JP6426722B2 - フロートの集合を伴う繊維構造 - Google Patents
フロートの集合を伴う繊維構造 Download PDFInfo
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Description
本発明の方法により繊維材料を製造するステップと、
各々の2次元織物層を把持し、繊維構造のブランク部分の限界において各2次元織物層の糸を切断するステップとを含むことを特徴とする、繊維補強プリフォームの製造方法をも提供する。
Claims (16)
- 第1の複数の糸層と第2の複数の糸層の間の3次元製織により単一の部品として形成されたブランク部分(210)を含む繊維構造(200)であって、前記ブランク部分が複合材料製の部品用の繊維補強プリフォームの全体又は一部分に対応している繊維構造において、
前記繊維構造(200)は1つ以上の2次元織物層(220a、220b)を含み、各2次元織物層が、ブランク部分(210)から退出した後の第1の複数の糸層の少なくとも一部を成す単一の層(201a)の糸(2010a)を集合させており、各2次元織物層が、ブランク部分の外側で、前記2次元織物層内に集合された第1の複数の糸層の糸の方向に延在していることを特徴とする繊維構造(200)。 - 第1の複数の糸層の糸(2010a)が縦糸に対応し、一方第2の複数の糸層の糸(2020a)が横糸に対応し、各々の2次元織物層(220a;220b)がブランク部分(210)に隣接していることを特徴とする、請求項1に記載の繊維構造。
- 各々の2次元織物層(220a;220b)の内部で、単一の縦糸層の糸(2010a)が単一の横糸層の糸(2020a)と合わせて製織されることを特徴とする、請求項2に記載の繊維構造。
- 各々の2次元織物層(420)がブランク部分から規定の距離のところに位置していることを特徴とする、請求項1に記載の繊維構造。
- 前記繊維構造が、ブランク部分(510)から引き出された横糸(5020a)を集合させ単一の横糸(502a)層に属する2次元織物層(521、522)を含むことを特徴とする、請求項4に記載の繊維構造。
- 第1の複数の糸層の糸が縦糸(6010a)に対応し、一方第2の複数の糸層の糸が横糸(6020a)に対応し、ブランク部分(610)が厚みの減少する部分(614)と厚みの増大する部分(615)とを含み、縦糸(6010a)が、厚みの減少する部分(614)を介してブランク部分(610)から引き出され、厚みの増大する部分(615)を介してブランク部分内に再挿入されており、前記繊維構造が、ブランク部分から引き出された縦糸(6010a)を集合させ単一の縦糸層(601a)に属する2次元織物層(620、621)を含むことを特徴とする、請求項1に記載の繊維構造。
- 第1の複数の糸層の糸が縦糸に対応し、一方第2の複数の糸層の糸が横糸に対応し、ブランク部分が厚みの減少する部分と厚みの増大する部分とを含み、縦糸が、厚みの減少する部分を介してブランク部分から引き出されており、厚みの増大する部分を介してブランク部分内に再挿入されており、前記繊維構造が、ブランク部分から引き出された横糸を集合させ単一の横糸層に属する2次元織物層を含むことを特徴とする、請求項1に記載の繊維構造。
- 各々の2次元織物層(620;621)が、第1の複数の層の糸の方向に対して直交する方向に配向された切抜き(620a;621a)を含むことを特徴とする、請求項6又は7に記載の繊維構造。
- 第1の複数の糸層と第2の複数の糸層の間の3次元製織により単一の部品としてブランク部分(210)を製織するステップを含む繊維構造の製造方法であって、前記ブランク部分が複合材料製の部品用の繊維補強プリフォームの全体又は一部分に対応している繊維構造の製造方法において、
前記製造方法は、ブランク部分(210)の外側で、1つ以上の2次元織物層(220a、220b)を製織するステップを含み、
各2次元織物層が、ブランク部分(210)から退出した後の第1の複数の糸層の少なくとも一部を成す単一の層(201a)の糸(2010a)を集合させており、各2次元織物層が、ブランク部分の外側で、前記2次元織物層内に集合された第1の複数の糸層の糸の方向に延在していることを特徴とする繊維構造の製造方法。 - 第1の複数の糸層(2010a)の糸が縦糸に対応し、一方第2の複数の糸層(2020a)の糸が横糸に対応し、各々の2次元織物層(220a;220b)がブランク部分(210)に隣接して製織されることを特徴とする、請求項9に記載の繊維構造の製造方法。
- 各々の2次元織物層(220a;220b)の内部で、単一の縦糸(201a)層の糸(2010a)が単一の横糸層の糸(2020a)と合わせて製織されることを特徴とする、請求項10に記載の繊維構造の製造方法。
- 各々の2次元織物層(420)がブランク部分から規定の距離のところで製織されることを特徴とする、請求項9に記載の繊維構造の製造方法。
- 第1の複数の糸層の糸が縦糸(6010a)に対応し、一方第2の複数の糸層の糸が横糸(6020a)に対応し、ブランク部分(620)が厚みの減少する部分(614)と厚みの増大する部分(615)とを含み、縦糸(6010a)が、厚みの減少する部分(614)を介してブランク部分(610)から引き出され、厚みの増大する部分(615)を介してブランク部分内に再挿入され、前記製造方法が、ブランク部分(610)から引き出された縦糸(6010a)を集合させ単一の縦糸層(601a)に属する2次元織物層(620、621)を製織するステップを含むことを特徴とする、請求項9に記載の繊維構造の製造方法。
- 第1の複数の糸層の糸が縦糸に対応し、一方第2の複数の糸層の糸が横糸に対応し、ブランク部分が厚みの減少する部分と厚みの増大する部分とを含み、縦糸が、厚みの減少する部分を介してブランク部分から引き出され、厚みの増大する部分を介してブランク部分内に再挿入され、前記製造方法が、ブランク部分から引き出された横糸を集合させ単一の横糸層に属する2次元織物層を製織するステップを含むことを特徴とする、請求項9に記載の繊維構造の製造方法。
- 各々の2次元織物層(620;621)の中に切抜き(620a;621a)を形成するステップをさらに含み、切抜きが第1の複数の層の糸の方向に対して直交する方向に配向されていることを特徴とする、請求項13又は14に記載の繊維構造の製造方法。
- 請求項9〜15のいずれか一項に記載の繊維材料を製造するステップと、
各々の2次元織物層を把持し、繊維構造のブランク部分の限界において各2次元織物層の糸を切断するステップとを含むことを特徴とする、繊維補強プリフォームの製造方法。
