JP2003148105A - Ceramics based composite member with band part and its manufacturing method - Google Patents
Ceramics based composite member with band part and its manufacturing methodInfo
- Publication number
- JP2003148105A JP2003148105A JP2001345712A JP2001345712A JP2003148105A JP 2003148105 A JP2003148105 A JP 2003148105A JP 2001345712 A JP2001345712 A JP 2001345712A JP 2001345712 A JP2001345712 A JP 2001345712A JP 2003148105 A JP2003148105 A JP 2003148105A
- Authority
- JP
- Japan
- Prior art keywords
- band
- blade
- wing
- composite member
- plain weave
- 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
Landscapes
- Turbine Rotor Nozzle Sealing (AREA)
Abstract
Description
【０００１】[0001]
【発明の属する技術分野】本発明は、フランジ部を有す
るセラミックス基複合部材とその製造方法に関する。BACKGROUND OF THE INVENTION 1. Field of the Invention The present invention relates to a ceramic-based composite member having a flange portion and a method for manufacturing the same.
【０００２】[0002]
【従来の技術】セラミックスは耐熱性が高いが脆い欠点
があるため、これをセラミックス繊維で強化したセラミ
ックス基複合部材（Ｃｅｒａｍｉｃ Ｍａｔｒｉｘ Ｃ
ｏｍｐｏｓｉｔｅ：以下、ＣＭＣと略称する）が開発さ
れている。すなわち、セラミックス基複合部材（ＣＭ
Ｃ）はセラミックス繊維とセラミックスマトリックスと
からなる。なお、一般にＣＭＣはその素材により、セラ
ミックス繊維／セラミックスマトリックス（例えば、両
方がＳｉＣからなる場合、ＳｉＣ／ＳｉＣ）と表示され
る。なお、以下、セラミックス基複合部材（ＣＭＣ）に
ついて詳述するが、本発明は、これに限定されず、炭素
系複合材（Ｃ／Ｃ）、Ｃ／ＳｉＣ、ＳｉＣ／Ｃ等にも同
様に適用することができる。2. Description of the Related Art Ceramics have high heat resistance but are fragile. Therefore, a ceramic matrix composite member (Ceramic Matrix C) reinforced with ceramic fibers is used.
omposite: hereinafter abbreviated as CMC) has been developed. That is, a ceramic matrix composite member (CM
C) consists of ceramic fibers and a ceramic matrix. Note that CMC is generally expressed as ceramic fiber / ceramic matrix (for example, SiC / SiC when both are made of SiC) depending on its material. The ceramic-based composite member (CMC) will be described in detail below, but the present invention is not limited to this and is similarly applied to carbon-based composite materials (C / C), C / SiC, SiC / C, and the like. can do.
【０００３】ＣＭＣは、軽量で耐熱性に優れるため、ジ
ェットエンジン部品（例えば、タービン翼、燃焼器、ア
フターバーナ部品等）へ適用することによりエンジンの
重量削減および燃料消費率の低減が期待される有望な材
料である。Since CMC is lightweight and has excellent heat resistance, it is expected to reduce the weight of the engine and the fuel consumption rate by applying it to jet engine parts (for example, turbine blades, combustors, afterburner parts, etc.). It is a promising material.
【０００４】しかし、従来のＣＭＣは、気密性を保持す
ることができず、かつ耐熱衝撃性が低い問題点があっ
た。すなわち、従来のＣＭＣは、所定の形状をセラミッ
クス繊維で構成したのち、いわゆるＣＶＩ処理（Ｃｈｅ
ｍｉｃａｌ Ｖａｐｏｒ Ｉｎｆｉｌｔｒａｔｉｏｎ：
気相含浸法）で繊維の隙間にマトリックスを形成する
が、このＣＶＩで繊維間の隙間を完全に埋めるには実用
不可能な長期間（例えば１年以上）を要する問題点があ
った。また、このように形成した従来のＣＭＣを高温で
試験等すると、激しい熱衝撃（例えば温度差が９００℃
以上）が作用した場合に、強度低下が激しく、再使用が
ほとんどできない問題点があった。そのため、従来のセ
ラミックス基複合部材（ＣＭＣ）は、タービン翼、燃焼
器のような気密性と耐熱衝撃性を要する部品には実質的
に使用できなかった。However, the conventional CMC has a problem that it cannot maintain airtightness and its thermal shock resistance is low. That is, in the conventional CMC, after a predetermined shape is made of ceramic fibers, so-called CVI treatment (Che treatment) is performed.
medical Vapor Information:
The matrix is formed in the interstices of the fibers by the vapor phase impregnation method), but there is a problem that it takes an impractical long time (for example, one year or more) to completely fill the interstices of the fibers with this CVI. Moreover, when the conventional CMC thus formed is tested at a high temperature, a severe thermal shock (for example, a temperature difference of 900 ° C.
