JP2003227302A - Blade for promoting wake mixing - Google Patents
Blade for promoting wake mixingInfo
- Publication number
- JP2003227302A JP2003227302A JP2002026586A JP2002026586A JP2003227302A JP 2003227302 A JP2003227302 A JP 2003227302A JP 2002026586 A JP2002026586 A JP 2002026586A JP 2002026586 A JP2002026586 A JP 2002026586A JP 2003227302 A JP2003227302 A JP 2003227302A
- Authority
- JP
- Japan
- Prior art keywords
- blade
- wake
- trailing edge
- mixing
- blades
- 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.)
- Pending
Links
Abstract
Description
【０００１】[0001]
【産業上の利用分野】本発明は、伴流の混合を促進し騒
音を低減する伴流混合促進翼に関する。BACKGROUND OF THE INVENTION 1. Field of the Invention The present invention relates to a wake mixing promoting blade for promoting wake mixing and reducing noise.
【０００２】[0002]
【従来の技術】図３（Ａ）は、ジェットエンジンのファ
ン、圧縮機、タービン等、翼列を有する流体機械におけ
る翼下流側の速度分布を模式的に示している。この図に
示すように翼１の下流側には、翼間を通過した主流２よ
りも速度の遅い伴流３（ｗａｋｅ又は後流とも呼ぶ）が
存在する。この伴流３は、一般的に翼１の直後では幅は
狭いが最大欠損速度が大きく、下流に進むに従って幅が
広がり最大欠損速度が小さくなる傾向を有する。2. Description of the Related Art FIG. 3A schematically shows a velocity distribution on a downstream side of a blade in a fluid machine having a blade row such as a fan of a jet engine, a compressor and a turbine. As shown in this figure, on the downstream side of the blades 1, there is a wake 3 (also called a wake or wake) having a lower velocity than the main flow 2 passing between the blades. In general, the wake 3 has a narrow width immediately after the blade 1 but has a large maximum breaking speed, and has a tendency that the width widens and the maximum breaking speed decreases as it goes downstream.
【０００３】動翼列の下流側に静翼列がある軸流のファ
ン、圧縮機、タービン等では、上述した伴流の存在によ
り、図３（Ｂ）に模式的に示す騒音が発生する。この騒
音は、翼列を構成する翼枚数と回転速度できまる周波数
の高い「キ−ン」というジェットエンジン特有の耳障り
な高周波音である。In an axial-flow fan, compressor, turbine, etc. having a stationary blade row on the downstream side of the moving blade row, the presence of the above-mentioned wake produces a noise schematically shown in FIG. 3 (B). This noise is an offensive high-frequency sound peculiar to the jet engine, which is a “key” having a high frequency that can be controlled by the number of blades forming the blade row and the rotation speed.
【０００４】[0004]
【発明が解決しようとする課題】伴流により生じる上述
した高周波音は、動翼相対系主流速度と回転速度の合成
ベクトルと、動翼相対系伴流速度と回転速度の合成ベク
トルとが、速度ベクトルの大きさと向きが異なるため、
動静翼と干渉した時に翼面上に音源となる大きな圧力変
動が発生することで、生じるものと考えられている。The above-mentioned high-frequency sound generated by the wake is generated by the combination of the main vector velocity and the rotational velocity of the rotor blade relative system and the composite vector of the wake velocity and the rotational velocity of the rotor blade relative system. Since the magnitude and direction of the vector are different,
It is thought that this is caused by the large pressure fluctuation that acts as a sound source on the blade surface when it interferes with the moving and stationary blades.
【０００５】図４は、動翼１の下流側に発生した伴流３
が下流に位置する静翼４と干渉する様子を、コンピュー
タシミュレーションで解析した結果である。この図にお
いて、（Ａ）は動翼と静翼の間隔Ｌが短い場合、（Ｂ）
はこの間隔Ｌが長い場合である。この図から明らかなよ
うに、間隔Ｌが短い場合、伴流３の幅は狭く最大欠損速
度が大きく、逆に間隔Ｌが長い場合、伴流３の幅は広く
最大欠損速度が小さくなる。FIG. 4 shows a wake 3 generated on the downstream side of the rotor blade 1.
