US20140369823A1 - Centrifugal compressor - Google Patents

Centrifugal compressor Download PDF

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Publication number
US20140369823A1
US20140369823A1 US14/366,910 US201314366910A US2014369823A1 US 20140369823 A1 US20140369823 A1 US 20140369823A1 US 201314366910 A US201314366910 A US 201314366910A US 2014369823 A1 US2014369823 A1 US 2014369823A1
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Prior art keywords
diffuser
impeller
hub
centrifugal compressor
line
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US14/366,910
Inventor
Shuichi Yamashita
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Mitsubishi Heavy Industries Compressor Corp
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Mitsubishi Heavy Industries Ltd
Mitsubishi Heavy Industries Compressor Corp
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Publication of US20140369823A1 publication Critical patent/US20140369823A1/en
Assigned to MITSUBISHI HEAVY INDUSTRIES, LTD., MITSUBISHI HEAVY INDUSTRIES COMPRESSOR CORPORATION reassignment MITSUBISHI HEAVY INDUSTRIES, LTD. ASSIGNMENT OF ASSIGNORS INTEREST (SEE DOCUMENT FOR DETAILS). Assignors: YAMASHITA, SHUICHI
Assigned to MITSUBISHI HEAVY INDUSTRIES COMPRESSOR CORPORATION reassignment MITSUBISHI HEAVY INDUSTRIES COMPRESSOR CORPORATION ASSIGNMENT OF ASSIGNORS INTEREST (SEE DOCUMENT FOR DETAILS). Assignors: MITSUBISHI HEAVY INDUSTRIES, LTD.
Abandoned legal-status Critical Current

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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
    • F04D29/26—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
    • 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
    • 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 with a large flow rate.
  • Increasing the flow rate of a centrifugal compressor means to increase the discharge flow rate of a compressor with the same shell size, and further of an impeller with the same outer diameter.
  • the centrifugal compressor mainly includes a suction inlet 1 , an impeller 2 , a hub 3 , a rotary shaft 4 , a diffuser 5 , and a scroll 6 .
  • the impeller 2 is connected to the rotary shaft 4 via the hub 3 .
  • the diffuser 5 is provided downstream of the impeller 2 , has a flow passage extending in a direction away from the rotary shaft 4 , and has an outlet directed in a radial direction in a meridian plane.
  • the scroll 6 is provided downstream of the diffuser 5 and communicates with the outlet of the diffuser 5 .
  • the suction inlet 1 plays a roll of guiding a gas to the impeller 2 .
  • the centrifugal compressor is configured such that the gas guided to the impeller 2 is sucked into the centrifugal compressor by the impeller 2 being rotated by the rotary shaft 4 .
  • the velocity of the gas having passed through the impeller 2 is decreased, and the pressure of the gas is increased, in the diffuser 5 .
  • the gas having passed through the diffuser 5 flows into the scroll 6 , and thereafter flows into a discharge port, which is not shown. In this way, the centrifugal compressor converts the kinetic energy of the gas to a pressure.
  • FIG. 7 is a cross-sectional view of the diffuser 5 and the impeller 2 of the conventional centrifugal compressor.
  • a large flow rate causes the velocity distribution of the gas sacked through an impeller inlet 2 a to be skewed to the hub 3 side at an impeller outlet 2 b.
  • the velocity vector is inclined toward an axial direction from the radial direction.
  • PATENT DOCUMENT 1 Japanese Patent No. 2569143
  • PATENT DOCUMENT 2 Japanese Patent No. 2703055
  • an object of the present invention is to solve the problems of the conventional techniques and to achieve higher efficiency in a centrifugal compressor with a large flow rate, not by providing a new mechanism, but by changing a shape of a diffuser.
