JPH07300098A - Low noise type blade - Google Patents
Low noise type bladeInfo
- Publication number
- JPH07300098A JPH07300098A JP9426394A JP9426394A JPH07300098A JP H07300098 A JPH07300098 A JP H07300098A JP 9426394 A JP9426394 A JP 9426394A JP 9426394 A JP9426394 A JP 9426394A JP H07300098 A JPH07300098 A JP H07300098A
- Authority
- JP
- Japan
- Prior art keywords
- blade
- opening
- tip
- view
- helicopter
- 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.)
- Withdrawn
Links
Abstract
Description
【０００１】[0001]
【産業上の利用分野】本発明は、先行するヘリコプタの
ブレードから発生する翼端渦が、後方のブレードと干渉
（Blade Vortex Interaction、以下ＢＶＩという）する
ことによって生じる騒音を、低減できる低騒音型ブレー
ドに関する。BACKGROUND OF THE INVENTION 1. Field of the Invention The present invention is a low noise type which can reduce the noise generated by the blade vortex generated from the blade of the preceding helicopter interfering with the blade behind (Blade Vortex Interaction, hereinafter referred to as BVI). Regarding the blade.
【０００２】[0002]
【従来の技術】図１２に示すように、ヘリコプタ０１０
はその飛行条件により、あるブレード０１の翼端０５で
生じた翼端渦０６が、後方のブレード０４と干渉０７し
て、そのブレード０４に短時間の揚力変動が生じるとい
う、ＢＶＩ現象を起すことがある。なお、翼端渦０６を
生じるのは、ブレード０１ばかりでなく、ブレード０２
〜０４でも発生し、残りの何れのブレードとも干渉を引
起す可能性はあるが、説明を簡単にする都合上、翼端渦
０６はブレード０１からのみ発生し、この翼端渦０６は
ブレード０４のみと、干渉するとして説明する。この現
象は、特に着陸のための降下時にＢＶＩ騒音０８として
観測され、ヘリコプタ０１０の運行上の問題となってい
る。2. Description of the Related Art As shown in FIG. 12, a helicopter 010
Causes the BVI phenomenon that the tip vortex 06 generated at the tip 05 of a certain blade 01 interferes 07 with the rear blade 04 due to the flight condition, and a short time lift force variation occurs in the blade 04. There is. It is to be noted that not only the blade 01 but also the blade 02 generates the tip vortex 06.
˜04, it may cause interference with any of the remaining blades, but for convenience of explanation, the tip vortex 06 is generated only from the blade 01, and the tip vortex 06 is generated by the blade 04. Only, it will be described as interfering. This phenomenon is observed as BVI noise 08 especially when descending for landing, which is a problem in operation of the helicopter 010.
【０００３】このＢＶＩ騒音は次のようにして発生す
る。図１３（Ｂ）に示す平面な形状に翼端０５が形成さ
れた、普通のブレード０１が動き出すと、図１４（Ａ）
に示すように、ブレード０１の後面から見て翼端０５付
近での、ブレード０１上面０１１と下面０１２との間に
は、図１４（Ｂ）に示すような大きな圧力勾配Δｐ／Δ
ｘが生じる。そして、図１４（Ｃ）に示すように、この
大きな圧力勾配Δｐ／Δｘにより、急激にブレード０１
の下面０１２から、翼端０５を通って上面０１１へ回り
込もうとする空気の流れ０１３が生じ、その慣性によ
り、翼端渦０６が生じる。ブレード０１の翼端０５がさ
らに移動すると、図１２の矢印で示すように、この翼端
渦０６が空中に取り残され、あとからやってくるブレー
ド０４と干渉し、ＢＶＩ騒音が発生する。This BVI noise is generated as follows. When the ordinary blade 01 having the blade tip 05 formed in the plane shape shown in FIG. 13 (B) starts to move, FIG. 14 (A)
As shown in FIG. 14, between the upper surface 011 and the lower surface 012 of the blade 01 near the blade tip 05 when viewed from the rear surface of the blade 01, a large pressure gradient Δp / Δ as shown in FIG.
x occurs. Then, as shown in FIG. 14 (C), the large pressure gradient Δp / Δx causes the blade 01
A flow 013 of air that flows from the lower surface 012 of the above to the upper surface 011 through the blade tip 05 is generated, and due to its inertia, a blade tip vortex 06 is generated. When the blade tip 05 of the blade 01 moves further, as shown by the arrow in FIG. 12, this blade tip vortex 06 is left in the air and interferes with the blade 04 that comes later, and BVI noise is generated.
【０００４】そのレベルは翼端渦０６の循環Γ（または
渦度）の強さに比例する。したがって、このＢＶＩ騒音
のレベルを下げるには、図１５に示すように、翼端０５
付近でのブレードの上面０１１と下面０１２との間の圧
力勾配Δｐ／Δｘを小さくすることにより、翼端渦０６
の循環Γの強さを小さくすればよい。The level is proportional to the strength of the circulation Γ (or vorticity) of the tip vortex 06. Therefore, in order to reduce the level of this BVI noise, as shown in FIG.
By reducing the pressure gradient Δp / Δx between the upper surface 011 and the lower surface 012 of the blade in the vicinity, the tip vortex 06
It is sufficient to reduce the strength of the circulation Γ of.
