JPS60192898A - Rotor blade shaft supporting structure of rotor blade variable-type axial fan - Google Patents
Rotor blade shaft supporting structure of rotor blade variable-type axial fanInfo
- Publication number
- JPS60192898A JPS60192898A JP4993084A JP4993084A JPS60192898A JP S60192898 A JPS60192898 A JP S60192898A JP 4993084 A JP4993084 A JP 4993084A JP 4993084 A JP4993084 A JP 4993084A JP S60192898 A JPS60192898 A JP S60192898A
- Authority
- JP
- Japan
- Prior art keywords
- rotor blade
- blade shaft
- ring
- support structure
- variable
- 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.)
- Granted
Links
Landscapes
- Structures Of Non-Positive Displacement Pumps (AREA)
Abstract
Description
【発明の詳細な説明】
〔発明の利用分野〕
本発明は動翼可変式軸流ファンの動翼軸支持構造に係わ
シ、動翼軸に形成されているねじ部の疲労破壊を抑制す
るに好適な動翼軸支持構造に関する。[Detailed Description of the Invention] [Field of Application of the Invention] The present invention relates to a rotor blade shaft support structure of a rotor blade variable type axial flow fan, and suppresses fatigue failure of a threaded portion formed on the rotor blade shaft. The present invention relates to a rotor blade shaft support structure suitable for.
従来の動翼可変式軸流ファンの動翼軸支持構造は、第１
図に示されるように、回転駆動軸（以下主軸という）２
にハブ３が嵌着され、このハブ３の外周立上シ部（以下
、リム部という）３Ａに半径方向放射状に動翼軸挿通孔
４が形成され、この挿通孔４に動翼軸５を挿通させて動
Ｊｉ６が取付けられている。リム部裏面に突出する動翼
軸外周囲にはスラスト軸受７が配設されておシ、動翼軸
５に形成されたねじ部８に締付ナツト９を組付けてスラ
スト軸受７の内輪７Ａｉ動翼軸５に固定し、動翼軸５ｔ
スラスト軸受７で支承した構造となっている。動翼軸５
には可変リンク機構ｌＯが設けられており、軸線１１回
りに動翼軸５を回動させて動翼６の迎角を変えることが
できるようになっている。また、スラスト軸受７に対す
る給油は強制給油方式で、主軸２には給油孔１２と排油
孔１３とが形成され、ハブ３には一端がスラスト軸受７
に臨み、他端が給油孔１２に臨む第１の導孔１４が形成
されておシ、動翼軸５には動翼軸挿通孔内の隙間４人を
介してスラスト軸受７に臨み、他端が排油孔１３に連通
する第２の導孔１５が形成されており、油導入装置（図
示せず）によって給油孔１２から第１の導孔１４を介し
てスラスト軸受７に強制的に潤滑油を供給するとともに
、第２の導孔１５．排油孔１３を介して排出されるよう
になっている。尚、符号１６．１７は潤滑油の漏洩防止
用のパツキンである。The rotor blade shaft support structure of the conventional rotor blade variable axial fan is
As shown in the figure, the rotary drive shaft (hereinafter referred to as the main shaft) 2
A hub 3 is fitted into the hub 3, and rotor blade shaft insertion holes 4 are formed radially in the outer circumferential upright portion (hereinafter referred to as rim portion) 3A of the hub 3, and rotor blade shafts 5 are inserted into the insertion holes 4. The moving Ji6 is attached by inserting it. A thrust bearing 7 is disposed around the outer circumference of the rotor blade shaft protruding from the back surface of the rim portion, and a tightening nut 9 is attached to a threaded portion 8 formed on the rotor blade shaft 5 to tighten the inner ring 7Ai of the thrust bearing 7. Fixed to the rotor blade shaft 5, the rotor blade shaft 5t
It has a structure in which it is supported by a thrust bearing 7. Moving blade shaft 5
is provided with a variable link mechanism lO, which allows the rotor blade shaft 5 to rotate about the axis 11 to change the angle of attack of the rotor blade 6. In addition, the thrust bearing 7 is lubricated by a forced lubrication method, and the main shaft 2 is formed with an oil supply hole 12 and an oil drain hole 13, and one end of the hub 3 is connected to the thrust bearing 7.
