JPH0357600Y2 - - Google Patents
Info
- Publication number
- JPH0357600Y2 JPH0357600Y2 JP1986090863U JP9086386U JPH0357600Y2 JP H0357600 Y2 JPH0357600 Y2 JP H0357600Y2 JP 1986090863 U JP1986090863 U JP 1986090863U JP 9086386 U JP9086386 U JP 9086386U JP H0357600 Y2 JPH0357600 Y2 JP H0357600Y2
- Authority
- JP
- Japan
- Prior art keywords
- shell
- composite
- sheet
- rotor blade
- composite material
- 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.)
- Expired
Links
- 239000002131 composite material Substances 0.000 claims description 32
- 239000000835 fiber Substances 0.000 claims description 15
- 239000000470 constituent Substances 0.000 claims description 9
- 239000000126 substance Substances 0.000 claims description 7
- 229920003002 synthetic resin Polymers 0.000 claims description 5
- 239000000057 synthetic resin Substances 0.000 claims description 5
- 239000004744 fabric Substances 0.000 claims description 4
- 238000010030 laminating Methods 0.000 claims description 3
- 230000002093 peripheral effect Effects 0.000 claims description 3
- 239000011162 core material Substances 0.000 description 6
- 230000032798 delamination Effects 0.000 description 5
- 238000000034 method Methods 0.000 description 5
- 239000000945 filler Substances 0.000 description 4
- 239000000463 material Substances 0.000 description 4
- 229920000271 Kevlar® Polymers 0.000 description 3
- 239000000853 adhesive Substances 0.000 description 3
- 230000001070 adhesive effect Effects 0.000 description 3
- 229910052782 aluminium Inorganic materials 0.000 description 3
- XAGFODPZIPBFFR-UHFFFAOYSA-N aluminium Chemical compound [Al] XAGFODPZIPBFFR-UHFFFAOYSA-N 0.000 description 3
- 239000004761 kevlar Substances 0.000 description 3
- 229920005989 resin Polymers 0.000 description 3
- 239000011347 resin Substances 0.000 description 3
- 238000010008 shearing Methods 0.000 description 3
- 229920000049 Carbon (fiber) Polymers 0.000 description 2
- 229920002430 Fibre-reinforced plastic Polymers 0.000 description 2
- 239000004917 carbon fiber Substances 0.000 description 2
- 239000004918 carbon fiber reinforced polymer Substances 0.000 description 2
- 230000000694 effects Effects 0.000 description 2
- 230000005284 excitation Effects 0.000 description 2
- 239000011151 fibre-reinforced plastic Substances 0.000 description 2
- 238000004519 manufacturing process Methods 0.000 description 2
- 239000007769 metal material Substances 0.000 description 2
- VNWKTOKETHGBQD-UHFFFAOYSA-N methane Chemical compound C VNWKTOKETHGBQD-UHFFFAOYSA-N 0.000 description 2
- 238000000465 moulding Methods 0.000 description 2
- 239000002759 woven fabric Substances 0.000 description 2
- RTAQQCXQSZGOHL-UHFFFAOYSA-N Titanium Chemical compound [Ti] RTAQQCXQSZGOHL-UHFFFAOYSA-N 0.000 description 1
- 238000005452 bending Methods 0.000 description 1
- -1 but recently Substances 0.000 description 1
- 238000007730 finishing process Methods 0.000 description 1
- 238000010438 heat treatment Methods 0.000 description 1
- 230000013011 mating Effects 0.000 description 1
- 239000004033 plastic Substances 0.000 description 1
- 229920003023 plastic Polymers 0.000 description 1
- 230000003014 reinforcing effect Effects 0.000 description 1
- 238000009958 sewing Methods 0.000 description 1
- 239000010936 titanium Substances 0.000 description 1
- 229910052719 titanium Inorganic materials 0.000 description 1
- 238000009941 weaving Methods 0.000 description 1
Description
【考案の詳細な説明】
〔産業上の利用分野〕
この考案は、航空機用プロペラ、ヘリコプター
ローター、風車などに使用される回転翼に関す
る。[Detailed Description of the Invention] [Industrial Application Field] This invention relates to rotary blades used in aircraft propellers, helicopter rotors, wind turbines, and the like.
＜従来の技術＞
一般にこれらの回転翼には引張り、曲げ、捩じ
り等の荷重が複雑に組合わさつた形で作用する
他、回転数の整数倍の加振力及び変動空気力が作
用する。<Prior art> In general, these rotor blades are subjected to complex combinations of loads such as tension, bending, and torsion, as well as excitation forces and fluctuating aerodynamic forces that are integral multiples of the rotational speed. .
