JPH01198329A - Manufacture of aerofoil of rotor blade twisted in three dimension - Google Patents
Manufacture of aerofoil of rotor blade twisted in three dimensionInfo
- Publication number
- JPH01198329A JPH01198329A JP63306790A JP30679088A JPH01198329A JP H01198329 A JPH01198329 A JP H01198329A JP 63306790 A JP63306790 A JP 63306790A JP 30679088 A JP30679088 A JP 30679088A JP H01198329 A JPH01198329 A JP H01198329A
- Authority
- JP
- Japan
- Prior art keywords
- fiber
- rotor blade
- airfoil
- strands
- fibers
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Pending
Links
- 238000004519 manufacturing process Methods 0.000 title claims description 14
- 239000000835 fiber Substances 0.000 claims abstract description 70
- 239000011159 matrix material Substances 0.000 claims abstract description 17
- 238000003825 pressing Methods 0.000 claims abstract description 6
- 239000011347 resin Substances 0.000 claims abstract description 5
- 229920005989 resin Polymers 0.000 claims abstract description 5
- 238000000034 method Methods 0.000 claims description 6
- 239000002657 fibrous material Substances 0.000 claims description 3
- 238000005303 weighing Methods 0.000 abstract 1
- 239000000463 material Substances 0.000 description 6
- 238000005516 engineering process Methods 0.000 description 3
- 239000004753 textile Substances 0.000 description 3
- 230000008901 benefit Effects 0.000 description 2
- 230000000694 effects Effects 0.000 description 2
- 238000003860 storage Methods 0.000 description 2
- PWKSKIMOESPYIA-BYPYZUCNSA-N L-N-acetyl-Cysteine Chemical compound CC(=O)N[C@@H](CS)C(O)=O PWKSKIMOESPYIA-BYPYZUCNSA-N 0.000 description 1
- 230000005540 biological transmission Effects 0.000 description 1
- 239000002131 composite material Substances 0.000 description 1
- 238000007796 conventional method Methods 0.000 description 1
- 238000013016 damping Methods 0.000 description 1
- 239000011094 fiberboard Substances 0.000 description 1
- 239000011888 foil Substances 0.000 description 1
- 239000000499 gel Substances 0.000 description 1
- 210000003127 knee Anatomy 0.000 description 1
- TYZROVQLWOKYKF-ZDUSSCGKSA-N linezolid Chemical compound O=C1O[C@@H](CNC(=O)C)CN1C(C=C1F)=CC=C1N1CCOCC1 TYZROVQLWOKYKF-ZDUSSCGKSA-N 0.000 description 1
- 229960003907 linezolid Drugs 0.000 description 1
- 239000007769 metal material Substances 0.000 description 1
- 239000000203 mixture Substances 0.000 description 1
- 239000011265 semifinished product Substances 0.000 description 1
- 238000004804 winding Methods 0.000 description 1
- 210000000707 wrist Anatomy 0.000 description 1
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C11/00—Propellers, e.g. of ducted type; Features common to propellers and rotors for rotorcraft
- B64C11/16—Blades
- B64C11/20—Constructional features
- B64C11/26—Fabricated blades
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
- B29C—SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
- B29C35/00—Heating, cooling or curing, e.g. crosslinking or vulcanising; Apparatus therefor
- B29C35/02—Heating or curing, e.g. crosslinking or vulcanizing during moulding, e.g. in a mould
- B29C35/08—Heating or curing, e.g. crosslinking or vulcanizing during moulding, e.g. in a mould by wave energy or particle radiation
- B29C35/10—Heating or curing, e.g. crosslinking or vulcanizing during moulding, e.g. in a mould by wave energy or particle radiation for articles of indefinite length
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
- B29C—SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
- B29C53/00—Shaping by bending, folding, twisting, straightening or flattening; Apparatus therefor
- B29C53/56—Winding and joining, e.g. winding spirally
- B29C53/566—Winding and joining, e.g. winding spirally for making tubular articles followed by compression
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
- B29C—SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
- B29C53/00—Shaping by bending, folding, twisting, straightening or flattening; Apparatus therefor
