DE3743485A1 - METHOD FOR PRODUCING A SPACIOUSLY WINDED ROTOR BLADE - Google Patents

METHOD FOR PRODUCING A SPACIOUSLY WINDED ROTOR BLADE

Info

Publication number
DE3743485A1
DE3743485A1 DE19873743485 DE3743485A DE3743485A1 DE 3743485 A1 DE3743485 A1 DE 3743485A1 DE 19873743485 DE19873743485 DE 19873743485 DE 3743485 A DE3743485 A DE 3743485A DE 3743485 A1 DE3743485 A1 DE 3743485A1
Authority
DE
Germany
Prior art keywords
fiber
rotor blade
blade
producing
pressure roller
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.)
Withdrawn
Application number
DE19873743485
Other languages
German (de)
Inventor
Bernhard Dr Woehrl
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
MTU Aero Engines GmbH
Original Assignee
MTU Motoren und Turbinen Union Muenchen GmbH
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by MTU Motoren und Turbinen Union Muenchen GmbH filed Critical MTU Motoren und Turbinen Union Muenchen GmbH
Priority to DE19873743485 priority Critical patent/DE3743485A1/en
Priority to GB8826325A priority patent/GB2213793A/en
Priority to IT8822738A priority patent/IT1227931B/en
Priority to JP63306790A priority patent/JPH01198329A/en
Priority to FR8816925A priority patent/FR2624786A1/en
Publication of DE3743485A1 publication Critical patent/DE3743485A1/en
Withdrawn legal-status Critical Current

Links

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

In the manufacture of a three-dimensionally twisted airfoil of a rotor blade, a fibre strand 9 is continuously impregnated with resin material, pressed by roller 11 on to an airfoil surface 1 and immediately precured at 15. The method permits the fast, simple and fully automatic manufacture of airfoils. The precuring device 15 may be an infrared radiator. The strand may be looped around nipples on a blade root. The winding device may be a six-axis robot. The precured airfoil is cured in a mould. <IMAGE>

Description

Die Erfindung betrifft ein Verfahren zur Herstellung eines räumlich verwundenen Rotorschaufelblattes durch Umwickeln eines Kernes mit harzdurchtränktem Fasermaterial.The invention relates to a method for producing a spatially twisted rotor blade by wrapping a core around resin-impregnated fiber material.

Fasertechnische Bauteile gewinnen auf Grund ihrer hervorragenden Eigenschaften eine immer größere technische Bedeutung. Ihre geringe Dichte, hohe Zugfestigkeit und vergleichsweise einfachen Formgestal­ tung lassen ihre Anwendung in Bereiche eindringen, die vormals den metallischen Werkstoffen vorbehalten waren. So gelangen faser­ verstärkte Werkstoffe auch im Flugzeugbau zum Einsatz, unter anderem für die dynamisch hoch belasteten Rotorblätter und Propeller oder Propfanblätter.Fiber components win because of their excellent Properties have an increasing technical importance. Your low Dense, high tensile strength and comparatively simple shape let their application penetrate into areas that were previously the were reserved for metallic materials. This is how fiber arrives reinforced materials also used in aircraft construction, among others for the dynamically highly loaded rotor blades and propellers or Graft leaves.

Eine weitere herausragende Eigenschaft der faserverstärkten Werkstoffe ist die Möglichkeit, durch Verlegen der Fasern in bevorzugten Richtun­ gen die Bauteileigenschaften zu beeinflussen und so in verschiedenen Richtungen unterschiedliche Werkstoffdaten, z. B. für den E-Modul oder Dämpfungskonstanten zu erzielen. Another outstanding property of the fiber-reinforced materials is the option of laying the fibers in the preferred direction to influence the component properties and thus in different Directions different material data, e.g. B. for the modulus of elasticity or To achieve damping constants.  

Technisch problematisch ist jedoch die Herstellung kompliziert geform­ ter Bauteile aus faserverstärkten Werkstoffen, bei denen die Oberflä­ chen räumlich verwunden, insbesondere teilweise konkav geformt sind und bei denen in verschiedenen Richtungen unterschiedliche Festig­ keits- und Schwingungseigenschaften gefordert werden. Dies trifft ins­ besondere für die Fan- oder Propfanschaufeln neuzeitlicher Turbotrieb­ werke zu, wobei die Anbringung der Schaufelblätter am Schaufelfuß bzw. am Rotor ein weiteres besonderes Problem darstellt.However, the production is technically problematic and complicated ter components made of fiber-reinforced materials, in which the surface chen spatially twisted, in particular partially concave and with different strengths in different directions and vibration properties are required. This is true especially for the fan or propane blades of modern turbo drives works, whereby the attachment of the blades to the blade root or represents another particular problem on the rotor.