従つて、この種の回転翼は十分な強度を有する
ことは勿論のこと、回転加振力及び変動空気力と
共振しないよう剛性を管理することも必要とされ
る。 Therefore, this type of rotor blade not only needs to have sufficient strength, but also needs to control its rigidity so as not to resonate with rotational excitation force and fluctuating aerodynamic force.
当初、このような回転翼は、アルミニウム等の
金属材料から削り出しでつくられていたが、最近
になつて、軽量でしかも強度的にも有利であると
の理由から、繊維強化プラスチツク、いわゆる
FRPが回転翼の材料に適用されるようになつて
きた。 Initially, such rotor blades were made by cutting out metal materials such as aluminum, but recently, fiber-reinforced plastics, or so-called fiber-reinforced plastics, have been used because they are lightweight and have the advantage of strength.
FRP has come to be used as a material for rotor blades.
FRPを使用する場合、回転翼は例えば第１図
（スパン方向断面図）に示す如く、翼スパン方向
に伸びる翼桁（スパー）２と所要の充填材３とで
構成された芯材４と、その周囲を覆い翼型を形成
するシエル（外皮ともいう）１とからなる構造を
採用する。そのシエルの構造としては、
一方向プリプレグシートまたは織物プリプレ
グシート（プリプレグシート‥繊維を並べまた
は織つて樹脂を含浸させ含浸樹脂を半硬化状態
にしたシート）をその繊維方向を適当に交叉さ
せて芯材４の上に所要の厚さに積層して接着硬
化させた構造、および
織物の繊維方向を適当に交叉させて所要の厚
さに配置し、これに合成樹脂をインジエクトし
て接着硬化させた構造（以下、これらを複合材
シエルという）が知られている。 When using FRP, the rotor blade has a core material 4 composed of a spar 2 extending in the blade span direction and a required filler 3, as shown in FIG. 1 (cross-sectional view in the span direction), for example. A structure consisting of a shell (also called outer skin) 1 that covers the periphery and forms an airfoil shape is adopted. The structure of the shell is as follows: A unidirectional prepreg sheet or a woven prepreg sheet (prepreg sheet: a sheet made by arranging or weaving fibers and impregnating them with a resin and semi-curing the impregnated resin) is made by intersecting the fiber directions appropriately and forming a core. A structure in which the fibers of the fabric were laminated to the required thickness and cured with adhesive, and the fibers of the fabric were arranged to the desired thickness with the fiber directions appropriately crossed, and a synthetic resin was injected into this and cured with adhesive. structures (hereinafter referred to as composite shells) are known.
ところで、このような複合材シエル１は、第１
図に示す如く、腹側１０と背側１１とに分割して
構成されるため、周縁に構成シートの自由端末部
１′ができる。
By the way, such a composite material shell 1 has a first
As shown in the figure, since it is divided into a ventral side 10 and a dorsal side 11, a free end portion 1' of the constituent sheet is formed at the periphery.
このようなシェルをもつ回転翼にあつては、使
用時、荷重を受けた場合、上記シート自由端末部
の層間に大きな剪断力が働き、この剪断力によつ
てシエル自体が構成シートの自由端末部、特に前
縁１ａあるいは後縁１ｂのシエル薄肉部から、構
成シートの層間剥離を生じやすく、一旦構成シー
トの層間剥離が生ずると、やがて翼全体の破損に
至る事態が避けられず、これが複合材回転翼の最
大の欠点となつていた。この欠点を克服するた
め、従来より種々の提案がなされてきた。 When a rotor blade having such a shell is subjected to a load during use, a large shearing force acts between the layers of the free end of the sheet, and this shearing force causes the shell itself to disintegrate into the free end of the constituent sheet. delamination of the constituent sheets is likely to occur from the thin shell parts, especially the leading edge 1a or the trailing edge 1b. This was the biggest drawback of rotor blades. Various proposals have been made to overcome this drawback.
杉綾織された樹脂含浸複合材シートで回転翼
外皮を構成し、複合材シートの杉綾織目の連続
する方向を回転翼のスパン方向に向けて配置す
ることにより剥離強度をもたせること（特開昭
50−63698号公報）。 The outer skin of the rotor blade is made of a resin-impregnated composite sheet with a herringbone weave, and the continuous direction of the herringbone weave of the composite sheet is oriented in the span direction of the rotor blade, thereby providing peel strength (Japanese Patent Application Laid-Open No.
50-63698).
