JP3345909B2 - Method of manufacturing compressor blade and compressor blade - Google Patents
Method of manufacturing compressor blade and compressor bladeInfo
- Publication number
- JP3345909B2 JP3345909B2 JP8114792A JP8114792A JP3345909B2 JP 3345909 B2 JP3345909 B2 JP 3345909B2 JP 8114792 A JP8114792 A JP 8114792A JP 8114792 A JP8114792 A JP 8114792A JP 3345909 B2 JP3345909 B2 JP 3345909B2
- Authority
- JP
- Japan
- Prior art keywords
- wing
- shape
- wing body
- manufacturing
- compressor
- 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.)
- Expired - Fee Related
Links
Landscapes
- Turbine Rotor Nozzle Sealing (AREA)
- Injection Moulding Of Plastics Or The Like (AREA)
Description
【０００１】[0001]
【産業上の利用分野】本発明は、航空用、産業用ガスタ
ービン等の圧縮機で使用される圧縮機翼の製造方法に関
する。BACKGROUND OF THE INVENTION 1. Field of the Invention The present invention relates to a method for manufacturing a compressor blade used in a compressor of an aeronautical or industrial gas turbine or the like.
【０００２】[0002]
【従来の技術】航空用、産業用ガスタービン等の圧縮機
で使用される動翼、静翼などの圧縮機翼は、一般にチタ
ン、ステンレス、アルミニウム等を素材とした金属製で
あり、この圧縮機翼を製造するにあたっては、従来、鋳
造加工、機械加工、仕上げ加工およびコーティング加工
の手順にしたがって作業が行なわれていた。BACKGROUND ART aviation, blades used in compressors, such as industrial gas turbines, compressors vanes such as vanes, are typically titanium, stainless steel, steel metal aluminum or the like to a material, the compression Conventionally, when manufacturing machine blades , operations have been performed according to the procedures of casting, machining, finishing, and coating.
【０００３】[0003]
【発明が解決しようとする課題】しかしながら、従来の
製造方法においては、（１）製造期間が長い、（２）素
材のコストが高くかつ加工工程が多いので高価である、
（３）細部の複雑な加工が困難で形状精度が得られな
い、（４）重量が重い、などの問題点を有していた。However, in the conventional manufacturing method, (1) the manufacturing period is long, (2) the cost of the material is high, and the number of processing steps is high, so that the method is expensive.
(3) The complicated processing of the details is difficult, and the shape accuracy cannot be obtained, and (4) the weight is heavy.
【０００４】本発明は、このような事情に鑑みてなされ
たものであって、製作期間の短縮化、作業の簡易化、形
状精度の向上、コストダウン、および軽量化を図り、さ
らに圧縮機翼の重要特性である振動減衰率、比強度、比
剛性の向上を図ることが可能な圧縮機翼の製造方法を提
供することを目的としている。[0004] The present invention was made in view of such circumstances, shortening of production period, simplification of work, improve the shape accuracy, cost, and reducing the weight, further compressor blades It is an object of the present invention to provide a method for manufacturing a compressor blade capable of improving vibration damping rate, specific strength, and specific rigidity, which are important characteristics of the compressor blade .
【０００５】[0005]
【課題を解決するための手段】本発明にあっては、プリ
プレグ材を積層一体化した翼本体形成材で、所望の翼形
状より小寸法でかつ該翼形状に近似の翼本体を形成し、
次いでこの翼本体を、所望の翼形状を得るためのモール
ドに挿入し、該翼本体とモールドとの間に形成される隙
間に熱可塑性樹脂を圧入、充填した状態で、圧縮成形を
行い、該翼本体の周囲に、該翼本体の翼形状を決定する
層を形成することを、前記課題の解決手段とした。According to the present invention, a wing body forming material obtained by laminating and integrating prepreg materials is used to form a wing body having dimensions smaller than a desired wing shape and approximate to the wing shape.
