JP6885167B2 - blade - Google Patents

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JP6885167B2
JP6885167B2 JP2017076660A JP2017076660A JP6885167B2 JP 6885167 B2 JP6885167 B2 JP 6885167B2 JP 2017076660 A JP2017076660 A JP 2017076660A JP 2017076660 A JP2017076660 A JP 2017076660A JP 6885167 B2 JP6885167 B2 JP 6885167B2
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reinforcing member
main body
blade
base
wing
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JP2018178799A (en
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祥 村田
祥 村田
和夫 島村
和夫 島村
真 豊田
真 豊田
充良 津乗
充良 津乗
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IHI Corp
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IHI Corp
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    • 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

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、海洋発電に使用可能な回転翼のブレードが記載されている。翼本体は、２つの分割体によって形成される。翼本体の基端側は、基端から先端に向かう翼長方向に垂直な断面形状が大凡楕円形状となっている。また、翼本体の基端側は、リーディングエッジとトレーリングエッジを結ぶコードライン方向が長く、コードライン方向に直交する直交方向が短くなっている。 For example, Patent Document 1 describes blades of rotary blades that can be used for ocean power generation. The wing body is formed by two split bodies. The base end side of the blade body has an approximately elliptical cross-sectional shape perpendicular to the blade length direction from the base end to the tip. Further, on the base end side of the wing body, the cord line direction connecting the leading edge and the trailing edge is long, and the orthogonal direction orthogonal to the cord line direction is short.

特開２０１５−１５１９６１号公報Japanese Unexamined Patent Publication No. 2015-151961

翼本体のうち、基端側に位置する基部には、海流による荷重が作用する。荷重は、基部のうち、コードライン方向に直交する直交方向に作用する。特許文献１に記載の構成では、海流による荷重に対して、翼本体の基部の強度が不足するおそれがある。 A load due to ocean currents acts on the base of the wing body located on the base end side. The load acts in the orthogonal direction of the base, which is orthogonal to the code line direction. With the configuration described in Patent Document 1, the strength of the base of the blade body may be insufficient with respect to the load due to the ocean current.

本開示は、このような課題に鑑み、翼本体の基部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 strength of the base 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、翼本体と、翼本体の基端側に設けられ、リーディングエッジとトレーリングエッジとを結ぶコードライン方向の外周面間の距離が、コードライン方向に直交する直交方向の外周面間の距離よりも短い基部と、基部の外側面の少なくとも一部を覆う外壁部が形成される円筒形状の本体を有する接続部材と、接続部材と基部との間に設けられる補強部材と、を備え、補強部材は、リーディングエッジ側に設けられた第１補強部材と、トレーリングエッジ側に設けられた第２補強部材と、を含み、第１補強部材と第２補強部材とは、基部の周方向に離隔して配置され、基部には、本体に沿って延在する円弧部と、本体の内周面から径方向内側に離隔する扁平部とが形成されており、第１補強部材および第２補強部材は、本体の内周面と扁平部に挟持される。 In order to solve the above problems, the blade according to one aspect of the present disclosure is provided on the base end side of the wing body and is a distance between the outer peripheral surfaces in the cord line direction connecting the leading edge and the trailing edge. However, a connecting member having a base portion shorter than the distance between the outer peripheral surfaces in the orthogonal direction orthogonal to the cord line direction, and a cylindrical main body in which an outer wall portion covering at least a part of the outer surface of the base portion is formed, and a connecting member. A reinforcing member provided between the base and the base portion is provided, and the reinforcing member includes a first reinforcing member provided on the leading edge side and a second reinforcing member provided on the trailing edge side. The 1st reinforcing member and the 2nd reinforcing member are arranged apart from each other in the circumferential direction of the base portion, and the base portion has an arc portion extending along the main body and a flat portion separated from the inner peripheral surface of the main body in the radial direction. A portion is formed, and the first reinforcing member and the second reinforcing member are sandwiched between the inner peripheral surface of the main body and the flat portion .

