СПОСОБ ЛОКАЛЬНОГО ВЛИЯНИЯ НА ПРОНИЦАЕМОСТЬ ДЛЯ СМОЛЫ СУХОЙ ЗАГОТОВКИ

Изобретение относится к способу локального влияния на проницаемость смолы сухой заготовки, имеющей один или более армирующих слоев. Техническим результатом является улучшение пропитки заготовок, имеющих сложную геометрию. Технический результат достигается способом, который включает нанесение избирательно проницаемой оболочки на один из армирующих слоев сухой заготовки. Причем избирательно проницаемая оболочка имеет узор оболочки, пространственная плотность которого выбирается в зависимости от проницаемости смолы по меньшей мере части сухой заготовки для достижения требуемого объема инфузии смолы, и выполнена с возможностью растворения или плавления в смоле с приданием заготовке, по меньшей мере локально, ударной вязкости после инфузии смолы и отверждения сухой заготовки. Обеспечиваются инфузия смолы в сухую заготовку и направление смолы через избирательно проницаемую оболочку таким образом, что смола пропитывает сухую заготовку. 2 н. и 25 з.п. ф-лы, 15 ил.

СПОСОБ УПЛОТНЕНИЯ ВОЛОКНИСТЫХ СТРУКТУР МЕТОДОМ ИНЖЕКЦИИ ПОЛИМЕРА В ФОРМУ ДЛЯ ИЗГОТОВЛЕНИЯ ТОЛСТЫХ ДЕТАЛЕЙ ИЗ КОМПОЗИТНЫХ МАТЕРИАЛОВ

Настоящее изобретение относится к изготовлению деталей из композитного материала с волокнистым армированием и полимерной матрицей с использованием метода инжекции полимера под давлением. Техническим результатом настоящего изобретения является разработка способа изготовления деталей из композитного материала с упрочняющим волокном и полимерной матрицей, позволяющего получить толстые детали с низкой пористостью при уменьшении времени процесса, проводимого в одну стадию. Технический результат достигается способом изготовления детали из композитного материала с волокнистым армированием и полимерной матрицей, включающим в себя следующие этапы подготовки волокнистой структуры, предназначенной для армирования изготавливаемой детали. Помещают волокнистую структуру в форму, у которой, по меньшей мере, одна стенка образована гибкой мембраной. Затем проводят инжекцию в форму смолы, выбранной из фенольных и фурановых смол, имеющей массовое содержание летучих веществ менее 25%, и температуру, при которой ...

СИСТЕМЫ, СПОСОБЫ И УСТРОЙСТВО ДЛЯ СРЕДСТВА РАСПРЕДЕЛЕНИЯ МАТЕРИАЛА, СВЯЗАННОГО С ИЗГОТОВЛЕНИЕМ КОМПОНЕНТОВ

Предложены системы, способы и устройство для управления потоком материала через компонент транспортного средства. В некоторых вариантах реализации устройство может содержать множество разделительных слоев, каждый разделительный слой из множества разделительных слоев имеет контур, причем по меньшей мере одно пространство между по меньшей мере некоторыми из множества разделительных слоев определяет по меньшей мере один путь потока. Устройство может также содержать первое множество распорок, расположенное по меньшей мере в одном пути потока, первое множество распорок имеет одно или более гидродинамических свойств, определенных на основании первого множества размеров, одно или более гидродинамических свойств по меньшей мере частично определяет второе свойство потока по меньшей мере одного пути потока. Обеспечивается уменьшение частоты появления «сухих пятен» внутри компонента транспортного средства, инфузию материалом которого осуществляют. 3 н. и 17 з.п. ф-лы, 15 ил.

СПОСОБ ОТВЕРЖДЕНИЯ КОМПОЗИТНОГО ИЗДЕЛИЯ С ИСПОЛЬЗОВАНИЕМ ПЕРЕПАДА ВАКУУМА

Изобретение относится к способу предотвращения просачивания через уплотнитель внутренней камеры вакуумного мешка. Техническим результатом является обеспечение целостности и повышение эффективности уплотнителя внутренней камеры мешка в процессе отверждения композитной укладки. Технический результат достигается способом предотвращения просачивания через уплотнитель внутренней камеры вакуумного мешка во время отверждения композитной укладки, который включает приложение давления вакуума внутреннего мешка к внутренней камере мешка и давления внешнего вакуума к внешней вакуумной камере. При этом внутренняя камера мешка образована вакуумным мешком, покрывающим композитную укладку и загерметизированным относительно формовочного приспособления, а давление вакуума внутреннего мешка не меньше, чем давление внешнего вакуума. Температура композитной укладки увеличивается до повышенной температуры для инициирования периода выдерживания при температуре. Вентилирование внешней вакуумной камеры соединением ...

СПОСОБ ИЗГОТОВЛЕНИЯ КОНСТРУКТИВНОГО КОМПОНЕНТА ИЗ АРМИРОВАННОГО ВОЛОКНАМИ КОМПОЗИЦИОННОГО МАТЕРИАЛА, ПРЕДНАЗНАЧЕННОГО ДЛЯ ВОЗДУШНОГО ИЛИ КОСМИЧЕСКОГО ЛЕТАТЕЛЬНОГО АППАРАТА, И СФОРМОВАННЫЙ СТЕРЖЕНЬ ДЛЯ ИЗГОТОВЛЕНИЯ ТАКОГО КОМПОНЕНТА

... 1. Способ изготовления конструктивного компонента (22) из армированного волокнами композиционного материала, предназначенного, в частности, для авиакосмической промышленности, в котором: ! вкладывают эластичный рукав (1) стержня в механизм (3) создания предварительного напряжения; ! осуществляют посредством приведения механизма (3) создания предварительного напряжения в активное состояние растяжение вложенного рукава (1) для создания в рукаве предварительного напряжения упругой деформации; ! вводят стабильное по размерам тело (13) стержня через отверстие (4) растянутого рукава (1) стержня; ! отпускают посредством приведения механизма (3) создания предварительного напряжения в неактивное состояние растянутый рукав (1) стержня для обеспечения плотной обтяжки тела (13) стержня рукавом (1), тем самым изготовления формовочного стержня (14); и ! накладывают, по меньшей мере, одну заготовку-полуфабрикат (16) из волоконного материала, по меньшей мере, частично на изготовленный формовочный стержень ...

ФОРМОВОЧНО-ЛИТЬЕВОЕ УСТРОЙСТВО И СПОСОБ ПРОИЗВОДСТВА ПРЕФОРМ И АРМИРОВАННЫХ ВОЛОКНОМ ПЛАСТМАСС С ПОМОЩЬЮ ФОРМОВОЧНО-ЛИТЬЕВОГО УСТРОЙСТВА

... 1. Формовочно-литьевое устройство для трансферного формования пластмасс, армированных волокном, полученное путем объединения рабочей пластинчатой части и плоской пластинчатой части с формированием полой выпуклой части, в которой система металлических труб в качестве пути потока теплоносителя объединена с нижней поверхностью рабочей пластинчатой части теплопроводящим материалом, и резиновый шнур объединен с внешней частью зоны, используемой для формования или литьевого формования, в плоской пластинчатой части. ! 2. Формовочно-литьевое устройство по п.1, в котором толщина рабочей пластинчатой части составляет 1 мм или больше и 15 мм или меньше. ! 3. Формовочно-литьевое устройство по п.1 или 2, в котором диаметр резинового шнура составляет 10 мм или больше и 100 мм или меньше. ! 4. Формовочно-литьевое устройство по п.1, в котором впускной канал для смолы и выпускной канал для связующей смолы для трансферного формования помещены в плоской пластинчатой части между выпуклой частью и резиновым ...

СПОСОБ ИЗГОТОВЛЕНИЯ КОМПОЗИЦИОННОГО МАТЕРИАЛА И УСТРОЙСТВО ИЗГОТОВЛЕНИЯ КОМПОЗИЦИОННОГО МАТЕРИАЛА

Изобретение относится к способу изготовления композиционного материала. Техническим результатом является уменьшение времени формования и затрат на оборудование. Технический результат достигается способом изготовления композиционного материала 400, содержащего армирующий материал 510 и смолу 600, вводимую в армирующий материал. Способ включает в себя: процесс нанесения для нанесения адгезива 520 на листовой армирующий материал, имеющий первую и вторую области 501 и 502, таким образом, что плотность содержимого адгезива второй области ниже плотности содержимого адгезива первой области. Процесс предварительной формовки для формирования заготовки 500 посредством предварительной формовки армирующего материала. Процесс формования композиционного материала 400 посредством введения смолы 600 в заготовку. 2 н. и 7 з.п. ф-лы, 12 ил.

НОВЫЕ АРМИРУЮЩИЕ МАТЕРИАЛЫ, ПОДХОДЯЩИЕ ДЛЯ ПОЛУЧЕНИЯ КОМПОЗИЦИОННЫХ ДЕТАЛЕЙ

... 1. Новый промежуточный материал, предназначенный для соединения с термореактивной смолой для получения композиционных деталей, состоящий из однонаправленного полотна углеродных волокон, имеющего поверхностную плотность от 100 до 280 г/м, соединенного на каждой из своих сторон с тонкой пленкой термопластичных волокон, причем указанные тонкие пленки имеют, каждая, толщину от 0,5 до 50 мкм, предпочтительно от 3 до 35 мкм, причем промежуточный материал имеет общую толщину от 80 до 380 мкм, предпочтительно от 90 до 320 мкм.2. Материал по п.1, отличающийся тем, что толщина промежуточного материала имеет малую изменяемость, в частности среднеквадратичные отклонения толщины не превышают 20 мкм, предпочтительно не превышают 10 мкм.3. Материал по п.1 или 2, отличающийся тем, что однонаправленное полотно не содержит никаких уточных нитей, переплетающихся с углеродными волокнами.4. Материал по п.1, отличающийся тем, что промежуточный материал является нетканым, несшитым, невязаным.5. Материал по п.1 ...

СПОСОБ ИЗГОТОВЛЕНИЯ КОНСТРУКТИВНОГО КОМПОНЕНТА ИЗ АРМИРОВАННОГО ВОЛОКНАМИ КОМПОЗИЦИОННОГО МАТЕРИАЛА, ПРЕДНАЗНАЧЕННОГО ДЛЯ АВИАЦИОННО-КОСМИЧЕСКОГО ЛЕТАТЕЛЬНОГО АППАРАТА

... 1. Способ изготовления конструктивного компонента (1) из армированного волокнами композиционного материала, в частности, для авиакосмической отрасли, который включает в себя следующие этапы: ! образуют формовочный стержень (4) спиральной конструкции, определяющей внешнюю геометрию формовочного стержня (4), причем при образовании формовочного стержня (4) образуют полый профиль (15, 16) с внешней геометрией, соответствующей формовочному стержню (4), и с прорезью (17), предусмотренной в стенке полого профиля (15, 16), спирально проходящей по периферии указанного профиля, и обеспечивают позиционную фиксацию для полого профиля (15, 16) с прорезью, при этом прорезь (17), спирально проходящая по периферии, пронизывает стенку полого профиля (15, 16), за исключением по меньшей мере трех участков, расположенных так, что они распределены по периметру стенки полого профиля (15, 16); ! по меньшей мере частично укладывают по меньшей мере одну армированную волокнами заготовку (3) на образованный формовочный ...

НАПРАВЛЯЮЩАЯ ЛОПАТКАВЕНТИЛЯТОРА, ВЫПОЛНЕННАЯ ИЗ ТРЕХМЕРНОГО КОМПОЗИЦИОННОГО МАТЕРИАЛА

... 1. Способ изготовления направляющей лопатки, отличающийся тем, что он включает: ! а) изготовление волоконной преформы (1) посредством трехмерного переплетения одной детали, причем преформа содержит первую часть (10), продолжающуюся вдоль продольной оси (А) и образующую преформу для аэродинамического профиля лопатки, и расположенную на продольном конце (11) первой части (10) вторую часть (20), образующую преформу для платформы лопатки, причем вторая часть (20) выполнена в виде первого слоя (40) и второго слоя (50), обращенного к первому слою и отделенного от первого слоя (40) посредством разделения без разрезания при изготовлении преформы (1); ! b) сгибание первого и второго слоев (40, 50) таким образом, что каждый из них расположен в плоскости, перпендикулярной продольной оси, по существу, симметрично друг другу относительно первой части (10), и таким образом, что первый участок (R1) первого слоя (40) перекрывает второй участок (R2) второго слоя (50) перед передней кромкой (15) первой части ...

ЭЛЕМЕНТ ЖЕСТКОСТИ С ПОКРЫТИЕМ (ВАРИАНТЫ), ПРИМЕНЕНИЕ ЭЛЕМЕНТА ЖЕСТКОСТИ, СПОСОБ ИЗГОТОВЛЕНИЯ УСИЛЕННОГО ВОЛОКНАМИ ПРОДУКТА

... 1. Элемент жесткости, на поверхность которого нанесено покрытие из композиции, отличающийся тем, что композиция состоит из твердой смолы и углеродных нанотрубок, причем композиция подвергнута термообработке при температуре свыше точки плавления или области стеклования и ниже температуры сшивания, при необходимости, самостоятельно сшиваемой твердой смолы, причем композиция зафиксирована на поверхности элемента жесткости.2. Элемент жесткости, на поверхность которого нанесено покрытие из композиции, отличающийся тем, что композиция содержит твердую смолу с показателем ТМ или TG>50°С, углеродные нанотрубки и дополнительные добавки, причем композиция подвергнута термообработке при температуре свыше точки плавления или области стеклования твердой смолы и ниже температуры сшивания, при необходимости, сшиваемой композиции, причем композиция зафиксирована на поверхности элемента жесткости.3. Элемент жесткости по п.1 или 2, отличающийся тем, что твердая смола выбирается из группы эпоксидных смол, ...

ЛОПАСТЬ РОТОРА, ЭЛЕМЕНТ ЛОПАСТИ РОТОРА И СПОСОБ ИЗГОТОВЛЕНИЯ

... 1. Лопасть ротора или элемент лопасти ротора для ветроэнергетической установки, содержащая/ий поверхностную пленку, прореагировавшую с отверждаемой смолой.2. Лопасть ротора или элемент лопасти ротора по п.1, дополнительно содержащая/ий волокнистый материал, пропитанный отверждаемой смолой.3. Элемент лопасти ротора по п.1, причем элемент лопасти ротора выбран из группы, состоящей из перемычки, наружной оболочки лопасти ротора и ее частей, в частности, половины оболочки нагнетающей стороны или засасывающей стороны, передней кромки лопасти ротора, задней кромки лопасти ротора, вершины лопасти ротора, пояса лонжерона, клейкого уголка, фланцевого усиления, внутреннего усиления для средств упора, камеры балласта и камеры балансира.4. Лопасть ротора или элемент лопасти ротора по п.1 со следующими размерами:- наружная оболочка, предпочтительно нагнетающая сторона лопасти ротора и/или засасывающая сторона лопасти ротора, пояса лонжеронов, клейкие уголки: длина от 1 м до 150 м, предпочтительно от ...

СИСТЕМЫ, СПОСОБЫ И УСТРОЙСТВО ДЛЯ СРЕДСТВА РАСПРЕДЕЛЕНИЯ МАТЕРИАЛА, СВЯЗАННОГО С ИЗГОТОВЛЕНИЕМ КОМПОНЕНТОВ

ОПОРНЫЙ ПРОФИЛЬ, СПОСОБ ИЗГОТОВЛЕНИЯ ОПОРНОГО ПРОФИЛЯ, А ТАКЖЕ ЕГО ПРИМЕНЕНИЕ В СПОСОБЕ ИЗГОТОВЛЕНИЯ УСИЛЕННОЙ ДЕТАЛИ КОРПУСА ТРАНСПОРТНОГО СРЕДСТВА

... 1. Опорный профиль (30) для опоры образованного из волокнистого композитного полуфабриката усилительного профиля (12) в процессе отверждения способа изготовления детали (10, 12) корпуса транспортного средства, в котором усилительный профиль (12) присоединяют к поверхности, образованной из волокнистого композитного полуфабриката обшивки (10) корпуса, отличающийся воздухонепроницаемым профильным рукавом (32) и по меньшей мере одним наконечником (34), который разъемно вставлен на одном из обоих концов профильного рукава и посредством этого разъемного соединения уплотнен относительно профильного рукава (32).2. Опорный профиль (30) по п.1, в котором на обоих концах профильного рукава предусмотрено по одному разъемно вставленному и посредством этого разъемного соединения уплотненному относительно профильного рукава (32) наконечнику (34).3. Опорный профиль (30) по п.1, в котором выступающий из конца профильного рукава внешний участок (36) наконечника (34) или же по меньшей мере одного из наконечников ...

ОПРАВКА ДЛЯ ПРОПИТКИ, СОДЕРЖАЩАЯ ВАКУУМНЫЙ МЕШОК, ДЛЯ ИЗГОТОВЛЕНИЯ КАРТЕРА ГАЗОВОЙ ТУРБИНЫ ИЗ КОМПОЗИЦИОННОГО МАТЕРИАЛА

... 1. Оправка для пропитки для изготовления картера газовой турбины из композиционного материала, содержащая:- оправку для пропитки (100), для размещения упрочняющего волокнистого элемента (28), образованного за счет напластованных друг на друга слоев волокнистой структуры, при этом оправка содержит центральную кольцевую стенку (102), профиль которой соответствует профилю картера, и две боковые закраины (104а, 104b), профиль которых соответствует профилю наружных фланцев картера;- перегородки уплотнения (106а, 106b), каждая их которых имеет угол (108а, 108b), который поджатый вплотную к части упрочняющего волокнистого элемента, покрывая углы, образованные между центральной стенкой и закраинами оправки, и соединительный фланец (110a, 110b), фиксируемый на соответствующей закраине оправки;- гибкую оболочку (118), образующую вакуумный мешок, накладываемый, по меньшей мере, на часть упрочняющего волокнистого элемента, покрывая центральную стенку оправки; и- средства (120, 124) для нагнетания смолы ...

СПОСОБ ИЗГОТОВЛЕНИЯ ОБОРУДОВАНИЯ ДЛЯ ФОРМОВАНИЯ ПОСРЕДСТВОМ ПЕРЕНОСА СМОЛЫ

... 1. Способ изготовления инструментальной оснастки для формования детали посредством формования с переносом смолы, содержащий по меньшей мере следующие этапы:- изготовления модели (1) упомянутой детали;- изготовления контрформы (2) с наружной поверхностью (3), имеющей выемку (4), стыкующуюся с первой стороной упомянутой модели (1);- помещения упомянутой модели (1) в упомянутую выемку контрформы (2);- вакуумного формования множества наложенных друг на друга текстильных слоев, пропитанных термореактивной смолой, на моделе (1) и на упомянутой наружной поверхности контрформы (2) для образования формы первой полуоболочки (6);- вулканизации упомянутой первой полуоболочки (6);- отделения контрформы (2) от модели (1) и от первой полуоболочки (6);- вакуумного формования множества наложенных друг на друга текстильных слоев на первой полуоболочке (6) и первой стороне модели для образования формы второй полуоболочки (7); и- вулканизации второй полуоболочки (7).2. Способ по п. 1, причем каждая полуоболочка ...

Process for producing a composite material

The invention can be used in the vacuum injection moulding process. The aim and object of the invention is the economical production of adequately strong, thin and complex-shaped laminates for composite materials. This object is achieved in that a prefabricated, at least partly thermoformable textile product is drawn onto at least one core, covering the latter so as to bear closely against it on all sides, in that subsequently at least one surface non-woven fabric or, after laying in a gel coat, one surface non-woven fabric is laid in a non-stationary mould, in that then the textile product is introduced into a non-stationary mould, after which, in a known manner, the composite material is produced by the vacuum injection moulding process.

FORMWERKZEUGANORDNUNG MIT SCHLIESSMECHANISMUS

Verfahren zum Herstellen eines Vorformlings und eines daraus hergestellten Faserverbundfertigbauteils

Verfahren zum Herstellen eines trockenen Vorformlings für eine Weiterverarbeitung zu einem harzbeinhaltenden Faserverbundfertigbauteil, mit den folgenden nacheinander ablaufenden Schritten: a) Herstellen eines wieder verwendbaren Kerns (11), b) direktes Umschließen des Kerns (11) oder eines auf den Kern (11) hinzugefügten Trennbauteils (13) mit Gewebematerialien (14), wie Fasern, und Bindemittelmaterialien, c) Beaufschlagen des Aufbaus aus zumindest Kern (11), Gewebematerial (14) und Bindemittel mit Wärme zum fixierenden Zwischenhärten des Gewebematerials (14) durch Ausschmelzen, Abkühlen und Vorverfestigen des Bindemittels, d) Entnehmen eines fixierten und zwischengehärteten Vorformlings aus Gewebematerial (14) und/oder Entnehmen des Kerns (11) aus dem zwischengehärteten Vorformling.

