JPH02275097A - Diffuser for centrifugal compressor - Google Patents
Diffuser for centrifugal compressorInfo
- Publication number
- JPH02275097A JPH02275097A JP1092846A JP9284689A JPH02275097A JP H02275097 A JPH02275097 A JP H02275097A JP 1092846 A JP1092846 A JP 1092846A JP 9284689 A JP9284689 A JP 9284689A JP H02275097 A JPH02275097 A JP H02275097A
- Authority
- JP
- Japan
- Prior art keywords
- diffuser
- blade
- centrifugal compressor
- impeller
- stationary
- 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
- 238000010586 diagram Methods 0.000 description 15
- 230000000694 effects Effects 0.000 description 13
- 230000002093 peripheral effect Effects 0.000 description 7
- 238000005192 partition Methods 0.000 description 5
- 230000006866 deterioration Effects 0.000 description 3
- 230000005284 excitation Effects 0.000 description 2
- 238000000926 separation method Methods 0.000 description 2
- 239000012530 fluid Substances 0.000 description 1
- 230000007774 longterm Effects 0.000 description 1
- 238000000034 method Methods 0.000 description 1
Classifications
-
- C—CHEMISTRY; METALLURGY
- C30—CRYSTAL GROWTH
- C30B—SINGLE-CRYSTAL GROWTH; UNIDIRECTIONAL SOLIDIFICATION OF EUTECTIC MATERIAL OR UNIDIRECTIONAL DEMIXING OF EUTECTOID MATERIAL; REFINING BY ZONE-MELTING OF MATERIAL; PRODUCTION OF A HOMOGENEOUS POLYCRYSTALLINE MATERIAL WITH DEFINED STRUCTURE; SINGLE CRYSTALS OR HOMOGENEOUS POLYCRYSTALLINE MATERIAL WITH DEFINED STRUCTURE; AFTER-TREATMENT OF SINGLE CRYSTALS OR A HOMOGENEOUS POLYCRYSTALLINE MATERIAL WITH DEFINED STRUCTURE; APPARATUS THEREFOR
- C30B13/00—Single-crystal growth by zone-melting; Refining by zone-melting
- C30B13/16—Heating of the molten zone
- C30B13/22—Heating of the molten zone by irradiation or electric discharge
- C30B13/24—Heating of the molten zone by irradiation or electric discharge using electromagnetic waves
-
- 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
- F04D29/40—Casings; Connections of working fluid
- F04D29/42—Casings; Connections of working fluid for radial or helico-centrifugal pumps
- F04D29/44—Fluid-guiding means, e.g. diffusers
- F04D29/441—Fluid-guiding means, e.g. diffusers especially adapted for elastic fluid pumps
- F04D29/444—Bladed diffusers
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2250/00—Geometry
- F05D2250/50—Inlet or outlet
- F05D2250/52—Outlet
Landscapes
- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Physics & Mathematics (AREA)
- Electromagnetism (AREA)
- Crystallography & Structural Chemistry (AREA)
- Materials Engineering (AREA)
- Metallurgy (AREA)
- Organic Chemistry (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
Abstract
Description
【発明の詳細な説明】
〔産業上の利用分野〕
本発明は、遠心圧縮機用ディフューザに係り、特に、広
い作動範囲と高い効率が求められる高速遠心圧縮機に好
適な遠心圧縮機のディフューザに関するものである。[Detailed Description of the Invention] [Industrial Application Field] The present invention relates to a diffuser for a centrifugal compressor, and particularly to a diffuser for a centrifugal compressor suitable for a high-speed centrifugal compressor that requires a wide operating range and high efficiency. It is something.
一般的な遠心圧縮機について、第２１図および第２２図
を参照して説明する。A general centrifugal compressor will be explained with reference to FIGS. 21 and 22.
第２１図は、従来の遠心圧縮機の断面図、第２２図は、
第２１図のｘ−ｘ矢視断面図である。Fig. 21 is a sectional view of a conventional centrifugal compressor, and Fig. 22 is a sectional view of a conventional centrifugal compressor.
FIG. 22 is a sectional view taken along the line xx in FIG. 21;
一般に、遠心圧縮機は、第２１図および第２２図に示す
ような構造で、羽根車１の回転によって矢印２で示す方
向の空気流を発生させる。Generally, a centrifugal compressor has a structure as shown in FIGS. 21 and 22, and generates an air flow in the direction shown by an arrow 2 by rotation of an impeller 1.
羽根車１から流出する空気流２は、大きな速度エネルギ
ーを持っているので、羽根車１の下流側に当る羽根車外
周部に静止翼４を備えたディフューザを設けて、羽根車
１から吐出される流体の速度エネルギーを圧力エネルギ
ーに変換するように作られている。Since the air flow 2 flowing out from the impeller 1 has large velocity energy, a diffuser equipped with stationary blades 4 is provided on the outer circumference of the impeller on the downstream side of the impeller 1, so that the air flow 2 flowing out from the impeller 1 is It is designed to convert the velocity energy of a fluid into pressure energy.
