JP2001041002A - Composite wings - Google Patents
Composite wingsInfo
- Publication number
- JP2001041002A JP2001041002A JP11211522A JP21152299A JP2001041002A JP 2001041002 A JP2001041002 A JP 2001041002A JP 11211522 A JP11211522 A JP 11211522A JP 21152299 A JP21152299 A JP 21152299A JP 2001041002 A JP2001041002 A JP 2001041002A
- Authority
- JP
- Japan
- Prior art keywords
- metal
- erosion
- composite material
- wing
- composite
- 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
- 239000002131 composite material Substances 0.000 title claims abstract description 82
- 229910052751 metal Inorganic materials 0.000 claims abstract description 98
- 239000002184 metal Substances 0.000 claims abstract description 98
- 230000003628 erosive effect Effects 0.000 claims abstract description 63
- 239000000853 adhesive Substances 0.000 claims description 27
- 230000001070 adhesive effect Effects 0.000 claims description 27
- 230000002265 prevention Effects 0.000 claims description 16
- 239000000463 material Substances 0.000 claims description 9
- 238000005299 abrasion Methods 0.000 abstract description 5
- 229920000049 Carbon (fiber) Polymers 0.000 description 5
- 239000004917 carbon fiber Substances 0.000 description 5
- VNWKTOKETHGBQD-UHFFFAOYSA-N methane Chemical compound C VNWKTOKETHGBQD-UHFFFAOYSA-N 0.000 description 5
- 239000004593 Epoxy Substances 0.000 description 3
- 230000008602 contraction Effects 0.000 description 3
- 229910001220 stainless steel Inorganic materials 0.000 description 3
- 239000010935 stainless steel Substances 0.000 description 3
- 229910001200 Ferrotitanium Inorganic materials 0.000 description 1
- RTAQQCXQSZGOHL-UHFFFAOYSA-N Titanium Chemical compound [Ti] RTAQQCXQSZGOHL-UHFFFAOYSA-N 0.000 description 1
- 230000002411 adverse Effects 0.000 description 1
- XAGFODPZIPBFFR-UHFFFAOYSA-N aluminium Chemical compound [Al] XAGFODPZIPBFFR-UHFFFAOYSA-N 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 230000005611 electricity Effects 0.000 description 1
- 229920006332 epoxy adhesive Polymers 0.000 description 1
- 239000000446 fuel Substances 0.000 description 1
- 239000011491 glass wool Substances 0.000 description 1
- 238000005461 lubrication Methods 0.000 description 1
- 238000004519 manufacturing process Methods 0.000 description 1
- 239000007769 metal material Substances 0.000 description 1
- 150000002739 metals Chemical class 0.000 description 1
- 238000000465 moulding Methods 0.000 description 1
- -1 polyethylene terephthalate Polymers 0.000 description 1
- 229920000139 polyethylene terephthalate Polymers 0.000 description 1
- 239000005020 polyethylene terephthalate Substances 0.000 description 1
- 229920001296 polysiloxane Polymers 0.000 description 1
- 229920002635 polyurethane Polymers 0.000 description 1
- 239000004814 polyurethane Substances 0.000 description 1
- 229920000915 polyvinyl chloride Polymers 0.000 description 1
- 239000004800 polyvinyl chloride Substances 0.000 description 1
- 230000003068 static effect Effects 0.000 description 1
- 229920001187 thermosetting polymer Polymers 0.000 description 1
- 239000010936 titanium Substances 0.000 description 1
Landscapes
- Turbine Rotor Nozzle Sealing (AREA)
Abstract
(57)【要約】
【課題】 複合材翼からエロージョン防止用金属が剥離
しずらく、また剥離しても新たなエロージョン防止用金
属に容易に交換修理することができる。
【解決手段】 複合材料から成る複合材翼（７）と、複
合材翼（７）のリーディングエッジ部（７ａ）に一体成
形し、かつ横断面が略Ｕ字形状の金属取付板（１２）
と、金属取付板（１２）に嵌まり合うように横断面が略
Ｕ字形状に形成した、磨耗を防止するためのエロージョ
ン防止用金属（１０）と、エロージョン防止用金属（１
０）を前記金属取付板（１２）に接着する接着剤（１
１）と、から成るものである。
(57) [Summary] [Problem] An erosion preventing metal is hard to peel off from a composite material wing, and even if peeled, it can be easily replaced and repaired with a new erosion preventing metal. SOLUTION: A composite material wing (7) made of a composite material, and a metal mounting plate (12) integrally formed on a leading edge portion (7a) of the composite material wing (7) and having a substantially U-shaped cross section.