Gerät zur Herstellung von Verbundkörpern

Verfahren zur Herstellung eines Gegenstandes aus Verbundwerkstoff durch Transfer-Spritzgiessen von Kunstharz (R.T.M.) und dadurch hergestellter Gegenstand

Verfahren zur Herstellung von Faserverbundbauteilen mittels eines Vakuum-Injektionsverfahrens

Die vorliegende Erfindung bezieht sich auf ein Verfahren zur Herstellung von Faserverbundbauteilen mittels eines Vakuum-Injektionsverfahrens mit den Schritten:- Anordnen des Faserverbund-Halbzeugs in einem Bauteilraum auf einem Werkzeug,- Anordnen und Positionieren eines dem Bauteilraum benachbarten Absaugraums zur Evakuierung von Gas aus dem Bauteilraum mit einer den Absaugraum vom Bauteilraum trennenden Trennmembran,- Abdichten des Bauteilraums und des Absaugraums zur Werkzeugumgebung mit einem gas- und matrixmaterialdichten Abdeckmaterial,- Anlegen eines Vakuums an den Absaugraum,- Einleiten eines Matrixmaterials in den Bauteilraum,- Aushärten und Entformen des fertigen Faserverbundbauteils.Um das Verfahren zur Herstellung eines Faserverbundbauteils noch effizienter auszugestalten, wird vorgeschlagen, dass der Absaugraum mit einem Abdeckmaterial abgedichtet ist, das mit einer Porengröße zwischen 0,4 und 30 µm eine stark harzbremsende Wirkung aufweist, jedoch nicht matrixmaterialdicht ...

Verfahren zur Herstellung von Windmühlenflügeln

Fiber reinforced sandwich structure with hollow core made by vacuum-assisted impregnation, e.g. for aircraft use, includes a separation layer to control resin penetration

Initially the dry reinforcing fibers a laid on one side of a hollow core, e.g. a honeycomb structure, and covered with a separating and bonding film (TV film) of a thermosetting resin (H1). The assembly is placed in a mold and covered by a second structure. The mold is then closed, evacuated and a second thermosetting resin (H2), which hardens at a lower temperature than the first resin (H1), is injected. The resins are then hardened successively at increasing temperature levels. Optionally the first film (H1) can be at least partially hardened before the assembly is placed in the mold. Independent claims are included for the following: (1) A thermosetting separating and bonding film (TV film) of a resin (H1) which is rigid enough to form a seal and has a higher setting temperature than the other resin (H2) and but is able to combine with it; (2) An intermediate product consisting of a fiber reinforced core covered with a TV film; (3) A set of resins (H1, H2) with the required properties ...

Verfahren zum Anbinden von vor- bzw. ausgehärteten Stringern an mindestens ein Strukturbauteil eines Luft- oder Raumfahrzeuges

Verfahren zum Anbinden von vorgehärteten Stringern (1) an mindestens ein Strukturbauteil (10) eines Luft- oder Raumfahrzeuges, mit folgenden Verfahrensschritten: vorab Aufbringen von Abdeckvakuumfolien (8) zumindest auf jeweils einem vorbestimmten Bereich (2, 5) der anzubindenden Stringer (1); Anlegen der Stringer (1) an das mindestens eine Strukturbauteil (10); Aufbringen und Anpressen von jeweiligen Vakuumfolienstreifen (13) zwischen den Stringern (1) unter Verwendung von Vakuumversiegelungsmittel (12) derart, dass eine durchgehende Vakuumanordnung bestehend aus den Abdeckvakuumfolien (8) und den Vakuumfolienstreifen (13) gebildet wird; und druckbeaufschlagtes Anbinden der Stringer (1) an das mindestens eine Strukturbauteil (10) mittels der gebildeten, durchgehenden Vakuumanordnung (8, 12, 13).

Verfahren zur Infiltration von Silikon in eine Faserverbundstruktur sowie Vorrichtung zur Ausführung eines Verfahrens zur Herstellung eines Faserverbundwerkstücks

Verfahren zur Herstellung eines Faserverbundwerkstücks mit einer Matrix aus vernetztem Silikon, aufweisend die folgenden Schritte: • Anordnen wenigstens zweier Matten (20) aus Fasern (22) übereinander, • Verbinden der wenigstens zwei Matten (20) miteinander zu wenigstens einem porösen Mattenverbund (30), • Herstellen einer Mischung (40) aus flüssigem, vernetzendem Silikon mit wenigstens einem flüchtigen Verdünnungsmittel, die eine geringere Viskosität hat als das Silikon alleine, • Einlegen und Untertauchen wenigstens des Mattenverbundes (30) in die Mischung (40), so dass sich der Mattenverbund in einer Position befindet, in welcher er von allen Seiten von der Mischung umgeben ist, und • Aushärten durch Vernetzen des Silikons und Verdampfen des Verdünnungsmittels.

Beschichteter Festigkeitsträger

Um einen beschichteten Festigkeitsträger bereitzustsellen, dessen Beschichtung es letztendlich ermöglicht, ein faserverstärktes Produkt insbesondere im Infusionsverfahren zur Verfügung zu stellen, das hervorragende mechanische Eigenschaften besitzt, wird vorgeschlagen, dass die Zusammensetzung der Beschichtung aus einem Festharz und Kohlenstoffnanoröhren besteht und diese Zusammensetzung einer Wärmebehandlung oberhalb der Schmelztemperatur oder der Erweichungstemperatur und unterhalb der Vernetzungstemperatur des gegebenenfalls selbstvernetzenden Festharzes unterzogen wurde, wodurch die Zusammensetzung auf der Oberfläche des Festigkeitsträgers fixiert ist.

Resin moulding systems

Resin infusion process

Press moulding method

Foam core for a composite laminated article, and manufacture thereof

Controlling flow of resin into a mould cavity using sensors

A method and apparatus for moulding composite articles are disclosed. There may be at least one skin 16 with a back side 54 and a front side 52, which defines a portion of a mould cavity. A pressure sensor 66 has a portion extending through the skin 16 into the cavity to generate a signal indicative of pressure in the cavity. A control unit controls injection of resin into the cavity in response to the signal generated by the sensor. Deflection sensors may be mounted to the back sides of upper and lower skins 20, 16 defining the cavity therebetween. The sensor, mounted on a deformable skin, may generate a signal indicative of skin deformation. The sensors, which may be connected to a CPU, stop or slow the flow of resin if the resin pressure builds up to deform the skins.

Process for making a fibre composite part

The process comprises a matrix of fibres 15 held inside a chamber 13 by connecting pipes 14, wherein a material is introduced into the chamber and expands compacting the fibres. A resin is then injected via the connecting pipes into the matrix of spaces around the fibres and contained within the expanded material. The resin is then cured and the process is completed by scavenging the expanded material from the cured resin and fibre part and removing the finished part from the expansion chamber. The foam material (18 figure 3) may be expanded polystyrene, expanded under chemical, gaseous and or thermal means and scavenged by pressure-blasting using shot (26 figure 6) or a chemical means and recycled. The fibres may be carbon fibres or any mix of carbon, metal or glass.

Liquid supply system

Improvements in the manufacture of resin impregnated components

Press moulding method

Method and device for forming a composite pipe

A device for forming a composite pipe, comprising: a first 10 and a second mould 20 enclosed by a vacuum bagging film 40, with a first/second mold surface, a smaller diameter first/second connecting end (12,22 fig.2) and a larger diameter opposite first/second restricting end (13,23 fig.2), the first mould surface is connected to the second mold surface forming a moulding surface (30 fig.2). A method for forming a composite pipe, comprising: providing a tube-shaped base material 60 with a hole (61, fig.3A) including a first and a second open end, moving a first 10 and a second mold 20 from the first and second open ends respectively toward the base material into the hole, connecting a first connecting end (12 fig.2) of the first mold to a second connecting end (22 fig.2) of the second mold forming a molding surface, laying a composite 70 (comprising resin 71 and fibres 72) and a metal 80 on the base material, enclosing the first/second moulds with vacuum bagging film 40 and vacuuming pressing ...

Composite structures with stiffeners and method of making the same

INJECTION MOULDING PROCESS

A container comprising fibre material for a fibre-reinforced composite component

A method

Improved system and method for resin transfer moulding

A precured fibrous strip for a load-carrying structure for a wind turbine blade

A precured fibrous composite strip 50, 50’ for a load-carrying structure, such as a spar cap 40, for a wind turbine blade; the strip has first and a second longitudinal ends 51, 52; a first and second sides 53, 54 defining a width; and upper and lower surfaces 55, 56 defining a thickness. The strip comprises a chamfer region 60 at an end of the strip comprising: a primary chamfer 60a formed in the upper surface and a secondary chamfer 60b in the lower surface; wherein the chamfers are shaped so that the chamfer region has an asymmetric profile shape. Preferably, the chamfer lengths are different, with the primary chamfer length being at least 10% larger than the secondary chamfer; the double chamfer surfaces may have changing taper angles or may be shaped to be substantially plane, parabolic, spline-shaped or s-shaped chamfers. Preferably, the chamfer region has a blunt face with an end step thickness. The precured strip is preferably a pultruded strip with unidirectional fibres oriented ...

Process for the manufacture of armed plastic body.

PROCEDURE AND ARTICLE FOR FORMING A CONSTRUCTION UNIT BY TRANSFER POURING OF RESIN (R.T.M.), WHEREBY THE SHAPED PART CONTAINS AT LEAST PARTIAL A FIBER-REINFORCED LAMINATE

COPYING METHOD

EINSTÜCKIGER CO-HARDENING COMPOUND WINGS

PROCEDURE AND DEVICE FOR THE SUPPLY FROM POLYMER TO THE USE WITH VACUUM INFUSION

PROCEDURE FOR THE PRODUCTION OF A GRP COMPONENTS COMPONENT FOR AIRPLANES AND SPACESHIPS

DEVICE AND PROCEDURE FOR THE PRODUCTION OF FIBER-REINFORCED COMPOUND STRUCTURES

PROCEDURE, DEVICE AND SYSTEM FOR THE DISCOVERY OF A LEAKAGE DURING A VARTM PROCESS

PROCEDURE FOR THE USE OF A DUCTILE NUCLEAR BLOCK FOR A RESIN IMPREGNATION PROCESS, PROCEDURE FOR MANUFACTURING A COMPOUND STRUCTURE AND AFTERWARDS MANUFACTURE COMPOUND STRUCTURE

PROCEDURE FOR THE TREATMENT OF A BONDING MATERIAL

PROCEDURE FOR THE PRODUCTION OF A PROFILE FROM GRP COMPONENTS MATERIAL

Method and apparatus for consolidating a fibre composite structure

Es werden ein Verfahren und eine Vorrichtung (10) zur Konsolidierung einer Faserverbundstruktur (12) mit wenigstens einem thermoplastischen und/oder thermoelastischen Polymer beschrieben. Bei dem Verfahren wird die Faserverbundstruktur (12) zwischen zwei Presselementen (16, 18) einer Vorrichtung (10) zum Konsolidieren der Faserverbundstruktur (12) angeordnet. Die Presselemente (16, 18) werden so aufeinander zu gedrückt, dass die Faserverbundstruktur (12) zwischen den Presselementen (16, 18) gepresst wird. Die Faserverbundstruktur (12) wird zumindest bis in den Bereich einer Schmelztemperatur des wenigstens einen thermoplastischen und/oder thermoelastischen Polymers erwärmt. Die konsolidierte Faserverbundstruktur (12) wird nach dem Abkühlen aus der Vorrichtung (10) entnommen. Wenigstens ein separates Ausgleichselement (20) wird im Bereich wenigstens eines Höhensprungs (14) der Faserverbundstruktur (12) so zwischen der Faserverbundstruktur (12) und einem der Presselemente (16, 18) angeordnet ...

PROCEDURE FOR THE PRODUCTION OF A MULTI-CELLULAR VEHICLE CHASSIS AND THUS MANUFACTURE VEHICLE CHASSIS

RIM FOR BICYCLES OR MOTORFAHRRAEDER

RIM FOR BICYCLES OR MOTORFAHRRAEDER

FASERVERSTÄRKTES VERBUNDFORMTEIL

Faserverbundbauteil und Verfahren zur Herstellung

Faserverbundbauteil mit einem faserverstärkten Grundkörper (2) und einer am Grundkörper (2) angeordneten Funktionalstruktur (3), insbesondere einer Verstärkungsstruktur, wobei der Grundkörper (2) und die Funktionalstruktur (3) zumindest teilweise aus Kunststoff gefertigt sind, wobei zumindest ein Dorn (4) und/oder zumindest eine Stange (5) sowohl in den Grundkörper (2) als auch in die Funktionalstruktur (3) zumindest teilweise eingebettet sind.

PROCEDURE FOR THE PRODUCTION OF WIND TURBINE BLADES WITH COMPOSITE MATERIALS

PROCEDURE AND DEVICE FOR THE PRODUCTION OF SHAPED PARTS FROM HARDEN-CASH PLASTIC.

PROCEDURE AND DEVICE FOR THE PRODUCTION OF MOLDED ARTICLES

MANUFACTURING PROCESS OF CO-HARDENED STRUCTURES BY TRANSFER SYRINGES OF SYNTHETIC RESIN

TRANSPORTATION OF PASSENGERS VEHICLE BODIES

LARGE COMPOUND NUCLEAR STRUCTURES THE BY OF VAKUUMUNTERSTÜZTES TRANSFER SYRINGES ARE MANUFACTURED BY RESIN AND PROCEDURES

A woven carbon fiber fabric, a fiber reinforced plastic molding obtained by using the woven fabric, and a production method of the molding

CARBON LAYUP TAPE WITH FUGITIVE BINDER AND METHOD OF USE

Multifunctional mandrel end cap and method

MULTIFUNCTIONAL MANDREL END CAP AND METHOD A multifunctional mandrel end cap (100) for the fabrication of composite parts having an end cap core (104) operatively connected to a mandrel (105) and substantially sealed using a bonding agent (112) or end cap sheath (110). The end cap sheath (110) substantially encloses the end cap core (104) and seals engage perimeter sealing features of the end cap core (104). The end cap core (104) has a passageway (106) fluidly connecting the mandrel (105) with a vacuum source (108). The vacuum source (108) is engageable by a vacuum conduit (107) having one or more vacuum conduit perimeter sealing features (109). -100 112 --- 15 10Fig1A 101 1 2 100 --104 Fig. IB10 -200 Fig. 2A X,-200 101102 10 3 108 105 109- 1010 Fig. 2B ...

Structural integrated repair method and system tool device for repairing delaminated composite structures

STRUCTURAL INTEGRATED REPAIR METHOD AND SYSTEM TOOL DEVICE FOR REPAIRING DELAMINATED COMPOSITE STRUCTURES A system for repair of damaged holes (16) in composite structures (10) incorporates a repair system tool device (33) having a sleeve (34) sized to be closely received in a hole (16) in a composite structure (10). The sleeve (34) has a central bore for receiving parent resin and an array of orifices (36) for radial expulsion of the parent resin into the hole (16). A caul plate (62) seals the central bore and a vacuum bag (64) covering the caul plate (62) is sealed to the surface of the composite structure (10). Introduction of vacuum in the vacuum bag (64) provides a differential pressure for infusion of resin from the orifices (36) in the sleeve into delaminations (14) extending from the hole (16). Li34 - -33 FIG. 5B 36~ I "-=16 ...

Resin-soluble veils for composite article fabrication and methods of manufacturing the same

Embodiments of the invention are directed to resin- soluble thermoplastic veils for use in liquid resin infusion processes, methods of manufacturing resin-soluble thermoplastic veils for use in liquid resin infusion processes, and methods of manufacturing composite articles using resin-soluble thermoplastic veils for use in liquid resin infusion applications. The resin- soluble thermoplastic veils according to embodiments of the invention and of which function as a toughening agent in composites having the veil incorporated therein have improved characteristics including, but not limited to, increased uniformity and decreased thickness relative to prior art veils. These characteristics translate into improvements in the processing of a composite article including, but not limited to, a substantial or complete elimination in premature dissolution of the veil during cure. The resultant composite article also realizes improvements including, but not limited to, distribution evenness of the ...

Dry fibrous tape for manufacturing preform

A dry, fibrous tape for use in an automated placement process such as ATL or AFP and a preform produced therefrom. The preform is configured for resin infusion. The tape contains a layer of unidirectional fibers, at least one nonwoven veil bonded to one side of the fiber layer, and at least binding materials present within the tape. The preform produced from laying down such tape exhibits a low-bulk property that is close to the final thickness of the cured fiber- reinforced resin article and no further consolidation or compaction is required.

Method of controlling the temperature of a vacuum resin infusion process

Gravity feed resin delivery system

Process for the vacuum-assisted resin impregnation of reinforcing material with equalized pressure

METHOD OF PRODUCING A FIBRE REINFORCED JOINT AND FIBRE REINFORCED JOINT OBTAINED THEREBY

COMPOSITE AND METAL COMPONENT PRODUCTION, FORMING AND BONDING SYSTEM

A system for producing composite or bonded metal components including: first and second pressure chambers, each pressure chamber having an elastically deformable chamber wall; means for circulating fluid at an elevated temperature and pressure through each said pressure chamber; and at least one mould assembly including at least one separate mould section providing a mould cavity within which a composite or bonded metal lay-up can be located; wherein when the system is in use, the pressure chambers are held together with the elastically deformable chamber walls located in opposing relation, the at least one mould assembly containing a said lay-up being accomodated between the chamber walls while fluid at elevated temperature and pressure is circulated through each pressure chamber such that the lay-up can be compressed and cured or formed.

WIND TURBINE BLADE

The invention relates to a wind turbine blade comprising a number of pre- fabricated strips arranged in a sequence along the outer periphery. The strips consist of a fibrous composite material, preferably carbon fibres, and consist of a wooden material, preferably plywood or wooden fibres held in a cured resin. The advantage is that it is possible to manufacture blades for wind turbines which are very stiff and generally have a high strength, but which nevertheless are easy to manufacture and also is much cheaper to manufacture compared to conventional manufacturing techniques. The invention also relates to methods for manufacturing prefabricated strips and for manufacturing wind turbine blades.

METHOD OF PRODUCING A FIBRE REINFORCED STRUCTURE

A method of producing a fibre reinforced structure in which a fibre material is laid on a mould surface (1) resembling a negative image of the fibre reinforced structure to be pro-duced and in which a resin is infused and cured after the fi-bre material is laid on the mould surface (1) is provided. Layering the fibre material on the mould surface (1) com-prises a step of laying rovings (13) of the fibre material on the mould surface (1) or on a fibre material already laid on the mould surface (1) and applying an underpressure to a space between the rovings (13) and the mould surface (1).

METHOD AND APPARATUS FOR REWORKING STRUCTURES USING RESIN INFUSION OF FIBER PREFORMS

An area of a structure is reworked using resin infusion of a fiber preform. A resin flow hole is formed through the structure from a first side of the structure to a second side of the structure. The fiber preform is placed on the first side of the structure and substantially saturated with resin by flowing resin into the preform and out through the resin flow hole to the second side of the structure.

CONSTANT PRESSURE INFUSION PROCESS FOR RESIN TRANSFER MOLDING

Methods and apparatuses for making PMC's and composites include an infusing step wherein the resin reservoir and the preform are maintained under substantially the same vacuum pressure during the infusing step or the associated structure associated with the maintenance. Substantially the same vacuum pressure may be accomplished using a collapsible resin reservoir that is enclosed within or external to the vacuum bagging assembly of the fiber preform. This method results in a maximum achievable vacuum compaction pressure and simplified resin infusion process. This process may be used to manufacture prepregs and aerospace grade fiber reinforced resin composites, also disclosed herein, that have fiber volume, void content and laminate quality that meets or exceeds those made using an autoclave.

METHOD FOR MAKING AN ACOUSTIC ATTENUATION PANEL, IN PARTICULAR FOR AERONAUTICS

Procédé de fabrication d'un panneau d'atténuation acoustique dans lequel on prend au moins un pain de mousse (1), on enrobe au moins la face acoustique de ce pain de mousse :(1); d'un matériau composite frais (9), et on réalise des perforations (27; 27a, 27b, 27c, 27d, 27e) dans l'enrobage ainsi réalisé.

METHOD AND DEVICE FOR PRODUCING TUBE-SHAPED STRUCTURAL COMPONENTS

The present invention relates to a method for producing a tube-shaped structural component (100). A tube-shaped forming tool (102) having an inner forming surface corresponding to an outer surface (104) of the structural component (100) is provided. A carrier surface (108) of an expandable carrier (110), shaped so that it fills out the forming tool (102) in the non-expanded state while leaving an expansion distance between the carrier surface (108) and the forming surface (106), is covered with a hose-shaped fiber mass. After disposing the carrier (110) in the forming tool (102), the fiber mass (114) is pressed against the forming surface (106) by expanding the carrier (110) and infiltrated with a curable matrix (115). Another aspect of the invention relates to a device for producing a tube-shaped structural component.