ディフューザを構成する静止翼４は、第２２図に示すよ
うに、羽根車１の外周部に複数個放射状に設けられてお
り、これらの静止翼４の翼間にはディフューザ流路３が
形成されている。As shown in FIG. 22, a plurality of stationary blades 4 constituting the diffuser are provided radially around the outer circumference of the impeller 1, and a diffuser flow path 3 is formed between the blades of these stationary blades 4. ing.
一般に、遠心羽根車出口の流れは、第３図に示すように
、幅方向に歪んでいる。流れの歪の状況は、流れの方向
が側板側では羽根車め接線方向に近く、一方心板側では
側板側と比較して接線方向から離れる方向を示す。Generally, the flow at the outlet of the centrifugal impeller is distorted in the width direction, as shown in FIG. The state of flow distortion indicates that the direction of flow is close to the tangential direction of the impeller on the side plate side, while on the core plate side it is in a direction away from the tangential direction compared to the side plate side.
このような圧縮機において１通過流量を増してゆくと、
ディフューザの静止翼４と側壁とにより形成される流路
の最小断面積部分において、チョークの発生、あるいは
、最小断面積部分近くにおける損失の増加によって圧縮
機の性能が急激に低下する。When the one-pass flow rate is increased in such a compressor,
At the minimum cross-sectional area portion of the flow path formed by the stationary vanes 4 and the side walls of the diffuser, the performance of the compressor is rapidly reduced due to the occurrence of choke or an increase in loss near the minimum cross-sectional area portion.
また、比較的高速回転で低流量の条件では、静止翼４の
負圧面５に剥離流れ領域が発生し、充分な圧力上昇が得
られなくなるサージ現象が発生する。この問題を解決す
るために、静止翼間に補助翼を設けたディフューザが提
案されている。Further, under conditions of relatively high rotation speed and low flow rate, a separated flow region occurs on the negative pressure surface 5 of the stationary blade 4, and a surge phenomenon occurs in which a sufficient pressure increase cannot be obtained. In order to solve this problem, a diffuser in which an aileron is provided between stationary wings has been proposed.
補助翼を設ける場合、流路の最小断面積が減少しないよ
うに、翼はできる限り薄くすることが望ましいが、強度
上一定の厚さが必要となる。このため、静止翼の枚数を
十分な流路断面積が確保できる程度とする必要があるが
、このようにすると、静止翼の外周に近い側の流路は静
止翼の間隔が過大となる。その結果、静止翼４の後縁近
くの負圧面５では流れが翼面に沿わず大規模な剥離域が
生じることになり、流れの実質的な断面積が減少してデ
ィフューザの流路が減少するとともに剥離域内での運動
エネルギーの拡散が起る。When providing an auxiliary wing, it is desirable to make the wing as thin as possible so as not to reduce the minimum cross-sectional area of the flow path, but a certain thickness is required for strength. For this reason, it is necessary to set the number of stationary blades to such an extent that a sufficient cross-sectional area of the flow path can be ensured, but if this is done, the interval between the stationary blades becomes excessive in the flow path near the outer periphery of the stationary blades. As a result, on the suction surface 5 near the trailing edge of the stationary blade 4, the flow does not follow the blade surface and a large separation area occurs, reducing the effective cross-sectional area of the flow and reducing the flow path of the diffuser. At the same time, kinetic energy spreads within the separation region.
この種の遠心圧縮機の作動範囲は多くの場合。The operating range of this kind of centrifugal compressor is often.
ディフューザによってｆＭ限を受ける。すなわち、小流
量側ではディフューザで発生した逆流が羽根車にまで達
するようになる失速限界であり、大流量側ではディフュ
ーザにおけるチョーク限界であることが多い、したがっ
て、圧縮機の作動範囲の拡大を図るには、第１にディフ
ューザの作動範囲の拡大が必要であり、いくつかの方法
が提案されている。It is fM limited by the diffuser. In other words, on the small flow side, this is the stall limit where the backflow generated in the diffuser reaches the impeller, and on the large flow side, it is often the choke limit in the diffuser.Therefore, the operating range of the compressor is expanded. First, it is necessary to expand the operating range of the diffuser, and several methods have been proposed.
現在、比較的広く採用れているものは、静止翼４を羽根
車１の回転軸と平行な支軸により回転可動に支承し、静
止翼の方向を羽根車から流出する流れの方向に応じて変
化させる方法である。Currently, the one that is relatively widely adopted is that the stationary blade 4 is rotatably supported by a support shaft parallel to the rotation axis of the impeller 1, and the direction of the stationary blade is adjusted according to the direction of the flow flowing out from the impeller. This is a way to change it.
この他に、例えば、米国特許第３７８１１２８号に開示
されているように、静止翼の先端を延長して境界層板を
設けたものとか、米国特許第３９０４３１２号あるいは
実開昭５３−１６２４０５号公報記載のように。In addition, for example, as disclosed in U.S. Pat. No. 3,781,128, a boundary layer plate is provided by extending the tip of a stationary blade, or as disclosed in U.S. Pat. As stated.
静止翼の入口の角度を翼高さ方向に変化させるものなど
が提案されている。Some proposals have been made that change the angle of the inlet of a stationary blade in the blade height direction.