- B29C53/80—Component parts, details or accessories; Auxiliary operations
- B29C53/84—Heating or cooling
- B29C53/845—Heating or cooling especially adapted for winding and joining
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
- B29C—SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
- B29C70/00—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts
- B29C70/04—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts comprising reinforcements only, e.g. self-reinforcing plastics
- B29C70/28—Shaping operations therefor
- B29C70/30—Shaping by lay-up, i.e. applying fibres, tape or broadsheet on a mould, former or core; Shaping by spray-up, i.e. spraying of fibres on a mould, former or core
- B29C70/38—Automated lay-up, e.g. using robots, laying filaments according to predetermined patterns
- B29C70/382—Automated fiber placement [AFP]
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
- B29D—PRODUCING PARTICULAR ARTICLES FROM PLASTICS OR FROM SUBSTANCES IN A PLASTIC STATE
- B29D99/00—Subject matter not provided for in other groups of this subclass
- B29D99/0025—Producing blades or the like, e.g. blades for turbines, propellers, or wings
- B29D99/0028—Producing blades or the like, e.g. blades for turbines, propellers, or wings hollow blades
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
- B29C—SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
- B29C35/00—Heating, cooling or curing, e.g. crosslinking or vulcanising; Apparatus therefor
- B29C35/02—Heating or curing, e.g. crosslinking or vulcanizing during moulding, e.g. in a mould
- B29C35/08—Heating or curing, e.g. crosslinking or vulcanizing during moulding, e.g. in a mould by wave energy or particle radiation
- B29C35/0805—Heating or curing, e.g. crosslinking or vulcanizing during moulding, e.g. in a mould by wave energy or particle radiation using electromagnetic radiation
- B29C2035/0822—Heating or curing, e.g. crosslinking or vulcanizing during moulding, e.g. in a mould by wave energy or particle radiation using electromagnetic radiation using IR radiation
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
- B29L—INDEXING SCHEME ASSOCIATED WITH SUBCLASS B29C, RELATING TO PARTICULAR ARTICLES
- B29L2031/00—Other particular articles
- B29L2031/08—Blades for rotors, stators, fans, turbines or the like, e.g. screw propellers
-
- 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
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T50/00—Aeronautics or air transport
- Y02T50/60—Efficient propulsion technologies, e.g. for aircraft
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Aviation & Aerospace Engineering (AREA)
- Health & Medical Sciences (AREA)
- Toxicology (AREA)
- Physics & Mathematics (AREA)
- Oral & Maxillofacial Surgery (AREA)
- Thermal Sciences (AREA)
- Robotics (AREA)
- Chemical & Material Sciences (AREA)
- Composite Materials (AREA)
- Moulding By Coating Moulds (AREA)
Abstract
Description
【発明の詳細な説明】
〔産業上の利用分野〕
本発明は、樹脂含浸繊維材料でコアを包む ことによっ
て立体的に捻じられたロータブレードのエーロフオイル
を製造する方法に関する。DETAILED DESCRIPTION OF THE INVENTION [Industrial Field of Application] The present invention relates to a method for producing an airfoil for a three-dimensionally twisted rotor blade by wrapping the core with a resin-impregnated fibrous material.
繊維技術の構成部材は、その優れた特性に基づいて、ま
ずます優れた技術的な意義を得つつある。Components of textile technology are gaining ever greater technical significance due to their excellent properties.
その低い密度、高い引張強度及び比較的容易な造形（Ｆ
ｏｒｍｇｅｓｔａｌｔｕｎｇ）以前は金属材料に留保さ
れた頭載にまで繊維材料の利用が進むことを可能にする
。それ故、繊維強化材料航空機に適用されるに到ってお
り、特に動的に高度に負荷されるブレードのニーフォイ
ル及びプロペラ又はプロプファンのエーロフオイルに適
用されるに至る。Its low density, high tensile strength and relatively easy fabrication (F
(orngestaltung) allows the use of textile materials to advance to a level previously reserved for metallic materials. Therefore, fiber-reinforced materials have found application in aircraft, in particular in the knee foils of blades and in the airfoils of propellers or propfans, which are subjected to high dynamic loads.
