WO2013108712A1 - Centrifugal compressor - Google Patents

Centrifugal compressor Download PDF

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Publication number
WO2013108712A1
WO2013108712A1 PCT/JP2013/050360 JP2013050360W WO2013108712A1 WO 2013108712 A1 WO2013108712 A1 WO 2013108712A1 JP 2013050360 W JP2013050360 W JP 2013050360W WO 2013108712 A1 WO2013108712 A1 WO 2013108712A1
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Prior art keywords
diffuser
impeller
centrifugal compressor
side line
hub side
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PCT/JP2013/050360
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French (fr)
Japanese (ja)
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山下　修一
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三菱重工業株式会社
三菱重工コンプレッサ株式会社
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Application filed by 三菱重工業株式会社, 三菱重工コンプレッサ株式会社 filed Critical 三菱重工業株式会社
Priority to US14/366,910 priority Critical patent/US20140369823A1/en
Priority to EP13738815.3A priority patent/EP2806170B1/en
Priority to CN201380004288.3A priority patent/CN103998790B/en
Publication of WO2013108712A1 publication Critical patent/WO2013108712A1/en

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    • 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
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D29/00—Details, component parts, or accessories
    • F04D29/26—Rotors specially for elastic fluids
    • F04D29/28—Rotors specially for elastic fluids for centrifugal or helico-centrifugal pumps for radial-flow or helico-centrifugal pumps
    • F04D29/284—Rotors specially for elastic fluids for centrifugal or helico-centrifugal pumps for radial-flow or helico-centrifugal pumps for compressors
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D17/00—Radial-flow pumps, e.g. centrifugal pumps; Helico-centrifugal pumps
    • F04D17/08—Centrifugal pumps
    • F04D17/10—Centrifugal pumps for compressing or evacuating
    • 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

Definitions

  • the present invention relates to a centrifugal compressor, and particularly to a centrifugal compressor having a large flow rate.
  • Increasing the flow rate in a centrifugal compressor means increasing the discharge flow rate in a compressor having the same outer shell size and an impeller having the same outer diameter.
  • the conventional centrifugal compressor mainly includes a suction port 1, an impeller 2, a hub 3, a rotating shaft 4, a diffuser 5, and a scroll 6.
  • the impeller 2 is connected to the rotary shaft 4 via the hub 3, and the diffuser 5 is provided downstream of the impeller 2, the flow path faces away from the rotary shaft 4, and the outlet is in the radial direction on the meridian plane Furthermore, the scroll 6 is provided downstream of the diffuser 5 and is connected to the outlet of the diffuser 5.
  • the suction port 1 has a role to guide the gas to the impeller 2.
  • the gas guided to the impeller 2 is structured such that the gas is sucked into the centrifugal compressor when the impeller 2 is rotated by the rotating shaft 4.
  • the gas that has passed through the impeller 2 is decelerated by the diffuser 5 to increase the pressure.
  • the gas that has passed through the diffuser 5 flows into a scroll 6 and then flows into a discharge port (not shown). In this way, the centrifugal compressor converts the kinetic energy of the gas into pressure.
  • FIG. 7 is a cross-sectional view of a diffuser 5 and an impeller 2 of a conventional centrifugal compressor.
  • the energy loss decreases as the gas velocity vector (arrow in the figure) is oriented in the radial direction on the meridian plane.
  • the gas sucked from the impeller inlet 2a has a velocity distribution at the point of the impeller outlet 2b. Is biased toward the hub 3, and the velocity vector is inclined in the axial direction from the radial direction.
  • the velocity distribution is further distorted, which becomes a cause of shear stress, reducing the amount of static pressure recovered, and reducing the overall efficiency of the compressor. Connected.
  • the present invention aims to solve the problems of the prior art by changing the shape of the diffuser instead of providing a new mechanism, and to improve the efficiency of a centrifugal compressor with a large flow rate.
  • the centrifugal compressor according to the first invention for solving the above-mentioned problems is An impeller connected to the rotating shaft via a hub;
  • a centrifugal compressor provided with a diffuser provided downstream of the impeller and having a flow path facing a direction away from the rotation axis and an outlet facing a radial direction on a meridian plane
  • An angle formed by the diffuser inlet hub side line at a point closest to the impeller outlet of the diffuser inlet hub side line that is the hub side line at the inlet of the diffuser with respect to the radial direction on the meridian plane is ⁇
  • the impeller The angle of the tangent of the impeller hub side line that is the hub side line closest to the diffuser inlet to the radial direction on the meridian plane is ⁇ > 0 °.