FIG. 7 is a result of computer simulation analysis of the state of interference with the stationary blades 4 located downstream. In this figure, (A) is a case where the distance L between the moving blade and the stationary blade is short, (B)
Indicates that this interval L is long. As is clear from this figure, when the interval L is short, the width of the wake 3 is narrow and the maximum loss velocity is large, and conversely, when the interval L is long, the width of the wake 3 is wide and the maximum loss velocity is small.
【０００６】上述したように、流体機械において翼列か
ら放出される伴流と下流に位置する翼列との干渉は、騒
音・翼振動といった流体機械の特性に悪影響を及ぼす。
そのため、従来、例えば航空エンジンの動静翼干渉音を
低減させるために、動静翼間の間隔を広くとり動翼伴流
の減衰を進めることで低騒音化を図っていた。As described above, the interference between the wake emitted from the blade row and the blade row located downstream in the fluid machine adversely affects the characteristics of the fluid machine such as noise and blade vibration.
For this reason, conventionally, for example, in order to reduce the interference noise of the moving and stationary blades of an aeroengine, the distance between the moving and stationary blades has been widened to reduce the noise of the moving blade wake.
【０００７】しかし、航空エンジンの場合、従来技術で
はファンの動翼と静翼の間隔Ｌを動翼のコード長の例え
ば１５０％から２００％程度にする必要があり、その
分、エンジン全体の軸方向長さが長くなってしまい、エ
ンジン重量の増加を招くことになっていた。However, in the case of an aviation engine, in the prior art, it is necessary to set the distance L between the moving blades of the fan and the stationary blades to, for example, about 150% to 200% of the cord length of the moving blades. The length in the direction becomes long, which causes an increase in engine weight.
【０００８】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、本発明は、伴流により
生じる騒音と振動を低減し、かつエンジン全体の軸方向
長さも短縮することができる伴流混合促進翼を提供する
ことにある。The present invention was devised to solve such problems. That is, the present invention is to provide a wake mixing promotion blade capable of reducing noise and vibration caused by the wake and reducing the axial length of the entire engine.
【０００９】[0009]
【課題を解決するための手段】本発明によれば、軸方向
に隣接して複数の翼列を有する軸流流体機械を構成する
翼（１０）であって、後縁（１０ｂ）からの流出角が、
基準の流出角に対して、半径方向の位置に応じて周方向
に交互に増減し、これにより二次流れ（１１）の作用で
伴流の混合が促進されるように、後縁部が形成されてい
る、ことを特徴とする伴流混合促進翼が提供される。According to the present invention, a vane (10) constituting an axial flow fluid machine having a plurality of blade rows adjacent to each other in the axial direction, which flows out from a trailing edge (10b). The corner
The trailing edge is formed such that it increases and decreases alternately in the circumferential direction with respect to the reference outflow angle depending on the radial position, thereby promoting mixing of the wake by the action of the secondary flow (11). A wake mixing promoting blade is provided.
【００１０】本発明の好ましい実施形態によれば、前記
後縁（１０ｂ）は、半径方向の位置に応じて滑らかな波
形に形成されている。また、前記軸流流体機械は、ファ
ン、圧縮機、又はタービンである。According to a preferred embodiment of the present invention, the trailing edge (10b) is formed in a smooth corrugation according to the radial position. The axial flow fluid machine is a fan, a compressor, or a turbine.
【００１１】上記本発明の構成によれば、後縁（１０
ｂ）からの流出角が、基準の流出角に対して、半径方向
の位置に応じて周方向に交互に増減するように、後縁部
が形成されているので、翼通過時に主流に生じる二次流
れを増大し、翼列伴流の混合を積極的に促進して、動静
翼間隔を広げたのと同じ効果を得ることができる。従っ
て、動静翼間隔を広げることなく短い動静翼間隔で、伴
流により生じる騒音と振動を低減し、かつエンジン全体
の軸方向長さも短縮することができる。According to the above configuration of the present invention, the trailing edge (10
Since the trailing edge is formed so that the outflow angle from b) alternately increases and decreases in the circumferential direction depending on the radial position with respect to the reference outflow angle, the two that occur in the main flow when passing through the blades. It is possible to increase the secondary flow and positively promote the mixing of the cascade wake to obtain the same effect as that of widening the interval between the moving and stationary blades. Therefore, it is possible to reduce the noise and vibration caused by the wake and shorten the axial length of the entire engine with a short moving and stationary blade interval without widening the moving and stationary blade interval.