繊維強化材料の別の優れた特性は、好ましい方向に繊維
を配置することによって構成部材の特性に影響を及ぼし
、それ故異なる方向で例えば弾性係数或いは減衰定数に
ついての材料データを得る可能性があることである。Another advantageous property of fiber-reinforced materials is the possibility of influencing the properties of the component by arranging the fibers in a preferred direction and thus obtaining material data, for example on the elastic modulus or damping constant, in different directions. That's true.
しかし、表面が立体的に捻しられており、特に部分的に
凹部に形成されており、異なる方向で種々の強さ及び振
動特性が要求される繊維強化材料製の複合化された成形
された構成部材は技術的に疑わしい。これは特に最近の
ターボエンジンのファン或いはプロプファンのブレート
について見られ、ブレードのエーロフオイルをブレード
の根部乃至はロータに取り付けることは別の特別な問題
を提出する。However, composite molded materials made of fiber-reinforced materials whose surfaces are three-dimensionally twisted, in particular partially recessed, and which require different strength and vibration properties in different directions, The components are technically questionable. This is particularly the case with modern turbo engine fan or prop fan blades, where attaching the blade airfoil to the blade root or rotor presents another special problem.
このような構成部材の従来の装造は、高度の費消と結合
されており、この費消はまた高い製造コストに帰着する
。それは所謂プリプレグであり、マトリックス材料が化
含浸せしめられた繊維板が中空型内に移され、更に圧力
と温度によって硬化せしめられる。その場合、原理上可
能な構成部材の特性への意識的な影響が製造方法におい
て、非常に高い費消の下でのみ可能であることは不利で
ある。Conventional equipping of such components is associated with a high degree of consumption, which also results in high manufacturing costs. It is a so-called prepreg, in which a fiberboard impregnated with a matrix material is transferred into a hollow mold and further hardened by pressure and temperature. It is disadvantageous in this case that the conscious influence on the properties of the component, which is possible in principle, is only possible in the manufacturing process at very high consumption.
本発明の課題は簡単に且つ迅速に製造することを可能に
し、目的とする繊維の配置によって目的とする構成部材
の特性を手際よく扱うことが出来る、立体的に捻じられ
たロータブレードエーロフオイルを製造する方法を提供
することである。The object of the present invention is to provide a three-dimensionally twisted rotor blade airfoil that can be manufactured simply and quickly, and that allows the desired properties of the component to be easily controlled by the desired fiber arrangement. An object of the present invention is to provide a method for manufacturing.
〔課題を解決するための手段及びその作用〕この課題は
、本発明に従って樹脂含浸繊維材料でコアｒＬを包むこ
とによって立体的に捻じられたロータブレードエーロフ
オイルを製造する方法において、樹脂７１へリソクスが
含浸せしめられた繊維ストランド９が繊維押さえロール
１１でコア１に押しく−Ｊげられ、繊維押さえロール１
１に連結されたプリキュア装置１５が押し付け後直ちに
樹脂マトリックスを硬化することを特徴とする立体的に
捻じられたロータプレートエーロフオイルの製造方法に
よって解決される。[Means for Solving the Problems and Their Effects] This problem is solved by the method of manufacturing a three-dimensionally twisted rotor blade airfoil by wrapping the core rL with a resin-impregnated fiber material according to the present invention. The fiber strand 9 impregnated with Lysox is pushed onto the core 1 by the fiber presser roll 11, and the fiber strand 9 is pushed onto the core 1 by the fiber presser roll 11.
The present invention is solved by a method for manufacturing a three-dimensionally twisted rotor plate airfoil, which is characterized in that a precure device 15 connected to a precure device 15 immediately cures the resin matrix after pressing.
本発明において、プリキュア装置１５が赤外線照射装置
として形成されている。In the present invention, the precure device 15 is formed as an infrared irradiation device.
本発明において、繊維ストランド９が繊維押さえロール
１１を用いて繊維供給導管１２を通して引っ張られ、該
繊維供給導管１２においてマトリックス材料が繊維スト
ランドに供給される。In the present invention, the fiber strand 9 is pulled using a fiber presser roll 11 through a fiber feed conduit 12 in which matrix material is fed to the fiber strand.