METHOD OF AND APPARATUS FOR PRODUCING SHAPED BODIES OF REINFORCED SYNTHETIC RESIN

METHOD FOR FORMING COMPOSITE STRUCTURES HAVING SECTIONS EXTENDING IN DIFFERENT DIRECTIONS

METHOD AND APPARATUS FOR PRODUCING FIBRE COMPOSITE MOULDINGS BY MEANS OF VACUUM INFUSION

A METHOD FOR CASTING A COMPONENT AND A COMPONENT COMPRISING AT LEAST PARTLY OF FIBRE-REINFORCED PLASTIC LAMINATE

The invention relates to a method for casting a component comprising at least partly of fibre-reinforced plastic laminate by which the fibre-reinforcement (1) is arranged in a casting mould (30,31), wherein at least one venting duct (2) is placed, wherein said fibre-reinforcement (1) and said venting duct (2) are at least partly wetted by the plastic (57) during the casting process in such a way that venting is achieved through said venting duct (2), and wherein the surface of the venting duct (2) is at least partially made with a semi-permeable membrane that allows the passage of gases but does not allow or only slowly allows the passage of plastics. Furthermore the invention relates to a component comprising at least partly of fibre-reinforced plastic laminate, wherein the plastic laminate (57) inside comprises of one or more venting ducts (2), wherein the surface of a venting duct (2) is at least partially made with a semi--permeable membrane that allows the passage of gases but does ...

FAN BLADE FOR AN AXIAL FLOW FAN AND METHOD OF FORMING SAME

INNER INFLATABLE AND COLLAPSIBLE MOLD

RESIN BARRIER DEVICE, GASKET AND METHOD FOR INFUSING A PREFORM

Disclosed is a resin barrier device (1) for connection in a vacuum line, for use in resin infusion during composite manufacture. The resin barrier device includes a housing (3) having an inlet port (9) for connection to a resin source; and an outlet port (11) for connection to a vacuum source, and a flow path (13) extends between the inlet and outlet ports. A gas-permeable membrane (15) is disposed across the flow path (13) to prevent resin from flowing to the vacuum pump. Also disclosed is a gasket (17) for supporting the membrane (15), adapted to prevent resin leakage and a method of infusing a preform with a resin.

SYSTEM, VALVE, AND METHOD FOR LIQUID RESIN INFUSION

Described herein is a system for infusing liquid resin into a sheet of fibrous material. The system comprises a tool and a permeable media layer, configured to have the sheet therebetween. The system further comprises a non-permeable bladder configured to be sealed to the tool about the sheet of fibrous material and the permeable media layer such that the sheet of fibrous material and the permeable media layer are sealed between the non-permeable bladder and the tool. The system additionally comprises an inlet selectively fluidly coupleable with the permeable media layer to deliver liquid resin to the permeable media layer. The system also comprises an outlet selectively fluidly coupleable with the permeable media layer to create a pressure differential across the non-permeable bladder. The system further comprises a permeability control valve selectively operable to adjust the permeability of the permeable media layer.

APPARATUS AND METHOD FOR MANUFACTURING LIQUID MOLDED COMPOSITES USING A DISCRETE NETWORK OF TOOL SURFACE RESIN DISTRIBUTION GROOVES

A tool and its method of use, where a plurality of grooves and/or a channel are formed into the tool surface of the tool. The grooves and/or channel distribute and deliver resin supplied to the tool surface throughout a dry fiber composite layup positioned on the tool surface in resin infusion and resin transfer molding. The grooves are formed in the tool surface extending to discrete areas on the tool surface to direct a flow of liquid resin to the discrete areas and infuse the dry fiber composite layup with the liquid resin at those discrete areas of the tool surface. When a channel is formed in the tool surface, a perforated plate extends over the channel to prevent fibers from the preform from being pulled from the preform and into the liquid resin flowing through the channel.

SYSTEM AND METHOD FOR RESIN INFUSION

Among other things, the present invention provides a system and method for improved infusion of a fiber containing preform with a resin. The system comprises a mould base portion adapted to support the preform and a mould closure portion adapted to overlie the mould base portion in sealable relation to define a mould chamber containing the preform. One or more sensors are attached to the mould base portion and/or to the mould closure portion for monitoring flow characteristics of the resin within the mould chamber. A control means responsive to the sensing means is operatively connected to a resin pump and to a vacuum pump for varying the flow of resin within the mould chamber by varying either or both of the volumetric flow rate of the resin and the level of vacuum within the mould chamber to control infusion of the preform.

FORMING-MOLDING TOOL AND PROCESS FOR PRODUCING PREFORMS AND FIBER REINFORCED PLASTICS WITH THE TOOL

A shaping mold for the resin transfer molding of fiber-reinforced plastic s which comprises a face plate forming a hollow convex portion and a flat pl ate which are unified, wherein a metal pipe serving as a passageway for a he ating medium is integrated with the mold on the back of the face plate by th e use of a heat-conducting material and rubber round bars are integrated the rewith outside the region of the flat plate to be used in shaping or molding . This shaping mold enables uniform heating of a laminate of reinforcing fib er base material with high accuracy.

METHOD FOR PRODUCING A FIBRE COMPOSITE COMPONENT FOR AEROSPACE

The invention relates to a method and a moulding core for producing a fib re composite component (34), in particular in aerospace, comprising the foll owing method steps: introducing a core sleeve (9) into a moulding tool (2) f or establishing an outer geometry of a moulding core (27) to be formed; fill ing the core sleeve (9) that is introduced with a vacuum-fixable filling mat erial (21); applying a vacuum to the core sleeve (9) and consequently vacuum -fixing the filling material (21) for forming the moulding core (27); and at least partly laying at least one semifinished fibre product (33a, 33b) on t he moulding core (27) that is formed, for the shaping of the fibre composite component (34) to be produced.

METHOD AND APPARATUS FOR PROVIDING POLYMER TO BE USED AT VACUUM INFUSION

Composite structures having integrated stiffeners with smooth runouts and method of making the same

A unitized composite structure comprises a composite member having at least one integrally formed composite stiffener. At least one end of the stiffener includes a runout forming a substantially smooth transition between the stiffener and the composite structure.

Vacuum Infusion Adhesive and Methods Related Thereto

An adhesive adapted to enable spray delivery and seamless polymerization during epoxy resin vacuum infusion techniques.

Method and mould for moulding a wind turbine blade

A mould for moulding a wind turbine blade using a reinforcing material and a matrix material is provided. The mould includes a solid non-stick lining, and wherein the material properties of the non-stick lining are chosen to prevent a matrix material from bonding with the non-stick lining of the mould. A method of moulding a wind turbine blade in a mould is also provided. The method includes applying a solid non-stick lining to an inside surface of the mould, assembling a reinforcement material lay-up for the wind turbine blade on the non-stick lining, distributing a matrix material through layers of the reinforcement material lay-up, performing curing steps to harden the matrix material, and subsequently removing the cured wind turbine blade from the mould.

Method of manufacturing an oblong shell part and such shell part

A plurality of fibre layers is stacked to form a fibre insertion extending in a longitudinal direction of the shell part to be manufactured, whereby a core element having a tapered edge section is arranged along the fibre insertion. The fibre layers are stacked so that the tapered edge section of the core element is wedged into the fibre insertion. The core element is composed by a first and a second core part that are arranged along each other. The first core part forms at least part of the tapered edge section of the core element. The surface of the first core part has a higher permeability to liquid polymer than that of the surface of the second core part so that, during infusion, liquid polymer penetrates the surface of the first core part more readily than it penetrates the surface of the second core part.

Cure tool with integrated edge breather and method of making the same

A tool for curing a composite layup comprises a tool body having a surface adapted to support a composite layup thereon. The tool includes an integrated breather for allowing removal of air from the layup during curing.

Infusion method and a system for an infusion method

Disclosed is an infusion method for the manufacture of a fibre-reinforced composite component with semi-finished textile products in an open moulding tool, in which at least one local gas reception space is designed for the reception of volatile substances, such as resin gases and residual air contained in the matrix material and/or in the system, which gas reception space is blocked off from the matrix material by a local semi-permeable membrane; also disclosed is a system for the execution of such a method.

Infusion method and flow aid

Disclosed is an infusion method for the manufacture of a fibre-reinforced composite component with a flow promoter 18 , wherein the flow velocity of the matrix material in a component 22 to be infiltrated is modified by means of the flow promoter 18 ; also disclosed is a flow promoter 18 , which has an integral body section 20 for the modification of the flow velocity.

Wind turbine rotor blade having a heating element and a method of making the same

The invention relates to a wind turbine rotor blade having a blade root, a blade tip, two interconnected rotor blade half shells, which include a fiber-reinforced plastics material, and an electrical heating element, which is arranged on an outer side of the rotor blade and has a blade root end and a blade tip end, wherein the blade tip end is connected via an electrical line leading to the blade root and at least a first segment of the electrical line, which is arranged on an inner side of one of the rotor blade half shells, is made of a carbon fiber material. Further, the present invention relates to a method for making a wind turbine rotor blade having an electrical heating element.

METHOD OF MANUFACTURING A TURBINE BLADE, SYSTEM FOR MANUFACTURING A TURBINE BLADE, INTERMEDIATE MEMBER FOR MANUFACTURING A TURBINE BLADE, AND TURBINE BLADE MANUFACTURED BY MEANS OF THE AFOREMENTIONED METHOD

A method of manufacturing a turbine blade is provided. The described method includes providing an elongate core, surrounding the elongate core with a textile structure, arranging the elongate core surrounded by the textile structure in a mold, pressing at least a part of the textile structure against the mold, and injecting a curing agent into the mold to interact with the textile structure, thereby forming the turbine blade. Also, a system and an intermediate member for manufacturing a turbine blade by means of the described method is provided. 1. A method of manufacturing a turbine blade , comprising:providing an elongate core;surrounding the elongate core with a textile structure;arranging the elongate core surrounded by the textile structure in a mold;pressing at least a part of the textile structure against the mold; andinjecting a curing agent into the mold to interact with the textile structure, thereby forming the turbine blade.2. The method as set forth in claim 1 , wherein the textile structure is woven around the elongate core by means of a 3D weaving process.3. The method as set forth in claim 1 , wherein the textile structure is formed by wrapping a textile sheet around the elongate core.4. The method as set forth in claim 1 , wherein the textile structure is cylindrical.5. The method as set forth in claim 4 , wherein the textile structure comprises a plurality of layers claim 4 , the plurality of layers comprising an inner layer and an outer layer which surrounds the inner layer.6. The method as set forth in claim 5 , wherein each of the plurality of layers comprises a specific textile material or a spacer material.7. The method as set forth in claim 5 , wherein the composition of material for at least one of the plurality of layers is varied along the longitudinal axis and/or the circumference of the substantially cylindrical structure.8. The method as set forth in claim 5 , wherein the textile structure is integrally formed.9. The method as set forth ...

Sensor arrangement and method for monitoring an infusion process

A sensor arrangement for monitoring an infusion process in a flow channel and a method for monitoring an infusion process in a flow channel are described. The sensor arrangement includes a pressure sensor with a sensor interface and a plug. The plug has an inner cavity with an inlet and an outlet. The inlet of the plug is in flow connection with the flow channel and the outlet of the plug is located at the sensor interface.

Method of manufacturing resin infused composite parts using a perforated caul sheet

Resin infused composite parts are fabricated using a caul sheet having perforations therein for optimizing the flow of resin through the parts. The method allows for a simplified tooling and consumable arrangement for complex parts while achieving a smooth, aerodynamic caul-side or bag-side finish. The component may be placed in direct contact with a tool, and the caul sheet may be placed in direct contact with the component thereby eliminating the necessity for consumables between these items.

Hybrid matrix for fiber composite materials

A fiber composite material obtainable by (a) mixing the components of a multi-component agent immediately before use, wherein component A of the multi-component agent contains at least one compound having two or more isocyanate groups, component B of the multi-component agent contains at least one compound which has at least two reactive groups selected from hydroxyl groups, thiol groups, primary amino groups and secondary amino groups and is simultaneously free from epoxy groups, and at least one of the components of the multi-component agent contains at least one epoxide prepolymer, (b) introducing the resulting application preparation into a mold in which fibers and optionally further additives are present, the resulting mixture containing at least one latent hardener for epoxide prepolymers, (c) pre-curing the resulting mixture at a temperature from 5° C. to 90° C., and (d) then finally curing the pre-cured fiber composite material at temperatures from 100° C. to 240° C., wherein the fiber composite material being removed from the mold after step (c) or step (d).

Composite Structural Member

An inflatable mold assembly for forming a hollow composite construction member that is suitable for use as a building material has a longitudinal axis. The mold assembly further has a flexible, substantially tubular bladder wall defining an elongated inflatable cavity. A reinforcing fabric is positioned concentrically around the flexible bladder wall. A flexible air-impervious outer layer is positioned concentrically around the fabric, with the bladder wall and the outer layer defining an elongated annular space, and with the fabric being positioned within the elongated annular space.

Process for producing sandwich elements

The present invention relates to processes for producing sandwich elements, where the sandwich elements comprise a rigid polyurethane foam as core foam surrounded entirely or to some extent by a plastics resin comprising reinforcing-agent layers, by producing the rigid polyurethane foam on the reinforcing-agent layers and then saturating the reinforcing-agent layers in a liquid resin and hardening the resin. The present invention further relates to sandwich elements that can be produced by a process of the invention, and also to the use of these sandwich elements as wind-turbine blade, aircraft wing, wind-turbine nacelle, boat-hull, or housing for vehicles.

Wind turbine blade part manufactured in two steps

A method of manufacturing a portion of a wind turbine blade is described. The method comprising the steps of: laying up a primary fibre material in a mould; infusing said primary fibre material with a primary resin; substantially curing said primary resin in said primary fibre material to form a cured blade element; laying up a secondary fibre material on top of at least a portion of said cured blade element; infusing said secondary fibre material with a secondary resin different to said primary resin, wherein said secondary resin has a higher strength level than said primary resin; and curing said secondary resin in said secondary fibre material to form an integrated reinforced section on said cured blade element.

Method for Forming Contoured Composite Laminates

A composite prepreg laminate such as a hat type-stringer is formed on a contoured mandrel using a combination of mechanical sweeping and vacuum forming. 137-. (canceled)38. A method of forming a composite prepreg laminate , comprising:placing at least one prepreg ply on a contoured mandrel;mechanically sweeping the prepreg ply over a first section of the contoured mandrel; andvacuum forming the prepreg ply over a second section of the contoured mandrel.39. The method of claim 38 , wherein vacuum forming the prepreg ply is performed after the mechanically sweeping.40. The method of claim 38 , further comprising:clamping a third section of the prepreg ply on the contoured mandrel.41. The method of claim 38 , wherein:placing at least one prepreg ply includes placing a plurality of prepreg plies on the contoured mandrel;the mechanically sweeping includes mechanically sweeping the plurality of prepreg plies over the first section of the contoured mandrel; andthe vacuum forming includes vacuum forming all of the prepreg plies as a group over the second section of the contoured mandrel after the mechanical sweeping.42. The method of claim 38 , wherein mechanically sweeping the plies includes:contacting the prepreg ply with opposing sets of fingers,pressing the prepreg ply against the second section of the mandrel using the opposing sets of fingers, anddisplacing the opposing sets of fingers as the opposing sets of fingers are pressing the prepreg ply against the second section of the mandrel.43. The method of claim 42 , further comprising:using the opposing sets of mechanical fingers to hold the prepreg ply against the mandrel while the prepreg ply is being vacuum formed over the second section of the mandrel.44. The method of claim 38 , wherein mechanically sweeping the prepreg ply is performed using a plurality of forming heads claim 38 , and the method further comprises aligning each of the forming heads with the contoured mandrel.45. The method of claim 38 , wherein ...

Collection of Process Data Using In-Situ Sensors

A system is provided for collecting data during vacuum molding of a composite part using a mold including an air tight, flexible membrane sealed to a tool. The system comprises a plurality of MEMS sensors coupled with the interior of the mold at different locations over the part. Each of the sensors produces signals related to a process parameter, such as pressure within the bag, that is sensed at the location of the sensor. 125-. (canceled)26. A system for molding a composite layup inside an autoclave , comprising:a mold tool;a vacuum bag sealed to the mold tool and having a plurality of openings therein at different sensing locations on the vacuum bag;a plurality of first MEMS vacuum pressure sensors attached to the vacuum bag and respectively coupled through the openings to the interior of the vacuum bag;at least one opening in the mold tool;a second pressure sensor mounted within the opening in the mold tool and configured to sense either a vacuum pressure or a fluid pressure inside the mold; anda processor configured to be placed inside the autoclave and to collect and process the pressures sensed by the first and second sensors.27. The system of wherein the processor further comprises a wireless transmitter configured to wirelessly transmit sensor data.28. The system of further comprising at least one additional sensor at least partially embedded within at least one of a caul claim 26 , a breather claim 26 , a peel ply claim 26 , a seal claim 26 , and the composite layup.29. The system of further comprising at least one additional sensor disposed inside the mold claim 26 , positioned between the vacuum bag and the composite layup.30. The system of further comprising at least one additional sensor embedded within the composite layup.31. An apparatus for molding a composite layup claim 26 , comprising:a mold including a mold tool and a vacuum bag configured to cover the composite layup, the mold tool including a breather;at least one sensor embedded in the ...

METHOD AND MOULD SYSTEM FOR NET MOULDING OF A CO-CURED, INTEGRATED STRUCTURE

The present invention relates to a mould system and a method for net moulding of a co-cured integrated structure () comprising a skin () provided with stringers () and rib feet () and with a gap () between the stringers () and the rib feet (). The mould system comprises a substantially rectangular frame () made of a low heat expanding material, a number of substantially rectangular boxes () made of a heat expanding material, connection plates () made of a heat expanding material and fastening means (). By means of the connection plates () the gap () is obtained. A moulding assembly () is created by applying prepregs to the surfaces of the boxes (), by connecting the boxes () to each other and by surrounding the connected boxes () with the frame (). The moulding assembly () is treated in a conventional way in an autoclave in order to cure the structure (). Thereafter the frame (), the boxes () and the connection plates () are removed. 19-. (canceled)102642642. A mould system for net moulding of a co-cured structure comprising a skin () provided with at least two stringers () and at least one rib foot () and a gap () between the stringers () and the at least one rib foot () , the mould system comprising:{'b': 12', '12', '54', '54', '56', '56, 'a substantially rectangular frame () made of a low heat expanding material, the frame () comprising a first longitudinal frame part (A), a second longitudinal frame part (B), a first transversal frame part (A) and a second transversal frame part (B);'}{'b': 20', '20, 'claim-text': [{'b': 18', '8, 'claim-text': [{'b': 8', '30', '46', '46', '44', '44, 'each box () has a bottom (), a first longitudinal side wall (A), a second longitudinal side wall (B), a first transversal side wall (A) and a second transversal side wall (B); and'}, {'b': 8', '18', '44', '44, 'the at least two boxes () in the row () are positioned such that the first transversal side wall (A) of a first box is facing the second transversal side wall (B) of a second ...

BED BOARD COMPOSED OF BASALT FIBERS FOR A DIAGNOSTIC BED OF A MEDICAL APPARATUS, AND METHOD FOR MANUFACTURING A BED BOARD

A bed board for a diagnostic bed of a medical examination apparatus is formed in a material that includes basalt fibers. The bed board may have a bed board body composed of basalt fibers and a filler in a predetermined ratio, or may be formed by a hollow shell, composed of basalt fibers and a binder in a predetermined ratio, with the hollow shell being filled by a filler material. 1. A bed board for a diagnostic bed of a medical examination apparatus , said diagnostic bed comprising a bed frame and a drive device , said bed board comprising:a bed board body having a size and shape that fits within said bed frame so as to allow said bed board body to be driven relative to the bed frame by the driving device; andsaid bed board body being comprised of a material that includes basalt fibers.2. A bed board as claimed in wherein said material comprises basalt fibers bound with a binder in a predetermined ratio.3. A bed board as claimed in wherein said bed board body comprises a shell and a lightweight filler claim 1 , said shell being comprised of basalt fibers bound with a binder in a predetermined ratio claim 1 , and said interior of said shell being hollow and being filled with the lightweight filler.4. A diagnostic bed for a medical apparatus claim 1 , said diagnostic bed comprising:a supporting device;a bed frame that supports said supporting device;a bed board situated in said bed frame and supported by said supporting device;a driving device that drives the bed board so as to move relative to the bed frame; andsaid bed board being comprised of a material that includes basalt fibers.5. A bed board as claimed in wherein said material comprises basalt fibers bound with a binder in a predetermined ratio.6. A bed board as claimed in wherein said bed board comprises a shell and a lightweight filler claim 4 , said shell being comprised of basalt fibers bound with a binder in a predetermined ratio claim 4 , and said interior of said shell being hollow and being filled with ...