【０００５】図１３（Ａ）は、このような翼端渦０６を
弱めることにより、ＢＶＩ騒音の低減しようとする発想
で使用されている、従来のブレード０１′の翼端形状を
示す図である。すなわち、図の矢印で示す方向に回動す
るブレード０１′の、翼端０５部の後縁側を削除するこ
とにより、図１５に示すように、ブレード０１′の上面
と下面との間に生じる圧力勾配Δｐ／Δｘを小さくし、
翼端渦の循環の強さを小さくして、ＢＶＩ騒音を低減す
ることは出来る。FIG. 13 (A) is a diagram showing a blade tip shape of a conventional blade 01 'which is used in the idea of reducing BVI noise by weakening such a blade tip vortex 06. . That is, by removing the trailing edge side of the blade tip 05 portion of the blade 01 'that rotates in the direction shown by the arrow in the figure, the pressure generated between the upper surface and the lower surface of the blade 01' as shown in FIG. Decrease the gradient Δp / Δx,
BVI noise can be reduced by reducing the strength of the circulation of the tip vortices.
【０００６】しかし、このように、ブレードの翼端形状
を変形することにより、翼端渦を弱めて、ＢＶＩ騒音を
低減するという、従来のやり方は、あまり良い効果を発
揮していない。すなわち、ブレード０１の翼端０５形状
は、ブレードの空力性能を決める上で、重要なものであ
り、ＢＶＩ騒音低減のために翼端０５形状を変形する
と、これに伴い、ブレード０１の空力性能を劣化させる
ことに連るからである。翼端形状を変形することによっ
て、ＢＶＩ騒音を低減できても、ＢＶＩ現象の起こらな
い飛行条件下においては、このブレード０１を装着した
ヘリコプタは、普通のヘリコプタに比べ、大きなエンジ
ン出力を必要とすることとなり、ヘリコプタの性能を悪
くするという結果をもたらすからである。However, the conventional method of reducing the BVI noise by weakening the blade tip vortex by deforming the blade tip shape in this way does not exhibit a very good effect. That is, the blade tip 05 shape of the blade 01 is important in determining the aerodynamic performance of the blade, and when the blade tip 05 shape is deformed to reduce BVI noise, the aerodynamic performance of the blade 01 is reduced accordingly. This is because it leads to deterioration. Even if the BVI noise can be reduced by deforming the wing tip shape, the helicopter equipped with this blade 01 requires a larger engine output than a normal helicopter under the flight condition in which the BVI phenomenon does not occur. This is because the result is that the performance of the helicopter is deteriorated.
【０００７】[0007]
【発明が解決しようとする課題】本発明は、ヘリコプタ
がＢＶＩ騒音を発生する飛行条件下にあり、ＢＶＩ騒音
を低減する必要のある際のみに、翼端渦を発生するブレ
ードの翼端付近の上面と下面との間に生じる圧力勾配を
小さくし、ＢＶＩ騒音レベルを低減するとともに、ＢＶ
Ｉ騒音の発生しない、通常の飛行条件下（水平飛行、上
昇、ホバリング時）、若しくはＢＶＩ騒音の低減より
も、空力性能を良好に保つ必要のある飛行条件下の際に
は、空力性能を下げることなく、ヘリコプタの飛行を行
えるようにした低騒音型ブレードを提供することを課題
とする。DISCLOSURE OF THE INVENTION The present invention is directed to a helicopter under the flight conditions that generate BVI noise, and only when it is necessary to reduce the BVI noise, a blade tip vortex near a blade tip is generated. The BVI noise level is reduced by reducing the pressure gradient generated between the upper surface and the lower surface, and
Reduces aerodynamic performance under normal flight conditions (horizontal flight, climbing, hovering) that do not generate I noise, or under flight conditions that require better aerodynamic performance than BVI noise reduction It is an object of the present invention to provide a low noise type blade that enables a helicopter to fly without a problem.
【０００８】[0008]
【課題を解決するための手段】このため、本発明の低騒
音型ブレードは次の手段とした。ヘリコプタ用ブレード
において、回動するブレードの翼端部に、ブレードの上
面と下面とを連通する開口を設けるとともに、必要に応
じて、この開口を開放し、又は完全に閉鎖できる開閉装
置を設けた。Therefore, the low noise type blade of the present invention has the following means. In the blade for helicopter, the blade end of the rotating blade is provided with an opening that connects the upper surface and the lower surface of the blade, and if necessary, an opening / closing device that can open this opening or completely close it is provided. .