  • a centrifugal compressor according to the second invention for solving the above-mentioned problems is In the centrifugal compressor according to the first invention, The ⁇ is 0 ° ⁇ ⁇ 34 °.
  • a centrifugal compressor according to a third invention for solving the above-described problem is In the centrifugal compressor according to the first or second invention, the diffuser inlet hub side line is a concave curve.
  • the centrifugal compressor according to the first aspect of the present invention by setting ⁇ > 0 °, the distortion of the gas velocity distribution is eliminated, and accordingly, the reduction of the static pressure recovery amount is suppressed, and the whole compressor High efficiency can be achieved.
  • the distortion of the gas velocity distribution can be further eliminated.
  • the centrifugal compressor according to the third aspect of the present invention by making the diffuser inlet hub side line a concave curve, the stagnation area in the diffuser is reduced, and higher efficiency can be achieved.
  • the apparatus mainly includes a suction port 1, an impeller 2, a hub 3, a rotating shaft 4, a diffuser 5, and a scroll 6, as in a conventional centrifugal compressor.
  • the impeller 2 is connected to the rotary shaft 4 via the hub 3, and the diffuser 5 is provided downstream of the impeller 2, the flow path faces away from the rotary shaft 4, and the outlet is in the radial direction on the meridian plane
  • the scroll 6 is provided downstream of the diffuser 5 and is connected to the outlet of the diffuser 5.
  • the rotating shaft 4 and the scroll 6 are not shown in FIG.
  • the suction port 1 has a role of guiding the gas to the impeller 2.
  • the gas guided to the impeller 2 is structured such that the gas is sucked into the centrifugal compressor when the impeller 2 is rotated by the rotating shaft 4.
  • the gas that has passed through the impeller 2 is decelerated by the diffuser 5 to increase the pressure.
  • the gas that has passed through the diffuser 5 flows into the discharge port after flowing into the scroll 6.
  • the line on the hub 3 side at the inlet of the diffuser 5 (hereinafter referred to as the diffuser inlet hub side line 5a) is inclined from the radial direction to the axial direction on the meridian plane.
  • an angle between the diffuser inlet hub side line 5a and the radial direction at a point B closest to the impeller outlet 2b of the diffuser inlet hub side line 5a is defined as ⁇ .
  • the angle formed by the tangent line 3b at the point A closest to the inlet of the diffuser 5 of the line on the hub 3 side of the impeller 2 (hereinafter referred to as the impeller hub side line 3a) is defined as ⁇ .
  • ⁇ be the angle formed by the impeller trailing edge 2c and the axial direction.
  • ⁇ is not particularly limited, but 0 ° ⁇ ⁇ ⁇ 35 °, which is a value used in a general centrifugal compressor.
  • the shroud 7 line matches the diffuser width ratio of the conventional shape, the shroud 7 line is also tilted as much as ⁇ is tilted.
  • FIG. 2 The simulation results of the compressor efficiency of this apparatus are shown in FIG. 2 where ⁇ and ⁇ are certain values and only ⁇ is a variable.
  • the horizontal axis represents ⁇
  • the vertical axis represents the compressor efficiency improvement rate.
  • the compressor efficiency improvement rate is the percentage difference between the compressor efficiency of this device and the compressor efficiency of the conventional technology. The higher the graph, the higher the compressor efficiency of this device. Is shown. From this, it can be seen that the compressor efficiency is improved when 0 ° ⁇ ⁇ 34 °.
  • the apparatus according to the second embodiment of the present invention is an improvement of the apparatus according to the first embodiment.
  • FIG. 4 shows differences between the apparatus according to the first embodiment and the present apparatus.
  • the diffuser inlet hub side line 5a is a straight line. Therefore, if the outlet of the diffuser 5 is directed in the radial direction, the angle of the diffuser 5 must be changed somewhere. Therefore, as shown in FIG. 4, a stagnation region 11 where the gas flow is stagnated is formed. A shear stress acts between the gas accumulated in the stagnation region 11 and the flowing gas, which may cause energy loss. This apparatus reduces this stagnation area 11.
  • This device is mainly provided with a suction port 1, an impeller 2, a hub 3, a rotating shaft 4, a diffuser 5 and a scroll 6 as shown in FIG.