A first guide hole 14 is formed in which the other end faces the oil supply hole 12, and the rotor blade shaft 5 faces the thrust bearing 7 through four gaps in the rotor blade shaft insertion hole. A second guide hole 15 is formed whose end communicates with the oil drain hole 13, and an oil introduction device (not shown) forcibly connects the thrust bearing 7 from the oil supply hole 12 through the first guide hole 14. In addition to supplying lubricating oil, the second guide hole 15. The oil is discharged through the oil drain hole 13. Incidentally, reference numerals 16 and 17 are packings for preventing leakage of lubricating oil.
しかし、このような従来の強制給油方式の動翼軸受構造
においては次のような欠点がある。However, such a conventional forced oil supply rotor blade bearing structure has the following drawbacks.
■ 主軸２、ハブ３、動翼軸５にそれぞれ形成する給排
油孔１２．１３．１４．１５．並びに潤滑油漏洩防止用
パツキン１６．１７の溝加工に多大の時間と費用を必要
とする。■ Oil supply and drainage holes 12, 13, 14, and 15 formed in the main shaft 2, hub 3, and rotor blade shaft 5, respectively. Furthermore, it takes a great deal of time and money to process the grooves in the packings 16 and 17 for preventing lubricating oil leakage.
■ 強制給油のだめの装置並びにその配管を必要とする
。■ Requires forced lubrication sump equipment and piping.
■ ！＃楓の分解時潤滑油がこぼれ作業性が極めて悪い
。■! # When Kaede is disassembled, lubricating oil spills and workability is extremely poor.
このような欠点を解消するため、第２図に示される↓う
に、スラスト軸受２７Ａ’に環状カバー２７Ｂで覆うと
ともに、その中に低燃度の潤滑油を充填したオイルバッ
ク構造のスラスト軸受２７を備えた動翼軸受の構造（特
願昭５４−９６８０７号）が提案されている。このオイ
ルバック構造のスラスト軸受２７は環状カバー２７Ｂ内
に予じめ潤滑油が充填されてお多しかも潤滑油漏洩のお
それがないので、潤滑油漏洩防止用パツキン１６．１７
（第１図参照）を設ける必要がなく、その他制滑油を強
制供給するための装置部品の加工等を省略でき動翼軸支
持構造の簡略化が計れる。しかし、第２図に示されるよ
うに、このオイルバック式スラスト軸受を用いた動翼軸
支持構造では、ハブのリム部３Ａに形成されている動翼
軸挿通孔４内には動翼軸５との間に隙間４Ａが形成され
てお９、この隙間４Ａの存在によって流体加振による動
翼６の振動が減衰されること々〈直接動翼軸５に形成さ
れているねじ部８に伝達され、その結果ねじ部８が疲労
破壊によシ折損するという新たな問題を提起するに至っ
た。動翼を模擬した平板具を用い、実稼動時の遠心力相
当の荷重を軸方向に加えて減衰を測定した結果、このオ
イルバック軸受を用いた動翼軸支持構造の動翼軸の減衰
効果は、強制給油方式の動翼軸支持構造のそれの約〒に
低下している。In order to eliminate such drawbacks, as shown in Fig. 2, the thrust bearing 27A' is covered with an annular cover 27B, and a thrust bearing 27 with an oil back structure in which a low-flammability lubricating oil is filled is provided. A structure of a rotor blade bearing (Japanese Patent Application No. 54-96807) has been proposed. This oil-back structure thrust bearing 27 has lubricating oil filled in the annular cover 27B in advance, and there is no risk of lubricating oil leakage.
(See FIG. 1) is not necessary, and machining of other device parts for forcibly supplying the damping oil can be omitted, and the rotor blade shaft support structure can be simplified. However, as shown in FIG. 2, in the rotor blade shaft support structure using this oil-back type thrust bearing, the rotor blade shaft 5 is not inserted into the rotor blade shaft insertion hole 4 formed in the rim portion 3A of the hub. A gap 4A is formed between the rotor blade shaft 5 and the rotor blade shaft 5. Due to the presence of this gap 4A, the vibration of the rotor blade 6 due to fluid excitation is attenuated (directly transmitted to the threaded portion 8 formed on the rotor blade shaft 5). As a result, a new problem arises in that the threaded portion 8 breaks due to fatigue fracture. Using a flat plate simulating a rotor blade, we applied a load equivalent to the centrifugal force during actual operation in the axial direction and measured the damping. The results showed the damping effect of the rotor blade shaft in the rotor blade shaft support structure using this oil back bearing. is approximately 20% lower than that of a rotor blade shaft support structure using forced oil supply.
