JPS62291499A - Vane pitch reverse type jet fan - Google Patents
Vane pitch reverse type jet fanInfo
- Publication number
- JPS62291499A JPS62291499A JP13699186A JP13699186A JPS62291499A JP S62291499 A JPS62291499 A JP S62291499A JP 13699186 A JP13699186 A JP 13699186A JP 13699186 A JP13699186 A JP 13699186A JP S62291499 A JPS62291499 A JP S62291499A
- Authority
- JP
- Japan
- Prior art keywords
- motor shaft
- hub casing
- reversed
- blade
- bevel gear
- 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
- 230000002441 reversible effect Effects 0.000 title claims abstract description 16
- 239000011295 pitch Substances 0.000 claims description 30
- 230000001105 regulatory effect Effects 0.000 claims description 4
- 238000009423 ventilation Methods 0.000 description 6
- 238000007664 blowing Methods 0.000 description 5
- 229920002545 silicone oil Polymers 0.000 description 4
- 230000000694 effects Effects 0.000 description 3
- 238000000034 method Methods 0.000 description 3
- 230000007423 decrease Effects 0.000 description 2
- 238000010586 diagram Methods 0.000 description 2
- 238000005452 bending Methods 0.000 description 1
- 230000033228 biological regulation Effects 0.000 description 1
- 230000005540 biological transmission Effects 0.000 description 1
- 238000004891 communication Methods 0.000 description 1
- 238000010276 construction Methods 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 239000000463 material Substances 0.000 description 1
- 230000000116 mitigating effect Effects 0.000 description 1
- 230000000149 penetrating effect Effects 0.000 description 1
- 230000035939 shock Effects 0.000 description 1
Landscapes
- Structures Of Non-Positive Displacement Pumps (AREA)
Abstract
Description
【発明の詳細な説明】
３、発明の詳細な説明
産業上の利用分野
本発明は、道路トンネル換気用などに用いる、翼ピッチ
（角度）自動反転式のジェットファンに関するものであ
る。Detailed Description of the Invention 3. Detailed Description of the Invention Field of Industrial Application The present invention relates to a jet fan of automatic blade pitch (angle) reversal type used for road tunnel ventilation.
従来の技術
道路トンネルの換気に、建設費の少ない、運転経費の安
い換気設備が要望されているが、各種換気方式の中でも
細流ファンを用いたジェットファンを配置した縦流式換
気方法が上記の要求に沿うものとして多く採用されてい
る。道路トンネル換気用ジェットファンには、ファンを
電動機の両端に取付けた２ファン方式と、１個のファン
でその翼ピッチｆ：１８０°反転して送風方向を反転さ
せるようにした方式とがある。従来、翼ピッチ反転式の
軸流ファンとして、たとえば第５図〜第６図に示すもの
が知られている。すなわち、正逆回転自在のモータのモ
ータ軸（１）に、ハブケーシング（２） ’！−ベアリ
ング（３）ヲ介して軸着し、そのハブケーシング（２）
に放射状に複数本の翼（４）を回転自在に収付け、その
取付軸（５）の先端部に傘歯車（６）を固設し、この傘
歯車（６）に噛合うよう大傘歯車（７）を前記モータ軸
（１）に固設し、かつ大傘歯車（７）の背面にストッパ
（８）を、またハブケーシング（２）内面に前記大傘歯
車（７）側のストッパ（８）と当接するストッパ（９）
を、諷取付角度により設定され、かつ正逆回転に対応す
る２箇所に配設している。モータ軸（１）の反転により
、大傘歯車（７）から具備の傘歯車（６）を経て翼（４
）が反転するととも罠、大傘歯車（７）側のストッパ（
８）が大傘歯車（７）の回転によりハブケーシング（２
）側のストッパ（９）に当接し、前記傘歯車（６）の回
転、すなわち翼（４）の反転が停止し、かつモータ軸（
１）の回転がハブケーシング（２）側、すなわち翼（４
ンに伝達される。上記において、翼（４）の区転が１８
００となる位置に、前記ハブケーシング（２）側の２箇
所のストッパ（９）が設けられる。さらにストッパ（８
）と（９）が当接する際に発生する衝撃を軽減するため
、ハブケーシング（２）にモータ軸（１）を中心とする
油室αＱを設け、この内部に円板（６）をモータ軸（１
）に固設して組込み、さらにその間隙にシリコン油＠を
封入して、前記円板但の回転に対するシリコン油＠の粘
性摩擦によって、反転起動時にハブケーシング（２）に
回転力を伝達して、ストッパ（８）と（９）との屈対速
度を小さくし、それにより両ヌトッパ（８）と（９）と
の当接により発生する衝撃を小さくするように構成して
