JPH06257404A - Blade/shaft cylinder integrated type three dimensional fiber-structural body and manufacture thereof - Google Patents
Blade/shaft cylinder integrated type three dimensional fiber-structural body and manufacture thereofInfo
- Publication number
- JPH06257404A JPH06257404A JP1124893A JP1124893A JPH06257404A JP H06257404 A JPH06257404 A JP H06257404A JP 1124893 A JP1124893 A JP 1124893A JP 1124893 A JP1124893 A JP 1124893A JP H06257404 A JPH06257404 A JP H06257404A
- Authority
- JP
- Japan
- Prior art keywords
- yarns
- yarn
- shaft
- blade
- woven
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Granted
Links
- 238000004519 manufacturing process Methods 0.000 title claims description 16
- 238000009941 weaving Methods 0.000 claims abstract description 12
- 239000000835 fiber Substances 0.000 claims description 53
- 238000005304 joining Methods 0.000 claims description 28
- 238000000034 method Methods 0.000 claims description 8
- 101150052610 Yars1 gene Proteins 0.000 abstract 1
- 239000011295 pitch Substances 0.000 abstract 1
- 239000002131 composite material Substances 0.000 description 8
- OKTJSMMVPCPJKN-UHFFFAOYSA-N Carbon Chemical compound [C] OKTJSMMVPCPJKN-UHFFFAOYSA-N 0.000 description 4
- 229910052799 carbon Inorganic materials 0.000 description 4
- RTAQQCXQSZGOHL-UHFFFAOYSA-N Titanium Chemical compound [Ti] RTAQQCXQSZGOHL-UHFFFAOYSA-N 0.000 description 3
- 239000000919 ceramic Substances 0.000 description 3
- 238000005520 cutting process Methods 0.000 description 3
- 239000011159 matrix material Substances 0.000 description 3
- 239000010936 titanium Substances 0.000 description 3
- 229910052719 titanium Inorganic materials 0.000 description 3
- 239000007769 metal material Substances 0.000 description 2
- 229920005989 resin Polymers 0.000 description 2
- 239000011347 resin Substances 0.000 description 2
- 125000006850 spacer group Chemical group 0.000 description 2
- 229920000049 Carbon (fiber) Polymers 0.000 description 1
- 230000001133 acceleration Effects 0.000 description 1
- 229920006231 aramid fiber Polymers 0.000 description 1
- 230000015572 biosynthetic process Effects 0.000 description 1
- 239000004917 carbon fiber Substances 0.000 description 1
- 239000000470 constituent Substances 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 239000003822 epoxy resin Substances 0.000 description 1
- 239000011888 foil Substances 0.000 description 1
- 239000003365 glass fiber Substances 0.000 description 1
- 238000003475 lamination Methods 0.000 description 1
- 239000002184 metal Substances 0.000 description 1
- 229910052751 metal Inorganic materials 0.000 description 1
- VNWKTOKETHGBQD-UHFFFAOYSA-N methane Chemical compound C VNWKTOKETHGBQD-UHFFFAOYSA-N 0.000 description 1
- 229920000647 polyepoxide Polymers 0.000 description 1
- HBMJWWWQQXIZIP-UHFFFAOYSA-N silicon carbide Chemical compound [Si+]#[C-] HBMJWWWQQXIZIP-UHFFFAOYSA-N 0.000 description 1
- 229910010271 silicon carbide Inorganic materials 0.000 description 1
Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05B—INDEXING SCHEME RELATING TO WIND, SPRING, WEIGHT, INERTIA OR LIKE MOTORS, TO MACHINES OR ENGINES FOR LIQUIDS COVERED BY SUBCLASSES F03B, F03D AND F03G
- F05B2250/00—Geometry
- F05B2250/20—Geometry three-dimensional
Landscapes
- Turbine Rotor Nozzle Sealing (AREA)
- Nonwoven Fabrics (AREA)
Abstract
Description
【０００１】[0001]
【産業上の利用分野】本発明は、航空機タービンその他
の軸流圧縮機等における翼型構造体を、三次元織物繊維
構造体で補強したＦＲＰ、ＦＲＭ、カーボン／カーボン
またはセラミック／セラミック複合材料によって構成す
るための翼／軸筒一体型三次元繊維構造体と、その製造
方法に関するものである。BACKGROUND OF THE INVENTION 1. Field of the Invention The present invention uses an FRP, FRM, carbon / carbon or ceramic / ceramic composite material in which an airfoil structure in an aircraft turbine or other axial compressor is reinforced with a three-dimensional woven fiber structure. The present invention relates to a wing / shaft tube-integrated three-dimensional fiber structure for constituting and a manufacturing method thereof.
【０００２】[0002]
【従来の技術】従来、航空機タービン等の翼型構造体
は、チタン製あるいはその他の金属材料によって製作さ
れていたが、重量が大きくなることや、加工工数が大と
なり、コスト高となる等の問題があった。2. Description of the Related Art Conventionally, an airfoil structure for an aircraft turbine or the like has been made of titanium or other metal material, but it is heavy and requires a large number of processing steps, resulting in high cost. There was a problem.
【０００３】そこで、航空機タービン等の翼型構造体
を、チタン製あるいはその他の金属材料から炭素／エポ
キシ樹脂などの複合材料に置き換え、軽量化しようとす
る試みは、いくらか提案されてきている。例えば、特開
昭６３−２９５７４１号公報、米国特許第３，６３２，
４６０号明細書、特開平２−１４４２９７号公報等が提
案されている。Therefore, some attempts have been proposed to replace the airfoil structure of an aircraft turbine or the like with a composite material such as carbon / epoxy resin from titanium or other metal materials to reduce the weight. For example, JP-A-63-295741 and US Pat. No. 3,632,
No. 460, JP-A No. 2-144297, etc. are proposed.