METHOD AND SYSTEM FOR PRODUCING AN AT LEAST TWO-LAYER COMPOSITE SERVING AS A LINING FOR A VEHICLE INTERIOR COMPONENT

A method for manufacturing a composite includes providing a first template including a cutout for a first layer of the composite, disposing the first layer in the cutout, and disposing a tablet, provided with an adhesive, on the first layer such that the first layer adheres to the tablet. Next, the tablet is removed, together with the first layer adhered thereto, from the cutout, and an adhesive is applied to a side of the first layer facing away from the tablet. A second template is provided that includes a cutout for a second layer of the composite, and then the second layer is disposed in the cutout. The tablet, together with the first layer adhered thereto, is disposed on the second layer disposed in the cutout of the second template, and the tablet is removed, together with the composite produced from the first and second layers, from the second template. 1. A method for manufacturing an at least two-layer composite cladding for a vehicle interior component , the method comprising:providing a first template including a cutout for a first layer of the at least two-layer composite;disposing the first layer in the cutout of the first template;disposing a tablet provided with an adhesive on the first layer disposed in the cutout, and in the cutout of the first template, such that the first layer adheres to the tablet;removing the tablet, together with the first layer adhered to the tablet, from the cutout of the first template, and applying an adhesive to a side of the first layer facing away from the tablet;providing a second template including a cutout for a second layer of the at least two-layer composite;disposing the second layer in the cutout of the second template;disposing the tablet together with the first layer, and provided with the adhesive, on the second layer disposed in the cutout of the second template, and in the cutout of the second template; andremoving the tablet together with the at least two-layer composite produced from the first and second ...

COMPOSITE MATERIAL MANUFACTURING METHOD AND COMPOSITE MATERIAL

An object is to provide a composite material manufacturing method for improving interlayer strength. The present disclosure provides a composite material manufacturing method of laminating a plurality of prepregs () formed of a fiber reinforced base material impregnated with an uncured matrix resin and performing hot molding, the method including: using the prepregs () each provided with a gap layer () that does not contain a resin and is continuous in an in-plane direction and resin layers () disposed on both surfaces of the gap layer; disposing a plurality of short fibers () on facing surfaces of the prepregs () that are adjacent to each other; and evacuating the laminated prepregs () to degas the gap layer () and then performing hot molding. 1. A composite material manufacturing method of laminating a plurality of prepregs formed of a fiber reinforced base material impregnated with an uncured matrix resin and performing hot molding , the method comprising:using the prepregs each provided with a gap layer that does not contain a resin and is continuous in an in-plane direction and resin layers disposed on both surfaces of the gap layer;disposing a plurality of short fibers on facing surfaces of the prepregs that are adjacent to each other; andevacuating the laminated prepregs to degas the gap layer and then performing hot molding.2. The composite material manufacturing method according to claim 1 , wherein the plurality of prepregs are laminated such that surfaces on a same side are directed in a same direction.3. The composite material manufacturing method according to claim 1 , wherein in a case in which thicknesses of the resin layers disposed on both the surfaces of the gap layer are different from each other claim 1 , the plurality of prepregs are laminated such that a thinner resin layer is directed upward in a lamination direction.4. The composite material manufacturing method according to claim 1 , wherein the matrix resin contained in the resin layers ...

VACUUM PRESSURIZED MOLDING

A system for forming a composite component includes a close mold tool defining a cavity that corresponds to a shape of the composite component and configured to receive a composite material. The system further includes a perforated release film defining a plurality of openings and configured to be positioned on a surface of the composite material within the cavity. The system further includes a breather configured to be positioned on the perforated release film, to allow a vacuum to be applied to the composite material through the breather and the plurality of openings, and to allow pressurized fluid to be applied to the perforated release film through the breather. 1. A system for forming a composite component , comprising:a close mold tool defining a cavity that corresponds to a shape of the composite component and configured to receive a composite material;a perforated release film defining a plurality of openings and configured to be positioned on a surface of the composite material within the cavity; anda breather configured to be positioned on the perforated release film, to allow a vacuum to be applied to the composite material through the breather and the plurality of openings, and to allow pressurized fluid to be applied to the perforated release film through the breather.2. The system of claim 1 , wherein the close mold tool further defines a passageway in fluid communication with the cavity and configured to allow the vacuum and the pressurized fluid to be applied to the breather and the perforated release film.3. The system of claim 2 , further comprising a vacuum source configured to be coupled to the passageway and configured to apply the vacuum to the cavity.4. The system of claim 2 , further comprising a pressurized fluid source configured to be coupled to the passageway and configured to apply the pressurized fluid to the cavity.5. The system of claim 4 , wherein the pressurized fluid source is configured to apply pressurized air to the cavity.6. ...

Production Method for a Fiber Composite Component, Fiber Composite Component, Test Method for a Fiber Composite Component, Computer Program, Machine-Readable Storage Medium and Device

A method for producing a fiber composite component is disclosed. A sensor device having a flexible circuit carrier and/or a sensor module is integrated in the fiber composite component. The method comprises: loading a tool configured to produce the fiber composite component with textile layers and the sensor device; closing the loaded tool and compressing the textile layers and the sensor device; introducing a liquid matrix into the closed tool and impregnating the textile layers to produce the fiber composite component; detecting an acceleration in relation to the closing of the tool and/or the introducing of the liquid matrix, using at least one of the sensor device and the sensor module of the sensor device; and determining a process state and/or a process parameter based on a spectral analysis of the detected acceleration in a frequency domain.

METHODS AND DEVICES FOR COUPLING SOLAR PANEL SUPPORT STRUCTURES AND/OR SECURING SOLAR PANEL SUPPORT STRUCTURES TO A ROOF

A mounting unit for mounting a solar panel on a roof includes a base having a first flange and a second flange that extend laterally from the base and a mounting surface positioned above the base via walls that connect the mounting surface and the base. The mounting surface is couplable with the solar panel to elevate and orient the solar panel above a surface of the roof. The mounting unit also includes a flexible membrane material that is coupled with the first flange of the base and that extends laterally therefrom. The mounting unit further includes an adhesive or tape that is applied to an underside of the second flange so that the second flange is free of the flexible membrane material. The flexible membrane material is couplable with the roof and the adhesive or tape is adherable to the roof to secure the mounting unit to the roof. 1. A method of attaching a solar panel mounting unit to a roof comprising: a base that includes a first flange and a second flange that extend laterally from the base;', 'a mounting surface positioned above the base via walls that connect the mounting surface and the base, the mounting surface being couplable with a solar panel to elevate the solar panel above a surface of the roof and angle the solar panel relative thereto;', 'a flexible membrane coupled with the first flange of the base and extending laterally therefrom; and', 'an adhesive or tape applied to an underside of the second flange, the second flange being free of the flexible membrane material;, 'providing a solar panel mounting unit havingcoupling the flexible membrane material with the roof to secure the solar panel mounting unit to the roof; andadhesively bonding the adhesive or tape with the roof to additionally secure the mounting unit to the roof.2. The method of claim 1 , further comprising:coupling the flexible membrane material with only the first flange of the base; andapplying the adhesive or tape with an underside of at least one other flange of the base ...

FABRICATION OF COMPLEX-SHAPED COMPOSITE STRUCTURES

A hot drape-forming method for shaping fibrous preforms and prepreg plies into complex geometries. For shaping fibrous preforms, the hot drape-forming method includes: a) dividing the total number of preforms into a plurality of sub-preforms (S, S, S); and b) consecutively shaping each sub-preform (S, S, S) by applying vacuum pressure and heat, wherein the shaping of all sub-preforms (S, S, S) are carried out in the same tool housing () over the same molding surface. The resulting shaped preform (S, S, S) is ready for resin infusion. The same method can also be used to shape resin-impregnated prepreg plies. 1. A shape forming method for fabricating a fibrous preform with three-dimensional configuration , comprising:(a) providing a tool housing with a mold positioned therein, said mold having a non-planar molding surface;(b) placing a first moldable sub-preform over the molding surface;(c) attaching a first flexible diaphragm to the tool housing so as to define a sealed chamber bounded by the first diaphragm and the tool housing and to enclose the first sub-preform and the mold in said sealed chamber;(d) enclosing a second moldable sub-preform between the first diaphragm and a second flexible diaphragm, which is placed above the first diaphragm, the first and second diaphragms defining an air-tight sealed pocket;(e) applying heat to the sub-preforms;(f) evacuating air from the sealed chamber bound by the first diaphragm and the tool housing until a vacuum pressure is reached such that the first diaphragm is pulled toward the molding surface, causing the first sub-preform to conform to the molding surface, thereby forming a first shaped sub-preform, and concurrently with evacuating air from the sealed chamber, venting the sealed pocket between the first and second diaphragms to atmospheric pressure to prevent the second diaphragm from being pulled toward the molding surface at the same time;(g) evacuating air from the sealed pocket between the first and second ...

COMPOSITE MATERIAL PACKAGED FIBER GRATING SENSOR AND MANUFACTURING METHOD THEREOF

A composite material packaged fiber grating sensor and a manufacturing method thereof. The sensor includes a fiber grating sensor component, a composite material coverage layer, a resin package layer and a composite material substrate layer. In the sensor, a temperature fiber grating and a strain fiber grating are packaged in a composite material structure, so that the structure is light and simple, its computability with the composite material is good, the measurement accuracy is high, and the survival rate and the service life of the installed sensor can be greatly improved, the sensor component can be externally pasted on to or inter-implanted in a composite material structural part, and can be applied to the distributed online health monitoring on the structural part. The manufacturing method of the composite material packaged fiber grating sensor is simple, efficient and stable, and is suitable for rapid mass production by enterprises. 1. A composite material packaged fiber grating sensor , comprising a fiber grating sensor component , a composite material coverage layer , a resin package layer and a composite material substrate layer , wherein the composite material coverage layer and the composite material substrate layer form a shell wrapping the resin package layer;the fiber grating sensor component comprises an optical fiber, one end of the optical fiber is connected with an optical fiber connector, a temperature fiber grating is arranged at the outermost of the other end of the optical fiber, a plurality of strain grating grid are engraved in the optical fiber on one end close to the temperature fiber grating, the temperature fiber grating and a strain fiber grating are arranged in series, and the optical fiber is smooth and is not bent; andwherein a part of fiber grating sensor component is arranged on the composite material substrate layer, and the part of fiber grating sensor component at least comprises the temperature fiber grating and the strain ...

NANO-CONDUCTIVE RUBBER SENSING UNIT AND PREPARATION METHOD THEREFOR

The present invention discloses a nano-conductive rubber sensing unit and a preparation method therefor, which belong to the technical field of pressure measurement. The nano-conductive rubber sensing unit of the invention comprises at least two fabric layers, wherein nano-conductive rubber is filled between every two adjacent fabric layers, and the nano-conductive rubber is a rubber matrix in which carbon nanotubes are dispersed. The preparation method for the nano-conductive rubber sensing unit of the invention comprises: S1, mixing a rubber matrix with carbon nanotubes in accordance with a mass proportion so as to make a nano-conductive rubber slurry; S2, laying flat one fabric layer, spreading the nano-conductive rubber slurry prepared in S1 over the fabric uniformly to a certain thickness, and then, laying flat the other fabric layer thereon; and S3, pressurizing and heating the nano-conductive rubber sensing unit prepared in S2 to cure the same. The nano-conductive rubber sensing unit of the invention achieves the technical effects of a large measuring range of pressure measurement, high sensitivity in the measuring range and good linearity of a piezoresistance characteristic curve, and can meet the requirement of a sheet type. 1. A nano-conductive rubber sensing unit , comprising two or more fabric layers , wherein:a nano-conductive rubber is sandwiched between each two adjacent fabric layers;fiber texture gaps of the fabric layers are filled with the nano-conductive rubber;the nano-conductive rubber is a rubber matrix in which carbon nanotubes are uniformly dispersed;the carbon nanotubes are multi-wall carbon nanotubes;the thickness of the nano-conductive rubber is not less than 1 mm;the nano-conductive rubber is a slurry before curing;the fabric layers comprise fabric and yarns;the yarns located at two sides of the sensing unit act as electrodes; andthe fabric layers are added as a strengthening frame of the nano-conductive rubber sensing unit.2. (canceled) ...

Vacuum desorption, impregnation and curing system, vacuum desorption device, and vacuum desorption process for protective layer of magnetic pole

A process and process apparatus for forming a protective coating on a magnetic pole of a permanent magnet motor. The process for forming a protective coating on a magnetic pole of a permanent magnet motor includes: horizontally placing a motor rotor, and controlling to perform, at positions of an inlet and an outlet operating on a vacuum bag in a current state, vacuumization and adhesive injection only on an arc section located at the bottom of the motor rotor; and driving the motor rotor to rotate by a predetermined angle after the adhesive in the arc section is initially cured so as to rotate the next arc section in which no adhesive is injected to the bottom, until all arc sections in the circumferential direction of the motor rotor are injected with the adhesive.

FIBER-REINFORCED COMPOSITE ARTICLES MADE FROM FIBERS HAVING COUPLING-INITIATOR COMPOUNDS AND METHODS OF MAKING THE ARTICLES

Methods of making a fiber-reinforced composite article are described. The methods may include providing fibers to an article template, where the fibers have been treated with a coupling-initiator compound. They may further include providing a pre-polymerized mixture that includes a monomer and a catalyst to the article template. The combination of the fibers and the pre-polymerized mixture may be heated to a polymerization temperature where the monomers polymerize around the fibers and form at least a portion of the composite article. The article may then be removed from the article template. Examples of the fiber-reinforced composite articles may include wind turbine blades for electric power generation. 1. A method of making a fiber-reinforced composite article , the method comprising: {'br': None, 'sub': 'n', 'S—X—(I)'}, 'providing fibers to an article template, wherein the fibers have been treated with a coupling-initiator compound and the coupling-initiator compound has the formula n is an integer having a value between 1 and 5,', 'S comprises a silicon-containing coupling moiety through which the coupling-initiator compound bonds to a substrate surface on the fibers,', 'X comprises a linking moiety to link the S moiety with the one or more I moieties,', {'sub': 'n', '(I)comprises one or more polymerization initiator moieties,'}, 'each of the initiator moieties is capable of initiating a polymerization of a monomer at the polymerization temperature, and', 'each of the initiator moieties is the same or different;, 'whereinproviding a pre-polymerized mixture comprising the monomer and a catalyst to the article template;heating a combination of the fibers and the pre-polymerized mixture to a polymerization temperature where the monomers polymerize around the fibers and form at least a portion of the composite article, wherein the portion of the composite article comprises a thermoplastic polymer; andremoving the composite article from the article template.2. ( ...

A method of manufacturing a shear web using a pre-formed web foot flange

A method of manufacturing a wind turbine blade component in form of a shear web is described. The method comprising the steps of: a) providing a pre-manufactured shear web body having a first side and a second side as well as a first end and a second end; b) providing a first pre-formed web foot flange comprising a fibre-reinforcement material; c) arranging a first fibre layer from the first pre-formed web foot flange and to a part of the first side of the shear web body; d) arranging a second fibre layer from the first pre-formed web foot flange and to a part of the second side of the shear web body; e) supplying a resin to said first fibre layer and second fibre layer simultaneous with or subsequent to steps c) and d); and f) allowing the resin to cure so as to form the shear web.

Multi-Matrix Composite Prosthetic Socket and Methods of Fabrication

A multi-matrix composite socket includes struts formed from a first matrix composite and inner and outer layers relative to the struts formed from at least a second matrix composite. Each matrix composite is comprised of fibers embedded in a resin. The fibers create spaces into which a flowable resin infuses during manufacturing and also reinforce the resin. A base and a plurality of struts are assembled and positioned over a first fabric layer and a second fabric layer is positioned over the struts. A resin is infused into the spaces defined by the first and second fabric layers and around the struts to form an over-molded multi-composite matrix socket. 1. A method of manufacturing a prosthetic socket for a residual limb of a patient , comprising:a) providing a structural frame having a first modulus, the structural frame comprised of a first matrix of a first thermoplastic resin and first fibers;b) providing a mold of the residual limb;c) positioning an inner layer of second fibers onto the mold;d) positioning the structural frame onto the mold over the layer of second fibers;e) positioning an outer layer of third fibers onto the mold over the structural frame; andf) causing a thermoplastic second resin to flow within the second and third fibers and around the structural frame to form a composite matrix including the inner layer, the first matrix of the structural frame, the outer layer and the second resin.2. The method of claim 1 , wherein providing the structural frame includes assembling the structural frame from a base and a plurality of struts.3. The method of claim 2 , wherein both of the base and the struts are made from the first matrix.4. The method of claim 1 , further comprising placing a vacuum bag over the outer layer of third fibers claim 1 , and wherein the causing the second resin to flow includes applying negative pressure at an interior of the vacuum bag.5. The method of claim 1 , wherein before causing the second resin to flow claim 1 , further ...

Method and system for manufacturing a shear web for a wind turbine

The present invention relates to a method and to a mould system ( 70 ) for manufacturing a shear web for a wind turbine blade as well as to a backing plate ( 66 ) for such method and mould system. The method involves arranging one or more fibre layers on top of a web mould part ( 61 ), arranging backing plates ( 66 ) at each end to create a mould cavity between the first and second backing plate ( 66, 68 ) and the web mould part ( 61 ). Each backing plate ( 66, 68 ) comprises an inner moulding surface ( 80 ), outer surfaces ( 98, 100 ) and a channel ( 82 ) or groove ( 83 ) extending between at least one of the outer surfaces ( 98, 100 ) and the inner moulding surface ( 80 ). Resin is supplied to the mould cavity via each channel or groove of the first and second backing plate ( 66, 68 ), and subsequently the resin is cured or hardened to form the shear web.

Method of Designing and Producing Connecting Rods formed of Fiber Composite Material

A method of designing and producing a connecting rod using chopped carbon fiber pre-impregnated composite material is provided. The method allows connecting rod designers to machine several different connecting rod designs, lengths, and beams. The connecting rod is first cast, forged or otherwise shaped in a basic form, and then machined into a specific connecting rod. After the specific machining is performed, the big-end and small-end bosses are bored, bolt holes drilled, and then all surfaces are finished or machined. The starting material is preferably a chopped fiber or woven fiber composite, and the connecting rods are then plated to seal carbon fiber based materials and the big-end rod bearing inserts are placed along with the rod's small-end bushing. In one embodiment interlocking serrations are machined onto opposing surface faces of the two halves of the rod, allowing the cap and beam to be aligned without requiring special alignment dowels, yet forming a unitary, and stronger rod assembly. The finished machined connecting rod pieces, then rods are plasma coated with anti-friction material(s), for example are plasma-nitrided.

Resin Flow Member for a Vacuum Assisted Resin Transfer Moulding Process

The disclosure relates to a fibre reinforced plastic composite material, including a vacuum assisted resin transfer moulded fibre reinforced plastic laminate prepared by use of a resin flow enhancing member, including a cavity with a first opening and a second opening as well as an resin flow adjusting arrangement for changing a resin flow cross section in a resin flow direction from the first opening to the second opening in the resin flow enhancing member by applying vacuum to the second opening. The resin flow adjusting arrangement includes a plurality of vacuum expandable filler elements that includes gas-filled closed cell cavities and flexible walls. The disclosure further relates to a vacuum assisted resin transfer moulding process for injecting resin from a resin flow enhancing member into a fibre stack. 1. A fibre reinforced plastic composite material , comprising: 'a cavity with a first opening connectable to a resin inlet of an VARTM apparatus and a second opening connectable to a vacuum pump of a VARTM apparatus, and a resin flow adjusting arrangement for changing a resin flow cross section in a resin flow direction from the first opening to the second opening in the cavity by applying vacuum to the second opening, wherein the resin flow adjusting arrangement comprises a plurality of vacuum expandable filler elements comprising gas-filled closed cell cavities and flexible walls.', 'a vacuum assisted resin transfer moulded fibre reinforced plastic laminate prepared by use of a resin flow enhancing member, the resin flow enhancing member comprising2. The fibre reinforced plastic composite material according to claim 1 , having a shape of a wind turbine blade.3. The fibre reinforced plastic composite material according to claim 1 , wherein the plurality of vacuum expandable filler elements comprises elastomeric plastic materials.4. The fibre reinforced plastic composite material according to claim 3 , wherein the plurality of vacuum expandable filler ...

ELASTIC FASTENER FOR VACUUM BAG PLEATS

A vacuum bag having an expandable pleat is provided. The vacuum bag includes a first surface region, a second surface region, and a third surface region between the first and second surface regions. The third surface region can be folded to bring the first surface region into proximity of the second surface region. The vacuum bag also includes a strip having a first attaching region at a first end of the strip, a second attaching region at a second end of the strip opposite the first end, and a central region between the first and second attaching regions. The first attaching region is fixed to the first surface region, and the second attaching region is fixed to the second surface region such that when the central region of the strip is in a non-expanded state, the first surface region is contiguous to the second surface region. 1. A vacuum bag comprising: a first surface region;', 'a second surface region; and', 'a third surface region between the first surface region and the second surface region, the third surface region configured to be folded to bring the first surface region into proximity of the second surface region; and, 'a bag surface comprisinga strip having a first attaching region at a first end of the strip, a second attaching region at a second end of the strip opposite the first end, and a central region between the first attaching region and the second attaching region, the first attaching region being fixed to the first surface region, the second attaching region being fixed to the second surface region,wherein the first attaching region is fixed to the first surface region and the second attaching region is fixed to the second attaching region such that when the central region of the strip is in a non-expanded state, the first surface region is contiguous to the second surface region.2. The vacuum bag of claim 1 , wherein the bag surface comprises a polymer film.3. The vacuum bag of claim 1 , wherein the strip comprises a polyurethane film.4. The ...