  • the impeller 2 is connected to the rotary shaft 4 via the hub 3, and the diffuser 5 is provided downstream of the impeller 2, the flow path faces away from the rotary shaft 4, and the outlet is in the radial direction on the meridian plane
  • the scroll 6 is provided downstream of the diffuser 5 and is connected to the outlet of the diffuser 5.
  • the rotating shaft 4 and the scroll 6 are not shown in FIG. Further, since the apparatus operation is the same as that of the apparatus according to the first embodiment and the related art, the description thereof is omitted.
  • this apparatus makes the diffuser inlet hub side line 5b a concave curve, and an angle formed by the tangent line 5c of the diffuser inlet hub side line 5b at the point B closest to the impeller outlet 2b of the diffuser inlet hub side line 5b with the radial direction.
  • the diffuser inlet hub side line 5b may be a single arc as long as it is a curve, or a plurality of arcs or ellipses may be smoothly combined.
  • this apparatus can reduce a shear stress and can achieve higher efficiency.
  • the present invention is suitable as a centrifugal compressor, particularly as a high flow centrifugal compressor.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)

Abstract

A centrifugal compressor for which θ-α > 0° and 0°< θ < 34°, when the angle formed by a diffuser inlet hub-side line (5a) and the radial direction at a point B in the meridian plane is θ, and the angle formed by a tangent line (3b) and the radial direction at a point A of an impeller hub-side line (3a) nearest the inlet of the diffuser (5) is α. Thus, skewing of the velocity distribution of a gas within the diffuser of the centrifugal compressor is eliminated.

Description

遠心圧縮機Centrifugal compressor
　本発明は遠心圧縮機、特に大流量の遠心圧縮機に関する。 The present invention relates to a centrifugal compressor, and particularly to a centrifugal compressor having a large flow rate.
　過給機、ガスタービン、産業用圧縮機等の製品では、性能向上の上で、大流量化が重大な課題である。遠心圧縮機における大流量化とは、同一外殻サイズの圧縮機、さらに同一外径のインペラにおいて、吐出流量を大きくするという意味である。 ∙ For products such as turbochargers, gas turbines, and industrial compressors, increasing the flow rate is an important issue for improving performance. Increasing the flow rate in a centrifugal compressor means increasing the discharge flow rate in a compressor having the same outer shell size and an impeller having the same outer diameter.
　この大流量化に伴う課題として効率低下が挙げられる。そのため、効率低下を抑制しながら大流量化する技術は工業上非常に有意義である。 An issue associated with this increase in flow rate is a decrease in efficiency. Therefore, the technology for increasing the flow rate while suppressing the decrease in efficiency is very significant industrially.
　従来の遠心圧縮機について図６を用いて説明する。従来の遠心圧縮機は、主に吸入口１、インペラ２、ハブ３、回転軸４、ディフューザ５及びスクロール６を備える。 A conventional centrifugal compressor will be described with reference to FIG. The conventional centrifugal compressor mainly includes a suction port 1, an impeller 2, a hub 3, a rotating shaft 4, a diffuser 5, and a scroll 6.
　インペラ２はハブ３を介して回転軸４に接続されており、また、ディフューザ５はインペラ２の下流に設けられ、流路が回転軸４から離れる方向を向き、且つ出口が子午面における半径方向を向いており、さらに、スクロール６はディフューザ５の下流に設けられ、ディフューザ５の出口と繋がっている。 The impeller 2 is connected to the rotary shaft 4 via the hub 3, and the diffuser 5 is provided downstream of the impeller 2, the flow path faces away from the rotary shaft 4, and the outlet is in the radial direction on the meridian plane Furthermore, the scroll 6 is provided downstream of the diffuser 5 and is connected to the outlet of the diffuser 5.
　吸入口１はガスをインペラ２へ案内する役割を持つ。インペラ２へ案内されたガスは、インペラ２が回転軸４により回転することで、ガスを遠心圧縮機内に吸入する仕組みとなっている。インペラ２を通過したガスは、ディフューザ５にて減速され、昇圧する。ディフューザ５を通過したガスは、スクロール６に流入後、図示しない吐出口へ流れるようになっている。このようにして、遠心圧縮機はガスの運動エネルギーを圧力に変換させている。 The suction port 1 has a role to guide the gas to the impeller 2. The gas guided to the impeller 2 is structured such that the gas is sucked into the centrifugal compressor when the impeller 2 is rotated by the rotating shaft 4. The gas that has passed through the impeller 2 is decelerated by the diffuser 5 to increase the pressure. The gas that has passed through the diffuser 5 flows into a scroll 6 and then flows into a discharge port (not shown). In this way, the centrifugal compressor converts the kinetic energy of the gas into pressure.