本発明による方法は、任意の成形されたロータブレード
のエーロフオイル上に簡単な方法で各方向に繊維を配置
し、そこで保って押さえ、すべって位置が変わることが
決して無いと云う利益をもたらす。The method according to the invention provides the advantage that the fibers can be placed in a simple manner in each direction on the airfoil of any shaped rotor blade and held there and held down so that they never slip and change position.
硬化後繊維は凹面に成形された面上にも接着して留まり
、それ故正確なしかも迅速な繊維の配置が補償される。After curing, the fibers also remain adhered to the concavely shaped surface, thus ensuring accurate and rapid fiber placement.
必要に応じて異なる方向或いは同方向で多数の繊維層を
重ねて取り付けることが出来る。プリキュア装置１５は
、その位置で繊維は固着されるが、繊維７トリソクス混
合物は硬化されないようにマトリックス材料をゲル化す
る。更に巻かれた構成部材は仕上げ寸法に型内で圧縮さ
れ、炉内で硬化せしめられる。Multiple fiber layers can be applied one on top of the other in different directions or in the same direction as desired. The precure device 15 gels the matrix material so that the fibers are fixed in place but the fiber 7 trisox mixture is not cured. The rolled component is then compressed to the finished size in a mold and hardened in an oven.
更に繊維技術の捻じられた構成部材の製造に必要な時間
は従来の方法に比して著しく短縮される。Furthermore, the time required to produce twisted components of textile technology is significantly reduced compared to conventional methods.
さらに本質的なことは、凹面に成形されたブレードを簡
単にしかも正確に繊維の層で覆うことが出来、このこと
は従来の繊維の取り付け方法では満足になしえなかった
ことである。What is also essential is that the concavely shaped blade can be simply and accurately covered with a layer of fibers, which could not be achieved satisfactorily with conventional fiber attachment methods.
それ故有利に巻き付け方法の著しい簡単化がもタラされ
、完全自動化されたコンピュータ及びロボット制御され
た製造の実施に適している。Advantageously, therefore, a significant simplification of the winding method is also achieved, making it suitable for fully automated, computer- and robot-controlled production implementations.
繊維ストランド９は有利に選ばれた軌道に沿って敷設す
ることが出来る。これによって、異方性の構成部材の構
造を得ることが出来、安定性と強度に恵まれた配置を造
ることが出来る。これによって、特に困難な問題を解消
することが出来る。The fiber strands 9 can be laid along an advantageously chosen trajectory. This makes it possible to obtain an anisotropic component structure and to create an arrangement that is endowed with stability and strength. This allows particularly difficult problems to be solved.
本発明の有利な形成において、ロータブレードのエーロ
フオイルをブレードの相部６に固定するために繊維スト
ランド、多数のブレードの根部６に設けられた保持用節
部５に巻きイ」けられる。これによって、駆動中に作用
する遠心力のブレードの根部６への特に有利な伝達が生
ずることを可能にする。In an advantageous embodiment of the invention, fiber strands are wound around retaining knots 5 provided at the roots 6 of a number of blades in order to fix the airfoil of the rotor blades on the phase 6 of the blades. This makes it possible for a particularly advantageous transmission of the centrifugal forces acting during the drive to the blade root 6 to occur.
本発明を添付の図面に照らして詳細に説明する。 The invention will be explained in detail in the light of the accompanying drawings.
図面において、第１図はファンのブレードを例示する斜
視口、第２図は繊維を敷設する装置を例示する斜視図、
第３図は太軸門形ロボット（ｓｉｘ−示されている。第
１図には配置されるべき繊維の好ましい方向：主引張方
向２及び斜め方向の層３及び４が描写されている。繊維
は好ましくはブレードの根部６上に設けられている複数
の保持用節部（Ｉｌａｌｔｅｎｏｐｐｅｎ） ５に括り
つけられている。これによって二つの部分間の良好な結
合が達成され、また駆動中にブレードに生ずる引張力が
ブレードの根部６に良好に導かれる。In the drawings, FIG. 1 is a perspective view illustrating a fan blade, FIG. 2 is a perspective view illustrating a fiber laying device,
FIG. 3 shows a thick-axis portal robot (six-). FIG. 1 depicts the preferred direction of the fibers to be placed: the main tension direction 2 and the diagonal layers 3 and 4. Fibers are preferably fastened to a plurality of retaining joints 5 which are provided on the blade root 6. This achieves a good connection between the two parts and also ensures that the blade does not hold during the drive. The resulting tensile forces are better guided to the root 6 of the blade.
