JP6885168B2 - blade - Google Patents

blade Download PDF

Info

Publication number
JP6885168B2
JP6885168B2 JP2017076661A JP2017076661A JP6885168B2 JP 6885168 B2 JP6885168 B2 JP 6885168B2 JP 2017076661 A JP2017076661 A JP 2017076661A JP 2017076661 A JP2017076661 A JP 2017076661A JP 6885168 B2 JP6885168 B2 JP 6885168B2
Authority
JP
Japan
Prior art keywords
reinforcing member
blade
main body
joint portion
wing
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.)
Active
Application number
JP2017076661A
Other languages
Japanese (ja)
Other versions
JP2018178800A (en
Inventor
祥 村田
祥 村田
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.)
IHI Corp
Original Assignee
IHI Corp
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 IHI Corp filed Critical IHI Corp
Priority to JP2017076661A priority Critical patent/JP6885168B2/en
Publication of JP2018178800A publication Critical patent/JP2018178800A/en
Application granted granted Critical
Publication of JP6885168B2 publication Critical patent/JP6885168B2/en
Active legal-status Critical Current
Anticipated expiration legal-status Critical

Links

Images

Classifications

    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02E—REDUCTION OF GREENHOUSE GAS [GHG] EMISSIONS, RELATED TO ENERGY GENERATION, TRANSMISSION OR DISTRIBUTION
    • Y02E10/00—Energy generation through renewable energy sources
    • Y02E10/20—Hydro energy
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02E—REDUCTION OF GREENHOUSE GAS [GHG] EMISSIONS, RELATED TO ENERGY GENERATION, TRANSMISSION OR DISTRIBUTION
    • Y02E10/00—Energy generation through renewable energy sources
    • Y02E10/30—Energy from the sea, e.g. using wave energy or salinity gradient

Landscapes

  • Hydraulic Turbines (AREA)
  • Other Liquid Machine Or Engine Such As Wave Power Use (AREA)

Description

本開示は、リーディングエッジおよびトレーリングエッジを有するブレードに関する。 The present disclosure relates to blades having a leading edge and a trailing edge.

近年、海洋における海水の運動エネルギーによって発電する海洋発電の研究が進められている。海洋発電には、潮の満ち引きを利用する潮流発電の他に、海流を利用する海流発電がある。海流発電では、定常的な海流を利用することで、昼夜や季節を問わず、長期的かつ安定的な発電を実現する可能性がある。 In recent years, research on ocean power generation, which uses the kinetic energy of seawater in the ocean to generate electricity, has been underway. Marine power generation includes ocean current power generation that uses ocean currents, in addition to tidal current power generation that uses the ebb and flow of the tide. In ocean current power generation, there is a possibility of realizing long-term and stable power generation regardless of day and night or season by using a steady ocean current.

例えば、特許文献１には、回転型の翼が記載されている。翼本体には、コードライン方向の幅が最大となる幅広部が形成される。翼本体のリーディングエッジは、先端部（回転中心の反対側の端部）から幅広部まで樹脂層(もしくは複合材料層)で覆われている。 For example, Patent Document 1 describes a rotary blade. A wide portion having a maximum width in the cord line direction is formed on the wing body. The leading edge of the wing body is covered with a resin layer (or composite material layer) from the tip portion (the end opposite to the center of rotation) to the wide portion.

特開２００７−１７０３２８号公報JP-A-2007-170328

翼本体は、２つの分割体を接合して形成される場合がある。翼本体に荷重が作用すると、接合部に応力が作用するため、接合部の強度を向上する技術の開発が希求される。 The wing body may be formed by joining two divided bodies. When a load acts on the blade body, stress acts on the joint, so the development of a technique for improving the strength of the joint is desired.

本開示は、このような課題に鑑み、翼本体の接合の強度を向上することができるブレードを提供することを目的としている。 In view of such a problem, the present disclosure aims to provide a blade capable of improving the joint strength of the blade body.

上記課題を解決するために、本開示の一態様に係るブレードは、第１本体部材および第２本体部材が接合部で接合された翼本体と、翼本体の基端側と接続された接続部材と、接続部材に対して径方向に対向する位置から延在し、翼本体のリーディングエッジ側の接合部を覆う第１補強部材と、接続部材に対して径方向に対向する位置から延在し、翼本体のトレーリングエッジ側の接合部を覆う第２補強部材と、を備え、第１補強部材と第２補強部材とは、翼本体の周方向に離隔して配置され、第１補強部材は、第２補強部材よりも翼本体の先端側まで延在する。 In order to solve the above problems, the blade according to one aspect of the present disclosure includes a wing body in which the first main body member and the second main body member are joined at a joint, and a connecting member connected to the base end side of the wing body. And the first reinforcing member that extends from the position that faces the connecting member in the radial direction and covers the joint on the leading edge side of the wing body, and extends from the position that faces the connecting member in the radial direction. A second reinforcing member that covers the joint portion on the trailing edge side of the wing body is provided , and the first reinforcing member and the second reinforcing member are arranged apart from each other in the circumferential direction of the wing body, and the first reinforcing member is provided. Extends to the tip end side of the wing body from the second reinforcing member .

翼本体のリーディングエッジは、ピークを備え、第１補強部材は、ピークを越えて延伸してもよい。 Leading edge of the blade main body is provided with a peak, the first reinforcing member may be stretched beyond the peak.

接合部は、第１補強部材より翼本体の先端側に延在してもよい。 The joint portion may extend from the first reinforcing member to the tip end side of the blade body.

リーディングエッジ側の接合部の広さは、第１補強部材に覆われた位置において最小となってもよい。 The width of the joint on the leading edge side may be minimized at the position covered by the first reinforcing member.

接合部は、第２補強部材より翼本体の先端側に延在してもよい。 The joint portion may extend from the second reinforcing member to the tip end side of the blade body.

トレーリングエッジ側の接合部の広さは、第２補強部材より翼本体の先端側に延在する位置において最大となってもよい。 The width of the joint portion on the trailing edge side may be maximized at a position extending from the second reinforcing member to the tip end side of the blade body.

翼本体は、繊維強化複合材料が積層されたものであり、接合部は、翼本体の内面側から外面側に向かい積層された断面同士が接合されていてもよい。 The wing body is made by laminating fiber-reinforced composite materials, and the joint portion may be joined to each other by laminating cross sections from the inner surface side to the outer surface side of the wing body.

上記課題を解決するために、本開示の一態様に係る他のブレードは、第１本体部材および第２本体部材が接合部で接合された翼本体と、翼本体のリーディングエッジおよびトレーリングエッジの双方に形成されたピークと、翼本体のリーディングエッジのピークよりも、翼本体の先端側から基端側まで、翼本体のリーディングエッジ側の接合部の外側を覆う第１補強部材と、翼本体のトレーリングエッジのピークよりも、翼本体の先端側から基端側まで、翼本体のトレーリングエッジ側の接合部の外側を覆う第２補強部材と、を備え、第１補強部材と第２補強部材とは、翼本体の周方向に離隔して配置され、第１補強部材は、第２補強部材よりも翼本体の先端側まで延在する。 In order to solve the above problems, other blades according to one aspect of the present disclosure include a wing body in which a first main body member and a second main body member are joined at a joint, and a leading edge and a trailing edge of the wing body. a peak formed in the twin who, than the peak of the leading edge of the blade main body, from the tip side of the blade body to the base end side, a first reinforcing member covering the outside of the junction of the leading edge side of the blade body, wings A second reinforcing member that covers the outside of the joint on the trailing edge side of the wing body from the tip end side to the base end side of the wing body from the peak of the trailing edge of the main body is provided , and the first reinforcing member and the first reinforcing member are provided. The two reinforcing members are arranged apart from each other in the circumferential direction of the blade body, and the first reinforcing member extends beyond the second reinforcing member to the tip end side of the blade body .

本開示によれば、翼本体の接合の強度を向上することが可能となる。 According to the present disclosure, it is possible to improve the joint strength of the blade body.

海流発電装置の斜視図である。It is a perspective view of the ocean current power generation device. 図２（ａ）は、ブレードをロータの回転軸方向、つまり、ブレードを挟んで発電機と反対側から見た場合の正面図である。図２（ｂ）は、ブレードの上面図である。図２（ｃ）は、ブレードの側面図である。FIG. 2A is a front view of the blade in the direction of the rotation axis of the rotor, that is, when the blade is viewed from the side opposite to the generator with the blade in between. FIG. 2B is a top view of the blade. FIG. 2C is a side view of the blade. 図３（ａ）は、ブレードの斜視図である。図３（ｂ）は、ブレードの分解斜視図である。FIG. 3A is a perspective view of the blade. FIG. 3B is an exploded perspective view of the blade. 図２（ａ）のＩＶ−ＩＶ線断面図である。FIG. 2 is a sectional view taken along line IV-IV of FIG. 2 (a). 図２（ａ）のＶ−Ｖ線断面図である。FIG. 2 is a sectional view taken along line VV of FIG. 2A. 図６（ａ）は、図２（ａ）のＶＩａ−ＶＩａ断面図である。図６（ｂ）は、図２（ａ）のＶＩｂ−ＶＩｂ断面図である。図６（ｃ）は、図２（ａ）のＶＩｃ−ＶＩｃ断面図である。図６（ｄ）は、図２（ａ）のＶＩｄ−ＶＩｄ断面図である。6 (a) is a sectional view taken along line VIa-VIa of FIG. 2 (a). FIG. 6B is a sectional view taken along line VIb-VIb of FIG. 2A. FIG. 6 (c) is a sectional view taken along line VIc-VIc of FIG. 2 (a). 6 (d) is a sectional view taken along line VId-VId of FIG. 2 (a). 図６（ｃ）のうち、第１補強部材近傍の抽出図である。FIG. 6 (c) is an extracted view of the vicinity of the first reinforcing member.

以下に添付図面を参照しながら、本開示の実施形態について詳細に説明する。実施形態に示す寸法、材料、その他具体的な数値等は、理解を容易とするための例示にすぎず、特に断る場合を除き、本開示を限定するものではない。なお、本明細書および図面において、実質的に同一の機能、構成を有する要素については、同一の符号を付することにより重複説明を省略する。また本開示に直接関係のない要素は図示を省略する。 The embodiments of the present disclosure will be described in detail with reference to the accompanying drawings. The dimensions, materials, and other specific numerical values shown in the embodiments are merely examples for facilitating understanding, and the present disclosure is not limited unless otherwise specified. In the present specification and the drawings, elements having substantially the same function and configuration are designated by the same reference numerals, so that duplicate description will be omitted. In addition, elements not directly related to the present disclosure are not shown.