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してもよい。 The first reinforcing member may extend beyond the second reinforcing member to the tip end side of the blade body.

翼本体は、直交方向の一方向側に位置する第１本体部材、および、直交方向の他方向側に位置する第２本体部材が接合部で接合されて形成され、補強部材は、少なくとも外壁部の内部において、接合部の外側に設けられてもよい。 The wing body is formed by joining a first main body member located on one direction side in the orthogonal direction and a second main body member located on the other direction side in the orthogonal direction at a joint, and the reinforcing member is at least an outer wall portion. It may be provided inside the joint and outside the joint.

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、扁平な翼面を持つ翼本体と、翼本体に延接される基部と、基部の外側面の少なくとも一部を覆う外壁部が形成される円筒形状の本体を有する接続部材と、接続部材と基部との間に設けられる補強部材と、を備え、補強部材は、翼本体のリーディングエッジ側に設けられた第１補強部材と、翼本体のトレーリングエッジ側に設けられた第２補強部材と、を含み、基部は、翼面の扁平方向と異なる向きに扁平となっており、第１補強部材と第２補強部材とは、基部の周方向に離隔して配置され、基部には、本体に沿って延在する円弧部と、本体の内周面から径方向内側に離隔する扁平部とが形成されており、第１補強部材および第２補強部材は、本体の内周面と扁平部に挟持される。 In order to solve the above problems, another blade according to one aspect of the present disclosure covers at least a part of a wing body having a flat wing surface, a base extending to the wing body, and an outer surface of the base. A connecting member having a cylindrical body on which an outer wall portion is formed and a reinforcing member provided between the connecting member and the base portion are provided, and the reinforcing member is a first reinforcement provided on the leading edge side of the wing body. A member and a second reinforcing member provided on the trailing edge side of the blade body are included, and the base portion is flattened in a direction different from the flattening direction of the blade surface, and the first reinforcing member and the second reinforcing member are flattened. Is arranged so as to be separated from each other in the circumferential direction of the base, and the base is formed with an arc portion extending along the main body and a flat portion radially inwardly separated from the inner peripheral surface of the main body. The first reinforcing member and the second reinforcing member are sandwiched between the inner peripheral surface of the main body and the flat portion .

本開示によれば、翼本体の基部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 strength of the base 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。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.

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）の幅が最も大きい本体最大部１３が形成される。本体最大部１３は、翼本体１１の基端側に形成されている。本体最大部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、基端から本体最大部１３に向かって徐々に拡大し、本体最大部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、基端から本体最大部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、本体最大部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 the largest main body having the widest 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 main body maximum portion 13 is formed on the base end side of the wing main body 11. The maximum portion 13 of the main body 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 main body maximum portion 13, and gradually decreases from the main body maximum portion 13 toward the tip 12. That is, the blade main 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 main body maximum portion 13. The wing main 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 main body maximum 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、本体最大部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。本体最大部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 main body maximum portion 13 and to the front side from the tip 12 of the wing main body 11. The first reinforcing member 30 extends to the tip 12 side of the second reinforcing member 32. In the maximum portion 13 of the main body, 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。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. 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。また、第１補強部材３０、第２補強部材３２は、挿通孔４１ａから上記の割断線を覆って、翼本体１１の先端に向って延伸している。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。 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. Further, the first reinforcing member 30 and the second reinforcing member 32 extend from the insertion hole 41a toward the tip of the wing body 11 so as to cover the above-mentioned breaking line. 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 central axis O direction in a state where the end surface 46a on the other end 41c side is in contact with the swivel seat (not shown). 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（ａ）、図６（ｂ）に示すように、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。 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. As shown in FIGS. 6A and 6B, 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.