第２図に繊維を敷設する装置８が図示されており、この
装置は本質的に繊維リール１０、繊維供給導管１２、繊
維押さえロール１１ （Ｆａｓｅｒａｎｄｒｊｃｋｒｏ
ｌｌｅ）及びプリキュア装置１５からなる。繊維リール
１０から巻き出された繊維ストランド（Ｆａｓｅｒｓｔ
ｒａｎｇ） ９は、繊維供給導管１２を通して繊維押さ
えロール１１によって引っ張られ、同時に繊維供給導管
１２において□はマトリックス（Ｍａｔｒｉｘ）材料が
７１〜リノクス計量装置１４からマトリックス供給装置
１３を通して繊維ストランド９に一定量で供給される。FIG. 2 shows a device 8 for laying fibers, which essentially consists of a fiber reel 10, a fiber supply conduit 12, a fiber presser roll 11
lle) and the Precure device 15. The fiber strand (Fasrst) unwound from the fiber reel 10
Rang) 9 is pulled by the fiber pressing roll 11 through the fiber supply conduit 12, and at the same time, in the fiber supply conduit 12, □ is a matrix material 71~Linox metering device 14 passes through the matrix supply device 13 to the fiber strand 9 in a constant amount. Supplied by
マトリックス材料は、貯蔵容器１６からフレキシブルな
供給管路１７を通してマトリックス計量装置１４に供給
される。そのとき、繊維の単位長当たり供給されるマト
リックスの容量は、好ましくは、繊維の送り速度（Ｆａ
ｓｅｒｄｕｒｃｈｓａｔｚ）に適合するように調整され
る。そのように濡らされた繊維は、構成部材のコアｌｌ
１ｌＬ上の上記した進路に正確に配置され、プリキュア
装置１５によってプリキュアされ（ゲル化され）、表面
が乾かされる。このようにして繊維が湾曲した軌道（Ｂ
ａｈｎ）に配置されるように固定される。プリキュアさ
れた繊維の上に更に別の繊維層が任意の方向に配置され
る。Matrix material is supplied from storage container 16 through flexible supply line 17 to matrix metering device 14 . The capacity of matrix fed per unit length of fiber is then preferably determined by the fiber feed rate (Fa
serdurchsatz). The fibers so wetted are then exposed to the core of the component.
It is precisely placed in the above-mentioned path on 1 liter, is precure (gelled) by the precure device 15, and the surface is dried. In this way, the fiber curved trajectory (B
ahn). Further fiber layers are placed on top of the precure fibers in any direction.
第３図に示されているように、ここで模式的に図示され
ている繊維を敷設する装置８は太軸門形ロボット７の手
首（Ｈａｎｄｇｅｌｅｎｋ）に結合されており、このよ
うにしてコンピュータ制御の下で予め計算された軌道に
沿って完全に自動的に構成部材のコア上に繊維ストラン
ド９を敷設することが出来る。これによって繊維の敷設
の非常に正確な再現（＜Ｑ、２ｍｍ）を達成することが
出来る。As shown in FIG. 3, the device 8 for laying the fibers, here schematically illustrated, is connected to the wrist of a wide-axis portal robot 7 and is thus computer-controlled. It is possible to lay the fiber strands 9 on the core of the component completely automatically along the pre-calculated trajectory under. This makes it possible to achieve a very accurate reproduction of the fiber laying (<Q, 2 mm).
このように作られた半製品（Ｒｏｈｔｅｉｌ）が完全に
巻かれた後、更にそれは型内に運ばれ、圧力及び温度に
よって通常の方法で硬化せしめられる。After the semi-finished product produced in this way has been completely rolled up, it is further conveyed into molds and hardened in the usual manner under pressure and temperature.
上述のように本発明によれば、任意の成形されたロータ
ブレードのエーロフオイル上に簡単な方法で各方向に繊
維を配置し、そこで保って押さえ、すべって位置が変わ
ることが決して無いという利益をもたらすものである。As mentioned above, according to the present invention, the fibers can be placed in a simple manner in each direction on the airfoil of any shaped rotor blade and held there, with the benefit of never slipping and changing position. It is something that brings.
