JPS5813758B2 - turbo blower impeller - Google Patents
turbo blower impellerInfo
- Publication number
- JPS5813758B2 JPS5813758B2 JP51148090A JP14809076A JPS5813758B2 JP S5813758 B2 JPS5813758 B2 JP S5813758B2 JP 51148090 A JP51148090 A JP 51148090A JP 14809076 A JP14809076 A JP 14809076A JP S5813758 B2 JPS5813758 B2 JP S5813758B2
- Authority
- JP
- Japan
- Prior art keywords
- blade
- blades
- flow
- turbo blower
- impeller
- 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
Links
Landscapes
- Structures Of Non-Positive Displacement Pumps (AREA)
Description
【発明の詳細な説明】 本発明はターボ送風機の羽根車に関するものである。[Detailed description of the invention] The present invention relates to an impeller for a turbo blower.
一般に、ターボ送風機等における理論性能は第１図に実
線で示される。Generally, the theoretical performance of a turbo blower or the like is shown by a solid line in FIG.
つまり理論ヘッドから羽根車内における滑り、流動損失
、衝突損失を差し引いたものが実際のヘッドとなり、通
常は第１図に示す如く山形のカーブとなる。In other words, the actual head is obtained by subtracting the slippage, flow loss, and collision loss within the impeller from the theoretical head, and usually forms a chevron-shaped curve as shown in FIG.
第１図において、衝突損失が大きくなると山形の形状が
大きくなり、少流量時にはサージングが問題となり、大
流量側では効率の低下が問題となる。In FIG. 1, as the collision loss increases, the shape of the chevron becomes larger, surging becomes a problem when the flow rate is small, and a decrease in efficiency becomes a problem when the flow rate is large.
この衝突損失は特に、一枚の連続した板から成形される
翼の入口における衝突損失で流量の増大に伴ない、第２
図、第３図に示す如く翼の圧力側に流れが突き当り負圧
側ではく離を生じる現象である。This collision loss is particularly the collision loss at the inlet of a blade formed from a single continuous plate, and as the flow rate increases, the second
As shown in Fig. 3, this is a phenomenon in which the flow impinges on the pressure side of the blade and causes separation on the negative pressure side.
第２図は流量が減少した場合、第３図は流量が増大した
場合を示す。FIG. 2 shows a case where the flow rate decreases, and FIG. 3 shows a case where the flow rate increases.
このような問題を解決するために例えば特公昭４８−３
７５２４号にみられるように翼に通気隙間を穿設して低
流量域を改善したものがある。In order to solve such problems, for example,
As seen in No. 7524, there is a type that improves the low flow area by providing ventilation gaps in the blades.
また軸流送風機においては遠心理論と翼理論の差はある
が特公昭４０−１６１８５号によれば、翼にスリットを
設け大流量側における圧力及び効率を改善している例が
ある。Regarding axial flow blowers, although there is a difference between centrifugal theory and blade theory, according to Japanese Patent Publication No. 40-16185, there is an example in which slits are provided in the blades to improve pressure and efficiency on the high flow rate side.
ところがこれらは大流量側を改善したものは少流量側で
は極端に圧力が下がったり、少流量域を改善したものは
大流量側で圧力が下がっている、などの欠点があった。However, these have drawbacks such as those with improved high flow rate side have extremely low pressure on low flow rate side, and those with improved low flow rate area have low pressure on high flow rate side.
本発明は、羽根を少くとも三分割し、互に流れに直角方
向に間隙を持たせ、かつ、流れ方向に沿って交互にくい
ちがって配備することにより、従来のものの上記の欠点
を除き、大流量域においても少流量域においても流れの
はくりを防止し、圧力低下を防ぎ効率向上をはかること
ができるターボ送風機の羽根車を提供することを目的と
するものである。The present invention eliminates the above-mentioned drawbacks of the conventional blades by dividing the blade into at least three parts, leaving a gap between them in the direction perpendicular to the flow, and arranging them alternately and differently along the flow direction. It is an object of the present invention to provide an impeller for a turbo blower that can prevent flow separation in both a flow rate region and a low flow rate region, prevent a pressure drop, and improve efficiency.
本発明は、ターボ送風機の各羽根を羽根に沿う流れの方
向に沿って少くとも三個の部分羽根にて構成し、隣接す
る各部分羽根は互に接触せずに羽根間隙を有して配設さ
れ、前記部分羽根が流れの方向に沿って、交互にくいち
がって配備されていることを特徴とするターボ送風機羽
根車である。In the present invention, each blade of a turbo blower is composed of at least three partial blades along the flow direction along the blade, and each adjacent partial blade is arranged with a blade gap without contacting each other. The turbo blower impeller is characterized in that the partial blades are arranged alternately and differently along the flow direction.