いる。Conventional technology For ventilation of road tunnels, there is a demand for ventilation equipment with low construction costs and low operating costs. Among the various ventilation methods, the vertical flow ventilation method using a jet fan using a trickle fan is the one mentioned above. It is widely adopted as it meets the requirements. Jet fans for road tunnel ventilation include a two-fan type in which fans are attached to both ends of an electric motor, and a type in which a single fan has a blade pitch f of 180° and the direction of air flow is reversed. 2. Description of the Related Art Conventionally, as an axial flow fan of a reversible blade pitch type, for example, those shown in FIGS. 5 and 6 are known. In other words, the hub casing (2)'! -Axially mounted via a bearing (3) and its hub casing (2)
A plurality of blades (4) are rotatably housed in a radial manner, a bevel gear (6) is fixed to the tip of the mounting shaft (5), and a large bevel gear is fitted to mesh with the bevel gear (6). (7) is fixed to the motor shaft (1), a stopper (8) is provided on the back of the large bevel gear (7), and a stopper (8) on the large bevel gear (7) side is provided on the inner surface of the hub casing (2). Stopper (9) that comes into contact with 8)
are set according to the vertical mounting angle and are arranged at two locations corresponding to forward and reverse rotation. By reversing the motor shaft (1), the blade (4) passes from the large bevel gear (7) to the equipped bevel gear (6).
) is reversed, the trap and the stopper on the large bevel gear (7) side (
8) is rotated by the large bevel gear (7) to rotate the hub casing (2).
) side stopper (9), the rotation of the bevel gear (6), that is, the reversal of the blades (4) is stopped, and the motor shaft (
1) rotates toward the hub casing (2) side, that is, the blade (4).
transmitted to the In the above, the rotation of wing (4) is 18
Two stoppers (9) on the hub casing (2) side are provided at the position 00. Furthermore, the stopper (8
) and (9) come into contact, an oil chamber αQ centered around the motor shaft (1) is provided in the hub casing (2), and a disk (6) is inserted into the hub casing (2). (1
), and furthermore, silicone oil @ is sealed in the gap, and the rotational force is transmitted to the hub casing (2) at the time of reverse startup by the viscous friction of the silicone oil @ against the rotation of the disc. , the bending speed of the stoppers (8) and (9) is reduced, thereby reducing the impact generated by the contact between the two stoppers (8) and (9).
発明が解決しようとする問題点
上記のように構成し友翼ピッチ反転式軸流ファンにおい
ては、油室αＱ内へ封入したシリコン油（イ）の粘性が
大気温度の変化や、モータのモータ軸（１）から伝導さ
れる熱により変化しやすく、そのため衝撃緩和の性能が
低下しやすく不安定である。また第７図に示すごとく、
回転方向囚、送風方向（Ｂｌで運転中、翼（４）に対し
翼ピッチを低下させる方向（０にトルクが発生する。こ
のトルクはハブケーシング（２）をモータ軸（１）に対
して進角させるように作用し、結果として翼ピッチが低
下し、ファン性能の不安定化を招くという問題があった
。Problems to be Solved by the Invention In the axial-flow fan with the pitch reversal of the blades configured as described above, the viscosity of the silicone oil (a) sealed in the oil chamber αQ is affected by changes in atmospheric temperature and the motor shaft of the motor. (1) It tends to change due to the heat conducted from it, and as a result, the shock mitigation performance tends to deteriorate and is unstable. Also, as shown in Figure 7,
During operation in the rotating direction and the air blowing direction (Bl), a torque is generated in the direction (0) that reduces the blade pitch against the blade (4). This torque advances the hub casing (2) with respect to the motor shaft (1). There was a problem in that the blade pitch was reduced as a result, leading to unstable fan performance.