第１図はファンのブレードを例示する斜視図、第２図は
繊維を敷設する装置を例示する斜視図、第３図は、六輪
門形ロボット（ｓｉｘ−ａｘｉｓ ｐｏｒｔａｌｒｏｂ
ｏｔ ）を例示する斜視図である。
１・・・・・・ロータブレードのエーロフオイル、２・
・・・・・主引張方向、３．４・・・・・・斜め方向の
層、５・・・・・・保持用節部、６・・・・・・ブレー
ドの根部、７・・・・・・太軸門形ロボット、８・・・
・・・繊維を敷設する装置、９・・・・・・繊維ストラ
ンド、１０・・・・・・繊維リール、１１・・・・・・
繊維押さえロール、１２・・・・・・繊維供給導管、１
３・・・・・・マトリックス供給装置、１４・・・・・
・７トリソクス計量装置、１５・・・・・・プリキュア
装置、１６・・・・・・貯蔵容器、１７・・・・・・フ
レキシブルな供給管路、１ル −コア。FIG. 1 is a perspective view illustrating fan blades, FIG. 2 is a perspective view illustrating a fiber laying device, and FIG. 3 is a six-axis portal robot.
ot) is a perspective view illustrating an example. 1... Aerof oil for rotor blades, 2.
...Main tensile direction, 3.4 ... Diagonal layer, 5 ... Holding knot, 6 ... Root of blade, 7 ... ...Thick-axis gate-shaped robot, 8...
... Fiber laying device, 9... Fiber strand, 10... Fiber reel, 11...
Fiber presser roll, 12...Fiber supply conduit, 1
3... Matrix supply device, 14...
・7 Trisox metering device, 15...Precure device, 16...Storage container, 17...Flexible supply conduit, 1 Lu-core.
Claims (4)
的に捻じられたロータブレードエーロフォイルを製造す
る方法において、樹脂マトリックスが含浸せしめられた
繊維ストランドが繊維押さえロール１１でコアに押し付
けられ、繊維押さえロール１１に連結されたプリキュア
装置１５が押し付け後直ちに樹脂マトリックスを硬化す
ることを特徴とする立体的に捻じられたロータブレード
のエーロフォイルの製造方法。(1) In a method of manufacturing a three-dimensionally twisted rotor blade airfoil by wrapping a core with a resin-impregnated fiber material, a fiber strand impregnated with a resin matrix is pressed against the core with a fiber presser roll 11, and the fiber A method for manufacturing an airfoil of a three-dimensionally twisted rotor blade, characterized in that a precure device 15 connected to a presser roll 11 cures the resin matrix immediately after pressing.
部６に固定するために繊維ストランド、多数のブレード
の根部６に設けられた保持用節部５に巻き付けられるこ
とを特徴とする請求項１に記載の立体的に捻じられたロ
ータブレードのエーロフォイルの製造方法。(2) A fiber strand is wound around a retaining knurl 5 provided in a plurality of blade roots 6 to secure the airfoil of the rotor blade to the blade root 6. A method of manufacturing a three-dimensionally twisted rotor blade airfoil.
ていることを特徴とする請求項１に記載の立体的に捻じ
られたロータブレードのエーロフォイルの製造方法。3. A method for producing an airfoil of a three-dimensionally twisted rotor blade according to claim 1, characterized in that the precure device is configured as an infrared irradiation device.
繊維供給導管を通して引っ張られ、該繊維供給導管にお
いてマトリックス材料が繊維ストランドに供給されるこ
とを特徴とする請求項１乃至３の何れか一つの請求項に
記載の立体的に捻じられたロータブレードのエーロフォ
イルの製造方法。(4) The fiber strand is pulled through a fiber supply conduit using a fiber presser roll 11, in which the matrix material is supplied to the fiber strand. A method of manufacturing a three-dimensionally twisted rotor blade airfoil as described in paragraphs.