Method and Moulding System for Manufacturing A Fibre-Reinforced Polymer Object Via A Feedback System for Controlling Resin Flow Rate

A method of manufacturing a fibre-reinforced polymer object by means of vacuum-assisted resin transfer moulding (VARTM), wherein fibre material is impregnated with liquid resin in a mould cavity comprising a rigid mould part having a mould surface defining an outer surface of the object, is described. One or more pressure sensors are connected to resin inlets of the VARTM system. A control unit is used for controlling a polymer supply unit based on measured resin pressure and is adapted to adjusting a resin flow rate, if pressure measured by the pressure sensors is below a lower threshold level or above a higher threshold level. 115-. (canceled)16. A method of manufacturing a fibre-reinforced polymer object by means of vacuum-assisted resin transfer moulding (VARTM) , wherein fibre material is impregnated with liquid resin in a mould cavity comprising a rigid mould part having a mould surface defining an outer surface of the object , said method comprising the following steps:a) arranging a fibre lay-up including a number of fibre layers on the mould surface,b) arranging at least one resin inlet above the fibre lay-up,c) attaching one or more pressure sensors to or near the at least one resin inlet,d) arranging a vacuum bag on top of the rigid mould part and sealing the vacuum bag to the mould part to define the mould cavity,e) evacuating the mould cavity,f) supplying liquid resin to the mould cavity so as to impregnate the fibre lay-up,g) monitoring the pressure and generating a signal indicative of said pressure,h) feeding said signal back to a control unit that controls a resin flow rate supplied to the resin inlets,i) increasing a resin flow rate, if the pressure measured by the pressure sensors at the resin inlet drops below a lower threshold level, and decreasing the resin flow rate, if the pressure measured by the pressure sensors at the resin inlet is above a higher pressure threshold, andj) allowing resin to cure so as to form the fibre-reinforced polymer ...

METHOD FOR MANUFACTURING SLIDE-ROOM FOR RECREATIONAL VEHICLE

A slide-room for installation in a recreational vehicle or other structure is disclosed. The slide-room comprises a shell, which can be constructed from fiberglass. The shell comprises an end wall, a ceiling, a floor, two opposing side walls, and a flange extending from the end wall, wherein the end wall, the ceiling, the floor, the side walls and the flange comprise a one-piece, unitary construction. Also disclosed are methods for molding composite components, such as slide-room. In one specific implementation, the shell for a slide-room is formed from fiberglass using a vacuum-assisted resin transfer process. During the vacuum-assisted resin transfer process, a mold apparatus can include a perimeter seal system to inhibit resin from flowing into spaces between mating components of the mold. The perimeter seal system can include clamp seal assemblies and/or vacuum seal assemblies. 1. A mandrel for use in molding a composite part , comprising:a side surface and a lower surface, the side surface and the lower surface having a common edge; anda vacuum seal arrangement located along the lower surface and the side surface of the mandrel, the vacuum seal arrangement defining a bounded area on the side surface and the lower surface that is continuous across the common edge.2. The mandrel of claim 1 , wherein the vacuum seal arrangement comprises a first seal located along the lower surface and the side surface of the mandrel claim 1 , and a second seal located along the lower surface and the side surface of the mandrel.3. The mandrel of claim 2 , wherein the first and second seals intersect one another at an end portion of the side surface opposite the common edge.4. The mandrel of claim 2 , wherein the first and second seals intersect one another at an end portion of the lower surface opposite the common edge.5. The mandrel of claim 2 , wherein the first seal comprises a flap seal.6. The mandrel of claim 1 , wherein the vacuum seal arrangement comprises:a first seal and ...

Methods of manufacturing rotor blades of a wind turbine

Methods of manufacturing rotor blades for a wind turbine and rotor blades produced in accordance with such methods are disclosed. In one embodiment, the method includes forming a first spar cap of the rotor blade from a first resin material. Another step includes placing the first spar cap within a first shell mold of the rotor blade. A further step includes infusing a second resin material into the first shell mold to form a first shell member of the rotor blade. Thus, at least a portion of the first spar cap is infused within the first shell member. Further, the second resin material is different than the first resin material. The method also includes infusing the second resin material into a second shell mold to form a second shell member of the rotor blade. Another step includes bonding the first and second shell members together so as to form the rotor blade.

Production Method for a Composite Fiber Component, Composite Fiber Component, Testing Method for a Composite Fiber Component, Computer Program, Machine-Readable Storage Medium and Apparatus

A method for producing a composite fiber component, in which a sensor apparatus having a flexible circuit carrier and/or a sensor module, in particular a micromechanical acceleration sensor module, is integrated, includes loading a tool for producing the composite fiber component with textile layers and the sensor apparatus; closing, in particular air-tight sealing, of the loaded tool and compressing the textile layers and the sensor apparatus; introducing a liquid matrix, in particular a resin, in particular a pure resin, into the sealed tool to produce the composite fiber component; detecting, in particular in real time, an acceleration relative to the introducing and/or sealing by means of the sensor apparatus and/or the sensor module of the sensor apparatus; and deriving and/or evaluating a process parameter of the production method depending on the detected acceleration.

IMPROVEMENTS RELATING TO WIND TURBINE BLADE MANUFACTURE

A method of making a prefabricated root section () for a wind turbine blade () is described. The method comprises: providing a male mould () extending longitudinally in a spanwise direction between an inboard end () and an outboard end () and extending transversely in a chordwise direction between a leading edge () and a trailing edge (), the male mould () defining a male mould surface () of convex curvature in the chordwise direction; providing a root plate () having one or more root inserts () projecting therefrom, the or each root insert () being arranged along an arcuate path; arranging one or more inner fibrous layers () on the male mould surface (); arranging the root plate () at the inboard end () of the male mould () such that the or each root insert () overlays an inner fibrous layer at the root end of the mould (). The method further comprises arranging one or more outer fibrous layers on top of the inner fibrous layers () and on top of the or each root insert (), providing resin to the fibrous layers () and to the or each root insert () and curing the resin to form a prefabricated root section () for subsequent use in the manufacture of a wind turbine blade (). Curing the resin to form the prefabricated root section () is conducted before removing the prefabricated root section () from the male mould (). 1. A method of making a prefabricated root section for a wind turbine blade , the method comprising:providing a male mould extending longitudinally in a spanwise direction between an inboard end and an outboard end and extending transversely in a chordwise direction between a leading edge and a trailing edge, the male mould defining a male mould surface of convex curvature in the chordwise direction;providing a root plate having one or more root inserts projecting therefrom, the or each root insert being arranged along an arcuate path;arranging one or more inner fibrous layers on the male mould surface;arranging the root plate at the inboard end of the ...

RESIN STRUCTURE

A resin structure includes a first structural portion and a second structural portion. The first structural portion includes a characteristic design surface and structures an end portion at a side of the resin structure at which the characteristic design surface is disposed. An orientation direction of fibers in a first pattern portion of the first structural portion differs from an orientation direction of fibers in a second pattern portion. The second structural portion includes a region disposed at the opposite side of the first structural portion to the side at which the characteristic design surface is disposed. Fibers contained in the second structural portion differ in fiber width from the fibers contained in the first structural portion. A portion of the fibers contained in a region of the second structural portion superposed with the first structural portion are configured to be visible through the resin of the first structural portion. 2. The resin structure according to claim 1 , wherein the fibers contained in the second structural portion have a greater fiber width than the fibers contained in the first structural portion.3. The resin structure according to claim 1 , wherein claim 1 , as seen from the side facing the characteristic design surface claim 1 , the orientation direction of the fibers of the first pattern portion and the orientation direction of the fibers of the second pattern portion are configured to be directions orthogonal to one another. This application is based on and claims priority under 35 USC 119 from Japanese Patent Application No. 2017-152638 filed on Aug. 7, 2017, the disclosure of which is incorporated by reference herein.The present disclosure relates to a resin structure.Technologies are known that relate to resin structures containing fibers (see Japanese Patent Application Laid-Open (JP-A) Nos. 2014-69390 and H5-38798). For example, JP-A No. 2014-69390 discloses a technology relating to a laminated sheet in which a resin ...

METHOD OF MANUFACTURING MOLDED ARTICLE

A method of manufacturing a design-imprinted molded article comprises providing a glass mold of a desired shape, that further comprises a desired shaped concave and a desired shaped rim, providing a plurality of sheets of polyacrylonitrile fibers, providing at least one design cutout of polyacrylonitrile fibers, overlaying the plurality of sheets on the surface of the desired shaped concave and desired shaped rim, overlaying the design cutout on the plurality of sheets, and applying high heat to the glass mold. 1) A method of manufacturing a design-imprinted molded article comprising:a) providing a glass mold of a desired shape;b) said glass mold further comprises a desired shaped concave and a desired shaped rim;c) providing a plurality of sheets of polyacrylonitrile fibers;d) providing at least one design cutout of polyacrylonitrile fibers;e) overlaying said plurality of sheets on the surface of said desired shaped concave and said desired shaped rim;f) overlaying said at least one design cutout on said plurality of sheets;g) applying high heat to said glass mold.2) The method of claim 1 , wherein sandwiching a plurality of resin layers between said plurality of sheets;3) The method of claim 1 , wherein coating the polyacrylonitrile fibers of said plurality of sheets with resin;4) The method of claim 1 , wherein disposing said design cutout such that the direction of the polyacrylonitrile fibers of said design cutout form an acute angle with the direction of the polyacrylonitrile fibers of said plurality of sheets;5) The method of claim 1 , wherein overlaying a design logo on said plurality of sheets;6) The method of claim 1 , wherein vacuuming said glass mold claim 1 , said plurality of sheets claim 1 , and said at least one design cutout.7) The method of claim 1 , wherein design-imprinted molded article is a travel luggage.8. The method of claim 1 , wherein design-imprinted molded article is a helmet.9) The method of claim 1 , wherein design-imprinted molded ...

A Wind Turbine Blade Manufacturing System and Method

There is described a system and apparatus for the manufacture of a wind turbine blade where portions of a blade, preferably blade half shells, are formed in suitable moulds, before transferral to a post-moulding station where post-moulding operations can be performed. The blade shells are formed in the mould to have integrated flanges which facilitate easy handling of the blade shells during subsequent manufacturing operations. There is also described a blade cradle of a post-moulding station to receive a wind turbine blade shell, where a lifting jack apparatus can be located within the blade cradle structure for the application of a lifting force to a surface of a blade shell received in the cradle, to facilitate access to all sections of the surface of the blade shell.

METHODS AND APPARATUS TO INCREASE STRENGTH AND TOUGHNESS OF AIRCRAFT STRUCTURAL COMPONENTS

Methods and apparatus to increase strength and toughness of aircraft structural components are disclosed. An example apparatus includes a composite structure of an aircraft, a stringer coupled to the composite structure of the aircraft, where the stringer and the composite structure form a stringer radius gap. A gap filler is disposed in the stringer radius gap, which includes chopped fibers randomly distributed throughout an entire volume of the gap filler. 1. An apparatus comprising:a composite structure of an aircraft;a stringer coupled to the composite structure of an aircraft, the stringer and the composite structure to form a stringer radius gap; anda gap filler disposed in the stringer radius gap, the gap filler including chopped fibers randomly distributed throughout substantially an entire volume of the gap filler.2. The apparatus as defined in claim 1 , wherein the gap filler further includes a thermoset resin in which the chopped fibers are disposed.3. The apparatus as defined in claim 1 , wherein the gap filler has a volume fraction of the chopped fibers between 45% and 65%.4. The apparatus as defined in claim 1 , wherein the gap filler further includes micron or nano-particles to increase a toughness of the gap filler.5. The apparatus as defined in claim 1 , wherein the stringer includes an edge chamfer of approximately 15 degrees.6. The apparatus as defined in claim 1 , wherein the chopped fibers include carbon fibers claim 1 , fiberglass claim 1 , aramid claim 1 , Kevlar claim 1 , or nylon.7. The apparatus as defined in claim 1 , wherein the gap filler has a fracture toughness of at least 2 in-lb/square inch.8. The apparatus as defined in claim 1 , wherein the gap filler has a minimum tensile strength of 15 ksi.9. The apparatus as defined in claim 1 , wherein the gap filler has an elastic modulus between 0.5 msi and 8 msi.10. A method comprising:forming chopped fiber flakes and a resin into a gap filler;curing the gap filler formed by the chopped ...

End of arm tooling

End of arm tooling system and a method for manufacture is provided. The end or arm tooling system provides automated material handling, part manipulation, pre-forming and transferring of a pre-impregnated carbon fiber material. A robot is connected to end of arm tooling for automated material handling and transfer operations from at least a lower preform tool system where light compression is applied to a molding press. The end or arm tooling system includes a cured silicone membrane as well as vacuum and air blow off, allowing for robotically preforming, picking up and dropping-off pre-impregnated carbon fiber materials which are notoriously sticky and difficult to handle.

PRESSURE SENSITIVE FLOW DISTRIBUTION MEDIUM FOR VARTM

A method for manufacturing a fibre reinforced composite by means of a vacuum assisted resin transfer moulding, comprising the steps of placing a fibre material in a mould, placing a flow distribution medium onto the fibre material, and covering the fibre material (1) and the flow distribution medium with a vacuum foil for forming a closed mould cavity between the mould and the vacuum foil is described. It is characterised in using a flow distribution medium with a thickness depending on a pressure gradient over the vacuum foil. 1. A method for manufacturing a fibre reinforced composite by means of vacuum assisted resin transfer moulding , comprising:placing a fibre material in a mould;placing a flow distribution medium onto the fibre material; andcovering the fibre material and the flow distribution medium with a vacuum foil for forming a closed mould cavity between the mould and the vacuum foil wherein the flow distribution medium has a thickness depending on a pressure gradient over the vacuum foil.2. The method as claimed in claim 1 , further comprising:placing a peel ply between the flow distribution medium and the fibre material.3. The method as claimed in claim 1 , wherein the flow distribution medium has a stiffness that enables the flow distribution medium to lift the vacuum foil.4. The method as claimed in claim 1 , wherein the flow distribution medium comprises nonwoven fibre material.5. The method as claimed in claim 1 , wherein the flow distribution medium comprises fibres claim 1 , the fibres having a diameter of at least 10 μm and/or maximal 500 μm.6. The method as claimed in claim 1 , wherein the flow distribution medium comprises thermoplastic material.7. The method as claimed in claim 1 , wherein the flow distribution medium comprises polyester and/or polypropylene and/or polyamide.8. The method as claimed in claim 1 , wherein the flow distribution medium comprises material having a thickness between 2 mm and 10 mm at 1.000 mbar and/or between 0.1 ...

WIND TURBINE BLADES

A reinforcing structure for a wind turbine blade is in the form of an elongate stack of layers of pultruded fibrous composite strips supported within a U-shaped channel. The length of each layer is slightly different to create a taper at the ends of the stack; the centre of the stack has five layers, and each end has a single layer. The ends of each layer are chamfered, and the stack is coated with a thin flexible pultruded fibrous composite strip extending the full length of the stack. The reinforcing structure extends along a curved path within the outer shell of the blade. The regions of the outer shell of the blade on either side of the reinforcing structure are filled with structural foam, and the reinforcing structure and the foam are both sandwiched between an inner skin and an outer skin. 1. A wind turbine blade of generally hollow construction and formed from first and second opposing half-shells;each half-shell comprising an inner skin and an outer skin and first and second elongate reinforcing structures being located between the inner and outer skins;each reinforcing structure extending along the lengthwise direction of the blade and comprising a stack of layers;each stack having a thickness which extends in a direction substantially perpendicular to a surface of the blade;each layer extending across a width of the respective stack, the width being perpendicular to the lengthwise direction of the blade and perpendicular to the thickness of the stack, and each layer comprising at least one pre-cured pultruded fibrous composite strip;each half-shell further comprising core material disposed between the inner and outer skins and extending: (a) between the first and second elongate reinforcing structures; (b) from the first elongate reinforcing structure towards a leading edge of the blade; and (c) from the second elongate reinforcing structure towards a trailing edge of the blade;the wind turbine blade further comprising an elongate web extending between at ...

A Wind Turbine Blade and an Associated Manufacturing Method

A manufacturing method is described for a wind turbine blade, where layers of fibre material are laid up in a mould to form a portion of the blade structure. The fibre layers are infused with a resin which is subsequently cured to form the hardened blade structure. Some of the layers of fibre material are arranged so that a portion of the layers are kept resin-free during the infusion and curing steps, so that the fibre layer extends freely out from the external surface of the blade, preferably at the blade trailing edge, to provide a flexible blade trailing edge to reduce blade operational noise. 1. A method of manufacturing a wind turbine blade comprising:arranging a plurality of fibre layers in a mould surface;infusing said plurality of fibre layers with a resin; andcuring said resin to form at least a portion of a fibre-composite blade structure,wherein the method further comprises:arranging a portion of said plurality of fibre layers such that said portion of said plurality of fibre layers are kept free from resin during said step of infusing, wherein said at least a portion of a fibre-composite blade structure comprises at least a section of a wind turbine blade trailing edge,wherein said portion of resin-free fibre layers forms a flexible fibre portion projecting from the wind turbine blade trailing edge section.2. The method of claim 1 , wherein said at least a portion of a fibre-composite blade structure comprises a wind turbine blade shell claim 1 , wherein the method further comprises the step of assembling said wind turbine blade shell with at least one other wind turbine blade shell to form a wind turbine blade having a fibre portion projecting from the trailing edge of said wind turbine blade.3. The method of claim 1 , wherein said step of arranging comprises positioning an end of at least one fibre layer to extend over an edge of said mould surface.4. The method of claim 1 , wherein the method comprises arranging a sealing member over said plurality ...

Thermo-rheological fluid valve for resin infusion

A resin flow-controlling apparatus for infusing composite reinforcement material with resin. The resin flow-controlling apparatus may have at least one viscosity valve to speed, slow, allow, or deny resin flow through the viscosity valve to the composite reinforcement material depending on the temperature of the viscosity valve. The viscosity valve may fluidly couple a resin reservoir with an enclosed chamber in which the composite reinforcement material resides. The viscosity valve may be thermally coupled with heating and/or cooling elements selectively variable between at least two different temperatures to affect viscosity of the resin and control resin flow from the resin reservoir into the composite reinforcement material. A vacuum port at an opposite end of the composite reinforcement material from the viscosity valve may fluidly couple with the enclosed chamber and a vacuum source may pull atmosphere and/or resin from the enclosed chamber and/or the resin reservoir.

COMPOSITE SNOW PLOW APPARATUS AND METHOD

The invention includes a snow plow blade made of a composite material. The invention also includes a snow plow system that incorporates a snow plow blade made of a composite material and that further includes a mounting area for a lift mechanism and threadable metal inserts. 1. A snow plow system comprising:a composite blade; anda lift mechanism having one end attached to the composite blade for raising and lowering the composite blade, the lift mechanism having another end attached to a vehicle.2. The snow plow system of further comprising a light system for positioning at least one headlamp above the blade.3. The snow plow system of wherein the inner radius of the snow plow blade varies across the snow moving surface of the snow plow blade.4. The snow plow system of wherein the inner radius of the snow plow blade increases in a non-linear fashion from the center of the snowplow blade to the outer edges.5. The snow plow system of wherein the composite blade includes a core of material substantially surrounded by woven fabric impregnated with resin.6. The snow plow system of further comprising: strengthening elements made of a core material and applied to the backside of the blade; and', 'metal inserts positioned in at least one of the strengthening elements., 'woven fabric impregnated with resin wrapped over a core of material to form a composite blade, the composite blade further including7. The snow plow system of wherein the strengthening elements are substantially vertical.8. The snow plow system of wherein the strengthening elements are substantially horizontal.9. The snow plow system of further comprising a pair of substantially vertical brackets attached to a strengthening element of the blade near one end claim 1 , and attached to the snow plow lifting mechanism at the other end.10. The snow plow system of wherein the pair of substantially vertical brackets includes at least one stop bracket.1118-. (canceled)19. A method for forming a composite blade ...

Method for preparing composite structures and consumable assembly therefor

Methods, a consumable assembly, and a tool for preparing a composite structure from a laminate disposed on a surface of a mold. The method involves preparing consumable materials, such as a breather sheet and a vacuum bag, and preparing an inflatable tool, outside of the mold. These prepared consumable materials and the inflatable tool are then inserted into the mold, and the inflatable tool is inserted into a folded assembly of the breather and vacuum bag. Once inserted into the mold, the inflatable tool is inflated, which deploys the consumable materials against the laminate. A vacuum can be generated, which maintains the deployed consumable materials against the laminate. This can be done for many hours. Finally, the laminate is cured inside the mold so as to form the composite structure.