When the above) acts, there is a problem that the strength is drastically reduced and reuse is hardly possible. Therefore, the conventional ceramics-based composite member (CMC) cannot be practically used for parts that require airtightness and thermal shock resistance, such as turbine blades and combustors.
【０００５】本発明の発明者等は、上述した問題点を解
決するために、気密性と耐熱衝撃性を大幅に高めること
ができ、これによりスラストチャンバ等にも実用可能な
「セラミックス基複合部材及びその製造方法」（特開２
０００−２１９５７６号）を創案し出願した。この発明
は、成形した繊維織物の表面にＳｉＣマトリックス層を
形成するＣＶＩ処理を行った後に、そのマトリックス層
の隙間に有機珪素ポリマーを基材として含浸し焼成する
ＰＩＰ処理を行うものである。In order to solve the above-mentioned problems, the inventors of the present invention can greatly enhance the airtightness and the thermal shock resistance, and thus the "ceramics-based composite member which can be practically used in the thrust chamber and the like. And its manufacturing method "
000-219576) was proposed and filed. According to the present invention, a CVI treatment for forming a SiC matrix layer on the surface of a molded fiber woven fabric is performed, and then a PIP treatment for impregnating the gaps in the matrix layer with an organic silicon polymer as a base material and firing the PIP treatment.
【０００６】[0006]
【発明が解決しようとする課題】上述したＣＭＣは、軽
量で耐熱性に優れるため、ジェットエンジンのガスター
ビン部品、例えば、タービン静翼や排気ディフューザベ
ーン）へ適用することが検討されている。しかし、ター
ビン静翼や排気ディフューザベーンは、図５に示すよう
に、翼部１の両端にフランジ部２（バンド部と呼ぶ）を
有する構造であり、このバンド部を有する翼形状をＣＭ
Ｃで一体成形することは、従来、困難であった。Since the CMC described above is lightweight and has excellent heat resistance, its application to gas turbine parts for jet engines, such as turbine vanes and exhaust diffuser vanes, is being studied. However, as shown in FIG. 5, the turbine vane and the exhaust diffuser vane have a structure in which there are flange portions 2 (called band portions) at both ends of the blade portion 1, and the blade shape having this band portion is CM.
It has been difficult in the past to integrally mold C.
【０００７】すなわち、バンド部２は平板状又は円弧面
であるのに対して、翼部１は翼形の中空筒形であるた
め、全体をＣＭＣの一体成形体とするには、平織りした
セラミックス繊維で翼部及びバンド部を成形し、これに
マトリックスを含浸してセラミックス基複合部材（ＣＭ
Ｃ）を製造する必要があった。この場合、全体の一体成
形化はできるものの、翼部１に繊維の縫い目があり、翼
部に作用するフープ応力に弱く、縫い目から亀裂が入り
やすい問題点があった。また、平織りのセラミックス繊
維で翼部を成形するのは、技術的に困難であり、コスト
がかかる問題点もあった。That is, the band portion 2 has a flat plate shape or an arc surface, while the wing portion 1 has a hollow cylindrical shape of a wing shape. Therefore, in order to make the whole into an integrally molded body of CMC, plain weave ceramics is used. Wings and bands are formed from fibers, and the matrix is impregnated into the ceramics-based composite member (CM
C) had to be manufactured. In this case, although the whole can be integrally molded, there is a problem that the wing portion 1 has a seam of fibers, is weak against the hoop stress acting on the wing part, and is likely to be cracked from the seam. Further, it is technically difficult to form the blade portion with the plain weave ceramic fiber, and there is a problem that the cost is high.
【０００８】そこで、翼部１のみをＣＭＣで製造し、バ
ンド部は別部品で組み立てる分割式のＣＭＣ翼が、例え
ば、ＵＳ５０７４７４９（図６）、ＵＳ５６３０７００
（図７）等に提案されている。しかし、かかる分割式の
ＣＭＣ翼は、翼部１とバンド部２とのシール性が不十分
であり、かつ両者を連結して一体化するために余分な部
品（ボルト、フランジ等）を必要とし、ＣＭＣを用いた
重量低減（軽量化）のメリットが失われてしまう問題点
があった。Therefore, a split type CMC blade in which only the blade portion 1 is manufactured by CMC and the band portion is assembled by separate parts is disclosed in, for example, US5074749 (FIG. 6) and US5630700.