And an erosion preventing metal (10) for preventing abrasion, the erosion preventing metal (10) having a substantially U-shaped cross section so as to fit into the metal mounting plate (12).
0) to the metal mounting plate (12).
1).
Description
【０００１】[0001]
【発明の属する技術の分野】本発明は、ターボファンエ
ンジンのファン等の静翼又はヘリコプター等の回転翼に
係り、特に複合材料から成る複合材翼に関するものであ
る。BACKGROUND OF THE INVENTION 1. Field of the Invention The present invention relates to a stationary blade such as a fan of a turbofan engine or a rotary blade such as a helicopter, and more particularly to a composite blade made of a composite material.
【０００２】[0002]
【従来の技術】ターボファンエンジンは、図３に示すよ
うに、その基本的な構成要素として、圧縮機１、燃焼器
２、タービン３及び運転上に必要な燃料制御装置、潤
滑、電気、空気、油圧系統の補機及び空気取入口４、ジ
ェットノズル５から成るものである。この中心部となる
圧縮機１、燃焼器２及びこの圧縮機１を駆動するタービ
ン３から構成された部分を通常コアエンジンといい、こ
のコアエンジンの前に空気取入口４とファン６とから成
る。ファン６は多数枚の静翼７と回転軸８の円周状に固
設された動翼９とから成るものである。これらの静翼７
及び動翼９は、従来はアルミニウム製の金属製のものが
主であった。これらの静翼７又は動翼９は、通常１００
℃程度に温められるだけであるため、エンジンの軽量化
と耐衝撃性という要請から、金属製のものに代えてＦＲ
Ｐ材料（炭素繊維型複合材料等）から成る複合材料で製
造したものがある。2. Description of the Related Art As shown in FIG. 3, a turbo fan engine has a compressor 1, a combustor 2, a turbine 3 and fuel control devices necessary for operation, lubrication, electricity, air as basic components. , Hydraulic system accessories, an air intake 4, and a jet nozzle 5. The central part consisting of the compressor 1, the combustor 2 and the turbine 3 for driving the compressor 1 is usually called a core engine, and is composed of an air intake 4 and a fan 6 before the core engine. . The fan 6 is composed of a number of stationary blades 7 and a moving blade 9 fixed around the rotating shaft 8. These stationary blades 7
Conventionally, the rotor blade 9 is mainly made of aluminum metal. These stationary blades 7 or moving blades 9 usually have 100
Because of the need to reduce the weight and impact resistance of the engine because it can only be heated to about
Some are manufactured from a composite material composed of a P material (such as a carbon fiber type composite material).
【０００３】しかし、このような複合材料から成る静翼
７又は動翼９は、金属製の静翼又は動翼に比較して耐磨
耗性が劣るため、空気取入口４側のリーディングエッジ
部（前縁先端部）７ａが飛行中に磨耗しやすかった。そ
こで、このような複合材料の静翼７には、図４に示すよ
うに、その磨耗を防止するために、リーディングエッジ
部７ａにエロージョン防止用金属１０を接合していた。However, the stationary blade 7 or the moving blade 9 made of such a composite material is inferior in abrasion resistance as compared with the metal stationary blade or the moving blade. (Front edge tip) 7a was easily worn during flight. Therefore, as shown in FIG. 4, an erosion preventing metal 10 is joined to the leading edge portion 7a of the stator vane 7 made of such a composite material, as shown in FIG.
【０００４】また、ヘリコプターにおけるメイン・ロー
タ・ブレード及びテイル・ロータ等の複合材料から成る
回転翼にも、上述したターボファンエンジンと同様にそ
の磨耗を防止するために、その回転方向となるリーディ
ングエッジ部にエロージョン防止用金属を接合してい
た。[0004] Similarly to the above-mentioned turbofan engine, the leading edge of the rotating blade made of a composite material such as a main rotor blade and a tail rotor in a helicopter is rotated in the rotating direction in order to prevent its wear. The metal for erosion prevention was joined to the part.
