JPH1037899A - Vaned diffuser for centrifugal compressor - Google Patents
Vaned diffuser for centrifugal compressorInfo
- Publication number
- JPH1037899A JPH1037899A JP8196309A JP19630996A JPH1037899A JP H1037899 A JPH1037899 A JP H1037899A JP 8196309 A JP8196309 A JP 8196309A JP 19630996 A JP19630996 A JP 19630996A JP H1037899 A JPH1037899 A JP H1037899A
- Authority
- JP
- Japan
- Prior art keywords
- impeller
- vane
- side plates
- pressure
- centrifugal compressor
- 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
【０００１】[0001]
【発明の属する技術分野】本発明は、遠心圧縮機の羽根
車の羽根出口部近傍の流路に設置され、羽根車の回転に
より加速されて、羽根車から吐出される作動流体の速度
をスクロールとともに、静圧に変換する遠心圧縮機用翼
付ディフューザに関する。BACKGROUND OF THE INVENTION 1. Field of the Invention The present invention relates to a centrifugal compressor, which is installed in a flow path near an impeller outlet of a centrifugal compressor, scrolls the speed of a working fluid discharged from the impeller while being accelerated by rotation of the impeller. Also, the present invention relates to a centrifugal compressor bladed diffuser for converting to static pressure.
【０００２】[0002]
【従来の技術】図４は、従来の遠心圧縮機用翼付ディフ
ューザの１例を示す概略図である。図において、０１は
羽根車であり、矢視Ｒ方向に回転して、紙面と直交する
方向から導入した作動流体を加速して、周辺部から紙面
方向に吐出する。このように、導入した作動流体を加速
するとき、図に示す如く、羽根車０１の出口部では、羽
根の圧力面側（以下ＰＳという）で圧力が高く、負圧面
側（以下ＳＳという）で圧力が低くなる圧力分布Ｐ′が
発生する。2. Description of the Related Art FIG. 4 is a schematic view showing an example of a conventional bladed diffuser for a centrifugal compressor. In the figure, reference numeral 01 denotes an impeller which rotates in the direction of arrow R, accelerates the working fluid introduced from a direction perpendicular to the plane of the paper, and discharges it from the peripheral portion in the direction of the paper. Thus, when the introduced working fluid is accelerated, as shown in the figure, at the outlet of the impeller 01, the pressure is high on the pressure surface side (hereinafter referred to as PS) of the blade and on the negative pressure surface side (hereinafter referred to as SS). A pressure distribution P 'in which the pressure decreases is generated.
【０００３】また、０２は羽根車０１の羽根出口部近傍
の通路に、羽根車０１の回転面と平行にして、対向して
配設された、２枚の環状円板からなる側板、０３は対向
して配設された２枚の側板０２に、それぞれ両端が固着
されて、側板０２の間を円周方向に等ピッチに配置され
た（ディフューザ）翼である。この側板０２および翼０
３からなる翼付ディフューザ０４では、羽根車０１の回
転に羽根出口部から吐出される作動流体の速度が静圧に
回復されて、昇圧される。この翼付ディフューザ０４で
も、羽根出口部から吐出される作動流体によって、羽根
出口部と同様に、図に示すように、翼０３の前縁のＰＳ
で圧力が高く、ＳＳで圧力が低くなり、周方向に変動す
る圧力分布Ｐが発生する。[0003] Further, reference numeral 02 denotes a side plate formed of two annular disks, which is disposed in the passage near the blade outlet of the impeller 01 in parallel with the rotation surface of the impeller 01 and opposed to each other. Both ends are fixed to two side plates 02 arranged opposite to each other, and (diffuser) blades are arranged at equal pitches in the circumferential direction between the side plates 02. This side plate 02 and wing 0
In the bladed diffuser 04 comprising the blade 3, the speed of the working fluid discharged from the blade outlet is restored to a static pressure by the rotation of the impeller 01, and the pressure is increased. In this diffuser with wings 04, the working fluid discharged from the outlet of the blade also causes the PS of the leading edge of the wing 03 as shown in FIG.
, The pressure is high, and the pressure is low in SS, and a pressure distribution P that fluctuates in the circumferential direction is generated.