(Fig. 7) and the like. However, such a split CMC blade does not have sufficient sealability between the blade portion 1 and the band portion 2 and requires extra parts (bolts, flanges, etc.) to connect and integrate the two. However, there is a problem that the merit of weight reduction (weight reduction) using CMC is lost.
【０００９】本発明は上述した問題点を解決するために
創案されたものである。すなわち、本発明の目的は、バ
ンド部と翼部を一体成形でき、かつ翼部がフープ応力に
強く、翼部とバンド部とのシール性を高めることができ
るバンド部付きセラミックス基複合部材とその製造方法
を提供することにある。The present invention was created to solve the above problems. That is, an object of the present invention is to integrally mold the band part and the wing part, and the wing part is resistant to hoop stress, and a ceramic base composite member with a band part capable of enhancing the sealing property between the wing part and the band part and the same. It is to provide a manufacturing method.
【００１０】[0010]
【課題を解決するための手段】本発明によれば、翼形筒
状の翼部（１）と、該翼部の端部に連続して形成された
平板状又は円弧状のバンド部（２）とからなり、前記翼
部は、セラミックス繊維のブレード織りで成形され、か
つ翼部端の張出部（１ａ）が折曲げられて、バンド部内
に挟持されており、前記バンド部は、セラミックス繊維
の平織り板（２ａ）からなる複数の積層体であり、更
に、前記翼部の折曲げられた張出部（１ａ）と平織り板
（２ａ）は、バンド部を貫通するセラミックス繊維
（３）で一体に縫い合わされている、ことを特徴とする
バンド部付きセラミックス基複合部材が提供される。According to the present invention, an airfoil-shaped tubular wing portion (1) and a flat plate-shaped or arc-shaped band portion (2) continuously formed at an end portion of the wing portion (2). ) Is formed by blade weaving of ceramic fibers, and the overhanging portion (1a) at the end of the blade is bent and sandwiched in the band portion, and the band portion is made of ceramics. A plurality of laminated bodies composed of a plain weave plate (2a) of fibers, and further, the bent overhanging portion (1a) and the plain weave plate (2a) of the wing portion are ceramic fibers (3) penetrating a band portion. A ceramic base composite member with a band portion is provided, which is sewn integrally with each other.
【００１１】また、本発明によれば、翼形筒状の翼部
（１）を翼部端の張出部（１ａ）と共にブレード織りで
成形する翼部成形ステップ（Ａ）と、平板状又は円弧状
のバンド部（２）を構成する複数の平織り板（２ａ）を
成形するバンド部成形ステップ（Ｂ）と、翼部端の張出
部（１ａ）を折曲げ、これを複数の平織り板（２ａ）の
間に挟持し、バンド部を貫通するセラミックス繊維で張
出部（１ａ）と平織り板（２ａ）を一体に縫い合わす一
体化ステップ（Ｃ）とを備える、ことを特徴とするバン
ド部付きセラミックス基複合部材の製造方法が提供され
る。According to the present invention, the blade portion forming step (A) of forming the blade-shaped tubular blade portion (1) together with the overhanging portion (1a) of the blade portion by blade weaving, and the flat plate shape or A band part forming step (B) for forming a plurality of plain weave plates (2a) constituting an arc-shaped band part (2) and a wing end protruding portion (1a) are bent, and a plurality of plain weave plates are formed. A band, characterized by comprising an integration step (C) of sandwiching it between (2a) and integrally stitching the overhanging part (1a) and the plain weave plate (2a) with a ceramic fiber penetrating the band part. A method of manufacturing a ceramic matrix composite member with a part is provided.
【００１２】本発明の好ましい実施形態によれば、前記
翼部成形ステップ（Ａ）において、治具の表面にセラミ
ックス繊維をブレード織りし、次いでその表面にマトリ
ックスを含浸させて翼部を成形する。According to a preferred embodiment of the present invention, in the blade portion forming step (A), ceramic fibers are braided on the surface of the jig and then the surface is impregnated with a matrix to form the blade portion.