  • a centrifugal compressor according to a first invention for solving the above-described problems is a centrifugal compressor comprising:
  • a diffuser provided downstream of the impeller, the diffuser having a flow passage which extends in a direction away from the rotary shaft and an outlet which is directed in a radial direction in a meridian plane, characterized in that
  • the centrifugal compressor satisfies ⁇ >0°
  • ⁇ is an angle formed by a diffuser inlet hub-side line with the radial direction in the meridian plane at a point closest to an outlet of the impeller in the diffuser inlet hub-side line, the diffuser inlet hub-side line being a line on the hub side in an inlet of the diffuser, and
  • ⁇ is an angle formed by a tangent line of an impeller hub-side line with the radial direction in the meridian plane at a point closest to the inlet of the diffuser in the impeller hub-side line, the impeller hub-side line being a line on the hub side in the impeller.
  • a centrifugal compressor according to a second invention for solving the above-described problems is the centrifugal compressor according to the first invention, characterized in that the ⁇ is such that 0° ⁇ 34°.
  • a centrifugal compressor according to a third invention for solving the above-described problems is the centrifugal compressor according to the first or second invention, characterized in that
  • the diffuser inlet hub-side line is a concave curved line.
  • centrifugal compressor of the first invention since ⁇ >0°, skewing of the velocity distribution of the gas is eliminated, and accordingly a decrease in amount of static pressure recovery is suppressed. Therefore, a higher efficiency of the entire compressor can be achieved.
  • the centrifugal compressor of the second invention since 0° ⁇ 34°, the skewing of the velocity distribution of the gas can be further eliminated.
  • the diffuser inlet hub-side line is a concave curved line, a stagnation region inside the diffuser is reduced. Therefore, a further higher efficiency can be achieved.
  • FIG. 1 is a cross-sectional view of a diffuser and an impeller of a centrifugal compressor according to Embodiment 1 of the present invention.
  • FIG. 2 is a graph showing a relationship between ⁇ and an efficiency improvement rate of the centrifugal compressor according to Embodiment 1 of the present invention.
  • FIG. 3 is a cross-sectional view of a diffuser and an impeller of a centrifugal compressor according to Embodiment 2 of the present invention.
  • FIG. 4 is a schematic view showing differences between the centrifugal compressor according to Embodiment 1 of the present invention and the centrifugal compressor according to Embodiment 2 of the present invention.
  • FIG. 5 is a schematic diagram showing a relationship between ⁇ and ⁇ of the centrifugal compressor according to Embodiment 1 or 2 of the present invention.
  • FIG. 6 is a cross-sectional view of a conventional centrifugal compressor.
  • FIG. 7 is a cross-sectional view of a diffuser and an impeller of the conventional centrifugal compressor.
  • the apparatus mainly includes a suction inlet 1 , an impeller 2 , a hub 3 , a rotary shaft 4 , a diffuser 5 , and a scroll 6 , as in the case of the conventional centrifugal compressor.
  • the impeller 2 is connected to the rotary shaft 4 via the hub 3 .
  • the diffuser 5 is provided downstream of the impeller 2 , has a flow passage directed in a direction away from the rotary shaft 4 , and has an outlet directed in a radial direction in a meridian plane.
  • the scroll 6 is provided downstream of the diffuser 5 , and communicates with an outlet of the diffuser 5 . Note that the rotary shaft 4 and the scroll 6 are not shown in FIG. 1 , but are assumed to be the same as those of the conventional technical.
  • the suction inlet 1 plays a role of guiding a gas to the impeller 2 .
  • the centrifugal compressor is configured such that the gas guided to the impeller 2 is sucked into the centrifugal compressor by the impeller 2 being rotated by the rotary shaft 4 .
  • the velocity of the gas having passed through the impeller 2 is decreased, and the pressure of the gas is increased, in the diffuser 5 .
  • the gas having passed through the diffuser 5 flows into the scroll 6 , and thereafter flows into a discharge port.
  • a line on the hub 3 side in the inlet of the diffuser 5 (hereinafter, stated as a diffuser inlet hub-side line 5 a ) is inclined toward an axial direction from the radial direction in the meridian plane.
  • ⁇ an angle formed by the diffuser inlet hub-side line 5 a with the radial direction at a point B closest to the impeller outlet 2 b in the diffuser inlet hub-side line 5 a.