上記従来技術における、ディフューザ翼を可動とするも
のは、構造が複雑になり、また境界層板を設けるものは
、羽根車出口流れの歪が大きい遠心圧縮機では境界層板
の効果が十分でない、さらに、静止翼の入口の角度を翼
高さ方向に変化させるものの場合、従来のものでは１作
動ＭＡ囲の拡大が少なかったり、また、作動範囲の拡大
のため静止翼の前縁を羽根車に近づけると、小流量側の
作動範囲の拡大は可能であるが、流路の最小断面積が減
少するための大流量側の作動範囲は狭くなり。In the above-mentioned prior art, the structure with movable diffuser blades is complicated, and the one with a boundary layer plate does not have sufficient effect in a centrifugal compressor where the impeller outlet flow is highly distorted. Furthermore, in the case of a device that changes the inlet angle of a stationary blade in the blade height direction, the expansion of the 1-operation MA area is small in the conventional type, and in order to expand the operating range, the leading edge of the stationary blade is used as an impeller. If they are brought closer together, it is possible to expand the operating range on the small flow rate side, but the operating range on the large flow rate side becomes narrower because the minimum cross-sectional area of the flow path is reduced.
羽根車と静止翼の空力干渉による強い加振力によって、
長期間の運転後に静止翼ないし羽根車が破壊する虞れが
′ＩＰ）、Ａなどの問題があった。Due to the strong excitation force caused by aerodynamic interference between the impeller and the stationary blade,
There were problems such as 'IP) and A where there was a risk that the stationary blade or impeller would break after long-term operation.
本発明は、上記従来技術の問題点を解決するためになさ
れたもので、簡便な構造で広い作動範囲を持ち、高い強
度を有する遠心圧縮機用ディフューザを提供することを
、その目的とするものである。The present invention has been made to solve the problems of the prior art described above, and an object thereof is to provide a diffuser for a centrifugal compressor that has a simple structure, a wide operating range, and high strength. It is.
（Ｉ［Ｉｇを解決するための手段〕
上記目的を達成するために、本発明に係る遠心圧縮機用
ディフューザの構成は、羽根車の外周に複数の静止翼を
備えてディフューザを形成した遠心圧縮機用ディフュー
ザにおいて、前記ディフューザの静止翼の内周に近い側
に、前記静止翼よりも弦長が短く、かつ高さが同等以下
の補助翼を設け、この補助翼の先端側の弦長が根本側の
弦長より小さい形状をなすものである。(I [Means for Solving Ig]) In order to achieve the above object, the configuration of the diffuser for a centrifugal compressor according to the present invention is a centrifugal compressor in which a diffuser is formed by providing a plurality of stationary blades on the outer periphery of an impeller. In the aircraft diffuser, an aileron whose chord length is shorter than the stationary wing and whose height is equal to or less than the stationary wing is provided on the side near the inner circumference of the stationary wing of the diffuser, and the chord length of the tip side of this aileron is provided. It has a shape smaller than the chord length on the root side.
上記の技術的手段による働きは下記のとおりである。 The operation of the above technical means is as follows.
本発明によれば、小流量の条件下での静止翼負圧面にお
ける剥離流れ領域の発生傾向が補助翼によって抑制され
るので、小流量側の作動範囲が拡大される。大流量側で
は、補助翼は抵抗として作用するが、先端側の弦長が根
本側の弦長より小さいので１弦長が根本から先端まで同
一の場合に比較して、以下の２点より抵抗が大幅に少な
く、大流量側の性能低下を極めて少なくできる。According to the present invention, the aileron suppresses the tendency for a separated flow region to occur on the negative pressure surface of the stationary blade under conditions of a small flow rate, so that the operating range on the small flow rate side is expanded. On the large flow side, the aileron acts as a resistance, but since the chord length on the tip side is smaller than the chord length on the root side, compared to the case where the chord length is the same from the root to the tip, the aileron acts as a resistance due to the following two points. This greatly reduces performance deterioration on the high flow rate side.
すなわち、その第１は、流れにさらされる補助翼の表面
積が大幅に少ないことによるものであり。The first is that the surface area of the ailerons exposed to the flow is significantly less.
第２は、壁面から離れて壁面近くに比較して流速が大き
い補助翼先端側の弦長が小さいので、表面積の減少以上
に抵抗の減少が少ないことによるものである。The second reason is that the chord length on the tip side of the aileron, where the flow velocity is greater than that near the wall and away from the wall, is small, so the reduction in resistance is smaller than the reduction in surface area.
以上が空力性能面の補助翼の作用であるが、強度面につ
いても補助翼先端側の弦長が根本側弦長より小さいので
片持温度である補助翼の強度は。The above is the effect of the aileron in terms of aerodynamic performance, but in terms of strength, the chord length on the tip side of the aileron is smaller than the chord length on the root side, so the strength of the aileron at cantilever temperature is:
先端側と根本側の弦長が同一の場合に比較して格段に改
善される。This is much improved compared to the case where the chord lengths on the tip side and the root side are the same.
以下、本発明の各実施例を第１図ないし第２０図を参照
して説明する。Embodiments of the present invention will be described below with reference to FIGS. 1 to 20.
