JPS5867999A - Moving vane structure in axial flow type fluid machine - Google Patents
Moving vane structure in axial flow type fluid machineInfo
- Publication number
- JPS5867999A JPS5867999A JP16417281A JP16417281A JPS5867999A JP S5867999 A JPS5867999 A JP S5867999A JP 16417281 A JP16417281 A JP 16417281A JP 16417281 A JP16417281 A JP 16417281A JP S5867999 A JPS5867999 A JP S5867999A
- Authority
- JP
- Japan
- Prior art keywords
- moving vane
- flow
- vane
- boundary layer
- 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.)
- Pending
Links
- 239000012530 fluid Substances 0.000 title claims abstract description 12
- 150000001875 compounds Chemical class 0.000 description 1
- 230000006835 compression Effects 0.000 description 1
- 238000007906 compression Methods 0.000 description 1
- 238000005034 decoration Methods 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 210000000744 eyelid Anatomy 0.000 description 1
- 238000000034 method Methods 0.000 description 1
- 239000011435 rock Substances 0.000 description 1
- 238000000926 separation method Methods 0.000 description 1
Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
- F04D—NON-POSITIVE-DISPLACEMENT PUMPS
- F04D29/00—Details, component parts, or accessories
- F04D29/26—Rotors specially for elastic fluids
- F04D29/32—Rotors specially for elastic fluids for axial flow pumps
- F04D29/38—Blades
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
- F01D5/12—Blades
- F01D5/14—Form or construction
- F01D5/141—Shape, i.e. outer, aerodynamic form
- F01D5/145—Means for influencing boundary layers or secondary circulations
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Physics & Mathematics (AREA)
- Fluid Mechanics (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
Abstract
Description
【発明の詳細な説明】
本発明は細流送風機及び細流圧縮機などの軸流形流体機
械における動翼′##造に関し、さらに峰しくは動翼の
翼面上に発生する境界層流れを制御するようにしたもの
である。DETAILED DESCRIPTION OF THE INVENTION The present invention relates to the structure of moving blades in axial flow fluid machines such as trickle blowers and trickle compressors, and furthermore, to control the boundary layer flow generated on the peaks or blade surfaces of the rotor blades. It was designed to do so.
従来のe+流形流体機における動li&儒造において、
翼面上に発生する境界層tlJ御するものとしては動翼
の表面に多数の孔を設けそこからJK面の境界層を吸い
込んだり、動Xを複葉にしたりする方法がある。In the conventional e+ flow type fluid machine,
To control the boundary layer tlJ generated on the blade surface, there are methods such as providing a large number of holes on the surface of the rotor blade and sucking the boundary layer of the JK surface through the holes, or making the rotor X a compound blade.
本発明は動翼上の境界層流れt−m流することによって
流体性能を同上させると共に、動翼とケーシング閲の隙
間を通って流れる洩れ菫も同時に減少させて効率同上を
図るようにした@流式流体機械における動翼m!を提供
することを目的とするもので、細流形流体慎械の動翼上
にリプ1c取り付け、翼面上の境界層流れt−整流する
ようにし友ものである。The present invention improves the fluid performance by flowing the boundary layer flow t-m over the rotor blade, and simultaneously reduces the leakage violet flowing through the gap between the rotor blade and the casing blade, thereby achieving the same efficiency. Moving blades in flow-type fluid machines m! The purpose is to provide a lip 1c on the rotor blade of a trickle type fluid machine to rectify the boundary layer flow on the blade surface.
軸流圧#慎の性NO同上を図るにr!翼面上に形成され
る境界層のi!tll飾が重要であり、本発明はその一
手段であるが、本発明によれば@流形流体機械の効率同
上に大きな効果があるだけでなく、流れei流すること
によってサージング特性も向上させることができる。Axial flow pressure i! of the boundary layer formed on the wing surface. tll decoration is important, and the present invention is one means for that purpose.According to the present invention, not only is there a great effect on the efficiency of flow type fluid machines, but also the surging characteristics are improved by flowing the flow. be able to.
以下を本発明を@流圧動機の場曾全例にと91g1図お
よび第2図によシ醗明する。The present invention will be explained below using a complete example of a hydraulic pressure machine, with reference to Figures 91g1 and 2.