【０００５】[0005]
【発明が解決しようとする課題】しかし、これらの炭素
繊維型複合材料の静翼７等に対してエロージョン防止用
金属１０を、例えばエポキシ系のフィルム接着剤で接合
しても、炭素繊維型複合材料と金属材料という異質材料
であるため、そのジェットエンジンの使用中、又はヘリ
コプターの回転翼の回転中にエロージョン防止用金属１
０が剥離しやすかった。更に、このように剥離したエロ
ージョン防止用金属１０はその交換修理が大変煩雑であ
るという問題があった。However, even if the metal 10 for preventing erosion is bonded to the stationary blade 7 or the like of the carbon fiber type composite material with, for example, an epoxy film adhesive, the carbon fiber type composite Erosion prevention metal 1 during the use of the jet engine or the rotation of the helicopter rotor blades.
0 was easy to peel off. Further, there is a problem that the replacement of the erosion preventing metal 10 thus separated is very complicated.
【０００６】また、エロージョン防止用金属１０を接着
した複合材料の静翼７は、外気温度から１００℃前後に
温度上昇するため、非常に硬く固化するエポキシ系の熱
硬化性のフィルム接着剤では、炭素繊維型複合材料の静
翼７とエロージョン防止用金属１０との熱膨張差を吸収
することができず、この接着剤部分で剥離しやすいとい
う問題を有していた。Further, since the temperature of the stationary vane 7 of the composite material to which the metal 10 for preventing erosion is adhered rises from the outside air temperature to about 100 ° C., an epoxy-based thermosetting film adhesive which hardens and solidifies is: There was a problem that the difference in thermal expansion between the stationary blade 7 of the carbon fiber type composite material and the metal 10 for preventing erosion could not be absorbed, and the adhesive portion easily peeled off.
【０００７】本発明は、かかる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、エ
ロージョン防止用金属が剥離しずらく、また剥離しても
新たなエロージョン防止用金属に容易に交換修理するこ
とができる複合材翼を提供することにある。The present invention has been made to solve such a problem. That is, an object of the present invention is to provide a composite wing in which the erosion preventing metal is hard to peel off and can be easily replaced and repaired with a new erosion preventing metal even after peeling.
【０００８】[0008]
【課題を解決するための手段】本発明によれば、複合材
料から成る複合材翼（７）と、該複合材翼（７）のリー
ディングエッジ部（７ａ）に一体成形し、かつ横断面が
略Ｕ字形状の金属取付板（１２）と、該金属取付板（１
２）に嵌まり合うように横断面が略Ｕ字形状に形成し
た、磨耗を防止するためのエロージョン防止用金属（１
０）と、該エロージョン防止用金属（１０）を前記金属
取付板（１２）に接着する接着剤（１１）と、から成る
ことを特徴とする複合材翼が提供される。According to the present invention, a composite wing (7) made of a composite material and a leading edge (7a) of the composite wing (7) are integrally formed and have a cross section. A substantially U-shaped metal mounting plate (12) and the metal mounting plate (1)
The erosion-preventing metal (1), which has a substantially U-shaped cross section so as to fit into 2), and prevents wear.
0), and an adhesive (11) for bonding the erosion preventing metal (10) to the metal mounting plate (12).
【０００９】上記発明の構成によれば、エロージョン防
止用金属（１０）を複合材翼（７）の金属取付板（１
２）を介して接着剤（１１）で接合した接着部分が金属
同士であるため、従来の複合材翼（７）の複合材料に直
接金属材を接着した異質材の接着力に比較してその接着
力が強い。また、複合材翼（７）の熱履歴における熱膨
張又は熱収縮による変化があっても、接着部分が金属同
士であるため、複合材翼（７）からエロージョン防止用
金属（１０）が剥離しづらい。なお、エロージョン防止
用金属（１０）が複合材翼（７）から剥離しても、その
内部の金属取付板（１２）が複合材翼（７）を保護する
作用もあるため、複合材翼（７）が直接露出せず、耐磨
耗性が一時的でも低下することがない。According to the structure of the invention, the metal (10) for preventing erosion is attached to the metal mounting plate (1) of the composite wing (7).
Since the bonding portion bonded with the adhesive (11) through 2) is made of metal, compared with the bonding force of a foreign material obtained by directly bonding a metal material to the composite material of the conventional composite wing (7), Strong adhesion. Even if there is a change due to thermal expansion or thermal contraction in the thermal history of the composite wing (7), the erosion preventing metal (10) is peeled off from the composite wing (7) because the bonded portion is made of metal. It is hard. In addition, even if the metal (10) for preventing erosion peels off from the composite wing (7), the metal mounting plate (12) inside also has the function of protecting the composite wing (7). 7) is not directly exposed, and the abrasion resistance is not reduced even temporarily.
