JPH0774038B2 - Rotor blade of a rotorcraft - Google Patents
Rotor blade of a rotorcraftInfo
- Publication number
- JPH0774038B2 JPH0774038B2 JP17118487A JP17118487A JPH0774038B2 JP H0774038 B2 JPH0774038 B2 JP H0774038B2 JP 17118487 A JP17118487 A JP 17118487A JP 17118487 A JP17118487 A JP 17118487A JP H0774038 B2 JPH0774038 B2 JP H0774038B2
- Authority
- JP
- Japan
- Prior art keywords
- blade
- dihedral
- rotor
- angle
- tip
- 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 - Lifetime
Links
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C27/00—Rotorcraft; Rotors peculiar thereto
- B64C27/32—Rotors
- B64C27/46—Blades
- B64C27/463—Blade tips
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Aviation & Aerospace Engineering (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
- Toys (AREA)
Description
【発明の詳細な説明】 〔産業上の利用分野〕 本発明は、回転翼VTOL機、ヘリコプタ等、回転翼を有す
る航空機の揚力ロータ・ブレードの改良に関する。Description: TECHNICAL FIELD The present invention relates to an improvement of a lift rotor blade of an aircraft having a rotor, such as a rotor VTOL machine and a helicopter.
従来のたとえば回転翼VTOL機の揚力ロータは、上・下反
角をもたないブレード形状であったが、最近、第３図、
第４図に示すように、翼端部に下反角がついたブレード
が出現した。この下反角は、ホバリング（空中停止）で
先行ブレードから放出される翼端渦と後続ブレードとの
干渉を防ぐことを目的としたものである。The lift rotor of a conventional rotor VTOL machine, for example, has a blade shape with no dihedral or dihedral, but recently, as shown in FIG.
As shown in FIG. 4, a blade with a dihedral angle appeared at the blade tip. This dihedral angle is intended to prevent interference between the tip vortex emitted from the leading blade and the trailing blade during hovering (air stop).
ところが、この下反角を有するブレードは高速飛行時、
翼端部ブレード空気力（抵抗）により、第５図に示すよ
うに頭下げ捩り変形の定常成分が大きくなる。However, when the blade with this dihedral angle is flying at high speed,
The blade aerodynamic force (resistance) increases the steady component of the head-down torsional deformation as shown in FIG.
この下反角の設けられた経緯は、ホバリング中の回転翼
VTOL機のブレードが直状の場合、先行ブレード翼端部か
ら発生する翼端渦が後続ブレードのごく近傍を通ること
により干渉を受け、局所迎角が増大し、第６図に示すよ
うにブレード失速が早まる。そこで、この干渉を防ぐ
為、翼端部に下反角をつけ、翼端渦と後続ブレードとの
上下間隔を離したものである。The history of this dihedral is because the rotor blades are hovering.
When the blade of the VTOL machine is straight, the tip vortex generated from the tip of the leading blade passes through the vicinity of the trailing blade, which causes interference and increases the local angle of attack. Stall speeds up. Therefore, in order to prevent this interference, a dihedral angle is given to the blade tip, and the vertical distance between the blade tip vortex and the succeeding blade is separated.
上記従来のブレードのように、下反角を設けたのみで
は、この部分に働く空気力（抵抗）により、高速飛行時
に捩り下げモーメントが大となる。高速で飛行中、前進
側及び後退側ブレードが受ける動圧のアンバランスを除
く為、後退側よりも前進側ブレード迎角を小さくして左
右のバランスをとっている。一般に、回転翼VTOL機の揚
力ロータは、性能を上げる為、ブレードに捩り下げをつ
ける。この為、速度を上げていくと前進側ブレード翼端
部は、角の迎角となる。この場合、下反角による捩り下
げ変形の発生は負の迎角すなわち、下向き揚力の増大を
生じ性能的に不利となる。As in the conventional blade described above, if only the dihedral angle is provided, the torsional moment becomes large during high-speed flight due to the aerodynamic force (resistance) acting on this portion. While flying at high speed, in order to eliminate the unbalance of the dynamic pressure received by the forward and backward blades, the angle of attack of the forward blades is made smaller than that of the backward sides to achieve left-right balance. In general, the lift rotor of a rotary VTOL machine is equipped with a twisted blade to improve performance. Therefore, as the speed is increased, the blade tip of the advancing blade has an angle of attack. In this case, the occurrence of twisting deformation due to the dihedral angle causes a negative angle of attack, that is, an increase in downward lift force, which is disadvantageous in terms of performance.