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（ａ）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。トレーリングエッジＴＥは、リーディングエッジＬＥよりも海流の流れに対する影響が小さい。そのため、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ても性能への影響が小さい。 As shown in FIG. 6A, 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. The trailing edge TE has a smaller effect on the ocean current than the leading edge LE. Therefore, even if the second reinforcing member 32 is formed shorter than the first reinforcing member 30, the influence on the performance is small.

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。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。 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 area where it is. 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 wing main body 11. large. Of the facing surfaces 15c and 16c, the trailing edge TE side has a larger area than the leading edge LE side.

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.

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、補強部材（第１補強部材３０、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、接続部材４０および補強部材は必須構成ではない。ただし、補強部材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 reinforcing members (first reinforcing member 30 and second reinforcing member 32) are provided has been described. However, the connecting member 40 and the reinforcing member are not essential configurations. However, the strength can be improved by providing the reinforcing member.

また、上述した実施形態では、補強部材は、第１補強部材３０と、第２補強部材３２とで構成される場合について説明した。しかし、第１補強部材３０、第２補強部材３２は、必須構成ではなく、例えば、第１補強部材３０、第２補強部材３２の一方のみが設けられてもよい。ただし、第１補強部材３０、第２補強部材３２の両方を設けることで、さらなる強度の向上が図られる。 Further, in the above-described embodiment, the case where the reinforcing member is composed of the first reinforcing member 30 and the second reinforcing member 32 has been described. However, the first reinforcing member 30 and the second reinforcing member 32 are not essential configurations, and for example, only one of the first reinforcing member 30 and the second reinforcing member 32 may be provided. However, by providing both the first reinforcing member 30 and the second reinforcing member 32, the strength can be further improved.

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。しかし、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。ただし、第１補強部材３０が、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、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. However, 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. However, when the first reinforcing member 30 extends beyond the second reinforcing member 32 to the tip 12 side of the blade body 11, for example, by forming the leading edge LE with the first reinforcing member 30, as described above. Performance deterioration due to misalignment of the facing surfaces 15c and 16c is suppressed.

また、上述した実施形態では、第１補強部材３０、第２補強部材３２が、接合部（対向面１５ｃ、１６ｃ）の外側に設けられる場合について説明した。しかし、第１補強部材３０、第２補強部材３２は、接合部（対向面１５ｃ、１６ｃ）から外れた位置に配されてもよい。ただし、第１補強部材３０、第２補強部材３２を接合部の外側に配することで、接合部の強度が向上する。 Further, in the above-described embodiment, the case where the first reinforcing member 30 and the second reinforcing member 32 are provided outside the joint portions (opposing surfaces 15c and 16c) has been described. However, the first reinforcing member 30 and the second reinforcing member 32 may be arranged at positions separated from the joints (opposing surfaces 15c and 16c). However, by arranging the first reinforcing member 30 and the second reinforcing member 32 on the outside of the joint portion, the strength of the joint portion is improved.

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.

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
１１ａ 翼面
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）
１９ 外周面
２１ 扁平部
３０ 第１補強部材（補強部材）
３２ 第２補強部材（補強部材）
４０ 接続部材
４２ 外壁部
ＬＥ リーディングエッジ
ＴＥ トレーリングエッジ
Ｌａ 距離
Ｌｂ 距離 10 Blade 11 Wing body 11a Wing surface 12 Tip 14 Base 15 First body member 15c Opposing surface (joint)
16 Second main body member 16c Opposing surface (joint)
19 Outer peripheral surface 21 Flat portion 30 First reinforcing member (reinforcing member)
32 Second reinforcing member (reinforcing member)
40 Connecting member 42 Outer wall LE Leading edge TE Trailing edge La Distance Lb Distance

Claims (4)