【０００４】図５は、圧力分布Ｐ′が発生する、羽根車
０１の羽根出口部のＰＳである、図４に示すＡ点が回転
して、圧力分布Ｐが発生している翼０３の前縁側を通過
するときの、Ａ点の圧力ＰA の時間ｔ変動を示したもの
である。すなわち、回転している羽根車０１と静止して
いる翼０３とは相対運動しており、常に羽根車０１の羽
根出口部は、翼０３の前縁側を通過するため、羽根車０
１の羽根出口部のうち、圧力分布Ｐ′が最大の圧力Ｐ′
max になっているＡ点の圧力ＰA は、翼０３の前縁に発
生している圧力分布Ｐの影響を受け、図５に示すような
圧力ＰA の時間変動が発生する。FIG. 5 shows a PS at the blade outlet of the impeller 01 where the pressure distribution P 'is generated. The point A shown in FIG. as it passes through the edge, there is shown the time t pressure fluctuations P a of the point a. In other words, the rotating impeller 01 and the stationary blade 03 are moving relative to each other, and the blade outlet of the impeller 01 always passes through the leading edge side of the blade 03.
The pressure distribution P 'is the maximum pressure P' among the blade outlets of one blade.
The pressure P A of the point A that is a max is influenced by the pressure distribution P occurring on the leading edge of the wing 03, the time variation of the pressure P A, as shown in FIG. 5 is generated.
【０００５】換言すれば、図４中の羽根車０１の羽根出
口部のＡ点は、着目しているある１つの羽根車０１のＰ
Ｓに位置する点であり、前述したように、羽根車０１の
出口に発生する圧力分布Ｐ′では、この点の圧力が最も
高く、しかも羽根車０１の回転により、このＡ点が翼０
３前縁に発生している圧力分布Ｐのうち、最大の圧力Ｐ
max となる翼０３の前縁のＰＳを通過するとき、Ａ点の
圧力ＰA は、最大の略ＰA ＝Ｐ′max ＋Ｐmax となり、
また翼０３の前縁のＳＳを通過するときのＡ点の圧力Ｐ
A は、最小の略ＰA ＝Ｐ′max ＋Ｐmin （但し、Ｐmin
は翼０３の前縁側のＳＳでの圧力）となり、羽根車０１
のＡ点は、その差に相当する振幅の圧力変動ΔＰA と、
振幅の最大圧力ＰAmaxを受けることになる。このこと
は、翼０３の前縁側も同様であり、前縁側の圧力分布Ｐ
に羽根車０１の回転に伴う圧力分布Ｐ′の変動分の影響
を受けることになる。[0005] In other words, the point A at the blade outlet of the impeller 01 in FIG.
As described above, the pressure at this point is the highest in the pressure distribution P ′ generated at the outlet of the impeller 01, and the point A
3 Among the pressure distributions P generated at the leading edge, the maximum pressure P
When passing through the PS of the leading edge of the blade 03 as the max, the pressure P A at the point A, the maximum approximately P A = P 'max + P max , and the
The pressure P at point A when passing through the SS at the leading edge of wing 03
A is the minimum approximately P A = P ′ max + P min (where P min
Is the pressure at the SS on the leading edge side of the wing 03), and the impeller 01
Point A is a pressure fluctuation ΔP A having an amplitude corresponding to the difference,
It will receive a maximum pressure P Amax of amplitude. This is the same for the leading edge side of the wing 03, and the pressure distribution P on the leading edge side
Accordingly, the pressure distribution P 'is affected by the fluctuation of the pressure distribution P' accompanying the rotation of the impeller 01.
【０００６】このように、羽根車０１の羽根出口部が、
翼付ディフューザ０４の翼０３間に発生する圧力分布Ｐ
の中を通過する際には、圧力が最大及び最小となる点が
発生し、この最大圧力ＰAmaxや変動圧力ΔＰA が過大に
なると、羽根車０１の羽根出口部や翼０３の前縁部の折
損等を引き起こすことがある。Thus, the blade outlet of the impeller 01 is
Pressure distribution P generated between wings 03 of winged diffuser 04
When passing through the inside, points where the pressure becomes maximum and minimum occur, and when the maximum pressure P Amax and the fluctuation pressure ΔP A become excessive, the blade outlet of the impeller 01 and the leading edge of the blade 03 May be broken.