第１図は１本発明の一実施例に係る遠心圧縮機の縦断面
図、第２図は、第１図のディフューザ部の拡大図、第３
図は、第２図の静止翼、補助翼を示す立体配置図で、こ
の第３図では静止翼に流入する流れの速度ベクトルを合
わせて示している。1 is a vertical cross-sectional view of a centrifugal compressor according to an embodiment of the present invention; FIG. 2 is an enlarged view of the diffuser section in FIG. 1;
The figure is a three-dimensional layout diagram showing the stationary blade and ailerons in Figure 2, and Figure 3 also shows the velocity vector of the flow flowing into the stationary blade.
図において、第２１図および第２２図に示す従来例と同
一または同等部分には同一符号を付して示し、その説明
を省略する。In the figure, parts that are the same or equivalent to those of the conventional example shown in FIGS. 21 and 22 are denoted by the same reference numerals, and the explanation thereof will be omitted.
第１〜３図において、６は、静止翼４の内周に近い側に
設けられた補助翼で、この補助Ｘ６は、静止Ｘ４より弦
長が短く、高さが静止翼４より同等以下であ河、その補
助翼６の先端側１０の弦長が根本側９の弦長より小さい
形状をなしている。In Figures 1 to 3, reference numeral 6 indicates an auxiliary wing provided near the inner circumference of the stationary wing 4. This auxiliary wing The chord length of the tip side 10 of the aileron 6 is smaller than the chord length of the root side 9.
このような補助翼を有する遠心圧縮機のディフューザの
作用を説明する。The function of the diffuser of a centrifugal compressor having such an aileron will be explained.
第３図に示すように、側板側の速度ベクトル７は、羽根
車１の接線方向８に近いが、羽根車１近くまで延びてい
る補助翼６の根本側９に近い部分の長い弦長によって静
止翼４に沿う方向に強く導かれるから、羽根ポ１を流出
した流れが逆流するのが抑制され、圧縮機の少流量側の
作動範囲を拡大できる。これに対し、補助翼６の先端側
１０に近い部分の流れは、接線方向８から離れて静止翼
４に近い方向の流れとなっているので、短い弦長で静止
翼４に沿う方向に導くことができる。As shown in FIG. 3, the velocity vector 7 on the side plate side is close to the tangential direction 8 of the impeller 1, but due to the long chord length of the part near the root side 9 of the aileron 6 that extends close to the impeller 1. Since the flow is strongly guided in the direction along the stationary blades 4, the flow flowing out of the vane port 1 is prevented from flowing backward, and the operating range of the compressor on the low flow rate side can be expanded. On the other hand, the flow near the tip side 10 of the aileron 6 is away from the tangential direction 8 and flows in a direction closer to the stationary blade 4, so it is guided in a direction along the stationary blade 4 with a short chord length. be able to.
圧縮機が大流量で運転される状態では、補助翼６は抵抗
として作用するが、流速が大きい先端側の弦長が小さい
ので抵抗が少なく、大流量側の性能低下を防ぐことがで
きる。また、先端側１０の弦長が小さいので強靭な片持
構造にできる。When the compressor is operated at a large flow rate, the ailerons 6 act as resistance, but since the chord length on the tip side where the flow velocity is high is small, the resistance is small, and performance deterioration on the high flow rate side can be prevented. Further, since the chord length of the tip end side 10 is small, a strong cantilevered structure can be achieved.
第１〜３図の実施例によれば、補助翼の作用によって小
流量時に側板側に起る逆流を抑制することができ、小流
量側の作動範囲の拡大を図ることができる。According to the embodiment shown in FIGS. 1 to 3, the action of the ailerons can suppress the backflow that occurs on the side plate side when the flow rate is small, and the operating range on the side of the small flow rate can be expanded.
次に、第４図、第５図を参照して本発明の他の実施例（
第２の実施例）を説明する６
第４図は、本発明の他の実施例に係る遠心圧縮機の横断
面図、第５図は、第４図の静止翼、補助翼を示す立体配
置図であり、第１図と同一符号のものは同一部分である
から、その説明を省略する。Next, referring to FIGS. 4 and 5, other embodiments of the present invention (
6. Fig. 4 is a cross-sectional view of a centrifugal compressor according to another embodiment of the present invention, and Fig. 5 is a three-dimensional arrangement showing the stationary blades and ailerons in Fig. 4. 1, parts with the same reference numerals as those in FIG. 1 are the same parts, so a description thereof will be omitted.
第４，５図の実施例の特徴は、補助翼６Ａの前縁におけ
る側板側の羽根角βＳが各板側の羽根角βｈより大きく
なるように形成したことである。A feature of the embodiment shown in FIGS. 4 and 5 is that the blade angle βS on the side plate side at the leading edge of the aileron 6A is formed to be larger than the blade angle βh on each plate side.
本実施例によれば、補助翼６Ａの形状は複雑になるもの
の、補助翼の角度と流れの角度との一致が良いので、大
流量側、小流量側ともに一層の性能向上が期待できる。According to this embodiment, although the shape of the aileron 6A is complicated, since the angle of the aileron and the flow angle are well matched, further performance improvement can be expected on both the large flow rate side and the small flow rate side.