図１は、本開示の一実施形態である海流発電装置１の斜視図である。図１に示すように、本実施形態の海流発電装置１は、一対のポッド２を備える。一対のポッド２は、連結ビーム３によって連結されている。ポッド２それぞれの内部には、発電機４が配されている。発電機４は、ポッド２それぞれの先端側に設けられたタービン５に連結される。タービン５は、ロータ６と、複数（例えば、２つ）のブレード１０を有する。ロータ６は、ポッド２に対し、回転自在に軸支される。ブレード１０は、ロータ６の外周面から径方向外側に突出する。 FIG. 1 is a perspective view of an ocean current power generation device 1 according to an embodiment of the present disclosure. As shown in FIG. 1, the ocean current power generation device 1 of the present embodiment includes a pair of pods 2. The pair of pods 2 are connected by a connecting beam 3. A generator 4 is arranged inside each of the pods 2. The generator 4 is connected to a turbine 5 provided on the tip side of each of the pods 2. The turbine 5 has a rotor 6 and a plurality (for example, two) blades 10. The rotor 6 is rotatably supported by the pod 2. The blade 10 projects radially outward from the outer peripheral surface of the rotor 6.

なお、発電機４は、連結ビーム３に配されてもよい。この場合、発電機４は、例えば、油圧回路を介してタービン５から回転動力を受ける。油圧回路を介する場合、発電機４は、２つのタービン５に対して１つのみ設けられてもよい。 The generator 4 may be arranged on the connected beam 3. In this case, the generator 4 receives rotational power from the turbine 5 via, for example, a hydraulic circuit. Only one generator 4 may be provided for each of the two turbines 5 via a hydraulic circuit.

ここでは図示を省略するが、海流発電装置１は、例えば、海中に設置され、海底に設置されたシンカーやアンカーに取り付けられた係留索が連結される。タービン５が海流によって回転することで、発電機４が発電する。 Although not shown here, the ocean current power generation device 1 is connected to, for example, a mooring line installed in the sea and attached to a sinker or an anchor installed on the seabed. The generator 4 generates electricity when the turbine 5 is rotated by the ocean current.

図２（ａ）は、ブレード１０をロータ６の回転軸方向、つまり、ブレード１０を挟んで発電機４と反対側から見た場合の正面図である。図２（ｂ）は、ブレード１０の上面図である。図２（ｃ）は、ブレード１０の側面図である。図２（ａ）に示すように、ブレード１０には、リーディングエッジＬＥ（前縁）およびトレーリングエッジＴＥが形成される。リーディングエッジＬＥは、ブレード１０のうち、ブレード１０をロータ６の回転軸方向から見たとき（つまり、ブレード１０を挟んで発電機４と反対側からロータ６の回転軸方向に垂直な平面に投影したとき）の、ブレード１０の回転方向の前方側の縁である。トレーリングエッジＴＥは、ブレード１０をロータ６の回転軸方向から見たときのブレード１０の回転方向の後方側の縁である。 FIG. 2A is a front view of the blade 10 when viewed from the rotation axis direction of the rotor 6, that is, from the side opposite to the generator 4 with the blade 10 sandwiched between them. FIG. 2B is a top view of the blade 10. FIG. 2C is a side view of the blade 10. As shown in FIG. 2A, the blade 10 is formed with a leading edge LE (front edge) and a trailing edge TE. The leading edge LE is projected onto the plane perpendicular to the rotation axis direction of the rotor 6 from the side opposite to the generator 4 across the blade 10 when the blade 10 is viewed from the rotation axis direction of the rotor 6 among the blades 10. This is the front edge of the blade 10 in the rotational direction. The trailing edge TE is an edge on the rear side in the rotation direction of the blade 10 when the blade 10 is viewed from the rotation axis direction of the rotor 6.

図２（ａ）〜図２（ｃ）に示すように、ブレード１０は、例えば、ＦＲＰ（Fiber-Reinforced Plastics）製の翼本体１１を備える。翼本体１１は、ロータ６側に位置する基端側（図２（ａ）、図２（ｂ）中、右側）から先端１２側（図２（ａ）、図２（ｂ）中、左側、ロータ６から離隔する側）に、トレーリングエッジＴＥとリーディングエッジＬＥとの距離（コード長）よりも長く延在している。すなわち、翼本体１１は、基端から先端１２に向かう方向が長手方向、トレーリングエッジＴＥからリーディングエッジＬＥに向かう方向が短手方向となっている。 As shown in FIGS. 2A to 2C, the blade 10 includes, for example, a blade body 11 made of FRP (Fiber-Reinforced Plastics). The blade body 11 is located on the rotor 6 side from the base end side (FIG. 2 (a), FIG. 2 (b), right side) to the tip 12 side (FIG. 2 (a), FIG. 2 (b), middle, left side, On the side separated from the rotor 6), it extends longer than the distance (cord length) between the trailing edge TE and the leading edge LE. That is, in the blade body 11, the direction from the base end to the tip 12 is the longitudinal direction, and the direction from the trailing edge TE to the leading edge LE is the lateral direction.

また、翼本体１１は、トレーリングエッジＴＥとリーディングエッジＬＥとの間に翼面１１ａを有する。翼面１１ａは、図２（ｂ）に示すように、翼本体１１に２面形成され、それぞれ、大凡扁平形状となっている。 Further, the blade body 11 has a blade surface 11a between the trailing edge TE and the leading edge LE. As shown in FIG. 2B, the blade surface 11a is formed on two surfaces on the blade body 11, and each has a substantially flat shape.

翼本体１１には、リーディングエッジＬＥとトレーリングエッジＴＥとを結ぶコードラインの延在方向（図２（ａ）中、上下方向、以下、コードライン方向と称す）の幅が最大となる幅広部１３が形成される。幅広部１３は、翼本体１１の基端側に形成されている。すなわち、幅広部１３は、翼本体１１のうち、先端１２より基端に近い。幅広部１３は、リーディングエッジＬＥ側よりもトレーリングエッジＴＥ側に膨らんだ形状となっている。翼本体１１のうち、コードライン方向の幅は、基端から幅広部１３に向かって徐々に拡大し、幅広部１３から先端１２に向かって徐々に縮小する。すなわち、翼本体１１は、基端から幅広部１３に向かって、後述する中心軸Ｏに垂直な断面における断面積が大きくなる。翼本体１１は、幅広部１３から先端１２に向かって、後述する中心軸Ｏに垂直な断面における断面積が小さくなる。 The wing body 11 has a wide portion having a maximum width in the extending direction of the cord line connecting the leading edge LE and the trailing edge TE (in FIG. 2A, the vertical direction, hereinafter referred to as the cord line direction). 13 is formed. The wide portion 13 is formed on the base end side of the blade body 11. That is, the wide portion 13 is closer to the base end of the wing body 11 than the tip end 12. The wide portion 13 has a shape that bulges toward the trailing edge TE side rather than the leading edge LE side. The width of the wing body 11 in the cord line direction gradually increases from the base end toward the wide portion 13, and gradually decreases from the wide portion 13 toward the tip 12. That is, the blade body 11 has a larger cross-sectional area in a cross section perpendicular to the central axis O, which will be described later, from the base end toward the wide portion 13. The wing body 11 has a smaller cross-sectional area in a cross section perpendicular to the central axis O, which will be described later, from the wide portion 13 toward the tip 12.

ブレード１０のうち、リーディングエッジＬＥ側には、第１補強部材３０（補強部材）が設けられる。第１補強部材３０は、例えば、ＦＲＰ製である。第１補強部材３０は、翼本体１１のうち、図２（ａ）中、上側の端部（縁）に沿って延在する。第１補強部材３０は、翼本体１１のうち、リーディングエッジＬＥ側の端部を覆う。ブレード１０のうち、トレーリングエッジＴＥ側には、第２補強部材３２（補強部材）が設けられる。第２補強部材３２は、例えば、ＦＲＰ製である。第２補強部材３２は、翼本体１１のうち、図２（ａ）中、下側の端部（縁）に沿って延在する。第２補強部材３２は、翼本体１１のうち、トレーリングエッジＴＥ側の端部を覆う。 A first reinforcing member 30 (reinforcing member) is provided on the leading edge LE side of the blade 10. The first reinforcing member 30 is made of, for example, FRP. The first reinforcing member 30 extends along the upper end (edge) of the wing body 11 in FIG. 2A. The first reinforcing member 30 covers the end of the wing body 11 on the leading edge LE side. A second reinforcing member 32 (reinforcing member) is provided on the trailing edge TE side of the blade 10. The second reinforcing member 32 is made of, for example, FRP. The second reinforcing member 32 extends along the lower end (edge) of the wing body 11 in FIG. 2A. The second reinforcing member 32 covers the end of the wing body 11 on the trailing edge TE side.

第１補強部材３０および第２補強部材３２は、翼本体１１のうち、幅広部１３よりも先端１２側に、先端１２より手前側まで延在する。第１補強部材３０は、第２補強部材３２よりも先端１２側まで延在する。幅広部１３のうち、第１補強部材３０および第２補強部材３２で覆われた部位に、ブレード１０が最大翼幅となる位置がある。 The first reinforcing member 30 and the second reinforcing member 32 extend to the tip 12 side of the wide portion 13 and to the front side from the tip 12 of the wing body 11. The first reinforcing member 30 extends to the tip 12 side of the second reinforcing member 32. In the wide portion 13, there is a position where the blade 10 has the maximum blade width at a portion covered by the first reinforcing member 30 and the second reinforcing member 32.

翼本体１１のうち、基端側の基部１４には、接続部材４０が設けられる。接続部材４０は、例えば、金属製である。接続部材４０は、円筒形状の本体４１を有する。本体４１には、図２（ｃ）に示すように、挿通孔４１ａが形成されている。挿通孔４１ａには、翼本体１１の基部１４が挿通される。すなわち、本体４１のうち、挿通孔４１ａが形成される外壁部４２は、基部１４の少なくとも一部を覆う。第１補強部材３０および第２補強部材３２は、基部１４とともに挿通孔４１ａに挿通されている。すなわち、第１補強部材３０、第２補強部材３２は、翼本体１１の基端側に、接続部材４０に径方向に対向する位置まで延在する。第１補強部材３０および第２補強部材３２は、翼本体１１と接続部材４０に挟持される。翼本体１１は、第１補強部材３０および第２補強部材３２に挟持される。 A connecting member 40 is provided at the base portion 14 on the base end side of the blade main body 11. The connecting member 40 is made of metal, for example. The connecting member 40 has a cylindrical body 41. As shown in FIG. 2C, an insertion hole 41a is formed in the main body 41. The base 14 of the wing body 11 is inserted into the insertion hole 41a. That is, in the main body 41, the outer wall portion 42 in which the insertion hole 41a is formed covers at least a part of the base portion 14. The first reinforcing member 30 and the second reinforcing member 32 are inserted into the insertion hole 41a together with the base portion 14. That is, the first reinforcing member 30 and the second reinforcing member 32 extend to the base end side of the blade body 11 to a position that faces the connecting member 40 in the radial direction. The first reinforcing member 30 and the second reinforcing member 32 are sandwiched between the blade body 11 and the connecting member 40. The wing body 11 is sandwiched between the first reinforcing member 30 and the second reinforcing member 32.