本発明は、従来の翼ピッチ反転式ジェットファンにおけ
る上記のごとき問題点を解決して、翼ピッチが低下せず
安定な送風性能を有する翼ピッチ反転式ジェットファン
を提供しようとするものである。The present invention aims to solve the above-mentioned problems in conventional jet fans with reversible blade pitches and to provide a jet fan with reversible blade pitches that does not reduce the blade pitch and has stable air blowing performance.
問題点を解決するための手段
上記の問題点を解決する九め、本発明の翼ピッチ反転式
ジェットファンは、正逆回転自在のモータのモータ軸に
軸着したハブケーシングに、放射状に偶数枚の翼を回転
自在に取付け、その取付軸を１本おきに長短２組の長さ
とし、かつその先端部にそれぞれ傘歯車を固設し、前記
２組の取付軸の傘歯車の各１組に噛合う傘歯車を前記モ
ータ軸に、そのモータ軸の反転により前記２組の取付軸
に対応する翼のピッチを互いに逆方向に反転するように
１対向して固設し、かつ具ピッチの反転角を規制し、反
転したモータ軸の回転を前記ハブケーシングに伝達する
手段を設は念軸流ファンを、円筒状ダクト内に配設した
ことを特徴とするものである。Means for Solving the Problems Ninthly, the blade pitch reversible jet fan of the present invention has an even number of blades radially mounted on a hub casing which is attached to the motor shaft of a motor that can freely rotate forward and backward. The blades are rotatably mounted, and every other mounting shaft has two sets of long and short lengths, and a bevel gear is fixed to the tip of each of the blades, and one set of bevel gears on each of the two sets of mounting shafts has a bevel gear. Meshing bevel gears are fixed to the motor shaft in such a way that the pitches of the blades corresponding to the two sets of mounting shafts are reversed in opposite directions when the motor shaft is reversed, and the tool pitch is reversed. The present invention is characterized in that a teleaxial flow fan is disposed within a cylindrical duct and has means for regulating the angle and transmitting the reversed rotation of the motor shaft to the hub casing.
作 用
本発明の翼ピッチ反転式ジェットファンにおいては、軸
流ファンがハブケーシングに偶数枚の翼を放射状に取付
け、１本おきに長短２組の長さの、朋記翼の取付軸の先
端部に傘歯車を固設し、前記取付軸の先端部の傘歯車の
１個おきの２組の各１組に、等しいギヤ比で噛合う傘歯
車を対向してモータ軸に固設して、モータ軸の回転方向
が反転した際、前記取付軸先端部の傘歯車すなわち翼が
、隣合う同士で互いに逆方向に１８０°反転するように
構成されているので、送風運転中に全ての翼に同じ方向
に発生する翼ピッチ低下トルクは、偶［ｋの翼のうちの
１枚おきの半数の翼においては、モータ軸に対してハブ
ケーシングを進角（先に進んで回転する）させるように
作用し、他の１枚おきの半数の翼においては遅角させる
ように作用することになり、これらの作用は大きさが等
しく、方向が反対であるため相殺して零となシ、これに
より運転中に翼ピッチが変化して性能が低下するという
問題は発生しない。In the blade pitch reversal type jet fan of the present invention, the axial flow fan has an even number of blades radially attached to the hub casing, and every other blade has two sets of long and short blades at the tips of the mounting shafts. A bevel gear is fixed to the motor shaft, and bevel gears meshing with every other two sets of bevel gears at the tip of the mounting shaft are fixed to the motor shaft so as to face each other and mesh with each other at an equal gear ratio. When the rotational direction of the motor shaft is reversed, the bevel gears or blades at the tip of the mounting shaft are configured so that adjacent ones rotate 180 degrees in opposite directions. The blade pitch reduction torque that occurs in the same direction as the blades causes the hub casing to advance (go forward and rotate) with respect to the motor shaft for every other half of the even [k blades]. The other half of every other blade acts to retard the angle, and since these effects are equal in magnitude and opposite in direction, they cancel each other out and become zero. Therefore, the problem that the blade pitch changes during operation and performance deteriorates does not occur.