次に、第６図は１本発明のさらに他の実施例（第３の実
施例）に係る遠心圧縮機のディフューザ部の拡大図、第
７図は、第６図の静止翼、補助翼を示す立体配置図であ
る０図中、先の第２，３図と同一符号のものは同一部分
であるから、その説明を省略する。Next, FIG. 6 is an enlarged view of the diffuser section of a centrifugal compressor according to still another embodiment (third embodiment) of the present invention, and FIG. In Figure 0, which is a three-dimensional layout diagram, the same parts as those in Figures 2 and 3 are the same parts, so the explanation thereof will be omitted.
第６，７図の実施例が、先の第１〜３図の実施例と相違
するところは、補助翼６Ｂの形状を変えたことで、はぼ
台形に近い形状となっている。The embodiment shown in FIGS. 6 and 7 differs from the previous embodiment shown in FIGS. 1 to 3 in that the shape of the aileron 6B is changed, so that it has a shape close to a trapezoid.
第６，７図の実施例によれば、先の第１〜３１ｍの実施
例と同様の効果が期待されるほか、補助翼の剛性が一層
高められ強靭な片持構造にできるという本実施例特有の
効果がある。According to the embodiments shown in Figures 6 and 7, the same effects as the previous embodiments 1 to 31m can be expected, and the rigidity of the ailerons is further increased and a strong cantilevered structure can be achieved. It has a unique effect.
第８図は１本発明の一実施例に係る遠心圧縮機にディフ
ューザ部の寸法関係を説明する拡大図で、補助Ｈｅの効
果の高い人口側半径位置および高さを説明する図面とな
っている。FIG. 8 is an enlarged view illustrating the dimensional relationship of the diffuser part in a centrifugal compressor according to an embodiment of the present invention, and is a drawing illustrating the radial position and height on the artificial side where auxiliary He is highly effective. .
第８図において、羽根車１の半径ｒ１．補助翼６の前縁
の半径位置ｒ２．静止翼４前緻の半径位’Ｉｔ ｒ ａ
の間に、１＜ｒｚ／ｒｚ≦１．１≦ｒｓ／ｒｚの関係が
ある場合、および補助翼６の高さｂｌと静止翼４の高さ
ｂとの間に、０．１＜ｂｉ／ｂ（０，６の関係がある場
合に、補助翼６の効果が高い。In FIG. 8, the radius r1 of the impeller 1. Radial position r2 of the leading edge of the aileron 6. Radius position of stationary wing 4 forward
If there is a relationship of 1<rz/rz≦1.1≦rs/rz, and if 0.1<bi/ b(0,6, the effect of the ailerons 6 is high.
次に、第９図は１本発明の一実施例に係る遠心圧縮機の
寸法関係を説明する横断面図で、補助翼６の効果の高い
後縁位置に関するものである。Next, FIG. 9 is a cross-sectional view illustrating the dimensional relationship of a centrifugal compressor according to an embodiment of the present invention, and is related to the trailing edge position where the aileron 6 is highly effective.
補助翼６は、隣接する静止翼４ａおよび４ｂのうち、曲
率半径の中心側の静止［４ａの前縁から他方の静止翼４
ｂに下とした垂線１１と交叉しないように配置されてい
る。Of the adjacent stationary wings 4a and 4b, the aileron 6 is stationary on the center side of the radius of curvature [from the leading edge of 4a to the other stationary wing 4
It is arranged so as not to intersect with the perpendicular line 11 drawn down to b.
次に、第１０図は１本発明の第４の実施例に係る遠心圧
縮機のディフューザ部の拡大図、第１１図は、第１０図
の静止翼、ディフューザを示す立体配置図である１図中
、先の第２，３図と同一符号のものは同一部分であるか
ら、その説明を省略する。Next, FIG. 10 is an enlarged view of a diffuser section of a centrifugal compressor according to a fourth embodiment of the present invention, and FIG. 11 is a three-dimensional layout diagram showing the stationary blade and diffuser of FIG. 10. Components with the same reference numerals as those in FIGS. 2 and 3 are the same parts, so their explanation will be omitted.
第１０．１１図の実施例は、補助翼６Ｃは高さを低くシ
、かつ、下流側から静止翼４の後縁を通過する円に達す
る仕切板１２を静止翼４に沿って配置したものである。In the embodiment shown in FIG. 10.11, the aileron 6C has a low height, and a partition plate 12 reaching a circle passing through the trailing edge of the stationary blade 4 from the downstream side is arranged along the stationary blade 4. It is.
本実施例によれば、先の第１〜３図の実施例と同様の効
果が期待されるほか、補助翼６Ｃの剛性を一層高める本
実施例特有の効果がある。According to this embodiment, the same effects as those of the embodiment shown in FIGS. 1 to 3 can be expected, and there is also an effect unique to this embodiment of further increasing the rigidity of the aileron 6C.
また、上記各実施例によれば、静止翼または補助翼の前
縁の一部だけが羽根車の近くに存在するので、空力干渉
による加振力の影響が小さくなり。Furthermore, according to each of the embodiments described above, only a portion of the leading edge of the stationary wing or aileron exists near the impeller, so that the influence of the excitation force due to aerodynamic interference is reduced.
相対的に静止翼、補助翼羽根車の強度が増大し、高い信
頼性が確保される。The strength of the stationary wing and aileron impeller is relatively increased, ensuring high reliability.