図３（ａ）は、ブレード１０の斜視図である。図３（ｂ）は、ブレード１０の分解斜視図である。図３（ｂ）に示すように、翼本体１１は、第１本体部材１５および第２本体部材１６を含んで構成される。第１本体部材１５は、コードライン方向に直交する直交方向（以下、単に直交方向という）の一方向側（図３（ａ）、図３（ｂ）中、矢印ａで示す）に位置する。第２本体部材１６は、直交方向の他方向側（図３（ａ）、図３（ｂ）中、矢印ｂで示す）に位置する。すなわち、翼本体１１には割断線があり、第１本体部材１５および第２本体部材１６は、割断線を重ね合わせて接合され、翼本体１１を成している。あるいは、翼本体１１の断面のうち、扁平な方向に２つの分割点があり、当該分割点により第１本体部材１５および第２本体部材１６が分離されているともいえる。 FIG. 3A is a perspective view of the blade 10. FIG. 3B is an exploded perspective view of the blade 10. As shown in FIG. 3B, the wing main body 11 includes a first main body member 15 and a second main body member 16. The first main body member 15 is located on one direction side (indicated by an arrow a in FIGS. 3A and 3B) in an orthogonal direction (hereinafter, simply referred to as an orthogonal direction) orthogonal to the code line direction. The second main body member 16 is located on the other direction side in the orthogonal direction (indicated by arrow b in FIGS. 3A and 3B). That is, the wing main body 11 has a breaking wire, and the first main body member 15 and the second main body member 16 are joined by overlapping the breaking wires to form the wing main body 11. Alternatively, it can be said that there are two dividing points in the flat direction in the cross section of the wing main body 11, and the first main body member 15 and the second main body member 16 are separated by the dividing points.

第１本体部材１５は、基端１５ａにおけるコードライン方向の中心部１５ｂが第２本体部材１６から離隔する方向に窪んでいる。第１本体部材１５のうち、第２本体部材１６との対向面１５ｃ（接合部）は、中心部１５ｂを除いて、第１本体部材１５の周縁に形成される。第１本体部材１５のうち、対向面１５ｃの内側（コードライン方向の中心側）は、第２本体部材１６から離隔する方向に窪んでいる。第２本体部材１６は、対向面１５ｃを挟んで、第１本体部材１５と大凡面対称な形状となっている。 The first main body member 15 is recessed in a direction in which the central portion 15b of the base end 15a in the cord line direction is separated from the second main body member 16. Of the first main body member 15, the facing surface 15c (joint portion) with the second main body member 16 is formed on the peripheral edge of the first main body member 15 except for the central portion 15b. Of the first main body member 15, the inside of the facing surface 15c (center side in the cord line direction) is recessed in a direction away from the second main body member 16. The second main body member 16 has a shape substantially symmetrical with that of the first main body member 15 with the facing surface 15c interposed therebetween.

第１本体部材１５の対向面１５ｃと第２本体部材１６の対向面１６ｃ（接合部）は、互いに接合される接合部となっている。翼本体１１は、第１本体部材１５と第２本体部材１６が接合されて形成される。第１補強部材３０、第２補強部材３２は、対向面１５ｃ、１６ｃの一部を、翼本体１１の外側から覆う。リーディングエッジＬＥおよびトレーリングエッジＴＥの一部は、第１補強部材３０、第２補強部材３２によって形成される。すなわち、リーディングエッジＬＥおよびトレーリングエッジＴＥには、翼本体１１から第１補強部材３０、第２補強部材３２に接続する接続部がある。 The facing surface 15c of the first main body member 15 and the facing surface 16c (joint portion) of the second main body member 16 are joint portions to be joined to each other. The wing main body 11 is formed by joining the first main body member 15 and the second main body member 16. The first reinforcing member 30 and the second reinforcing member 32 cover a part of the facing surfaces 15c and 16c from the outside of the wing body 11. A part of the leading edge LE and the trailing edge TE is formed by the first reinforcing member 30 and the second reinforcing member 32. That is, the leading edge LE and the trailing edge TE have a connecting portion that connects the blade body 11 to the first reinforcing member 30 and the second reinforcing member 32.

本実施形態においては、後述する中心軸Ｏと接合部とが、同一平面内に含まれている。すなわち、翼本体１１は、後述する中心軸Ｏを含む断面において、リーディングエッジＬＥ側の基端からトレーリングエッジＴＥ側の基端まで延在する断面を備える。当該断面において、中心軸Ｏにより分割されるリーディングエッジＬＥ側の接合部と、トレーリングエッジＴＥ側の接合部は、それぞれ、後述する中心軸Ｏからの径方向の離間が最大となるリーディングエッジＬＥ側の第１のピークＰ１（ピーク、図２（ａ）参照）と、トレーリングエッジＴＥ側の第２のピークＰ２（ピーク、図２（ａ）参照）とを備える。本実施形態において、幅広部１３の中心軸Ｏに対する軸方向位置は、第１のピークＰ１と第２のピークＰ２の間に位置する。 In the present embodiment, the central axis O and the joint portion, which will be described later, are included in the same plane. That is, the blade body 11 has a cross section including the central axis O, which will be described later, extending from the base end on the leading edge LE side to the base end on the trailing edge TE side. In the cross section, the joint portion on the leading edge LE side and the joint portion on the trailing edge TE side, which are divided by the central axis O, are respectively the leading edge LE having the maximum radial separation from the central axis O, which will be described later. It includes a first peak P1 on the side (peak, see FIG. 2A) and a second peak P2 on the trailing edge TE side (peak, see FIG. 2A). In the present embodiment, the axial position of the wide portion 13 with respect to the central axis O is located between the first peak P1 and the second peak P2.

なお、本実施形態においては、後述する中心軸Ｏと接合部とが、同一平面内に含まれているが、これに限られない。例えば、接合部が中心軸Ｏを含む断面内に収まらない場合(接合部が中心軸Ｏを含む断面を通過して延伸する場合)であっても、中心軸Ｏ周りの径方向の離間が最大となるリーディングエッジＬＥ側の第１のピークＰ１と、トレーリングエッジＴＥ側の第２のピークＰ２を備える。 In this embodiment, the central axis O and the joint portion, which will be described later, are included in the same plane, but the present invention is not limited to this. For example, even if the joint does not fit within the cross section including the central axis O (when the joint extends through the cross section including the central axis O), the radial separation around the central axis O is maximum. It is provided with a first peak P1 on the leading edge LE side and a second peak P2 on the trailing edge TE side.

本実施形態において、第１補強部材３０は、第１のピークＰ１を含み、第１のピークＰ１から接合部の延伸方向の両側に延在して、接合部を覆っている。あるいは、第１補強部材３０は翼本体１１の先端１２側から延伸し、第１のピークＰ１を越え、基端側まで延伸しているともいえる。つまり、第１のピークＰ１は第１補強部材３０で覆われている。 In the present embodiment, the first reinforcing member 30 includes the first peak P1 and extends from the first peak P1 on both sides in the extending direction of the joint portion to cover the joint portion. Alternatively, it can be said that the first reinforcing member 30 extends from the tip 12 side of the blade body 11, exceeds the first peak P1, and extends to the base end side. That is, the first peak P1 is covered with the first reinforcing member 30.

同様に、第２補強部材３２は第２のピークＰ２を含み、第２のピークＰ２から接合部の延伸方向の両側に延在して、接合部を覆っている。あるいは、第２補強部材３２は翼本体１１の先端１２側から延伸し、第２のピークＰ２を越え、基端側まで延伸しているともいえる。つまり、第２のピークＰ２は第２補強部材３０で覆われている。 Similarly, the second reinforcing member 32 includes the second peak P2 and extends from the second peak P2 on both sides in the extending direction of the joint portion to cover the joint portion. Alternatively, it can be said that the second reinforcing member 32 extends from the tip 12 side of the blade body 11, exceeds the second peak P2, and extends to the base end side. That is, the second peak P2 is covered with the second reinforcing member 30.

第１補強部材３０、第２補強部材３２は、基部１４の接合部（対向面１５ｃ、１６ｃ）の外側を覆う。すなわち、第１補強部材３０、第２補強部材３２は、挿通孔４１ａ内で上記の割断線を覆う。第１補強部材３０、第２補強部材３２は、基部１４から翼本体１１の先端１２側に延伸している。ここでは、第１補強部材３０、第２補強部材３２は、基部１４の接合部の外側を覆う場合について説明した。ただし、第１補強部材３０、第２補強部材３２は、接合部を、少なくとも幅広部１３よりも翼本体１１の基端側（基部１４側）まで覆えばよい。この場合、第１補強部材３０、第２補強部材３２が、接合部を、幅広部１３までしか覆わない場合に比べ、接合部の強度を向上することができる。 The first reinforcing member 30 and the second reinforcing member 32 cover the outside of the joint portions (opposing surfaces 15c and 16c) of the base portion 14. That is, the first reinforcing member 30 and the second reinforcing member 32 cover the above-mentioned breaking wire in the insertion hole 41a. The first reinforcing member 30 and the second reinforcing member 32 extend from the base portion 14 to the tip 12 side of the blade body 11. Here, the case where the first reinforcing member 30 and the second reinforcing member 32 cover the outside of the joint portion of the base portion 14 has been described. However, the first reinforcing member 30 and the second reinforcing member 32 may cover the joint portion at least to the base end side (base portion 14 side) of the blade body 11 rather than the wide portion 13. In this case, the strength of the joint portion can be improved as compared with the case where the first reinforcing member 30 and the second reinforcing member 32 cover the joint portion only up to the wide portion 13.

上記のように、第１補強部材３０および第２補強部材３２は、翼本体１１のうち、幅広部１３よりも先端１２側に、先端１２より手前側まで延在する。すなわち、第１補強部材３０および第２補強部材３２は、接合部を、幅広部１３よりも先端１２側まで覆う。第１補強部材３０および第２補強部材３２は、接合部を、先端１２より手前側まで覆う。接合部は、第１補強部材３０および第２補強部材３２より翼本体１１の先端１２側に延在する。 As described above, the first reinforcing member 30 and the second reinforcing member 32 extend to the tip 12 side of the wing body 11 from the wide portion 13 and to the front side from the tip 12. That is, the first reinforcing member 30 and the second reinforcing member 32 cover the joint portion to the tip 12 side of the wide portion 13. The first reinforcing member 30 and the second reinforcing member 32 cover the joint portion from the tip 12 to the front side. The joint portion extends from the first reinforcing member 30 and the second reinforcing member 32 to the tip 12 side of the blade body 11.