　図７は従来の遠心圧縮機のディフューザ５及びインペラ２の断面図である。ガスの速度ベクトル（図中の矢印）が子午面における半径方向に向いているほどエネルギー損失は少なくなるが、大流量になると、インペラ入口２ａから吸入されたガスはインペラ出口２ｂの時点で速度分布がハブ３側に偏ってしまい、速度ベクトルが半径方向から軸方向に傾いてしまう。また、そのままガスがディフューザ５内を進んでいくとさらに速度分布が歪（ひず）み、それがせん断応力の発生要因となって、静圧回復量が減少し、圧縮機全体の効率低下に繋がる。 FIG. 7 is a cross-sectional view of a diffuser 5 and an impeller 2 of a conventional centrifugal compressor. The energy loss decreases as the gas velocity vector (arrow in the figure) is oriented in the radial direction on the meridian plane. However, when the flow rate is large, the gas sucked from the impeller inlet 2a has a velocity distribution at the point of the impeller outlet 2b. Is biased toward the hub 3, and the velocity vector is inclined in the axial direction from the radial direction. Further, as the gas advances through the diffuser 5 as it is, the velocity distribution is further distorted, which becomes a cause of shear stress, reducing the amount of static pressure recovered, and reducing the overall efficiency of the compressor. Connected.
　その解決策として、ディフューザ内に、案内羽根（特許文献１参照）や、インペラ入口への案内流路（特許文献２参照）等を設け、ガスの速度分布を一様な分布に近づける方法がある。 As a solution, there is a method in which a guide vane (see Patent Document 1), a guide flow path to an impeller inlet (see Patent Document 2), and the like are provided in the diffuser to make the gas velocity distribution close to a uniform distribution. .
特許第２５６９１４３号公報Japanese Patent No. 2569143 特許第２７０３０５５号公報Japanese Patent No. 2703555
　しかしながら上述のような装置では、ディフューザ内に新たな機構を設けなければならず、生産コストや作業時間の浪費となってしまう可能性がある。 However, in the apparatus as described above, a new mechanism must be provided in the diffuser, which may waste production costs and work time.
　そこで本発明では、新たな機構を設けるのではなく、ディフューザの形状を変化させることで、従来技術の問題点を解消し、大流量の遠心圧縮機における高効率化を図ることを目的とする。 Therefore, the present invention aims to solve the problems of the prior art by changing the shape of the diffuser instead of providing a new mechanism, and to improve the efficiency of a centrifugal compressor with a large flow rate.
　上記課題を解決する第１の発明に係る遠心圧縮機は、
　ハブを介して回転軸に接続されたインペラと、
　当該インペラの下流に設けられ、流路が前記回転軸から離れる方向を向き、且つ出口が子午面における半径方向を向いたディフューザとを備える遠心圧縮機において、
　前記ディフューザの入口における前記ハブ側のラインであるディフューザ入口ハブ側ラインの、最も前記インペラの出口に近い点における、前記ディフューザ入口ハブ側ラインが子午面における半径方向となす角度をθとし、前記インペラの前記ハブ側のラインであるインペラハブ側ラインの、最も前記ディフューザの入口に近い点における接線が、子午面における半径方向となす角度をαとしたとき、θ－α＞０°であることを特徴とする。 The centrifugal compressor according to the first invention for solving the above-mentioned problems is
An impeller connected to the rotating shaft via a hub;
In a centrifugal compressor provided with a diffuser provided downstream of the impeller and having a flow path facing a direction away from the rotation axis and an outlet facing a radial direction on a meridian plane,
An angle formed by the diffuser inlet hub side line at a point closest to the impeller outlet of the diffuser inlet hub side line that is the hub side line at the inlet of the diffuser with respect to the radial direction on the meridian plane is θ, and the impeller The angle of the tangent of the impeller hub side line that is the hub side line closest to the diffuser inlet to the radial direction on the meridian plane is θ−α> 0 °. And
　上記課題を解決する第２の発明に係る遠心圧縮機は、
　上記第１の発明に係る遠心圧縮機において、
　前記θが、０°＜θ＜３４°であることを特徴とする。 A centrifugal compressor according to the second invention for solving the above-mentioned problems is
In the centrifugal compressor according to the first invention,
The θ is 0 ° <θ <34 °.