【０００４】[0004]
【発明が解決しようとする課題】特開昭６３−２９５７
４１号公報の提案は、複合材料によって円筒状構造体を
製造することができるが、翼部分を一体に賦形すること
ができない。従って、この提案の場合では、翼部分と軸
筒部分とを、後に何等かの手段で接合しなければならな
い。Problems to be Solved by the Invention JP-A-63-2957
The proposal of Japanese Patent No. 41 can manufacture a cylindrical structure with a composite material, but cannot form the blade portion integrally. Therefore, in the case of this proposal, the blade portion and the barrel portion must be joined later by some means.
【０００５】また、米国特許第３，６３２，４６０号明
細書の提案は、翼部分と軸筒部分とを複合材料によって
一体に賦形可能としているが、繊維の配向に関しては一
次元構造が提案されているだけであって、繊維相互の絡
み合いがない。Further, the proposal of US Pat. No. 3,632,460 makes it possible to integrally form the blade portion and the shaft tube portion by a composite material, but a one-dimensional structure is proposed for the orientation of the fibers. However, the fibers are not entangled with each other.
【０００６】特開平２−１４４２９７号公報の提案は、
翼部分と軸筒部分とを複合材料によって相互に別体とし
て製作し、接合ピンによって組み立てるようにしたもの
であって、翼部分と軸筒部分とを複合材料によって一体
に賦形可能としたものではない。The proposal of Japanese Patent Laid-Open No. 144297/1990 is as follows.
A wing part and a shaft part are manufactured separately from each other by a composite material, and are assembled by a joining pin, and the wing part and the shaft part can be integrally molded by the composite material. is not.
【０００７】上記特開昭６３−２９５７４１号公報の提
案及び特開平２−１４４２９７号公報の提案は、翼部分
と軸筒部分とを後で接合することになるため、これらの
接合部の強度向上が難しく、仮に強度が満足できたとし
ても、重量的に大きくなり、所定回転数までの立ち上が
り性能（加速性能）及び変速応答性も悪くなる等の問題
がある。According to the proposals of Japanese Patent Laid-Open No. 63-295741 and Japanese Patent Laid-Open No. 144297/1990, the blade portion and the barrel portion are joined later, so that the strength of these joined portions is improved. However, even if the strength can be satisfied, there is a problem that the weight becomes large and the start-up performance (acceleration performance) up to a predetermined number of rotations and the shift response are deteriorated.
【０００８】また、上記米国特許第３，６３２，４６０
号明細書の提案は、繊維の配向が一次元構造であり、各
部における繊維相互の絡み合いがないため、翼部に作用
する推力、遠心力、捩れ力などの各方向の外力、衝撃や
振動に対する強度の向上が図り難い。The above-mentioned US Pat. No. 3,632,460
According to the proposal in the specification, since the fiber orientation is a one-dimensional structure and there is no entanglement between the fibers in each part, external force in each direction such as thrust, centrifugal force, twisting force, etc. acting on the blade part, against impact or vibration It is difficult to improve strength.
【０００９】なお、従来、複合材料製の三次元繊維構造
体から航空機タービン等の翼型構造体を製作することも
提案されているが、この提案は、ブロック状の三次元繊
維構造体を先ず製作しておき、これを切削加工して翼型
構造体を製作するものであるため、複雑な形状の翼型構
造体の場合、切削加工自体が困難であったり、仮に、切
削加工ができたとしても、繊維の切断が随所で発生して
おり、衝撃や振動等の外力に対して、三次元繊維構造体
としての強度を十分に発揮させられない等の問題があっ
た。Although it has been conventionally proposed to manufacture an airfoil structure, such as an aircraft turbine, from a three-dimensional fiber structure made of a composite material, this proposal first describes a block-shaped three-dimensional fiber structure. Since the wing-shaped structure is manufactured by cutting it beforehand, the wing-shaped structure having a complicated shape is difficult to cut, or even cut. In this case, however, the fibers are cut everywhere, and there is a problem that the strength of the three-dimensional fiber structure cannot be sufficiently exerted against external force such as impact or vibration.
【００１０】本発明は、翼部に糸条の切断端を生じさせ
ず、翼部と軸筒部とを一体で賦形することにより、その
接合部の強度を向上させた翼／軸筒一体型三次元繊維構
造体と、その製造方法を提供することを目的としてい
る。According to the present invention, a blade / shaft cylinder having improved strength at the joint portion is formed by integrally forming the blade portion and the shaft cylinder portion without forming a cut end of a yarn on the blade portion. It is an object of the present invention to provide a body type three-dimensional fiber structure and a manufacturing method thereof.
【００１１】[0011]
【課題を解決するための手段】上記目的を達成するた
め、本発明の翼／軸筒一体型三次元繊維構造体は、少な
くとも軸筒部又は翼部のいずれか又は両方が三次元方向
に配向された糸条で織成され、翼部の糸条の一部又は全
部が軸筒部と連続して織成されており、翼部に切断端が
ない連続糸により賦形されていることを特徴としてい
る。In order to achieve the above object, the blade / shaft tube-integrated three-dimensional fiber structure of the present invention has at least one or both of the shaft tube section and the blade section oriented in a three-dimensional direction. The part or all of the thread of the wing part is continuously woven with the shaft tube part, and it is shaped by continuous thread with no cut end on the wing part. It has a feature.
【００１２】また、本発明の翼／軸筒一体型三次元繊維
構造体は、上記翼部の面内における糸条の配列方向が二
軸以上であることを特徴としている。Further, the blade / shaft tube-integrated three-dimensional fiber structure of the present invention is characterized in that the yarns are arranged in two or more axes in the plane of the blade portion.