第１補強部材３０は、第２補強部材３２よりも先端１２側まで延在する。第１補強部材３０は、翼本体１１の基端から先端１２までの長手方向の長さに対して、例えば、９０％以上の長さとなっている。 The first reinforcing member 30 extends to the tip 12 side of the second reinforcing member 32. The first reinforcing member 30 has a length of, for example, 90% or more with respect to the length in the longitudinal direction from the base end to the tip end 12 of the blade body 11.

また、リーディングエッジＬＥおよびトレーリングエッジＴＥは、翼本体１１のうち、対向面１５ｃ、１６ｃの外面側のうち、第１補強部材３０、第２補強部材３２で覆われていない部位によっても形成されている。 Further, the leading edge LE and the trailing edge TE are also formed by the portions of the blade body 11 on the outer surface sides of the facing surfaces 15c and 16c that are not covered by the first reinforcing member 30 and the second reinforcing member 32. ing.

図４は、図２（ａ）のＩＶ−ＩＶ線断面図である。すなわち、図４は、後述する中心軸Ｏを含む面によるブレード１０の断面図である。図４に示すように、翼本体１１の基部１４は、大凡筒形状となっている。上記のように、基部１４は、接続部材４０の挿通孔４１ａに、本体４１の一端４１ｂ側から挿通されている。挿通孔４１ａの内周面４３には、径方向内側に突出する底面部４４が形成されている。すなわち、翼本体１１の一部が本体４１に囲まれており、翼本体１１の本体４１に囲まれた部分より一端側は、本体４１から露出している。底面部４４は、内周面４３のうち、本体４１の他端４１ｃ側に形成されている。底面部４４は、周方向に延在している。挿通孔４１ａのうち、翼本体１１（基部１４）の基端１５ａ（第１本体部材１５の基端１５ａ）は、底面部４４に当接する。 FIG. 4 is a sectional view taken along line IV-IV of FIG. 2 (a). That is, FIG. 4 is a cross-sectional view of the blade 10 with a surface including the central axis O described later. As shown in FIG. 4, the base portion 14 of the wing body 11 has a roughly tubular shape. As described above, the base portion 14 is inserted into the insertion hole 41a of the connecting member 40 from one end 41b side of the main body 41. A bottom surface portion 44 projecting inward in the radial direction is formed on the inner peripheral surface 43 of the insertion hole 41a. That is, a part of the wing main body 11 is surrounded by the main body 41, and one end side of the wing main body 11 surrounded by the main body 41 is exposed from the main body 41. The bottom surface portion 44 is formed on the other end 41c side of the main body 41 of the inner peripheral surface 43. The bottom surface portion 44 extends in the circumferential direction. Of the insertion holes 41a, the base end 15a of the blade main body 11 (base portion 14) (base end 15a of the first main body member 15) comes into contact with the bottom surface portion 44.

本体４１の外周面４５のうち、底面部４４の径方向外側には、フランジ部４６が形成されている。フランジ部４６は、外周面４５から径方向外側に突出している。また、フランジ部４６は、周方向に延在している。フランジ部４６は、本体４１の径方向の幅（肉厚）が、底面部４４よりも大きい。フランジ部４６は、外周面４５のうち、本体４１の他端４１ｃまで延在している。フランジ部４６は、他端４１ｃ側の端面４６ａが不図示の旋回座に当接した状態で、不図示のボルトなどの締結部材が本体４１の中心軸Ｏ方向に挿通されて旋回座に締結される。旋回座は、不図示のモータなどによって中心軸Ｏ周りに回転可能となっている。そのため、ブレード１０の傾きは、可変となっている。 A flange portion 46 is formed on the radial outer side of the bottom surface portion 44 of the outer peripheral surface 45 of the main body 41. The flange portion 46 projects radially outward from the outer peripheral surface 45. Further, the flange portion 46 extends in the circumferential direction. The width (thickness) of the flange portion 46 in the radial direction of the main body 41 is larger than that of the bottom surface portion 44. The flange portion 46 extends to the other end 41c of the main body 41 of the outer peripheral surface 45. The flange portion 46 is fastened to the swivel seat by inserting a fastening member such as a bolt (not shown) in the direction of the central axis O of the main body 41 in a state where the end surface 46a on the other end 41c side is in contact with the swivel seat (not shown). To. The swivel seat can be rotated around the central axis O by a motor (not shown) or the like. Therefore, the inclination of the blade 10 is variable.

本体４１の外周面４５には、一端４１ｂ側に向かって外径が縮小するテーパ部４７が形成されている。本体４１のうち、フランジ部４６とテーパ部４７との中心軸Ｏ方向の間には、内周面４３から外周面４５まで貫通する貫通孔４８が形成されている。貫通孔４８は、本体４１の周方向に離隔して複数形成されている。 On the outer peripheral surface 45 of the main body 41, a tapered portion 47 whose outer diameter decreases toward one end 41b side is formed. In the main body 41, a through hole 48 penetrating from the inner peripheral surface 43 to the outer peripheral surface 45 is formed between the flange portion 46 and the tapered portion 47 in the central axis O direction. A plurality of through holes 48 are formed so as to be separated from each other in the circumferential direction of the main body 41.

貫通孔４８には、小径部４８ａ、大径部４８ｂ、および、座面４８ｃが形成されている。貫通孔４８のうち、内周面４３側が小径部４８ａ、外周面４５側が小径部４８ａよりも内径が大きい大径部４８ｂとなっている。座面４８ｃは、小径部４８ａと大径部４８ｂを繋ぐ面であり、貫通孔４８の径方向に延在する。 The through hole 48 is formed with a small diameter portion 48a, a large diameter portion 48b, and a seat surface 48c. Of the through holes 48, the inner peripheral surface 43 side is a small diameter portion 48a, and the outer peripheral surface 45 side is a large diameter portion 48b having an inner diameter larger than that of the small diameter portion 48a. The seat surface 48c is a surface connecting the small diameter portion 48a and the large diameter portion 48b, and extends in the radial direction of the through hole 48.

翼本体１１の基部１４には、貫通孔４８と対向する位置に対向孔１７が形成されている。対向孔１７は、基部１４のうち、内周面１８から外周面１９まで貫通する。対向孔１７は、貫通孔４８と同様、基部１４の周方向に離隔して複数形成されている。対向孔１７の内径は、小径部４８ａの内径と大凡等しい。 A facing hole 17 is formed in the base portion 14 of the blade body 11 at a position facing the through hole 48. The facing hole 17 penetrates from the inner peripheral surface 18 to the outer peripheral surface 19 of the base portion 14. Similar to the through hole 48, a plurality of facing holes 17 are formed so as to be separated from each other in the circumferential direction of the base portion 14. The inner diameter of the facing hole 17 is approximately equal to the inner diameter of the small diameter portion 48a.

締結部材５０は、例えば、ボルトで構成され、貫通孔４８および対向孔１７に、径方向外側から挿通される。締結部材５０の頭部５１は、貫通孔４８の小径部４８ａよりも大きく、小径部４８ａに進入しない。頭部５１は、貫通孔４８の大径部４８ｂの内部まで進入し、座面４８ｃに当接している。締結部材５０のうち、対向孔１７から基部１４の内周面１８側に突出した突出部５２に、不図示のナットが締結される。こうして、基部１４と接続部材４０が締結される。 The fastening member 50 is composed of, for example, bolts, and is inserted into the through hole 48 and the facing hole 17 from the outside in the radial direction. The head portion 51 of the fastening member 50 is larger than the small diameter portion 48a of the through hole 48 and does not enter the small diameter portion 48a. The head 51 has entered the inside of the large diameter portion 48b of the through hole 48 and is in contact with the seat surface 48c. A nut (not shown) is fastened to a protruding portion 52 of the fastening member 50 that protrudes from the facing hole 17 toward the inner peripheral surface 18 side of the base portion 14. In this way, the base 14 and the connecting member 40 are fastened.

また、本体４１の外周面４５には、リブ４９が形成されている。リブ４９は、外周面４５のうち、テーパ部４７よりも他端４１ｃ側に位置する。リブ４９は、フランジ部４６と一体となっている。リブ４９は、締結部材５０と周方向の位置を異にして、周方向に複数形成されている。リブ４９には、一端４１ｂ側に向かって本体４１の径方向内側に傾斜するテーパ部４９ａが形成されている。 Further, ribs 49 are formed on the outer peripheral surface 45 of the main body 41. The rib 49 is located on the other end 41c side of the outer peripheral surface 45 with respect to the tapered portion 47. The rib 49 is integrated with the flange portion 46. A plurality of ribs 49 are formed in the circumferential direction at different positions in the circumferential direction from the fastening member 50. The rib 49 is formed with a tapered portion 49a that is inclined inward in the radial direction of the main body 41 toward one end 41b side.

図５は、図２（ａ）のＶ−Ｖ線断面図である。つまり、図５は、中心軸Ｏと直交する面による断面である。当該断面は、外周面４５と翼本体１１を含んでいる。図５では、コードライン方向が水平に位置し、直交方向が垂直に位置する向きに示す。図５に示すように、基部１４のうち、コードライン方向の中央部分には、本体４１に沿って延在する円弧部２０が形成されている。円弧部２０と本体４１の内周面４３との間に接着剤が介在し、円弧部２０と本体４１の内周面４３とが接着剤によって接合される。 FIG. 5 is a sectional view taken along line VV of FIG. 2A. That is, FIG. 5 is a cross section of a plane orthogonal to the central axis O. The cross section includes the outer peripheral surface 45 and the wing body 11. In FIG. 5, the code line direction is shown horizontally and the orthogonal direction is shown vertically. As shown in FIG. 5, an arc portion 20 extending along the main body 41 is formed in the central portion of the base portion 14 in the cord line direction. An adhesive is interposed between the arc portion 20 and the inner peripheral surface 43 of the main body 41, and the arc portion 20 and the inner peripheral surface 43 of the main body 41 are joined by the adhesive.