　上記課題を解決する第３の発明に係る遠心圧縮機は、
　上記第１または２の発明に係る遠心圧縮機において、
　前記ディフューザ入口ハブ側ラインが凹状の曲線であることを特徴とする。 A centrifugal compressor according to a third invention for solving the above-described problem is
In the centrifugal compressor according to the first or second invention,
The diffuser inlet hub side line is a concave curve.
　上記第１の発明に係る遠心圧縮機によれば、θ－α＞０°とすることで、ガスの速度分布の歪みが解消され、それに伴い静圧回復量の減少が抑制され、圧縮機全体での高効率化が可能となる。 According to the centrifugal compressor according to the first aspect of the present invention, by setting θ−α> 0 °, the distortion of the gas velocity distribution is eliminated, and accordingly, the reduction of the static pressure recovery amount is suppressed, and the whole compressor High efficiency can be achieved.
　上記第２の発明に係る遠心圧縮機によれば、０°＜θ＜３４°とすることで、よりガスの速度分布の歪みを解消することができる。 According to the centrifugal compressor according to the second aspect of the invention, by setting 0 ° <θ <34 °, the distortion of the gas velocity distribution can be further eliminated.
　上記第３の発明に係る遠心圧縮機によれば、ディフューザ入口ハブ側ラインを凹状の曲線とすることで、ディフューザ内の淀み域が減少し、より高効率化が可能となる。 According to the centrifugal compressor according to the third aspect of the present invention, by making the diffuser inlet hub side line a concave curve, the stagnation area in the diffuser is reduced, and higher efficiency can be achieved.
本発明の実施例１に係る遠心圧縮機のディフューザ及びインペラの断面図である。It is sectional drawing of the diffuser and impeller of the centrifugal compressor which concerns on Example 1 of this invention. 本発明の実施例１に係る遠心圧縮機のθと効率改善率の関係を示したグラフである。It is the graph which showed the relationship between (theta) and the efficiency improvement rate of the centrifugal compressor which concerns on Example 1 of this invention. 本発明の実施例２に係る遠心圧縮機のディフューザ及びインペラの断面図である。It is sectional drawing of the diffuser and impeller of the centrifugal compressor which concerns on Example 2 of this invention. 本発明の実施例１に係る遠心圧縮機と本発明の実施例２に係る遠心圧縮機との相違点を示した模式図である。It is the schematic diagram which showed the difference between the centrifugal compressor which concerns on Example 1 of this invention, and the centrifugal compressor which concerns on Example 2 of this invention. 本発明の実施例１または２に係る遠心圧縮機のθとαの関係を示す概略図である。It is the schematic which shows the relationship of (theta) and (alpha) of the centrifugal compressor which concerns on Example 1 or 2 of this invention. 従来の遠心圧縮機の断面図である。It is sectional drawing of the conventional centrifugal compressor. 従来の遠心圧縮機のディフューザ及びインペラの断面図である。It is sectional drawing of the diffuser and impeller of the conventional centrifugal compressor.
　以下、本発明に係る遠心圧縮機を実施例にて図面を用いて説明する。 Hereinafter, the centrifugal compressor according to the present invention will be described with reference to the drawings in the embodiments.
　本発明の実施例１に係る装置について図１を用いて説明する。本装置は、従来の遠心圧縮機と同様、主に吸入口１、インペラ２、ハブ３、回転軸４、ディフューザ５及びスクロール６を備える。インペラ２はハブ３を介して回転軸４に接続されており、また、ディフューザ５はインペラ２の下流に設けられ、流路が回転軸４から離れる方向を向き、且つ出口が子午面における半径方向を向いており、さらに、スクロール６はディフューザ５の下流に設けられ、ディフューザ５の出口と繋がっている。尚、回転軸４やスクロール６は図１中にはないが、従来技術と同様とする。 The apparatus according to the first embodiment of the present invention will be described with reference to FIG. The apparatus mainly includes a suction port 1, an impeller 2, a hub 3, a rotating shaft 4, a diffuser 5, and a scroll 6, as in a conventional centrifugal compressor. The impeller 2 is connected to the rotary shaft 4 via the hub 3, and the diffuser 5 is provided downstream of the impeller 2, the flow path faces away from the rotary shaft 4, and the outlet is in the radial direction on the meridian plane Furthermore, the scroll 6 is provided downstream of the diffuser 5 and is connected to the outlet of the diffuser 5. The rotating shaft 4 and the scroll 6 are not shown in FIG.