【００１３】上記本発明の構造及び方法によれば、翼形
筒状の翼部（１）の翼部端の張出部（１ａ）を折曲げ
て、バンド部を構成する複数の平織り板（２ａ）の間に
挟持し、かつ翼部の折曲げた張出部（１ａ）と平織り板
（２ａ）が、バンド部を貫通するセラミックス繊維
（３）で一体に縫い合わされるので、翼部とバンド部と
の境目には、折曲げられバンド部内に挟持された翼部
（１）の張出部（１ａ）が翼部と連続して存在する。従
って、翼部とバンド部は、ブレード織りの織物と平織り
板とが実質的に一体化され、かつ境目に隙間が全くでき
ないので高いシール性を得ることができる。According to the above-described structure and method of the present invention, a plurality of plain weave plates (which constitute the band portion) are formed by bending the protruding portion (1a) of the blade end of the blade-shaped tubular blade portion (1). Since the overhanging portion (1a) sandwiched between 2a) and the bent wing portion and the plain weave plate (2a) are integrally sewn together with the ceramic fiber (3) penetrating the band portion, At the boundary with the band part, the overhanging part (1a) of the wing part (1) which is bent and sandwiched in the band part exists continuously with the wing part. Therefore, since the blade weave fabric and the plain weave plate are substantially integrated in the wing portion and the band portion, and no gap is formed at the boundary, high sealing performance can be obtained.
【００１４】また、翼部（１）は、セラミックス繊維の
ブレード織りで成形されるので、フープ応力に対し強い
強度を得ることができる。更に、一体で作られた静翼の
ため、従来の分割式のＣＭＣや一体式のＣＭＣに比較し
て構造がシンプルであり、大幅なコストダウンが可能で
ある。更にまた、ブレード織りと平織りをそれぞれ独立
に最適化することにより、繊維の体積割合の高い高強度
織物構造とすることができる。Further, since the blade portion (1) is formed by braiding of ceramic fibers, it is possible to obtain a high strength against hoop stress. Further, since the stator vanes are integrally formed, the structure is simpler than that of the conventional split type CMC or the integral type CMC, and the cost can be significantly reduced. Furthermore, by independently optimizing the braid weave and the plain weave, it is possible to obtain a high-strength woven structure having a high fiber volume ratio.
【００１５】[0015]
【発明の実施の形態】以下、本発明の好ましい実施形態
を図面を参照して説明する。なお、各図において共通す
る部分には同一の符号を付し、重複した説明を省略す
る。BEST MODE FOR CARRYING OUT THE INVENTION Preferred embodiments of the present invention will be described below with reference to the drawings. In addition, in each figure, the common part is denoted by the same reference numeral, and the duplicated description will be omitted.
【００１６】図１は、本発明のバンド部付きセラミック
ス基複合部材の分解斜視図であり、図２は、その完成後
の全体斜視図である。図１及び図２に示すように、本発
明のバンド部付きセラミックス基複合部材１０は、翼形
筒状の翼部１と、翼部１の端部に連続して形成された平
板状又は円弧状のバンド部２とからなる。FIG. 1 is an exploded perspective view of a ceramic base composite member with a band portion according to the present invention, and FIG. 2 is an overall perspective view after completion thereof. As shown in FIGS. 1 and 2, a ceramic base composite member 10 with a band portion according to the present invention has a wing portion 1 having a cylindrical airfoil shape and a flat plate shape or a circle continuously formed at an end portion of the wing portion 1. The band portion 2 has an arc shape.
【００１７】翼部１は、フープ応力に対し強いセラミッ
クス繊維のブレード織りで成形されている。「ブレード
織り」とは、図３に模式的に示すように、中央糸に組み
糸を交互に斜めに織り込む織物であり、治具の表面に効
率的に織物を成形できると共に、フープ応力に対し強い
特徴を有する。また、翼部端の張出部１ａは、翼部１と
共にブレード織りで成形された後、一部に切り込みを入
れて水平に折曲げられ、バンド部内に挟持されている。The wing portion 1 is formed of a braid weave of ceramic fibers that is strong against hoop stress. "Blade weaving" is a woven fabric in which a braiding yarn is alternately woven diagonally into a central yarn, as schematically shown in FIG. 3, and the woven fabric can be efficiently formed on the surface of the jig, and the hoop stress Has strong characteristics. Further, the overhanging portion 1a at the end of the wing portion is formed by blade weaving together with the wing portion 1, and is partially bent to be horizontally bent and sandwiched in the band portion.