実施例
本発明の一実施例を、第１図〜第４図に基づいて説明す
る。第４図に示すごとく、ジェットファンＩ２１）は、
円筒状ダクト圏内に直Ｉ＃駆動式の軸流ファン脅を取付
けて形成され、前記軸流ファン四は、正逆回転自在のモ
ータ（ハ）のモータ軸（７）に直妾羽根車（ホ）が取付
けられている。羽根車（ホ）は、第１図〜第３図に示す
ごとく、モータ軸（７）にベアリング勿＠を介して軸着
したハブケーシング（ト）に、偶数枚の翼＠を、その下
部の取付軸（７）によ）モータ軸（７）に対し垂直方向
に、放射状に、かつベアリングＩ３Ｄを介して回転自在
に取付けて形成されている。そして前記取付軸（１）は
、１本おきに長短の２組（３０ａ）（３０ｂ）の長さと
し、その先端部にそれぞれ傘歯車（３２ａＸ３２ｂ）を
固設し、この２組の取付軸（３０ａＸ３０ｂ）の傘歯車
（３２ａＸ３２ｂ）の各１組に噛合う傘歯車（３３ａ）
（３３ｂ）を、対向してモータ軸（ホ）へキー（３４ａ
）（３４ｂ）を用いて固設し、モータ軸四の反転により
傘歯車（３３ａＸ３３ｂ）を介して前記２組の、すなわ
ち、隣シ合う取付軸（３０ａＸ３０ｂ）の先端部の傘歯
車（３２ａＸ３２ｂ）が、そして翼（２９ａＸ２９ｂ）
のピッチ（取付角度）が、互いに逆方向に１８０°反転
するよう構成している。Embodiment An embodiment of the present invention will be explained based on FIGS. 1 to 4. As shown in Fig. 4, the jet fan I21) is
The axial fan 4 is formed by installing a direct I# drive type axial flow fan in the cylindrical duct area, and the axial fan 4 has a direct impeller (housing) attached to the motor shaft (7) of a motor (c) that can freely rotate in forward and reverse directions. ) is installed. As shown in Figures 1 to 3, the impeller (E) has an even number of blades attached to the hub casing (G), which is attached to the motor shaft (7) via a bearing. The mounting shaft (7) is formed so as to be rotatably mounted perpendicularly to the motor shaft (7), radially, and via a bearing I3D. Each of the mounting shafts (1) has two sets of long and short lengths (30a and 30b), each having a bevel gear (32aX32b) fixed at its tip, and these two sets of mounting shafts (30aX30b). ) Bevel gears (33a) that mesh with each set of bevel gears (32aX32b)
(33b) to the motor shaft (E) facing the key (34a).
) (34b), and by reversing the motor shaft 4, the two sets of bevel gears (32aX32b) at the tips of the adjacent mounting shafts (30aX30b) are connected via the bevel gears (33aX33b). , and wings (29aX29b)
The pitches (mounting angles) of the two are reversed by 180° in opposite directions.