【０００７】一般には、羽根車０１の羽根の固有振動数
を、回転数×翼０３の枚数と等しくならないようにし
て、翼付ディフューザ０４との共振を避け、材料強度等
を考慮して安全に設計されるが、運転中に局所的な腐食
の発生、異物の混入、衝突等による強度劣化等の不測の
事態が生じた場合、前述のように、羽根車０１の羽根車
出口部や翼０３前縁部に折損等が生じることがある。In general, the natural frequency of the blades of the impeller 01 is set so as not to be equal to the number of revolutions times the number of blades 03, thereby avoiding resonance with the winged diffuser 04, and taking the material strength etc. into consideration. Although it is designed, if an unexpected situation such as local corrosion occurs, foreign matter is mixed in, or the strength is deteriorated due to collision or the like during operation, as described above, the impeller exit portion of the impeller 01 and the blade 03 The leading edge may be broken.
【０００８】このような事故を防ぐには、羽根車０１の
羽根出口部の厚みや、翼０３の厚みを増大して、剛性の
強化を図ることが考えられるが、このような剛性を大き
くして、折損事故を防止する方法では、遠心圧縮機の重
量増に伴う不具合が発生するほか、流体力学的な効率の
低下を来し、遠心圧縮機の効率の低下を招くという、新
たな不具合が発生することになる。In order to prevent such an accident, it is conceivable to increase the thickness of the blade outlet portion of the impeller 01 or the thickness of the blades 03 so as to enhance the rigidity. In the method of preventing breakage accidents, new problems such as a decrease in the efficiency of the centrifugal compressor due to the increase in the weight of the centrifugal compressor and a decrease in the hydrodynamic efficiency are caused. Will happen.
【０００９】[0009]
【発明が解決しようとする課題】本発明は、上述した従
来の遠心圧縮機用翼付ディフューザの不具合を解決する
ため、羽根車の回転に伴い羽根車の羽根出口部、すなわ
ち翼付ディフューザの翼入口部に、発生する最大圧力や
圧力の変動の大きさを小さくして、種々の不具合が発生
する羽根車の羽根出口部の肉厚、若しくは翼付ディフュ
ーザの翼厚の増大等を行うことなく、羽根出口部若しく
は翼前縁部の折損による事故等を未然に防ぎ、遠心圧縮
機を信頼性の高いものにできる遠心圧縮機用翼付ディフ
ューザを提供することを課題とする。SUMMARY OF THE INVENTION The present invention solves the above-mentioned disadvantages of the conventional diffuser with a blade for a centrifugal compressor. At the inlet, reduce the maximum pressure generated and the magnitude of pressure fluctuations, without increasing the thickness of the blade outlet of the impeller where various problems occur or the blade thickness of the winged diffuser It is another object of the present invention to provide a centrifugal compressor bladed diffuser which can prevent an accident or the like due to breakage of a blade outlet portion or a blade leading edge portion and can make the centrifugal compressor highly reliable.
【００１０】[0010]
【課題を解決するための手段】このため、本発明の遠心
圧縮機用翼付ディフューザは、次の手段とした。 （１）遠心圧縮機の羽根車の羽根出口部に近接する作動
流体の通路に、対向して配設された２枚の環状円板から
なる側板の間を、周方向に等ピッチで複数配設された翼
の前縁上流側で、圧力面側の側板対向面に開口を持つ小
孔を設けた。なお、小孔は、側板の間に配置された翼に
対応させて、同一半径上を周方向に設けることが好まし
い。また、小孔は、対向させた側板の一方のみに設ける
ようにしても、若しくは両方の側板に設けるようにして
も良い。 （２）環状円板からなる側板の内部に円周方向に穿設さ
れ、側板の互に相対する対向面に開口させた小孔を、側
板内で連通させる環状通路を設けた。なお、環状通路
は、同一の側板に設けたすべての小孔を連通させるよう
に設けることが好ましい。For this reason, the bladed diffuser for a centrifugal compressor of the present invention has the following means. (1) A plurality of side plates formed of two annular disks disposed opposite to each other are disposed at equal intervals in a circumferential direction in a working fluid passage close to a blade outlet of an impeller of a centrifugal compressor. On the upstream side of the leading edge of the blade, a small hole having an opening was provided on the side facing the side plate on the pressure surface side. Preferably, the small holes are provided on the same radius in the circumferential direction in correspondence with the blades arranged between the side plates. The small holes may be provided in only one of the opposed side plates, or may be provided in both side plates. (2) An annular passage is provided in the side plate formed in the circumferential direction inside the side plate formed of the annular disk, and communicates in the side plate with small holes opened in the opposing surfaces of the side plate facing each other. The annular passage is preferably provided so as to communicate all the small holes provided in the same side plate.