【００１８】バンド部２は、セラミックス繊維により２
次元又は３次元に織られた平織り板２ａからなる複数の
積層体である。この平織り板２ａは、縦糸と横糸からな
る通常の平織りの他、ロービングを一方向に並列したプ
リプレグシート、或いは３軸織物でも良い。また、この
平織り板２ａには、翼部１の翼形に対応した開口２ｂが
設けられている。なお、この開口２ｂは、バンド部２の
外面に使用する平織り板２ａの場合には省略することも
できる。The band portion 2 is made of ceramic fiber 2
It is a plurality of laminated bodies composed of a plain weave plate 2a woven three-dimensionally or three-dimensionally. The plain weave plate 2a may be a normal plain weave composed of warp yarns and weft yarns, a prepreg sheet in which rovings are arranged in one direction, or a triaxial woven fabric. Further, the plain weave plate 2a is provided with an opening 2b corresponding to the wing shape of the wing portion 1. The opening 2b can be omitted in the case of the plain weave plate 2a used for the outer surface of the band portion 2.
【００１９】更に、翼部の折曲げられた張出部１ａと平
織り板２ａは、バンド部２を厚さ方向に貫通するセラミ
ックス繊維３で一体に縫い合わされている。この縫い合
わせは、図２に示すように、縦方向と横方向に複数行
い、繊維密度を十分に高めるのがよい。Further, the bent overhanging portion 1a of the wing portion and the plain weave plate 2a are integrally sewn together with a ceramic fiber 3 penetrating the band portion 2 in the thickness direction. As shown in FIG. 2, this stitching is preferably performed in plural in the longitudinal direction and in the lateral direction to sufficiently increase the fiber density.
【００２０】本発明のバンド部付きセラミックス基複合
部材１０は、上述のように成形した繊維織物の表面にＳ
ｉＣマトリックス層を形成するＣＶＩ処理を行った後
に、そのマトリックス層の隙間に有機珪素ポリマーを基
材として含浸し焼成するＰＩＰ処理を行ったものであ
る。The ceramic-based composite member 10 with a band portion of the present invention has S formed on the surface of the fiber fabric formed as described above.
After the CVI treatment for forming the iC matrix layer, the PIP treatment of impregnating the gaps in the matrix layer with the organic silicon polymer as the base material and firing the PIP treatment is performed.
【００２１】図４は、本発明によるバンド部付きセラミ
ックス基複合部材の製造方法の模式図である。この図に
示すように、本発明の製造方法は、翼部成形ステップ
（Ａ）、バンド部成形ステップ（Ｂ）及び一体化ステッ
プ（Ｃ）を有する。FIG. 4 is a schematic view of a method for manufacturing a ceramic base composite member with a band portion according to the present invention. As shown in this figure, the manufacturing method of the present invention includes a blade forming step (A), a band forming step (B), and an integration step (C).
【００２２】翼部成形ステップ（Ａ）は、治具の表面に
セラミックス繊維をブレード織りする翼部ブレード織り
工程Ｓ１１と、ブレード織りした織物の表面にＣＶＩで
０．１〜０．２μｍ程度のカーボンをコーティングする
Ｃ−ＣＶＤ工程Ｓ１２と、更にその繊維表面にＣＶＩに
よりＳｉＣのマトリックスを含浸させるＳｉＣ−ＣＶＩ
工程Ｓ１３とからなる。セラミックス繊維には、例えば
宇部興産株式会社製のチラノＺＭＩ繊維を用いる。この
翼部成形ステップ（Ａ）では、翼形筒状の翼部１を翼部
端の張出部１ａと共にブレード織りで成形する。また、
ＳｉＣ−ＣＶＩ工程Ｓ１３におけるマトリックスの含浸
量は、一体化ステップ（Ｃ）における翼部１の加工が容
易にできる程度に抑える。The wing portion forming step (A) is a wing portion blade weaving step S11 for blade-weaving ceramic fibers on the surface of the jig, and carbon of about 0.1 to 0.2 μm in CVI on the surface of the blade-woven fabric. C-CVD step S12 for coating SIC, and further SiC-CVI for impregnating the fiber surface with a matrix of SiC by CVI
And step S13. As the ceramic fiber, for example, Tyranno ZMI fiber manufactured by Ube Industries, Ltd. is used. In the blade forming step (A), the blade 1 having a cylindrical airfoil shape is formed by blade weaving together with the protruding portion 1a at the blade end. Also,
The impregnation amount of the matrix in the SiC-CVI step S13 is suppressed to such an extent that the wing portion 1 can be easily processed in the integration step (C).