Applications Claiming Priority (2)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| DE3743485.3 | 1987-12-22 | ||
| DE19873743485 DE3743485A1 (en) | 1987-12-22 | 1987-12-22 | METHOD FOR PRODUCING A SPACIOUSLY WINDED ROTOR BLADE |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| JPH01198329A true JPH01198329A (en) | 1989-08-09 |
Family
ID=6343233
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| JP63306790A Pending JPH01198329A (en) | 1987-12-22 | 1988-12-02 | Manufacture of aerofoil of rotor blade twisted in three dimension |
Country Status (5)
| Country | Link |
|---|---|
| JP (1) | JPH01198329A (en) |
| DE (1) | DE3743485A1 (en) |
| FR (1) | FR2624786A1 (en) |
| GB (1) | GB2213793A (en) |
| IT (1) | IT1227931B (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JP2012006400A (en) * | 2005-03-03 | 2012-01-12 | Coriolis Composites | Fiber coating machine |
| JP2013240882A (en) * | 2011-02-23 | 2013-12-05 | Airbus Operations Ltd | Composite structural body |
Families Citing this family (26)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| DE4002087A1 (en) * | 1990-01-25 | 1991-08-08 | Messerschmitt Boelkow Blohm | DEPOSING FIBER TAPES ON DOUBLE-CURVED BODIES OR SURFACES |
| US5273602A (en) * | 1990-12-19 | 1993-12-28 | Hercules Incorporated | Ribbonizing method for selectively heating a respective one of a plurality of fiber tows |
| EP0534092B1 (en) * | 1991-07-31 | 1996-09-18 | Hercules Incorporated | Cure-on-the-fly system |
| GB2269800B (en) * | 1992-08-22 | 1995-10-11 | Ferodo Caernarfon Ltd | Fabrication of friction elements |
| US5266139A (en) * | 1992-10-02 | 1993-11-30 | General Dynamics Corporation, Space Systems Division | Continuous processing/in-situ curing of incrementally applied resin matrix composite materials |
| FR2865156B1 (en) * | 2004-01-19 | 2006-11-10 | Dcmp | DEVICE FOR REMOVING FLOOR OR WIRES IN A MOLD FOR MANUFACTURING PARTS OF COMPOSITE MATERIALS |
| FR2878779B1 (en) | 2004-12-02 | 2007-02-09 | Eads Ccr Groupement D Interet | DEVICE FOR DRAPING PRE-IMPREGNATED FLEXIBLE BANDS |
| DE102006006337A1 (en) * | 2006-02-11 | 2007-08-16 | Kümpers GmbH & Co. KG | Spatial textile component structure on high-strength threads, as well as methods for their production |
| FR2912680B1 (en) | 2007-02-21 | 2009-04-24 | Coriolis Composites Sa | METHOD AND DEVICE FOR MANUFACTURING PARTS OF COMPOSITE MATERIAL, IN PARTICULAR AIRBORNE FUSELAGE STRINGS |
| FR2912953B1 (en) | 2007-02-28 | 2009-04-17 | Coriolis Composites Sa | FIBER APPLICATION MACHINE WITH FLEXIBLE FIBER DELIVERY TUBES |
| FR2913365B1 (en) | 2007-03-06 | 2013-07-26 | Coriolis Composites Attn Olivier Bouroullec | FIBER APPLICATION HEAD WITH PARTICULAR FIBER CUTTING SYSTEMS |
| WO2009156157A1 (en) * | 2008-06-25 | 2009-12-30 | Zsk Stickmaschinen Gmbh | Device and method for applying a band-shaped material |
| FR2943943A1 (en) | 2009-04-02 | 2010-10-08 | Coriolis Composites | METHOD AND MACHINE FOR APPLYING A FIBER BAND TO CONVEXED SURFACES AND / OR WITH AREES |
| FR2948058B1 (en) | 2009-07-17 | 2011-07-22 | Coriolis Composites | FIBER APPLICATION MACHINE COMPRISING A FLEXIBLE COMPACTION ROLL WITH THERMAL CONTROL SYSTEM |
| EP2404742A1 (en) * | 2010-07-09 | 2012-01-11 | Siemens Aktiengesellschaft | Method to manufacture a component of a composite structure |
| US9511543B2 (en) | 2012-08-29 | 2016-12-06 | Cc3D Llc | Method and apparatus for continuous composite three-dimensional printing |