翼成形後前縁部と後縁部にオーバーレイを施
しこの外面を所定形状に仕上げること（特開昭
56−104197号公報）。 After forming the wing, an overlay is applied to the leading edge and trailing edge to finish the outer surface into a predetermined shape (Japanese Patent Laid-Open No.
56-104197).
上記２つがその代表的なものであるが、前者は
複合材シートを特殊な杉綾織とする必要上、シー
トのコスト、製作工数の増加が著しく、後者はオ
ーバーレイ後に手仕上げ工程が必要で熟練加工技
能者を必要とするのみならず、表面にどうしても
凹凸が残り効率のよい翼を得ることが困難である
など、いずれも実用上十分なものとは言い難かつ
た。 The above two are typical examples, but the former requires a special herringbone weave for the composite sheet, which significantly increases sheet cost and manufacturing man-hours, while the latter requires a hand-finishing process after overlaying, which requires skilled processing. Not only did it require a skilled worker, but it was also difficult to obtain an efficient blade due to the unavoidable unevenness of the surface, making it difficult to say that it was sufficient for practical use.
この考案は、上記の問題に鑑みてなされたもの
であつて、複合材シエル周縁部における構成シー
トの層間剥離を確実に防止でき、しかも特殊構造
のシートを用いず、また製造に当たり特別な技能
も必要せず、且つ凹凸のない滑らかな表面を持つ
複合材回転翼を提供するものである。 This invention was made in view of the above problems, and can reliably prevent delamination of the component sheets at the peripheral edge of the composite shell, and does not require special skills to manufacture. To provide a composite rotor blade having a smooth surface without any unevenness.
本考案の回転翼は、合成樹脂含浸複合材シート
を積層して、あるいは織物に合成樹脂をインジエ
クシヨンして形成した翼型の複合材シエル１を有
し、シエル周縁に構成シートの自由端末部１′を
有する複合材回転翼において、翼周縁部の少なく
ともシエル薄肉部に、シート自由端末部１′の構
成シート同士を複合材シエル１の硬化前に化学繊
維糸により縫合した縫合部５を設けたことに特徴
がある。
The rotor blade of the present invention has an airfoil-shaped composite material shell 1 formed by laminating synthetic resin-impregnated composite material sheets or by injecting synthetic resin into a fabric, and has a free end portion 1 of the component sheet at the periphery of the shell. In the composite rotor blade having a composite material rotor blade, a seam portion 5 is provided at least in the thin shell portion of the blade peripheral portion, in which the sheets constituting the sheet free end portion 1′ are sewn together with chemical fiber thread before the composite material shell 1 is cured. There are certain characteristics.
すなわち本考案は、前出第１図に示す複合材シ
エル１のシート自由端末部１′における構成シー
ト同士を、とくに層間剥離をおこし易い薄肉部に
おいて、引張に強い繊維糸、例えばケブラー（ア
ラミド繊維）糸等で縫い合わせるというもので、
この縫合により、使用時に働く前断力により複合
材シエル１の構成シートが自由端末部１′から層
間剥離を生じるのを確実に阻止でき、比強度の高
い複合材の特徴を有効に活用することが可能とな
る。
That is, the present invention connects the constituent sheets in the sheet free end portion 1' of the composite material shell 1 shown in FIG. ) It is sewn together with thread, etc.
By this suturing, it is possible to reliably prevent delamination of the constituent sheets of the composite material shell 1 from the free end portion 1' due to the front shearing force acting during use, and to effectively utilize the characteristics of the composite material with high specific strength. becomes possible.
また本考案は、実施に当たり特別なシート構造
や特殊技能を必要とせず、コスト、工数的に有利
で実用性があるのみならず、シエルの翼型に影響
せず、効率のよい本来のシエル形状を維持でき
る。 In addition, this invention does not require a special seat structure or special skills to implement, and is not only advantageous and practical in terms of cost and man-hours, but also does not affect the airfoil shape of the shell and maintains the original shell shape, which is efficient. can be maintained.
以下、本考案回転翼を、第１図の回転翼をベー
スとしたものについて更に具体的かつ詳細に説明
する。
Hereinafter, the rotor blade of the present invention, which is based on the rotor blade shown in FIG. 1, will be explained more specifically and in detail.
本考案回転翼は、基本的には翼桁２と、充填材
３で構成される芯材４と、この周囲を覆う複合材
シエル１とからなり、この基本構造についてまず
述べる。 The rotor blade of the present invention basically consists of a wing spar 2, a core material 4 made of a filler material 3, and a composite shell 1 that covers the periphery of the core material 4. First, the basic structure will be described.