本発明は上記問題点解決の手段として、回転中心よりみ
てブレード長の80〜100％の範囲に設けられた上反部
と、同上反部に近接して設けられた下反部とを備えたこ
とを特徴とする回転翼機のロータ・ブレードを提供しよ
うとするものである。As a means for solving the above problems, the present invention includes a valgus portion provided within a range of 80 to 100% of the blade length as viewed from the center of rotation, and a valgus portion provided near the valgus portion. An object of the present invention is to provide a rotor blade of a rotary wing machine characterized by the above.
本発明は上記のよに構成するので、上反部から下反部へ
変化する部分の下に、或は下反部から上反部へ変化する
部分の上に、先行ブレードから発生する翼端渦をやり過
すことによりブレードと渦との干渉が回避されるので、
ホバリング性能が向上する。又、下反部と上反部を組み
合わすことにより捩り下げモーメントの発生が小さく抑
えられ、捩り下げ変形の増大を防ぐことができる。Since the present invention is configured as described above, the blade tip generated from the leading blade is provided below the portion that changes from the valgus portion to the varus portion, or on the portion that changes from the valgus portion to the valgus portion. By passing through the vortex, the interference between the blade and the vortex is avoided, so
The hovering performance is improved. Further, by combining the inferior portion and the inferior portion, the generation of the twisting-down moment can be suppressed to be small, and an increase in the twisting-down deformation can be prevented.
本発明の一実施例を第１図により説明する。図におい
て、１はロータ・ブレード（ブレードと同義である）、
２はその直状部、３はロータ・ブレード１の回転中心か
ら凡そ80％近傍でロータ・ブレード１が上反角θで上方
に向かうよう設けられた上反部、４は同じく80％から10
0％（全長）の範囲の最適位置で下反角φで下方に向か
うよう設けられた下反部である。なお、後述の通り、ロ
ータ・ブレード１が一層の性能を発揮するよう、図
（ａ）に示すようにその翼端部の平面形状は後退角と先
細り状の擬似テーパを有している。An embodiment of the present invention will be described with reference to FIG. In the figure, 1 is a rotor blade (synonymous with blade),
2 is the straight portion, 3 is the valvular portion provided so that the rotor blade 1 is directed upward at the dihedral angle θ approximately 80% from the center of rotation of the rotor blade 1, and 4 is the same from 80% to 10%.
It is a varus portion provided downward at the dihedral angle φ at the optimum position in the range of 0% (total length). As will be described later, in order to further enhance the performance of the rotor blade 1, the blade tip has a plane shape with a receding angle and a tapered pseudo taper as shown in FIG.
次に作用について説明する。Next, the operation will be described.
従来通りの下反角のみであれば、高速飛行時、翼端ブレ
ード空気力（抵抗）により頭下げの捩り変形（定常成
分）が大きくなるが本実施例では下反角φに対し上反角
θが設けられているのでその組合わせにより捩り下げ変
形の増大を防ぐことができる。第２図はたとえば頭上
げ、下げの各モーメントを説明した図であるが、下反部
による頭下げモーメントM2＝γ2D2がロータ・ブレード
をその先端が下る方向即ち、図に対して右回りのモーメ
ントを発生するのに対し、上反部は先端が上る方向即
ち、左回りのモーメントM1＝γ1D1を発生してこれを相
殺する。If only the dihedral angle as in the past is used, the wing tip blade aerodynamic force (resistance) increases the head-down torsional deformation (steady component) during high-speed flight, but in this embodiment the dihedral angle φ is dihedral. Since θ is provided, it is possible to prevent an increase in torsional deformation due to the combination. FIG. 2 is a diagram for explaining the moments of raising and lowering the head, for example, but the moment of lowering the head M 2 = γ 2 D 2 due to the inversion part is the direction in which the tip of the rotor blade descends, that is, with respect to the figure. While a clockwise moment is generated, the valgus portion cancels out by generating a counterclockwise moment M 1 = γ 1 D 1 in the direction in which the tip goes up.