基部１４のうち、コードライン方向の両端部分には、本体４１の内周面４３から径方向内側に離隔する扁平部２１が形成されている。扁平部２１は、基部１４のうちの他の部位に比べて曲率半径が大きい。扁平部２１は、翼本体１１の翼面１１ａ（図２（ａ）、図２（ｂ）参照）と向きが異なる。例えば、翼面１１ａは、リーディングエッジＬＥとトレーリングエッジＴＥとの間に形成され、大凡コードライン方向（図５中、大凡左右方向）に延在する。一方、扁平部２１は、大凡直交方向（図５中、大凡上下方向）に延在する。このように、基部１４のうち、扁平部２１は、翼本体１１の翼面１１ａの扁平方向と異なる向きに扁平となっている。扁平部２１は、翼本体１１の翼面１１ａに対して、大凡直交する方向に延在する。 Flat portions 21 that are radially inwardly separated from the inner peripheral surface 43 of the main body 41 are formed at both ends of the base portion 14 in the cord line direction. The flat portion 21 has a larger radius of curvature than the other portion of the base 14. The flat portion 21 has a different orientation from the blade surface 11a of the blade body 11 (see FIGS. 2A and 2B). For example, the blade surface 11a is formed between the leading edge LE and the trailing edge TE, and extends in the approximate cord line direction (approximately in the left-right direction in FIG. 5). On the other hand, the flat portion 21 extends in a substantially orthogonal direction (generally in the vertical direction in FIG. 5). As described above, of the base portion 14, the flat portion 21 is flattened in a direction different from the flattening direction of the blade surface 11a of the blade body 11. The flat portion 21 extends in a direction approximately orthogonal to the blade surface 11a of the blade body 11.

扁平部２１と本体４１との隙間には、リーディングエッジＬＥ側（図５中、左側）に第１補強部材３０が配され、トレーリングエッジＴＥ側（図５中、右側）に第２補強部材３２が配される。扁平部２１は、第１補強部材３０、第２補強部材３２に接着剤などで接合される。第１補強部材３０、第２補強部材３２は、本体４１に接着剤などが介在し接合される。 In the gap between the flat portion 21 and the main body 41, the first reinforcing member 30 is arranged on the leading edge LE side (left side in FIG. 5), and the second reinforcing member 30 is arranged on the trailing edge TE side (right side in FIG. 5). 32 is arranged. The flat portion 21 is joined to the first reinforcing member 30 and the second reinforcing member 32 with an adhesive or the like. The first reinforcing member 30 and the second reinforcing member 32 are joined to the main body 41 with an adhesive or the like interposed therebetween.

第１本体部材１５と第２本体部材１６の接合部（対向面１５ｃ、１６ｃ）は、扁平部２１に位置している。第１補強部材３０および第２補強部材３２は、挿通孔４１ａ（外壁部４２）の内部において、第１本体部材１５と第２本体部材１６の接合部（対向面１５ｃ、１６ｃ）の外側に設けられる。すなわち、第１補強部材３０および第２補強部材３２は、接続部材４０と翼本体１１の基部１４との隙間に介在する。言い換えれば、第１補強部材３０および第２補強部材３２は、接続部材４０と基部１４に挟まれる。 The joints (opposing surfaces 15c and 16c) of the first main body member 15 and the second main body member 16 are located on the flat portion 21. The first reinforcing member 30 and the second reinforcing member 32 are provided inside the insertion hole 41a (outer wall portion 42) and outside the joint portions (opposing surfaces 15c and 16c) of the first main body member 15 and the second main body member 16. Be done. That is, the first reinforcing member 30 and the second reinforcing member 32 are interposed in the gap between the connecting member 40 and the base portion 14 of the blade body 11. In other words, the first reinforcing member 30 and the second reinforcing member 32 are sandwiched between the connecting member 40 and the base portion 14.

接続部材４０の本体４１は、上記の通り、円筒形状である。扁平部２１は、第１補強部材３０、第２補強部材３２の肉厚分、円弧部２０よりも径方向内側に位置している。扁平部２１は、コードライン方向の外周面１９間の距離Ｌａが、直交方向の外周面１９間の距離Ｌｂよりも短い。すなわち、距離Ｌｂは、距離Ｌａよりも長く、基部１４は、直交方向に膨らんだ扁平形状となっている。第１補強部材３０、第２補強部材３２の内面（翼本体１１側の面）は、外面（本体４１側の面）に向って窪んだ形状である。第１補強部材３０の内面は、曲率中心が第１補強部材３０より基部１４側に位置する円弧形状となっている。第２補強部材３２の内面は、曲率中心が第２補強部材３２より基部１４側に位置する円弧形状となっている。 As described above, the main body 41 of the connecting member 40 has a cylindrical shape. The flat portion 21 is located radially inside the arc portion 20 by the wall thickness of the first reinforcing member 30 and the second reinforcing member 32. In the flat portion 21, the distance La between the outer peripheral surfaces 19 in the cord line direction is shorter than the distance Lb between the outer peripheral surfaces 19 in the orthogonal direction. That is, the distance Lb is longer than the distance La, and the base portion 14 has a flat shape bulging in the orthogonal direction. The inner surface (the surface on the wing body 11 side) of the first reinforcing member 30 and the second reinforcing member 32 has a shape recessed toward the outer surface (the surface on the main body 41 side). The inner surface of the first reinforcing member 30 has an arc shape whose center of curvature is located on the base 14 side of the first reinforcing member 30. The inner surface of the second reinforcing member 32 has an arc shape whose center of curvature is located on the base 14 side of the second reinforcing member 32.

あるいは、本開示の実施形態の第１補強部材３０、第２補強部材３２は、中心軸Ｏを中心とした内面と外面の径方向間隔が、周方向両端の間の位置で一つのピークを持っている。なお、本開示の実施形態では、補強部材（第１補強部材３０、第２補強部材３２）の内面の中心軸Ｏに直交する面での断面形状が円弧形状である場合について説明した。ただし、補強部材の内面の断面形状は、これに限られない。断面形状において、補強部材の内面の曲率の平均(曲線長さあたりの平均)と比べ、補強部材の外面の曲率の平均が大きくてもよい。 Alternatively, the first reinforcing member 30 and the second reinforcing member 32 of the embodiment of the present disclosure have one peak at a position where the radial distance between the inner surface and the outer surface about the central axis O is between both ends in the circumferential direction. ing. In the embodiment of the present disclosure, the case where the cross-sectional shape of the inner surface of the reinforcing member (first reinforcing member 30, second reinforcing member 32) orthogonal to the central axis O is an arc shape has been described. However, the cross-sectional shape of the inner surface of the reinforcing member is not limited to this. In the cross-sectional shape, the average curvature of the outer surface of the reinforcing member may be larger than the average curvature of the inner surface of the reinforcing member (average per curve length).

また、第１補強部材３０の内面に対する曲率中心が描く曲線の重心位置(曲線長さを重量に見立てた場合の重心)と、第１補強部材３０の内面を成す曲線の重心位置の間の長さを第１所定幅とする。第１補強部材３０の内面に対する曲率中心が描く曲線の重心位置と、第２補強部材３２の内面を成す曲線の重心位置の間の長さを第２所定幅とする。このとき、第１所定幅より第２所定幅の方が短くてもよい。さらにいえば、断面において翼本体１１の補強部材に対向しない部分のおける翼本体１１の外面の曲率の平均と比べ、補強部材の内面の曲率の平均が小さくてもよい。 Further, the length between the position of the center of gravity of the curve drawn by the center of curvature with respect to the inner surface of the first reinforcing member 30 (the center of gravity when the length of the curve is regarded as weight) and the position of the center of gravity of the curve forming the inner surface of the first reinforcing member 30. Let this be the first predetermined width. The length between the position of the center of gravity of the curve drawn by the center of curvature with respect to the inner surface of the first reinforcing member 30 and the position of the center of gravity of the curve forming the inner surface of the second reinforcing member 32 is defined as the second predetermined width. At this time, the second predetermined width may be shorter than the first predetermined width. Furthermore, the average curvature of the inner surface of the reinforcing member may be smaller than the average curvature of the outer surface of the blade main body 11 in the portion of the cross section that does not face the reinforcing member.

海流によってブレード１０が回転するとき、翼本体１１の基部１４には、海流による荷重が作用する。この荷重は、基部１４に対して直交方向に作用する。ここでは、直交方向の基部１４の幅（距離Ｌｂ）が、コードライン方向の基部１４の幅（距離Ｌａ）よりも大きいため、直交方向に作用する荷重に対する基部１４の強度が向上する。 When the blade 10 is rotated by the ocean current, a load due to the ocean current acts on the base 14 of the blade body 11. This load acts orthogonally to the base 14. Here, since the width (distance Lb) of the base portion 14 in the orthogonal direction is larger than the width (distance La) of the base portion 14 in the cord line direction, the strength of the base portion 14 with respect to the load acting in the orthogonal direction is improved.

図６（ａ）は、図２（ａ）のＶＩａ−ＶＩａ断面図である。図６（ｂ）は、図２（ａ）のＶＩｂ−ＶＩｂ断面図である。図６（ｃ）は、図２（ａ）のＶＩｃ−ＶＩｃ断面図である。図６（ｄ）は、図２（ａ）のＶＩｄ−ＶＩｄ断面図である。つまり、図６（ａ）、図６（ｂ）、図６（ｃ）、図６（ｄ）は、中心軸Ｏと直交する断面における翼本体１１の断面図であり、図６（ａ）、図６（ｂ）、図６（ｃ）、図６（ｄ）の順番で基端側から離れている。図６（ａ）、図６（ｂ）、図６（ｃ）に示すように、中心軸Ｏの軸方向において基端側に位置する断面(図６（ｃ）、または、図６（ｄ）)においては、第１補強部材３０と、第２補強部材３２のいずれもが含まれている。他方、翼本体１１の先端１２側に位置する断面(図６（ｂ）)においては、第２補強部材３２は含まれない。つまり、第１補強部材３０は、第２補強部材３２よりも翼本体１１の先端１２側まで延在している。上記のように、第１補強部材３０および第２補強部材３２は、リーディングエッジＬＥおよびトレーリングエッジＴＥを形成している。つまり、ブレード１０のリーディングエッジＬＥは、翼本体１１の先端１２側から延在し、第１補強部材３０を介して基端側まで延在している。あるいは、リーディングエッジＬＥは、翼本体１１を構成する部材と第１補強部材３０との接続部を越えて延在しているともいえる。 6 (a) is a sectional view taken along line VIa-VIa of FIG. 2 (a). FIG. 6B is a sectional view taken along line VIb-VIb of FIG. 2A. FIG. 6 (c) is a sectional view taken along line VIc-VIc of FIG. 2 (a). 6 (d) is a sectional view taken along line VId-VId of FIG. 2 (a). That is, FIGS. 6 (a), 6 (b), 6 (c), and 6 (d) are cross-sectional views of the blade body 11 in a cross section orthogonal to the central axis O, and FIGS. It is separated from the base end side in the order of FIG. 6 (b), FIG. 6 (c), and FIG. 6 (d). As shown in FIGS. 6 (a), 6 (b), and 6 (c), a cross section located on the proximal end side in the axial direction of the central axis O (FIG. 6 (c) or FIG. 6 (d)). ), Both the first reinforcing member 30 and the second reinforcing member 32 are included. On the other hand, the second reinforcing member 32 is not included in the cross section (FIG. 6B) located on the tip 12 side of the blade body 11. That is, the first reinforcing member 30 extends beyond the second reinforcing member 32 to the tip 12 side of the blade body 11. As described above, the first reinforcing member 30 and the second reinforcing member 32 form the leading edge LE and the trailing edge TE. That is, the leading edge LE of the blade 10 extends from the tip 12 side of the blade body 11 and extends to the base end side via the first reinforcing member 30. Alternatively, it can be said that the leading edge LE extends beyond the connecting portion between the member constituting the blade body 11 and the first reinforcing member 30.