【００１３】そしてまた、本発明の翼／軸筒一体型三次
元繊維構造体は、軸筒部又は翼部のいずれか又は両方に
配向されている糸条には、Ｘ方向の糸条及びＹ方向の糸
条の配列面内に、両方向と交差して配置された斜向糸条
を包含していることを特徴としている。Further, in the wing / shaft cylinder integrated three-dimensional fiber structure of the present invention, the yarns oriented in either or both of the shaft cylinder portion and the wing portion are the yarns in the X direction and the Y direction. It is characterized in that obliquely oriented yarns arranged so as to intersect with both directions are included in the yarn arranging plane of the directions.
【００１４】さらに、本発明の翼／軸筒一体型三次元繊
維構造体の製造方法は、軸筒部の織成部を軸筒部を展開
した状態として形成し、かつ、翼部の織成部を軸筒部の
一側に所定のピッチ及び角度で一連に形成し、これら軸
筒部織成部及び翼部織成部のＺ方向に沿って複数本の糸
条案内管を所定ピッチで平行に配列させ、その間をＸ方
向の糸条及びＹ方向の糸条或いは３軸以上の方向の糸条
を連続状態で積層配置して上記両織成部内を充足させ、
その後、Ｚ方向の糸条を上記両織成部内に糸条案内管と
置換配置して充足させ、最後に、軸筒部の展開両端部を
糸条で接合して環状の軸筒部を形成させたことを特徴と
している。Further, according to the method of manufacturing a three-dimensional wing / shaft cylinder integrated type three-dimensional fiber structure of the present invention, the weave portion of the shaft cylinder portion is formed in a state where the shaft cylinder portion is expanded, and the weave portion is woven. Portions are formed in series on one side of the shaft tubular portion at a predetermined pitch and angle, and a plurality of yarn guide tubes are provided at a predetermined pitch along the Z direction of the shaft tubular portion woven portion and the blade portion woven portion. The yarns in the X direction and the yarns in the Y direction or the yarns in the directions of three or more axes are laminated and arranged in a continuous state between them to fill the inside of the woven parts.
After that, the yarns in the Z direction are replaced and arranged with the yarn guide tubes in both of the woven portions so as to be satisfied, and finally, both developed end portions of the shaft tubular portion are joined with the yarns to form an annular shaft tubular portion. It is characterized by having done.
【００１５】また、本発明の翼／軸筒一体型三次元繊維
構造体の製造方法は、Ｘ方向の糸条及びＹ方向の糸条の
配列面内に、両方向と交差する斜向糸条を配置して織成
したことを特徴としている。Further, in the method for manufacturing a three-dimensional wing / shaft cylinder integrated type three-dimensional fiber structure of the present invention, oblique yarns intersecting both directions are arranged in the arrangement plane of the yarns in the X direction and the Y direction. It is characterized by being placed and woven.
【００１６】さらに、本発明の翼／軸筒一体型三次元繊
維構造体の製造方法は、軸筒部の展開両端部の織成部内
に、複数本の接合糸条用案内管を配置し、一方の接合糸
条用案内管の一端を小径端とし、軸筒部の接合時に、軸
筒部の展開両端部の接合糸条用案内管同士を上記小径端
で接合させて接合用糸条と置換配置させるようになした
ことを特徴としている。Further, according to the method of manufacturing the blade / shaft tube integrated three-dimensional fiber structure of the present invention, a plurality of joining yarn guide tubes are arranged in the weaving portions at both ends of the development of the shaft tube portion, One end of one of the joining yarn guide tubes is a small diameter end, and when joining the shaft tubular portion, the joining yarn guide tubes at both ends of the development of the shaft tubular portion are joined at the above small diameter end to form a joining yarn. It is characterized in that it is arranged to be replaced.
【００１７】[0017]
【作用】本発明の翼／軸筒一体型三次元繊維構造体は、
繊維が切断されておらず、配向された糸条によって、予
定通りの強度が発揮される。しかも、翼部の糸条が軸筒
部の糸条と連続しているため、翼部と軸筒部との接合部
における強度が向上する。The three-dimensional fiber structure integrated with the blade / shaft cylinder of the present invention is
The fibers are not cut and the oriented yarns provide the expected strength. Moreover, since the yarn of the blade portion is continuous with the yarn of the shaft tubular portion, the strength at the joint between the blade portion and the shaft tubular portion is improved.
【００１８】また、本発明の翼／軸筒一体型三次元繊維
構造体の製造方法は、軸筒部を展開状態で織成すると共
に展開状態の軸筒部の両端を糸条で接合して環状とする
ことにより、翼部に作用する推力、遠心力、捩れ力など
の各方向の外力に対する強度を得るために必要なＸ方向
の糸条及びＹ方向の糸条の配列面内に、両方向と交差す
る斜向糸条を配置した複雑な形状で糸条切断端のない翼
部を軸筒部と一体に織成することを可能ならしめた。さ
らに、軸筒部の展開両端部の織成部内に、複数本の接合
糸条用案内管を配置し、一方の接合糸条用案内管の一端
を小径端とし、軸筒部の接合時に、軸筒部の展開両端部
の接合糸条用案内管同士を上記小径端で接合させて接合
用糸条と置換配置させるようになしたことによって、軸
筒部の接合が容易となる。Further, in the method for manufacturing the blade / shaft tube integrated three-dimensional fiber structure of the present invention, the shaft tube portion is woven in the expanded state and both ends of the shaft tube portion in the expanded state are joined by the yarns. By making it annular, both directions can be obtained in the planes in which the X-direction yarns and the Y-direction yarns are arranged in order to obtain strength against external forces in each direction, such as thrust, centrifugal force, and twisting force acting on the blade. It is possible to weave a wing part without a yarn cutting end in a complicated shape with diagonal yarns intersecting with the shaft cylinder part. Furthermore, a plurality of joining yarn guide tubes are arranged in the woven portions at both ends of the development of the shaft tubular portion, one end of one joining yarn guide tube is made a small diameter end, and when joining the shaft tubular portion, By joining the joining yarn guide tubes at both ends of the development of the shaft tubular portion at the small-diameter ends so as to replace the yarn for joining, the joining of the shaft tubular portion becomes easy.