Die bisherige Herstellung derartiger Bauteile ist mit einem hohen Aufwand verbunden, was ebenfalls zu hohen Herstellkosten führt. So werden sogenannte "prepregs", das sind mit Matrixwerkstoff durch­ tränkte Faserplatten in eine Hohlform gebracht und anschließend durch Druck und Temperatur ausgehärtet. Nachteilig ist dabei, daß die im Prinzip mögliche bewußte Beeinflussung der Bauteileigenschaften bei diesem Herstellverfahren nur unter sehr hohem Aufwand möglich ist.The previous production of such components is high Effort connected, which also leads to high manufacturing costs. So are so-called "prepregs", which are made with matrix material impregnated fiberboard into a hollow mold and then through Pressure and temperature hardened. The disadvantage here is that the Principle of possible deliberate influence on component properties this manufacturing process is possible only with very great effort.

Aufgabe der Erfindung ist es, ein Verfahren zur Herstellung von räum­ lich verwundenen Rotorschaufelblättern zu schaffen, das eine einfache und schnelle Herstellung erlaubt, wobei durch gezielte Faserverlegung die Bauteileigenschaften gezielt manipulierbar sind. Dabei soll ins­ besondere an konkav geformten Flächen eine gute Faseraufbringung möglich sein.The object of the invention is to provide a method for producing space Lich twisted rotor blades to create a simple and rapid production allowed, with targeted fiber laying the component properties can be manipulated in a targeted manner. Thereby ins good fiber application especially on concave surfaces to be possible.

Gelöst wird die Aufgabe erfindungsgemäß mit den Merkmalen des Patent­ anspruchs 1. Vorteilhafte Ausgestaltungen der Erfindung sind in den Unteransprüchen angegeben.The object is achieved according to the invention with the features of the patent claims 1. Advantageous embodiments of the invention are in the Subclaims specified.

Das erfindungsgemäße Verfahren bringt den Vorteil mit sich, daß Fasern in jeder Richtung auf einfache Weise auf beliebig geformte Oberflächen des Rotorschaufelblattes aufgebracht werden können und dort festhaf­ ten, d. h. nicht mehr verrutschen. Nach dem Anhärten der Fasern blei­ ben diese auch an konkav geformten Flächen haften und gewährleisten so ein exaktes und schnelles Verlegen der Fasern. Es können je nach An­ forderung mehrere Faserlagen in unterschiedlicher oder gleicher Aus­ richtung übereinander angebracht werden.The process according to the invention has the advantage that fibers in any direction on surfaces of any shape of the rotor blade can be applied and fixed there ten, d. H. don't slip anymore. After the fibers have hardened, lead  They also adhere to concave surfaces and thus guarantee an exact and quick laying of the fibers. Depending on the type demand multiple fiber layers in different or the same design direction on top of each other.

Die Vorhärtanlage geliert das Matrixmaterial so an, daß die Faser in ihrer Lage festgeklebt wird, das Faser-Matrixgemisch jedoch noch nicht aushärtet. Anschließend wird das gewickelte Bauteil in eine Form auf die Fertigmaße gepresst und in einem Ofen ausgehärtet.The pre-curing system gels the matrix material so that the fiber is in their position is glued, but not yet the fiber matrix mixture hardens. The wound component is then opened into a mold the finished dimensions are pressed and cured in an oven.

Überdies ist der erforderliche Zeitaufwand zur Herstellung eines ver­ wundenen fasertechnischen Bauteils gegenüber den herkömmlichen Metho­ den erheblich verkürzt. Wesentlich ist ferner, daß konkav geformte Schaufeln einfach und genau mit Faserlagen bedeckt werden können, was nach den herkömmlichen Aufbringverfahren nur unzureichend möglich ist.In addition, the time required to produce a ver wound fiber-optic component compared to conventional metho that shortened considerably. It is also essential that concave Scoops can be covered with fiber layers easily and precisely what is only insufficiently possible according to the conventional application methods.