リーディングエッジＬＥの形状は、海流の流れに対する影響が大きい。リーディングエッジＬＥを第１補強部材３０で形成することで、仮に、対向面１５ｃ、１６ｃの位置ずれがあったとしても、リーディングエッジＬＥで対向面１５ｃ、１６ｃの外面が覆われていることから、性能低下が抑制される。 The shape of the leading edge LE has a large effect on the flow of ocean currents. By forming the leading edge LE with the first reinforcing member 30, even if the facing surfaces 15c and 16c are misaligned, the leading edge LE covers the outer surfaces of the facing surfaces 15c and 16c. Performance degradation is suppressed.

図６（ｂ）に示すように、先端１２側におけるトレーリングエッジＴＥ側は、第１本体部材１５、第２本体部材１６の対向面１５ｃ、１６ｃの外面が第２補強部材３２で覆われていない。すなわち、本実施形態では、第２補強部材３２は、第１補強部材３０よりも短く形成されている。つまり、第１補強部材３０は、第２補強部材３２より先端側に延在している。また、本実施形態の第１本体部材１５および第２本体部材１６は、繊維強化樹脂材料で構成される。 As shown in FIG. 6B, on the trailing edge TE side on the tip 12 side, the outer surfaces of the facing surfaces 15c and 16c of the first main body member 15 and the second main body member 16 are covered with the second reinforcing member 32. Absent. That is, in the present embodiment, the second reinforcing member 32 is formed shorter than the first reinforcing member 30. That is, the first reinforcing member 30 extends to the tip end side of the second reinforcing member 32. Further, the first main body member 15 and the second main body member 16 of the present embodiment are made of a fiber reinforced resin material.

本実施形態の第１本体部材１５は、シート状の繊維の層が積層されて構成される。当該シート状の繊維の層は、対向面１５ｃに向かい延伸し、対向面１５ｃにおいて端部となっている(対向面１５ｃの表面に樹脂の層が形成されているなら、シート状の繊維の層は、当該樹脂の層の背面で端部となっている)。つまり、対向面１５ｃにおいて、繊維の終端が露出している(対向面１５ｃ表面に樹脂の層が形成されているなら、当該樹脂の層の背面で繊維の終端が露出している)。あるいは、対向面１５ｃは、シート状の繊維の層が積層された断面となっている。 The first main body member 15 of the present embodiment is configured by laminating sheet-like fiber layers. The sheet-shaped fiber layer extends toward the facing surface 15c and becomes an end portion on the facing surface 15c (if a resin layer is formed on the surface of the facing surface 15c, the sheet-shaped fiber layer is formed. Is the end on the back of the resin layer). That is, the end of the fiber is exposed on the facing surface 15c (if a resin layer is formed on the surface of the facing surface 15c, the end of the fiber is exposed on the back surface of the resin layer). Alternatively, the facing surface 15c has a cross section in which sheet-like fiber layers are laminated.

同様に、本実施形態の第２本体部材１６は、シート状の繊維の層が積層されて構成される。当該シート状の繊維の層は対向面１６ｃに向かい延伸し、対向面１６ｃにおいて端部となっている(対向面１６ｃの表面に樹脂の層が形成されているなら、シート状の繊維の層は、当該樹脂の層の背面で端部となっている)。つまり、対向面１６ｃにおいて、繊維の終端が露出している(対向面１６ｃ表面に樹脂の層が形成されているなら、当該樹脂の層の背面で繊維の終端が露出している)。あるいは、対向面１６ｃは、シート状の繊維の層が積層された断面となっている。 Similarly, the second main body member 16 of the present embodiment is configured by laminating sheet-like fiber layers. The sheet-shaped fiber layer extends toward the facing surface 16c and becomes an end portion at the facing surface 16c (if a resin layer is formed on the surface of the facing surface 16c, the sheet-shaped fiber layer is formed. , At the back of the resin layer). That is, the end of the fiber is exposed on the facing surface 16c (if a resin layer is formed on the surface of the facing surface 16c, the end of the fiber is exposed on the back surface of the resin layer). Alternatively, the facing surface 16c has a cross section in which sheet-like fiber layers are laminated.

つまり、接合部はシート状の繊維の層が積層された第１本体部材１５および第２本体部材１６の端部同士が接合されている。あるいは、接合部は、翼本体１１の内面側から外面側に向かい積層された断面を持つともいえる。 That is, in the joint portion, the ends of the first main body member 15 and the second main body member 16 on which the sheet-shaped fiber layers are laminated are joined to each other. Alternatively, it can be said that the joint portion has a cross section laminated from the inner surface side to the outer surface side of the blade body 11.

当該構成であるため、本実施形態のトレーリングエッジＴＥは、海流の下流側に向かって鋭角に尖った形状である。 Because of this configuration, the trailing edge TE of the present embodiment has an acute-angled shape toward the downstream side of the ocean current.

第１本体部材１５、第２本体部材１６の対向面１５ｃ、１６ｃのうち、外面が第２補強部材３２で覆われていない部位は、第１補強部材３０、第２補強部材３２で覆われている部位よりも面積が大きい(対向面１５ｃ、１６ｃの幅が広い)。すなわち、第１本体部材１５、第２本体部材１６の対向面１５ｃ、１６ｃのうち、外面が第２補強部材３２で覆われていない部位は、翼本体１１の基端側の部位よりも面積が大きい(対向面１５ｃ、１６ｃの幅が広い)。対向面１５ｃ、１６ｃのうち、トレーリングエッジＴＥ側は、リーディングエッジＬＥ側よりも面積が大きい(対向面１５ｃ、１６ｃの幅が広い)。 Of the facing surfaces 15c and 16c of the first main body member 15 and the second main body member 16, the portion whose outer surface is not covered with the second reinforcing member 32 is covered with the first reinforcing member 30 and the second reinforcing member 32. The area is larger than the existing part (the width of the facing surfaces 15c and 16c is wide). That is, of the facing surfaces 15c and 16c of the first main body member 15 and the second main body member 16, the portion whose outer surface is not covered with the second reinforcing member 32 has a larger area than the portion on the proximal end side of the blade main body 11. Large (wide facing surfaces 15c and 16c). Of the facing surfaces 15c and 16c, the trailing edge TE side has a larger area than the leading edge LE side (the widths of the facing surfaces 15c and 16c are wider).

さらにいえば、中心軸Ｏと直交し第２のピークＰ２を含む断面における、トレーリングエッジＴＥ側の接続部の幅は、中心軸Ｏと直交し第２のピークＰ２より先端１１側のトレーリングエッジＴＥの第２補強部材３２に覆われていない位置を含む断面におけるトレーリングエッジＴＥ側の対向面の幅より小さい。あるいは、トレーリングエッジＴＥ側の対向面１５ｃ、１６ｃは、第２補強部材３２の先端側から翼本体１１の基端部の間で幅が最小となる。さらに、レーリングエッジＴＥ側の対向面１５ｃ、１６ｃは、第２補強部材３２より先端側に延在する位置で幅(翼本体１１の接合部の幅)が最大となる。トレーリングエッジＴＥ側の接合部の広さは、第２補強部材３２より翼本体１１の先端１２側に延在する位置において最大となる。 Furthermore, the width of the connecting portion on the trailing edge TE side in the cross section orthogonal to the central axis O and including the second peak P2 is the trailing on the tip 11 side of the second peak P2 orthogonal to the central axis O. It is smaller than the width of the facing surface on the trailing edge TE side in the cross section including the position not covered by the second reinforcing member 32 of the edge TE. Alternatively, the width of the facing surfaces 15c and 16c on the trailing edge TE side is minimized between the tip end side of the second reinforcing member 32 and the base end portion of the blade body 11. Further, the facing surfaces 15c and 16c on the railing edge TE side have a maximum width (width of the joint portion of the blade body 11) at a position extending toward the tip end side from the second reinforcing member 32. The width of the joint portion on the trailing edge TE side is maximum at a position extending from the second reinforcing member 32 to the tip 12 side of the blade body 11.

また、図６（ａ）に示すように、本実施例の翼本体１１の先端１２側は、リーディングエッジＬＥ側の第１補強部材３０に覆われていない。すなわち、翼本体１１の先端１２側において翼本体１１が露出している。当該翼本体１１の先端１２側においては、リーディングエッジＬＥ側の接合部も、翼本体１１の基端側の部位よりも面積が大きい(対向面１５ｃ、１６ｃの幅が広い)。リーディングエッジＬＥ側の接合部（対向面１５ｃ、１６ｃ）の広さは、第１補強部材３０に覆われた位置において最小となる。 Further, as shown in FIG. 6A, the tip 12 side of the wing body 11 of this embodiment is not covered with the first reinforcing member 30 on the leading edge LE side. That is, the wing body 11 is exposed on the tip 12 side of the wing body 11. On the tip 12 side of the blade body 11, the joint portion on the leading edge LE side also has a larger area than the portion on the base end side of the blade body 11 (the widths of the facing surfaces 15c and 16c are wide). The width of the joints (opposing surfaces 15c and 16c) on the leading edge LE side is minimized at the position covered by the first reinforcing member 30.

対向面１５ｃ、１６ｃは、第２補強部材３２で補強する代わりに、対向面１５ｃ、１６ｃの面積を大きくすることで、接合力が向上している。 The facing surfaces 15c and 16c are reinforced by the second reinforcing member 32, but the joining force is improved by increasing the area of the facing surfaces 15c and 16c.

図６（ｄ）は、幅広部１３よりも翼本体１１の基端側（基部１４側）の断面である。上記のように、第１補強部材３０、第２補強部材３２は、接合部を、少なくとも幅広部１３よりも翼本体１１の先端１２側から基端側（基部１４側）まで覆う。 FIG. 6D is a cross section of the blade body 11 on the base end side (base 14 side) of the wide portion 13. As described above, the first reinforcing member 30 and the second reinforcing member 32 cover the joint portion from at least the tip 12 side of the wing body 11 to the base end side (base 14 side) of the wide portion 13.