尚、従来の強制給油方式の動翼軸支持構造は、潤滑油漏
洩防止用パツキン１６．１７によっである程匿の動翼振
動の減衰効果を有しているが、これらのパツキン１６、
エフはニトリルゴムを主成分とする断面Ｙ字形のＹパツ
キンであシ、潤滑油漏洩防止が第１の目的でおり、動翼
の振動を減衰させるという効果はあくまで２次的なもの
であるため、動翼振動を減衰させる一ヒで充分というも
のではなく、動翼のねじ部の疲労破壊による折損を確実
に抑制できる程のものではなかった。Incidentally, the conventional forced lubrication system rotor blade shaft support structure has the effect of damping the rotor blade vibration to a certain extent by the packings 16 and 17 for preventing lubricating oil leakage, but these packings 16,
F is a Y-shaped packing made of nitrile rubber as its main component, and its primary purpose is to prevent lubricating oil leakage, and the effect of damping the vibrations of the rotor blades is only secondary. However, it was not enough to dampen the vibration of the rotor blade, and it was not enough to reliably suppress the breakage of the threaded portion of the rotor blade due to fatigue failure.
父、動兵町変式軸流ファンは火力発電用プラントのボイ
ラーに大容量の燃焼用空気を供給するために使用される
が、一般に火力発電所は海岸近くに設置されるため、空
気には塩素分が多量に含まれておυ、ナツト９の組付け
られている動翼軸ねじ部８は、動翼軸５と動翼軸挿通孔
４との間の隙間４Ａｔ−介して塩素含有空気にさらされ
ることとなるので、ねじ部８には腐食疲労も加わって一
層疲労破壊の可能性が高くなる。Father, Doheicho Variable axial flow fans are used to supply large volumes of combustion air to the boilers of thermal power plants, but since thermal power plants are generally installed near the coast, the air Since a large amount of chlorine is contained υ, the rotor blade shaft threaded portion 8 to which the nut 9 is assembled is freed from chlorine-containing air through the gap 4At between the rotor blade shaft 5 and the rotor blade shaft insertion hole 4. Therefore, the threaded portion 8 is also subjected to corrosion fatigue, further increasing the possibility of fatigue failure.
本発明は前記問題点に鑑みなされたもので、その目的は
流体加振による動翼軸の振動応答を低レベルに保つこと
によって、動翼軸ねじ部に疲労破壊の生じない動翼軸支
持構造を提供することにあ机
〔−発明の概要〕
周面とこの挿通孔内に挿通された動翼軸の外周面との間
にダンパリングを設けたことを特徴とするもので、これ
によって前記目的が達成される。The present invention was made in view of the above-mentioned problems, and its purpose is to maintain a rotor blade shaft support structure in which fatigue failure does not occur in the rotor blade shaft screw portion by keeping the vibration response of the rotor blade shaft due to fluid excitation to a low level. [-Summary of the Invention] A damper ring is provided between the circumferential surface and the outer circumferential surface of the rotor blade shaft inserted into the insertion hole, thereby achieving the above-mentioned The purpose is achieved.
さらに、・動翼軸挿通孔内局面又は動翼軸外周面にダン
パリング装着用のリング溝を周設するとともに、ダンパ
リングを動翼振動減衰効果の高い０リングと、摺動性に
優れたシールリングと、これら両リングの脱落防止用の
バックアップリングとによって構成することによシ、動
翼軸の円滑な回動を妨げることなく動翼軸の振動応答を
低レベル〔発明の実施例〕
次に本発明の詳細な説明する。In addition, a ring groove for mounting a damper ring is provided on the inside surface of the rotor blade shaft insertion hole or on the outer circumferential surface of the rotor blade shaft, and the damper ring is replaced with an 0 ring that has a high rotor blade vibration damping effect and an excellent sliding property. By comprising a seal ring and a backup ring to prevent both rings from falling off, the vibration response of the rotor blade shaft can be reduced to a low level without interfering with the smooth rotation of the rotor blade shaft [Embodiment of the invention] Next, the present invention will be explained in detail.