【００１１】本発明の遠心圧縮機用翼付ディフューザ
は、上述の構成により、翼付ディフューザを構成する翼
の前縁上流の圧力面側の、側板の対向面に小孔を開け、
この小孔を側板内部に穿設した環状通路で連通させたこ
とにより、翼付ディフューザの入口部である翼前縁部
に、羽根車の羽根出口部より流入する作動流体で発生
し、周方向に変動する圧力分布が均等化され、隣接する
翼間に生じる圧力分布の圧力差が小さくなる。The centrifugal compressor winged diffuser of the present invention has the above-described configuration, in which a small hole is formed in the surface facing the side plate on the pressure surface side upstream of the leading edge of the wing constituting the winged diffuser.
By communicating these small holes with an annular passage formed inside the side plate, working fluid flowing from the blade outlet of the impeller is generated at the leading edge of the blade, which is the inlet of the diffuser with blades, and is formed in the circumferential direction. The pressure distribution that fluctuates in a uniform manner is equalized, and the pressure difference in the pressure distribution generated between adjacent blades is reduced.
【００１２】このため、羽根車の回転により、羽根車の
羽根出口部に発生する圧力分布の影響により増大する、
羽根出口部および翼前縁部の変動圧力、及びその振幅の
絶対値が小さくなり、遠心圧縮機の効率上、肉厚が薄く
せざるを得ない、羽根車の羽根出口部及び翼付ディフュ
ーザの翼前縁部が折損するような事故を起すことのない
ものにでき、遠心圧縮機の信頼性を向上させることがで
きる。For this reason, the rotation of the impeller increases due to the influence of the pressure distribution generated at the blade outlet of the impeller.
The fluctuating pressure at the blade outlet and the leading edge of the blade and the absolute value of its amplitude are reduced, and the thickness of the impeller blade outlet and the diffuser with blades must be reduced for the efficiency of the centrifugal compressor. An accident such as breakage of the blade leading edge can be prevented, and the reliability of the centrifugal compressor can be improved.
【００１３】[0013]
【発明の実施の形態】以下、本発明の遠心圧縮機用翼付
ディフューザの実施の一形態を、図面にもとづき説明す
る。図１は、本発明の遠心圧縮機用翼付ディフューザの
実施の第１形態を示す図で、図１（ａ）は部分縦断面
図、図１（ｂ）は図１（ａ）に示す矢視Ａ−Ａにおける
正面図である。BRIEF DESCRIPTION OF THE DRAWINGS FIG. 1 is a perspective view of a diffuser with blades for a centrifugal compressor according to an embodiment of the present invention. FIG. 1 is a view showing a first embodiment of a diffuser with wings for a centrifugal compressor according to the present invention. FIG. 1 (a) is a partial longitudinal sectional view, and FIG. 1 (b) is an arrow shown in FIG. 1 (a). It is a front view in the view AA.
【００１４】図において、１は羽根車であり、軸方向に
流入する作動流体３を加速して、外周の羽根出口部２か
ら半径方向に吐出する。In FIG. 1, reference numeral 1 denotes an impeller, which accelerates a working fluid 3 flowing in an axial direction and discharges the working fluid 3 in a radial direction from an outer blade outlet 2.
【００１５】４は羽根出口部２に近接して内径端が配置
され、羽根車１の回転面と平行にされた側面を、互に対
向させた２枚の環状円板からなる側板、５は対向する側
板４に、それぞれ両端部が固着されて、側板４の間を円
周方向に等ピッチに配設された（ディフューザ）翼、６
は翼５の前縁側の圧力面側（ＰＳ）の側板４上流側に設
けられた小孔であり、側板４の対向面側に、側板４間を
等ピッチで円周方向に設けられている、各翼５毎に設け
られている。なお、小孔６は、左側の一方のみの側板４
に設ける例を示しているが、互に対向させて設けた側板
４の両方に設けるようにしても、右側の一方のみの側板
４に設けるようにしても良いものである。Reference numeral 4 denotes a side plate having an inner diameter end disposed close to the blade outlet portion 2 and comprising two annular disks whose side surfaces parallel to the rotation surface of the impeller 1 face each other. (Diffuser) wings 6, both ends of which are fixed to the opposing side plates 4, which are arranged at equal pitches in the circumferential direction between the side plates 4.