【０００９】[0009]
【作用】本発明の低騒音型ブレードは、上述の手段によ
り、ヘリコプタがＢＶＩ騒音を発生する飛行条件下にあ
り、さらに、ＢＶＩ騒音を低減する必要のある飛行時に
おいては、翼端渦を発生しているブレードの翼端部に設
けた、ブレードの上面と下面をつなぐ開口を開けること
により、この翼端渦の循環（もしくは渦度）を弱め、こ
れによりＢＶＩ騒音を低減する。また、ヘリコプタがＢ
ＶＩ騒音を発生しない通常の飛行条件下にある場合、若
しくはＢＶＩ騒音を発生する飛行条件下にあっても、Ｂ
ＶＩ騒音の低減よりも、ブレードの空力性能を良好に保
つ必要のある飛行時においては、開口を開閉装置により
閉鎖して、ブレードの空力性能を良好にすることができ
る。With the low noise type blade of the present invention, the above-mentioned means allows the helicopter to generate a wing tip vortex in a flight condition under which the BVI noise is generated, and when the BVI noise needs to be reduced during flight. By opening an opening provided at the blade tip portion of the blade that connects the upper surface and the lower surface of the blade, the circulation (or vorticity) of this blade tip vortex is weakened, thereby reducing BVI noise. Also, the helicopter is B
Under normal flight conditions without VI noise, or even under flight conditions with BVI noise, B
During flight, in which it is necessary to maintain good aerodynamic performance of the blade rather than reduction of VI noise, the opening and closing device can close the opening to improve the aerodynamic performance of the blade.
【００１０】[0010]
【実施例】以下、本発明の低騒音型ブレードの実施例を
図面により説明する。図１は、本発明の低騒音型ブレー
ドの第１実施例を示す平面図である。図示するように、
ブレード１の翼端部２に、ブレード１の上面１１と下面
１２とを連通する、円形、または楕円形の開口３，
３′，３″を複数個開けている。本実施例においては、
翼端部２付近の圧力勾配が翼端４に向けてスムーズに小
さくなるよう、各開口３，３′，３″の大きさを、翼端
４近傍になる程大きくして、そこを通る空気の流量を大
きくして、ブレード１の上面１１と下面１２の圧力差
が、翼端４に向けて除々に小さくなるように調整してい
る。Embodiments of the low noise type blade of the present invention will be described below with reference to the drawings. FIG. 1 is a plan view showing a first embodiment of a low noise type blade of the present invention. As shown,
A circular or elliptical opening 3, which connects the upper surface 11 and the lower surface 12 of the blade 1 to the tip 2 of the blade 1,
A plurality of 3'and 3 "are opened. In this embodiment,
In order for the pressure gradient near the blade tip 2 to decrease smoothly toward the blade tip 4, the size of each of the openings 3, 3 ', 3 "is increased toward the blade tip 4 and the air passing therethrough is increased. Is increased so that the pressure difference between the upper surface 11 and the lower surface 12 of the blade 1 gradually decreases toward the blade tip 4.
【００１１】図２は、第２実施例を示す平面図である。
第１実施例と同様に、翼端部２に円形または楕円形の開
口５を複数個開けているが、本実施例においては、開口
５の大きさは同一にして、開口４の内部に金属多孔質
材、又はセラミック多孔質材等の多孔質材６を入れ、多
孔質材６の空孔率により、ブレードの下面１２から上面
１１へ抜ける空気の流量を、翼端４に近づくつれ大きく
なるように調整している例である。翼端４近傍になる程
空孔率を大きくして、開口５を通る空気の流量を大きく
することにより、翼端４近傍になる程、ブレードの上面
１１と下面１２との圧力差が小さくなって、圧力勾配が
小さくなり、その結果、翼端渦の循環Γの強さを低減
し、ＢＶＩ騒音を低減できる。FIG. 2 is a plan view showing the second embodiment.
Similar to the first embodiment, a plurality of circular or elliptical openings 5 are formed in the blade tip portion 2. However, in this embodiment, the openings 5 have the same size and the inside of the openings 4 is made of metal. A porous material 6 such as a porous material or a ceramic porous material is inserted, and the porosity of the porous material 6 increases the flow rate of the air flowing from the lower surface 12 to the upper surface 11 of the blade as it approaches the blade tip 4. It is an example in which adjustment is performed as follows. By increasing the porosity toward the blade tip 4 and increasing the flow rate of the air passing through the opening 5, the pressure difference between the upper surface 11 and the lower surface 12 of the blade becomes smaller toward the blade tip 4. As a result, the pressure gradient becomes smaller, and as a result, the strength of the circulation Γ of the blade tip vortex can be reduced and BVI noise can be reduced.
【００１２】図３は、第３実施例を示す平面図である。
本実施例は一つの大きな開口７を翼端部２に開けた例で
ある。翼端部２付近の圧力勾配がスムーズになるよう、
開口７の幅は翼端４近傍になる程大きくして、そこを通
る空気の流量を上述と同様に調整している。FIG. 3 is a plan view showing a third embodiment.
This embodiment is an example in which one large opening 7 is opened in the blade tip 2. To make the pressure gradient near the blade tip 2 smooth,
The width of the opening 7 is increased toward the blade tip 4 and the flow rate of air passing therethrough is adjusted in the same manner as described above.