この図において、主軸３２にハブ３３が嵌着され、この
ハブ３３外周の立上が９部（リム部）３３Ａに半径方向
放射状に動翼軸挿通孔３．４が形成されておシ、この挿
通孔３４に動翼軸３５が挿通され、リム部３３Ａの裏側
に突出する′ｄＪｈ翼軸は先端部がオイルレス軸受５０
で支承されて＃１ｌ１３６がハブ３３に取付けられてい
る。ハブ３３の裏イ１＋１ａ ３ Ｂにおいて、動翼軸
３５の周シにはオイルバック構造のスラスト軸受３７が
配設され、動翼軸３５に形成されたねじ部３８に締め付
はナツト３９ｔ−組付けてスリーブ４１を介してこのス
ラスト軸受３７ｆ：動翼軸３５に固定し、動翼軸３５が
スラスト軸受３７で支承されるようになっている、
動翼軸３５には可変リング機構６ｏが設けられておシ、
動翼軸３５を軸線６１回シに回動させて動Ｒ３６の迎角
を変えることができるようになっている。In this figure, a hub 33 is fitted onto the main shaft 32, and rotor blade shaft insertion holes 3.4 are formed radially in the 9 part (rim part) 33A of the outer periphery of the hub 33. The rotor blade shaft 35 is inserted into the insertion hole 34, and the tip of the 'dJh blade shaft that protrudes from the back side of the rim portion 33A is an oil-less bearing 50.
#1l136 is attached to the hub 33. At the rear side A1+1a3B of the hub 33, a thrust bearing 37 with an oil back structure is disposed around the rotor blade shaft 35, and is tightened with a nut 39t set on a threaded portion 38 formed on the rotor blade shaft 35. The thrust bearing 37f is fixed to the rotor blade shaft 35 via the sleeve 41, and the rotor blade shaft 35 is supported by the thrust bearing 37.The rotor blade shaft 35 is provided with a variable ring mechanism 6o. I'm tired,
The angle of attack of the rotor blade R36 can be changed by rotating the rotor blade shaft 35 61 times around the axis.
動翼軸挿通孔３４内に挿通されている動翼軸３５の外周
面には、リング溝４２が３本周設されておシ、この溝４
２内には第４図に示されるような０リング４４Ａ、シー
ルリング４４Ｂおよびバックアップリング４４Ｃから構
成されるダンパリング４４がそれぞれ装着されている。Three ring grooves 42 are provided on the outer peripheral surface of the rotor blade shaft 35 inserted into the rotor blade shaft insertion hole 34.
Damper rings 44 consisting of an O-ring 44A, a seal ring 44B and a backup ring 44C as shown in FIG.
リング溝４２の底部には、ニトリルゴム、バイトン叫ヲ
主成分とする弾性材によって形成されているＯリング４
４Ａが装着され、この０リング４４Ａ外周には０リング
外周面に整合する内周面形状を有し動翼軸挿通孔３４内
局面に密着状態で当接するシールリング４４Ｂが装着さ
れておシ、このシールリング４４Ｂは耐摩耗性及び摺動
性に優れたフッ素樹脂にて形成されている。またリング
溝４２内の動翼軸付根側には、外周面が動翼軸挿通孔３
４内局面に当接する耐摩耗性に優れたバックアップリン
グ４４Ｃが装着されておシ、遠心力の作用によりＯリン
グ４４Ａ、シールリング４４Ｂが脱落すること全防止し
ている。At the bottom of the ring groove 42, there is an O-ring 4 formed of an elastic material mainly composed of nitrile rubber and Viton rubber.
A seal ring 44B is attached to the outer periphery of the O-ring 44A, and the seal ring 44B has an inner circumferential surface shape that matches the outer circumferential surface of the O-ring and is in close contact with the inner surface of the rotor blade shaft insertion hole 34. This seal ring 44B is made of fluororesin which has excellent wear resistance and sliding properties. In addition, the outer peripheral surface of the rotor blade shaft root side in the ring groove 42 has the rotor blade shaft insertion hole 3.