次に、第１２図ないし第２０図は、静止翼の前縁側に補
助翼、後縁側に中間翼を設けた遠心圧縮機の実施例であ
り、これらの各図中、第２，３図と同一符号のものは同
一部分であるから、その説明を省略する。Next, Figures 12 to 20 show examples of centrifugal compressors in which an auxiliary blade is provided on the leading edge side of a stationary blade and an intermediate blade is provided on the trailing edge side. Components with the same reference numerals are the same parts, so a description thereof will be omitted.
第１２図は、本発明の第５の実施例に係る遠心圧縮機の
ディフューザ部の拡大図、第１３図は、第１２図の要部
を示す立体配置図、第１４図は、第１２図の遠心圧縮機
の横断面図である。FIG. 12 is an enlarged view of the diffuser section of a centrifugal compressor according to a fifth embodiment of the present invention, FIG. 13 is a three-dimensional layout diagram showing the main parts of FIG. 12, and FIG. FIG. 2 is a cross-sectional view of a centrifugal compressor.
第１２〜１４図の実施例では、第１〜３図の実施例で説
明した補助’Ｒ６を有するディフューザにおいて、静止
翼４の後縁側に静止翼と同じ高さの中間′Ｒ１３を配設
したものである。中間翼１３は、静止翼４の外周端から
隣接する静止翼の内周側への延長線に下した垂線１４を
通過し、その中間翼１３の外周端は静止翼４の外周端を
通過する円に達し、かつ垂線１４より内側にある中間翼
の長さは該中間′Ｒ１３全長の２０％以下としている。In the embodiment shown in FIGS. 12 to 14, in the diffuser having the auxiliary R6 described in the embodiment shown in FIGS. It is something. The intermediate blade 13 passes through a perpendicular line 14 drawn from the outer peripheral end of the stationary blade 4 to the inner peripheral side of the adjacent stationary blade, and the outer peripheral end of the intermediate blade 13 passes through the outer peripheral end of the stationary blade 4. The length of the intermediate blade that reaches the circle and is located inside the perpendicular line 14 is 20% or less of the entire length of the intermediate 'R13.
また、中間翼１３全体の形状は仮想的に該中間翼を羽根
車の回転軸中心を中心として回転移動した場合に静止翼
の内部に含まれるように構成されている。Moreover, the shape of the intermediate blade 13 as a whole is configured such that when the intermediate blade is virtually rotated about the rotation axis of the impeller, it is included inside the stationary blade.
ところで、内周側の補助翼６はできる限り簿くすること
が望ましいが１強度上一定の厚さが必要となる。このた
め、静止翼４の枚数を十分な流路断面積が確保できる程
度とする必要がある。By the way, it is desirable to make the aileron 6 on the inner peripheral side as thin as possible, but it is necessary to have a certain thickness for the sake of strength. For this reason, it is necessary to set the number of stationary blades 4 to such an extent that a sufficient cross-sectional area of the flow path can be ensured.
しかし、このようにすると、静止翼４の外周に近い側の
流路は静止翼の間隔が過大となり性能が低下するが、静
止翼間の外周に近い側には、中間翼１３が静止翼４の外
周端から隣接する静止翼の翼面に下した垂線１４の中点
を通過するように延在しているので、静止翼４の外周縁
付近は実質的に静止翼の間隔が適正な値となり性能低下
を防ぐことができる。However, in this case, the interval between the stationary blades becomes too large in the flow path near the outer periphery of the stationary blade 4, resulting in a decrease in performance. The space extends from the outer peripheral edge of the stationary blade 4 to pass through the midpoint of the perpendicular line 14 drawn to the blade surface of the adjacent stationary blade, so that the distance between the stationary blades is substantially at an appropriate value near the outer peripheral edge of the stationary blade 4. This can prevent performance deterioration.
第１２〜１４図の実施例によれば、先の第１〜３図の実
施例と同様の効果が期待されるほか、中間翼を配置した
のでディフューザの効率を改善できる。According to the embodiments shown in FIGS. 12 to 14, the same effects as those of the embodiments shown in FIGS. 1 to 3 can be expected, and the efficiency of the diffuser can be improved because intermediate blades are provided.
次に、第１５図、本発明の第６の実施例に係る遠心圧縮
機のディフューザ部の拡大図、第１６図は、第１５図の
要部を示す立体配置図である。Next, FIG. 15 is an enlarged view of a diffuser section of a centrifugal compressor according to a sixth embodiment of the present invention, and FIG. 16 is a three-dimensional layout diagram showing the main parts of FIG. 15.
第１５．１６図に示す実施例は、補助翼６と中間Ｘ１３
との間の側板側が、補助翼６より充分低い高さの仕切板
１５によって接続されている。The embodiment shown in Fig. 15.16 has an aileron 6 and an intermediate X13.
The side plates between the two are connected by a partition plate 15 whose height is sufficiently lower than that of the aileron 6.
第１５．１６図の実施例によれば、第１〜３図の実施例
と同様の効果が期待されるほか、補助翼６と中間翼１３
との間に仕切板１５を設けたので、翼の剛性が大きくな
り、長期にわたって安定した性能が保証される。According to the embodiment shown in Figs. 15 and 16, the same effects as those of the embodiment shown in Figs.