Next, the wing main body is inserted into a mold for obtaining a desired wing shape, and compression molding is performed while a thermoplastic resin is press-fitted and filled in a gap formed between the wing main body and the mold. Forming a layer that determines the wing shape of the wing body around the wing body is a means for solving the above problem.
【０００６】[0006]
【作用】本発明に係る圧縮機翼の製造方法によれば、翼
本体を形成する工程では、所望の翼形状に近似した大略
の形状を得るようにするので、厳密な形状制御が要ら
ず、作業が簡易である。そして、最終的に目的の翼を形
成する工程では、翼本体の周囲に熱可塑性樹脂を圧入、
充填した状態で圧縮成形を行なうので、作業性が良く、
しかも形状精度が向上する。According to the method for manufacturing a compressor blade according to the present invention, in the step of forming the blade body, an approximate shape close to a desired blade shape is obtained, so that strict shape control is not required. The work is simple. And finally, in the process of forming the target wing, a thermoplastic resin is pressed around the wing body,
Since compression molding is performed in the filled state, workability is good,
Moreover, the shape accuracy is improved.
【０００７】[0007]
【実施例】以下、本発明に係る圧縮機翼の製造方法の一
実施例について、図１ないし図６を参照して説明する。DETAILED DESCRIPTION OF THE PREFERRED EMBODIMENTS One embodiment of a method for manufacturing a compressor blade according to the present invention will be described below with reference to FIGS.
【０００８】まず、プリプレグ材１ａ、１ａ…を板状に
積層一体化して翼本体形成材１を形成する。プリプレグ
材１ａは、母材（マトリックス）がエポキシ樹脂等の熱
硬化性樹脂、強化材が炭素繊維からなる強化プラスチッ
クであり、これを複数枚板状に積層して、オートクレー
ブ内に入れ、窒素雰囲気のもと加圧加熱状態で、一体化
する。翼本体形成材１は、動翼あるいは静翼など、所望
の圧縮機翼（以下、単に翼と略称する。）を２分割した
ものに近似の形状を有し、図１にはこの翼本体形成材１
の平面図、図２には側面図を示している。First, the prepreg materials 1a, 1a,... Are laminated and integrated in a plate shape to form the blade body forming material 1. The prepreg material 1a is made of a thermosetting resin such as an epoxy resin as a base material (matrix) and a reinforced plastic made of carbon fiber as a reinforcing material. Under pressure and heating. The blade body forming material 1 may be a desired one such as a moving blade or a stationary blade.
Has a shape similar to that obtained by dividing a compressor blade (hereinafter simply referred to as a blade) into two parts.
2 is a plan view, and FIG. 2 is a side view.
【０００９】次に、図３および図４に示すように、前記
翼本体形成材１、１を２体重ね合わせて、簡易モールド
２に挿入し、圧縮成形する。簡易モールド２には、所望
の翼形状より若干小さめで該翼形状に近似のキャビティ
２ａを有するものを使用する。図３には、この簡易モー
ルド２で前記翼本体形成材１、１を圧縮成形する方法を
示す正断面図、図４には、図３のIV−IV線に沿う断面図
を示している。圧縮成形は、１８０℃程度の温度条件下
で行なう。この圧縮成形により、所望の翼形状より若干
小さめで該翼形状に近似した形状の翼本体３が得られ
る。Next, as shown in FIGS. 3 and 4, the two wing body forming materials 1, 1 are superimposed, inserted into a simple mold 2, and compression-molded. As the simple mold 2, a mold having a cavity 2a slightly smaller than a desired blade shape and similar to the blade shape is used. FIG. 3 is a front sectional view showing a method of compression-molding the wing body forming materials 1 and 1 with the simple mold 2, and FIG. 4 is a sectional view taken along line IV-IV of FIG. The compression molding is performed under a temperature condition of about 180 ° C. By this compression molding, a blade body 3 slightly smaller than a desired blade shape and having a shape similar to the blade shape is obtained.