【００１０】また、本発明によれば、前記金属取付板
（１２）が、前記エロージョン防止用金属（１０）と同
材質であることを特徴とする複合材翼が提供される。Further, according to the present invention, there is provided a composite wing, wherein the metal mounting plate (12) is made of the same material as the erosion preventing metal (10).
【００１１】この構成により、接着部分が同材質の金属
同士であるため、その接着力が強固になる。一方、複合
材翼（７）からエロージョン防止用金属（１０）の一部
が剥離したときは、飛行機やヘリコプターのオーバーホ
ール前でも強制的にそのエロージョン防止用金属（１
０）を剥がし取って、新たなエロージョン防止用金属
（１０）に付け替えることができる。このときにエロー
ジョン防止用金属（１０）と複合材翼（７）とが直接接
着していないため、従来のように複合材翼（７）のリー
ディングエッジ部（７ａ）を剥がす際に、その表面がざ
らつくことがないので、新たなエロージョン防止用金属
（１０）を接着してもその密着性が低下することはな
い。[0011] With this configuration, since the bonding portion is made of the same metal, the bonding strength is increased. On the other hand, when a part of the erosion preventing metal (10) has separated from the composite wing (7), the erosion preventing metal (1) is forcibly forced even before the overhaul of an airplane or a helicopter.
0) can be peeled off and replaced with a new erosion preventing metal (10). At this time, since the erosion prevention metal (10) and the composite material wing (7) are not directly adhered to each other, when the leading edge portion (7a) of the composite material wing (7) is peeled off as in the related art, the surface thereof is not removed. Since there is no roughness, even if a new metal for erosion prevention (10) is bonded, its adhesion does not decrease.
【００１２】更に、本発明によれば、複合材料から成る
複合材翼（７）と、該複合材翼（７）のリーディングエ
ッジ部（７ａ）に嵌まり合うように横断面が略Ｕ字形状
に形成した、磨耗を防止するためのエロージョン防止用
金属（１０）と、該エロージョン防止用金属（１０）を
前記リーディングエッジ部（７ａ）に接着する弾性接着
剤（１１）と、から成ることを特徴とする複合材翼が提
供される。Further, according to the present invention, a composite material wing (7) made of a composite material and a substantially U-shaped cross section is fitted to the leading edge (7a) of the composite material wing (7). An erosion preventing metal (10) for preventing abrasion and an elastic adhesive (11) for adhering the erosion preventing metal (10) to the leading edge portion (7a). A composite wing is provided.
【００１３】この複合材翼（７）にエロージョン防止用
金属（１０）を接着する弾性接着剤は、ある温度範囲で
低い弾性率を保ち、剥離強さはエポキシ系の接着剤より
やや劣る程度であるため、温度履歴による熱膨張差を吸
収することができる。そこで、この弾性接着剤の接着部
分でエロージョン防止用金属（１０）が複合材翼（７）
のリーディングエッジ部（７ａ）から剥離することを防
止する。The elastic adhesive for bonding the erosion preventing metal (10) to the composite wing (7) has a low elastic modulus in a certain temperature range, and has a peel strength slightly lower than that of the epoxy adhesive. Therefore, the difference in thermal expansion due to the temperature history can be absorbed. Therefore, the metal (10) for preventing erosion is applied to the composite wing (7) at the bonding portion of the elastic adhesive.
From the leading edge (7a).
【００１４】[0014]
【発明の実施の形態】以下、本発明の好ましい実施の形
態を図面を参照して説明する。なお、各図において共通
の部材には同一の符号を付し重複した説明を省略する。
図１及び図２は本発明の複合材翼の発明の実施の形態を
示すものである。この図において、複合材翼とは、ター
ボファンエンジンのファン６を構成する静翼７と動翼９
の総称をいい、例えば静翼（複合材翼）７は炭素繊維型
複合材料から成る。この複合材翼７は物の衝突等による
磨耗を防止するために、そのリーディングエッジ部７ａ
にチタン製又はステンレス製の横断面が略Ｕ字形状に成
るエロージョン防止用金属１０を接合してある。しか
し、本発明ではこのエロージョン防止用金属１０を複合
材翼７のリーディングエッジ部７ａに直接接着したので
はなく、このリーディングエッジ部７ａに先ず横断面が
略Ｕ字形状の金属取付板１２を一体成形し、この金属取
付板１２を介してエロージョン防止用金属１０を接着剤
１１で接着したことに構造的な特徴を有する（図２の断
面図を参照）。この金属取付板１２は、複合材翼７の製
造の際に金型による一体成形等でリーディングエッジ部
７ａに埋め込み、従来の複合材翼７に接着剤で接着した
エロージョン防止用金属１０の接合力と比較して強固で
ある。DETAILED DESCRIPTION OF THE PREFERRED EMBODIMENTS Preferred embodiments of the present invention will be described below with reference to the drawings. In the drawings, common members are denoted by the same reference numerals, and duplicate description is omitted.