図７は、図６（ｃ）のうち、第１補強部材３０近傍の抽出図である。図７に示すように、第１補強部材３０のうち、翼本体１１側の内面３０ａは、中心軸Ｏに垂直な断面形状が曲面となっている。そのため、第１補強部材３０の内面３０ａと接着剤との接触面積を大きく確保できる。 FIG. 7 is an extracted view of the vicinity of the first reinforcing member 30 in FIG. 6 (c). As shown in FIG. 7, of the first reinforcing member 30, the inner surface 30a on the blade body 11 side has a curved cross-sectional shape perpendicular to the central axis O. Therefore, a large contact area between the inner surface 30a of the first reinforcing member 30 and the adhesive can be secured.

また、第１補強部材３０は、厚肉部３０ｂを有する。厚肉部３０ｂは、肉厚（例えば、内面３０ａの法線方向の厚み、または、コードライン方向の厚み）が最大となる。厚肉部３０ｂは、第１本体部材１５、第２本体部材１６の対向方向（図７中、上下方向、直交方向）の中心近傍（対向面１５ｃ、１６ｃ近傍）に位置する。第１補強部材３０の肉厚は、厚肉部３０ｂから内面３０ａの両端３０ｃ、３０ｄに向って漸減する。すなわち、第１補強部材３０は、厚肉部３０ｂから両端３０ｃ、３０ｄに向って徐々に薄くなっている。また、中心軸Ｏに垂直な断面において、第１補強部材３０の外周面の曲率の平均は、第１補強部材３０の内周面の曲率の平均と比べ大きい。さらに、当該断面において、第１補強部材３０の外周面の曲率の最大は、第１補強部材３０の内周面の曲率の最大より大きい。第１補強部材３０は、両端３０ｃ、３０ｄ近傍において、翼本体１１の外表面と滑らかに連続する形状となっている。 Further, the first reinforcing member 30 has a thick portion 30b. The thick portion 30b has the maximum wall thickness (for example, the thickness of the inner surface 30a in the normal direction or the thickness in the cord line direction). The thick portion 30b is located near the center (near the facing surfaces 15c and 16c) of the first main body member 15 and the second main body member 16 in the facing direction (vertical direction, orthogonal direction in FIG. 7). The wall thickness of the first reinforcing member 30 gradually decreases from the thick portion 30b toward both ends 30c and 30d of the inner surface 30a. That is, the first reinforcing member 30 gradually becomes thinner from the thick portion 30b toward both ends 30c and 30d. Further, in the cross section perpendicular to the central axis O, the average curvature of the outer peripheral surface of the first reinforcing member 30 is larger than the average curvature of the inner peripheral surface of the first reinforcing member 30. Further, in the cross section, the maximum curvature of the outer peripheral surface of the first reinforcing member 30 is larger than the maximum curvature of the inner peripheral surface of the first reinforcing member 30. The first reinforcing member 30 has a shape that is smoothly continuous with the outer surface of the blade body 11 at both ends 30c and 30d.

また、翼本体１１の内面側に第１補強部材３０、第２補強部材３２を設ける場合、まず、例えば、第１本体部材１５の内面に第１補強部材３０、第２補強部材３２を接合する。そして、第１補強部材３０、第２補強部材３２に接着剤を塗布した後、第２本体部材１６を、図７中、下方向に移動させて第１本体部材１５に近接させながら、第１補強部材３０、第２補強部材３２に接合する。第２本体部材１６を第１本体部材１５に近接させるとき、第１補強部材３０、第２補強部材３２に塗布された接着剤が削げ落ちてしまう。翼本体１１の外面側に第１補強部材３０、第２補強部材３２を設けることで、接着剤が削げ落ちる事態を回避できる。 When the first reinforcing member 30 and the second reinforcing member 32 are provided on the inner surface side of the wing body 11, for example, the first reinforcing member 30 and the second reinforcing member 32 are joined to the inner surface of the first main body member 15. .. Then, after applying the adhesive to the first reinforcing member 30 and the second reinforcing member 32, the second main body member 16 is moved downward in FIG. 7 so as to be close to the first main body member 15. It is joined to the reinforcing member 30 and the second reinforcing member 32. When the second main body member 16 is brought close to the first main body member 15, the adhesive applied to the first reinforcing member 30 and the second reinforcing member 32 is scraped off. By providing the first reinforcing member 30 and the second reinforcing member 32 on the outer surface side of the blade main body 11, it is possible to avoid a situation in which the adhesive is scraped off.

以上、添付図面を参照しながら本開示の実施形態について説明したが、本開示はかかる実施形態に限定されないことは言うまでもない。当業者であれば、特許請求の範囲に記載された範疇において、各種の変更例または修正例に想到し得ることは明らかであり、それらについても当然に本開示の技術的範囲に属するものと了解される。 Although the embodiments of the present disclosure have been described above with reference to the accompanying drawings, it goes without saying that the present disclosure is not limited to such embodiments. It is clear to those skilled in the art that various modifications or modifications can be conceived within the scope of the claims, and it is understood that they also naturally belong to the technical scope of the present disclosure. Will be done.

例えば、上述した実施形態では、第２補強部材３２が設けられる場合について説明した。しかし、第２補強部材３２は必須構成ではない。ただし、第２補強部材３２を設けることで強度の向上が図られる。 For example, in the above-described embodiment, the case where the second reinforcing member 32 is provided has been described. However, the second reinforcing member 32 is not an essential configuration. However, the strength can be improved by providing the second reinforcing member 32.

また、上述した実施形態では、第１補強部材３０は、第２補強部材３２よりも翼本体１１の先端１２側まで延在する場合について説明した。この場合、例えば、リーディングエッジＬＥを第１補強部材３０で形成することで、上記のように、対向面１５ｃ、１６ｃの位置ずれによる性能低下が抑制される。 Further, in the above-described embodiment, the case where the first reinforcing member 30 extends beyond the second reinforcing member 32 to the tip 12 side of the blade body 11 has been described. In this case, for example, by forming the leading edge LE with the first reinforcing member 30, performance deterioration due to misalignment of the facing surfaces 15c and 16c is suppressed as described above.

また、第２補強部材３２が、第１補強部材３０よりも先端１２側まで延在してもよいし、第１補強部材３０、第２補強部材３２が同程度に延在してもよい。この場合、第１本体部材１５と第２本体部材１６で形成されるトレーリングエッジＴＥと同様、第２補強部材３２の外面を鋭角に形成する必要がある。第２補強部材３２がＦＲＰ製の場合、鋭角形状とするには、強度上の限界がある。そこで、トレーリングエッジＴＥには、例えば、鋭角形状の金属部材を設けてもよい。また、第２補強部材３２のうち、トレーリングエッジＴＥとなる部位を鋸刃（セレーション）形状としてもよい。この場合、騒音抑制によりエネルギー損失を低減することが可能となる。 Further, the second reinforcing member 32 may extend to the tip 12 side of the first reinforcing member 30, or the first reinforcing member 30 and the second reinforcing member 32 may extend to the same extent. In this case, it is necessary to form the outer surface of the second reinforcing member 32 at an acute angle, as in the trailing edge TE formed by the first main body member 15 and the second main body member 16. When the second reinforcing member 32 is made of FRP, there is a limit in strength in order to form an acute angle shape. Therefore, the trailing edge TE may be provided with, for example, an acute-angled metal member. Further, the portion of the second reinforcing member 32 that becomes the trailing edge TE may have a saw blade (serration) shape. In this case, it is possible to reduce the energy loss by suppressing noise.

また、上述した実施形態では、翼本体１１、第１補強部材３０、第２補強部材３２がＦＲＰ製である場合について説明した。しかし、翼本体１１、第１補強部材３０、第２補強部材３２はＦＲＰ製に限られない。 Further, in the above-described embodiment, the case where the blade body 11, the first reinforcing member 30, and the second reinforcing member 32 are made of FRP has been described. However, the wing body 11, the first reinforcing member 30, and the second reinforcing member 32 are not limited to those made of FRP.

また、上述した実施形態では、第１補強部材３０および第２補強部材３２が、基部１４とともに挿通孔４１ａに挿通されている場合について説明した。しかし、第１補強部材３０および第２補強部材３２は、接合部を、少なくとも幅広部１３よりも翼本体１１の先端１２側から基端側（基部１４側）まで覆えばよい。 Further, in the above-described embodiment, the case where the first reinforcing member 30 and the second reinforcing member 32 are inserted into the insertion hole 41a together with the base portion 14 has been described. However, the first reinforcing member 30 and the second reinforcing member 32 may cover the joint portion from at least the tip 12 side of the blade body 11 to the base end side (base 14 side) of the wide portion 13.

例えば、第１補強部材３０および第２補強部材３２のうち、基部１４側の端部が、接続部材４０の手前までしか延在していない場合、第１補強部材３０および第２補強部材３２の端部近傍に応力が作用してしまう。第１補強部材３０および第２補強部材３２が、接続部材４０の挿通孔４１ａの内部まで連続して延在する場合、このような応力が抑制される。また、第１補強部材３０および第２補強部材３２によって、作用する曲げモーメントが大きい基部１４の接合部の強度を向上することができる。ここで、第１補強部材３０および第２補強部材３２は、翼本体１１の基端側に、接続部材４０に径方向に対向する位置まで延在していればよい。すなわち、第１補強部材３０および第２補強部材３２は、接続部材４０の外周面４５の外側に延在してもよい。 For example, when the end of the first reinforcing member 30 and the second reinforcing member 32 on the base 14 side extends only to the front of the connecting member 40, the first reinforcing member 30 and the second reinforcing member 32 Stress acts near the end. When the first reinforcing member 30 and the second reinforcing member 32 continuously extend to the inside of the insertion hole 41a of the connecting member 40, such stress is suppressed. Further, the strength of the joint portion of the base portion 14 having a large bending moment acting can be improved by the first reinforcing member 30 and the second reinforcing member 32. Here, the first reinforcing member 30 and the second reinforcing member 32 may extend to the base end side of the blade body 11 to a position that faces the connecting member 40 in the radial direction. That is, the first reinforcing member 30 and the second reinforcing member 32 may extend outside the outer peripheral surface 45 of the connecting member 40.