【００１３】また、図４は、第４実施例を示す平面図で
ある。第３実施例と同様に本実施例においても、翼端部
２に一つの大きな開口８を設けているが、本実施例の開
口８の幅は、ブレード１の幅方向に同じにしてあり、こ
の開口８の内部に第２実施例と同様の多孔質材６を入
れ、その空孔率により空気の流量を調整している。この
ようにして翼端２近傍になる程、空孔率を大きくして、
そこを通る空気の流量を調整し、翼端部２におけるブレ
ード１の上面１１、下面１２における圧力勾配を小さく
して、循環Γの強さを小さくして、ＢＶＩ騒音の低減を
図っている。FIG. 4 is a plan view showing the fourth embodiment. In this embodiment as well as in the third embodiment, one large opening 8 is provided in the blade tip portion 2, but the width of the opening 8 in this embodiment is the same in the width direction of the blade 1, The same porous material 6 as in the second embodiment is put inside the opening 8 and the flow rate of air is adjusted by the porosity. In this way, the porosity is increased toward the tip 2 and
The flow rate of the air passing therethrough is adjusted, the pressure gradient on the upper surface 11 and the lower surface 12 of the blade 1 at the blade tip 2 is made small, and the strength of the circulation Γ is made small to reduce the BVI noise.
【００１４】以上、ブレード１の翼端部２に設ける開口
の平面形に関する実施例を示したが、図５はこれらを立
体的に示した斜視図である。The embodiment relating to the planar shape of the opening provided in the blade tip portion 2 of the blade 1 has been described above, and FIG. 5 is a perspective view showing these three-dimensionally.
【００１５】次に、図６、図７は図５の矢視断面図を示
し、開口３の断面形状を示す。図６（Ａ）は図５の矢視
Ａ−Ａで示す、ブレード１の開口３部の横断面図、図６
（Ｂ）は図５の矢視Ｂ−Ｂで示す、ブレード１の開口３
部の縦断面図を示し、開口断面形の第１実施例を示す。
本実施例では、圧力の高いブレード１の下面１２から上
面１１への空気の流れの方向が、ブレード１に作用する
対気の流れと同じ方向になり、スムーズになるように、
横断面図において斜め後方上部に向けて開口３を開けて
いる。さらに、縦断面図においても、翼端４をまわり、
下面１２から上面１１へ流れる空気の流れと、同様の空
気の流れが発生するような断面形状にして、効率良く、
ブレード１の上面１１と下面１２の圧力勾配が小さくす
るようにしている。Next, FIGS. 6 and 7 show sectional views taken along the arrow in FIG. 5, showing the sectional shape of the opening 3. 6A is a cross-sectional view of the opening 3 portion of the blade 1, which is taken along the line AA in FIG.
(B) is an opening 3 of the blade 1 shown by the arrow BB in FIG.
The longitudinal cross-sectional view of a part is shown, and 1st Example of an opening cross-sectional shape is shown.
In the present embodiment, the direction of the air flow from the lower surface 12 to the upper surface 11 of the high pressure blade 1 is the same as the direction of the air flow acting on the blade 1, so that the air becomes smooth.
In the cross-sectional view, the opening 3 is opened obliquely toward the upper rear. Furthermore, also in the longitudinal sectional view, around the wing tip 4,
Efficiently with a cross-sectional shape that produces the same air flow as the air flow flowing from the lower surface 12 to the upper surface 11.
The pressure gradient between the upper surface 11 and the lower surface 12 of the blade 1 is made small.
【００１６】また、図７（Ａ）は図５の矢視Ａ−Ａで示
す、ブレード１の開口３部の横断面図、図７（Ｂ）は図
５の矢視Ｂ−Ｂで示す、ブレード１の開口３部の縦断面
図を示し、開口断面形の第２実施例を示す。本実施例の
横断面図、縦断面図における、ブレード１の下面１２か
ら上面１１へ連通する開口３の方向は、第１実施例と同
じあるが、本実施例のものは、開口３の出、入口の角に
円弧部１４が形成されており、ブレード１の下面１２か
ら上面１１へ流れる空気の流れがスムーズになり、かつ
通過する空気流による気柱共鳴や空力音が生じない利点
がある。Further, FIG. 7 (A) is a cross-sectional view of the opening 3 of the blade 1 shown by the arrow AA in FIG. 5, and FIG. 7 (B) is shown by the arrow BB in FIG. The longitudinal cross-sectional view of the opening 3 part of the blade 1 is shown, and 2nd Example of an opening cross-sectional shape is shown. The direction of the opening 3 communicating from the lower surface 12 to the upper surface 11 of the blade 1 in the cross sectional view and the vertical sectional view of the present embodiment is the same as that of the first embodiment. Since the arc portion 14 is formed at the corner of the inlet, the flow of air flowing from the lower surface 12 to the upper surface 11 of the blade 1 is smooth, and air column resonance and aerodynamic noise due to the passing air flow are not generated. .