Are small holes provided upstream of the side plate 4 on the pressure surface side (PS) on the leading edge side of the blade 5, and are provided in the circumferential direction at equal pitches between the side plates 4 on the opposing surface side of the side plate 4. , For each wing 5. In addition, the small hole 6 is the left side only one side plate 4.
Is provided, but it may be provided on both of the side plates 4 provided to face each other, or may be provided on only one side plate 4 on the right side.
【００１６】７は、側板４の内部を同一半径上で周方向
に穿設され、１側の側板４に周方向に等ピッチで設けら
れた小孔６の全部を側板４の内部で連通するようにした
環状通路である。Numeral 7 is formed in the side plate 4 in the circumferential direction at the same radius, and all the small holes 6 provided in the one side plate 4 at the same pitch in the circumferential direction communicate with the inside of the side plate 4. It is an annular passage as described above.
【００１７】これらの側板４、翼５、小孔６、および環
状通路７により、翼付ディフューザ８が構成されてい
る。また、９は翼付ディフューザ８の外周側に設けら
れ、翼付ディフューザ８とともに、羽根出口部２から吐
出される作動流体３の速度を静圧に回復させ、昇圧する
スクロールである。The side plate 4, the wing 5, the small hole 6, and the annular passage 7 constitute a winged diffuser 8. Reference numeral 9 denotes a scroll which is provided on the outer peripheral side of the winged diffuser 8 and restores the speed of the working fluid 3 discharged from the blade outlet 2 to static pressure together with the winged diffuser 8 to increase the pressure.
【００１８】上述した構成の本実施の形態の遠心圧縮機
用翼付ディフューザを具える遠心圧縮機の作用効果を、
図２、図３にもとづき説明する。図に示すように、羽根
車１の回転により、羽根車１の羽根出口部２において
は、ＰＳの圧力が高く、負圧面側（ＳＳ）の圧力が低
い、図４に示したものと同様の圧力分布Ｐ′が形成され
る。The operation and effect of the centrifugal compressor provided with the centrifugal compressor bladed diffuser of the present embodiment having the above-described configuration will be described below.
A description will be given based on FIGS. As shown in the drawing, the rotation of the impeller 1 causes the pressure of PS to be high and the pressure on the negative pressure side (SS) to be low at the blade outlet 2 of the impeller 1, similar to that shown in FIG. A pressure distribution P 'is formed.
【００１９】一方、翼５の前縁側のＰＳ側の上流側の側
板４の対向面に開口された小孔６は、全翼５に対応して
各々に設けられ、側板４の内部に設けられた環状通路７
により連通されている。このために、羽根車１の羽根出
口部２より吐出され、翼付ディフューザ８に流入する作
動流体３によって、翼５の前縁のＰＳで圧力が高く、Ｓ
Ｓで圧力が低くなり、周方向に変動する点線で示す圧力
分布Ｐにおける圧力変動は、この小孔６により均等化さ
れ、小孔６のない場合と比較して、ＰＳとＳＳでの圧力
差が小さい実線で示す圧力分布Ｐ″となる。On the other hand, the small holes 6 opened on the facing surface of the side plate 4 on the upstream side of the PS on the leading edge side of the wing 5 are provided corresponding to all the wings 5 and provided inside the side plate 4. Annular passage 7
Communication. For this reason, the working fluid 3 discharged from the blade outlet portion 2 of the impeller 1 and flowing into the winged diffuser 8 causes a high pressure at the PS at the leading edge of the wing 5, and S
The pressure fluctuation in the pressure distribution P indicated by the dotted line which fluctuates in the circumferential direction when the pressure decreases in S is equalized by the small holes 6, and the pressure difference between PS and SS is compared with the case without the small holes 6. Is a pressure distribution P ″ indicated by a small solid line.