Since the partition plate 15 is provided between the blade and the blade, the rigidity of the blade is increased, and stable performance is guaranteed over a long period of time.
次に、第４７は、本発明の第７の実施例に係る遠心圧縮
機のディフューザ部の拡大図、第１８図は、第１７図の
要部を示す立体配！！！図である。Next, Fig. 47 is an enlarged view of the diffuser section of a centrifugal compressor according to the seventh embodiment of the present invention, and Fig. 18 is a three-dimensional layout showing the main parts of Fig. 17! ! ! It is a diagram.
第１７．１８図に示す実施例は、第１〜３図の実施例で
説明した補助翼６を有するディフューザにおいて、静止
翼４の後縁側に静止翼４より低い高さの中間翼１３Ａが
配置されたものである。The embodiment shown in FIGS. 17 and 18 is a diffuser having the ailerons 6 described in the embodiments of FIGS. It is what was done.
第１７．１８図の実施例によれば、先の第１２゜１３図
の実施例と同様の効果が期待される。According to the embodiment shown in FIGS. 17 and 18, the same effects as the embodiment shown in FIGS. 12 and 13 can be expected.
次に、第１９図は、本発明の第８の実施例に係る遠心圧
縮機のディフューザ部の拡大図、第２０図は、第１９図
の要部を示す立体配置図である。Next, FIG. 19 is an enlarged view of a diffuser section of a centrifugal compressor according to an eighth embodiment of the present invention, and FIG. 20 is a three-dimensional layout diagram showing the main parts of FIG. 19.
第１９．２０図に示す実施例は、第１７．１８図の実施
例で示した補助翼６と中間翼１３Ａとの間を、第１５．
１６図の実施例で示した仕切板１５によって接続したも
のである。The embodiment shown in Fig. 19.20 has the auxiliary wing 6 and the intermediate wing 13A shown in the embodiment shown in Fig. 17.
They are connected by the partition plate 15 shown in the embodiment shown in FIG.
第１９．２０図の実施例によれば、先の第１５゜１６図
の実施例と同様の効果が期待される。According to the embodiment shown in FIGS. 19 and 20, the same effects as those of the previous embodiment shown in FIGS. 15 and 16 can be expected.
以上詳細に説明したように、本発明によれば、簡便な構
造で広い作動範囲を持ち、高い強度を有する遠心圧縮機
用ディフューザを提供することができる。As described in detail above, according to the present invention, it is possible to provide a diffuser for a centrifugal compressor that has a simple structure, a wide operating range, and high strength.
第１図は１本発明の一実施例に係る遠心圧縮機の縦断面
図、第２図は、第１図のディフューザ部の拡大図、第３
図は、第２図の静止翼、補助翼を示す立体配置図、第４
図は、本発明の他の実施例に係る遠心圧縮機の横断面図
、第５図は、第４図の静止翼、補助翼を示す立体配置図
、第６図は、本発明のさらに他の実施例に係る遠心圧縮
機のディフューザ部の拡大図、第７図は、第６図の静止
翼、補助翼を示す立体配置図、第８図は、本発明の一実
施例に係る遠心圧縮機のディフューザ部の寸法関係を説
明する拡大図、第９図は、本発明の一実施例に係る遠心
圧縮機の寸法関係を説明する横断面図、第１０図は、本
発明の第４の実施例に係る遠心圧縮機のディフューザ部
の拡大図、第１１図は、第１０図の静止翼、補助翼を示
す立体配置図、第１２図は、本発明の第５の実施例に係
る遠心圧縮機のディフューザ部の拡大図、第１３図は、
第１２図の要部を示す立体配置図、第１４図は、第１２
図の遠心圧縮機の横断面図、第１５図は１本発明の第６
の実施例に係る遠心圧縮機のデイプユーザ部の拡大図、
第１６図は、第１５図の要部を示す立体配置図、第１７
図は、本発明の第７の実施例に係る遠心圧縮機のディフ
ューザ部の拡大図、第１８図は、第１７図の要部を示す
立体配置図１本１９図は、本発明の第８の実施例に係る
遠心圧縮機のディフューザ部の拡大図、第２０図は、第
１９図の要部を示す立体配置図、第２１図は、従来の遠
心圧縮機の断面図、第２２図は、第２１図のＸ−ｘ矢視
断面図である。
１・・・羽根車、３・・・ディフューザ通路、４・・・
静止翼、６．６Ａ、６Ｂ、６Ｇ・・・静止翼、９・・・
根本側、１０・・・先端側、１２．１５・・・仕切板、
１３．１３Ａ蔓 １ 図
ノ
１−−一羽躍卓
３−デイｈ−す嬰
第
図
第
図
冨
乙
図
葛
巳
で
図
！
図
不
篤
ｔθ
国
１ｚ ・・−イブ＝９１シ乏、
不
遁
／４
因
乙
ｊ３−−一中間１゜
第
口
冨
冨
図
第
図
Ｉ５．−−イ尤ｔ７ノシ之
慕
図
慕
ｇ
図
葛
図
冨
２ρ
図1 is a vertical cross-sectional view of a centrifugal compressor according to an embodiment of the present invention; FIG. 2 is an enlarged view of the diffuser section in FIG. 1;
The figure is a three-dimensional layout diagram showing the stationary wing and ailerons in Figure 2, and Figure 4.