A backup ring 44C with excellent abrasion resistance that contacts the inner surface of the ring 4 is attached to completely prevent the O-ring 44A and the seal ring 44B from falling off due to the action of centrifugal force.
一般に、動ｇ３６及び動翼軸３５には遠心力を軽減する
ため比重の小さい高力アルミ合金が使用され、ハブ３３
には強度を確保するためｃｒ−Ｍ。Generally, high-strength aluminum alloy with low specific gravity is used for the rotor g36 and rotor blade shaft 35 to reduce centrifugal force, and the hub 33
CR-M to ensure strength.
合金が使用されるが、高力アルミ合金はｃｒ −Ｍ（。The high strength aluminum alloy is CR-M(.
合金に比べて他の材料との摺動性が悪いので、動翼軸３
５側にＯリング−４４人を装着し、動翼軸挿通孔３４内
局面側にシールリング４４８ｔ−配設することが望まし
い。また動翼軸３５とハブ３３の構成材料を考慮して各
リングの配置を決定することが望ましい。Since sliding properties with other materials are poor compared to alloys, the rotor blade shaft 3
It is preferable that 44 O-rings be installed on the 5th side, and a seal ring 448t be provided on the inner side of the rotor blade shaft insertion hole 34. Further, it is desirable to determine the arrangement of each ring in consideration of the constituent materials of the rotor blade shaft 35 and the hub 33.
動翼軸３５と動翼挿通孔３４との間に配設されるダンパ
リング４４の数は、減衰効果の点からは多い方が良いが
、作業性及び動翼軸３５の摺動性等の点からは３本が妥
当と解される。The number of damper rings 44 disposed between the rotor blade shaft 35 and the rotor blade insertion hole 34 is better from the point of view of damping effect, but the number of damper rings 44 disposed between the rotor blade shaft 35 and the rotor blade insertion hole 34 is better. From the point of view, it can be understood that 3 is appropriate.
動翼を模擬した平板翼を使用し、兵先姑部を衝打して動
翼に自由振動を与え、動翼軸ねじ部に設置した歪ゲージ
によって減衰量を測定して０リングの本数の違いによる
減衰効果の違いをめたところ、０リングが１本又は２本
でＯリング金−初使用しない場合に比べて減衰は約３倍
大きくなシ、０リングが３本の場合では約４．５倍大き
くなった。Using a flat blade that simulates a rotor blade, the rotor blade is given free vibration by impacting the tip and rear parts, and the amount of attenuation is measured with a strain gauge installed on the screw part of the rotor blade shaft, and the number of O rings is determined. When we looked at the difference in damping effect due to the difference, we found that when there are one or two O-rings, the attenuation is about 3 times greater than when the O-ring is not used for the first time, and when there are three O-rings, the attenuation is about 4 times greater. .5 times larger.
実機動翼にダンパリング４４を装着して同様の試験を行
なった結果、ダンパリング４４をｌケＤｉ設置した場合
はダンパリング４４を１つたく使用しない場合・の約７
倍の減衰効果がわり、ダンパリング４４を３ケＤ丁設け
た場合にはダンパリング４４をまったく設けない場合の
約９乃至１０倍の減衰効果が得ら扛た。As a result of conducting similar tests with damper rings 44 attached to actual rotor blades, it was found that when damper rings 44 were installed, the difference was approximately 7 times lower than when one damper ring 44 was not used.
The damping effect is about 9 to 10 times greater when three damper rings 44 are provided than when no damper ring 44 is provided.