【００２０】その結果、圧力分布Ｐ′が発生する、羽根
車１の羽根出口部のＰＳである、図２に示すＡ点が回転
して、圧力分布Ｐ″が発生している翼５の前縁側を通過
するときのＡ点の圧力ＰA の時間変動は、図３に実線で
示すようになる。すなわち、点線で示す小孔６を設けな
い場合の圧力ＰA の時間変動に比較して、実線で示す小
孔を設けた場合の圧力ＰA の時間変動は、急峻な圧力ピ
ークがなくなり、圧力の最大値ＰAmax、及びその振幅の
差ΔＰA が小さくなる。As a result, the point A shown in FIG. 2, which is the PS at the blade outlet of the impeller 1, at which the pressure distribution P 'is generated, rotates before the blade 5 at which the pressure distribution P "is generated. time variation of the pressure P a of the point a as it passes through the edge is as shown by the solid line in FIG. 3. in other words, compared to the time variation of the pressure P a in the case without the small holes 6 shown by a dotted line , the time variation of the pressure P a in the case of providing a small hole indicated by a solid line, there is no sudden pressure peak, the maximum value P Amax pressure, and the difference [Delta] P a of its amplitude decreases.
【００２１】これにより、遠心圧縮機の運転効率上、肉
厚を薄くせざるを得ない羽根車１の羽根出口部２や、翼
５前縁部にかかる圧力変動を小さくすることができると
ともに、振幅の最大値も、小さくすることができ、翼の
折損等を未然に防止でき、遠心圧縮機の信頼性を向上さ
せることができる。As a result, the pressure fluctuation applied to the blade outlet 2 of the impeller 1 and the leading edge of the blade 5 which must be reduced in thickness in terms of the operation efficiency of the centrifugal compressor can be reduced. The maximum value of the amplitude can also be reduced, breakage of the blade can be prevented, and the reliability of the centrifugal compressor can be improved.
【００２２】尚、上述した実施の形態では、小孔６、環
状通路７を側板４の一方側に設けたものを示したが、他
側の側板４に設けても良く、さらには、両方の側板４に
設けても、同様の効果が得られるものである。Although the small holes 6 and the annular passage 7 are provided on one side of the side plate 4 in the above-described embodiment, they may be provided on the other side plate 4. The same effect can be obtained even if it is provided on the side plate 4.
【００２３】[0023]
【発明の効果】以上説明したように、本発明の遠心圧縮
機用翼付ディフューザによれば、特許請求の範囲に示す
構成により、羽根車の羽根及びディフューザ翼の折損等
を未然に防止し、信頼性の高い遠心圧縮機が実現でき
る。また、折損を防止するための剛性の強化を図る必要
もなく、剛性強化に伴う、遠心圧縮機の効率低下、若し
くは重量増等の不具合を招くこともない。As described above, according to the centrifugal compressor bladed diffuser of the present invention, the blade impeller blades and the diffuser blades can be prevented from being broken, etc. A highly reliable centrifugal compressor can be realized. In addition, there is no need to increase the rigidity for preventing breakage, and there is no inconvenience such as a decrease in the efficiency of the centrifugal compressor or an increase in the weight due to the increased rigidity.
【図１】本発明の遠心圧縮機用翼付ディフューザの実施
の第１形態を示す図で、図１（ａ）は部分縦断面図、図
１（ｂ）は図１（ａ）に示す矢視Ａ−Ａにおける正面
図，FIG. 1 is a view showing a first embodiment of a diffuser with blades for a centrifugal compressor according to the present invention, wherein FIG. 1 (a) is a partial longitudinal sectional view, and FIG. 1 (b) is an arrow shown in FIG. 1 (a). Front view in sight A-A,
【図２】図１に示す実施の形態の遠心圧縮機用翼付ディ
フューザを具える遠心圧縮機の作用を説明する図，FIG. 2 is a view for explaining the operation of the centrifugal compressor having the centrifugal compressor bladed diffuser according to the embodiment shown in FIG. 1;
【図３】図１に示す実施の形態の遠心圧縮機用翼付ディ
フューザを設けたときの、羽根車の出口部ＰＳの回転位
置での圧力変動を示す図，FIG. 3 is a view showing a pressure fluctuation at a rotational position of an outlet portion PS of an impeller when the diffuser with blades for a centrifugal compressor according to the embodiment shown in FIG. 1 is provided;
【図４】従来の遠心圧縮機用翼付ディフューザを具える
遠心圧縮機の部分正面図、および作用を説明する図，FIG. 4 is a partial front view of a conventional centrifugal compressor provided with a bladed diffuser for a centrifugal compressor, and a view for explaining the operation thereof;
【図５】図４に示す遠心圧縮機用翼付ディフューザを設
けたときの、羽根車の出口部ＰＳの回転位置での圧力変
動を示す図である。FIG. 5 is a diagram showing pressure fluctuations at the rotational position of the outlet portion PS of the impeller when the centrifugal compressor bladed diffuser shown in FIG. 4 is provided.