Applications Claiming Priority (3)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
FR1359476 | 2013-10-01 | ||
FR1359476A FR3011253B1 (fr) | 2013-10-01 | 2013-10-01 | Structure fibreuse avec regroupement des flottes |
PCT/FR2014/052449 WO2015049449A1 (fr) | 2013-10-01 | 2014-09-29 | Structure fibreuse avec regroupement des flottes |
Publications (2)
Publication Number | Publication Date |
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JP2016533437A JP2016533437A (ja) | 2016-10-27 |
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EP (1) | EP3052685B1 (ja) |
JP (1) | JP6426722B2 (ja) |
CN (1) | CN105593417B (ja) |
BR (1) | BR112016007194B1 (ja) |
CA (1) | CA2925836C (ja) |
FR (1) | FR3011253B1 (ja) |
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Families Citing this family (9)
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FR3040909B1 (fr) * | 2015-09-16 | 2018-03-16 | Safran Aircraft Engines | Preforme fibreuse pour aube de turbomachine en materiau composite et procede de fabrication d'une telle preforme |
US10436036B2 (en) * | 2016-07-05 | 2019-10-08 | Safran Aircraft Engines | Fitted platform for a turbine engine fan, and a method of fabricating it |
FR3082854B1 (fr) | 2018-06-25 | 2020-09-11 | Safran Ceram | Structure fibreuse et piece en materiau composite incorporant une telle structure |
WO2019097147A1 (fr) | 2017-11-14 | 2019-05-23 | Safran Ceramics | Structure fibreuse et piece en materiau composite incorporant une telle structure |
FR3076814B1 (fr) * | 2018-01-12 | 2020-01-31 | Safran Aircraft Engines | Aube ou pale d'helice composite avec longeron integre pour aeronef |
US20200141268A1 (en) * | 2018-11-01 | 2020-05-07 | General Electric Company | Frangible Gas Turbine Engine Airfoil |
CN109972271B (zh) * | 2019-03-27 | 2023-03-14 | 南京玻璃纤维研究设计院有限公司 | 一种变厚度预制体、一种复合部件以及一种变厚度预制体的减纱方法 |
FR3102391B1 (fr) * | 2019-10-29 | 2021-10-15 | Safran | Préforme fibreuse tissée pour réaliser une pièce en matériau composite, notamment une aube de turbomachine |
FR3107719B1 (fr) * | 2020-03-02 | 2023-02-10 | Safran Aircraft Engines | Texture fibreuse pour aube de turbomachine en matériau composite |
Family Cites Families (20)
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JP4062879B2 (ja) * | 2000-12-11 | 2008-03-19 | 株式会社豊田自動織機 | 三次元繊維構造体 |
US6446675B1 (en) * | 2001-07-05 | 2002-09-10 | Albany International Techniweave, Inc. | Minimum distortion 3D woven preforms |
JP2005002514A (ja) * | 2003-06-12 | 2005-01-06 | Mitsubishi Rayon Co Ltd | 複合材料用三次元織編組物及びその製造方法並びに三次元プリフォーム |
FR2861143B1 (fr) * | 2003-10-20 | 2006-01-20 | Snecma Moteurs | Aube de turbomachine, notamment aube de soufflante et son procede de fabrication |
FR2902803B1 (fr) * | 2006-06-21 | 2008-11-14 | Snecma Propulsion Solide Sa | Structure fibreuse de renfort pour piece en materiau composite et piece la comportant |