【００１０】次いで、図５および図６に示すように、こ
の翼本体３を、所望の翼形状を得るための最終モールド
４に挿入する。そして、該翼本体３と最終モールド４と
の間に形成される隙間５に、熱可塑性樹脂６をインジェ
クション方式により圧入し、この隙間５を充填した状態
で、圧縮成形を行う。最終モールド４には、最終的に所
望の翼形状に同形のキャビティ４ａを有し、該キャビテ
ィ４ａには熱可塑性樹脂６を圧入するための圧入口４ｂ
を有するものを使用する。図５には、この最終モールド
４で圧縮成形を行う方法を示す正断面図、図６には図５
のVI−VI線に沿う断面図を示している。熱可塑性樹脂６
にはＰＥＥＫ（ポリエーテルエーテルケトン）、あるい
はＰＥＥＫに強化材としてカーボンファイバ等を混入し
た複合材などを用いる。圧縮成形は、ＰＥＥＫの熱可塑
流動性を発現させ得る温度（４００℃程度）に加熱した
条件下で行なう。これにより、翼本体３の周囲に厚さ
０.１〜1.０ｍｍ程度のＰＥＥＫの層が形成された所望
の翼形状の翼が得られる。Next, as shown in FIGS. 5 and 6, the wing body 3 is inserted into a final mold 4 for obtaining a desired wing shape. Then, a thermoplastic resin 6 is press-fitted into a gap 5 formed between the wing body 3 and the final mold 4 by an injection method, and compression molding is performed with the gap 5 filled. The final mold 4 has a cavity 4a having the same shape as the final wing shape, and a press-in port 4b for press-fitting the thermoplastic resin 6 into the cavity 4a.
Use the one with FIG. 5 is a front sectional view showing a method of performing compression molding with the final mold 4, and FIG.
1 is a sectional view taken along line VI-VI of FIG. Thermoplastic resin 6
PEEK (polyetheretherketone) or a composite material obtained by mixing carbon fiber or the like as a reinforcing material in PEEK. The compression molding is performed under the condition of heating to a temperature (about 400 ° C.) at which the thermoplastic fluidity of PEEK can be exhibited. As a result, a wing having a desired wing shape in which a layer of PEEK having a thickness of about 0.1 to 1.0 mm is formed around the wing body 3 is obtained.
【００１１】このように、本実施例の製造方法によれ
ば、翼本体３を形成する工程では、簡易モールド２を用
いて、所望の翼形状に近似した大略の形状を得るように
するので、厳密な形状制御が要らず、作業が簡易であ
る。そして、最終的に目的の翼を形成する工程では、翼
本体３の周囲に熱可塑性樹脂６を圧入した状態で圧縮成
形を行なうので、作業性が良く、しかも形状精度の向上
を図り、さらにはボイドや層間剥離等の欠陥発生を防止
することができる。As described above, according to the manufacturing method of the present embodiment, in the step of forming the wing body 3, the approximate shape approximate to the desired wing shape is obtained by using the simple mold 2. Strict shape control is not required and the operation is simple. In the step of finally forming a target blade, compression molding is performed in a state where the thermoplastic resin 6 is press-fitted around the blade body 3, so that workability is good and shape accuracy is improved. The occurrence of defects such as voids and delamination can be prevented.
【００１２】また、表面の仕上げ加工が不要であること
から、製作工程を削減して、製作期間の短縮化およびコ
ストダウンを図ることができる。このため、実際のガス
タービンの圧縮機翼としてはもちろん、開発検討用の圧
縮機翼として使用するに当たっても最適である。Further, since the finishing process of the surface is unnecessary, the number of manufacturing steps can be reduced, so that the manufacturing period can be shortened and the cost can be reduced. Therefore, of course the compressor blades of the actual gas turbine, pressure for development study
Ideal for use as a compressor wing .
【００１３】また、金属製の圧縮機翼に比べて、振動減
衰率、比強度、比剛性が高く、かつ軽量である。また、
翼面の仕上がりが滑らかで、そのため空力性能が向上す
る。[0013] Further, as compared with a metal compressor blade , the vibration damping ratio, specific strength, specific rigidity are high, and the weight is light. Also,
The finish on the wing surface is smooth, which improves aerodynamic performance.