Vorteilhafterweise ergibt sich so eine bedeutende Vereinfachung des Wickel-Verfahrens, was sich für eine vollautomatische computer- und robotergesteuerte Durchführung eignet.This advantageously results in a significant simplification of the Winding process, which is a fully automated computer and robot-controlled implementation is suitable.

Die Faserstränge können vorteilhafterweise entlang bevorzugter Bahnen verlegt werden. Hierdurch ist eine gezielte anisotrope Bauteilstruktur er­ reichbar, wodurch stabilitäts- und festigkeitsbegünstigende Anordnun­ gen geschaffen werden können. Hierdurch können insbesondere Schwin­ gungsprobleme behoben werden.The fiber strands can advantageously along preferred paths be relocated. This results in a targeted anisotropic component structure reachable, which means stability and strength-enhancing arrangement gen can be created. This allows Schwin in particular problems are resolved.

In vorteilhafter Ausbildung der Erfindung werden die Faserstränge zur Befestigung des Rotorschaufelblattes an einem Schaufelfuß um eine Anzahl am Schaufelfuß angebrachter Befestigungsnoppen geschlungen. Hierdurch läßt sich eine besonders günstige Krafteinleitung der im Betrieb wirkenden Fliehkräfte auf den Schaufelfuß erzielen.In an advantageous embodiment of the invention, the fiber strands Attachment of the rotor blade to a blade root by one Number of fastening knobs attached to the blade root looped. This allows a particularly favorable introduction of force in Achieve centrifugal forces acting on the blade root during operation.

Die Erfindung wird nachfolgend an Hand der beigefügten Zeichnungen weiter erläutert. Es zeigt:The invention will now be described with reference to the accompanying drawings explained further. It shows:

Fig. 1 ein Schrägbild einer Fanschaufel, Fig. 1 is an oblique view of a fan blade,

Fig. 2 ein Schrägbild der Faseraufbringungsvorrichtung, Fig. 2 is an oblique view of the fiber application device,

Fig. 3 ein Schrägbild eines 6-Achsen Portalroboters. Fig. 3 is an oblique view of a 6-axis gantry robot.

Fig. 1 zeigt ein mit der erfindungsgemäßen Verfahren herstellbares Rotorschaufelblatt 1. Eingezeichnet sind die bevorzugten Richtungen der aufzubringenden Fasern: die Hauptzugrichtung 2 und Schräglagen 3 und 4. Vorzugsweise werden die Fasern um Haltenoppen 5 geführt, die an einem Schaufelfuß 6 angebracht sind. Hierdurch läßt sich eine gute Verbindung beider Bauteile erreichen und die im Betrieb der Schaufel auftretende Zugkraft in den Schaufelfuß 6 gut einleiten. Fig. 1 shows a producible with the process of the invention the rotor blade 1. The preferred directions of the fibers to be applied are shown: the main tensile direction 2 and inclined positions 3 and 4 . The fibers are preferably guided around holding knobs 5 which are attached to a blade root 6 . In this way, a good connection between the two components can be achieved and the tensile force that occurs during operation of the blade can be introduced well into the blade root 6 .

In Fig. 2 ist eine Faseraufbringungsvorrichtung 8 gezeigt, die im wesentlichen aus einer Faserrolle 10, einem Faserzuführkanal 12 einer Faserandrückrolle 11 und einer Vorhärteanlage 15 besteht. Der von der Faservorratsrolle 10 abgewickelte Faserstrang 9 wird von der Faseran­ drückrolle 11 durch den Faserzuführkanal 12 gezogen, wobei gleichzei­ tig Matrixmaterial vom Matrixdosiergerät 14 über die Matrixzuführung 13 dem Faserstrang in definierten Mengen zugeführt wird. Das Matrixma­ terial wird aus dem Speicherbehälter 16 über die flexible Zuführlei­ tung 17 dem Matrixdosiergerät 14 zugeführt. Dabei ist das pro Faserlänge zugeführte Matrixvolumen einstellbar, vorzugsweise dem Faserdurchsatz angepaßt. Die derart benetzten Fasern werden mit der Faserandrückrolle 11 genau in die vorgegebene Bahn auf dem Bauteil­ kern 1 gelegt und mittels der Vorhärteanlage 15 angehärtet (ange­ liert), so daß die Oberfläche antrocknet. Auf diese Weise ist die Faser soweit fixiert, daß sie auf kurvigen Bahnen verlegt werden kann. Über die vorgehärteten Fasern können anschließend weitere Faserlagen in beliebiger Richtung verlegt werden. FIG. 2 shows a fiber application device 8 which essentially consists of a fiber roll 10 , a fiber feed channel 12, a fiber pressure roller 11 and a pre-hardening system 15 . The unwound from the fiber supply roll 10 fiber strand 9 is pulled by the fiber pressure roller 11 through the fiber feed channel 12 , at the same time matrix material from the matrix metering device 14 via the matrix feed 13 is fed to the fiber strand in defined quantities. The matrix material is fed from the storage container 16 via the flexible feed line 17 to the matrix metering device 14 . The matrix volume supplied per fiber length is adjustable, preferably adapted to the fiber throughput. The fibers so wetted are placed with the fiber pressure roller 11 exactly in the predetermined path on the component core 1 and hardened by means of the pre-curing system 15 (gelled), so that the surface dries. In this way, the fiber is fixed so far that it can be laid on curved paths. Further fiber layers can then be laid in any direction over the pre-hardened fibers.