  • an angle formed by a tangent line 3 b of a line on the hub 3 side in the impeller 2 (hereinafter, stated as an impeller hub-side line 3 a ) with the radial direction at a point A closest to an inlet of the diffuser 5 in the impeller hub-side line 3 a is represented by ⁇ .
  • the present apparatus is set such that ⁇ > 0 ° as shown in FIG. 5 , and further ⁇ is set such that 0° ⁇ 34°.
  • ⁇ an angle formed by the impeller rear edge 2 c with the axial direction is represented by ⁇ .
  • ⁇ has not necessary to be limited, but is set such that 0° ⁇ 35°, which is a value used in a general centrifugal compressor.
  • a line of the shroud 7 is also inclined in conjunction with the inclination of ⁇ to confirm with a diffuser width ratio of the conventional shape.
  • the diffuser width ratio is b 3 /b 2 (see FIG. 1 ), and has a value set for each impeller.
  • FIG. 2 shows a result of simulation of the compressor efficiency of the present apparatus, conducted under conditions that ⁇ and ⁇ are certain constant values and only ⁇ is a variable.
  • the horizontal axis represents ⁇ and the vertical axis represents a compressor efficiency improvement rate.
  • the compressor efficiency improvement rate represents a difference, expressed in percentage, between the compressor efficiency of the present apparatus and the compressor efficiency of the conventional technique. As becoming higher in the graph, the compressor efficiency improvement rate indicates that the compressor efficiency of the present apparatus is higher. It can be understood from the graph that the compressor efficiency is improved when 0° ⁇ 34°.
  • the skewing of the velocity distribution of the gas in the diffuser which has conventionally occurred, is eliminated, and accordingly a decrease in the amount of static pressure recovery in the diffuser is suppressed. Therefore, a higher efficiency of the entire compressor can be achieved.
  • FIG. 4 shows differences between the apparatus according to Embodiment 1 and the present apparatus.
  • the diffuser inlet hub-side line 5 a is a straight line, directing the outlet of the diffuser 5 in the radial direction requires that the angle of the diffuser 5 has to be changed at a certain portion.
  • a stagnation region 11 where the flow of the gas stagnates is formed. Shear stress acts between the gas stagnating in the stagnation region 11 and the flowing gas, leading to a possibility of occurrence of an energy loss.
  • the present apparatus reduces the stagnation region 11 .
  • the present apparatus mainly includes a suction inlet 1 , an impeller 2 , a hub 3 , a rotary shaft 4 , a diffuser 5 , and a scroll 6 .
  • the impeller 2 is connected to the rotary shaft 4 via the hub 3 .
  • the diffuser 5 is provided downstream of the impeller 2 , has a flow passage extending in a direction away from the rotary shaft 4 , and has an outlet directed in a radial direction in a meridian plane.
  • the scroll 6 is provided downstream of the diffuser 5 and communicates with the outlet of the diffuser 5 .
  • the rotary shaft 4 and the scroll 6 are not shown in FIG. 3 , but are assumed to be the same as those of the conventional technique.
  • the operation of the present apparatus is also the same as those of the apparatus according to Embodiment 1 and of the conventional technique, and is accordingly omitted.
  • the diffuser inlet hub-side line 5 b is made to be a concave curved line.
  • An angle formed by a tangent line 5 c of the diffuser inlet hub-side line 5 b with a radial direction at a point B closest to an impeller outlet 2 b in the diffuser inlet hub-side line 5 b is represented by ⁇ .
  • the line of the shroud 7 , ⁇ , and ⁇ are set such that ⁇ >0° as shown in FIG. 5 , and further ⁇ is set such that 0° ⁇ 34° as in the case of the apparatus according to Embodiment 1.
  • the diffuser inlet hub-side line 5 b may be a single arc, or may be a line obtained by smoothly combining a plurality of arcs or ovals, as long as it is a curved line.
  • the present apparatus can reduce the stagnation region 11 , which exists in the case of the apparatus according to Embodiment 1. Therefore, the present apparatus can reduce shear stress and makes it possible to achieve higher efficiency.
  • the present invention is favorable as a centrifugal compressor, and in particular a centrifugal compressor with a large flow rate.