　さらに従来技術と同様、吸入口１はガスをインペラ２へ案内する役割を持つ。インペラ２へ案内されたガスは、インペラ２が回転軸４により回転することで、ガスを遠心圧縮機内に吸入する仕組みとなっている。インペラ２を通過したガスは、ディフューザ５にて減速され、昇圧する。ディフューザ５を通過したガスは、スクロール６に流入後、吐出口へ流れるようになっている。 Furthermore, as in the prior art, the suction port 1 has a role of guiding the gas to the impeller 2. The gas guided to the impeller 2 is structured such that the gas is sucked into the centrifugal compressor when the impeller 2 is rotated by the rotating shaft 4. The gas that has passed through the impeller 2 is decelerated by the diffuser 5 to increase the pressure. The gas that has passed through the diffuser 5 flows into the discharge port after flowing into the scroll 6.
　ここで、ディフューザ５の入口におけるハブ３側のライン（以下、ディフューザ入口ハブ側ライン５ａと記載）を、子午面における半径方向から軸方向へ傾ける。このとき、ディフューザ入口ハブ側ライン５ａの最もインペラ出口２ｂに近い点Ｂにおける、ディフューザ入口ハブ側ライン５ａが半径方向となす角度をθとする。 Here, the line on the hub 3 side at the inlet of the diffuser 5 (hereinafter referred to as the diffuser inlet hub side line 5a) is inclined from the radial direction to the axial direction on the meridian plane. At this time, an angle between the diffuser inlet hub side line 5a and the radial direction at a point B closest to the impeller outlet 2b of the diffuser inlet hub side line 5a is defined as θ.
　次に、インペラ２のハブ３側のライン（以下、インペラハブ側ライン３ａと記載）の、最もディフューザ５の入口に近い点Ａにおける接線３ｂが、半径方向となす角度をαとする。 Next, the angle formed by the tangent line 3b at the point A closest to the inlet of the diffuser 5 of the line on the hub 3 side of the impeller 2 (hereinafter referred to as the impeller hub side line 3a) is defined as α.
　従来技術では、インペラハブ側ライン３ａとディフューザ入口ハブ側ライン５ａが滑らかに繋がるようにするため、θ＝αとなるようにしているが、本装置では、図５のようにθ－α＞０°とし、さらにθは０°＜θ＜３４°となるようにする。 In the prior art, in order to smoothly connect the impeller hub side line 3a and the diffuser inlet hub side line 5a, θ = α is set. However, in this apparatus, θ−α> 0 ° as shown in FIG. Further, θ is set to satisfy 0 ° <θ <34 °.
　また、インペラ後縁２ｃが軸方向となす角度をβとする。このときβは特に限定する必要はないが、一般的な遠心圧縮機に用いられる値である、０°≦β≦３５°となるようにする。 Also, let β be the angle formed by the impeller trailing edge 2c and the axial direction. At this time, β is not particularly limited, but 0 ° ≦ β ≦ 35 °, which is a value used in a general centrifugal compressor.
　尚、シュラウド７のラインは従来形状のディフューザ幅比に合わせるため、θが傾いた分、シュラウド７のラインも傾けることになる。ディフューザ幅比とはｂ3／ｂ2（図１参照）のことで、インペラ毎に値が決まっており、通常はｂ3／ｂ2＝０．６～１．０の値をとる。 Since the shroud 7 line matches the diffuser width ratio of the conventional shape, the shroud 7 line is also tilted as much as θ is tilted. The diffuser width ratio is b 3 / b 2 (see FIG. 1), and the value is determined for each impeller, and normally takes a value of b 3 / b 2 = 0.6 to 1.0.
　上述のような構造とすることで、インペラ出口２ｂからディフューザ５へ流出した時点でのガスの速度ベクトルは従来と変わらずとも、速度分布の歪みを抑えることができる。 By adopting the structure as described above, even when the gas velocity vector flows out of the impeller outlet 2b into the diffuser 5, the velocity distribution distortion can be suppressed.