Wie in Fig. 3 zu sehen, ist die schematisch angedeutete Faseraufbrin­ gungsvorrichtung 8 an dem "Handgelenk" eines 6-Achsen Portalroboters 7 angebracht und kann auf diese Weise, von einem Rechner gesteuert, den Faserstrang 9 vollautomatisch entlang den vorausberechneten Bahnen auf den Bauteilkern aufbringen. Hierdurch ist eine sehr genaue Reprodu­ zierbarkeit (<0,2 mm) der Faserverlegung erzielbar.As can be seen in Fig. 3, the schematically indicated fiber application device 8 is attached to the "wrist" of a 6-axis gantry robot 7 and can, in this way, controlled by a computer, apply the fiber strand 9 fully automatically along the pre-calculated paths to the component core . This enables a very precise reproducibility (<0.2 mm) of the fiber laying to be achieved.

Nachdem das derart hergestellte Rohteil fertig gewickelt ist, wird es anschließend in eine Form gebracht und mittels Druck und Temperatur auf herkömmliche Weise ausgehärtet.After the raw part produced in this way is completely wound, it becomes then brought into a mold and by means of pressure and temperature cured in a conventional manner.

Claims (4)

1. Verfahren zur Herstellung eines räumlich verwundenen Rotorschau­ felblattes durch Umwickeln eines Kernes mit harzdurchtränktem Fasermaterial, dadurch gekennzeichnet, daß mit einer Harz-Matrix getränkte Faserstränge mittels einer Andrückrolle (11) gegen den Kern gedrückt werden und eine mit der Andrückrolle (11) gekoppelte Vorhärteanlage (15) die Harz-Matrix unmittelbar nach dem Andrücken anhärtet.1. A process for producing a spatially twisted rotor blade blade by wrapping a core with resin-impregnated fiber material, characterized in that fiber strands impregnated with a resin matrix are pressed against the core by means of a pressure roller ( 11 ) and a pre-hardening system coupled to the pressure roller ( 11 ) ( 15 ) the resin matrix hardens immediately after pressing. 2. Verfahren nach Anspruch 1, dadurch gekennzeichnet, daß die Faserstränge zur Befestigung des Rotorschaufelblattes an einem Schaufelfuß (6) um eine Anzahl am Schaufelfuß (6) angebrachter Befestigungsnoppen (5) geschlungen werden.2. The method according to claim 1, characterized in that the fiber strands for fastening the rotor blade to a blade root ( 6 ) by a number on the blade root ( 6 ) attached fastening knobs ( 5 ) are looped. 3. Verfahren nach Anspruch 1, dadurch gekennzeichnet, daß die Vorhärteanlage als Infrarotstrahler ausgeführt ist. 3. The method according to claim 1, characterized in that the Pre-curing system is designed as an infrared heater.   4. Verfahren nach Anspruch 1 bis 3, dadurch gekennzeichnet, daß die Faserstränge mittels der Andrückrolle (11) durch einen Faser­ zuführkanal gezogen werden, wobei Matrixmaterial den Fasersträngen zugeführt wird.4. The method according to claim 1 to 3, characterized in that the fiber strands are pulled by means of the pressure roller ( 11 ) through a fiber feed channel, with matrix material being fed to the fiber strands.
DE19873743485 1987-12-22 1987-12-22 METHOD FOR PRODUCING A SPACIOUSLY WINDED ROTOR BLADE Withdrawn DE3743485A1 (en)