翼本体と、
前記翼本体の基端側に設けられ、リーディングエッジとトレーリングエッジとを結ぶコードライン方向の外周面間の距離が、前記コードライン方向に直交する直交方向の外周面間の距離よりも短い基部と、
前記基部の外側面の少なくとも一部を覆う外壁部が形成される円筒形状の本体を有する接続部材と、
前記接続部材と前記基部との間に設けられる補強部材と、
を備え、
前記補強部材は、
前記リーディングエッジ側に設けられた第１補強部材と、
前記トレーリングエッジ側に設けられた第２補強部材と、
を含み、
前記第１補強部材と前記第２補強部材とは、前記基部の周方向に離隔して配置され、
前記基部には、前記本体に沿って延在する円弧部と、前記本体の内周面から径方向内側に離隔する扁平部とが形成されており、
前記第１補強部材および前記第２補強部材は、前記本体の内周面と前記扁平部に挟持されるブレード。 With the wing body
A base portion provided on the base end side of the wing body, in which the distance between the outer peripheral surfaces in the cord line direction connecting the leading edge and the trailing edge is shorter than the distance between the outer peripheral surfaces in the orthogonal direction orthogonal to the cord line direction. When,
A connecting member having a cylindrical body on which an outer wall portion covering at least a part of the outer surface of the base portion is formed.
A reinforcing member provided between the connecting member and the base,
Equipped with a,
The reinforcing member is
The first reinforcing member provided on the leading edge side and
The second reinforcing member provided on the trailing edge side and
Including
The first reinforcing member and the second reinforcing member are arranged apart from each other in the circumferential direction of the base portion.
The base portion is formed with an arc portion extending along the main body and a flat portion radially inwardly separated from the inner peripheral surface of the main body.
The first reinforcing member and the second reinforcing member are blades sandwiched between the inner peripheral surface of the main body and the flat portion. 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請求項１に記載のブレード。 The blade according to claim 1 , wherein the first reinforcing member extends beyond the second reinforcing member to the tip end side of the blade body. 前記翼本体は、
前記直交方向の一方向側に位置する第１本体部材、および、前記直交方向の他方向側に位置する第２本体部材が接合部で接合されて形成され、
前記補強部材は、少なくとも前記外壁部の内部において、前記接合部の外側に設けられる請求項１または２に記載のブレード。 The wing body
A first main body member located on one direction side in the orthogonal direction and a second main body member located on the other direction side in the orthogonal direction are joined and formed at a joint portion.
The blade according to claim 1 or 2 , wherein the reinforcing member is provided outside the joint portion at least inside the outer wall portion. 扁平な翼面を持つ翼本体と、
前記翼本体に延接される基部と、
前記基部の外側面の少なくとも一部を覆う外壁部が形成される円筒形状の本体を有する接続部材と、
前記接続部材と前記基部との間に設けられる補強部材と、
を備え、
前記補強部材は、
前記翼本体のリーディングエッジ側に設けられた第１補強部材と、
前記翼本体のトレーリングエッジ側に設けられた第２補強部材と、
を含み、
前記基部は、前記翼面の扁平方向と異なる向きに扁平となっており、
前記第１補強部材と前記第２補強部材とは、前記基部の周方向に離隔して配置され、
前記基部には、前記本体に沿って延在する円弧部と、前記本体の内周面から径方向内側に離隔する扁平部とが形成されており、
前記第１補強部材および前記第２補強部材は、前記本体の内周面と前記扁平部に挟持されるブレード。 A wing body with a flat wing surface and
The base extending to the wing body and
A connecting member having a cylindrical body on which an outer wall portion covering at least a part of the outer surface of the base portion is formed.
A reinforcing member provided between the connecting member and the base,
With
The reinforcing member is
The first reinforcing member provided on the leading edge side of the wing body and
A second reinforcing member provided on the trailing edge side of the wing body and
Including
The base portion is flattened in a direction different from the flattening direction of the wing surface .
The first reinforcing member and the second reinforcing member are arranged apart from each other in the circumferential direction of the base portion.
The base portion is formed with an arc portion extending along the main body and a flat portion radially inwardly separated from the inner peripheral surface of the main body.
The first reinforcing member and the second reinforcing member are blades sandwiched between the inner peripheral surface of the main body and the flat portion.
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