【００１７】次に、上述した開口を開閉するための開閉
装置について説明する。図８は、図６に示す開口３を開
閉するための開閉装置の第１実施例を示す横断面図であ
る。本実施例の開閉装置１５は、ブレード１の上面外皮
１６、および下面外皮１７の各内面で、ブレード１の翼
弦方向に摺動するとともに、開口３部で上面外皮１６、
および下面外皮１７の各外面と同一面をなして、開口３
を塞ぐシャッタ１８と、シャッタ１８を、上述のように
作動させる作動機構、およびサーボモータ等からなる駆
動装置とからなる。シャッタ１８は図９（Ａ）で示すよ
うに開口３を全閉することも、開口３の一部を開放して
開ける量を任意に調整することも、図９（Ｂ）に示すよ
うに開口３を全開することもできる。また、上面外皮１
６、および下面外皮１７部分に収納される、上、下のシ
ャッタ１８は収納時横（翼幅方向）に平行移動して、図
８、および図９（Ｂ）に示すように、ブレード１の上面
外皮１６、および下面外皮１７の内面側にしまい込まれ
る。Next, an opening / closing device for opening / closing the above-mentioned opening will be described. FIG. 8 is a transverse sectional view showing a first embodiment of an opening / closing device for opening / closing the opening 3 shown in FIG. The opening / closing device 15 of the present embodiment slides in the chord direction of the blade 1 on each of the inner surfaces of the upper surface skin 16 and the lower surface skin 17 of the blade 1, and at the opening 3 part, the upper surface skin 16,
And the outer surface of the lower surface skin 17 is flush with the outer surface of the opening 3
The shutter 18 closes the shutter, the actuating mechanism for actuating the shutter 18 as described above, and the driving device including a servomotor. As for the shutter 18, the opening 3 can be fully closed as shown in FIG. 9A, or a part of the opening 3 can be opened to arbitrarily adjust the opening amount, and the shutter 18 can be opened as shown in FIG. 9B. It is also possible to fully open 3. Also, the upper surface skin 1
6, and the upper and lower shutters 18, which are housed in the lower surface skin 17, move in parallel laterally (wing width direction) when housed, and as shown in FIG. 8 and FIG. It is stowed on the inner surface side of the upper surface skin 16 and the lower surface skin 17.
【００１８】また、図１０は開閉装置の第２実施例を示
す横断面図である。本実施例の開閉装置１９は、開口３
へ繰り出されて開口３を塞ぐ構造のものであり、、繰り
出し方向には可撓にされ、これと直交する方向は剛体と
されたシャッタ２０と、シャッタ２０を巻出し、巻戻し
するローラ２１と、ローラ２１を駆動する駆動装置とか
らなる。開口３を塞ぐため、ローラ２１からシャッタ２
０を巻き出すと、繰り出されたシャッタ２０は、開口３
の両側に設けられた溝内を摺動して、後方へ移動し、上
面外皮１６、および下面外皮１７の外表面と同一面をな
して、開口３を点線で示すように閉鎖する。また、ロー
ラ２１の回動量を調整することにより、開口３の部分開
放も任意に調整して行うことができる。本実施例は第１
実施例に比較して、シャッタ２０の駆動、および収納機
構が簡単にできる利点がある。FIG. 10 is a cross sectional view showing a second embodiment of the opening / closing device. The opening / closing device 19 of this embodiment has the opening 3
A shutter 20 that is of a structure that is drawn out to close the opening 3, is flexible in the drawing direction, and is a rigid body in the direction orthogonal to this, and a roller 21 that unwinds and unwinds the shutter 20. , And a drive device that drives the roller 21. In order to block the opening 3, the roller 21 moves from the shutter 2
When 0 is unwound, the shutter 20 that has been unwound causes the opening 3
Of the upper surface skin 16 and the lower surface skin 17 are flush with each other, and the opening 3 is closed as indicated by a dotted line. Further, by adjusting the amount of rotation of the roller 21, the partial opening of the opening 3 can be adjusted arbitrarily. This embodiment is the first
Compared with the embodiment, there is an advantage that the drive of the shutter 20 and the storage mechanism can be simplified.
【００１９】図１１は、図２および図４に示したよう
に、開口５又は８の内部に、多孔質材６を充填して空孔
率を調整した、開口に適用される開閉装置を示す第３実
施例で、図１１（Ａ）は、この様な開口５に図８の開閉
装置１５を適用した横断面図を示す。この実施例の開口
５では、多孔質材６の外表面が上面外皮１６、および下
面外皮１７の外表面と略同一面をなしており、開口５に
上面外皮１６、および下面外皮１７と同一面をなすシャ
ッタ８を設けなくても、ブレード１の外表面には、顕著
な凹凸面は生じず、開口５の凹凸面形成に伴う、ブレー
ド１の空力性能の劣化の問題はきわめて少いため、多孔
質材６の厚み方向、中央部に貫通孔２２を設け、シャッ
タ８を１枚だけ設けたものである。FIG. 11 shows an opening / closing device applied to an opening in which the porosity is adjusted by filling the inside of the opening 5 or 8 with the porous material 6 as shown in FIGS. 2 and 4. In the third embodiment, FIG. 11A shows a cross-sectional view in which the opening / closing device 15 of FIG. 8 is applied to such an opening 5. In the opening 5 of this embodiment, the outer surface of the porous material 6 is substantially flush with the outer surfaces of the upper surface skin 16 and the lower surface skin 17, and the opening 5 is flush with the upper surface skin 16 and the lower surface skin 17. Even if the shutter 8 forming the structure is not provided, no remarkable uneven surface is formed on the outer surface of the blade 1, and the problem of deterioration of the aerodynamic performance of the blade 1 due to the formation of the uneven surface of the opening 5 is extremely small. A through hole 22 is provided in the central portion in the thickness direction of the quality material 6, and only one shutter 8 is provided.