次にハブケーシング（ハ）に、円板状で、中心部と中心
部から直径方向に所定角度で扇形状に空所側を設けた油
室形成板（至）を、モータ軸（至）を中心として液密状
急に内設し、前記油室形成板−の空所軸内に、モータ軸
（至）へキー的を用いて固設され直径方向に腕（３８ａ
Ｘ３８ｂ）を設けたヨーク側を嵌合して油室（４０ａＸ
４０ｂ）を形成し、前記腕（３８ａＸ３８ｂ）に油移動
月の孔（４１ａＸ４１ｂ） ’に：それぞれ設け、かつ
油室（４０ａＸ４０ｂ）にはシリコン油等の油を封入し
ている。ｔ４′２１４３はシールリングである。モータ
軸四の回転によりヨーク（３９）が回転して、腕（３８
ａＸ３８ｂ）が各油室（４０ａＸ４０ｂ）の扇形の半径
方向の一方の内壁面を押して（第３図架想線）、これに
よりハブケーシング（ト）に、モータ軸（７）の回転を
伝達し、ｊｌＬ翰が回転して送風する。Next, attach an oil chamber forming plate (to) to the hub casing (c), which is disc-shaped and has a fan-shaped cavity side at a predetermined angle in the diametrical direction from the center and the center, and connect the motor shaft (to) to the hub casing (c). The arm (38 a
Fit the yoke side with the oil chamber (40a
40b), and the arms (38aX38b) are provided with oil transfer holes (41aX41b), respectively, and the oil chamber (40aX40b) is filled with oil such as silicone oil. t4'2143 is a seal ring. The yoke (39) rotates due to the rotation of the motor shaft 4, and the arm (38) rotates.
aX38b) pushes one inner wall surface of the fan-shaped radial direction of each oil chamber (40aX40b) (phantom line in Figure 3), thereby transmitting the rotation of the motor shaft (7) to the hub casing (g), The jlL wing rotates and blows air.
このとき腕（３８ａ）（３８ｂ）の勧きは、腕（３８ａ
Ｘ３８ｂ）によって油室（４０ａＸ４０ｂ）が分画され
た（４０ａ、）と（４０ａ２） 、（４０ｂ＋ ）と（
４０ｂ２）の間で孔（４１ａ）（４１ｂ） を通じて油
が移動することによって可能になる。そして孔（４１ａ
Ｘ４１ｂ）の径を調整すれば、腕（３８ａＸ３８ｂ）の
移動方向（財）のｎ１１方の分画油室（４０ａ、Ｘ４０
ｂ、）に油圧が発生し、ハブケーシング（ハ）へ回転を
伝達しはじめ、しかもその油圧が徐々に低下することに
より、腕（３８ａＸ３８ｂ）は急激には油室（４０ａＸ
４０ｂ）の内壁面に当接せず、衝撃を発生することなく
、逆転起動が極めて円滑に行なわれる。At this time, the arm (38a) (38b) is
The oil chamber (40aX40b) was separated by (40a,), (40a2), (40b+) and (
40b2) through the holes (41a) and (41b). and hole (41a
By adjusting the diameter of X41b), the fractional oil chamber (40a, X40
Hydraulic pressure is generated in the hub casing (c), and as the oil pressure gradually decreases, the arm (38aX38b) suddenly moves to the oil chamber (40aX
40b), and the reverse start is performed extremely smoothly without any impact being generated.
この場合油圧を利用しているため油の粘性の影響を受け
ない。なお、上記ヨーク側の腕（３８ａＸ３８ｂ）に設
けた油移動用の孔（４１ａＸ４１ｂ）に代えて、油室形
成板（資）の本体外同部（３５ａ）を貫通して外部に、
分画油室（４０ａ 、）と（４０ａ２） 、（４０ｂ、
）と（４０ｂ２）ｔ−それぞれ弁を介して連通ずる連通
管（図示せず）を設けてもよい。In this case, since hydraulic pressure is used, it is not affected by the viscosity of the oil. In addition, instead of the oil movement hole (41aX41b) provided in the arm (38aX38b) on the yoke side, a hole is provided outside the body by penetrating the same part (35a) outside the main body of the oil chamber forming plate (material).
Fractionated oil chamber (40a,) and (40a2), (40b,
) and (40b2)t- may be provided with communication pipes (not shown) that communicate with each other via valves.