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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 (5 a) and the radial direction at a point B in the meridian plane is θ, and the angle formed by a tangent line (3 b) and the radial direction at a point A of an impeller hub-side line (3 a) 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

    TECHNICAL FIELD
  • The present invention relates to a centrifugal compressor, and particularly to a centrifugal compressor with a large flow rate.
    • BACKGROUND ART
  • For improving the performances of products such as superchargers, gas turbines, and industrial compressors, it is a critical issue to increase the flow rate. Increasing the flow rate of a centrifugal compressor means to increase the discharge flow rate of a compressor with the same shell size, and further of an impeller with the same outer diameter.
  • One of the problems associated with the increase in flow rate is a decrease in efficiency. For this reason, a technique of increasing the flow rate while suppressing the decrease in efficiency is industrially very significant.
  • A conventional centrifugal compressor will be described by using FIG. 6. The centrifugal compressor mainly includes a suction inlet 1, an impeller 2, a hub 3, a rotary shaft 4, a diffuser 5, and a scroll 6.
  • The impeller 2 is connected to the rotary shaft 4 via the hub 3. The diffuser 5 is provided downstream of the impeller 2, has a flow passage extending in a direction away from the rotary shaft 4, and has an outlet directed in a radial direction in a meridian plane. Moreover, the scroll 6 is provided downstream of the diffuser 5 and communicates with the outlet of the diffuser 5.
  • The suction inlet 1 plays a roll of guiding a gas to the impeller 2. The centrifugal compressor is configured such that the gas guided to the impeller 2 is sucked into the centrifugal compressor by the impeller 2 being rotated by the rotary shaft 4. The velocity of the gas having passed through the impeller 2 is decreased, and the pressure of the gas is increased, in the diffuser 5. The gas having passed through the diffuser 5 flows into the scroll 6, and thereafter flows into a discharge port, which is not shown. In this way, the centrifugal compressor converts the kinetic energy of the gas to a pressure.
  • FIG. 7 is a cross-sectional view of the diffuser 5 and the impeller 2 of the conventional centrifugal compressor. The more the velocity vector of the gas (the arrow in the figure) is directed in a radial direction in the meridian plane, the less the energy loss is. However, a large flow rate causes the velocity distribution of the gas sacked through an impeller inlet 2 a to be skewed to the hub 3 side at an impeller outlet 2 b. As a result, the velocity vector is inclined toward an axial direction from the radial direction. In addition, if the gas flows further inside the diffuser 5 in this state, the velocity distribution is further skewed to become a cause of occurrence of shear stress, reducing the amount of static pressure recovery, and in turn leading to a decrease in efficiency of the entire compressor.
  • To solve the above-described problem, there is a method of bringing the velocity distribution of the gas into a more uniform distribution by providing the inside of the diffuser with a guide blade (see Patent Document 1) or a guide flow passage to the impeller inlet (see Patent Document 2).
    • PRIOR ART DOCUMENTS Patent Documents
  • PATENT DOCUMENT 1: Japanese Patent No. 2569143
  • PATENT DOCUMENT 2: Japanese Patent No. 2703055
    • SUMMARY OF THE INVENTION Problems To Be Solved by the Invention
  • However, the above-described apparatuses require that new mechanisms should be provided in the diffuser, and have a possibility that the production costs and working hours are wasted.
  • In view of this, an object of the present invention is to solve the problems of the conventional techniques and to achieve higher efficiency in a centrifugal compressor with a large flow rate, not by providing a new mechanism, but by changing a shape of a diffuser.
    • Means for Solving the Problems
  • A centrifugal compressor according to a first invention for solving the above-described problems is a centrifugal compressor comprising:
  • an impeller connected to a rotary shaft via a hub; and
  • a diffuser provided downstream of the impeller, the diffuser having a flow passage which extends in a direction away from the rotary shaft and an outlet which is directed in a radial direction in a meridian plane, characterized in that
  • the centrifugal compressor satisfies θ−α>0°
  • where
  • θ is an angle formed by a diffuser inlet hub-side line with the radial direction in the meridian plane at a point closest to an outlet of the impeller in the diffuser inlet hub-side line, the diffuser inlet hub-side line being a line on the hub side in an inlet of the diffuser, and
  • α is an angle formed by a tangent line of an impeller hub-side line with the radial direction in the meridian plane at a point closest to the inlet of the diffuser in the impeller hub-side line, the impeller hub-side line being a line on the hub side in the impeller.