【００１９】[0019]
【実施例】図１の（Ａ）（Ｂ）は、本発明の実施例の翼
部の繊維配向を示し、（Ｃ）は、軸筒部の繊維配向を示
し、（Ｄ）は、本発明の翼／軸筒一体型三次元繊維構造
体の展開状態の一例を示す概略斜視図、（Ｅ）は、
（Ｄ）に示した本発明の翼／軸筒一体型三次元繊維構造
体の最終形状の概略斜視図を示している。これらの図に
おいて、（１）はＸ方向の糸条、（２）はＹ方向の糸
条、（３）はＶ方向の糸条、（４）はＷ方向の糸条、
（５）は糸条案内管を示している。Ｖ方向の糸条（３）
及びＷ方向の糸条（４）は、Ｘ方向の糸条（１）及びＹ
方向の糸条（２）の配列面内に、両方向と交差して配置
される斜向糸条であって、図１の（Ｂ）では両方向と４
５°の角度の場合を例示しているが、これに制約され
ず、他の交差角度としてもよい。Examples (A) and (B) of FIG. 1 show the fiber orientation of the blade portion of the embodiment of the present invention, (C) shows the fiber orientation of the shaft cylinder portion, and (D) shows the present invention. (E) is a schematic perspective view showing an example of a developed state of the blade / shaft tube-integrated three-dimensional fiber structure of FIG.
FIG. 6D is a schematic perspective view of the final shape of the blade / shaft tube-integrated three-dimensional fiber structure of the present invention shown in FIG. In these figures, (1) is a yarn in the X direction, (2) is a yarn in the Y direction, (3) is a yarn in the V direction, (4) is a yarn in the W direction,
(5) shows a yarn guide tube. Threads in V direction (3)
And the W-direction yarn (4) is the X-direction yarn (1) and the Y-direction yarn (4).
The diagonal yarns are arranged in the plane of arrangement of the yarns (2) in the two directions so as to intersect the two directions. In FIG.
Although the case of an angle of 5 ° is illustrated, the present invention is not limited to this and other intersecting angles may be used.
【００２０】本発明の翼／軸筒一体型三次元繊維構造体
（10）は、図１の（Ｅ）に示すように、軸筒部（６）
と、この軸筒部（６）の外周囲に所定のピッチ及び角度
で一体に形成された翼部（７）とからなる。このような
本発明の翼／軸筒一体型三次元繊維構造体（10）は、図
１の（Ｄ）に示すように、軸筒部（６）を展開し、この
軸筒部（６）に翼部（７）を一体に形成させた状態で織
成し、織成後、この軸筒部（６）の両端部（6a）（6b）
を接合糸で接合して環状とする。この織成に当たって、
少なくとも軸筒部（６）又は翼部（７）のいずれか又は
両方が三次元方向に配向された糸条で織成され、翼部
（７）の糸条の一部又は全部が軸筒部（６）と連続して
織成されている。即ち、軸筒部（６）は、図１の（Ｃ）
に例示しているように、所定ピッチで配置された糸条案
内管（５）にＸ方向の糸条（１）及びＹ方向の糸条
（２）を連続状態で積層配置し、Ｚ方向の糸条は図示し
ていないが、糸条案内管（５）と置換して配置される。
必要に応じ、斜向配置も行なわれる。また、翼部（７）
は、図１の（Ａ）（Ｂ）に示すように、所定ピッチで配
置された糸条案内管（５）にＸ方向の糸条（１）、Ｙ方
向の糸条（２）、Ｖ方向の糸条（３）及びＷ方向の糸条
（４）を所定の順番及び積層数で夫々連続した状態で積
層配置し、かつ、Ｚ方向の糸条は図示していないが、糸
条案内管（５）と置換して配置される。The blade / shaft tube integrated three-dimensional fiber structure (10) of the present invention has a shaft tube portion (6) as shown in FIG. 1 (E).
And a blade portion (7) integrally formed on the outer periphery of the shaft tubular portion (6) at a predetermined pitch and angle. Such a blade / shaft tube integrated type three-dimensional fiber structure (10) of the present invention, as shown in FIG. 1 (D), develops the shaft tube section (6), and the shaft tube section (6) is expanded. Woven with the blade (7) integrally formed on the shaft, and after weaving, both ends (6a) (6b) of the shaft cylinder (6)
Are joined with a joining thread to form a ring. In this weaving,
At least one or both of the shaft cylinder part (6) and the wing part (7) are woven by yarns oriented in a three-dimensional direction, and a part or all of the yarns of the wing part (7) is the shaft cylinder part. It is woven continuously with (6). That is, the shaft cylinder part (6) is shown in (C) of FIG.
As illustrated in Fig. 2, the yarn guide tubes (5) arranged at a predetermined pitch are continuously laminated with the yarns (1) in the X direction and the yarns (2) in the Y direction and arranged in the Z direction. Although not shown, the yarn is arranged in place of the yarn guide tube (5).
Oblique placement is also performed if necessary. Also, the wings (7)
As shown in FIGS. 1 (A) and 1 (B), a yarn guide tube (5) arranged at a predetermined pitch has a yarn (1) in the X direction, a yarn (2) in the Y direction, and a V direction. The yarns (3) and the yarns (4) in the W direction are laminated and arranged in a predetermined order and the number of laminated layers are continuous, and the yarns in the Z direction are not shown, but the yarn guide tube (5) is replaced and arranged.