本実施例における軸流ファン＠は上記のごとく構成され
、かつ駆動されるが、モータ軸（イ）が反転し次とき下
記のように動作する。すなわち、モータ軸□□□が反転
すると、傘歯車（３３８Ｘ３３ｂ）が反転し、これが傘
歯車（３２ａ）（３２ｂ）に伝達され、隣り合う轟（２
９ａ）（２９ｂ）がそれぞれ逆方向にピッチを反転する
。The axial fan in this embodiment is constructed and driven as described above, but when the motor shaft (a) is reversed, it operates as follows. That is, when the motor shaft □□□ is reversed, the bevel gear (338X33b) is reversed, this is transmitted to the bevel gears (32a) (32b), and
9a) and (29b) each invert the pitch in the opposite direction.
それと同時に前記油室形成板（資）内でヨーク側が反転
し、油室（４０ａＸ４０ｂ）内を油の移動とは逆方向に
動きつつ、油田を発生して緩やかにハブケーシング（ト
）に反転を伝達して、免翰の逆転起動を行ない、これに
より送風方向を反転するとともに、翼翰のピッチ反転の
角度（１８０つが油室（４０ａＸ４０ｂ）の扇形の角度
によって規制される。送風中に翼翰に発生する謔ピッチ
低下トルクは、全てのｆｉ （２９ａ）（２９ｂ）で太
きさと方向が同じである。したがって、偶数の翼（２９
ａＸ２９ｂ）のうちの、１枚おきの半数の翼（２９ａ）
ま念は（２９ｂ）に発生した翼ピッチ低下トルクは、モ
ータ軸（７）に対してハブケーシング（至）を進角させ
るように作用し、他の１枚おきの半数の翼（２９ｂ）ま
たは（２９ａ）に発生した前記トルクは遅角させるよう
に作用し、この進角と遅角の作用は大きさが等しく方向
が反対であるため、相殺して零となり、送風運転中に翼
ピッチが変化し、性能が低下することはない。また本実
施例では、モータ軸（至）の回転のハブケーシング（至
）への伝達、および翼ピッチ反転角の規制を、°上記の
ごとく油室形成板−とヨーク（との組合せで行ない、そ
れにより油の粘性の変化等に何等影響されることなく、
衝撃を発生することなく、逆転起動を円滑に行なうこと
ができる。At the same time, the yoke side is reversed within the oil chamber forming plate (40a x 40b), and while moving in the opposite direction to the oil movement within the oil chamber (40a x 40b), an oil field is generated and the hub casing (g) is gently reversed. The information is transmitted to start the reversal of the fan blade, thereby reversing the direction of air blowing, and the pitch reversal angle of the blade blade (180 is regulated by the fan-shaped angle of the oil chamber (40a x 40b). The pitch reduction torque generated in the pitch reduction torque is the same in thickness and direction for all fi (29a) (29b).Therefore, for even numbered blades (29
aX29b), every other half of the wings (29a)
Actually, the blade pitch reduction torque generated at (29b) acts to advance the hub casing (to) with respect to the motor shaft (7), and the other half of the blades (29b) or The torque generated in (29a) acts to retard the angle, and since the advance and retard effects are equal in magnitude and opposite in direction, they cancel each other out and become zero, causing the blade pitch to change during the air blowing operation. There will be no change in performance. In addition, in this embodiment, the transmission of the rotation of the motor shaft to the hub casing and the regulation of the blade pitch reversal angle are performed by the combination of the oil chamber forming plate and the yoke as described above. As a result, it is not affected by changes in oil viscosity, etc.
Reverse start can be smoothly performed without generating impact.
なお本発明において、モータ軸（至）の回転全ハブケー
シング（ハ）へ緩やかに伝達し、かつ免ピッチ反転角を
規制する手段として、主計実施例のほか、温度変化の少
ない条件下では、第５図〜第６図に示す、油の粘性摩擦
とストッパを利用する方式を採用しうろことはいうまで
もない。In addition, in the present invention, as a means for gently transmitting the rotation of the motor shaft (to) to the entire hub casing (c) and regulating the pitch-free reversal angle, in addition to the master embodiment, under conditions with little temperature change, Needless to say, a method using the viscous friction of oil and a stopper as shown in FIGS. 5 to 6 is adopted.