【００１４】なお、本発明は前記実施例のみに限定され
るものではなく、本発明の要旨を逸脱しない範囲内であ
れば、種々の変更を加え得ることはもちろんである。例
えば、前記実施例では、翼本体形成材１を所望の翼形状
を２分割したものに近似の形状としたが、該翼本体形成
材１は、一体でもよいし、あるいは３分割以上に分割さ
れたものに近似の形状とされてもよい。It should be noted that the present invention is not limited to the above-described embodiment, and various changes can be made without departing from the scope of the present invention. For example, in the above-described embodiment, the wing body forming material 1 has a shape approximate to a desired wing shape divided into two. However, the wing body forming material 1 may be integrated or divided into three or more. The shape may be an approximate shape.
【００１５】[0015]
【発明の効果】以上説明したように、本発明の圧縮機翼
の製造方法及び圧縮機翼によれば、以下のような効果を
奏する。 （１）大略の翼形状を得る工程と、目的の最終的な翼形
状を得る工程とを経るため、作業性が良く、形状精度の
向上を図ることができる。 （２）表面の仕上げ加工が不要であるため、製作工程を
削減して、製作期間の短縮化およびコストダウンを図る
ことができる。 （３）製作期間が短いため、開発検討用の圧縮機翼とし
て使用するに当たって最適である。 （４）金属製の圧縮機翼に比べて、振動減衰率、比強
度、比剛性が高く、かつ軽量である。As described above, according to the method for manufacturing a compressor blade and the compressor blade of the present invention, the following effects can be obtained. (1) Since a step of obtaining a general blade shape and a step of obtaining a target final blade shape are performed, workability is good and shape accuracy can be improved. (2) Since finishing work on the surface is not required, the number of manufacturing steps can be reduced, so that the manufacturing period can be shortened and the cost can be reduced. (3) Since the production period is short, it is most suitable for use as a compressor blade for development studies. (4) Higher vibration damping rate, specific strength, specific rigidity, and lighter weight than metal compressor blades .
【図１】本発明に係る圧縮機翼の製造方法の一実施例に
おいて、プリプレグ材を積層一体化して得た翼本体形成
材の一例を示す平面図である。FIG. 1 is a plan view showing an example of a blade body forming material obtained by laminating and integrating prepreg materials in one embodiment of a method for manufacturing a compressor blade according to the present invention.
【図２】図１の翼本体形成材の側面図である。FIG. 2 is a side view of the wing body forming member of FIG. 1;
【図３】本発明に係る圧縮機翼の製造方法の一実施例に
おいて、翼本体形成材から翼本体を形成する方法を示す
正断面図である。FIG. 3 is a front sectional view showing a method for forming a wing body from a wing body forming material in one embodiment of a method for manufacturing a compressor blade according to the present invention.
【図４】図３のIV−IV線に沿う断面図である。FIG. 4 is a sectional view taken along line IV-IV in FIG. 3;
【図５】本発明に係る圧縮機翼の製造方法の一実施例に
おいて、翼本体から目的の翼を形成する方法を示す正断
面図である。FIG. 5 is a front sectional view showing a method of forming a target wing from a wing body in one embodiment of a method for manufacturing a compressor wing according to the present invention.