EVACUABLE MOLD FOR FIBER COMPOSITE PLASTIC COMPONENTS

Evacuable, stable mold having a design obtained by thermal deformation at temperatures ≦ C. and corresponding to a fiber composite plastic component to be produced, consisting of an at least two-layered thermoplastic, vacuum-tight plastic film from a surface layer which is made of at least one thermoplastic polyamide or copolyimide, which has optionally functional groups, and a separating layer which form the inner side and is made of at least one thermoplastic fluorinated copolymer which has functional groups. 1. A stable evacuable mold with a shape obtained by thermoforming at temperatures ≦240° C. and corresponding to the respective fiber-composite plastics component to be produced therewith , and made of an at least two-layer vacuum-tight thermoplastic film comprisinga) a surface layer made of at least one thermoplastic polyamide or copolyamide which optionally has functional groups, andb) a release layer forming the internal side of the mold and made of at least one thermoplastic tetrafluoroethylene copolymer, which has functional groups, composed of γ) copolymerized units of monounsaturated aliphatic dicarboxylic acids or cyclic anhydrides thereof, and also', {'sub': 2', '1-10, 'sup': 1', '1, 'CF═CFOR, where Ris a Cperfluoroalkyl moiety which can comprise an oxygen atom,'}, 'δ) copolymerized units of at least one fluorinated monomer differing from tetrafluoroethylene, selected from the group consisting of'}], 'b1) α) copolymerized units of tetrafluoroethylene and'}{'sub': 2', '2', 'p', '2, 'CF═CF(CF)OCF═CF, where p is 1 or 2,'}{'sub': 2', '2', 'Q, 'sup': 3', '4', '3', '4, 'claim-text': {'sub': 2', '4, 'β) copolymerized units of C-Colefins, or'}, 'perfluoro (2-methylene-4-methyl-1,3 dioxolane) and CH═CX(CF)X, where Xis a hydrogen atom or a fluorine atom, Q is an integer from 2 to 10 and Xis a hydrogen atom or a fluorine atom, and/or'}b2) an olefin/tetrafluoroethylene copolymer which has been modified by free-radical grafting of from 0.01 to 5 mol % of carboxy ...

Actuatable Flow Media

An actuatable flow media for the control of a flow rate of a liquid through the flow media, the actuatable flow media comprising a base having at least one cavity formed therein, at least one aperture formed in the cavity defining a liquid flow path for the entry of liquid into or exit of liquid from the flow media; a flexible membrane arranged in spaced relation with the base and defining a liquid flow path through the flow media; and an elastically deformable element arranged in the cavity and extending between the base and the flexible membrane for actuation between at least a first configuration in which the element is substantially undeformed and the liquid flow path through the at least one aperture is open and a second configuration in which the element is substantially deformed and the liquid flow path through the at least one aperture is closed.

METHOD FOR SECURING CORE TO TOOL DURING MACHINING

A method for preparing a part using a rigid tool surface having a shape. The method includes applying a breather sheet comprising gas-permeable material over the rigid tool surface. A vacuum bag is applied over the breather sheet, and a vacuum pressure is applied underneath the vacuum bag to conform the breather sheet and the vacuum bag to the shape of the rigid tool surface. A resin pre-impregnated ply is applied over the vacuum bag, and the part is positioned over the ply. 1. A method of preparing a part using a rigid tool surface having a shape , the method comprising:applying a vacuum bag over the rigid tool surface;applying vacuum pressure to the vacuum bag to conform the vacuum bag to the shape of the rigid tool surface;applying a resin pre-impregnated ply over the vacuum bag; andapplying the part over the ply.2. The method of claim 1 , further comprising applying a breather sheet over the rigid tool surface before applying the vacuum bag.3. The method of claim 1 , wherein the part comprises a honeycomb core comprising one or both of fiberglass and aluminum.4. The method of claim 3 , wherein the rigid tool comprises one or more of aluminum claim 3 , steel and fiberglass.5. The method of claim 1 , wherein the part comprises two pieces each comprising an interface surface claim 1 , further comprising—applying an adhesive to at least one of the interface surfaces,positioning the interface surfaces against each other.6. The method of claim 1 , further comprising heating the part on the rigid tool to cure the resin pre-impregnated ply.7. The method of claim 6 , wherein a portion of the part has a thickness during the curing of the resin pre-impregnated ply claim 6 , further comprising applying a machine tool to the portion of the part after the curing of the resin pre-impregnated ply to reduce the thickness.8. The method of claim 7 , further comprising removing the vacuum pressure from the vacuum bag to at least partly release the part from the rigid tool.9. The ...

Actuatable Flow Media

An actuatable flow media for controlling a flow rate of a liquid through the flow media, the actuatable flow media comprising a base having a plurality of base cavities formed therein, at least one aperture formed in each base cavity defining a liquid flow path for the entry of liquid into or exit of liquid from the flow media; a flexible membrane arranged in spaced relation with the base and defining a liquid flow path through the flow media; and an elastically deformable element arranged in each base cavity and extending between the base and the flexible membrane for actuation between at least a first configuration in which the element is substantially undeformed and the liquid flow path through the at least one aperture is open and a second configuration in which the element is substantially deformed and the liquid flow path through the at least one aperture is closed.

DEVICE AND METHOD FOR PRODUCING A COMPONENT

A device and method for producing a component. The device is composed of two mold elements, wherein one of the mold elements has a cavity which communicates with the position of one side of a component to be produced. An inflatable tube which is fluidically linked to the surrounding atmosphere is provided in the cavity. A cover covers the first and the second mold element and seals the first and said second mold element in relation to the surrounding atmosphere. The tube is expanded by applying a vacuum within the sealed regions and the tube can shape or facilitate shaping the side of the component to be produced. 1. A device for producing a component , wherein the device comprises:a first mold element which on one side is configured for shaping at least one portion of the component to be produced;a second mold element which has a cavity, wherein the second mold element is specified for being disposed on the first mold element such that the cavity communicates with one side of the component to be produced;an inflatable tube disposed in the cavity; anda cover which covers the first mold element and the second mold element and seals said first mold element and said second mold element in relation to a surrounding atmosphere,wherein the interior of the inflatable tube is fluidically linked to the surrounding atmosphere.2. The device according to claim 1 , further comprising:a semi-permeable membrane disposed between the inflatable tube and the component to be produced.3. The device according to claim 2 , wherein the semi-permeable membrane is disposed between the first mold element and the second mold element and spans the side of the component to be produced.4. The device according to claim 3 , further comprising:a seal element disposed between the semi-permeable membrane and the first mold element, or between the semi-permeable membrane and the second mold element.5. The device according to claim 2 , wherein the semi-permeable membrane is configured so as to be ...

PRE-CURED ROTOR BLADE COMPONENTS HAVING AREAS OF VARIABLE STIFFNESS

The present disclosure is directed to a rotor blade component for a wind turbine. The rotor blade component includes a plurality of pre-cured members arranged in one or more layers. Each of the pre-cured members is constructed of a plurality of fiber materials cured together via a resin material having a first stiffness and at least additional material having a second stiffness. Further, the second stiffness is lower than the first stiffness. As such, the additional low-stiffness material is cured within the resin material so as to increase flexibility of the pre-cured members. 1. A rotor blade component for a wind turbine , the rotor blade component comprising: a plurality of fiber materials cured together via a resin material having a first stiffness; and,', 'at least one additional material cured within the resin material and having a second stiffness, the second stiffness being lower than the first stiffness,', 'wherein the additional material increases flexibility of the pre-cured members., 'a plurality of pre-cured members arranged in one or more layers, each of the pre-cured members comprising2. The rotor blade component of claim 1 , wherein the pre-cured members are formed via at least one of pultrusion or belt-pressing.3. The rotor blade component of claim 1 , wherein the rotor blade component comprises at least one of a spar cap claim 1 , a shear web claim 1 , or a root ring.4. The rotor blade component of claim 1 , wherein the additional material comprises at least one of a rubber material claim 1 , a silicon material claim 1 , a foam material claim 1 , or a flexible glass material.5. The rotor blade component of claim 1 , wherein the additional material comprises a pre-cured low-stiffness component.6. The rotor blade component of claim 5 , wherein the low-stiffness component comprises at least one of the following cross-sectional shapes: square claim 5 , arcuate claim 5 , rectangular claim 5 , T-shaped claim 5 , V-shaped claim 5 , or U-shaped.7. The ...

COMPOSITE FOAM LAMINATE AND ITS USAGE

The present disclosure relates to a laminate for making a molded article comprising at least one fiber reinforcement impregnated with a resin matrix as a first layer and a foam as a second layer. The foam can be laminated to the first layer using a nanocomposite adhesive. The laminates can be easily molded using bagging mold techniques. The resulting molded devices have uses in biomedical, health care and sport protective devices. Due to the improved strength of material, it is possible to drill holes into the device shell allowing for improved ventilation. 1. A laminate for making a molded article comprising at least one fiber reinforcement impregnated with a resin matrix as a first layer and a foam as a second layer.2. The laminate according to claim 1 , wherein the first layer consists of multiple layers of fiber reinforcement impregnated with the resin matrix.3. The laminate according to claim 1 , wherein the foam layer is laminated to the first layer using an adhesive layer.4. The laminate according to claim 3 , wherein the adhesive layer is made from a nano-silica based nanocomposite.5. The laminate according to claim 1 , wherein the material of the fiber reinforcement is selected from a carbon claim 1 , glass claim 1 , para-aramid synthetic or polymer fibers.6. The laminate according to claim 1 , wherein the resin matrix is an epoxy resin.7. The laminate according to claim 1 , wherein the resin matrix additionally comprises a filler.8. The laminate according to claim 1 , wherein the laminate has holes.9. The laminate according to claim 8 , wherein the holes have a size of about 0.1 to 10 mm.10. A process for making a laminate according to claim 1 , which comprises the following steps:(a) immersing the fiber reinforcement into the resin matrix,(b) impregnating the reinforcement,(c) optionally applying an adhesive to a foam or the impregnated reinforcement, and(d) attaching the impregnated reinforcement to the foam.11. A process for making a molded article ...

METHOD FOR MANUFACTURING SLIDE-ROOM FOR RECREATIONAL VEHICLE

A slide-room for installation in a recreational vehicle includes a shell, which can be constructed from fiberglass. The shell has an end wall, a ceiling, a floor, two opposing side walls, and a flange extending from the end wall, wherein the end wall, the ceiling, the floor, the side walls and the flange have a one-piece, unitary construction. The shell for a slide-room can be formed from fiberglass using a vacuum-assisted resin transfer process. During the vacuum-assisted resin transfer process, a mold apparatus can include a perimeter seal system to inhibit resin from flowing into spaces between mating components of the mold. The perimeter seal system can include clamp seal assemblies and/or vacuum seal assemblies. 1. A mandrel for use in molding a composite part , comprising:a side surface and a lower surface, the side surface and the lower surface having a common edge; anda vacuum seal arrangement located along the lower surface and the side surface of the mandrel, the vacuum seal arrangement extending from the side surface to the lower surface across the common edge and defining a bounded area on the side surface and the lower surface that is continuous across the common edge, the vacuum seal arrangement being configured such that a portion of the lower surface is within the bounded area and a portion of the lower surface is outside the bounded area.2. The mandrel of claim 1 , wherein the mandrel is configured such that when the mandrel is positioned on a base surface with the seal arrangement contacting the base surface and contacting an adjacent mandrel claim 1 , the vacuum seal arrangement defines a vacuum chamber that at least partially encloses the bounded area.3. The mandrel of claim 1 , wherein the seal arrangement is configured such that when the mandrel is positioned on a base surface the seal arrangement spaces the lower surface of the mandrel above the base surface claim 1 , and the portion of the lower surface that is outside the bounded area ...

COMPOSITE STRUCTURE AND METHOD OF MAKING A COMPOSITE STRUCTURE

In accordance with the present teachings, a method of producing composite having a 3A Q3D reinforcement phase is disclosed. The method of producing the composite provides producing a three-dimensionally woven configuration where a first fiber from a first sheet of reinforcement phase is interwoven or mechanically linked with at least one of an adjacent second layer and then back into the first sheet. The linking fibers are passed between layers at an acute angle generally less than about 10 degrees. The method includes impregnating the woven construction with a curable polymer such as epoxy. 1. A composite structure comprising:a first fiber composite layer having a first reinforcing layer having a plurality of first fibers having a respective relative fiber directions of about 0°, and 60° and −60°;at least a second fiber composite layer having a first reinforcing layer having a plurality of second fibers having a respective relative fiber directions of about 0°, and 60° and −60°, in relation to the first composite layer, the layers being secured together adjacent each other in an overlapping manner; andan inter-layer fiber being woven within both the first and third reinforcing layers.2. The composite structure of claim 1 , further comprising a fourth skin composite layer attached to an opposite portion of at least one of the first and second composite layers claim 1 , the third and fourth composite layers being substantially parallel and spaced apart from each other claim 1 , wherein the inter-layer fiber is woven within the fourth layer.3. The composite structure of claim 1 , further comprising an optically clear matrix claim 1 , and wherein the first fibers and second fibers are optically clear.4. A composite structure comprising:a first fiber composite layer having a relative fiber direction of about 0°;{'b': '31', 'and at least a second fiber composite layer having a relative fiber direction of between about 60° and 60°, inclusive, compared to the first ...

METHOD FOR MANUFACTURING FIBER-REINFORCED PLASTIC PRODUCTS

The present application relates to a method for manufacturing fiber-reinforced plastic products. This method comprises: preparing a fiber preform on a mold; disposing first and second flow meshes and first and second demolding cloths; sealing the fiber preform to form a vacuum system by pumping; penetrating the resin through the first peel ply via the first flow mesh and impregnates the fiber preform from bottom to top; penetrating the resin through the second peel ply via the second flow mesh and impregnates the fiber preform from top to bottom; and attaining a resin-impregnated fiber perform and finally attaining fiber-reinforced plastic products. 1. A method for manufacturing fiber-reinforced plastic products:preparing a fiber preform on a mold and disposing a first peel ply and a first flow mesh between said mold and said fiber perform;disposing a second peel ply and a second flow mesh on said fiber perform;disposing a first injection port and a second injection port for supplying a resin on said first flow mesh and said second flow mesh, respectively;sealing the fiber preform to form a sealing system, and pumping the air within the sealing system via a suction port until said sealing system becomes a vacuum system;supplying said resin to said first flow mesh via said first injection port so that said resin penetrates through said first peel ply and impregnates the fiber preform from bottom to top;supplying said resin to said second flow mesh via said second injection port so that said resin penetrates through said second peel ply and impregnates said fiber preform from top to bottom; andattaining a resin-impregnated fiber perform and finally attaining said fiber-reinforced plastic products,whereina first film is disposed on a resin-injection side of said fiber perform to cover said first injection port, said first peel ply, said first flow mesh and at least a part of said fiber perform, wherein after the resin is supplied to said first flow mesh via said first ...

METHOD FOR MANUFACTURING GOLF CLUB HEAD PART

A method for manufacturing a golf club head part includes the steps of: sewing at least one roving material onto a base material, so as to form a laminate blank; placing the laminate blank into a cavity of a mold assembly; vacuuming the cavity, and then impregnating a resin material into the laminate blank that is placed in the cavity under vacuum; and thermoforming the laminate blank and the resin material in the cavity into the golf club head part. 1. A method for manufacturing a golf club head part , comprising the steps of:sewing at least one roving material onto a base material, so as to form a laminate blank;placing the laminate blank into a cavity of a mold assembly;vacuuming the cavity, and then impregnating a resin material into the laminate blank placed in the cavity under vacuum; andthermoforming the laminate blank and the resin material in the cavity into the golf club head part.2. The method according to claim 1 , wherein in the sewing step claim 1 , at least one thread material is further stitched to the base material to fix the at least one roving material on the base material.3. The method according to claim 1 , wherein the laminate blank is tailored to have a predetermined shape by trimming the base material before the placing step.4. The method according to claim 1 , wherein the at least one roving material is selected from the group consisting of carbon fibers claim 1 , glass fibers claim 1 , and commingled yarns.5. The method according to claim 2 , wherein the at least one thread material is selected from the group consisting of a cotton yarn claim 2 , a carbon fiber claim 2 , a glass fiber claim 2 , and combinations thereof.6. The method according to claim 1 , wherein the base material is selected from the group consisting of glass fibers claim 1 , thermoplastic polymers claim 1 , and a combination thereof. This application claims priority to Taiwanese Invention Patent Application No. 109132326, filed on Sep. 18, 2020.The disclosure relates to a ...

Method of molding a shell part of a wind turbine blade

The present invention relates to a method of molding a shell part of a wind turbine blade comprising the steps of providing a mold ( 64 ) comprising a mold cavity ( 66 ) with a root end ( 68 ) and an opposing tip end ( 70 ), arranging one or more preformed sheets ( 72 a, 72 b, 72 c ) in the mold cavity ( 66 ), wherein each preformed sheet comprises a mixture of fibre rovings ( 82 ) and a binding agent, wherein the fibre rovings are at least partially joined together by means of the binding agent, and injecting the one or more preformed sheets ( 72 a, 72 b, 72 c ) with a resin to mold the shell part. The present invention also relates to a shell part of a wind turbine blade obtainable by said method, to a preformed sheet for use in said method and to a method of manufacturing said preformed sheet.

IN-SITU REBUILD METHOD FOR IN-SITU REBUILDING AND REPAIRING PIPES AND CONTAINMENT STRUCTURE

The in-situ rebuild method comprises roughening by a roughening technique a surrounding inner or outer surface to be treated around a defective section of a pipe or containment structure, applying one or more layers of a self-adhesive fiber sheet onto the roughened surface to be treated, encapsulating with a vacuum bag the one or more layers of the self-adhesive fiber sheet laying on the surface to be treated, creating by means of a vacuum system a low pressure into a space between the vacuum bag and the surface to be treated, injecting by means of an injection system an impregnation curable resin into the mentioned space, stopping the injecting and letting the impregnation curable resin to cure thereby forming a composite rebuild laminate on the surface to be treated surrounding the defective section, and disconnecting the vacuum system and the injection system and removing the vacuum bag. 2. The in-situ rebuild method according to claim 1 , wherein said roughening technique comprises the steps of:adhering a peelable fabric with an adhesive curable resin onto said surrounding inner or outer surface to be treated, said peelable fabric surrounding said defective section of the pipe or containment structure;letting said adhesive curable resin to cure; andstripping off said peelable fabric and the adhesive curable resin thereby roughening said surrounding inner or outer surface to be treated.3. The in-situ rebuild method according to claim 1 , further comprising an additional step of protecting said composite rebuild laminate with a protective coating compatible with intended work conditions and/or with an intended service fluid.4. The in-situ rebuild method according to claim 2 , further comprising an additional step of protecting said composite rebuild laminate with a protective coating compatible with intended work conditions and/or with an intended service fluid.5. The in-situ rebuild method according to claim 1 , wherein the impregnation curable resin is injected ...

Shaping a radius filler against a mandrel

A radius filler material positioned at an intersection of a mandrel and a placement surface is heated to form a heated radius filler material. Mechanical pressure is applied to the heated radius filler material to shape the heated radius filler material to a shaped radius filler having a desired shape against a radius of the mandrel. A composite ply is applied over the mandrel and the shaped radius filler.

MOLD FOR MANUFACTURING COMPOSITE MATERIAL STRUCTURE

A mold for a composite material structure includes: a plurality of segments including side surfaces configured to be coupled to each other, seal grooves being provided on at least one of the adjacent side surfaces; a pair of annular holding members configured to fix both respective end surfaces of the segments to keep them as a single structure; and seal members configured to seal between the segments when the side surfaces are coupled with the seal member inserted in the seal groove. Each seal member is formed in a line shape having ends. A lip portion is provided at a seal upper portion of the member. The seal member is hollow or includes a concave portion on at least a seal bottom portion thereof. With this, complication of manufacture of a hollow composite material structure can be suppressed or avoided while realizing a satisfactory sealed state between the adjacent segments. 1. A mold for manufacturing a hollow composite material structure ,the mold being located in the hollow composite material structure,the mold comprising:a plurality of segments including side surfaces configured to be coupled to each other, each of seal grooves being provided on at least one of the adjacent side surfaces of the segments; anda pair of annular holding members configured to fix both respective end surfaces of the segments, wherein:the segments are kept as a single structure by coupling the side surfaces of the segments to each other and fixing the end surfaces of the segments to the annular holding members;the mold further includes seal members each configured to seal between the segments when the side surfaces of the segments are coupled to each other with the seal member inserted in the seal groove;each of the seal members is formed in a line shape having ends;a part of the seal member which part contacts a bottom surface of the seal groove when the seal member is inserted in the seal groove is referred to as a seal bottom portion;a part of the seal member which part is ...

Method and system for producing a panel member for an airframe

A method of producing a composite panel member, especially a composite panel member having a foam core sandwich structure for an airframe of an aircraft or spacecraft, including: providing at least one fiber reinforcement layer in a panel molding tool; moving or transferring the molding tool to an infusion station that is pre-heated to an infusion temperature and infusing the fiber reinforcement layer in the molding tool with a polymer resin; moving or transferring the molding tool to a curing station that is pre-heated to a curing temperature and curing the at least one resin-infused fiber reinforcement layer in the molding tool to form a composite panel member; and moving or transferring the molding tool to a cooling station that is provided at a cooling temperature and cooling the composite panel member in the molding tool.