  • A centrifugal compressor according to a second invention for solving the above-described problems is the centrifugal compressor according to the first invention, characterized in that the θ is such that 0°<θ<34°.
  • A centrifugal compressor according to a third invention for solving the above-described problems is the centrifugal compressor according to the first or second invention, characterized in that
  • the diffuser inlet hub-side line is a concave curved line.
    • Effect of the Invention
  • According to the centrifugal compressor of the first invention, since θ−α>0°, skewing of the velocity distribution of the gas is eliminated, and accordingly a decrease in amount of static pressure recovery is suppressed. Therefore, a higher efficiency of the entire compressor can be achieved.
  • According to the centrifugal compressor of the second invention, since 0°<θ<34°, the skewing of the velocity distribution of the gas can be further eliminated.
  • According to the centrifugal compressor of the third invention, since the diffuser inlet hub-side line is a concave curved line, a stagnation region inside the diffuser is reduced. Therefore, a further higher efficiency can be achieved.
    • BRIEF DESCRIPTION OF THE DRAWINGS
  • FIG. 1 is a cross-sectional view of a diffuser and an impeller of a centrifugal compressor according to Embodiment 1 of the present invention.
  • FIG. 2 is a graph showing a relationship between θ and an efficiency improvement rate of the centrifugal compressor according to Embodiment 1 of the present invention.
  • FIG. 3 is a cross-sectional view of a diffuser and an impeller of a centrifugal compressor according to Embodiment 2 of the present invention.
  • FIG. 4 is a schematic view showing differences between the centrifugal compressor according to Embodiment 1 of the present invention and the centrifugal compressor according to Embodiment 2 of the present invention.
  • FIG. 5 is a schematic diagram showing a relationship between θ and α of the centrifugal compressor according to Embodiment 1 or 2 of the present invention.
  • FIG. 6 is a cross-sectional view of a conventional centrifugal compressor.
  • FIG. 7 is a cross-sectional view of a diffuser and an impeller of the conventional centrifugal compressor.
    •  MODES FOR CARRYING OUT THE INVENTION
  • Hereinafter, a centrifugal compressor according to the present invention will be described referring to embodiments by use of the drawings.
    • Embodiment 1
  • An apparatus according to Embodiment 1 of the present invention will be described by use of FIG. 1. The apparatus mainly includes a suction inlet 1, an impeller 2, a hub 3, a rotary shaft 4, a diffuser 5, and a scroll 6, as in the case of the conventional centrifugal compressor. The impeller 2 is connected to the rotary shaft 4 via the hub 3. In addition, the diffuser 5 is provided downstream of the impeller 2, has a flow passage directed in a direction away from the rotary shaft 4, and has an outlet directed in a radial direction in a meridian plane. Moreover, the scroll 6 is provided downstream of the diffuser 5, and communicates with an outlet of the diffuser 5. Note that the rotary shaft 4 and the scroll 6 are not shown in FIG. 1, but are assumed to be the same as those of the conventional technical.
  • Furthermore, like the conventional technique, the suction inlet 1 plays a role of guiding a gas to the impeller 2. The centrifugal compressor is configured such that the gas guided to the impeller 2 is sucked into the centrifugal compressor by the impeller 2 being rotated by the rotary shaft 4. The velocity of the gas having passed through the impeller 2 is decreased, and the pressure of the gas is increased, in the diffuser 5. The gas having passed through the diffuser 5 flows into the scroll 6, and thereafter flows into a discharge port.