翼桁２は、複合材シエル１内長手方向に配置さ
れ、材料はアルミニウムやチタン等の金属材料あ
るいは炭素繊維強化プラスチツク（以下CFRPと
称す）等が使用される。 The wing spar 2 is disposed in the longitudinal direction within the composite shell 1, and is made of a metal material such as aluminum or titanium, or carbon fiber reinforced plastic (hereinafter referred to as CFRP).
充填材３は、前記翼桁２の前後に設けられ、翼
桁２と複合材シエル１とで形成される空間を満た
すもので、化学繊維製またはアルミニウム製ハニ
カム構造体が好ましいが、ハニカム構造体の代替
品として発泡プラスチツクを使用してもよい。こ
の充填材４は、翼桁２に接着材で取付けられる。 The filler 3 is provided before and after the wing spar 2 to fill the space formed by the wing spar 2 and the composite shell 1, and is preferably a honeycomb structure made of chemical fiber or aluminum, but a honeycomb structure Foamed plastic may be used as an alternative. This filler 4 is attached to the wing spar 2 with an adhesive.
複合材シエル１は、ケブラー繊維のプリプレグ
シートや炭素繊維のプリプレグシートを複数枚積
層して形成するか、または化学繊維で織つた織物
を用いこれにあとから合成樹脂をインジエクトし
て形成する。前者のものについて一例を挙げれ
ば、まずケブラー繊維のプリプレグシートを置
き、次に炭素繊維のプリプレグシートを７〜８枚
積層する。このようなシエル１は、先に述べたと
おり腹側１０と背側１１に分けて構成される。 The composite shell 1 is formed by laminating a plurality of Kevlar fiber prepreg sheets or carbon fiber prepreg sheets, or by injecting a synthetic resin into the woven fabric using chemical fibers. To give an example of the former method, first a Kevlar fiber prepreg sheet is placed, and then seven to eight carbon fiber prepreg sheets are laminated. Such a shell 1 is divided into a ventral side 10 and a dorsal side 11 as described above.
複合材シエル１は、芯材４の両面側に上記のよ
うにシエル体を構成し、これを型に入れて加熱す
ること（硬化成型）により、プリプレグシート
（あるいは織物）に含浸した合成樹脂を繊維間に
流動させ各合わせ面を接合して一体化させる。 The composite shell 1 is formed by forming shell bodies on both sides of the core material 4 as described above, and by placing the shell bodies in a mold and heating them (hardening molding), a prepreg sheet is formed.
Synthetic resin impregnated into (or woven fabric) is made to flow between the fibers to join and integrate each mating surface.
基本構造は以上のようなものであるが、ここで
本考案の回転翼の特徴は、上記複合材シエル１の
前後縁１ａ，１ｂ及び翼端部１ｃの薄肉部を第２
図に示す如く化学繊維の糸で縫合した（縫合部：
符号５）点である。図示例においては、前縁１ａ
の基端側の一部１a′が縫合されていないが、この
部分は厚肉部であり、ここを起点に複合材シエル
の構成シートが層間剥離をおこすことはほとんど
なく、同部の補強はとくに必要でない。またこの
例では、前後縁とともに、翼端部１ｃにも縫合部
５を設け、層間剥離の確実な防止を図つている。 Although the basic structure is as described above, the feature of the rotor blade of the present invention is that the thin-walled portions of the front and rear edges 1a, 1b and the blade tip 1c of the composite shell 1 are
It was sutured with chemical fiber thread as shown in the figure (sutured part:
It is a point 5). In the illustrated example, the leading edge 1a
Although a part 1a' on the proximal end side of the shell is not sutured, this part is a thick part, and delamination of the constituent sheets of the composite shell is unlikely to occur from this part, so reinforcing this part is not necessary. Not particularly necessary. Further, in this example, a seam portion 5 is provided not only at the front and rear edges but also at the wing tip portion 1c to reliably prevent delamination.
縫合する糸は、引張に対し強い化学繊維糸であ
れば何れでもよいが、とくにケブラー糸の使用が
望ましい。 The suture thread may be any chemical fiber thread that is strong against tension, but it is particularly desirable to use Kevlar thread.
縫合の仕方としては、チエイン・ステツチが好
ましく、これによると腹側、背側のシエルを２本
の糸で縫い付けることができ、丈夫な縫合部５が
得られる。 As for the suturing method, a chain stitch is preferable. According to this method, the ventral and dorsal shells can be sewn with two threads, and a strong sutured portion 5 can be obtained.