Method for producing fiber-reinforced plastic from prepreg

A method for producing a fiber-reinforced plastic from a prepreg is provided with: executing a first heating to retain the prepreg in a first atmosphere, a temperature of the first atmosphere being above a room temperature and not higher than 100 degrees C.; after executing the first heating, executing a second heating to retain the prepreg in a second atmosphere, a temperature of the second atmosphere being not lower than 150 degrees C. and lower than a curing temperature of the prepreg; and after executing the second heating, executing a third heating to retain the pregreg in a third atmosphere, a temperature of the third atmosphere being higher than the curing temperature, wherein at least the first atmosphere and the second atmosphere are under reduced pressure below an atmospheric pressure.

A SYSTEM AND METHOD FOR MANUFACTURING A REINFORCED WIND TURBINE BLADE

The present invention relates to a method and system for manufacturing a wind turbine blade. The method comprising the steps of forming a cured blade element () of a first blade shell, forming a cured blade element () of a second blade shell, transferring the cured blade element () of the first blade shell to a first cradle (), and transferring the cured blade element () of the second blade shell to a second cradle (). Each cradle comprises a mould body () having a moulding surface for abutting against a surface of the cured blade element to advantageously form a seal therebetween. 1. A method of manufacturing a wind turbine blade , the method comprising the steps of:{'b': '102', 'forming a cured blade element () of a first blade shell,'}{'b': '102', 'forming a cured blade element () of a second blade shell,'}{'b': 102', '92, 'transferring the cured blade element () of the first blade shell to a first cradle (),'}{'b': 94', '96', '98', '97', '97', '102, 'transferring the cured blade element of the second blade shell to a second cradle (), wherein each cradle comprises a mould body (, ) having a moulding surface (), and wherein each cured blade element is arranged in its respective cradle such that the moulding surface (), or a part thereof, abuts against a surface of the cured blade element (),'}{'b': '104', 'forming a reinforced section () on the cured blade element of the first blade shell in the first cradle,'}{'b': '104', 'forming a reinforced section () on the cured blade element of the second blade shell in the second cradle,'}{'b': '100', 'closing said first and second blade shells () to form a closed wind turbine blade shell, and'}bonding said first and second blade shells in said closed wind turbine blade shell to form a wind turbine blade.2102102. A method according to claim 1 , wherein each cured blade element () is arranged in its respective cradle such that a section of the moulding surface is placed underneath a part of the cured blade element () claim ...

METHOD FOR MANUFACTURING COMPOSITE MATERIAL

A method for manufacturing a composite material includes placing a netlike sheet material, through which a resin composition permeates, on reinforcing fiber substrates disposed on a forming die. The method includes covering the reinforcing fiber substrates disposed on the forming die and the bag surface-smoothing sheet with a bag film to form a sealed forming space between the bag film and the forming die. The method includes infusing a resin composition into the forming space to impregnate the reinforcing fiber substrates. The method includes curing the resin composition impregnated in the reinforcing fiber substrates. Warp yarns and weft yarns are disposed in a lattice pattern and, after placing the bag surface-smoothing sheet on the reinforcing fiber substrates so that the warp yarns and the weft yarns form acute angles with respect to corners of the reinforcing fiber substrates, the bag surface-smoothing sheet projecting from the reinforcing fiber substrates is bent. 1. A method for manufacturing a composite material comprising:a placement step of placing a netlike sheet, through which a resin composition permeates, on a reinforcing fiber substrate disposed on a forming die;a covering step of covering the reinforcing fiber substrate and the netlike sheet disposed on the forming die with a bag film to form a sealed forming space between the bag film and the forming die;an injection/impregnation step of injecting the resin composition into the forming space to impregnate the reinforcing fiber substrate with the resin composition; anda resin curing step of curing the resin composition impregnated in the reinforcing fiber substrate,wherein in the netlike sheet, a plurality of warp yarns and a plurality of weft yarns are disposed in a lattice pattern, andin the placement step, after the netlike sheet is placed on the reinforcing fiber substrate such that the warp yarns and the weft yarns form acute angles with respect to corners of the reinforcing fiber substrate, ...

Vacuum Port Base

A vacuum port base comprises an upper face, a lower face, a first channel, and a second channel. The upper face is configured to interface with a vacuum port. The lower face is configured to interface with a surface of a tool. The first channel formed in the lower face is configured to receive an edge breather. The second channel formed within the vacuum port base is configured to receive the vacuum port such that the vacuum port is in fluid communication with the first channel and the edge breather to remove gases from a composite structure. 1. A vacuum port base comprising:an upper face configured to interface with a vacuum port;a lower face configured to interface with a surface of a tool;a first channel formed in the lower face and configured to receive an edge breather; anda second channel formed within the vacuum port base and configured to receive the vacuum port such that the vacuum port is in fluid communication with the first channel and the edge breather to remove gases from a composite structure.2. The vacuum port base of further comprising:a number of magnets configured to magnetically attach the vacuum port base to the tool.3. The vacuum port base of further comprising:a number of recesses formed within the lower face and configured to house the number of magnets such that each magnet is flush against the lower face and a surface of the tool.4. The vacuum port base of further comprising:elongate grooves formed in the lower face and running radially from the first channel toward an edge of the lower face of the vacuum port base.5. The vacuum port base of claim 1 , wherein the edge breather is a rigid breather.6. The vacuum port base of claim 5 , wherein the rigid breather has a tent shape.7. The vacuum port base of further comprising:a number of pins associated with the first channel, wherein the number of pins is configured to engage with the rigid breather to hold the rigid breather in place.8. The vacuum port base of claim 7 , wherein the rigid ...

Method of Positioning a Braided Fibre Sleeve

A method of positioning a braided fibre sleeve relative to a tool surface, the braided fibre sleeve comprising a longitudinal axis and biaxially oriented tows arranged at acute angles relative to the longitudinal axis, the method comprising; applying tension to a plurality of axial threads disposed along the longitudinal axis, such tension forming a tensioned braided fibre sleeve; positioning the tensioned braided fibre sleeve relative to a tool surface; and releasing tension on the plurality of axial threads.

SCALABLE TOOLING SYSTEM USING HIGHLY PARALLEL CONVECTION HEATING FOR PROCESSING OF HIGH TEMPERATURE COMPOSITE MATERIALS

The present example provides a scalable tooling system using highly parallel convection heating for processing of high temperature composite materials. A single-sided mold is provided with vacuum pressure to cast and consolidate a raw material. The mold is integrally heated by a plurality of discretized heat sources providing a plurality of convection airflow sources to minimize the hot and cold spots inherit to typical convection oven processing. Airflow is arranged by orifices aligned conformally to the mold's profile surface such that rapid heating rates may be achieved while maintaining temperature control along the mold surface. 1. A tooling system comprising:a mold having a fist side upon which a work piece is disposed, and a second side including a plurality of indentations;a plurality of heated air sources, each heated air source of the plurality of air sources positioned to direct a heated air flow to each of the plurality of indentations, whereby heating of the work piece is controlled.2. The tooling system of claim 1 , in which the heated air source includes an electric heating element.3. The tooling system of claim 1 , in which the heated air source includes an orifice.4. The tooling system of claim 1 , in which the heated air source is coupled to a duct that supplies an air flow.5. The tooling system of claim 1 , in which the plurality of heated air sources is controlled electrically.6. The tooling system of claim 1 , in which the plurality of heated air sources is controlled by a controller.7. The tooling system of claim 1 , in which the indentations are formed in a grid structure8. The tooling system of claim 1 , in which one or more of the indentations of the plurality of indentations are adjacent to each other.9. The tooling system of claim 1 , in which one or more of the indentations of the plurality of indentations are not immediately adjacent to each other.10. A tooling system comprising:a mold having a top surface upon which high temperature ...

Method for Identifying a Fiber-Reinforced Plastic Component, and a Resin Transfer Molding (RTM) Mold

A method for identifying a fiber-reinforced plastic component includes the acts of providing a fiber preform, applying a label to the fiber preform and holding it in place, inserting the preform together with the label in a mold and closing the mold, and infiltrating the preform with a plastic compound and curing it in the closed mold. In order to reliably identify the plastic component, the label comes to rest on a flow aid portion formed on the inner mold wall which has at least one channel-shaped depression. The longitudinal extension of the flow aid portion projects beyond the label. 1. A method for identifying a fiber-reinforced plastic component , comprising the acts of:providing a semifinished fiber product;applying and fixing a label to the semifinished fiber product;inserting the semifinished fiber product with label into a mold and closing the mold; andinfiltrating the semifinished fiber product with a plastic compound and curing the plastic compound in the closed mold;wherein the label lies on a flow aid portion which is formed on an inner wall of the mold, wherein the flow aid portion has at least one channel-shaped depression, and wherein the at least one channel-shaped depression has a length which projects beyond the label.2. The method according to claim 1 , wherein the at least one channel-shaped depression forms a lattice-shaped arrangement.3. The method according to claim 2 , wherein the lattice-shaped arrangement covers less than 30 percent of an area of the label or less than 20 percent of the area of the label.4. The method according to claim 2 , wherein the lattice-shaped arrangement extends over an area which is at least double an area of the label.5. The method according to claim 1 , wherein a width of the at least one channel-shaped depression lies in a range from 0.2 mm to 5 mm.6. The method according to claim 2 , wherein the lattice-shaped arrangement has a peripheral annular channel.7. The method according to claim 1 , wherein the label ...

MOLDING ASSEMBLY AND METHOD OF CO-CURING STIFFENER WITH PANEL

There is disclosed a molding assembly including a mold having a first surface and an opposed second surface. The mold defines a cavity bounded by two side walls converging toward each other from the first surface toward the second surface. Two mandrels are each removably receivable in the cavity and have a first wall, a second wall opposed to the first wall, an inner wall, and an outer wall opposed to the inner wall. The inner walls face each other and define a gap therebetween for receiving a composite material to be cured. The outer walls are angled and each slidably engage a respective one of the two side walls. A method of co-curing a stiffener and a panel is also disclosed. 1. A molding assembly , comprising:a mold having a first surface and an opposed second surface, the mold defining a cavity being bounded by two side walls converging toward each other from the first surface toward the second surface, the cavity having a centerline axis extending between the first and second surfaces and spaced equidistantly from the side walls; andtwo mandrels each being removably receivable in the cavity and having a first wall, a second wall opposed to the first wall, an inner wall, and an outer wall opposed to the inner wall, the inner wall and the outer wall extending from the first wall to the second wall, the inner walls facing each other and defining a gap therebetween upon the two mandrels being received in the cavity, the gap configured for receiving a composite material to be cured, the outer walls being angled and each slidably engaging a respective one of the two side walls.2. The molding assembly of claim 1 , wherein a value of an angle defined between each of the two side walls and the first surface is equal to a value of an angle defined between each of the outer walls and each of the first walls.3. The molding assembly of claim 1 , wherein each of the outer walls define an angle between 15° and 25° with the first wall.4. The molding assembly of claim 1 , ...

Elastic fastener for vacuum bag pleat

A vacuum bag having an expandable pleat is provided. The vacuum bag includes a first surface region, a second surface region, and a third surface region between the first and second surface regions. The third surface region can be folded to bring the first surface region into proximity of the second surface region. The vacuum bag also includes a strip having a first attaching region at a first end of the strip, a second attaching region at a second end of the strip opposite the first end, and a central region between the first and second attaching regions. The first attaching region is fixed to the first surface region, and the second attaching region is fixed to the second surface region such that when the central region of the strip is in a non-expanded state, the first surface region is contiguous to the second surface region.

Carbon Fiber Equestrian Tack Trunk

A carbon fiber tack trunk is described. In an example, an equestrian tack trunk comprises a base, walls and a lid made from carbon fiber. In another example, a method is described to fabricate a carbon fiber tack trunk. The method may include manufacturing composite parts of the carbon fiber equestrian tack trunk from carbon fiber. The composite parts may be seamed to fabricate the carbon fiber equestrian tack trunk. 1. An equestrian tack trunk , comprising:a base made from carbon fiber;walls of the trunk made from carbon fiber that are coupled to the base; anda lid made from carbon fiber that is coupled to at least one of the walls.2. The equestrian tack trunk of claim 1 , wherein the base claim 1 , the walls and the lid are made from a sheet of carbon fiber that is molded from at least one of a press claim 1 , a vacuum or a wet lay-up.3. The equestrian tack trunk of claim 1 , wherein the carbon fiber is a single sheet of carbon fiber.4. The equestrian tack trunk of claim 1 , further comprising a carbon fiber tray that is located within an interior portion of the equestrian tack trunk.5. The equestrian tack trunk of claim 3 , further comprising a carbon fiber tray that is located within an interior portion of the equestrian tack trunk.6. The equestrian tack trunk of claim 1 , wherein the carbon fiber material includes at least one of a resin or a pre-impregnated carbon fiber.7. The equestrian tack trunk of claim 1 , wherein at least a portion of corners of the equestrian tack trunk are rounded.8. The equestrian tack trunk of claim 1 , wherein the lid is coupled to at least one of the walls using a hinge.911-. (canceled)12. A method for fabricating a carbon fiber equestrian tack trunk claim 1 , comprising the steps of:manufacturing composite parts of the carbon fiber equestrian tack trunk, wherein the composite parts are made from carbon fiber;seaming the composite parts to fabricate the carbon fiber equestrian tack trunk.13. The method of claim 12 , wherein ...

MULTILAYER PRESPREG STRUCTURE AND METHOD OF MANUFACTURING THE SAME

Disclosed are a multilayer prepreg structure and a method of manufacturing the same. The multilayer prepreg structure includes a prepreg layer formed by impregnating a carbon fiber fabric with a first resin, and a fixed layer formed of a second resin having a higher curing rate than the first resin and provided on one surface of the prepreg layer. 1. A multilayer prepreg structure comprising:a prepreg layer formed by impregnating a carbon fiber fabric with a first resin; anda fixed layer formed of a second resin having a higher curing rate than the first resin and applied to a surface of the prepreg layer.2. The multilayer prepreg structure according to claim 1 , wherein the ratio of the thickness of the prepreg layer to the thickness of fixed layer is between about 1:0.25 and about 1:1.3. The multilayer prepreg structure according to claim 2 , wherein the thickness of the prepreg layer is 0.4 mm or less.4. The multilayer prepreg structure according to claim 1 , wherein:the first resin has a gel-time of 8-30 minutes at a temperature of 125 degrees Celsius; andthe second resin has a gel-time of 2-10 minutes at a temperature of 125 degrees Celsius.5. The multilayer prepreg structure according to claim 1 , wherein:the first resin is an epoxy resin containing a dicyandiamide-based hardener; andthe second resin is an epoxy resin containing a urea-based hardener.6. The multilayer prepreg structure according to claim 1 , further comprising a clear coat layer applied to a surface of the fixed layer.7. A method of manufacturing a multilayer prepreg structure claim 1 , the method comprising:weaving a carbon fiber fabric;impregnating the carbon fiber fabric with a first resin to form a prepreg layer;applying a fixed layer, comprising a second resin having a higher curing rate than the first resin, to one surface of the prepreg layer;vacuum-packing the prepreg layer hving the fixed layer applied thereto; andhot-pressing the vacuum-packed prepreg layer within an autoclave.8. The ...

A method of manufacturing a wind turbine blade with fewer manufacturing defects

The present invention relates to a method of manufacturing a wind turbine blade using a two-step curing process, wherein the second curing is performed in the presence of a resin flow medium () comprising a curing inhibitor.

CONSTRUCTION OF TUBULAR ASSEMBLIES

A method and apparatus for constructing a tubular assembly comprising an inner portion () and a further portion () surrounding the inner portion. The inner portion () comprises reinforcement () and the further portion () being formed from a strip () of material comprising two opposed longitudinal marginal side portions (). The apparatus comprises an assembly station () comprising a wall (). The apparatus comprises means for advancing the inner portion () along a first path () extending passed the wall (), and means for advancing the strip () along a second path () and causing the strip to encircle the wall () and thereby wrap about and surround the inner portion (). The apparatus further comprises means () for introducing resinous binder into the reinforcement () as the strip () is being wrapped about the inner portion ().

METHOD AND APPARATUS FOR FABRICATION OF COMPOSITE TOOLING

A method and apparatus for manufacturing a composite part is provided. A composite laminate is formed upon a first tool that provides a first mold line for the composite laminate. A second tool is placed against the composite laminate in which a tooling surface of the second tool is used to create a second mold line for the composite laminate. The second tool is formed from a plurality of prefabricated sections joined by a joining material in which the tooling surface is formed by a layer adhered to the plurality of prefabricated sections and the joining material. 1. A method for manufacturing a composite part , the method comprising:forming a composite laminate upon a first tool that provides a first mold line for the composite laminate; andplacing a second tool against the composite laminate in which a tooling surface of the second tool is used to create a second mold line for the composite laminate, the second tool being formed from a plurality of prefabricated sections joined by a joining material in which the tooling surface is formed by a layer adhered to the plurality of prefabricated sections and the joining material.2. The method of claim 1 , wherein the layer has a release side that forms the tooling surface and an adhesive side adhered to the plurality of prefabricated sections and the joining material.3. The method of claim 2 , wherein the layer is a pressure sensitive tape.4. The method of claim 1 , wherein the joining material is an adhesive that is a quick-hardening adhesive material.5. The method of claim 1 , further comprising:curing the composite laminate; andremoving the first tool and the second tool to leave the composite part.6. A portion of an aircraft fabricated according to the method of .7. A method for forming a composite part claim 1 , the method comprising:forming a composite laminate upon a first tool that provides a first mold line for the composite laminate; andplacing a second tool against the composite laminate in which a tooling ...

METHOD AND TOOL FOR MANUFACTURING A COMPOSITE AIRCRAFT WINDOW FRAME

The invention relates to a method for manufacturing a composite aircraft window frame; the method comprises the steps of: a) positioning in a mold a preform made of pre-impregnated material including dispersed fibers, with a predefined orientation, in a thermosetting resin matrix; b) closing the mold so as to define a gap between at least one surface of said preform and a portion of said mold; c) injecting thermosetting resin into the closed mold through an inlet opening of the mold itself, so as to fill the gap and completely lap said surface of the preform; and d) applying a uniform hydrostatic pressure on the surface by the injection of the resin. 1. A method for manufacturing a composite aircraft window frame; the method comprising the steps of:a) positioning in a mold a preform made of pre-impregnated material including dispersed fibers, with a predefined orientation, in a thermosetting resin matrix;b) closing the mold so as to define a gap between at least one surface of said preform and a portion of said mold;c) injecting thermosetting resin into the closed mold through an inlet opening of the mold itself, so as to fill said gap and completely lap said surface of the preform; andd) applying a uniform hydrostatic pressure on said surface by the injection of said resin.2. The method as claimed in claim 1 , wherein the step d) comprises the steps of:e) sealing the mold in a fluid-tight manner, with the exception of said inlet opening; andf) continuing to inject the resin through said inlet opening.3. The method as claimed in claim 2 , wherein the mold comprises an outlet opening through which the resin exits claim 2 , in use claim 2 , from the mold itself; and in which the step c) is carried out with the outlet opening opened and the step d) is carried out with the outlet opening sealed.4. The method as claimed in claim 1 , wherein claim 1 , in steps c) and d) claim 1 , the thermosetting resin is injected onto said surface claim 1 , without impregnating the ...

METHOD AND SEMI-FINISHED ITEM FOR PRODUCING COMPOSITE PRODUCTS AND THE PRODUCTS THUS OBTAINED

A method for producing products made of composite material, comprising the following operating steps: 115-. (canceled)16. A semi-finished item for producing composite material products , the semi-finished item comprising:at least one fabric layer of composite material fiber fabric,at least one resin layer of non-polymerized, non-self-reacting composite material resin, substantially free of hardener, is-applied on a first surface of the at least one fabric layer,at least one thermoplastic film applied on a second surface of the at least one fabric layer opposite to the first surface.17. The semi-finished item according to claim 16 , and further comprising a protective sheet applied removably on the at least one resin layer.1821-. (canceled) This invention relates to a method for producing composite products comprising layers of fibres, specifically layers of carbon fibre fabrics. This description also relates to a semi-finished item which can be used in this method and to a product made using this method and/or with this semi-finished item.As is known, the RTM (Resin Transfer Moulding) method can be used to produce parts from composite materials comprising carbon fibre fabrics. In this known method, one or more superposed layers of dry fabric, that is to say, fabric which is substantially not impregnated with resins, are placed between two matching moulds into which a resin mixed with a hardener is injected under high pressure in such a way that the resin polymerizes in the mould to obtain the finished product.In a variant of this method, known as RTM-L (RTM-Light), the resin is injected at a lower pressure so as to increase the working life of the moulds and thus reduce investment costs.While the resin is being injected, however, in the RTM and RTM-L methods, the fibres of the fabric layers, especially the outer layers, are displaced on account of the resin pressure gradients at the impregnation stage, with consequent loss of weave regularity, worsening the ...