5 is a cross-sectional view of a centrifugal compressor according to another embodiment of the present invention, FIG. 5 is a three-dimensional layout diagram showing the stationary blade and aileron of FIG. 4, and FIG. FIG. 7 is an enlarged view of the diffuser part of a centrifugal compressor according to an embodiment of the present invention, FIG. 7 is a three-dimensional layout diagram showing the stationary blades and ailerons of FIG. FIG. 9 is a cross-sectional view illustrating the dimensional relationship of a centrifugal compressor according to an embodiment of the present invention, and FIG. FIG. 11 is an enlarged view of the diffuser section of the centrifugal compressor according to the embodiment, FIG. 11 is a three-dimensional layout diagram showing the stationary blades and ailerons in FIG. 10, and FIG. 12 is the centrifugal compressor according to the fifth embodiment of the present invention. Figure 13 is an enlarged view of the diffuser section of the compressor.
Figure 14 is a three-dimensional layout diagram showing the main parts of Figure 12.
15 is a cross-sectional view of the centrifugal compressor shown in FIG.
An enlarged view of the deep user part of the centrifugal compressor according to the embodiment,
Figure 16 is a three-dimensional layout diagram showing the main parts of Figure 15;
The figure is an enlarged view of the diffuser section of a centrifugal compressor according to the seventh embodiment of the present invention, FIG. 18 is a three-dimensional layout diagram showing the main parts of FIG. 17, and FIG. FIG. 20 is a three-dimensional layout diagram showing the main parts of FIG. 19, FIG. 21 is a sectional view of a conventional centrifugal compressor, and FIG. , is a sectional view taken along the line X-x in FIG. 21. 1... Impeller, 3... Diffuser passage, 4...
Stationary wing, 6.6A, 6B, 6G... Stationary wing, 9...
Root side, 10... tip side, 12.15... partition plate,
13. 13A vine 1 Figure No. 1--Ichiba Yutaku 3-Day h-Su-yo Figure Figure Tomitsu-zu Katsumi! Figure Futsu tθ Country 1z...-Eve = 91 Shisho, Futon/4 Inotsu j3--One middle 1゜゜口冨冨图 Figure I5. --I尤t7 Noshi no Muzu Mug Figure Gezuzu Tomi 2ρ Figure
Claims (1)
を形成した遠心圧縮機用ディフューザにおいて、前記デ
ィフューザの静止翼の内周に近い側に、前記静止翼より
も弦長が短く、かつ高さが同等以下の補助翼を設け、こ
の補助翼の先端側の弦長が根本側の弦長より小さい形状
をなすことを特徴とする遠心圧縮機用ディフューザ。1. In a diffuser for a centrifugal compressor in which a plurality of stationary blades are provided on the outer periphery of an impeller to form a diffuser, a diffuser having a chord length shorter than that of the stationary blade and a height 1. A diffuser for a centrifugal compressor, characterized in that the ailerons are provided with aileron blades of equal or smaller diameter, and the chord length of the tip side of the aileron blades is smaller than the chord length of the root side.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| JP1092846A JPH02275097A (en) | 1989-04-14 | 1989-04-14 | Diffuser for centrifugal compressor |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| JP1092846A JPH02275097A (en) | 1989-04-14 | 1989-04-14 | Diffuser for centrifugal compressor |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| JPH02275097A true JPH02275097A (en) | 1990-11-09 |
Family
ID=14065795
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| JP1092846A Pending JPH02275097A (en) | 1989-04-14 | 1989-04-14 | Diffuser for centrifugal compressor |
Country Status (1)
| Country | Link |
|---|---|
| JP (1) | JPH02275097A (en) |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JP2013519035A (en) * | 2010-02-05 | 2013-05-23 | キャメロン インターナショナル コーポレイション | Vanelet of diffuser of centrifugal compressor |
| JP2019178616A (en) * | 2018-03-30 | 2019-10-17 | 日立グローバルライフソリューションズ株式会社 | Electric blower and vacuum cleaner employing the same |
| WO2022093434A1 (en) * | 2020-10-30 | 2022-05-05 | Praxair Technology, Inc. | Hydrogen centrifugal compressor |
-
1989
- 1989-04-14 JP JP1092846A patent/JPH02275097A/en active Pending
Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JP2013519035A (en) * | 2010-02-05 | 2013-05-23 | キャメロン インターナショナル コーポレイション | Vanelet of diffuser of centrifugal compressor |
| EP2531732B1 (en) * | 2010-02-05 | 2019-03-06 | Ingersoll-Rand Company | Centrifugal compressor diffuser vanelet |
| JP2019178616A (en) * | 2018-03-30 | 2019-10-17 | 日立グローバルライフソリューションズ株式会社 | Electric blower and vacuum cleaner employing the same |
| WO2022093434A1 (en) * | 2020-10-30 | 2022-05-05 | Praxair Technology, Inc. | Hydrogen centrifugal compressor |
| US11401947B2 (en) | 2020-10-30 | 2022-08-02 | Praxair Technology, Inc. | Hydrogen centrifugal compressor |
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