本実施例によれば、ダンパリング４４によって７Ｂｂ翼
の加振が抑制されるので動翼軸３５に形成さｇているね
じ部３８の振動応答が低レベルに保たれ、ねじ部３８の
疲労破壊が防止される。また、ダンパリング４４のシー
ル効果によって動Ｉ２軸挿通孔３４内のすき間は確実に
閉塞されるので、送風空気中にたとえ塩素分が含まれて
いても！ｌｌｌ＋翼軸ねじ部の腐食疲労は防止される。According to this embodiment, the vibration of the 7Bb blade is suppressed by the damper ring 44, so that the vibration response of the threaded portion 38 formed on the rotor blade shaft 35 is kept at a low level, resulting in fatigue failure of the threaded portion 38. is prevented. Furthermore, the sealing effect of the damper ring 44 reliably closes the gap in the dynamic I2 shaft insertion hole 34, even if the blown air contains chlorine! Corrosion fatigue of the wing shaft threaded portion is prevented.
すなわち、ねじ部３８の疲労強度を低下させる２つの要
因が除かれることになり、軸流ファンの信頼性および耐
久性が確保されるのである。That is, the two factors that reduce the fatigue strength of the threaded portion 38 are removed, and the reliability and durability of the axial fan are ensured.
又、ダンパリング４４の動翼軸挿通孔３４内周面との密
着部はノールリング４４Ｂによって形成されておシ、動
翼軸挿通孔３４内周面との間の摺動性は良く、動翼軸３
５？ｌｃ円滑に回動させることができる。In addition, the part of the damper ring 44 in close contact with the inner circumferential surface of the rotor blade shaft insertion hole 34 is formed by a knoll ring 44B, and the sliding property between the damper ring 44 and the inner circumferential surface of the rotor blade shaft insertion hole 34 is good. Wing axis 3
5? lc can be rotated smoothly.
第５図は本発明の第２芙施例を示すもので、リング溝４
２内にＯＩＪンク５４Ａが装着され、その外周に動翼軸
挿通孔３４内周面に密幅・するシールリング５４Ｂ？ｃ
−装漸したもので、リング溝４２内に装ルするダンパリ
ング５４を０リング５４Ａとシールリング５４Ｂとによ
って構成し、シールリング５４Ｂの内側をリング溝４２
内に収納することによって脱落全防止し、バックアップ
リングを不用とした点に特徴がある。FIG. 5 shows a second embodiment of the present invention, in which the ring groove 4
2, an OIJ link 54A is installed in the rotor blade shaft insertion hole 34, and a seal ring 54B with a tight width is attached to the inner circumferential surface of the rotor blade shaft insertion hole 34 on its outer periphery. c.
- The damper ring 54 installed in the ring groove 42 is composed of an O ring 54A and a seal ring 54B, and the inner side of the seal ring 54B is inserted into the ring groove 42.
It is unique in that it is completely prevented from falling off by storing it inside, and eliminates the need for a backup ring.
その他は前記第１実施例と同様でおるため同一の符号音
符すことによりその説明は省略する。Since the rest is the same as the first embodiment, the same reference numerals and notes will be used and the explanation thereof will be omitted.
この第２の実施例によっても前記第１実施例と同様の効
果全行ることができ／？８゜
第６図は本発明の第３実施例全示すもので、動翼軸挿通
孔３４内局面にダンパリング収納用のリンク溝５２を形
成し、この溝５２内にダンパリング４４金収納したこと
に特徴がある。This second embodiment also provides all the same effects as the first embodiment. 8. FIG. 6 shows the third embodiment of the present invention, in which a link groove 52 for storing a damper ring is formed in the inner surface of the rotor blade shaft insertion hole 34, and a 44-karat gold damper ring is stored in this groove 52. There are certain characteristics.
七の他はＯ１Ｉ記第１実施例と同様であるため同一の符
号？符すことによシその説明は省略する。本実施例にお
いても前記第１及び第２実施例と同様の効果葡嬰するこ
とができる。Other than 7, it is the same as the first embodiment of O1I, so are the same symbols? The explanation will be omitted. In this embodiment as well, the same effects as in the first and second embodiments can be obtained.
以上の説明がら明らかなように、木り６明によれば動翼
軸のねじ部に動翼加振に起因した疲労破壊の生ずること
の７よいｆＪＪＪ腟軸叉愕構造が得られる。As is clear from the above description, according to Kiri 6 Akira, a fJJJ vaginal axis discontinuation structure is obtained which is less likely to cause fatigue failure in the threaded portion of the rotor blade shaft due to vibration of the rotor blade.