【００２０】また、図１１（Ｂ）は図１１（Ａ）の同様
な貫通孔２２に、図１０のシャッタ２０を挿入して開口
５の開閉を行うようにしたものである。Further, FIG. 11 (B) shows the opening 5 opened / closed by inserting the shutter 20 of FIG. 10 into the same through hole 22 of FIG. 11 (A).
【００２１】また、図１２は上述した開口、および開閉
装置を設置する部分のブレード１を切欠き、この切欠き
部分２４と同形状にされ、上述の開口、および開閉装置
を一体化し、カセット状にした機構部２３を嵌め込むよ
うにしたものである。このようにすることにより、ブレ
ード１の開口作製、又はブレード１内への開閉装置の組
込み等が、ブレード１の製作と独立に行うことができる
とともに、保守点検作業等がきわめて容易になる。Further, FIG. 12 shows the above-described opening and the blade 1 at the portion where the opening / closing device is installed by cutting out the blade 1 to have the same shape as the notched portion 24. The mechanical unit 23 is fitted in. By doing so, the opening of the blade 1 can be manufactured or the opening / closing device can be incorporated in the blade 1 independently of the manufacturing of the blade 1, and the maintenance and inspection work can be extremely facilitated.
【００２２】以上述べたように、ブレード１の翼端部に
開口と、開口を開閉できる開閉装置を設けたので、図１
３（Ａ）に示すように、開口の開放により、ブレード１
の翼端部２の、ブレード１の下面１２から上面１１へ
の、ブレード１を貫通する空気の流れが発生し、図１３
（Ｂ）実線に示すように、下面１２から上面１１へかけ
ての圧力勾配が小さくなり、翼端４を旋回する空気の流
れが低減して、翼端渦の強さが減少する。これにより、
ＢＶＩ騒音レベルを低減させることができる。As described above, since the opening and the opening / closing device for opening / closing the opening are provided at the blade end portion of the blade 1, the blade 1 shown in FIG.
As shown in FIG. 3 (A), the blade 1 is opened by opening the opening.
The air flow through the blade 1 from the lower surface 12 to the upper surface 11 of the blade 1 of the blade tip 2 of FIG.
(B) As shown by the solid line, the pressure gradient from the lower surface 12 to the upper surface 11 is reduced, the flow of air swirling the blade tip 4 is reduced, and the strength of the blade tip vortex is reduced. This allows
The BVI noise level can be reduced.
【００２３】また、開口を開閉装置により閉鎖すること
により、図１３（Ｂ）点線に示すように、通常のブレー
ドと同様の圧力勾配にでき、ブレード１の空力性能を通
常のブレードと同様にすることもできる。Further, by closing the opening with the opening / closing device, a pressure gradient similar to that of a normal blade can be obtained as shown by the dotted line in FIG. 13 (B), and the aerodynamic performance of the blade 1 becomes the same as that of a normal blade. You can also
【００２４】[0024]
【発明の効果】以上述べたように、本発明の低騒音型ブ
レードによれば、特許請求の範囲に示す簡素な構成によ
り、ヘリコプタがＢＶＩ騒音を発生する飛行条件下にあ
り、しかも、従来のブレードを装着したヘリコプタで
は、騒音問題により難しかった、人口密度の高い都市部
での離着陸時等、ＢＶＩ騒音を低減する必要のある飛行
時においては、ブレードの翼端部に設けた、ブレードの
上、下面を連通する開口を開放することにより、ＢＶＩ
騒音を低減し、これにより、ヘリコプタを都市間交通手
段として、大いに利用できることとなり、ヘリコプタ需
要の増大および価格低下につなげることができる。As described above, according to the low noise type blade of the present invention, the helicopter is under the flight condition of generating the BVI noise and has the simple structure shown in the claims. When using a helicopter equipped with a blade, which was difficult due to noise problems, such as when taking off and landing in a densely populated city area, or when flying to reduce BVI noise, the blade mounted on the blade tip, , BVI is opened by opening the opening that connects the bottom surface.
By reducing noise, the helicopter can be greatly utilized as an inter-city transportation means, which can lead to an increase in helicopter demand and a decrease in price.
【００２５】また、これらの開口は音波レーダーに対す
るステルス性能を有するので、このような性能を必要と
するヘリコプタに活用することもできる。Further, since these apertures have stealth performance for the acoustic wave radar, they can be utilized for a helicopter that requires such performance.
【００２６】また、ＢＶＩ騒音を低減する必要のない飛
行時、又はＢＶＩ騒音が発生しない通常の飛行条件下に
おいては、開口を開閉装置により閉鎖することにより、
ブレードの空力性能を充分に発揮させることができ、ヘ
リコプタの性能向上に資することができる。Further, during flight in which it is not necessary to reduce BVI noise, or under normal flight conditions in which BVI noise is not generated, the opening is closed by the opening / closing device.
The aerodynamic performance of the blade can be fully exerted, which can contribute to the performance improvement of the helicopter.
【図１】本発明の低騒音型ブレードに係るブレードに設
ける開口の第１実施例を示す平面図、FIG. 1 is a plan view showing a first embodiment of openings provided in a blade relating to a low noise type blade of the present invention,
【図２】図１の開口の第２実施例を示す平面図、FIG. 2 is a plan view showing a second embodiment of the opening shown in FIG.