FIG. 1 and FIG. 2 show an embodiment of the invention of the composite blade of the present invention. In this figure, a composite blade is a stationary blade 7 and a moving blade 9 that constitute a fan 6 of a turbofan engine.
For example, the stationary blade (composite material blade) 7 is made of a carbon fiber type composite material. The composite material wing 7 has a leading edge portion 7a for preventing abrasion due to collision of an object.
And an erosion prevention metal 10 made of titanium or stainless steel and having a substantially U-shaped cross section. However, in the present invention, the metal 10 for preventing erosion is not directly bonded to the leading edge portion 7a of the composite wing 7, but a metal mounting plate 12 having a substantially U-shaped cross section is integrated with the leading edge portion 7a. It has a structural feature in that it is formed and bonded to the erosion preventing metal 10 with an adhesive 11 via the metal mounting plate 12 (see the sectional view of FIG. 2). The metal mounting plate 12 is embedded in the leading edge portion 7a by integral molding with a mold or the like at the time of manufacturing the composite material wing 7, and the bonding force of the erosion preventing metal 10 bonded to the conventional composite material wing 7 with an adhesive. Stronger than.
【００１５】この複合材翼７に一体成形した金属取付板
１２に、接着剤１１で横断面が略Ｕ字形状のエロージョ
ン防止用金属１０を接合してある。このように金属同士
の接着は、複合材翼７の複合材料とエロージョン防止用
金属１０の金属という異質材同士の接着力に比較してそ
の接着力が強い。従来のように複合材翼７にエロージョ
ン防止用金属１０を接着剤１１で直接接着したものと比
較して剥離しずらい。これは複合材翼７の熱履歴におけ
る熱膨張又は熱収縮による熱変化の影響を受けても、そ
の接着部分が金属同士であるため熱膨張差を吸収するこ
とができるためである。特に、ステンレス製のエロージ
ョン防止用金属１０と同材質のステンレス製の金属取付
板１２を複合材翼７に接着したものは、その接着力がよ
り強固である。An erosion preventing metal 10 having a substantially U-shaped cross section is joined to a metal mounting plate 12 integrally formed with the composite material wing 7 by an adhesive 11. As described above, the bonding strength between metals is stronger than the bonding strength between different materials such as the composite material of the composite material blade 7 and the metal of the erosion prevention metal 10. The erosion preventing metal 10 is harder to be peeled off compared to the conventional one in which the erosion preventing metal 10 is directly adhered to the composite material wing 7 with the adhesive 11. This is because even if the composite material blade 7 is affected by a thermal change due to thermal expansion or thermal contraction in the thermal history, the difference in thermal expansion can be absorbed because the bonded portion is made of metal. In particular, when the stainless steel metal attachment plate 12 made of the same material as the stainless steel erosion prevention metal 10 is bonded to the composite wing 7, the bonding strength is stronger.
【００１６】複合材翼７からエロージョン防止用金属１
０が剥離したとしても、その内側の金属取付板１２が複
合材翼７を保護しているため、この複合材翼７が露出し
ないようになっている。また、使用中に複合材翼７のリ
ーディングエッジ部７ａからエロージョン防止用金属１
０の一部が剥離したきは、飛行機のオーバーホール前で
も強制的にそのエロージョン防止用金属１０を剥がし取
って、新たなエロージョン防止用金属１０に付け替える
ことができる。このときに、エロージョン防止用金属１
０に複合材翼７を直接接着していないため、従来のよう
に複合材翼７からエロージョン防止用金属１０を剥した
後、リーディングエッジ部７ａの表面がざらつくことが
ないので、新たなエロージョン防止用金属１０の接着に
悪い影響を与えることはない。The metal 1 for preventing erosion from the composite wing 7
Even if 0 is peeled off, since the metal mounting plate 12 inside protects the composite wing 7, the composite wing 7 is not exposed. During use, the erosion preventing metal 1 is removed from the leading edge portion 7a of the composite material blade 7.