　本装置の圧縮機効率を、α及びβをある一定の値とし、θのみを変数として、シミュレーションした結果を図２に示す。図２のグラフは、横軸がθ、縦軸が圧縮機効率改善率を表している。圧縮機効率改善率とは、本装置の圧縮機効率と従来技術の圧縮機効率との差をパーセンテージで表したもので、グラフの上に行くほど本装置の圧縮機効率が高くなっていることを示している。これを見ると、０°＜θ＜３４°のときに、圧縮機効率が改善されていることがわかる。 The simulation results of the compressor efficiency of this apparatus are shown in FIG. 2 where α and β are certain values and only θ is a variable. In the graph of FIG. 2, the horizontal axis represents θ, and the vertical axis represents the compressor efficiency improvement rate. The compressor efficiency improvement rate is the percentage difference between the compressor efficiency of this device and the compressor efficiency of the conventional technology. The higher the graph, the higher the compressor efficiency of this device. Is shown. From this, it can be seen that the compressor efficiency is improved when 0 ° <θ <34 °.
　よって本装置では、従来発生していたディフューザ内でガスの速度分布の歪みが解消され、ディフューザ内での静圧回復量の減少を抑制して、圧縮機全体としての高効率化が可能となる。 Therefore, in this apparatus, the distortion of the gas velocity distribution that has occurred in the conventional diffuser is eliminated, and the reduction of the static pressure recovery amount in the diffuser is suppressed, and the overall efficiency of the compressor can be increased. .
　本発明の実施例２に係る装置は、実施例１に係る装置を改良したものである。図４に実施例１に係る装置と本装置の相違点を示す。実施例１に係る装置では、ディフューザ入口ハブ側ライン５ａが直線であるため、ディフューザ５の出口が半径方向を向くようにすると、必ず何処かでディフューザ５の角度を変えなければならない。よって図４に表されるように、ガスの流れが停滞する淀み域１１ができてしまう。淀み域１１に溜まったガスと流れているガスとの間にはせん断応力が働き、エネルギー損失が起こる可能性がある。本装置は、この淀み域１１を削減するものである。 The apparatus according to the second embodiment of the present invention is an improvement of the apparatus according to the first embodiment. FIG. 4 shows differences between the apparatus according to the first embodiment and the present apparatus. In the apparatus according to the first embodiment, the diffuser inlet hub side line 5a is a straight line. Therefore, if the outlet of the diffuser 5 is directed in the radial direction, the angle of the diffuser 5 must be changed somewhere. Therefore, as shown in FIG. 4, a stagnation region 11 where the gas flow is stagnated is formed. A shear stress acts between the gas accumulated in the stagnation region 11 and the flowing gas, which may cause energy loss. This apparatus reduces this stagnation area 11.
　本装置は実施例１に係る装置及び従来技術と同様、図３のように、主に吸入口１、インペラ２、ハブ３、回転軸４、ディフューザ５及びスクロール６を備える。インペラ２はハブ３を介して回転軸４に接続されており、また、ディフューザ５はインペラ２の下流に設けられ、流路が回転軸４から離れる方向を向き、且つ出口が子午面における半径方向を向いており、さらに、スクロール６はディフューザ５の下流に設けられ、ディフューザ５の出口と繋がっている。尚、回転軸４やスクロール６は図３中にはないが、従来技術と同様とする。さらに、装置動作も実施例１に係る装置及び従来技術と同様であるため、省略する。 This device is mainly provided with a suction port 1, an impeller 2, a hub 3, a rotating shaft 4, a diffuser 5 and a scroll 6 as shown in FIG. The impeller 2 is connected to the rotary shaft 4 via the hub 3, and the diffuser 5 is provided downstream of the impeller 2, the flow path faces away from the rotary shaft 4, and the outlet is in the radial direction on the meridian plane Furthermore, the scroll 6 is provided downstream of the diffuser 5 and is connected to the outlet of the diffuser 5. The rotating shaft 4 and the scroll 6 are not shown in FIG. Further, since the apparatus operation is the same as that of the apparatus according to the first embodiment and the related art, the description thereof is omitted.