【００２１】図１の（Ａ）（Ｂ）（Ｃ）では、翼部
（７）の糸条の一部、即ち、Ｘ方向の糸条（１）及びＹ
方向の糸条（２）を軸筒部（６）と連続して織成させた
場合を例示しているが、Ｖ方向の糸条（３）及びＷ方向
の糸条（４）についても連続して織成させてもよい。ま
た、斜向糸条は、Ｖ方向の糸条（３）及びＷ方向の糸条
（４）に加えて更に別方向の糸条を組合せ配置してもよ
い。In FIGS. 1A, 1B and 1C, a part of the yarns of the wing portion (7), that is, the yarns (1) and Y in the X direction.
Although the case where the yarn (2) in the direction is continuously woven with the shaft tube portion (6) is illustrated, the yarn (3) in the V direction and the yarn (4) in the W direction are also continuous. It may be woven. Further, as the obliquely oriented yarns, in addition to the yarns (3) in the V direction and the yarns (4) in the W direction, yarns in different directions may be arranged in combination.
【００２２】上記翼／軸筒一体型三次元繊維構造体（1
0）の製造方法は、図２の（Ａ）（Ｂ）にも示すよう
に、軸筒部（６）を展開状態とし、その一側に翼部
（７）を所定のピッチ及び角度で一体に織成し、織成
後、展開状態の軸筒部（６）の両端部（6a）（6b）を接
合して環状とする。この場合、展開状態の軸筒部（６）
の両端部（6a）（6b）は、相互に係合段部（6c）（6d）
を形成しておき、これらを係合させて、接合部の厚さと
強度の極端な変化を防止させている。翼部（７）の断面
形状は、図２の（Ｃ）（Ｄ）に示すように三日月形状や
航空機翼形状（Aero-foil）等とすることができる。The above-mentioned wing / shaft cylinder integrated three-dimensional fiber structure (1
As shown in FIGS. 2 (A) and 2 (B), the manufacturing method of (0) is such that the shaft cylinder portion (6) is in a developed state, and the blade portion (7) is integrated on one side thereof at a predetermined pitch and angle. After weaving, both ends (6a) and (6b) of the shaft cylinder (6) in the unfolded state are joined to form a ring. In this case, the shaft cylinder portion (6) in the expanded state
Both ends (6a) and (6b) of the two are engaged with each other at the steps (6c) and (6d).
Are formed, and these are engaged with each other to prevent an extreme change in the thickness and strength of the joint portion. The cross-sectional shape of the wing portion (7) may be a crescent shape, an aircraft wing shape (Aero-foil), or the like, as shown in FIGS.
【００２３】図３の（Ａ）（Ｂ）は、上記翼／軸筒一体
型三次元繊維構造体（10）の製造方法の具体例を示す側
面図と正面図であって、その織成に当たっては、軸筒部
（６）の織成部（８）を軸筒部（６）を展開した状態と
して形成し、かつ、翼部（７）の織成部（９）を軸筒部
（６）の一側に所定のピッチ及び角度で一連に形成し、
これら両織成部（８）（９）にベースプレート（11）を
介して糸条案内管（５）をＺ方向に沿って最終成形物形
状に要求される特性に応じたピッチで植立させ、翼部
（７）の織成部（９）の間の糸条案内管（５）の間に予
め決められた形状のスペーサ（12）を設置しつつ両織成
部（８）（９）にＸ方向の糸条（１）、Ｙ方向の糸条
（２）、Ｖ方向の糸条（３）及びＷ方向の糸条（４）を
所定の順番及び積層数で夫々連続した状態で積層配置し
て両織成部（８）（９）内を充足させる。3A and 3B are a side view and a front view showing a specific example of a method of manufacturing the blade / shaft tube-integrated three-dimensional fiber structure (10). Forms the woven portion (8) of the shaft tubular portion (6) in a state in which the shaft tubular portion (6) is expanded, and sets the woven portion (9) of the blade portion (7) to the shaft tubular portion (6). ) One side is formed in series with a predetermined pitch and angle,
The yarn guide tubes (5) are erected in these two woven parts (8) and (9) through the base plate (11) at a pitch according to the characteristics required for the final molded product shape, The spacers (12) having a predetermined shape are installed between the yarn guide tubes (5) between the weaving parts (9) of the wing parts (7), and both spacers (8) and (9) are installed. The X-direction yarn (1), the Y-direction yarn (2), the V-direction yarn (3), and the W-direction yarn (4) are laminated in a predetermined order and in a laminated state in a continuous state. Then, the both weaving parts (8) and (9) are filled.
【００２４】糸条案内管（５）に対する各方向の糸条の
配置は、図１の（Ａ）（Ｂ）（Ｃ）で例示した要領で配
置される。The arrangement of the yarns in each direction with respect to the yarn guide tube (5) is performed in the manner illustrated in FIGS. 1A, 1B and 1C.
【００２５】積層開始の一部と積層終了の一部、即ち、
展開状態の軸筒部（６）の両端部（6a）（6b）には、係
合段部（6c）（6d）を形成させるために糸条の積層配置
を減少させ、また、この減少部分に接合糸条用案内管
（13）（14）を挿入しながら糸条を積層する。Part of the start of stacking and part of the end of stacking, that is,
In order to form engaging step portions (6c) and (6d) at both end portions (6a) and (6b) of the shaft cylindrical portion (6) in the unfolded state, the stacking arrangement of the yarns is reduced, and this reduced portion is also reduced. The yarns are laminated while inserting the guide pipes (13) (14) for the joined yarns.
【００２６】図３では、糸条案内管（５）を垂直方向に
配置した場合を例示しているが、翼部（７）の形成形状
（湾曲面形状等）に適合させてベースプレート（11）に
所定の傾斜角（例えば、１５°〜３０°等）で傾斜させ
て植立させてもよい。Although FIG. 3 illustrates the case where the yarn guide tube (5) is arranged in the vertical direction, it is adapted to the formation shape (curved surface shape, etc.) of the wing portion (7) and the base plate (11). Alternatively, the planting may be performed by inclining at a predetermined inclination angle (for example, 15 ° to 30 °).