When a part of 0 is peeled off, the erosion preventing metal 10 can be forcibly peeled off even before the overhaul of the airplane and replaced with a new erosion preventing metal 10. At this time, the erosion preventing metal 1
Since the composite wing 7 is not directly bonded to the composite wing 7, the surface of the leading edge portion 7a does not become rough after the erosion preventing metal 10 is peeled off from the composite wing 7 as in the related art, so that new erosion prevention is performed. It does not adversely affect the adhesion of the metal 10 for use.
【００１７】次に、本発明の他の実施の形態を説明す
る。この実施の形態は、金属取付板１２に代えて簡易に
エロージョン防止用金属１０の接着力を強めるため、複
合材翼７のリーディングエッジ部７ａに、エロージョン
防止用金属１０を所謂弾性接着剤で接着するようになっ
ている。ここで弾性接着剤とは、ポリウレタンやシリコ
ーン等のゴム様の性質を有する接着剤をいい、例えば軟
質のポリ塩化ビニル系接着剤やポリエチレンテレフタレ
ート接着剤等の熱膨張率の異なる材質間においても接着
力が低下しない性質を有するものである。この弾性接着
剤は、ある温度範囲で低い弾性率を保ち、剥離強さはエ
ポキシ系の接着剤よりやや劣るが、温度履歴による熱膨
張差を吸収することができるため、この弾性接着剤の接
着部分でエロージョン防止用金属１０が複合材翼７のリ
ーディングエッジ部７ａから剥離することを防止するこ
とができる。Next, another embodiment of the present invention will be described. In this embodiment, the erosion preventing metal 10 is bonded to the leading edge portion 7a of the composite wing 7 with a so-called elastic adhesive in order to easily strengthen the adhesive force of the erosion preventing metal 10 instead of the metal mounting plate 12. It is supposed to. Here, the elastic adhesive refers to an adhesive having a rubber-like property such as polyurethane or silicone, and is used for bonding between materials having different coefficients of thermal expansion such as a soft polyvinyl chloride adhesive or a polyethylene terephthalate adhesive. It has the property that the force does not decrease. This elastic adhesive maintains a low elastic modulus in a certain temperature range, and has a slightly lower peel strength than an epoxy-based adhesive, but can absorb a difference in thermal expansion due to a temperature history. It is possible to prevent the erosion preventing metal 10 from being separated from the leading edge portion 7a of the composite material blade 7 at a portion.
【００１８】なお、本発明のエロージョン防止用金属１
０を接合した複合材翼７は、ターボファンエンジンのフ
ァン６を構成する静翼７の他に、ヘリコプターにおける
メイン・ロータ・ブレイド又はテイル・ロータ等の複合
材料から成る回転翼にも実施することができる。The erosion preventing metal 1 of the present invention
In addition to the stationary blades 7 constituting the fan 6 of the turbofan engine, the composite blades 7 joined to each other may be applied to a rotor blade made of a composite material such as a main rotor blade or a tail rotor in a helicopter. Can be.
【００１９】更に、本発明は上記実施の形態にのみ限定
されるものではなく、複合材料から成る翼であれば、上
述したような構成、材質に限定されずに、グラスウール
の複合材料等の他のＦＲＰ材料を採用でき、そのため本
発明の要旨を逸脱しない範囲内において種々変更を加え
得ることは勿論である。また、複合材翼を構成する対象
もターボファンエンジン等の静翼、又はヘリコプターの
メイン・ロータ・ブレードやテイル・ロータ等の回転翼
に限定されない。Further, the present invention is not limited to the above-described embodiment, but is not limited to the above-described configuration and material, but may be any other material such as a glass wool composite material. It is needless to say that various changes can be made without departing from the gist of the present invention. Further, the object constituting the composite material blade is not limited to a stationary blade such as a turbofan engine or a rotating blade such as a main rotor blade or a tail rotor of a helicopter.
【００２０】[0020]
【発明の効果】上述したように、本発明の複合材翼は、
エロージョン防止用金属を複合材翼に強固に一体成形し
た金属取付板を介して接着剤で取り付けてあるため、エ
ロージョン防止用金属を複合材翼に直接接着したものと
比較して、その接着力が強い。また、接着部分が金属同
士であるため、複合材翼の熱履歴における熱膨張又は熱
収縮による熱変化を吸収することができるので、エロー
ジョン防止用金属が複合材翼のリーディングエッジ部か
ら剥離しづらい。As described above, the composite wing of the present invention has the following features.