【図３】図１の開口の第３実施例を示す平面図、FIG. 3 is a plan view showing a third embodiment of the opening shown in FIG.
【図４】図１の開口の第４実施例を示す平面図、FIG. 4 is a plan view showing a fourth embodiment of the opening shown in FIG.
【図５】図１に示す実施例の斜視図、5 is a perspective view of the embodiment shown in FIG. 1,
【図６】図５に示す開口部の翼断面形の第１実施例を示
す図で、図６（Ａ）は図５の矢視Ａ−Ａで示す横断面
図、図６（Ｂ）は図５の矢視Ｂ−Ｂで示す縦断面図、6 is a view showing a first embodiment of a blade cross-sectional shape of the opening shown in FIG. 5, FIG. 6 (A) is a cross-sectional view taken along the line AA in FIG. 5, and FIG. 6 (B) is FIG. 5 is a vertical sectional view taken along the line BB of FIG.
【図７】図５に示す開口部の翼断面形の第２実施例を示
す図で、図７（Ａ）は図５の矢視Ａ−Ａで示す横断面
図、図７（Ｂ）は図５の矢視Ｂ−Ｂで示す縦断面図、7 is a diagram showing a second embodiment of the blade cross-sectional shape of the opening shown in FIG. 5, FIG. 7 (A) is a cross-sectional view taken along the line AA in FIG. 5, and FIG. 7 (B) is FIG. 5 is a vertical sectional view taken along the line BB of FIG.
【図８】本発明の低騒音型ブレードに係る、ブレードに
設ける開閉装置の第１実施例を示す横断面図、FIG. 8 is a cross-sectional view showing a first embodiment of an opening / closing device provided on the low noise blade of the present invention,
【図９】図８に示す実施例を具えたブレード全体横断面
を示す図で、図９（Ａ）は開口閉鎖時を示す横断面図、
図９（Ｂ）は開口開放時を示す横断面図、9 is a view showing a cross section of the entire blade including the embodiment shown in FIG. 8, and FIG. 9 (A) is a cross section showing the state when the opening is closed;
FIG. 9 (B) is a cross-sectional view showing the opening opening,
【図１０】図８の開閉装置の第２実施例を示す横断面
図、10 is a cross sectional view showing a second embodiment of the opening / closing device of FIG.
【図１１】図８の開閉装置の第３実施例を示す図で、図
１１（Ａ）は図８の実施例を図２、又は図４の開口に適
用した横断面図、図１１（Ｂ）は図１０の実施例を図
２、又は図４の開口に適用した横断面、11 is a view showing a third embodiment of the opening / closing device of FIG. 8, FIG. 11 (A) is a cross-sectional view of the embodiment of FIG. 8 applied to the opening of FIG. 2 or FIG. 4, and FIG. ) Is a cross section of the embodiment of FIG. 10 applied to the aperture of FIG. 2 or FIG.
【図１２】本発明を構成する開口、および開閉装置を、
ブレードと別体化した実施例を示す斜視図、FIG. 12 shows an opening and an opening / closing device which constitute the present invention,
A perspective view showing an embodiment separated from the blade,
【図１３】本発明の低騒音型ブレードの作動状況および
効果を示す図、FIG. 13 is a diagram showing an operating condition and effects of the low noise type blade of the present invention;
【図１４】ＢＶＩ騒音の発生を説明するための飛行中の
ヘリコプタの斜視図、FIG. 14 is a perspective view of a helicopter in flight to explain the generation of BVI noise;
【図１５】ブレードの翼端を示す平面図で、図１５
（Ａ）は従来のＢＶＩ騒音低減に使用されているブレー
ド翼端平面図、図１５（Ｂ）は通常のブレードの翼端平
面図、FIG. 15 is a plan view showing a wing tip of the blade shown in FIG.
FIG. 15A is a plan view of a blade tip used for conventional BVI noise reduction, and FIG. 15B is a plan view of a blade tip of a normal blade.
【図１６】ブレード翼端における空気の流れの状況を示
す図で、図１６（Ａ）は座標系を示すためのブレード縦
断面図、図１６（Ｂ）は圧力勾配を示す図、図１６
（Ｃ）は翼端の空気の流れの状況を示す模式図、16A and 16B are diagrams showing the state of air flow at the blade tip, where FIG. 16A is a longitudinal sectional view of the blade for showing the coordinate system, and FIG. 16B is a diagram showing a pressure gradient;
(C) is a schematic diagram showing the state of the air flow at the blade tip,
【図１７】翼端渦の循環の強さを低減した時の、ブレー
ド翼端における空気の流れの状況を示す図で、図１７
（Ａ）は翼端の空気の流れの状況を示す模式図、図１７
（Ｂ）は図１７（Ａ）の空気の流れにおける圧力勾配を
示す図である。FIG. 17 is a diagram showing the state of air flow at the blade tip when the strength of the circulation of the tip vortex is reduced.
FIG. 17A is a schematic diagram showing the state of air flow at the blade tip, FIG.
17B is a diagram showing a pressure gradient in the air flow of FIG. 17A.