また、上述した実施形態では、接合部は、第１補強部材３０、第２補強部材３２より翼本体１１の先端１２側に延在する場合について説明した。すなわち、接合部のうち、翼本体１１の先端１２側の一部は、第１補強部材３０、第２補強部材３２で覆われていない場合について説明した。しかし、接合部は、翼本体１１の先端１２まで第１補強部材３０または第２補強部材３２で覆われていてもよい。ただし、接合部のうち、翼本体１１の先端１２側の一部が、第１補強部材３０、第２補強部材３２で覆われていない場合、ブレード１０の先端を薄く形成し易い。そのため、騒音抑制によりエネルギー損失を低減することが可能となる。 Further, in the above-described embodiment, the case where the joint portion extends from the first reinforcing member 30 and the second reinforcing member 32 to the tip 12 side of the blade body 11 has been described. That is, a case has been described in which a part of the joint portion on the tip 12 side of the blade body 11 is not covered with the first reinforcing member 30 and the second reinforcing member 32. However, the joint portion may be covered with the first reinforcing member 30 or the second reinforcing member 32 up to the tip 12 of the blade body 11. However, when a part of the joint portion on the tip 12 side of the blade body 11 is not covered with the first reinforcing member 30 and the second reinforcing member 32, the tip of the blade 10 is likely to be thinly formed. Therefore, it is possible to reduce energy loss by suppressing noise.

本開示は、リーディングエッジおよびトレーリングエッジを有するブレードに利用することができる。 The present disclosure is available for blades with leading and trailing edges.

１０ ブレード
１１ 翼本体
１２ 先端
１４ 基部
１５ 第１本体部材
１５ｃ 対向面（接合部）
１６ 第２本体部材
１６ｃ 対向面（接合部）
３０ 第１補強部材
３２ 第２補強部材
４０ 接続部材
ＬＥ リーディングエッジ
ＴＥ トレーリングエッジ
Ｐ１ 第１のピーク（ピーク）
Ｐ２ 第２のピーク（ピーク） 10 Blade 11 Wing body 12 Tip 14 Base 15 First body member 15c Opposing surface (joint)
16 Second main body member 16c Opposing surface (joint)
30 1st reinforcing member 32 2nd reinforcing member 40 Connecting member LE Leading edge TE Trailing edge P1 1st peak (peak)
P2 2nd peak (peak)

Claims (8)

第１本体部材および第２本体部材が接合部で接合された翼本体と、
前記翼本体の基端側と接続された接続部材と、
前記接続部材に対して径方向に対向する位置から延在し、前記翼本体のリーディングエッジ側の前記接合部を覆う第１補強部材と、
前記接続部材に対して径方向に対向する位置から延在し、前記翼本体のトレーリングエッジ側の前記接合部を覆う第２補強部材と、
を備え、
前記第１補強部材と前記第２補強部材とは、前記翼本体の周方向に離隔して配置され、
前記第１補強部材は、前記第２補強部材よりも前記翼本体の先端側まで延在するブレード。 A wing body in which the first main body member and the second main body member are joined at a joint,
A connecting member connected to the base end side of the wing body and
A first reinforcing member that extends from a position that is radially opposed to the connecting member and covers the joint portion on the leading edge side of the wing body.
A second reinforcing member that extends from a position that is radially opposed to the connecting member and covers the joint portion on the trailing edge side of the wing body.
Equipped with a,
The first reinforcing member and the second reinforcing member are arranged apart from each other in the circumferential direction of the blade body.
The first reinforcing member is a blade extending from the second reinforcing member to the tip end side of the blade body. 前記翼本体の前記リーディングエッジは、ピークを備え、
前記第１補強部材は、前記ピークを越えて延伸している請求項１に記載のブレード。 The leading edge of the blade body includes a peak,
The blade according to claim 1, wherein the first reinforcing member extends beyond the peak. 前記接合部は、前記第１補強部材より前記翼本体の先端側に延在する請求項１または２に記載のブレード。 The blade according to claim 1 or 2, wherein the joint portion extends from the first reinforcing member to the tip end side of the blade body. 前記リーディングエッジ側の前記接合部の広さは、前記第１補強部材に覆われた位置において最小となる請求項３に記載のブレード。 The blade according to claim 3 , wherein the width of the joint portion on the leading edge side is minimized at a position covered by the first reinforcing member. 前記接合部は、前記第２補強部材より前記翼本体の先端側に延在する請求項１から４のいずれか１項に記載のブレード。 The blade according to any one of claims 1 to 4 , wherein the joint portion extends from the second reinforcing member to the tip end side of the blade body. 前記トレーリングエッジ側の前記接合部の広さは、前記第２補強部材より前記翼本体の先端側に延在する位置において最大となる請求項５に記載のブレード。 The blade according to claim 5 , wherein the width of the joint portion on the trailing edge side is maximized at a position extending from the second reinforcing member to the tip end side of the blade body. 前記翼本体は、繊維強化複合材料が積層されたものであり、
前記接合部は、前記翼本体の内面側から外面側に向かい積層された断面同士が接合されている請求項１から６のいずれか１項に記載のブレード。 The wing body is a laminated fiber-reinforced composite material.
The blade according to any one of claims 1 to 6 , wherein the joint portion is formed by joining the cross sections laminated from the inner surface side to the outer surface side of the blade body. 第１本体部材および第２本体部材が接合部で接合された翼本体と、
前記翼本体のリーディングエッジおよびトレーリングエッジの双方に形成されたピークと、
前記翼本体の前記リーディングエッジの前記ピークよりも、前記翼本体の先端側から基端側まで、前記翼本体の前記リーディングエッジ側の前記接合部の外側を覆う第１補強部材と、
前記翼本体の前記トレーリングエッジの前記ピークよりも、前記翼本体の先端側から基端側まで、前記翼本体の前記トレーリングエッジ側の前記接合部の外側を覆う第２補強部材と、
を備え、
前記第１補強部材と前記第２補強部材とは、前記翼本体の周方向に離隔して配置され、
前記第１補強部材は、前記第２補強部材よりも前記翼本体の先端側まで延在するブレード。 A wing body in which the first main body member and the second main body member are joined at a joint,
A peak formed in bi towards the leading edge and trailing edge of the blade body,
A first reinforcing member that covers the outside of the joint portion on the leading edge side of the wing body from the tip end side to the proximal end side of the wing body from the peak of the leading edge of the wing body.
A second reinforcing member that covers the outside of the joint portion on the trailing edge side of the wing body from the tip end side to the base end side of the wing body from the peak of the trailing edge of the wing body.
Equipped with a,
The first reinforcing member and the second reinforcing member are arranged apart from each other in the circumferential direction of the blade body.
The first reinforcing member is a blade extending from the second reinforcing member to the tip end side of the blade body.
JP2017076661A 2017-04-07 2017-04-07 blade Active JP6885168B2 (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
JP2017076661A JP6885168B2 (en) 2017-04-07 2017-04-07 blade

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
JP2017076661A JP6885168B2 (en) 2017-04-07 2017-04-07 blade

Publications (2)

Publication Number Publication Date
JP2018178800A JP2018178800A (en) 2018-11-15
JP6885168B2 true JP6885168B2 (en) 2021-06-09

Family

ID=64281567

Family Applications (1)

Application Number Title Priority Date Filing Date
JP2017076661A Active JP6885168B2 (en) 2017-04-07 2017-04-07 blade

Country Status (1)

Country Link
JP (1) JP6885168B2 (en)

Family Cites Families (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JPS62282177A (en) * 1986-05-31 1987-12-08 Yamaha Motor Co Ltd Blade fixing structure for windmill rotor
FR2616409B1 (en) * 1987-06-09 1989-09-15 Aerospatiale BLADE OF COMPOSITE MATERIALS AND MANUFACTURING METHOD THEREOF
US7637721B2 (en) * 2005-07-29 2009-12-29 General Electric Company Methods and apparatus for producing wind energy with reduced wind turbine noise
CN102448711B (en) * 2009-04-10 2015-05-13 湘电达尔文有限责任公司 A protected wind turbine blade, a method of manufacturing it and a wind turbine
JP2015151961A (en) * 2014-02-17 2015-08-24 三菱重工業株式会社 Rotary wing blade, rotary wing, and rotary wing blade manufacturing method
JP6407057B2 (en) * 2014-07-30 2018-10-17 積水化学工業株式会社 Method for producing molded thermoplastic resin

Also Published As

Publication number Publication date
JP2018178800A (en) 2018-11-15

Similar Documents

Publication Publication Date Title
KR101808947B1 (en) Wind turbine blade and wind turbine generator, and method of producing or retrofitting wind turbine blade
WO2013084634A1 (en) Wind turbine and wind power generation device
EP3085952B1 (en) Airflow configuration for a wind turbine rotor blade
JP6877575B2 (en) Windmill wings and wind power generators
US8550786B2 (en) Vertical axis wind turbine with self-starting capabilities
JP5536103B2 (en) Wind turbine rotor
US8186964B2 (en) Spar assembly for a wind turbine rotor blade
US20140271198A1 (en) Wind turbine blades with layered, multi-component spars, and associated systems and methods
BR112020003184B1 (en) ROTOR BLADE ASSEMBLY AND CONNECTION STRUCTURE
US11506182B2 (en) Wind turbine blade assembly
WO2019235522A1 (en) Vertical axis windmill and wind power generation device
EP3751133B1 (en) Rotor blade for a wind turbine
EP2691634A1 (en) Spar for a water-driven turbine blade and manufacture thereof
JP6885168B2 (en) blade
JP2022502595A (en) Joint wind turbine blades with noise reduction tape
JP6885167B2 (en) blade
WO2022114106A1 (en) Vortex generator for wind turbine blade, wind turbine blade, and wind-power generation apparatus
JP5730408B2 (en) Wind turbine blade and wind power generator
WO2014127923A1 (en) Wind turbine blade having twisted spar web
US20230016436A1 (en) Reinforcing structure for a wind turbine blade
JP2018146025A (en) Fastening structure
JP2018146026A (en) Fastening structure
JP2005147080A (en) Blade of horizontal axis wind mill
WO2024193779A1 (en) A pitch controlled wind turbine

Legal Events

Date Code Title Description
A621 Written request for application examination

Free format text: JAPANESE INTERMEDIATE CODE: A621

Effective date: 20200316

A977 Report on retrieval

Free format text: JAPANESE INTERMEDIATE CODE: A971007

Effective date: 20210112

A131 Notification of reasons for refusal

Free format text: JAPANESE INTERMEDIATE CODE: A131

Effective date: 20210126

A521 Written amendment

Free format text: JAPANESE INTERMEDIATE CODE: A523

Effective date: 20210323

TRDD Decision of grant or rejection written
A01 Written decision to grant a patent or to grant a registration (utility model)

Free format text: JAPANESE INTERMEDIATE CODE: A01

Effective date: 20210413

A61 First payment of annual fees (during grant procedure)

Free format text: JAPANESE INTERMEDIATE CODE: A61

Effective date: 20210426

R151 Written notification of patent or utility model registration

Ref document number: 6885168

Country of ref document: JP

Free format text: JAPANESE INTERMEDIATE CODE: R151