（高圧面） 1 propeller with wing tip plate 2 wing 2a wing leading edge 3 propeller boss 4 wing tip 5 wing end plate 5a end plate leading edge 6 wing rear surface (high pressure surface)
Claims (1)
数葉の翼を設け、各翼の翼端を円弧形状に形成するとと
もに、各翼の後面側に軸方向に張り出す翼端板を翼端に
沿って設けた翼端板付きプロペラであって、プロペラの
回転方向において翼端板の前縁をなす端板前縁が翼の前
縁をなす翼前縁より適当距離だけ後退して位置すること
を特徴とする翼端板付きプロペラ。1. A propeller boss is provided with blades having a plurality of leaves extending in a radial direction, the blade tips of the blades are formed in an arc shape, and a blade tip plate extending axially to the rear surface side of each blade is provided at the blade tip. A propeller with a wing end plate provided along the wing tip plate, wherein the end plate leading edge forming the leading edge of the wing end plate is positioned at a proper distance from the wing leading edge forming the leading edge of the wing in the rotational direction of the propeller. A characteristic propeller with a wing tip plate.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| JP6161624A JPH0826186A (en) | 1994-07-14 | 1994-07-14 | Propeller with blade tip plate |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| JP6161624A JPH0826186A (en) | 1994-07-14 | 1994-07-14 | Propeller with blade tip plate |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| JPH0826186A true JPH0826186A (en) | 1996-01-30 |
Family
ID=15738724
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| JP6161624A Pending JPH0826186A (en) | 1994-07-14 | 1994-07-14 | Propeller with blade tip plate |
Country Status (1)
| Country | Link |
|---|---|
| JP (1) | JPH0826186A (en) |
Cited By (10)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| DE10246886A1 (en) * | 2002-10-08 | 2004-04-22 | Helmut Obieglo | Marine propeller screw blade has flow edge as wing or nozzle normal to screw blade right across blade for added hydrodynamicity. |
| JP2011226376A (en) * | 2010-04-20 | 2011-11-10 | Mitsubishi Heavy Ind Ltd | Turbo machine |
| US8261681B2 (en) | 2005-06-17 | 2012-09-11 | Aloys Wobben | Ship |
| KR101225177B1 (en) * | 2010-07-16 | 2013-01-22 | 삼성중공업 주식회사 | Propeller and ship including the same |
| KR101422225B1 (en) * | 2012-11-16 | 2014-07-22 | 삼성중공업 주식회사 | Vessel having auxiliary propulsion apparatus |
| US8950353B2 (en) | 2010-09-16 | 2015-02-10 | Wobben Properties Gmbh | Ship and gangway for the same |
| US9205903B2 (en) | 2010-04-06 | 2015-12-08 | Wobben Properties Gmbh | Ship with at least one sail rotor and adjustable panel at the bow |
| CN107140166A (en) * | 2017-05-26 | 2017-09-08 | 巢湖市银环航标有限公司 | A kind of preposition hull tractor of deployable and collapsible |
| EP2631168A4 (en) * | 2010-10-19 | 2017-09-20 | Mitsubishi Heavy Industries, Ltd. | Propulsion device and ship using same |
| CN108698678A (en) * | 2016-03-01 | 2018-10-23 | 株式会社铃诗苑 | Horizontal axis rotor and the boat for having horizontal axis rotor |
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|---|---|---|---|---|
| JPS5366696A (en) * | 1976-01-08 | 1978-06-14 | Espanoles Astilleros | Marine screw |
| JPS60186299U (en) * | 1984-05-21 | 1985-12-10 | 近藤 亘裕 | Marine screw with current plate |
| JPS62157891A (en) * | 1986-01-04 | 1987-07-13 | Yoshiro Nakamatsu | Flow feed straightening blade |
| JPH0710089A (en) * | 1993-06-25 | 1995-01-13 | Ishikawajima Harima Heavy Ind Co Ltd | Propeller blade for aircraft |
-
1994
- 1994-07-14 JP JP6161624A patent/JPH0826186A/en active Pending
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPS5366696A (en) * | 1976-01-08 | 1978-06-14 | Espanoles Astilleros | Marine screw |
| JPS60186299U (en) * | 1984-05-21 | 1985-12-10 | 近藤 亘裕 | Marine screw with current plate |
| JPS62157891A (en) * | 1986-01-04 | 1987-07-13 | Yoshiro Nakamatsu | Flow feed straightening blade |
| JPH0710089A (en) * | 1993-06-25 | 1995-01-13 | Ishikawajima Harima Heavy Ind Co Ltd | Propeller blade for aircraft |
Cited By (12)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| DE10246886A1 (en) * | 2002-10-08 | 2004-04-22 | Helmut Obieglo | Marine propeller screw blade has flow edge as wing or nozzle normal to screw blade right across blade for added hydrodynamicity. |
| US8261681B2 (en) | 2005-06-17 | 2012-09-11 | Aloys Wobben | Ship |
| KR101238612B1 (en) * | 2005-06-17 | 2013-02-28 | 워벤 알로이즈 | Ship comprising magnus rotors |
| US8601964B2 (en) | 2005-06-17 | 2013-12-10 | Wobben Properties Gmbh | Ship |
| US9205903B2 (en) | 2010-04-06 | 2015-12-08 | Wobben Properties Gmbh | Ship with at least one sail rotor and adjustable panel at the bow |
| JP2011226376A (en) * | 2010-04-20 | 2011-11-10 | Mitsubishi Heavy Ind Ltd | Turbo machine |
| KR101225177B1 (en) * | 2010-07-16 | 2013-01-22 | 삼성중공업 주식회사 | Propeller and ship including the same |
| US8950353B2 (en) | 2010-09-16 | 2015-02-10 | Wobben Properties Gmbh | Ship and gangway for the same |
| EP2631168A4 (en) * | 2010-10-19 | 2017-09-20 | Mitsubishi Heavy Industries, Ltd. | Propulsion device and ship using same |
| KR101422225B1 (en) * | 2012-11-16 | 2014-07-22 | 삼성중공업 주식회사 | Vessel having auxiliary propulsion apparatus |
| CN108698678A (en) * | 2016-03-01 | 2018-10-23 | 株式会社铃诗苑 | Horizontal axis rotor and the boat for having horizontal axis rotor |
| CN107140166A (en) * | 2017-05-26 | 2017-09-08 | 巢湖市银环航标有限公司 | A kind of preposition hull tractor of deployable and collapsible |
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