【００１２】[0012]
【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て使用する。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 same parts are denoted by the same reference numerals.
【００１３】図１は、本発明による伴流混合促進翼の模
式的斜視図である。本発明の伴流混合促進翼１０は、軸
方向に隣接して複数の翼列を有する軸流流体機械を構成
するための翼である。この軸流流体機械は、ファン、圧
縮機、又はタービンであり、伴流混合促進翼１０は、上
流側に位置する翼列、好ましくは動翼列を構成する。FIG. 1 is a schematic perspective view of a wake mixing promotion blade according to the present invention. The wake mixing promotion blade 10 of the present invention is a blade for constituting an axial flow fluid machine having a plurality of blade rows adjacent to each other in the axial direction. The axial flow fluid machine is a fan, a compressor, or a turbine, and the wake mixing promotion blade 10 constitutes a blade row located on the upstream side, preferably a blade row.
【００１４】図１に示すように、本発明の伴流混合促進
翼１０の後縁１０ｂは、半径方向の位置に応じて滑らか
な波形に形成されている。なお１０ａは前縁である。As shown in FIG. 1, the trailing edge 10b of the wake mixing promotion blade 10 of the present invention is formed in a smooth waveform according to the position in the radial direction. Note that 10a is the leading edge.
【００１５】すなわち、この例では、翼の末端側から先
端側に向かう半径方向の位置ｘに対して、後縁１０ｂの
周方向位置ｙが例えばサイン又はコサインに変化してお
り、後縁１０ｂからの流出角が、基準の流出角に対し
て、半径方向の位置に応じて周方向に交互に増減するよ
うに構成されている。これに伴い、後縁１０ｂの近傍の
後縁部も同様に、周方向に交互に滑らかに増減するのが
よい。That is, in this example, the circumferential position y of the trailing edge 10b is changed to, for example, a sine or a cosine with respect to a radial position x from the distal end side of the blade toward the tip side thereof, and the trailing edge 10b changes from the trailing edge 10b. Is configured to alternately increase and decrease in the circumferential direction in accordance with the radial position with respect to the reference outflow angle. Along with this, it is preferable that the trailing edge portion near the trailing edge 10b also be smoothly increased / decreased alternately in the circumferential direction.
【００１６】なお、周方向に交互に増減する半径方向の
ピッチは、図１のように一定でもよく、或いは半径方向
位置に応じて変化させてもよい。また、後縁１０ｂから
の流出角の増減に対応させて、図１のように、後縁１０
ｂの近傍の後縁部のみの翼形状を変化させてもよく、あ
るいは翼のスタッキングを半径方向の位置に応じて変化
させてもよい。The pitch in the radial direction that alternately increases and decreases in the circumferential direction may be constant as shown in FIG. 1 or may be changed according to the radial position. In addition, as shown in FIG. 1, the trailing edge 10 is adjusted to correspond to the increase or decrease of the outflow angle from the trailing edge 10b.
The blade shape may be changed only at the trailing edge near b, or the blade stacking may be changed according to the radial position.
【００１７】図２は、翼列により生じる二次流れの比較
図であり、（Ａ）は従来例、（Ｂ）は本発明の場合であ
る。図２（Ａ）に示すように、翼１の下流側には伴流３
が形成され、翼１で構成される翼列の下流側には、主流
に直交して隣接する翼間で循環する翼間二次流れ５と、
伴流の背側と腹側との間を小さく循環する伴流渦６（後
流渦）が形成される。本発明では、この翼間二次流れ５
と伴流渦６の両方を含めて二次流れ１１と呼ぶ。2A and 2B are comparative diagrams of the secondary flow generated by the blade rows, where FIG. 2A is a conventional example and FIG. 2B is the case of the present invention. As shown in FIG. 2A, a wake 3 is formed on the downstream side of the blade 1.
Is formed, and on the downstream side of the blade row constituted by the blades 1, an inter-blade secondary flow 5 that circulates between the blades that are adjacent to each other orthogonally to the main flow,
A wake vortex 6 (wake vortex) that circulates between the back side and the ventral side of the wake is formed. In the present invention, this secondary flow between blades 5
And the wake vortex 6 as well as the secondary flow 11.