FR2902802B1 (fr) * | 2006-06-21 | 2008-12-12 | Snecma Propulsion Solide Sa | Structure fibreuse de renfort pour piece en materiau composite et piece la comportant |
FR2913053B1 (fr) * | 2007-02-23 | 2009-05-22 | Snecma Sa | Procede de fabrication d'un carter de turbine a gaz en materiau composite et carter ainsi obtenu |
JP4544266B2 (ja) * | 2007-05-11 | 2010-09-15 | 株式会社豊田自動織機 | 繊維強化複合材 |
JP2009161886A (ja) * | 2008-01-09 | 2009-07-23 | Toray Ind Inc | 強化繊維基材、プリフォーム、複合材料およびその製造方法 |
FR2932408B1 (fr) * | 2008-06-11 | 2010-05-28 | Aircelle Sa | Preforme destinee a former une piece mecanique structurante creuse |
FR2939153B1 (fr) * | 2008-11-28 | 2011-12-09 | Snecma Propulsion Solide | Realisation d'une structure fibreuse a epaisseur evolutive par tissage 3d |
FR2939129B1 (fr) | 2008-11-28 | 2014-08-22 | Snecma Propulsion Solide | Aube de turbomachine en materiau composite et procede pour sa fabrication. |
GB0901189D0 (en) * | 2009-01-26 | 2009-03-11 | Rolls Royce Plc | Manufacturing a composite component |
FR2953225B1 (fr) * | 2009-11-30 | 2012-03-02 | Snecma | Composant comportant des fils de renfort sous la forme de fils de chaine et de fils de trame tisses en trois dimensions. |
FR2954271B1 (fr) * | 2009-12-21 | 2012-02-17 | Snecma | Pale d'helice d'aeronef |
FR2962175B1 (fr) * | 2010-07-02 | 2012-08-10 | Snecma | Aube a longeron composite integre |
RU2616574C2 (ru) * | 2011-12-14 | 2017-04-17 | Снекма | Волокнистая структура, имеющая нити с переменным номером пряжи |
WO2013088038A2 (fr) * | 2011-12-14 | 2013-06-20 | Snecma | Structure fibreuse de renfort de pieces en materiau composite a portion d'epaisseur reduite |
CN102517759B (zh) * | 2011-12-29 | 2013-12-25 | 山东岱银纺织集团股份有限公司 | 同幅异厚三维机织物的织造方法 |
WO2013104852A2 (fr) * | 2012-01-09 | 2013-07-18 | Snecma | Preforme fibreuse d'une aube de turbomachine en materiau composite a plate-forme integree, et son procede de realisation |
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- 2013-10-01 FR FR1359476A patent/FR3011253B1/fr active Active
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2014
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- 2014-09-29 JP JP2016519854A patent/JP6426722B2/ja active Active
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EP3052685B1 (fr) | 2017-11-15 |
FR3011253B1 (fr) | 2016-06-10 |
WO2015049449A1 (fr) | 2015-04-09 |
US20160244897A1 (en) | 2016-08-25 |
CA2925836C (fr) | 2021-09-21 |
RU2016117234A3 (ja) | 2018-05-31 |
US10041196B2 (en) | 2018-08-07 |
EP3052685A1 (fr) | 2016-08-10 |
BR112016007194A2 (pt) | 2017-08-01 |
BR112016007194B1 (pt) | 2021-11-23 |
CN105593417A (zh) | 2016-05-18 |
CN105593417B (zh) | 2017-06-30 |
RU2016117234A (ru) | 2017-11-13 |
CA2925836A1 (fr) | 2015-04-09 |
JP2016533437A (ja) | 2016-10-27 |
FR3011253A1 (fr) | 2015-04-03 |
RU2664216C2 (ru) | 2018-08-15 |
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