発明の効果
本発明の翼ピッチ反転式ジェットファンでは、軸流ファ
ンが、翼ピッチ低下を起こすことが無く、モータ軸の反
転により、自動的に翼ピッチを反転して円滑に起動でき
、安定した正逆２方向の送風性能を発揮する。Effects of the Invention In the blade pitch reversible jet fan of the present invention, the axial flow fan does not cause a decrease in the blade pitch, and by reversing the motor shaft, the blade pitch can be automatically reversed and started smoothly, resulting in stable operation. Demonstrates air blowing performance in two directions: forward and reverse.
第１図は本発明の一実施例の要部を示す側縦断面図、第
２図は第１図の１−１線断面図、第３図は第１図の１−
１線断面図、第４図は本発明の一実施例の全体概略構成
図、第５図は従来例の要部を示す側断面図、第６図は第
５図の遺−厘線断面図、第７図は翼ピッチ低下トルク発
生の説明図である。
Ｇ！υ・・・ジェットファン、（支）・・・円筒状ダク
ト、輸・・・軸流ファン、（至）・・・モータ、（至）
・・・モータ軸、（７）・・・ハブケーシング、＠（２
９ａＸ２９ｂ） ・＝翼、ｍ （３０ａＸ３０ｂ） ＝
−取付軸、（３２ａＸ３２ｂ）−傘歯車、（３３ａＸ３
３ｂ）−傘歯車、（至）・・・油室形成板、酷・・・ヨ
ーク、（４０ａＸ４０ｂ）・・・油室第４図
第Ｓ図
第４図 −第７図FIG. 1 is a side vertical cross-sectional view showing essential parts of an embodiment of the present invention, FIG. 2 is a cross-sectional view taken along the line 1--1 in FIG. 1, and FIG.
4 is a general schematic configuration diagram of an embodiment of the present invention, FIG. 5 is a side sectional view showing main parts of a conventional example, and FIG. 6 is a sectional view taken along a line taken from FIG. 5. , FIG. 7 is an explanatory diagram of generation of blade pitch lowering torque. G! υ...Jet fan, (support)...Cylindrical duct, Transport...axial fan, (to)...motor, (to)
...Motor shaft, (7)...Hub casing, @(2
9aX29b) ・= wing, m (30aX30b) =
-Mounting shaft, (32aX32b) -Bevel gear, (33aX3
3b) - Bevel gear, (to)...Oil chamber forming plate, Damage...Yoke, (40aX40b)...Oil chamber Fig. 4 Fig. S Fig. 4 - Fig. 7
Claims (1)
ーシングに、放射状に偶数枚の翼を回転自在に取付け、
その取付軸を１本おきに長短２組の長さとし、かつその
先端部にそれぞれ傘歯車を固設し、前記２組の取付軸の
傘歯車の各１組に噛合う傘歯車を前記モータ軸に、その
モータ軸の反転により前記２組の取付軸に対応する翼の
ピッチを互いに逆方向に反転するよう、対向して固設し
、かつ翼ピッチの反転角を規制し、反転したモータ軸の
回転を前記ハブケーシングに伝達する手段を設けた軸流
ファンを、円筒状ダクト内に配設したことを特徴とする
翼ピッチ反転式ジェットファン。1. An even number of blades are rotatably attached radially to a hub casing that is attached to the motor shaft of a motor that can freely rotate in forward and reverse directions.