当然のことながら縫合は、複合材シエル１の成
型硬化の前に行つておくものである。成型硬化の
工程により、その縫合部５は、シートの含浸樹脂
によりシエル外面に一体化した形となる。 Naturally, the suturing is performed before the composite shell 1 is molded and hardened. Through the molding and curing process, the stitched portion 5 becomes integrated with the outer surface of the shell due to the impregnated resin of the sheet.
以上に説明したように本考案の複合材回転翼
は、周縁に構成シートの自由端末部を有する複合
材シエルの前後縁及び翼端部等の薄肉部を化学繊
維糸で縫合、補強した構造をもつから、使用時に
おける自由端末部からの構成シートの隙間剥離を
確実に防止できる。しかも、その縫合部は、特殊
な材料や技能を必要とせず、簡単な工程の追加で
構成可能であり、また、シエル硬化前の縫合によ
り翼表面を凹凸のない滑らかな形状にする。した
がつて、本考案は、周縁に構成シートの自由端末
部を有する回転翼の品質、耐久性の向上策として
実用的価値がきわめて大きい。
As explained above, the composite rotor blade of the present invention has a structure in which the thin parts such as the front and rear edges and wing tips of the composite shell, which has the free ends of the constituent sheets at the periphery, are sewn and reinforced with chemical fiber yarn. Therefore, it is possible to reliably prevent the component sheet from peeling off from the free end portion during use. Furthermore, the sutured portion does not require any special materials or skills, and can be constructed by adding a simple process, and the blade surface can be made into a smooth shape without irregularities by suturing before the shell hardens. Therefore, the present invention has extremely great practical value as a measure to improve the quality and durability of a rotor blade having a free end portion of a constituent sheet at its periphery.
第１図は複合材回転翼の一般的構造を示す断面
斜視図、第２図は本考案回転翼の縫合構造を示す
平面図である。
１……複合材シエル、２……翼桁、３……充填
材、４……芯材、５……縫合部。
FIG. 1 is a cross-sectional perspective view showing the general structure of a composite rotor blade, and FIG. 2 is a plan view showing the stitched structure of the rotor blade of the present invention. 1... Composite shell, 2... Wing spar, 3... Filling material, 4... Core material, 5... Sewing portion.
Claims (1)
は織物に合成樹脂をインジエクシヨンして形成し
た翼型の複合材シエル１を有し、且つ、シエル周
縁に構成シートの自由端末部１′を有する複合材
回転翼において、翼周縁部の少なくともシエル薄
肉部に、シート自由端末部１′の構成シート同士
を複合材シエル１の硬化前に化学繊維糸により縫
合した縫合部５を設けたことを特徴とする複合材
回転翼。 A composite material having an airfoil-shaped composite material shell 1 formed by laminating synthetic resin-impregnated composite material sheets or by injecting a synthetic resin into a fabric, and having a free end portion 1' of the constituent sheet at the periphery of the shell. The rotary blade is characterized in that a seam 5 is provided at least in the thin shell part of the blade peripheral area, in which the sheets constituting the sheet free end part 1' are sewn together with a chemical fiber thread before the composite shell 1 hardens. Composite rotor blade.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| JP1986090863U JPH0357600Y2 (en) | 1986-06-13 | 1986-06-13 |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| JP1986090863U JPH0357600Y2 (en) | 1986-06-13 | 1986-06-13 |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| JPS62201200U JPS62201200U (en) | 1987-12-22 |
| JPH0357600Y2 true JPH0357600Y2 (en) | 1991-12-27 |
Family
ID=30951122
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| JP1986090863U Expired JPH0357600Y2 (en) | 1986-06-13 | 1986-06-13 |
Country Status (1)
| Country | Link |
|---|---|
| JP (1) | JPH0357600Y2 (en) |
Families Citing this family (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US10414487B2 (en) * | 2013-07-08 | 2019-09-17 | Safran Aircraft Engines | Composite propeller blade for an aircraft |
Citations (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPS584679A (en) * | 1981-04-08 | 1983-01-11 | シユウイン・バイシクル・コンパニ− | Regulator for rear carrier of bicycle |
-
1986
- 1986-06-13 JP JP1986090863U patent/JPH0357600Y2/ja not_active Expired
Patent Citations (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPS584679A (en) * | 1981-04-08 | 1983-01-11 | シユウイン・バイシクル・コンパニ− | Regulator for rear carrier of bicycle |
Also Published As
| Publication number | Publication date |
|---|---|
| JPS62201200U (en) | 1987-12-22 |
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