　ここで本装置は、ディフューザ入口ハブ側ライン５ｂを凹状の曲線とし、ディフューザ入口ハブ側ライン５ｂの最もインペラ出口２ｂに近い点Ｂにおける、ディフューザ入口ハブ側ライン５ｂの接線５ｃが半径方向となす角度をθとし、シュラウド７のライン、α及びβは実施例１に係る装置と同様として、図５のようにθ－α＞０°とし、さらにθは０°＜θ＜３４°となるようにする。尚、ディフューザ入口ハブ側ライン５ｂは、曲線であれば、１つの円弧であってもよいし、複数の円弧や楕円などを滑らかに組み合わせてもよい。 Here, this apparatus makes the diffuser inlet hub side line 5b a concave curve, and an angle formed by the tangent line 5c of the diffuser inlet hub side line 5b at the point B closest to the impeller outlet 2b of the diffuser inlet hub side line 5b with the radial direction. Is the same as in the apparatus according to the first embodiment, and θ−α> 0 ° as shown in FIG. 5 and θ is 0 ° <θ <34 °. To do. The diffuser inlet hub side line 5b may be a single arc as long as it is a curve, or a plurality of arcs or ellipses may be smoothly combined.
　上述のような構造とすることで、図４のように、実施例１に係る装置で存在していた淀み域１１を削減することができる。よって、本装置はせん断応力を低減でき、より高効率化が可能となる。 By adopting the structure as described above, it is possible to reduce the stagnation region 11 existing in the apparatus according to the first embodiment as shown in FIG. Therefore, this apparatus can reduce a shear stress and can achieve higher efficiency.
　本発明は遠心圧縮機、特に大流量の遠心圧縮機として好適である。 The present invention is suitable as a centrifugal compressor, particularly as a high flow centrifugal compressor.
１　吸入口
２　インペラ
２ａ　インペラ入口
２ｂ　インペラ出口
２ｃ　インペラ後縁
３　ハブ
３ａ　インペラハブ側ライン
３ｂ　接線
４　回転軸
５　ディフューザ
５ａ　（本発明の実施例１に係る装置における）ディフューザ入口ハブ側ライン
５ｂ　（本発明の実施例２に係る装置における）ディフューザ入口ハブ側ライン
５ｃ　接線
６　スクロール
７　シュラウド
１１　淀み域 DESCRIPTION OF SYMBOLS 1 Inlet 2 Impeller 2a Impeller inlet 2b Impeller outlet 2c Impeller trailing edge 3 Hub 3a Impeller hub side line 3b Tangent 4 Rotating shaft 5 Diffuser 5a (in the apparatus according to Embodiment 1 of the present invention) Diffuser inlet hub side line 5b Diffuser inlet hub side line 5c tangent 6 scroll 7 shroud 11

Claims (3)

  1. 　ハブを介して回転軸に接続されたインペラと、
    　当該インペラの下流に設けられ、流路が前記回転軸から離れる方向を向き、且つ出口が子午面における半径方向を向いたディフューザとを備える遠心圧縮機において、
    　前記ディフューザの入口における前記ハブ側のラインであるディフューザ入口ハブ側ラインの、最も前記インペラの出口に近い点における、前記ディフューザ入口ハブ側ラインが子午面における半径方向となす角度をθとし、前記インペラの前記ハブ側のラインであるインペラハブ側ラインの、最も前記ディフューザの入口に近い点における接線が、子午面における半径方向となす角度をαとしたとき、θ－α＞０°であることを特徴とする遠心圧縮機。     An impeller connected to the rotating shaft via a hub;
    In a centrifugal compressor provided with a diffuser provided downstream of the impeller and having a flow path facing a direction away from the rotation axis and an outlet facing a radial direction on a meridian plane,
    An angle formed by the diffuser inlet hub side line at a point closest to the impeller outlet of the diffuser inlet hub side line that is the hub side line at the inlet of the diffuser with respect to the radial direction on the meridian plane is θ, and the impeller The angle of the tangent of the impeller hub side line that is the hub side line closest to the diffuser inlet to the radial direction on the meridian plane is θ−α> 0 °. And centrifugal compressor.
  2. 　前記θが、０°＜θ＜３４°であることを特徴とする請求項１に記載の遠心圧縮機。 The centrifugal compressor according to claim 1, wherein the θ satisfies 0 ° <θ <34 °.
  3. 　前記ディフューザ入口ハブ側ラインが凹状の曲線であることを特徴とする請求項１または２に記載の遠心圧縮機。 The centrifugal compressor according to claim 1 or 2, wherein the diffuser inlet hub side line is a concave curve.
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