| DE102013208471B4 (en) * | 2013-05-08 | 2015-08-20 | Deutsches Zentrum für Luft- und Raumfahrt e.V. | Method and device for producing a molded component |
| DE202014101350U1 (en) * | 2014-03-24 | 2015-03-26 | Deutsches Zentrum für Luft- und Raumfahrt e.V. | fiber feeding |
| FR3034338B1 (en) | 2015-04-01 | 2017-04-21 | Coriolis Composites | FIBER APPLICATION HEAD WITH PARTICULAR APPLICATION ROLLER |
| DE102015215669A1 (en) * | 2015-08-18 | 2017-02-23 | Bayerische Motoren Werke Aktiengesellschaft | Method for producing a fiber composite component by means of impregnated fiber rovings |
| FR3043010B1 (en) | 2015-10-28 | 2017-10-27 | Coriolis Composites | FIBER APPLICATION MACHINE WITH PARTICULAR CUTTING SYSTEMS |
| WO2017090551A1 (en) * | 2015-11-25 | 2017-06-01 | 株式会社Adeka | Molding machine, production method, and fiber-reinforced resin material |
| FR3048373B1 (en) | 2016-03-07 | 2018-05-18 | Coriolis Group | PROCESS FOR MAKING PREFORMS WITH APPLICATION OF A BINDER ON DRY FIBER AND CORRESPONDING MACHINE |
| FR3056438B1 (en) | 2016-09-27 | 2019-11-01 | Coriolis Group | METHOD FOR PRODUCING COMPOSITE MATERIAL PARTS BY IMPREGNATING A PARTICULAR PREFORM |
| US10865769B2 (en) * | 2017-11-21 | 2020-12-15 | General Electric Company | Methods for manufacturing wind turbine rotor blade panels having printed grid structures |
| US11926099B2 (en) | 2021-04-27 | 2024-03-12 | Continuous Composites Inc. | Additive manufacturing system |
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| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| IL26368A (en) * | 1965-09-08 | 1970-02-19 | Balzaretti Modigliani Spa | Continuous production of a fibrous tubular structure |
| DE1619039A1 (en) * | 1966-01-19 | 1969-09-18 | Ferro Corp | Resin-impregnated fiberglass composition and process for making the same |
| DE2421619C3 (en) * | 1974-05-04 | 1982-07-08 | Stiebel Eltron Gmbh & Co Kg, 3450 Holzminden | Process for producing a glass fiber reinforced plastic molded part and device for carrying out the process |
| US4170505A (en) * | 1976-09-24 | 1979-10-09 | General Electric Company | Method for making and applying irradiation curable glass banding |
| ZA827460B (en) * | 1981-12-28 | 1983-08-31 | United Technologies Corp | Method of manufacturing a filament wound article |
| DE3211417C2 (en) * | 1982-03-27 | 1986-12-18 | Uranit GmbH, 5170 Jülich | Device for producing cross-wound layers for fiber-reinforced, rotationally symmetrical wound bodies |
| JPS63112142A (en) * | 1986-10-28 | 1988-05-17 | フイリツプス ピトロ−リアム カンパニ− | Method and device for manufacturing thermoplastic structure |
-
1987
- 1987-12-22 DE DE19873743485 patent/DE3743485A1/en not_active Withdrawn
-
1988
- 1988-11-10 GB GB8826325A patent/GB2213793A/en not_active Withdrawn
- 1988-11-25 IT IT8822738A patent/IT1227931B/en active
- 1988-12-02 JP JP63306790A patent/JPH01198329A/en active Pending
- 1988-12-21 FR FR8816925A patent/FR2624786A1/en not_active Withdrawn
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JP2012006400A (en) * | 2005-03-03 | 2012-01-12 | Coriolis Composites | Fiber coating machine |
| JP2013240882A (en) * | 2011-02-23 | 2013-12-05 | Airbus Operations Ltd | Composite structural body |
Also Published As
| Publication number | Publication date |
|---|---|
| DE3743485A1 (en) | 1989-07-13 |
| GB8826325D0 (en) | 1988-12-14 |
| IT8822738A0 (en) | 1988-11-25 |
| FR2624786A1 (en) | 1989-06-23 |
| IT1227931B (en) | 1991-05-14 |
| GB2213793A (en) | 1989-08-23 |
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