【００１８】図２（Ｂ）に示すように、本発明の伴流混
合促進翼１０では、後縁１０ｂからの流出角が、基準の
流出角に対して、半径方向の位置に応じて周方向に交互
に増減するように、後縁部が形成されているので、翼通
過時に主流に生じる二次流れ１１、局所的には伴流渦６
の作用、大域的には翼間二次流れ５の作用を利用し、翼
列伴流の混合を積極的に促進して、動静翼間隔を広げた
のと同じ効果を得ることができる。たとえば、航空エン
ジンの場合、従来技術ではファンの動翼と静翼の間隔Ｌ
を動翼のコード長の例えば１５０％から２００％程度に
する必要があったが、本発明により同程度の騒音レベル
において動翼と静翼の間隔Ｌを動翼のコード長の例えば
１００％程度にすることができる。従って、動静翼間隔
を広げることなく短い動静翼間隔で、伴流により生じる
騒音と振動を低減し、かつエンジン全体の軸方向長さも
短縮することができる。As shown in FIG. 2B, in the wake mixing promotion blade 10 of the present invention, the outflow angle from the trailing edge 10b is measured in the circumferential direction according to the radial position with respect to the reference outflow angle. Since the trailing edge portion is formed so as to increase and decrease alternately, the secondary flow 11 generated in the main flow when passing the blade, and locally the wake vortex 6
The effect of the secondary flow 5 between blades is utilized globally, and the mixing of blade cascade wakes is positively promoted to obtain the same effect as when the interval between the moving and stationary blades is widened. For example, in the case of an aero engine, in the prior art, the distance L between the moving blades of the fan and the stationary blades is L.
Was required to be, for example, about 150% to 200% of the cord length of the rotor blade. However, according to the present invention, at the same noise level, the distance L between the rotor blade and the stator blade is about 100% of the cord length of the rotor blade. Can be Therefore, it is possible to reduce the noise and vibration caused by the wake and shorten the axial length of the entire engine with a short moving and stationary blade interval without widening the moving and stationary blade interval.
【００１９】なお、本発明は上述した実施形態に限定さ
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。例えば、本発明は、ファンに限定さ
れず軸流の圧縮機及びタービンにも適用できる。また、
ジェットエンジンに限定されず翼列を有するすべての流
体機械に適用することができる。It should be noted that the present invention is not limited to the above-described embodiments, and it goes without saying that various modifications can be made without departing from the gist of the present invention. For example, the present invention is not limited to fans and can be applied to axial flow compressors and turbines. Also,
The present invention is not limited to jet engines and can be applied to all fluid machines having a cascade of blades.
【００２０】[0020]
【発明の効果】上述したように、本発明の伴流混合促進
翼は、伴流により生じる騒音と振動を低減し、かつエン
ジン全体の軸方向長さも短縮することができる等の優れ
た効果を有する。As described above, the wake mixing promotion blade of the present invention has excellent effects such as reduction of noise and vibration caused by wake and reduction of the axial length of the entire engine. Have.
【図１】本発明による伴流混合促進翼の模式的斜視図で
ある。FIG. 1 is a schematic perspective view of a wake mixing promotion blade according to the present invention.
【図２】翼列により生じる二次流れの比較図である。FIG. 2 is a comparative diagram of a secondary flow generated by blade rows.
【図３】翼下流側の速度分布（Ａ）と騒音特性（Ｂ）の
説明図である。FIG. 3 is an explanatory diagram of velocity distribution (A) and noise characteristics (B) on the downstream side of the blade.
【図４】動翼下流側に発生した伴流と静翼との干渉を示
すシミュレーション結果である。FIG. 4 is a simulation result showing the interference between the wake generated on the downstream side of the moving blade and the stationary blade.