本発明を実施例につき図面を用いて説明すれば、第４図
において、ある一枚の羽根４は流れの方向（羽根４の根
本から先へ向かう方向）に沿って三つの部分羽根に分割
され、隣接する分割羽根は第一分割羽根１、第二分割羽
根２及び第三分割羽根３相互の間に、流れの方向に沿っ
てｌ１及びｌ２なるオーバーラップ、流れに直角な方向
に沿ってＳ１及びＳ２なる羽根間隙を有し、交互にくい
ちがって配備されている。To explain the present invention with reference to an embodiment of the drawing, in FIG. 4, one blade 4 is divided into three partial blades along the flow direction (direction from the root of the blade 4 to the tip). , the adjacent divided blades have an overlap between the first divided blade 1, the second divided blade 2, and the third divided blade 3, which is 11 and 12 along the flow direction, and S1 along the direction perpendicular to the flow. and S2, and are arranged alternately and differently.
ｒ及びＲは羽根車の内径及び外径を示す。r and R indicate the inner diameter and outer diameter of the impeller.
羽根４の羽根に沿った全長をＬとする。Let L be the total length of the blade 4 along the blade.
オーバーラップ量ｌ１，ｌ２羽根間隙Ｓ， ， Ｓ２は
風量、圧力、回転数、羽根形状、寸法などにより適宜選
ばれるが、
ｌ１及び２２−（０〜０．２）Ｌ
Ｓ１及びＳ２＝（０．０１〜０． ０ ８ ） Ｌ程度
が好ましい。The amount of overlap l1, l2 blade gaps S, , S2 are appropriately selected depending on the air volume, pressure, rotation speed, blade shape, dimensions, etc., and l1 and 22 - (0 to 0.2) L S1 and S2 = (0. 01 to 0.08) L is preferable.
分割により形成される羽根間隙の位置は第２図又は第３
図によりはくり、渦流の生じ易い場所を選ぶ。The position of the blade gap formed by division is shown in Figure 2 or 3.
Select a location where peeling and eddies are likely to occur according to the diagram.
このように構成された羽根車を用いたターボ送風機を運
転すれば、羽根４に沿って流れが外方に進む場合、挾い
羽根間隙を通過する気体は羽根４０表面から裏面へ又は
裏面から表面へ噴出し、エジエクタ効果によってはくり
、渦流を防止しまた羽根に衝突する流れの向きを調整し
て衝突を緩和し、これらによる損失を防止することがで
きる。When a turbo blower using an impeller configured in this way is operated, when the flow proceeds outward along the blades 4, the gas passing through the gap between the blades flows from the surface of the blade 40 to the back surface or from the back surface to the surface. It is possible to prevent losses caused by jetting out to the blade, peeling off due to the ejector effect, preventing eddy currents, and adjusting the direction of the flow that impinges on the blades to alleviate collisions.
大流量の場合でも少流量の場合でも、はくり、渦流衝突
などによる流れの乱れを生ずる部分に予め羽根間隙が設
けられエジエクタ効果により損失を防ぐので、大流量か
ら少流量の全域にわたって圧力特性及び効率を著しく向
上せしめることができる。Regardless of whether the flow rate is large or small, vane gaps are provided in advance in areas where flow turbulence occurs due to peeling, vortex collision, etc., and the ejector effect prevents loss, so the pressure characteristics and Efficiency can be significantly improved.
即ち、大流量時には、羽根の前側が負圧となってはくり
を生じ易いが、圧力側から羽根隙間Ｓ２を通って負圧側
に流体が流れ込みはくりを有効に防止する。That is, when the flow rate is large, the front side of the blade becomes negative pressure and peeling is likely to occur, but fluid flows from the pressure side to the negative pressure side through the blade gap S2, effectively preventing peeling.
少流量時には、逆に羽根の後側が負圧となってはくりを
生じ易いが、圧力側から羽根隙間Ｓ１を通って負圧側は
流体が流れ込みはくりを有効に防止する。When the flow rate is small, on the contrary, the rear side of the blade becomes negative pressure, which tends to cause peeling, but fluid flows from the pressure side through the blade gap S1 to the negative pressure side, effectively preventing peeling.
このように分割羽根１，２．３を交互にくいちがわせる
ことにより、流量の犬少にかかわらず、即ち、羽根の前
側後側の倒れの側にはくりを生じようとしても、その発
生を防止し、全流量域にわたってはくりを防止し、圧力
特性の向上、効率の向上をはかることができる。By alternating the divided blades 1, 2, and 3 in this way, no matter how small or small the flow rate is, in other words, even if the blades tend to bulge on the front or rear side, this can be prevented from occurring. However, it is possible to prevent peeling over the entire flow range, improve pressure characteristics, and improve efficiency.
その一例を第１図に点線Ａにて示す。An example of this is shown by dotted line A in FIG.