細流圧縮機ケーシング内の流れtl′iJK[fD及び
ケージング壁付近の境界層流れとそれ以外の粘性をもた
ないポテンシャル流れとの二つに分けて考えることがで
きる。圧縮機での摩掬損失はこの境界層内で生じるので
、この境界層を制御することによって大巾に摩擦損失を
減少させることができる。The flow tl'iJK[fD in the trickle compressor casing can be divided into two parts: the boundary layer flow near the casing wall, and the other potential flow that has no viscosity. Since frictional losses in the compressor occur within this boundary layer, frictional losses can be greatly reduced by controlling this boundary layer.
圧**の動翼上における境界層流れの典型的なパターン
が第1図に示されている。図において、1はケーシング
、2はシャ7)、3iシヤフト2に取9付けられた動翼
で、このm萬3の翼面上の開瞼5が境界層流れを表わし
ている。図に示すように、動JK3の元端に近ずつ程遠
心力の影響を強く受けるので、動翼3の先端付近での境
界ノー流れ5はかな9半径方回に曲げられる。従って、
境界層流れ5は動翼先端の方へ片沓っていき、動翼先端
付近で二次流れが生じ大きな損失となる。ま九、流れが
片をるため動#!3を通過した流れが靜翼4に流入する
際、その流入角が静翼上で一足にならない。この流入角
の牛後方向に対する不均一性は大きな衝突損失を生じる
。A typical pattern of boundary layer flow over a rotor blade at pressure ** is shown in FIG. In the figure, 1 is a casing, 2 is a rotor blade 9 attached to the shaft 2, and the open eyelid 5 on the blade surface of this mman 3 represents a boundary layer flow. As shown in the figure, the closer to the base end of the rotor blade 3, the stronger the influence of the centrifugal force is, so the boundary flow 5 near the tip of the rotor blade 3 is bent into a radial direction. Therefore,
The boundary layer flow 5 flows toward the tip of the rotor blade, and a secondary flow occurs near the tip of the rotor blade, resulting in a large loss. Makin, the flow is moving #! When the flow that has passed through the stationary blade 3 flows into the stationary blade 4, its inflow angle is not equal to one foot on the stationary blade. This non-uniformity of the inflow angle in the rearward direction causes a large collision loss.
こうした流れの片寄シをなくシ、流れを[流するように
したのが本発明である。s2図にその概略を示す。図に
おいて、2はmfL圧−慎のシャフト、3は!ItlX
、6は動翼3の翼面上に賊り付けた整流用のリプで、こ
のリプ6はほぼ軸方向に形成されている。現在問題とな
るのは境界I−だけであるので、リプ6の爾さはIIJ
JIjL上の境界層の厚みと同程匿(通常2〜3關)と
しである。このリブ6會設けることによって動翼上の視
界層t−m流し、静翼に均一な流入角で流れ込むように
することができるので1衝突屓矢を減らすことができる
。ま友、このli流リプ6は境界層流れが牛後方向に曲
げられるのを抑える拗きをするので、二次流れ全防止す
ることができると共に、ケーシング壁と動翼3の隙間を
通って漏れる童も少なくすることができ、効率を同上さ
せることができる。このリプ6は動JIK3の一枚に対
し5〜10本程度とする。The present invention eliminates this bias in the flow and allows the flow to flow. The outline is shown in figure s2. In the figure, 2 is the mfL pressure shaft, and 3 is! ItlX
, 6 is a lip for rectification attached to the blade surface of the rotor blade 3, and this lip 6 is formed approximately in the axial direction. Currently, only boundary I- is a problem, so the severity of reply 6 is IIJ
The thickness of the boundary layer on JIjL is approximately the same (usually 2 to 3 degrees). By providing these six ribs, it is possible to flow the visibility layer t-m on the rotor blade and flow into the stationary blade at a uniform inflow angle, thereby reducing the number of collisions. Friend, this LI flow lip 6 suppresses the boundary layer flow from being bent in the backward direction, so it is possible to completely prevent secondary flow and also to prevent the flow from passing through the gap between the casing wall and the rotor blade 3. It is also possible to reduce the number of children who are left behind, thereby increasing efficiency. The number of reps 6 is about 5 to 10 per sheet of dynamic JIK 3.