COMPOSITE ARTICLE WITH FLY-AWAY BAG CARRIER

Provided is a method for forming a co-cured composite article. The method includes: providing a bag carrier; providing a vacuum bag, wherein the vacuum bag at least partially surrounds the bag carrier; providing an outer skin, wherein the outer skin at least partially surrounds the vacuum bag; forming a space between the bag carrier and the the outer skin; and providing a filler between the outer skin and the bag carrier. 1. A method for forming a co-cured composite article , comprising:providing a bag carrier;providing a vacuum bag, wherein the vacuum bag at least partially surrounds the bag carrier;providing an outer skin, wherein the outer skin at least partially surrounds the vacuum bag;pressurizing the vacuum bag, wherein at least a portion of the pressurized vacuum bag is positioned to define a space between the outer skin and the bag carrier; andproviding a filler between the outer skin and the bag carrier.2. The method of claim 1 , wherein the providing of the filler comprises at least partially filling the space between the bag carrier and the outer skin with the filler.3. The method of claim 2 , wherein the filler comprises an uncured resin.4. The method of claim 3 , further comprising at least partially curing the uncured resin to form an at least partially cured resin.5. The method of claim 4 , wherein the cured resin comprises a thickness of from about 0.02″ to about 1″.6. The method of claim 2 , wherein the filler material comprises a liquid foam.7. The method of claim 6 , further comprising solidifying the liquid foam to form a solid foam.8. The method of claim 7 , wherein a thickness of the solid foam is in a range of from about 10% to about 200% of a thickness of the outer skin.9. The method of claim 1 , wherein the filler comprises plaster of paris.10. The method of claim 1 , wherein providing of the filler comprises at least partially filling the space between the outer skin and the bag carrier.11. The method of claim 1 , wherein the providing of ...

Method of curing a composite article using differential vacuum

A method of curing a composite layup may include applying an inner bag vacuum pressure to an inner bag chamber and an outer vacuum pressure to an outer vacuum chamber. The vacuum inner bag chamber may be formed by a vacuum bag covering a composite layup and sealed to a forming tool with an inner bag chamber seal. The inner bag vacuum pressure may be no less than the outer vacuum pressure. The temperature of the composite layup may be increased to an elevated temperature to initiate a temperature hold period. The method may additionally include venting the outer vacuum chamber to atmosphere to initiate an outer vacuum chamber venting period during the temperature hold period, and applying compaction pressure to the inner bag chamber seal during the outer vacuum chamber venting period. The outer vacuum pressure may be re-applied to the outer vacuum chamber to terminate the outer vacuum chamber venting period.

DEVICE FOR HEATING A MOLD

A heating device to heat a molding face, particularly a large molding face. The heating device includes a metal sheet having a ferromagnetic layer, and a part formed into a shape that defines the molding face and a forming plane. A base of the heating device supports the metal sheet. An inductor of the heating device provides the induction heating of the metal sheet. 134-. (canceled)35. A heating device to heat a molding face , comprising a metal sheet comprising a ferromagnetic layer and a part formed into a shape that defines the molding face and a forming plane; a base; support studs to support the metal sheet on the base; and an induction circuit providing an induction heating of said metal sheet.36. The heating device according to claim 35 , wherein the base is made of a non-metallic and non-electrically conductive material claim 35 , the material being either concrete or ceramic.37. The heating device according to claim 35 , wherein the metal sheet comprises a ferromagnetic layer made of an alloy of a FeNi36 type comprising iron and nickel.38. The heating device according to claim 35 , wherein the metal sheet comprises a ferromagnetic layer made of nickel.39. The heating device according to claim 35 , further comprising a bagging to demarcate claim 35 , with the molding face claim 35 , a sealed cavity configured to contain a fibrous preform; and a vacuum pump and a conduit to apply a vacuum to a volume located between the molding face and the bagging.40. The heating device according to claim 39 , further comprising an injector to inject a resin in the sealed cavity demarcated by the molding face.41. The heating device according to claim 35 , further comprising a circuit to circulate a cooling fluid in contact with the metal sheet.42. The heating device according to claim 39 , wherein the bagging comprises a bladder comprising a heater.43. The heating device according to claim 39 , wherein the molding face of the metal sheet is ferromagnetic; and the heating ...

Method of liquid resin infusion of a composite preform

An assembly and method for infusing composite material with liquid resin to form a composite part with a smooth outer mold line (OML) surface and a complex inner mold line (IML) surface. The method may include placing a flow media into a deepest tier of a two-tiered recess in a rigid tool, placing a perforated caul sheet into a shallowest tier of the two-tiered recess, and placing uninfused composite material over the perforated caul sheet. Next, the method may include placing an impermeable membrane over the composite material and sealing the impermeable membrane to the rigid tool. Finally, the method may include vacuuming air from a vacuum port of the impermeable membrane to compress the impermeable membrane toward the composite material and the rigid tool, thus pull liquid resin from a resin reservoir, through the flow media, through the perforations of the caul sheet, and throughout the composite material.

MOLDING DEVICE

A molding device for curing of composite components comprising: a molding die, composite material in the molding die, heat application means, sheathing means for the composite material and the molding die and vacuum means for the application of vacuum to the composite material in the molding die. The heat application means comprise at least one heat pipe with a heat exchanger attached to the molding die for thermal conduction to the composite material. 2. The molding device according to claim 1 , wherein at least one heat exchanger is provided with the heat pipe claim 1 , said at least one heat exchanger being inside the molding die.3. The molding device according to claim 2 , wherein the heat exchanger of the heat pipe is in contact with the composite components through the molding die.4. The molding device according to claim 1 , wherein a plurality of heat pipes are arranged in parallel through the molding die.5. The molding device according to claim 1 , wherein a plurality of heat pipes have a fan type arrangement in the molding die.6. The molding device according to claim 1 , wherein at least one outer heat pipe is connected for thermal conduction to an inner heat pipe through the molding die.7. The molding device according to claim 2 , wherein the at least one heat exchanger comprises a die heat exchanger and a base heat exchanger and wherein a contact force generating element is provided between said die heat exchanger and said base heat exchanger claim 2 , said contact force generating element pressing the die heat exchanger against the molding die and the base heat exchanger against the base plate. This application claims priority to European patent application No. 13 400022.3 filed on Oct. 15, 2013, the disclosure of which is incorporated in its entirety by reference herein.(1) Field of the InventionThe invention is related to a molding device for composite components with the features of the preamble of claim .(2) Description of Related ArtMolding of ...

Method for the simultaneous production of two or more fiber composite components and fiber composite component

A method for the simultaneous production of two or more fiber composite components, to a fiber composite component, to a rotor blade of a wind power installation, as well as to a wind power installation. A method for the simultaneous production of two or more fiber composite components, in particular of two or more substantially identical fiber composite components which have a component contour, the method comprising providing at least one fibrous material, at least one planar separation element, and at least one matrix material, wherein the at least one planar separation element at least in portions is permeable to the matrix material; producing a semi-finished fibrous pack by disposing the fibrous material layer-by-layer so as to form semi-finished fibrous products stacked on top of one another, wherein at least one of the planar separation elements is in each case disposed between the semi-finish fibrous products; infusing the semi-finished fibrous pack with the matrix material; cutting the component contour into the infused semi-finished fibrous pack.

MOLDING SYSTEM AND METHODS FOR FORMING STRUCTURES

A molding system and methods of forming a structure are presented. The molding system is configured to sequentially form features of a structure. The molding system comprises a first tool comprising a number of features configured to completely form a first set of radii of a structure and a number of partial forming features configured to partially form a second set of radii of the structure, and a second tool comprising a number of completion features configured to complete shaping of the second set of radii. 1. A molding system configured to sequentially form features of a structure , the molding system comprising:a first tool comprising a number of features configured to completely form a first set of radii of a structure and a number of partial forming features configured to partially form a second set of radii of the structure; anda second tool comprising a number of completion features configured to complete shaping of the second set of radii.2. The molding system of claim 1 , wherein the first tool comprises a male mold having the number of features.3. The molding system of claim 2 , wherein the number of features comprises a first corner and a second corner.4. The molding system of claim 3 , wherein the number of partial forming features are configured to form angles into a preform claim 3 , wherein the angles are larger than final angles of the second set of radii of the structure.5. The molding system of claim 1 , wherein the first tool and the second tool are configured to form a structure having a hat-shaped cross-section.6. The molding system of further comprising:a first bagging layer and a second bagging layer positioned between the first tool and the second tool.7. The molding system of claim 6 , wherein the first bagging layer and the second bagging layer are both sealed to the first tool.8. The molding system of claim 7 , wherein the second tool is sealed to the second bagging layer.9. The molding system of claim 8 , wherein the number of ...

Improved system and method for resin transfer moulding

Apparatuses, devices, systems 1 and methods for resin transfer moulding of composite articles are disclosed. A mould enclosure enclosing a fibre pack ( 9 ) is provided and one or more resin ports ( 6 a - 6 e ) are provided along a resin flow path within the fibre pack ( 9 ). Resin ingress into the fibre pack ( 9 ) is controlled via valves ( 44 a - 44 e ) or a flow control mechanism ( 30 ), each being operable to impose a flow rate on resin passing into the fibre pack ( 9 ).

Composite components with impact detection

A fiber-reinforced polymer composite component formed from a polymer matrix material containing fiber reinforcement. The component comprises a main portion and at least one raised feature extending from a surface plane s of said main portion. The at least one raised feature is arranged to incur visually perceptible damage when the component is subject to an impact with an energy above a predetermined impact energy threshold and to resist an impact with an energy below the predetermined impact energy threshold.

LAMINATE APPARATUS WITH BONDED LINER

A laminate apparatus for engaging a fluid includes a structural medium made from plies bonded together with a resin. The structural medium defines a fluid facing surface. The laminate apparatus further includes a liner membrane bonded to the fluid facing surface of the structural medium with the resin. The liner membrane has one or more of a desired barrier characteristic and a desired chemical compatibility characteristic with respect to the fluid. 1. A laminate apparatus for engaging a fluid , the laminate apparatus comprising:a structural medium comprising plies bonded together with a resin, wherein the structural medium defines a fluid facing surface; anda liner membrane bonded to the fluid facing surface of the structural medium with the resin, wherein the liner membrane has one or more of a desired barrier characteristic and a desired chemical compatibility characteristic with respect to the fluid.2. The laminate apparatus of claim 1 , wherein the liner membrane is free of vacuum lines and resin injection lines.3. The laminate apparatus of claim 1 , wherein the laminate apparatus is a cryogenic fluid containment vessel and the fluid is a cryogenic fluid.4. The laminate apparatus of claim 1 , wherein the structural medium further comprises reinforcing fabric plies.5. A laminate system comprising:a structural mold;a structural medium comprising resin infusible plies, wherein the structural medium defines a fluid facing surface and an opposite surface, wherein the opposite surface engages the structural mold; anda liner membrane bondable to the fluid facing surface of the structural medium, wherein the liner membrane has one or more of a desired barrier characteristic and a desired chemical compatibility characteristic with respect to the fluid, wherein the liner membrane is sealable about the fluid facing surface of the structural medium to form, in conjunction with the structural mold, a vacuum enclosure about the structural medium for a vacuum resin infusion ...

Method for infusing resin into a composite laminate

A method of infusing a preform with a resin for the formation of a composite laminate in which the preform is placed between a mold and a vacuum bag. An offset tool is placed outside of the vacuum bag so as to permit the vacuum bag to lift away from a surface of the preform in a controlled amount. A charge of the resin is injected between the vacuum bag and the preform so as to lift the vacuum bag off the surface of the preform and move the vacuum bag toward the offset tool, so that the resin occupies a volume between the vacuum bag and the surface of the preform. The preform is infused with the resin by applying a super-atmospheric pressure to an outer surface of the vacuum bag to transport the resin from the volume between the vacuum bag and the surface of the preform into a volume within the preform. The resin in the preform is cured, thereby forming the composite laminate.

FIBER REINFORCED THERMOPLASTIC COMPOSITES AND METHODS OF MAKING

Methods of making a fiber-reinforced thermoplastic polyurethane composite are described. The methods may include applying a sizing composition to a plurality of fibers to make sized fibers, where the sizing composition may include at least one curative for a thermoplastic polyurethane prepolymer. The sized fibers may be contacted with a thermoplastic polyurethane prepolymer composition to form a resin-fiber amalgam, where the thermoplastic polyurethane prepolymer composition includes 50 wt. % or less of a total amount of the curative that is also present on the sized fibers. The resin-fiber amalgam may then be cured to form the fiber-reinforced thermoplastic polyurethane composite. 1. A method of making a fiber-reinforced polyurethane composite , the method comprising:applying a sizing composition to a plurality of fibers to make sized fibers, wherein the sizing composition comprises at least one curative for a thermoplastic polyurethane prepolymer;contacting the sized fibers with the thermoplastic polyurethane prepolymer composition to form a resin-fiber amalgam, wherein the thermoplastic polyurethane prepolymer composition includes 50 wt. % or less of a total amount of the at least one curative that is also present on the sized fibers; andcuring the resin-fiber amalgam to form the fiber-reinforced polyurethane composite.2. The method of claim 1 , wherein the thermoplastic polyurethane prepolymer composition comprises 0 wt. % of the curative that is present on the sized fibers.3. The method of claim 1 , wherein the thermoplastic polyurethane prepolymer composition is the reaction product of a polyol and a polyisocyanate compound.4. The method of claim 3 , wherein the polyol comprises a polyester polyol or a polyether polyol.5. The method of claim 4 , wherein the polyester polyol comprises a reaction product of adipic acid and diethylene glycol.6. The method of claim 4 , wherein the polyether polyol comprises a polyalkylene glycol.7. The method of claim 1 , wherein ...

METHOD OF MANUFACTURING A COMPOSITE ARTICLE

A method for creating a composite article using fast heat treating thermoset resin materials for 3D printing articles, including articles of complex geometry. The method includes using vacuum impregnation and subsequent heat treating as post printing processes to further strengthen and enhance the functionality of the article. 1. A method of creating a composite article comprising:creating a three dimensional virtual model of the article;dividing the virtual model into a plurality of contiguous two dimensional layers;loading the divided virtual model into a three dimensional printing device that is operable to create a three dimensional article made from a thermoset polymer resin material;impregnating the three dimensional article with a reinforcing material; andheat treating the impregnated three dimensional article.2. The method of wherein the thermoset polymer resin material is an epoxy resin with or without reinforcing fillers.3. The method of wherein the thermoset polymer resin is a phenolic resin with or without reinforcing fillers.4. The method of wherein the thermoset polymer resin is an unsaturated polyester based resin system with or without reinforcing fillers.5. The method of wherein impregnating the three dimensional article further comprises using a liquid thermoset resin having curatives.6. The method of wherein impregnating the three dimensional article is accomplished with a vacuum impregnation process.7. The method of wherein impregnating the three dimensional article is accomplished with a pressurized impregnation process.8. The method of wherein the liquid thermoset resin is an epoxy resin.9. The method of wherein the liquid thermoset resin is phenolic resin.10. The method of wherein the liquid thermoset resin is an unsaturated polyester based resin system.11. The method of wherein the liquid thermoset resin includes at least one reinforcing filler material.12. The method of wherein heat treating the impregnated article further comprises heat ...

COMPOSITE MATERIAL PRESSURIZING DEVICE AND COMPOSITE MATERIAL FORMING METHOD

A first pressure transmission member is formed of a soft material that is softer than the material of a second pressure transmission member. The second pressure transmission member has an area that is larger than that of the first pressure transmission member, and includes a pressurizing surface in contact with the first pressure transmission member, and a pressure receiving surface, which is disposed on the reverse side of the pressurizing surface, and which faces a bag material, the pressure receiving surface having an area that is larger than that of the pressurizing surface. 1. A composite material pressurizing device used to form a composite material member made of a composite material containing resin , the device comprising:a first pressure transmission member disposed in contact with a forming region of the composite material member;a second pressure transmission member having a plate shape, being in contact with the first pressure transmission member, and pressurizing the composite material member via the first pressure transmission member;a bag material covering the first pressure transmission member and the second pressure transmission member; anda vacuum generation unit generating a vacuum in a space formed between the bag material and the composite material member,wherein the first pressure transmission member is formed of a soft material softer than a material of the second pressure transmission member,wherein the second pressure transmission member has a larger area than the first pressure transmission member, and includes a pressurizing surface in contact with the first pressure transmission member, and a pressure receiving surface which is disposed on a reverse side of the pressurizing surface, and which faces the bag material, andwherein the pressure receiving surface has a larger area than the pressurizing surface.2. The composite material pressurizing device according to claim 1 ,wherein the second pressure transmission member is formed of a hard ...

PRESS MOULDING METHOD

A method of press moulding a moulding material to form a moulded part of fibre-reinforced resin matrix composite material, the method comprising the steps of: 1. A method of press moulding a moulding material to form a moulded part of fibre-reinforced resin matrix composite material , the method comprising the steps of:i. providing a mould tool having a lower mould part and an upper mould part, the upper mould part having a first moulding surface for moulding a first moulded surface of the moulded part and the lower mould part having a second moulding surface for moulding a second moulded surface of the moulded part;ii. providing a multilaminar panel of moulding material comprising at least one layer of fibres and at least one layer of resin, the multilaminar panel having first and second opposite major surfaces;iii. locating the moulding material in the mould tool; a. a preliminary closing phase to achieve mutual engagement between the lower and upper mould parts,', 'b. a secondary closing phase after engagement between the lower and upper mould parts with the mould tool partially closed to define a closed intermediate cavity containing the moulding material, the closed intermediate cavity being larger than the moulded part and the first moulding surface of the upper mould part being spaced from the first major surface by a spacing distance, in the secondary phase air being at least partially evacuated from the closed intermediate cavity while the first moulding surface of the upper mould part is spaced from the first major surface to provide a vacuum pressure, and', I. a first stage prior to both the first moulding surface contacting the first major surface and the second moulding surface contacting the second major surface, and', 'II. a second compression stage after both the first moulding surface has contacted the first major surface and the second moulding surface has contacted the second major surface, the closure speed of relative movement between the lower ...

Press moulding method

A method of press moulding a moulding material to form a moulded part of fibre-reinforced resin matrix composite material, the method comprising the steps of: i. providing a mould tool having a lower mould part and an upper mould part, the upper mould part having a first moulding surface for moulding a first moulded surface of the moulded part and the lower mould part having a second moulding surface for moulding a second moulded surface of the moulded part; ii. providing a multilaminar panel of moulding material comprising at least one layer of fibres and at least one layer of resin, the multilaminar panel having first and second opposite major surfaces, a surface resin layer of the multilaminar panel being at or adjacent to the first major surface; iii. locating the moulding material in the mould tool; iv. closing the mould tool to define a substantially closed mould cavity containing the moulding material, the closing step including the sub-steps of: a. partially closing the mould tool to define a closed intermediate cavity containing the moulding material, the closed intermediate cavity being larger than the moulded part and the first moulding surface of the upper mould part being spaced from the first major surface, the upper mould part being at an elevated temperature as compared to the temperature of the moulding material; and b. at least partially evacuating air from the closed intermediate cavity while the first moulding surface of the upper mould part is spaced from the first major surface; v. applying pressure to the moulding material in the mould cavity to configure the moulding material in a fully moulded shape; and vi. substantially fully curing the resin to form a moulded part from the moulding material.

COMPOSITE MATERIAL STRUCTURE AND MANUFACTURING METHOD OF COMPOSITE MATERIAL STRUCTURE

According to one implementation, a composite material structure includes a corrugated stringer and a panel. The corrugated stringer has a corrugated structure including portions each having hat-shaped cross section. The corrugated stringer is made of a composite material. The panel is integrated with the corrugated stringer. The is made of a composite material. Further, according to one implementation, a manufacturing method of a composite material structure includes: setting a textile on a laminated body of prepregs; and producing the composite material structure by covering the laminated body with a bagging film, forming a vacuum state in a space covered with the bagging film, impregnating the textile with the resin, and thermal curing of the laminated body of the prepregs. The laminated body is a panel before curing. The textile has a structure corresponding to a corrugated stringer. 1. A composite material structure comprising:a stringer having a corrugated structure including portions each having hat-shaped cross section, the stringer being made of a composite material; anda panel integrated with the stringer, the panel being made of a composite material,wherein a foamed core material is filled inside each of the portions each having the hat-shaped cross section.2. A composite material structure comprising:a stringer having a corrugated structure including portions each having hat-shaped cross section, the stringer being made of a composite material; anda panel integrated with the stringer, the panel being made of a composite material,wherein the stringer is made of a composite material which is reinforced by woven fibers of which length directions include a board thickness of the stringer and a direction perpendicular to the board thickness of the stringer.3. The composite material structure according to claim 2 ,wherein a foamed core material is filled inside each of the portions each having the hat-shaped cross section.4. The composite material structure ...