【００２３】バンド部成形ステップ（Ｂ）は、平板状又
は円弧状の平織り板２ａを平織りするバンド部平織り工
程Ｓ２１と、平織りした織物の表面にＣＶＩで０．１〜
０．２μｍ程度のカーボンをコーティングするＣ−ＣＶ
Ｄ工程Ｓ２２と、更にその繊維表面にＣＶＩによりＳｉ
Ｃのマトリックスを含浸させるＳｉＣ−ＣＶＩ工程Ｓ２
３とからなる。Ｃ−ＣＶＤ工程Ｓ２２とＳｉＣ−ＣＶＩ
工程２３は、Ｃ−ＣＶＤ工程Ｓ１２とＳｉＣ−ＣＶＩ工
程Ｓ１３と実質的に同一である。平織り板２ａの翼部１
の翼形に対応した開口２ｂは、工程Ｓ２１で加工しても
よく、或いは、ＳｉＣ−ＣＶＩ工程Ｓ１３の後で加工し
てもよい。また、通常の平織りの代わりに、ロービング
を一方向に並列したプリプレグシート、或いは３軸織物
を用いてもよい。The band portion forming step (B) includes a band portion plain weaving step S21 for plain weaving the flat or arcuate plain weave plate 2a, and a CVI of 0.1 to 0.1 on the surface of the plain woven fabric.
C-CV coating carbon of about 0.2 μm
D step S22, and Si on the fiber surface by CVI
SiC-CVI step S2 of impregnating C matrix
3 and 3. C-CVD process S22 and SiC-CVI
Step 23 is substantially the same as C-CVD step S12 and SiC-CVI step S13. Wing 1 of plain woven board 2a
The opening 2b corresponding to the airfoil may be processed in step S21, or may be processed after the SiC-CVI step S13. Further, instead of a normal plain weave, a prepreg sheet in which rovings are arranged in one direction may be used, or a triaxial woven fabric may be used.
【００２４】一体化ステップ（Ｃ）は、翼部１と共にブ
レード織りで成形された翼部端の張出部１ａの一部にカ
ッター等で切り込みを入れ、次いで張出部１ａを図１で
水平に折曲げる翼部の端部加工工程Ｓ３１と、折曲げた
翼部端の張出部１ａを複数の平織り板２ａの間に挟持
し、バンド部を貫通するセラミックス繊維３で張出部１
ａと平織り板２ａを一体に縫い合わせる縫合わせ工程Ｓ
３２とからなる。In the integration step (C), a notch is used to cut a part of the overhanging portion 1a at the end of the blade formed by blade weaving together with the blade portion 1, and then the overhanging portion 1a is horizontal in FIG. The wing end processing step S31 of folding the blade into a wing and the bulging portion 1a of the bent wing end are sandwiched between a plurality of plain weave plates 2a, and the bulging portion 1 is formed by the ceramic fibers 3 penetrating the band portion.
a and the plain woven plate 2a are integrally sewn together in the sewing step S
And 32.
【００２５】縫合わせ工程Ｓ３２が完了すると、図２に
示すようなバンド部付きセラミックス基複合部材の織物
が完成する。次いで、織物の繊維表面にＣＶＩによりＳ
ｉＣのマトリックスを再度含浸させるＳｉＣ−ＣＶＩ工
程Ｓ４１、マトリックス層の隙間に有機珪素ポリマーを
基材として含浸し焼成するＰＩＰ工程Ｓ４２を行った
後、機械加工（Ｓ４３）し、最後に再度ＳｉＣ−ＣＶＩ
工程Ｓ４４を行って目的とするバンド部付きセラミック
ス基複合部材１０が完成する。When the sewing step S32 is completed, the woven fabric of the ceramic base composite member with the band portion as shown in FIG. 2 is completed. Then, the S fiber is applied to the fiber surface of the fabric by CVI.
After performing a SiC-CVI step S41 of re-impregnating the iC matrix and a PIP step S42 of impregnating and baking the organosilicon polymer in the gaps of the matrix layer, machining (S43) is performed, and finally SiC-CVI is performed again.
By carrying out step S44, the target ceramics-based composite member 10 with a band portion is completed.
【００２６】翼部成形ステップ（Ａ）において使用した
治具（例えばカーボン製）は、最終形状を保持できる限
りで、どの工程において外してもよいが、ＳｉＣ−ＣＶ
Ｉ工程１３の後、或いはＳｉＣ−ＣＶＩ工程Ｓ４１の後
で外すのが好ましい。The jig (for example, made of carbon) used in the step (A) for forming the blade portion may be removed in any step as long as it can maintain the final shape.