  • Here, a line on the hub 3 side in the inlet of the diffuser 5 (hereinafter, stated as a diffuser inlet hub-side line 5 a) is inclined toward an axial direction from the radial direction in the meridian plane. At this time, an angle formed by the diffuser inlet hub-side line 5 a with the radial direction at a point B closest to the impeller outlet 2 b in the diffuser inlet hub-side line 5 a is represented by θ.
  • Next, an angle formed by a tangent line 3 b of a line on the hub 3 side in the impeller 2 (hereinafter, stated as an impeller hub-side line 3 a) with the radial direction at a point A closest to an inlet of the diffuser 5 in the impeller hub-side line 3 a is represented by α.
  • The conventional technique is set such that θ=α in order to smoothly connect the impeller hub-side line 3 a and the diffuser inlet hub-side line 5 a. On the other hand, the present apparatus is set such that θ−α>0° as shown in FIG. 5, and further θ is set such that 0°<θ<34°.
  • In addition, an angle formed by the impeller rear edge 2 c with the axial direction is represented by β. Here, β has not necessary to be limited, but is set such that 0°≦β≦35°, which is a value used in a general centrifugal compressor.
  • Note that a line of the shroud 7 is also inclined in conjunction with the inclination of θ to confirm with a diffuser width ratio of the conventional shape. The diffuser width ratio is b3/b2 (see FIG. 1), and has a value set for each impeller. In general, the value of the diffuser width ratio is set such that b3/b2=0.6 to 1.0.
  • With the above-described structure, while the velocity vector of the gas at the time when the gas has flowed from the impeller outlet 2 b to the diffuser 5 is not changed from that of the conventional one, the skewing of the velocity distribution can be suppressed.
  • FIG. 2 shows a result of simulation of the compressor efficiency of the present apparatus, conducted under conditions that α and β are certain constant values and only θ is a variable. In a graph of FIG. 2, the horizontal axis represents θ and the vertical axis represents a compressor efficiency improvement rate. The compressor efficiency improvement rate represents a difference, expressed in percentage, between the compressor efficiency of the present apparatus and the compressor efficiency of the conventional technique. As becoming higher in the graph, the compressor efficiency improvement rate indicates that the compressor efficiency of the present apparatus is higher. It can be understood from the graph that the compressor efficiency is improved when 0°<θ<34°.
  • Accordingly, in the present apparatus, the skewing of the velocity distribution of the gas in the diffuser, which has conventionally occurred, is eliminated, and accordingly a decrease in the amount of static pressure recovery in the diffuser is suppressed. Therefore, a higher efficiency of the entire compressor can be achieved.
    • Embodiment 2
  • An apparatus according to Embodiment 2 of the present invention is one obtained by improving the apparatus according to Embodiment 1. FIG. 4 shows differences between the apparatus according to Embodiment 1 and the present apparatus. In the apparatus according to Embodiment 1, since the diffuser inlet hub-side line 5 a is a straight line, directing the outlet of the diffuser 5 in the radial direction requires that the angle of the diffuser 5 has to be changed at a certain portion. As a result, as shown in FIG. 4, a stagnation region 11 where the flow of the gas stagnates is formed. Shear stress acts between the gas stagnating in the stagnation region 11 and the flowing gas, leading to a possibility of occurrence of an energy loss. The present apparatus reduces the stagnation region 11.
  • As in the case of the apparatus according to Embodiment 1, as shown in FIG. 3, the present apparatus mainly includes a suction inlet 1, an impeller 2, a hub 3, a rotary shaft 4, a diffuser 5, and a scroll 6. The impeller 2 is connected to the rotary shaft 4 via the hub 3. The diffuser 5 is provided downstream of the impeller 2, has a flow passage extending in a direction away from the rotary shaft 4, and has an outlet directed in a radial direction in a meridian plane. Moreover, the scroll 6 is provided downstream of the diffuser 5 and communicates with the outlet of the diffuser 5. Note that the rotary shaft 4 and the scroll 6 are not shown in FIG. 3, but are assumed to be the same as those of the conventional technique. Furthermore, the operation of the present apparatus is also the same as those of the apparatus according to Embodiment 1 and of the conventional technique, and is accordingly omitted.