ま友、整流のし方が急激であると逆に大きな抵抗になり
摩擦損失になるため、前記リプ6I/i、動翼30先遇
に近いもの程圧縮磯シャフト2とのなす角が大きくなる
ようにしている。Friend, if the rectification is sudden, it will cause a large resistance and friction loss, so the closer the rotor blade 30 is to the above-mentioned Lip 6I/i, the larger the angle it makes with the compression rock shaft 2. That's what I do.
本発明は、動翼上にリプを取付けるように構成したので
、流体性能的には境界層流れtki流することができ、
したがって、動翼元端付近での二次流れ損失を少なくす
ることができると共に、動翼先端の隙間からの洩れ損失
をも少なくすることができ、大幅な効率向上1達成する
ことができるという効果がある。また、静翼への流入角
もコントロールできるので静翼での衝突損失も者しく減
少し、流体性Xt回上させることができる。さらに、本
発明ではサージングに対しても有利である。即ち、流れ
の整流によりサージングの引き金ともなる境界層の剥離
の防止にも効果があるので、サージングに関しても従来
のものに比べ格段に優れている。In the present invention, since the lip is attached to the rotor blade, boundary layer flow tki can flow in terms of fluid performance.
Therefore, it is possible to reduce the secondary flow loss near the root end of the rotor blade, and also to reduce the leakage loss from the gap at the tip of the rotor blade, resulting in a significant efficiency improvement. There is. Furthermore, since the inflow angle to the stator vane can be controlled, the collision loss at the stator vane can be significantly reduced, and the fluidity Xt can be increased. Furthermore, the present invention is also advantageous against surging. In other words, the rectification of the flow is effective in preventing separation of the boundary layer, which is a trigger for surging, and is therefore far superior to conventional systems in terms of surging.
第1図は動翼上における境界層流れのパターンを説明す
るための軸流圧組慎の概略図、第2図は本発明の構造【
示す概略図である。
3・・・m萬、5・・・境界層訛れ、6・・・リプ。
vi i 目Figure 1 is a schematic diagram of an axial flow pressure assembly to explain the boundary layer flow pattern on the rotor blade, and Figure 2 is the structure of the present invention.
FIG. 3... m 10,000, 5... boundary layer accent, 6... reply. vi i eye
Claims (1)
境界ノ曽流れ金歴流するようにしたことを特徴とする軸
流形流体機械における動萬#It造。This is an axial flow type fluid machine structure, characterized in that a lip is attached to the wJ band of the axial flow type fluid machine so that the flow flows across the boundary on the blade surface.
Priority Applications (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
JP16417281A JPS5867999A (en) | 1981-10-16 | 1981-10-16 | Moving vane structure in axial flow type fluid machine |
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
JP16417281A JPS5867999A (en) | 1981-10-16 | 1981-10-16 | Moving vane structure in axial flow type fluid machine |
Publications (1)
Publication Number | Publication Date |
---|---|
JPS5867999A true JPS5867999A (en) | 1983-04-22 |
Family
ID=15788090
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
JP16417281A Pending JPS5867999A (en) | 1981-10-16 | 1981-10-16 | Moving vane structure in axial flow type fluid machine |
Country Status (1)
Country | Link |
---|---|
JP (1) | JPS5867999A (en) |
Cited By (11)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
NL1012753C2 (en) * | 1999-07-30 | 2001-02-01 | Chromalloy Holland B V | Gas turbine energy components with effectively reduced drag comprise a number of riblets on the gas flow surface of specific height, width and length |
WO2001009405A1 (en) * | 1999-07-30 | 2001-02-08 | Chromalloy Holland B.V. | Drag reduction for gas turbine engine components |
US6454524B1 (en) | 1998-07-21 | 2002-09-24 | Seiko Instruments Inc. | Vacuum pump and vacuum apparatus |