４ し１面の閏年な歌、明
第１図及び鯖２図は従来の勤興可変式軸流ファンの動翼
軸文持檜造の断面メ１、第３図は不発明に係わる動共可
汲式軸流ファンの励典軸支持構造第１実施例の断面図、
第４図はその要部を拡大した断面図、第５図は本発明の
第２実施例の要部断面図、第６図は本発明の第３実施例
の要部断１朗図でおる。4. The leap year song on page 1, Figures 1 and 2 are cross-sections of the rotor blade shaft design of a conventional variable axial flow fan, and Figure 3 is a cross-section of the rotor shaft pattern of a conventional variable axial fan. A sectional view of a first embodiment of an excitation shaft support structure of a pumpable axial flow fan,
Fig. 4 is an enlarged sectional view of the main part, Fig. 5 is a sectional view of the main part of the second embodiment of the present invention, and Fig. 6 is a cross-sectional view of the main part of the third embodiment of the invention. .
３２・・・回転駆動軸、３３・・・ハブ、３３Ａ・・・
ハブのリム部、３４・・・動翼軸挿通孔、３５・・・動
翼軸、３６・・・動感、３８・・・ねじ部、３９・・・
締付ナツト、４２．５２・・・リング溝、４４．５４・
・・ダンパリング、４４Ａ、５４Ａ・・・Ｏリング、４
４Ｂ、５４Ｂ・・・７−ルリング、４４Ｃ・・・バック
アップリング。32... Rotation drive shaft, 33... Hub, 33A...
Rim portion of hub, 34... rotor blade shaft insertion hole, 35... rotor blade shaft, 36... dynamic feeling, 38... screw portion, 39...
Tightening nut, 42.52...Ring groove, 44.54.
...Damper ring, 44A, 54A...O ring, 4
4B, 54B...7-ring, 44C...backup ring.
代理人 鵜 沼 辰 之 第１図 第２図 第３図 第４図Agent Tatsuyuki Unuma Figure 1 Figure 2 Figure 3 Figure 4
Claims (1)
軸挿通孔が半径方向放射状に形成され、該挿通孔に動翼
軸が挿通されるとともに、ノ・ブ裏面に突出する動翼軸
が動翼軸受で支承された動翼可変式軸流ファンの動翼軸
支持構造において、前記挿通孔内周面と動翼軸外周面と
の間にダンパリングが設けられていることを特徴とする
動翼可変式軸流ファンの動翼軸支持構造。 （２） 前記ダンパリングは動翼軸挿通孔内局面及び動
翼軸外周面に密着状態に設けられていることを特徴とす
る特許請求の範囲第１項記載の動翼可変式軸流ファンの
動翼軸支持構造。 （３〕 前記ダンパリングは動翼軸挿通孔内局面又は動
翼軸外周面に周設されたリング溝に装着されていること
を特徴とする特許請求の範囲第１項記載の動翼可変式軸
流ファンの動翼軸支持構造。 （４） 前記リング溝内に収納されるリングくリングは
、前記リング溝底部に収納されるＯ ＩＪングと、この
０リング外周に装着されるシールリングと、一部がリン
グ溝内に収納され、これら両リングの脱落を防止するだ
めのバックアップリングとから構成されていることを特
徴とする特許請求の範囲第３項記載の動翼可変式軸流フ
ァンの動翼軸支持構造。 （５） 前記動翼軸受はオイルバック構造のスラスト軸
受であることを特徴とする特許請求の範囲第１項記載の
動翼可変式軸流ファンの動翼軸支持構造。[Scope of Claims] (1) A hub is fitted onto the rotary drive shaft, rotor blade shaft insertion holes are formed in the hub in a radial direction, and the rotor blade shafts are inserted into the insertion holes. In a rotor blade shaft support structure of a variable rotor blade axial flow fan in which a rotor blade shaft protruding from the rear surface of the rotor blade is supported by a rotor blade bearing, a damper ring is provided between the inner circumferential surface of the insertion hole and the outer circumferential surface of the rotor blade shaft. A rotor blade shaft support structure for a variable rotor blade axial flow fan, characterized in that the rotor blade shaft support structure is provided. (2) The variable rotor blade axial fan according to claim 1, wherein the damper ring is provided in close contact with the inner surface of the rotor blade shaft insertion hole and the outer peripheral surface of the rotor blade shaft. Rotating blade shaft support structure. (3) The variable rotor blade type according to claim 1, wherein the damper ring is installed in a ring groove provided around the inner surface of the rotor blade shaft insertion hole or the outer peripheral surface of the rotor blade shaft. A rotor blade shaft support structure for an axial fan. (4) The ring ring housed in the ring groove includes an O IJ ring housed at the bottom of the ring groove, and a seal ring attached to the outer periphery of the O ring. , and a backup ring that is partially housed in the ring groove and prevents both rings from falling off. (5) The rotor blade shaft support structure for a variable rotor blade axial flow fan according to claim 1, wherein the rotor blade bearing is a thrust bearing with an oil back structure. .