Priority Applications (5)

Application Number Priority Date Filing Date Title
DE19873743485 DE3743485A1 (en) 1987-12-22 1987-12-22 METHOD FOR PRODUCING A SPACIOUSLY WINDED ROTOR BLADE
GB8826325A GB2213793A (en) 1987-12-22 1988-11-10 Winding airfoil
IT8822738A IT1227931B (en) 1987-12-22 1988-11-25 PROCEDURE FOR THE MANUFACTURE OF A THREE-DIMENSIONALLY WINDED ROTOR BLADE
JP63306790A JPH01198329A (en) 1987-12-22 1988-12-02 Manufacture of aerofoil of rotor blade twisted in three dimension
FR8816925A FR2624786A1 (en) 1987-12-22 1988-12-21 PROCESS FOR MANUFACTURING A LEFT-SHAPED ROTOR BLADE IN SPACE USING RESIN IMPREGNATED FIBERS

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
DE19873743485 DE3743485A1 (en) 1987-12-22 1987-12-22 METHOD FOR PRODUCING A SPACIOUSLY WINDED ROTOR BLADE

Publications (1)

Publication Number Publication Date
DE3743485A1 true DE3743485A1 (en) 1989-07-13

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Family Applications (1)

Application Number Title Priority Date Filing Date
DE19873743485 Withdrawn DE3743485A1 (en) 1987-12-22 1987-12-22 METHOD FOR PRODUCING A SPACIOUSLY WINDED ROTOR BLADE

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)

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US5200019A (en) * 1990-01-25 1993-04-06 Hendrik Brandis Apparatus for depositing slivers on double-curved bodies or surfaces
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WO2006059051A1 (en) * 2004-12-02 2006-06-08 European Aeronautic Defence And Space Company Eads France Device for the drape forming of pre-impregnated flexible bands
FR2882681A1 (en) * 2005-03-03 2006-09-08 Coriolis Composites Sa FIBER APPLICATION HEAD AND CORRESPONDING MACHINE
WO2007090555A2 (en) * 2006-02-11 2007-08-16 Sgl Kümpers Gmbh & Co. Kg Three-dimensional textile component structure consisting of high-tensile threads and method for producing said structure
US7819160B2 (en) 2007-02-28 2010-10-26 Coriolis Composites Device for using fibers with flexible fiber-routing tubes
US7926537B2 (en) 2007-03-06 2011-04-19 Coriolis Composites Applicator head for fibers with particular systems for cutting fibers
US8052819B2 (en) 2009-04-02 2011-11-08 Coriolis Composites Method and machine for applying a band of fibers on convex surfaces and/or with edges
US8057618B2 (en) 2007-02-21 2011-11-15 Coriolis Composites Method and apparatus for making structures of composite material, in particular airplane fuselage sections
US8191596B2 (en) 2009-07-17 2012-06-05 Coriolis Composites Fiber application machine comprising a flexible compacting roller with a thermal regulation system
DE102013208471A1 (en) * 2013-05-08 2014-11-13 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
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
US10369594B2 (en) 2015-04-01 2019-08-06 Coriolis Group Fiber application head with a specific application roll
US10821682B2 (en) 2015-10-28 2020-11-03 Coriolis Group Fiber application machine comprising specific cutting systems
US10894341B2 (en) 2016-03-07 2021-01-19 Coriolis Group Method for producing preforms with application of a binder to dry fiber, and corresponding machine
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US10821682B2 (en) 2015-10-28 2020-11-03 Coriolis Group Fiber application machine comprising specific cutting systems
US10894341B2 (en) 2016-03-07 2021-01-19 Coriolis Group Method for producing preforms with application of a binder to dry fiber, and corresponding machine
US11491741B2 (en) 2016-09-27 2022-11-08 Coriolis Group Process for producing composite material parts by impregnating a specific preform
EP3713750A4 (en) * 2017-11-21 2021-08-11 General Electric Company Methods for manufacturing wind turbine rotor blade panels having printed grid structures

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GB2213793A (en) 1989-08-23
IT8822738A0 (en) 1988-11-25
FR2624786A1 (en) 1989-06-23

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