EP1371813A1 (en) * | 2002-06-13 | 2003-12-17 | ALSTOM (Switzerland) Ltd | Blading of a turbomachine |
JP2005194923A (en) * | 2004-01-06 | 2005-07-21 | Ishikawajima Harima Heavy Ind Co Ltd | Compressor moving blade |
JP2007040202A (en) * | 2005-08-03 | 2007-02-15 | Mitsubishi Heavy Ind Ltd | Impeller and propeller fan |
US20100124500A1 (en) * | 2008-11-14 | 2010-05-20 | Snecma | Turbomachine having an unducted fan provided with air guide means |
US7815418B2 (en) | 2005-08-03 | 2010-10-19 | Mitsubishi Heavy Industries, Ltd. | Shroud and rotary vane wheel of propeller fan and propeller fan |
EP2492514A1 (en) * | 2009-10-19 | 2012-08-29 | Mitsubishi Heavy Industries, Ltd. | Heat exchange module for vehicle |
FR3081913A1 (en) * | 2018-06-04 | 2019-12-06 | Safran Aircraft Engines | BLADE OF TURBOMACHINE COMPRISING AN ANTI-VIRTUAL FIN |
EP3591238A1 (en) * | 2018-07-05 | 2020-01-08 | Xylem Europe GmbH | Axial flow fan and fan guard for a motor cooling assembly |
-
1981
- 1981-10-16 JP JP16417281A patent/JPS5867999A/en active Pending
Cited By (17)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US6454524B1 (en) | 1998-07-21 | 2002-09-24 | Seiko Instruments Inc. | Vacuum pump and vacuum apparatus |
NL1012753C2 (en) * | 1999-07-30 | 2001-02-01 | Chromalloy Holland B V | Gas turbine energy components with effectively reduced drag comprise a number of riblets on the gas flow surface of specific height, width and length |
WO2001009405A1 (en) * | 1999-07-30 | 2001-02-08 | Chromalloy Holland B.V. | Drag reduction for gas turbine engine components |
US6666646B1 (en) | 1999-07-30 | 2003-12-23 | Chromalloy Holland B.V. | Drag reduction for gas turbine engine components |
EP1371813A1 (en) * | 2002-06-13 | 2003-12-17 | ALSTOM (Switzerland) Ltd | Blading of a turbomachine |
JP2005194923A (en) * | 2004-01-06 | 2005-07-21 | Ishikawajima Harima Heavy Ind Co Ltd | Compressor moving blade |
JP4617674B2 (en) * | 2004-01-06 | 2011-01-26 | 株式会社Ihi | Compressor blade |
US7815418B2 (en) | 2005-08-03 | 2010-10-19 | Mitsubishi Heavy Industries, Ltd. | Shroud and rotary vane wheel of propeller fan and propeller fan |
JP2007040202A (en) * | 2005-08-03 | 2007-02-15 | Mitsubishi Heavy Ind Ltd | Impeller and propeller fan |
US7909572B2 (en) | 2005-08-03 | 2011-03-22 | Mitsubishi Heavy Industries, Ltd. | Shroud and rotary vane wheel of propeller fan and propeller fan |
US20100124500A1 (en) * | 2008-11-14 | 2010-05-20 | Snecma | Turbomachine having an unducted fan provided with air guide means |
US8221081B2 (en) * | 2008-11-14 | 2012-07-17 | Snecma | Turbomachine having an unducted fan provided with air guide means |
EP2492514A1 (en) * | 2009-10-19 | 2012-08-29 | Mitsubishi Heavy Industries, Ltd. | Heat exchange module for vehicle |
EP2492514A4 (en) * | 2009-10-19 | 2013-08-21 | Mitsubishi Heavy Ind Ltd | Heat exchange module for vehicle |
FR3081913A1 (en) * | 2018-06-04 | 2019-12-06 | Safran Aircraft Engines | BLADE OF TURBOMACHINE COMPRISING AN ANTI-VIRTUAL FIN |
EP3591238A1 (en) * | 2018-07-05 | 2020-01-08 | Xylem Europe GmbH | Axial flow fan and fan guard for a motor cooling assembly |
WO2020008007A1 (en) * | 2018-07-05 | 2020-01-09 | Xylem Europe Gmbh | Axial flow fan and fan guard for a motor cooling assembly |
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