１ 翼（動翼）、２ 主流、３ 伴流（ｗａｋｅ又は後
流）、４ 静翼、５ 翼間二次流れ、６ 伴流渦（後流
渦）、１０ 翼（伴流混合促進翼）、１０ａ 前縁、１
０ｂ 後縁、１１ 二次流れ1 blade (moving blade), 2 main flow, 3 wake (wake or wake), 4 stationary blade, 5 secondary flow between blades, 6 wake vortex (wake vortex), 10 wing (wake mixing promotion blade) 10a leading edge, 1
0b Trailing edge, 11 Secondary flow
Claims (3)
流流体機械を構成する翼（１０）であって、 後縁（１０ｂ）からの流出角が、基準の流出角に対し
て、半径方向の位置に応じて周方向に交互に増減し、こ
れにより二次流れ（１１）の作用で伴流の混合が促進さ
れるように、後縁部が形成されている、ことを特徴とす
る伴流混合促進翼。1. A blade (10) constituting an axial flow fluid machine having a plurality of blade rows adjacent to each other in an axial direction, wherein an outflow angle from a trailing edge (10b) is relative to a reference outflow angle. The trailing edge is formed so as to alternately increase and decrease in the circumferential direction according to the radial position, thereby promoting mixing of the wake by the action of the secondary flow (11). And a wake mixing promotion blade.
に応じて滑らかな波形に形成されている、ことを特徴と
する請求項１に記載の伴流混合促進翼。2. The wake mixing promotion blade according to claim 1, wherein the trailing edge (10b) is formed in a smooth waveform according to a position in the radial direction.
又はタービンである、ことを特徴とする請求項１に記載
の伴流混合促進翼。3. The axial fluid machine comprises a fan, a compressor,
The wake mixing promotion blade according to claim 1, which is a turbine.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| JP2002026586A JP2003227302A (en) | 2002-02-04 | 2002-02-04 | Blade for promoting wake mixing |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| JP2002026586A JP2003227302A (en) | 2002-02-04 | 2002-02-04 | Blade for promoting wake mixing |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| JP2003227302A true JP2003227302A (en) | 2003-08-15 |
Family
ID=27748373
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| JP2002026586A Pending JP2003227302A (en) | 2002-02-04 | 2002-02-04 | Blade for promoting wake mixing |
Country Status (1)
| Country | Link |
|---|---|
| JP (1) | JP2003227302A (en) |
Cited By (13)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JP2005194923A (en) * | 2004-01-06 | 2005-07-21 | Ishikawajima Harima Heavy Ind Co Ltd | Compressor moving blade |
| WO2007116621A1 (en) | 2006-04-07 | 2007-10-18 | Ihi Corporation | Axial flow fluid device and blade |
| EP2014870A2 (en) * | 2007-07-09 | 2009-01-14 | General Electric Company | Airfoil for use in rotary machines and method for fabricating same |
| US7891943B2 (en) | 2005-11-29 | 2011-02-22 | Ishikawajima-Harima Heavy Industries, Co. Ltd. | Stator cascade of turbo type fluid machine |
| JP2011247261A (en) * | 2010-05-28 | 2011-12-08 | General Electric Co <Ge> | System and method for enhanced turbine wake mixing via fluidic-generated vortices |
| US8657561B2 (en) | 2009-09-24 | 2014-02-25 | Rolls-Royce Plc | Variable shape rotor blade |
| EP2713008A1 (en) * | 2012-10-01 | 2014-04-02 | Rolls-Royce plc | Aerofoil for axial-flow machine with a cambered trailing edge |
| US8721280B2 (en) | 2008-01-07 | 2014-05-13 | Daikin Industries, Ltd. | Propeller fan |
| JP2015503694A (en) * | 2011-12-22 | 2015-02-02 | ゼネラル・エレクトリック・カンパニイ | Wing for wake desensitization and manufacturing method thereof |
| WO2015054023A1 (en) * | 2013-10-08 | 2015-04-16 | United Technologies Corporation | Detuning trailing edge compound lean contour |
| JP2015075062A (en) * | 2013-10-11 | 2015-04-20 | 株式会社日立製作所 | Axial flow type blade, and wind power generation apparatus using the same |
| GB2529757A (en) * | 2014-07-03 | 2016-03-02 | Snecma | Undulating stator for reducing the noise produced by interaction with a rotor |
| US11795823B2 (en) | 2019-02-07 | 2023-10-24 | Ihi Corporation | Method for designing vane of fan, compressor and turbine of axial flow type, and vane obtained by the designing |
-
2002
- 2002-02-04 JP JP2002026586A patent/JP2003227302A/en active Pending
Cited By (21)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
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