It is preferably removed after the I step 13 or after the SiC-CVI step S41.
【００２７】上述した本発明の構造及び方法によれば、
翼形筒状の翼部１の翼部端の張出部１ａを折曲げて、バ
ンド部を構成する複数の平織り板２ａの間に挟持し、か
つ翼部の折曲げた張出部１ａと平織り板２ａが、バンド
部を貫通するセラミックス繊維３で一体に縫い合わされ
るので、翼部とバンド部との境目には、折曲げられバン
ド部内に挟持された翼部１の張出部１ａが翼部と連続し
て存在する。従って、翼部とバンド部は、ブレード織り
の織物と平織り板とが実質的に一体化され、かつ境目に
隙間が全くできないので高いシール性を得ることができ
る。According to the structure and method of the present invention described above,
The protruding portion 1a at the end of the blade portion of the airfoil-shaped tubular blade portion 1 is bent and sandwiched between a plurality of plain weave plates 2a forming the band portion, and the protruding portion 1a is formed by bending the blade portion. Since the plain weave plate 2a is integrally sewn with the ceramic fibers 3 penetrating the band part, the overhanging part 1a of the wing part 1 which is bent and sandwiched in the band part is formed at the boundary between the wing part and the band part. It exists continuously with the wings. Therefore, since the blade weave fabric and the plain weave plate are substantially integrated in the wing portion and the band portion, and no gap is formed at the boundary, high sealing performance can be obtained.
【００２８】また、翼部１は、セラミックス繊維のブレ
ード織りで成形されるので、フープ応力に対し強い強度
を得ることができる。更に、一体で作られた静翼のた
め、従来の分割式のＣＭＣや一体式のＣＭＣに比較して
構造がシンプルであり、大幅なコストダウンが可能であ
る。更にまた、ブレード織りと平織りをそれぞれ独立に
最適化することにより、繊維の体積割合の高い高強度織
物構造とすることができる。Further, since the wing portion 1 is formed by the ceramic fiber braid weave, it is possible to obtain strong strength against the hoop stress. Further, since the stator vanes are integrally formed, the structure is simpler than that of the conventional split type CMC or the integral type CMC, and the cost can be significantly reduced. Furthermore, by independently optimizing the braid weave and the plain weave, it is possible to obtain a high-strength woven structure having a high fiber volume ratio.
【００２９】なお、本発明は上述した実施の形態に限定
されず、本発明の要旨を逸脱しない範囲で種々変更でき
ることは勿論である。The present invention is not limited to the above-mentioned embodiments, and it goes without saying that various modifications can be made without departing from the gist of the present invention.
【００３０】[0030]
【発明の効果】上述したように本発明のバンド部付きセ
ラミックス基複合部材とその製造方法は、一体で作られ
た静翼のため、複雑な構造を必要としない、シール性に
優れる、コストメリットがある、織り構造を組み合わせ
て最適化することで、繊維体積割合の高い高強度織物構
造とできる、等の特徴を有する。As described above, the ceramic base composite member with a band portion and the method for manufacturing the same according to the present invention do not require a complicated structure because of the integrally formed stationary blade, have excellent sealing properties, and have a cost advantage. There is a feature that a high strength woven structure having a high fiber volume ratio can be obtained by combining and optimizing a woven structure.
【００３１】従って、本発明のバンド部付きセラミック
ス基複合部材とその製造方法は、バンド部と翼部を一体
成形でき、かつ翼部がフープ応力に強く、翼部とバンド
部とのシール性を高めることができる等の優れた効果を
有する。Therefore, according to the ceramic base composite member with the band portion and the method for manufacturing the same of the present invention, the band portion and the blade portion can be integrally formed, the blade portion is resistant to hoop stress, and the sealing property between the blade portion and the band portion is improved. It has an excellent effect that it can be enhanced.
【図１】本発明のバンド部付きセラミックス基複合部材
の分解斜視図である。FIG. 1 is an exploded perspective view of a ceramic base composite member with a band portion according to the present invention.
【図２】本発明のバンド部付きセラミックス基複合部材
の全体斜視図である。FIG. 2 is an overall perspective view of a ceramic base composite member with a band portion of the present invention.
【図３】ブレード織りの模式図である。FIG. 3 is a schematic diagram of blade weaving.