【００２７】以上のようにして、Ｘ方向の糸条（１）、
Ｙ方向の糸条（２）、Ｖ方向の糸条（３）及びＷ方向の
糸条（４）の積層を終了すると、Ｚ方向の糸条（図示省
略）を糸条案内管（５）と置換配置する。この置換配置
は、例えば、糸条案内管（５）を抜き取りつつその後へ
Ｚ方向の糸条を挿入していくことによって行なわれる。
このＺ方向の糸条は、展開状態の軸筒部（６）の両端部
又は一端部で連続させて配置するのが好ましい。また、
翼部（７）ではＺ方向の糸条を連続させ、切断端を生じ
させないように配置させる。As described above, the yarn (1) in the X direction,
When the lamination of the Y-direction yarn (2), the V-direction yarn (3) and the W-direction yarn (4) is completed, the Z-direction yarn (not shown) is used as the yarn guide tube (5). Replace it. This replacement arrangement is performed, for example, by pulling out the yarn guide tube (5) and inserting a yarn in the Z direction thereafter.
It is preferable that the yarns in the Z direction are arranged continuously at both ends or one end of the shaft cylinder portion (6) in the expanded state. Also,
In the wing portion (7), the yarns in the Z direction are continuous and arranged so as not to cause a cut end.
【００２８】このようにして、Ｚ方向の糸条の配置を終
了すると、軸筒部（６）を湾曲させて、両端部（6a）
（6b）の係合段部（6c）（6d）を係合させる。この場
合、接合糸条用案内管（13）（14）の一方の端部を図３
の（Ｃ）に示すように、小径端（14a）として、係合段
部（6c）（6d）の係合時、他方の接合糸条用案内管（1
3）の端部に嵌合させ、この状態で両方の接合糸条用案
内管（13）（14）を抜き取りつつ接合糸条（図示省略）
を挿入して翼部（７）が一体となった環状の軸筒部
（６）を形成する。When the arrangement of the yarns in the Z direction is completed in this way, the shaft tube portion (6) is curved and both end portions (6a) are bent.
The engagement step portions (6c) and (6d) of (6b) are engaged. In this case, connect one end of the joining yarn guide tube (13) (14) to
As shown in (C) of FIG. 2, when the engagement step portions (6c) and (6d) are engaged as the small diameter end (14a), the other joining yarn guide tube (1
Fitting to the end of 3), and in this state, pull out both guide yarn guide tubes (13) and (14) while joining yarn (not shown)
Is inserted to form an annular shaft cylinder portion (6) in which the blade portions (7) are integrated.
【００２９】上記のようにして形成された翼／軸筒一体
型三次元繊維構造体（10）は、この後、樹脂マトリック
スまたは高温特性に優れる炭素、炭化珪素等の無機質マ
トリックスが公知の方法で付与され、複合材料製の翼体
が構成される。なお、本発明で使用される糸条の構成繊
維は、炭素繊維、ガラス繊維、セラミックス繊維、アラ
ミド繊維等耐熱性を有する各種の繊維が使用可能であ
り、繊維の形態は、連続繊維状、スパン糸状等いずれで
もよい。上記した実施例は、糸条案内管（５）を、軸筒
部（６）の展開方向に沿って配列した場合を例示してい
るが、これに制約されない。The blade / shaft tube-integrated three-dimensional fiber structure (10) formed as described above is then processed by a known method using a resin matrix or an inorganic matrix such as carbon or silicon carbide having excellent high temperature characteristics. The composite airfoil is provided. The constituent fibers of the yarn used in the present invention can be various fibers having heat resistance such as carbon fiber, glass fiber, ceramic fiber, and aramid fiber, and the fiber form is continuous fiber or spun. It may be in a thread form or the like. Although the above-mentioned embodiment illustrates the case where the yarn guide tubes (5) are arranged along the developing direction of the shaft tubular portion (6), the present invention is not limited to this.
【００３０】[0030]
【発明の効果】本発明の翼／軸筒一体型三次元繊維構造
体は、繊維が切断されておらず、配向された糸条によっ
て、予定通りの強度が発揮される。しかも、翼部の糸条
が軸筒部の糸条と連続しているため、翼部と軸筒部との
接合部における強度が向上する。EFFECTS OF THE INVENTION In the blade / shaft tube integrated three-dimensional fiber structure of the present invention, the fibers are not cut, and the oriented yarn exhibits the expected strength. Moreover, since the yarn of the blade portion is continuous with the yarn of the shaft tubular portion, the strength at the joint between the blade portion and the shaft tubular portion is improved.
【００３１】また、本発明の翼／軸筒一体型三次元繊維
構造体の製造方法は、軸筒部を展開状態で織成すると共
に展開状態の軸筒部の両端を糸条で接合して環状とする
ことにより、翼部に作用する推力、遠心力、捩れ力など
の各方向の外力に対する強度を得るために必要なＸ方向
の糸条及びＹ方向の糸条の配列面内に、両方向と交差す
る斜向糸条を配置した複雑な形状で糸条切断端のない翼
部を軸筒部と一体に織成することを可能ならしめた。さ
らに、軸筒部の展開両端部の織成部内に、複数本の接合
糸条用案内管を配置し、一方の接合糸条用案内管の一端
を小径端とし、軸筒部の接合時に、軸筒部の展開両端部
の接合糸条用案内管同士を上記小径端で接合させて接合
用糸条と置換配置させるようになしたことによって、軸
筒部の接合が容易となる。Further, in the method of manufacturing the blade / shaft tube integrated three-dimensional fiber structure of the present invention, the shaft tube portion is woven in the expanded state, and both ends of the shaft tube portion in the expanded state are joined by the yarns. By making it annular, both directions can be obtained in the planes in which the X-direction yarns and the Y-direction yarns are arranged in order to obtain strength against external forces in each direction, such as thrust, centrifugal force, and twisting force acting on the blade. It is possible to weave a wing part without a yarn cutting end in a complicated shape with diagonal yarns intersecting with the shaft cylinder part. Furthermore, a plurality of joining yarn guide tubes are arranged in the woven portions at both ends of the development of the shaft tubular portion, one end of one joining yarn guide tube is made a small diameter end, and when joining the shaft tubular portion, By joining the joining yarn guide tubes at both ends of the development of the shaft tubular portion at the small-diameter ends so as to replace the yarn for joining, the joining of the shaft tubular portion becomes easy.