Since the erosion prevention metal is attached to the composite wing with an adhesive through a metal mounting plate that is firmly molded, the adhesive strength is lower than that of the erosion prevention metal directly bonded to the composite wing. strong. Further, since the bonded portion is made of metal, it is possible to absorb a thermal change due to thermal expansion or thermal contraction in the thermal history of the composite blade, so that the erosion preventing metal is less likely to peel from the leading edge portion of the composite blade. .
【００２１】特に、複合材翼からエロージョン防止用金
属の一部が剥離したときは、飛行機やヘリコプターのオ
ーバーホール前でも強制的にそのエロージョン防止用金
属を剥がし取って、新たなエロージョン防止用金属に付
け替えることができる。このときに、エロージョン防止
用金属と複合材翼とが直接接着していないため、従来の
ようにエロージョン防止用金属を剥がした後に、その表
面がざらつくことがないので、新たに接着したエロージ
ョン防止用金属の密着性が低下することはない。In particular, when a part of the metal for preventing erosion has separated from the composite wing, the metal for preventing erosion is forcibly peeled off even before the overhaul of an airplane or a helicopter and replaced with a new metal for preventing erosion. be able to. At this time, since the metal for erosion prevention and the composite material wing are not directly adhered to each other, the surface of the metal does not become rough after the metal for erosion prevention is peeled off as in the conventional case. There is no decrease in metal adhesion.
【００２２】更に、金属取付板に代えた簡易な接合手段
となる弾性接着剤は、温度履歴による熱膨張差を吸収す
ることができるため、この弾性接着剤の接着部分でもエ
ロージョン防止用金属が複合材翼から剥離することを防
止することができる、等の優れた効果がある。Furthermore, since the elastic adhesive, which is a simple joining means in place of the metal mounting plate, can absorb the difference in thermal expansion due to the temperature history, the metal for erosion prevention is also used at the bonded portion of the elastic adhesive. There are excellent effects such as being able to prevent peeling from the blade.
【図１】本発明の複合材翼の発明の実施の形態を示す斜
視図である。FIG. 1 is a perspective view showing an embodiment of the invention of a composite material blade of the present invention.
【図２】同じく部分拡大平断面図である。FIG. 2 is a partially enlarged plan sectional view of the same.
【図３】ターボファンエンジンを示す断面図である。FIG. 3 is a sectional view showing a turbofan engine.
【図４】従来のエロージョン防止用金属を接着した静翼
を示す斜視図である。FIG. 4 is a perspective view showing a conventional vane to which a metal for preventing erosion is adhered.
７ 静翼（複合材翼） ７ａ リーディングエッジ部 １０ エロージョン防止用金属 １１ 接着剤 １２ 金属取付板 7 Static Wing (Composite Wing) 7a Leading Edge 10 Metal for Erosion Prevention 11 Adhesive 12 Metal Mounting Plate
Claims (3)
体成形し、かつ横断面が略Ｕ字形状の金属取付板（１
２）と、 該金属取付板（１２）に嵌まり合うように横断面が略Ｕ
字形状に形成した、磨耗を防止するためのエロージョン
防止用金属（１０）と、 該エロージョン防止用金属（１０）を前記金属取付板
（１２）に接着する接着剤（１１）と、から成ることを
特徴とする複合材翼。1. A composite material wing (7) made of a composite material, and a metal mounting plate (1) formed integrally with a leading edge portion (7a) of the composite material wing (7) and having a substantially U-shaped cross section.
2) and the cross section is substantially U so as to fit into the metal mounting plate (12).
An erosion prevention metal (10) for preventing wear, formed in a character shape, and an adhesive (11) for bonding the erosion prevention metal (10) to the metal mounting plate (12). A composite wing.
ジョン防止用金属（１０）と同材質であることを特徴と
する請求項１の複合材翼。2. The composite wing of claim 1, wherein said metal mounting plate (12) is of the same material as said erosion preventing metal (10).