Each of the mounting shafts has two sets of long and short lengths, and a bevel gear is fixed to each end thereof, and a bevel gear that meshes with each set of bevel gears of the two sets of mounting shafts is connected to the motor shaft. The motor shafts are fixedly opposed to each other so that the pitches of the blades corresponding to the two sets of mounting shafts are reversed in opposite directions when the motor shafts are reversed, and the reversal angle of the blade pitches is regulated. A jet fan with reversible blade pitch, characterized in that an axial flow fan provided with a means for transmitting the rotation of the blade to the hub casing is disposed within a cylindrical duct.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| JP13699186A JPS62291499A (en) | 1986-06-11 | 1986-06-11 | Vane pitch reverse type jet fan |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| JP13699186A JPS62291499A (en) | 1986-06-11 | 1986-06-11 | Vane pitch reverse type jet fan |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| JPS62291499A true JPS62291499A (en) | 1987-12-18 |
Family
ID=15188227
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| JP13699186A Pending JPS62291499A (en) | 1986-06-11 | 1986-06-11 | Vane pitch reverse type jet fan |
Country Status (1)
| Country | Link |
|---|---|
| JP (1) | JPS62291499A (en) |
Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US7179054B1 (en) * | 2004-05-14 | 2007-02-20 | The United States Of America As Represented By The Secretary Of The Navy | Flow reversal system for axial fan |
| KR100903050B1 (en) | 2007-09-17 | 2009-06-18 | (주)한서정공 | Fan for spraying agricultural chemicals |
| JP2011012558A (en) * | 2009-06-30 | 2011-01-20 | Mitsui Miike Mach Co Ltd | Jet fan |
| KR200454113Y1 (en) | 2009-03-11 | 2011-06-16 | (주)한서정공 | Fan for spraying agricultural chemicals |
| CN109209998A (en) * | 2018-10-23 | 2019-01-15 | 常州工学院 | Angle of fan leaves regulating system, device and blower based on face gear transmission |
-
1986
- 1986-06-11 JP JP13699186A patent/JPS62291499A/en active Pending
Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US7179054B1 (en) * | 2004-05-14 | 2007-02-20 | The United States Of America As Represented By The Secretary Of The Navy | Flow reversal system for axial fan |
| KR100903050B1 (en) | 2007-09-17 | 2009-06-18 | (주)한서정공 | Fan for spraying agricultural chemicals |
| KR200454113Y1 (en) | 2009-03-11 | 2011-06-16 | (주)한서정공 | Fan for spraying agricultural chemicals |
| JP2011012558A (en) * | 2009-06-30 | 2011-01-20 | Mitsui Miike Mach Co Ltd | Jet fan |
| CN109209998A (en) * | 2018-10-23 | 2019-01-15 | 常州工学院 | Angle of fan leaves regulating system, device and blower based on face gear transmission |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| US3893789A (en) | Pitch change actuator for a variable pitch fan propulsor | |
| US2648387A (en) | Rotor head | |
| US3902822A (en) | Modular gearbox for a variable pitch fan propulsor | |
| KR840001296A (en) | Drilling device | |
| JP7307559B2 (en) | rotator and aircraft | |
| US4021142A (en) | Pitch-change apparatus for a ducted thrust fan | |
| US11780562B2 (en) | Turbomachine module for a propeller having variable-pitch blades and turbomachine comprising same | |
| JPS6085202A (en) | Pitch altering mechanism | |
| JPS62291499A (en) | Vane pitch reverse type jet fan | |
| GB1375988A (en) | Pitch varying mechanism for variable pitch fan | |
| JP2006242169A (en) | Rotary wing and power generating device using it | |
| US4326846A (en) | Dental handpiece | |
| KR920004745A (en) | Fluid clutch | |
| US3794442A (en) | Variable pitch rotary blading | |
| US2544713A (en) | Automatically adjustable rotary turbine-type hydraulic coupling | |
| EP1711726B1 (en) | Method for driving a unidirectional propeller control unit pump | |
| GB1371372A (en) | Variable pitch rotary blading | |
| US2810512A (en) | Axial blower with flow control stator | |
| GB1251955A (en) | ||
| GB1598773A (en) | Axial-flow fan | |
| KR200150828Y1 (en) | Reverse revolution of axial fan | |
| JPH09280155A (en) | Windmill | |
| BR102021001704A2 (en) | BLADE PITCH ACTION MECHANISM, PROPELLER SYSTEM, AND METHOD FOR ADJUSTING THE PITCH OF A BLADE IN A PROPELLER SYSTEM | |
| JPS5982532A (en) | Power transmitting apparatus of ship gas turbine | |
| US1767027A (en) | Cooling-fan mechanism |