【００３２】また、本発明の製造方法は、最終形状の翼
部及び軸筒部を連続糸で一体的に織成した三次元繊維構
造体を型の中でマトリックス樹脂と共に固化させること
によって製造するため、加工工数が少なく、低コストと
できる。Further, since the manufacturing method of the present invention is manufactured by solidifying the three-dimensional fiber structure in which the wing portion and the shaft cylinder portion of the final shape are integrally woven with the continuous yarn in the mold together with the matrix resin. The number of processing steps is small, and the cost can be reduced.
【００３３】しかも、翼部の軸筒部に対する傾斜角度も
種々のものが製作でき、従って簡単な湾曲翼形状から複
雑な湾曲翼形状まで容易に製作できる。Moreover, various inclination angles of the blade portion with respect to the shaft cylinder portion can be manufactured, and therefore, a simple curved blade shape to a complicated curved blade shape can be easily manufactured.
【００３４】さらに、本発明の翼／軸筒一体型三次元繊
維構造体は、従来のチタン製などの金属製と比べ、軽量
化され、所定回転数までの立ち上がりが速く、加速性能
及び変速応答性が向上する。また、比強度も大きく、回
転数の増大が可能となり、高出力が得られる。Further, the blade / shaft tube integrated three-dimensional fiber structure of the present invention is lighter in weight, quicker to start up to a predetermined number of revolutions, more accelerating performance and speed change response than those made of conventional metal such as titanium. The property is improved. Also, the specific strength is large, the number of rotations can be increased, and high output can be obtained.
【図１】（Ａ）（Ｂ）は、本発明の実施例の翼部の繊維
配向を示し、（Ｃ）は、軸筒部の繊維配向を示し、
（Ｄ）は、本発明の翼／軸筒一体型三次元繊維構造体の
展開状態の一例を示す概略斜視図、（Ｅ）は、（Ｄ）に
示した本発明の翼／軸筒一体型三次元繊維構造体の最終
形状の概略斜視図を示している。FIG. 1 (A) and (B) show the fiber orientation of a blade portion of an embodiment of the present invention, and (C) shows the fiber orientation of a shaft cylinder portion,
(D) is a schematic perspective view showing an example of a developed state of the blade / shaft tube integrated three-dimensional fiber structure of the present invention, and (E) is a blade / shaft tube integrated type of the present invention shown in (D). FIG. 3 shows a schematic perspective view of the final shape of the three-dimensional fiber structure.
【図２】（Ａ）は、本発明の翼／軸筒一体型三次元繊維
構造体の展開状態の他の一例を示す概略斜視図、（Ｂ）
は、（Ａ）に示した本発明の翼／軸筒一体型三次元繊維
構造体の最終形状の概略斜視図、（Ｃ）（Ｄ）は、翼部
の断面形状例を示す概略断面図である。FIG. 2 (A) is a schematic perspective view showing another example of the developed state of the blade / shaft tube integrated three-dimensional fiber structure of the present invention, (B).
Is a schematic perspective view of the final shape of the blade / shaft tube-integrated three-dimensional fiber structure of the present invention shown in (A), and (C) and (D) are schematic cross-sectional views showing an example of the cross-sectional shape of the blade portion. is there.
【図３】（Ａ）（Ｂ）は本発明の製造方法により積層さ
れた繊維構造体の側面図と正面図であり、（Ｃ）は接合
糸条用案内管の説明用斜視図である。3 (A) and 3 (B) are a side view and a front view of a fiber structure laminated by a manufacturing method of the present invention, and FIG. 3 (C) is a perspective view for explaining a joining yarn guide tube.
１ Ｘ方向の糸条 ２ Ｙ方向の糸条 ３ Ｖ方向の糸条 ４ Ｗ方向の糸条 ５ 糸条案内管 ６ 軸筒部 ７ 翼部 ８ 軸筒部の織成部 ９ 翼部の織成部 10 翼／軸筒一体型三次元繊維構造体 13 接合糸条用案内管 14 接合糸条用案内管 1 Y-direction yarn 2 Y-direction yarn 3 V-direction yarn 4 W-direction yarn 5 Yarn guide tube 6 Shaft cylinder part 7 Wing part 8 Shaft cylinder weaving part 9 Wing part weaving Part 10 Wing / shaft cylinder integrated three-dimensional fiber structure 13 Guide tube for joint yarn 14 Guide pipe for joint yarn
─────────────────────────────────────────────────────
─────────────────────────────────────────────────── ───
【手続補正書】[Procedure amendment]
【提出日】平成５年３月２日[Submission date] March 2, 1993
【手続補正１】[Procedure Amendment 1]
【補正対象書類名】明細書[Document name to be amended] Statement
【補正対象項目名】特許請求の範囲[Name of item to be amended] Claims
【補正方法】変更[Correction method] Change
【補正内容】[Correction content]
【特許請求の範囲】[Claims]
フロントページの続き (72)発明者 西山 茂 愛知県名古屋市港区大江町10番地 三菱重 工業株式会社名古屋航空機宇宙システム製 作所内 (72)発明者 広川 哲朗 滋賀県近江八幡市多賀町485−４ (72)発明者 石橋 正康 滋賀県八日市市建部北町297Front page continued (72) Inventor Shigeru Nishiyama 10 Oe-cho, Minato-ku, Nagoya, Aichi Mitsubishi Heavy Industries, Ltd.Nagoya Aerospace Systems Works (72) Inventor Tetsuro Hirokawa 485-4 Taga-cho, Omihachiman City, Shiga Prefecture (72) Inventor Masayasu Ishibashi 297 Takebe Kitamachi, Yokaichi City, Shiga Prefecture
Claims (6)
は両方が三次元方向に配向された糸条で織成され、翼部
の糸条の一部又は全部が軸筒部と連続して織成されてお
り、翼部に糸条の切断端がない連続糸により賦形されて
いることを特徴とする翼／軸筒一体型三次元繊維構造
体。1. At least one or both of the shaft tubular portion and the blade portion are woven by yarns oriented in a three-dimensional direction, and some or all of the yarns of the blade portion are continuous with the shaft tubular portion. A wing / shaft tube-integrated three-dimensional fiber structure, which is woven and shaped by a continuous yarn having no cut end of a yarn on the wing portion.