１ ブレード ２ （ブレードの）翼端部 ３，３′，３″，５，７，８ 開口 ４ 翼端 ６ 多孔質材 １１ （ブレードの）上面 １２ （ブレードの）下面 １３ 気流 １４ 円弧部 １５，１９ 開閉装置 １６ 上面外皮 １７ 下面外皮 １８ シャッタ ２０ シャッタ ２１ ローラ ２２ 貫通孔 ２３ 機構部 DESCRIPTION OF SYMBOLS 1 Blade 2 Blade tip (of blade) 3, 3 ', 3 ", 5, 7, 8 Opening 4 Blade tip 6 Porous material 11 Upper surface (of blade) 12 Lower surface (of blade) 13 Airflow 14 Arc portion 15, 19 Opening / closing device 16 Upper surface skin 17 Lower surface skin 18 Shutter 20 Shutter 21 Roller 22 Through hole 23 Mechanism part
Claims (1)
タ用のブレードにおいて、前記ブレードの翼端部に、前
記ブレードの上面と下面とを連通させて設けられた開口
と、前記開口を開閉する開閉装置とを設けたことを特徴
とする低騒音型ブレード。1. A blade for a helicopter that rotates to hold an airframe in the air, and an opening provided at the blade end portion of the blade so as to connect the upper surface and the lower surface of the blade to each other. A low noise type blade, which is provided with an opening / closing device.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| JP9426394A JPH07300098A (en) | 1994-05-06 | 1994-05-06 | Low noise type blade |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| JP9426394A JPH07300098A (en) | 1994-05-06 | 1994-05-06 | Low noise type blade |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| JPH07300098A true JPH07300098A (en) | 1995-11-14 |
Family
ID=14105403
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| JP9426394A Withdrawn JPH07300098A (en) | 1994-05-06 | 1994-05-06 | Low noise type blade |
Country Status (1)
| Country | Link |
|---|---|
| JP (1) | JPH07300098A (en) |
Cited By (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP1577212A2 (en) * | 2004-03-16 | 2005-09-21 | Westland Helicopters Limited | Improvements in or relating to aerofoils |
| WO2007007108A1 (en) * | 2005-07-13 | 2007-01-18 | City University | An element for generating a fluid dynamic force |
| EP2549097A1 (en) * | 2011-07-20 | 2013-01-23 | LM Wind Power A/S | Wind turbine blade with lift-regulating means |
| DK178158B1 (en) * | 2010-09-17 | 2015-07-06 | Gen Electric | Wind turbine rotor blade with actuatable airfoil passages |
| DK178193B1 (en) * | 2010-12-07 | 2015-08-03 | Gen Electric | Wind turbine rotor blade with permeable window and controllable cover element |
| US10933988B2 (en) | 2015-12-18 | 2021-03-02 | Amazon Technologies, Inc. | Propeller blade treatments for sound control |
| US11163302B2 (en) | 2018-09-06 | 2021-11-02 | Amazon Technologies, Inc. | Aerial vehicle propellers having variable force-torque ratios |
-
1994
- 1994-05-06 JP JP9426394A patent/JPH07300098A/en not_active Withdrawn
Cited By (13)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JP4713160B2 (en) * | 2004-03-16 | 2011-06-29 | ウエストランド・ヘリコプターズ・リミテッド | Airfoil, aircraft with this airfoil, and method of forming this airfoil |
| JP2005263201A (en) * | 2004-03-16 | 2005-09-29 | Westland Helicopters Ltd | Aerofoil and method for forming the aerofoil |
| EP1577212A3 (en) * | 2004-03-16 | 2005-12-21 | Westland Helicopters Limited | Improvements in or relating to aerofoils |
| EP1577212A2 (en) * | 2004-03-16 | 2005-09-21 | Westland Helicopters Limited | Improvements in or relating to aerofoils |
| US7264444B2 (en) | 2004-03-16 | 2007-09-04 | Westland Helicopters Limited | Aerofoils |
| EP2316729A3 (en) * | 2005-07-13 | 2011-11-02 | City University | An element for generating a fluid dynamic force |
| WO2007007108A1 (en) * | 2005-07-13 | 2007-01-18 | City University | An element for generating a fluid dynamic force |
| DK178158B1 (en) * | 2010-09-17 | 2015-07-06 | Gen Electric | Wind turbine rotor blade with actuatable airfoil passages |
| DE102011053712B4 (en) | 2010-09-17 | 2022-12-22 | General Electric Company | WIND TURBINE ROTOR BLADE WITH ACTUABLE PROFILE PASSAGES |
| DK178193B1 (en) * | 2010-12-07 | 2015-08-03 | Gen Electric | Wind turbine rotor blade with permeable window and controllable cover element |
| EP2549097A1 (en) * | 2011-07-20 | 2013-01-23 | LM Wind Power A/S | Wind turbine blade with lift-regulating means |
| US10933988B2 (en) | 2015-12-18 | 2021-03-02 | Amazon Technologies, Inc. | Propeller blade treatments for sound control |
| US11163302B2 (en) | 2018-09-06 | 2021-11-02 | Amazon Technologies, Inc. | Aerial vehicle propellers having variable force-torque ratios |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| A300 | Withdrawal of application because of no request for examination |
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