  • Here, in the present apparatus, the diffuser inlet hub-side line 5 b is made to be a concave curved line. An angle formed by a tangent line 5 c of the diffuser inlet hub-side line 5 b with a radial direction at a point B closest to an impeller outlet 2 b in the diffuser inlet hub-side line 5 b is represented by θ. The line of the shroud 7, α, and β are set such that θ−α>0° as shown in FIG. 5, and further θ is set such that 0°<θ<34° as in the case of the apparatus according to Embodiment 1. Note that the diffuser inlet hub-side line 5 b may be a single arc, or may be a line obtained by smoothly combining a plurality of arcs or ovals, as long as it is a curved line.
  • With the above-described structure, as shown in FIG. 4, the present apparatus can reduce the stagnation region 11, which exists in the case of the apparatus according to Embodiment 1. Therefore, the present apparatus can reduce shear stress and makes it possible to achieve higher efficiency.
    • INDUSTRIAL APPLICABILITY
  • The present invention is favorable as a centrifugal compressor, and in particular a centrifugal compressor with a large flow rate.
    • EXPLANATION OF REFERENCE NUMERALS
    • 1 suction inlet
    • 2 impeller
    • 2 a impeller inlet
    • 2 b impeller outlet
    • 2 c impeller rear edge
    • 3 hub
    • 3 a impeller hub-side line
    • 3 b tangent line
    • 4 rotary shaft
    • 5 diffuser
    • 5 a diffuser inlet hub-side line (in the apparatus according to Embodiment 1 of the present invention)
    • 5 b diffuser inlet hub-side line (in the apparatus according to Embodiment 2 of the present invention)
    • 5 c tangent line
    • 6 scroll
    • 7 shroud
    • 11 stagnation region

Claims (3)

1. A centrifugal compressor comprising:
an impeller connected to a rotary shaft via a hub; and
a diffuser provided downstream of the impeller, the diffuser having a flow passage which extends in a direction away from the rotary shaft and an outlet which is directed in a radial direction in a meridian plane, characterized in that
the centrifugal compressor satisfies θ−α>0°
where
θ is an angle formed by a diffuser inlet hub-side line with the radial direction in the meridian plane at a point closest to an outlet of the impeller in the diffuser inlet hub-side line, the diffuser inlet hub-side line being a line on the hub side in an inlet of the diffuser, and
α is an angle formed by a tangent line of an impeller hub-side line with the radial direction in the meridian plane at a point closest to the inlet of the diffuser in the impeller hub-side line, the impeller hub-side line being a line on the hub side in the impeller, and
a rear edge of the impeller has an inclined angle, the diffuser inlet hub-side line is a straight line, and an angle formed by the diffuser inlet hub-side line and the rear edge of the impeller is substantially 90° or more.
2. The centrifugal compressor according to claim 1, characterized in that the θ is such that 0°<θ<34°.
3. (canceled)
US14/366,910 2012-01-17 2013-01-11 Centrifugal compressor Abandoned US20140369823A1 (en)

Applications Claiming Priority (3)

Application Number Priority Date Filing Date Title
JP2012006714A JP5905268B2 (en) 2012-01-17 2012-01-17 Centrifugal compressor
JP2012-006714 2012-01-17
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US11428240B2 (en) * 2018-04-04 2022-08-30 Mitsubishi Heavy Industries Engine & Turbocharger, Ltd. Centrifugal compressor and turbocharger including the same
US11143201B2 (en) 2019-03-15 2021-10-12 Pratt & Whitney Canada Corp. Impeller tip cavity
US11187242B2 (en) * 2019-07-04 2021-11-30 Mitsubishi Heavy Industries, Ltd. Multi-stage centrifugal compressor
US11268536B1 (en) * 2020-09-08 2022-03-08 Pratt & Whitney Canada Corp. Impeller exducer cavity with flow recirculation
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CN103998790B (en) 2016-10-19
EP2806170A4 (en) 2015-11-18
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WO2013108712A1 (en) 2013-07-25
JP5905268B2 (en) 2016-04-20

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