軸以上であることを特徴とする請求項１に記載の翼／軸
筒一体型三次元繊維構造体。2. The wing / shaft tube-integrated three-dimensional fiber structure according to claim 1, wherein the yarns are arranged in two or more axes in the plane of the wing portion.
向されている糸条には、Ｘ方向の糸条及びＹ方向の糸条
の配列面内に、両方向と交差して配置された斜向糸条を
包含していることを特徴とする請求項１または２に記載
の翼／軸筒一体型三次元繊維構造体。3. A yarn oriented to either or both of the axial tube portion and the wing portion is arranged in the arrangement plane of the yarn in the X direction and the yarn in the Y direction so as to intersect with both directions. The wing / shaft tube-integrated three-dimensional fiber structure according to claim 1 or 2, characterized in that the obliquely oriented yarn is included.
として形成し、かつ、翼部の織成部を軸筒部の一側に所
定のピッチ及び角度で一連に形成し、これら軸筒部織成
部及び翼部織成部のＺ方向に沿って複数本の糸条案内管
を所定ピッチで平行に配列させ、その間をＸ方向の糸条
及びＹ方向の糸条を連続状態で積層配置して上記両織成
部内を充足させ、その後、Ｚ方向の糸条を上記両織成部
内に糸条案内管と置換配置して充足させ、最後に、軸筒
部の展開両端部を糸条で接合して環状の軸筒部を形成さ
せたことを特徴とする翼／軸筒一体型三次元繊維構造体
の製造方法。4. The woven portion of the shaft tubular portion is formed with the shaft tubular portion in a developed state, and the woven portion of the blade portion is formed in series on one side of the shaft tubular portion at a predetermined pitch and angle. , A plurality of yarn guide tubes are arranged in parallel at a predetermined pitch along the Z direction of the axial tubular portion woven portion and the blade portion woven portion, and the X direction yarn yarn and the Y direction yarn yarn are arranged between them. The two weaving parts are filled by arranging them in a continuous state, and then the yarns in the Z direction are replaced with the yarn guide tubes in the both weaving parts to be filled, and finally, the shaft cylinder part is expanded. A method for manufacturing a blade / shaft tube integrated three-dimensional fiber structure, characterized in that both ends are joined with a thread to form an annular shaft tube section.
内に、両方向と交差する斜向糸条を配置して織成したこ
とを特徴とする請求項３に記載の翼／軸筒一体型三次元
繊維構造体の製造方法。5. The blade / shaft according to claim 3, wherein diagonally oriented yarns intersecting both directions are woven in the arrangement plane of the yarns in the X direction and the yarns in the Y direction. A method for manufacturing a cylinder-integrated three-dimensional fiber structure.
本の接合糸条用案内管を配置し、一方の接合糸条用案内
管の一端を小径端とし、軸筒部の接合時に、軸筒部の展
開両端部の接合糸条用案内管同士を上記小径端で接合さ
せて接合用糸条と置換配置させるようになしたことを特
徴とする請求項３または４に記載の翼／軸筒一体型三次
元繊維構造体の製造方法。6. A plurality of splicing yarn guide tubes are arranged in the woven parts at both ends of expansion of the shaft tubular portion, and one splicing yarn guide tube has one end as a small diameter end, 5. When joining, the joining yarn guide tubes at both ends of the development of the shaft tube portion are joined at the small-diameter end so as to be replaced with the joining yarn and arranged. Of the blade / shaft cylinder integrated three-dimensional fiber structure of the above.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| JP1124893A JP2984805B2 (en) | 1993-01-27 | 1993-01-27 | Method of manufacturing three-dimensional fiber structure integrated with blade / shaft cylinder |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| JP1124893A JP2984805B2 (en) | 1993-01-27 | 1993-01-27 | Method of manufacturing three-dimensional fiber structure integrated with blade / shaft cylinder |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| JPH06257404A true JPH06257404A (en) | 1994-09-13 |
| JP2984805B2 JP2984805B2 (en) | 1999-11-29 |
Family
ID=11772643
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| JP1124893A Expired - Fee Related JP2984805B2 (en) | 1993-01-27 | 1993-01-27 | Method of manufacturing three-dimensional fiber structure integrated with blade / shaft cylinder |
Country Status (1)
| Country | Link |
|---|---|
| JP (1) | JP2984805B2 (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US8038408B2 (en) | 2004-11-05 | 2011-10-18 | Rolls-Royce Plc | Composite aerofoil |
-
1993
- 1993-01-27 JP JP1124893A patent/JP2984805B2/en not_active Expired - Fee Related
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US8038408B2 (en) | 2004-11-05 | 2011-10-18 | Rolls-Royce Plc | Composite aerofoil |
| US8333565B2 (en) | 2004-11-05 | 2012-12-18 | Rolls-Royce Plc | Composite aerofoil |
Also Published As
| Publication number | Publication date |
|---|---|
| JP2984805B2 (en) | 1999-11-29 |
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