【図４】本発明によるバンド部付きセラミックス基複合
部材の製造方法の模式図である。FIG. 4 is a schematic diagram of a method for producing a ceramics-based composite member with a band portion according to the present invention.
【図５】バンド部付きセラミックス基複合部材の模式図
である。FIG. 5 is a schematic view of a ceramics-based composite member with a band portion.
【図６】従来の分割式ＣＭＣ翼の模式図である。FIG. 6 is a schematic view of a conventional split CMC blade.
【図７】従来の分割式ＣＭＣ翼の別の模式図である。FIG. 7 is another schematic view of a conventional split CMC blade.
１ 翼部、１ａ 翼部端の張出部、２ バンド部、２ａ
平織り板、３ セラミックス繊維、１０ バンド部付
きセラミックス基複合部材1 Wing portion, 1a Wing end portion overhanging portion, 2 Band portion, 2a
Plain woven board, 3 ceramics fibers, 10 ceramics base composite member with band part
Claims (3)
に連続して形成された平板状又は円弧状のバンド部
（２）とからなり、 前記翼部は、セラミックス繊維のブレード織りで成形さ
れ、かつ翼部端の張出部（１ａ）が折曲げられて、バン
ド部内に挟持されており、 前記バンド部は、セラミックス繊維の平織り板（２ａ）
からなる複数の積層体であり、 更に、前記翼部の折曲げられた張出部（１ａ）と平織り
板（２ａ）は、バンド部を貫通するセラミックス繊維
（３）で一体に縫い合わされている、ことを特徴とする
バンド部付きセラミックス基複合部材。1. A wing-shaped tubular wing part (1), and a flat plate-shaped or arc-shaped band part (2) continuously formed at an end of the wing part, the wing part comprising: It is formed by blade weaving of ceramic fibers, and the overhanging portion (1a) of the blade end is bent and sandwiched in the band portion, and the band portion is a plain weave plate (2a) of ceramic fiber.
The bent overhang portion (1a) and the plain weave plate (2a) of the wing portion are integrally sewn together with a ceramic fiber (3) penetrating the band portion. A ceramic-based composite member with a band portion, characterized in that
（１ａ）と共にブレード織りで成形する翼部成形ステッ
プ（Ａ）と、平板状又は円弧状のバンド部（２）を構成
する複数の平織り板（２ａ）を成形するバンド部成形ス
テップ（Ｂ）と、翼部端の張出部（１ａ）を折曲げ、こ
れを複数の平織り板（２ａ）の間に挟持し、バンド部を
貫通するセラミックス繊維で張出部（１ａ）と平織り板
（２ａ）を一体に縫い合わす一体化ステップ（Ｃ）とを
備える、ことを特徴とするバンド部付きセラミックス基
複合部材の製造方法。2. A wing portion forming step (A) of forming a wing-shaped tubular wing portion (1) together with an overhanging portion (1a) of the wing portion by blade weaving, and a flat plate-shaped or arc-shaped band portion ( 2) A band portion forming step (B) for forming a plurality of plain weave plates (2a) and a protruding portion (1a) at the wing end are bent, and this is placed between a plurality of plain weave plates (2a). A ceramic base composite member with a band part, comprising an integrated step (C) for sandwiching and sandwiching the overhanging part (1a) and the plain weave plate (2a) with a ceramic fiber penetrating the band part. Manufacturing method.
治具の表面にセラミックス繊維をブレード織りし、次い
でその表面にマトリックスを含浸させて翼部を成形す
る、ことを特徴とする請求項２に記載の製造方法。3. In the step (A) of forming the wing portion,
3. The manufacturing method according to claim 2, wherein the surface of the jig is braided with ceramic fibers, and then the surface is impregnated with a matrix to form a wing portion.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| JP2001345712A JP3978766B2 (en) | 2001-11-12 | 2001-11-12 | Ceramic matrix composite member with band and method for manufacturing the same |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| JP2001345712A JP3978766B2 (en) | 2001-11-12 | 2001-11-12 | Ceramic matrix composite member with band and method for manufacturing the same |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| JP2003148105A true JP2003148105A (en) | 2003-05-21 |
| JP3978766B2 JP3978766B2 (en) | 2007-09-19 |
Family
ID=19159008
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| JP2001345712A Expired - Lifetime JP3978766B2 (en) | 2001-11-12 | 2001-11-12 | Ceramic matrix composite member with band and method for manufacturing the same |
Country Status (1)
| Country | Link |
|---|---|
| JP (1) | JP3978766B2 (en) |
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