なお、実施例の翼端は上記の通り擬似テーパを有してい
るので翼端ドラグが減少し、かつ、後退角を有している
ので空気に対する圧縮性を軽減でき、これらはロータの
必要馬力を減少するので燃費の改善に寄与する。又、搭
載エンジンも小型化でき、コスト低減，ペイロード向上
に役立つ。特に擬似テーパはホバリング性能を向上さ
せ、後退角は前進飛行性能を向上させる。In addition, since the blade tip of the embodiment has the pseudo taper as described above, the blade tip drag is reduced, and since it has the sweepback angle, the compressibility with respect to air can be reduced. Reduces fuel consumption and contributes to improved fuel economy. The onboard engine can also be made smaller, which helps reduce costs and improve payload. In particular, the pseudo taper improves hovering performance and the receding angle improves forward flight performance.
以上実施例では翼端側に下反部、ロータ回転中心側に上
反部を設けたが設計条件によってはその逆に設けてもよ
い。又、後退角，擬似テーパは飛行条件によっては必ず
しも設ける必要はない。In the above embodiment, the lower portion is provided on the blade tip side and the upper portion is provided on the rotor rotation center side. Further, the receding angle and the pseudo taper are not necessarily required depending on the flight conditions.
又、適用機種はVTOLのみに限定されるものではない。Also, the applicable model is not limited to VTOL only.
本発明は上記のように構成するので以下の効果を有す
る。Since the present invention is configured as described above, it has the following effects.
（１） 高速飛行時の捩り下げ変形の少ないロータ・ブ
レードが得られる。(1) A rotor blade with less twisting deformation during high-speed flight can be obtained.
（２） ホバリング性能が向上する。(2) The hovering performance is improved.
（３） 燃費が改善される。(3) Fuel economy is improved.
（４） ペイロードが増す。(4) Payload increases.
第１図は本発明の一実施例の上・下反角付ロータ・ブレ
ードの翼端部を示す図で、（ａ）は平面図、（ｂ）はそ
の後面図、第２図は上・下反角による捩りモーメントの
説明図、第３図は従来例の斜視図及びその下反角効果を
説明する図、第４図は第３図のIV囲いの詳細図（但し、
翼端を後方から見る）、第５図は下反角による空力弾性
変形のグラフ、第６図は翼端渦とブレードの干渉を示す
図である。 １……ロータ・ブレード、２……直状部、３……上反
部、４……下反部、θ……上反角、φ……下反角。FIG. 1 is a view showing a wing tip portion of a rotor blade with dihedral and dihedral according to an embodiment of the present invention. FIG. FIG. 3 is a perspective view of a conventional example and a diagram for explaining its dihedral effect, and FIG. 4 is a detailed view of the IV enclosure of FIG. 3 (however,
FIG. 5 is a graph of aeroelastic deformation due to the dihedral angle, and FIG. 6 is a view showing interference between the blade tip vortex and the blade. 1 ... Rotor blade, 2 ... Straight portion, 3 ... Dihedral portion, 4 ... Dihedral portion, θ ... Dihedral angle, φ ... Dihedral angle.
Claims (1)
の範囲に設けられた上反部と、同上反部に近接して設け
られた下反部とを備えたことを特徴とする回転翼機のロ
ータ・ブレード。1. The blade length is 80 to 100% as viewed from the center of rotation.
A rotor blade for a rotary wing machine, comprising: a valgus portion provided in a range of the above and a valgus portion provided in the vicinity of the valgus portion.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| JP17118487A JPH0774038B2 (en) | 1987-07-10 | 1987-07-10 | Rotor blade of a rotorcraft |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| JP17118487A JPH0774038B2 (en) | 1987-07-10 | 1987-07-10 | Rotor blade of a rotorcraft |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| JPS6416498A JPS6416498A (en) | 1989-01-19 |
| JPH0774038B2 true JPH0774038B2 (en) | 1995-08-09 |
Family
ID=15918562
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| JP17118487A Expired - Lifetime JPH0774038B2 (en) | 1987-07-10 | 1987-07-10 | Rotor blade of a rotorcraft |
Country Status (1)
| Country | Link |
|---|---|
| JP (1) | JPH0774038B2 (en) |
Families Citing this family (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JP3916723B2 (en) | 1997-05-15 | 2007-05-23 | 富士重工業株式会社 | Rotor blade of rotorcraft |
| GB2486021B (en) * | 2010-12-02 | 2017-07-19 | Agustawestland Ltd | Aerofoil |
-
1987
- 1987-07-10 JP JP17118487A patent/JPH0774038B2/en not_active Expired - Lifetime
Also Published As
| Publication number | Publication date |
|---|---|
| JPS6416498A (en) | 1989-01-19 |
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