まり合うように横断面が略Ｕ字形状に形成した、磨耗を
防止するためのエロージョン防止用金属（１０）と、 該エロージョン防止用金属（１０）を前記リーディング
エッジ部（７ａ）に接着する弾性接着剤（１１）と、か
ら成ることを特徴とする複合材翼。3. A composite material wing (7) comprising a composite material, and a cross-section formed in a substantially U-shape so as to fit into a leading edge portion (7a) of the composite material wing (7). A composite wing comprising: a metal for preventing erosion (10) for preventing the metal; and an elastic adhesive (11) for bonding the metal for preventing erosion (10) to the leading edge (7a). .
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| JP21152299A JP4390026B2 (en) | 1999-07-27 | 1999-07-27 | Composite wing |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| JP21152299A JP4390026B2 (en) | 1999-07-27 | 1999-07-27 | Composite wing |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| JP2001041002A true JP2001041002A (en) | 2001-02-13 |
| JP4390026B2 JP4390026B2 (en) | 2009-12-24 |
Family
ID=16607304
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| JP21152299A Expired - Lifetime JP4390026B2 (en) | 1999-07-27 | 1999-07-27 | Composite wing |
Country Status (1)
| Country | Link |
|---|---|
| JP (1) | JP4390026B2 (en) |
Cited By (13)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JP2003056497A (en) * | 2001-08-10 | 2003-02-26 | Ishikawajima Harima Heavy Ind Co Ltd | Engine stationary vane |
| WO2011092019A1 (en) * | 2010-01-29 | 2011-08-04 | Lufthansa Technik Ag | Repair method for a composite component for an aircraft, composite component for an aircraft, and device for repairing a composite component for an aircraft |
| FR2970197A1 (en) * | 2011-01-11 | 2012-07-13 | Snecma | METHOD FOR DEOLIDARIZING / SOLIDARIZING BY INDUCING A MAGNETIC MECHANICAL PIECE FIXED WITH A MECHANICAL PART |
| JP2013213427A (en) * | 2012-04-02 | 2013-10-17 | Toshiba Corp | Hollow nozzle and manufacturing method thereof |
| WO2015025598A1 (en) | 2013-08-19 | 2015-02-26 | 株式会社Ihi | Composite vane |
| JP2015532695A (en) * | 2012-07-30 | 2015-11-12 | ゼネラル・エレクトリック・カンパニイ | Metal leading edge protective strip, corresponding airfoil and manufacturing method |
| RU2659258C1 (en) * | 2015-03-13 | 2018-06-29 | АйЭйчАй КОРПОРЕЙШН | Blade coating application device |
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| JP2003056497A (en) * | 2001-08-10 | 2003-02-26 | Ishikawajima Harima Heavy Ind Co Ltd | Engine stationary vane |
| WO2011092019A1 (en) * | 2010-01-29 | 2011-08-04 | Lufthansa Technik Ag | Repair method for a composite component for an aircraft, composite component for an aircraft, and device for repairing a composite component for an aircraft |
| FR2970197A1 (en) * | 2011-01-11 | 2012-07-13 | Snecma | METHOD FOR DEOLIDARIZING / SOLIDARIZING BY INDUCING A MAGNETIC MECHANICAL PIECE FIXED WITH A MECHANICAL PART |
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| US9885244B2 (en) | 2012-07-30 | 2018-02-06 | General Electric Company | Metal leading edge protective strips for airfoil components and method therefor |
| JP2015532695A (en) * | 2012-07-30 | 2015-11-12 | ゼネラル・エレクトリック・カンパニイ | Metal leading edge protective strip, corresponding airfoil and manufacturing method |
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| RU2659258C1 (en) * | 2015-03-13 | 2018-06-29 | АйЭйчАй КОРПОРЕЙШН | Blade coating application device |
| US10746045B2 (en) | 2018-10-16 | 2020-08-18 | General Electric Company | Frangible gas turbine engine airfoil including a retaining member |
| US10760428B2 (en) | 2018-10-16 | 2020-09-01 | General Electric Company | Frangible gas turbine engine airfoil |
| US10837286B2 (en) | 2018-10-16 | 2020-11-17 | General Electric Company | Frangible gas turbine engine airfoil with chord reduction |
| US11111815B2 (en) | 2018-10-16 | 2021-09-07 | General Electric Company | Frangible gas turbine engine airfoil with fusion cavities |
| US11149558B2 (en) | 2018-10-16 | 2021-10-19 | General Electric Company | Frangible gas turbine engine airfoil with layup change |
| US11434781B2 (en) | 2018-10-16 | 2022-09-06 | General Electric Company | Frangible gas turbine engine airfoil including an internal cavity |
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