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| JP4993084A JPS60192898A (en) | 1984-03-15 | 1984-03-15 | Rotor blade shaft supporting structure of rotor blade variable-type axial fan |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| JP4993084A JPS60192898A (en) | 1984-03-15 | 1984-03-15 | Rotor blade shaft supporting structure of rotor blade variable-type axial fan |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| JPS60192898A true JPS60192898A (en) | 1985-10-01 |
| JPS647237B2 JPS647237B2 (en) | 1989-02-08 |
Family
ID=12844729
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| JP4993084A Granted JPS60192898A (en) | 1984-03-15 | 1984-03-15 | Rotor blade shaft supporting structure of rotor blade variable-type axial fan |
Country Status (1)
| Country | Link |
|---|---|
| JP (1) | JPS60192898A (en) |
Citations (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPS5496807A (en) * | 1978-01-18 | 1979-07-31 | Hitachi Ltd | Structure of moving vane bearing in variable moving vane type axial fan |
| JPS55144894U (en) * | 1979-04-06 | 1980-10-17 |
-
1984
- 1984-03-15 JP JP4993084A patent/JPS60192898A/en active Granted
Patent Citations (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPS5496807A (en) * | 1978-01-18 | 1979-07-31 | Hitachi Ltd | Structure of moving vane bearing in variable moving vane type axial fan |
| JPS55144894U (en) * | 1979-04-06 | 1980-10-17 |
Also Published As
| Publication number | Publication date |
|---|---|
| JPS647237B2 (en) | 1989-02-08 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| US4214796A (en) | Bearing assembly with multiple squeeze film damper apparatus | |
| US5651616A (en) | Tapered bearing housing | |
| US4772135A (en) | Bearing arrangement for the impellers of the compressor and the turbine in the turbine housing that are arranged next to one another on a shaft of a rotor shaft | |
| JP2008542628A (en) | Vacuum pump | |
| KR840006042A (en) | Rotary Fluid Machine Reduces Fluid Leakage | |
| JP2015522773A (en) | Gasket device for turbomachine bearings, including two elastic seals | |
| EP0253839A1 (en) | Centrifugal seal. | |
| AU620005B2 (en) | Bellows seal with vibration damper | |
| NO832778L (en) | INTEGRAL BEARING SYSTEM. | |
| JPS58102819A (en) | Tilting pad bearing | |
| US5906440A (en) | Dynamic pressure type fluid bearing device | |
| US5017023A (en) | Asymmetrically stepped hydrostatic bearing | |
| JPS60192898A (en) | Rotor blade shaft supporting structure of rotor blade variable-type axial fan | |
| US4343591A (en) | Turbomachine seal system | |
| DK155848B (en) | AXIAL FAN WHEELS | |
| US4219310A (en) | Construction of adjustable blade shaft bearing in axial-flow fan with adjustable blades | |
| EP2029920B1 (en) | Mechanical seal with banded ring | |
| JP2001140888A (en) | Bearing device and turbocharger provided therewith | |
| EP0903834B1 (en) | Sealing device for explosion-proof motors | |
| JPH05332355A (en) | Tilting pad type journal bearing | |
| US5368313A (en) | Bushing for trapped bushing seal | |
| US6860483B2 (en) | Gas film hydraulic shaft seal | |
| US2813761A (en) | Thrust bearing | |
| CN112360632B (en) | Oil retainer for gas turbine | |
| US2400028A (en) | Bearing |