１，０１ 羽根車 ２ 羽根出口部 ３ 作動流体 ４，０２ 側板 ５，０３ （ディフューザ）翼 ６ 小孔 ７ 環状通路 ８，０４ 翼付ディフューザ ９ スクロール 1,01 impeller 2 blade outlet 3 working fluid 4,02 side plate 5,03 (diffuser) wing 6 small hole 7 annular passage 8,04 winged diffuser 9 scroll
Claims (1)
対向して配設された２枚の環状円板からなる側板と、前
記側板の間を周方向に等ピッチで配設された複数の翼と
からなり、前記羽根車から吐出される作動流体の速度を
静圧に回復する遠心圧縮機用翼付ディフューザにおい
て、前記翼の上流圧力面側の前記側板に開口を設けた小
孔と、前記側板内を周方向に穿設され、前記小孔を連通
する環状通路とを設けたことを特徴とする遠心圧縮機用
翼付ディフューザ。1. An impeller discharge side passage of a centrifugal compressor, a side plate composed of two annular disks disposed to face each other, and a space between the side plates arranged at a constant pitch in a circumferential direction. A centrifugal compressor vaned diffuser comprising a plurality of vanes and recovering the velocity of a working fluid discharged from the impeller to a static pressure, wherein a small hole provided with an opening in the side plate on the upstream pressure surface side of the vane. And an annular passage formed in the side plate in a circumferential direction and communicating with the small hole.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| JP19630996A JP3492097B2 (en) | 1996-07-25 | 1996-07-25 | Diffuser with wings for centrifugal compressor |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| JP19630996A JP3492097B2 (en) | 1996-07-25 | 1996-07-25 | Diffuser with wings for centrifugal compressor |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| JPH1037899A true JPH1037899A (en) | 1998-02-13 |
| JP3492097B2 JP3492097B2 (en) | 2004-02-03 |
Family
ID=16355671
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| JP19630996A Expired - Fee Related JP3492097B2 (en) | 1996-07-25 | 1996-07-25 | Diffuser with wings for centrifugal compressor |
Country Status (1)
| Country | Link |
|---|---|
| JP (1) | JP3492097B2 (en) |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| KR100405984B1 (en) * | 2001-02-22 | 2003-11-15 | 엘지전자 주식회사 | Diffuser mounting structure of Turbo compressor |
| JP2009068423A (en) * | 2007-09-13 | 2009-04-02 | Ihi Corp | Centrifugal compressor |
| JP2019163725A (en) * | 2018-03-20 | 2019-09-26 | 本田技研工業株式会社 | Centrifugal compressor |
Citations (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPS58101299A (en) * | 1981-12-14 | 1983-06-16 | Hitachi Ltd | Centrifugal compressor |
| JPS6067797A (en) * | 1983-09-22 | 1985-04-18 | ドレツサ−・インダストリ−ズ・インコ−ポレ−テツド | Diffuser structure of centrifugal compressor |
-
1996
- 1996-07-25 JP JP19630996A patent/JP3492097B2/en not_active Expired - Fee Related
Patent Citations (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPS58101299A (en) * | 1981-12-14 | 1983-06-16 | Hitachi Ltd | Centrifugal compressor |
| JPS6067797A (en) * | 1983-09-22 | 1985-04-18 | ドレツサ−・インダストリ−ズ・インコ−ポレ−テツド | Diffuser structure of centrifugal compressor |
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| KR100405984B1 (en) * | 2001-02-22 | 2003-11-15 | 엘지전자 주식회사 | Diffuser mounting structure of Turbo compressor |
| JP2009068423A (en) * | 2007-09-13 | 2009-04-02 | Ihi Corp | Centrifugal compressor |
| JP2019163725A (en) * | 2018-03-20 | 2019-09-26 | 本田技研工業株式会社 | Centrifugal compressor |
| US10760588B2 (en) | 2018-03-20 | 2020-09-01 | Honda Motor Co., Ltd. | Centrifugal compressor |
Also Published As
| Publication number | Publication date |
|---|---|
| JP3492097B2 (en) | 2004-02-03 |
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