第５図は別の実施例で、羽根車の形状によって、回転方
向に対して分割羽根の重ね方を異ならしめることもでき
る。FIG. 5 shows another embodiment, and depending on the shape of the impeller, the way the divided blades are overlapped in the rotation direction can be made different.
羽根車が長い場合は各流量に応じてはくり、渦流、衝突
の起こる場所が異なるので、この位置に合わせて羽根間
隙を設けるよう羽根を四分割以上にすることもできる。If the impeller is long, the locations where peeling, eddies, and collisions occur will vary depending on the flow rate, so the blades can be divided into four or more sections to provide gaps between the blades to suit these locations.
本発明により、大流量から少流量にわたってはくり、渦
流、衝突などによる流れの乱れを防止し、流量の全領域
にわたって圧力特性を改善し、効率を著しく向上するこ
とができるターボ送風機羽根車を提供することができ、
実用上極めて犬なる効果を有するものである。The present invention provides a turbo blower impeller that can prevent flow disturbances due to peeling, vortices, collisions, etc. from large flow rates to small flow rates, improve pressure characteristics over the entire flow range, and significantly improve efficiency. can,
In practical terms, this has an extremely effective effect.
第１図はターボ送風機の性能曲線、第２図及び第３図は
従来の羽根車における流れの乱れを示す説明図、第４図
及び第５図は本発明のそれぞれ異なる実施例の部分断面
図である。
１，２，３・・・・・・分割羽根、４・・・・・・羽根
、Ｓ１，Ｓ２・・・・・・間隙、ｌ１，ｌ２・・・・・
・オーバーラップ。Fig. 1 is a performance curve of a turbo blower, Figs. 2 and 3 are explanatory diagrams showing flow turbulence in a conventional impeller, and Figs. 4 and 5 are partial cross-sectional views of different embodiments of the present invention. It is. 1, 2, 3...Divided blade, 4...Blade, S1, S2...Gap, l1, l2...
·Overlap.
Claims (1)
沿って少くとも三個の部分羽根にて構成し、隣接する各
部分羽根は互に接触せずに羽根間隙を有して配設され、
前記部分羽根が流れの方向に沿って、交互にくいちがっ
て配備されていることを特徴とするターボ送風機羽根車
。 ２ 分割数が三分割である特許請求の範囲第１項記載の
羽根車。 ３ 羽根間隙が羽根全長のほぼ０．０１〜０．０８倍で
ある特許請求の範囲第１項又は第２項記載の羽根車。 ４ 隣接する各部分羽根の流れの方向に沿ったオーバー
ラップ量が、羽根全長のほぼ０〜０．２倍である特許請
求の範囲第１項、第２項又は第３項記載の羽根車。[Claims] 1. Each blade of a turbo blower is composed of at least three partial blades along the direction of flow along the blade, and each adjacent partial blade does not contact each other and has a gap between the blades. arranged with
A turbo blower impeller characterized in that the partial blades are arranged alternately and differently along the flow direction. 2. The impeller according to claim 1, wherein the number of divisions is three. 3. The impeller according to claim 1 or 2, wherein the blade gap is approximately 0.01 to 0.08 times the total length of the blades. 4. The impeller according to claim 1, 2, or 3, wherein the amount of overlap of each adjacent partial blade in the flow direction is approximately 0 to 0.2 times the total length of the blade.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| JP51148090A JPS5813758B2 (en) | 1976-12-09 | 1976-12-09 | turbo blower impeller |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| JP51148090A JPS5813758B2 (en) | 1976-12-09 | 1976-12-09 | turbo blower impeller |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| JPS5372206A JPS5372206A (en) | 1978-06-27 |
| JPS5813758B2 true JPS5813758B2 (en) | 1983-03-15 |
Family
ID=15445004
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| JP51148090A Expired JPS5813758B2 (en) | 1976-12-09 | 1976-12-09 | turbo blower impeller |
Country Status (1)
| Country | Link |
|---|---|
| JP (1) | JPS5813758B2 (en) |
Families Citing this family (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPS6128796A (en) * | 1984-07-19 | 1986-02-08 | Nippon Kikai Gijutsu Kk | Impeller for blower |
| AT503184B1 (en) * | 2006-02-14 | 2009-02-15 | Hermann Riegerbauer | SUBJECT WATER WHEEL |
Citations (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US2753808A (en) * | 1950-02-15 | 1956-07-10 | Kluge Dorothea | Centrifugal impeller |
-
1976
- 1976-12-09 JP JP51148090A patent/JPS5813758B2/en not_active Expired
Patent Citations (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US2753808A (en) * | 1950-02-15 | 1956-07-10 | Kluge Dorothea | Centrifugal impeller |
Also Published As
| Publication number | Publication date |
|---|---|
| JPS5372206A (en) | 1978-06-27 |
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