【図６】図５のVI−VI線に沿う断面図である。FIG. 6 is a sectional view taken along the line VI-VI in FIG. 5;
１ 翼本体形成材 １ａ プリプレグ材 ２ 簡易モールド ３ 翼本体 ４ 最終モールド ５ 隙間 ６ 熱可塑性樹脂 Reference Signs List 1 wing body forming material 1a prepreg material 2 simple mold 3 wing body 4 final mold 5 gap 6 thermoplastic resin
───────────────────────────────────────────────────── フロントページの続き (56)参考文献 特開 昭58−165501（ＪＰ，Ａ) 特開 昭64−56902（ＪＰ，Ａ) 実開 平３−37203（ＪＰ，Ｕ) 実開 平１−111102（ＪＰ，Ｕ) (58)調査した分野(Int.Cl.7，ＤＢ名) B29D 31/00 F01D 5/14 ──────────────────────────────────────────────────続 き Continuation of the front page (56) References JP-A-58-165501 (JP, A) JP-A-64-56902 (JP, A) JP-A-3-37203 (JP, U) JP-A-1 111102 (JP, U) (58) Fields investigated (Int. Cl. 7 , DB name) B29D 31/00 F01D 5/14
Claims (4)
成材で、所望の翼形状より小寸法でかつ該翼形状に近似
の翼本体を形成し、次いでこの翼本体をモールドに挿入
し、該翼本体とモールドとの間に形成される隙間に熱可
塑性樹脂を圧入、充填した状態で圧縮成形を行ない、該
翼本体の周囲に、該翼本体の翼形状を決定する層を形成
することを特徴とする圧縮機翼の製造方法。A wing body forming material obtained by laminating and integrating a prepreg material to form a wing body having dimensions smaller than a desired wing shape and approximate to the wing shape, and then inserting the wing body into a mold, It is preferable that a thermoplastic resin is press-fitted into a gap formed between the wing body and the mold, compression-molded in a filled state, and a layer that determines the wing shape of the wing body is formed around the wing body. A method for manufacturing a compressor blade .
テルケトンを含むことを特徴とする請求項１に記載の圧
縮機翼の製造方法。Wherein said thermoplastic resin pressure according to claim 1, characterized in that it comprises a polyether ether ketone
Manufacturing method for compressor wings .
れ、所望の翼形状より小寸法でかつ該翼形状に近似する
翼本体と、該翼本体の周囲に配設され、翼形状を決定す
る熱可塑性樹脂の層とを有することを特徴とする圧縮機
翼。3. A wing body which is formed by laminating and integrating prepreg materials, is smaller in size than a desired wing shape, and approximates the wing shape, and a heat source disposed around the wing body to determine the wing shape. compressor, characterized in that it comprises a layer of thermoplastic resin
Wings .
１．０ｍｍ程度であることを特徴とする請求項３に記載
の圧縮機翼。4. The thermoplastic resin layer has a thickness of 0.1 to 0.1.
The compressor blade according to claim 3, wherein the diameter is about 1.0 mm.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| JP8114792A JP3345909B2 (en) | 1992-04-02 | 1992-04-02 | Method of manufacturing compressor blade and compressor blade |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| JP8114792A JP3345909B2 (en) | 1992-04-02 | 1992-04-02 | Method of manufacturing compressor blade and compressor blade |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| JPH05278063A JPH05278063A (en) | 1993-10-26 |
| JP3345909B2 true JP3345909B2 (en) | 2002-11-18 |
Family
ID=13738320
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| JP8114792A Expired - Fee Related JP3345909B2 (en) | 1992-04-02 | 1992-04-02 | Method of manufacturing compressor blade and compressor blade |
Country Status (1)
| Country | Link |
|---|---|
| JP (1) | JP3345909B2 (en) |
Families Citing this family (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JP4060981B2 (en) | 1998-04-08 | 2008-03-12 | 本田技研工業株式会社 | Gas turbine stationary blade structure and unit thereof |
| US6821087B2 (en) | 2002-01-21 | 2004-11-23 | Honda Giken Kogyo Kabushiki Kaisha | Flow-rectifying member and its unit and method for producing flow-rectifying member |
| FR2925106B1 (en) * | 2007-12-14 | 2010-01-22 | Snecma | METHOD FOR DESIGNING A TURBOMACHINE MULTI-STAGE TURBINE |
-
1992
- 1992-04-02 JP JP8114792A patent/JP3345909B2/en not_active Expired - Fee Related
Also Published As
| Publication number | Publication date |
|---|---|
| JPH05278063A (en) | 1993-10-26 |
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