US20170260998A1 - Centrifugal impeller and centrifugal compressor - Google Patents

Centrifugal impeller and centrifugal compressor Download PDF

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Publication number
US20170260998A1
US20170260998A1 US15/503,806 US201515503806A US2017260998A1 US 20170260998 A1 US20170260998 A1 US 20170260998A1 US 201515503806 A US201515503806 A US 201515503806A US 2017260998 A1 US2017260998 A1 US 2017260998A1
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US
United States
Prior art keywords
blade
shroud
hub
inclination angle
leading edge
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.)
Abandoned
Application number
US15/503,806
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English (en)
Inventor
Jo Masutani
Daisuke Hirata
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Mitsubishi Heavy Industries Ltd
Mitsubishi Heavy Industries Compressor Corp
Original Assignee
Mitsubishi Heavy Industries Ltd
Mitsubishi Heavy Industries Compressor Corp
Priority date (The priority date 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 date listed.)
Filing date
Publication date
Application filed by Mitsubishi Heavy Industries Ltd, Mitsubishi Heavy Industries Compressor Corp filed Critical Mitsubishi Heavy Industries Ltd
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: HIRATA, DAISUKE, MASUTANI, JO
Publication of US20170260998A1 publication Critical patent/US20170260998A1/en
Abandoned legal-status Critical Current

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Classifications

    • 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
    • F04D29/30—Vanes
    • 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
    • F04D29/4206—Casings; Connections of working fluid for radial or helico-centrifugal pumps especially adapted for elastic fluid pumps
    • 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
    • F04D29/66—Combating cavitation, whirls, noise, vibration or the like; Balancing
    • F04D29/68—Combating cavitation, whirls, noise, vibration or the like; Balancing by influencing boundary layers
    • F04D29/681—Combating cavitation, whirls, noise, vibration or the like; Balancing by influencing boundary layers especially adapted for elastic fluid pumps
    • 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
    • F05D2240/00—Components
    • F05D2240/20—Rotors
    • F05D2240/30—Characteristics of rotor blades, i.e. of any element transforming dynamic fluid energy to or from rotational energy and being attached to a rotor
    • F05D2240/303—Characteristics of rotor blades, i.e. of any element transforming dynamic fluid energy to or from rotational energy and being attached to a rotor related to the leading edge of a rotor blade
    • 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
    • F05D2240/00—Components
    • F05D2240/20—Rotors
    • F05D2240/30—Characteristics of rotor blades, i.e. of any element transforming dynamic fluid energy to or from rotational energy and being attached to a rotor
    • F05D2240/304—Characteristics of rotor blades, i.e. of any element transforming dynamic fluid energy to or from rotational energy and being attached to a rotor related to the trailing edge of a rotor blade
    • 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
    • F05D2250/70—Shape

Definitions

  • the present invention relates to a centrifugal impeller and a centrifugal compressor including the centrifugal impeller.
  • Centrifugal compressors for industrial use are generally used in petrochemical plants or natural gas plants, for example.
  • a centrifugal compressor of this type employs a centrifugal impeller for blowing out fluid in a radial direction by the rotation of a rotary shaft, including a hub fixed to the rotary shaft and a plurality of blades disposed in the hub (see Patent Literature 1, for example).
  • the blade 100 when a blade 100 of a centrifugal impeller is viewed from an intake port 101 side, the blade 100 is formed in such a manner that an angle made by a camber line 103 of a leading edge 102 and a straight line 104 extending in a radial direction from the center of rotation is approximately 0° over a region from a wall surface 105 on a hub side to a wall surface 106 on a shroud side as shown in FIG. 11 .
  • the blade latter half of the blade 100 including a trailing edge 108 inclines obliquely in such a manner that a suction surface S of the blade 100 faces the wall surface 106 on the shroud side as shown in FIG. 12 .
  • a boundary layer 109 is generated on the wall surface 106 on the shroud side, which constitutes a passage for fluid.
  • the boundary layer 109 develops in a deceleration zone of the wall surface 106 on the shroud side in the first half of the blade.
  • a boundary layer develops, starting from the leading edge 102 , on the suction surface S having larger deceleration than a pressure surface P to which a positive pressure is applied by the rotation. This boundary layer is attracted to a radially upper part by centrifugal force, thereby flowing into and merging with the boundary layer 109 generated on the wall surface 106 on the shroud side.
  • the boundary layer 109 on the wall surface 106 on the shroud side develops further.
  • the thus developed boundary layer develops further also in the latter half of the blade, thereby creating a large energy deficit portion on a blade outlet side.
  • the conventional configuration has made no contraption for suppressing the boundary layer 109 developed on the wall surface 106 on the shroud side in the first half of the blade, in particular.
  • the present invention has been made in view of such circumstances, and it is an object of the present invention to provide a centrifugal impeller capable of suppressing the development of a boundary layer and thus fulfilling its performance sufficiently, and a centrifugal compressor.
  • a centrifugal impeller comprises: a hub; a shroud; and a plurality of blades disposed between the hub and the shroud, the centrifugal impeller blowing out fluid in a radial direction by rotation of a rotary shaft fixed to the hub.
  • the blade is formed in such a manner that the inclination angle of a leading edge is zero or positive on the hub side and gradually increasing toward the shroud and the inclination angle is gradually decreasing from the leading edge toward a trailing edge in a flow direction.
  • the inclination angle of the leading edge in the blade is zero or positive on the hub side and gradually increasing toward the shroud.
  • a pressure surface of the blade faces the shroud in a portion of the blade from the leading edge to the first half thereof. Consequently, a boundary layer is pressed against the shroud by force of the pressure surface of the blade, thereby suppressing the development of the boundary layer.
  • a boundary layer is pressed against the suction surface by centrifugal force, thereby preventing its movement toward the shroud and thus suppressing the development of the boundary layer.
  • the blade is formed in such a manner that the inclination angle is gradually decreasing from the leading edge toward the trailing edge.
  • the inclination angle of the trailing edge in the blade is preferably zero or positive on the hub side and gradually increasing toward the shroud.
  • the pressure surface of the blade faces the shroud also in the latter half of the blade. Consequently, the boundary layer is pressed against the shroud by the force of the pressure surface of the blade, thereby suppressing the development of the boundary layer.
  • the inclination angle of the trailing edge in the blade is preferably zero or positive over a region from the hub side to the shroud side. Moreover, such a positive value is preferably closer to zero. According to such a configuration, the length of the trailing edge of the blade can be made the shortest distance, thereby minimizing an amount of wake flow due to the thickness of the trailing edge of the blade. Furthermore, the reduced surface area of the blade in the latter half of the blade can reduce the amount of the boundary layer developed over the blade surface in the latter half of the blade as compared to the conventional technique.
  • the leading edge of the blade when projected onto the meridional cross section, preferably has a linear shape from the hub side to the shroud side or a shape protruded toward an upstream side of the flow direction between the hub side and the shroud side. According to such a configuration, the area of a portion of the leading edge of the blade facing the shroud can be increased, thereby more effectively suppressing the development of the boundary layer accordingly.
  • the provision of the above-described centrifugal impeller in a centrifugal compressor can suppress the generation of the energy deficit portion on the blade outlet side, thus improving the compression efficiency of the centrifugal compressor.
  • the blade is formed in such a manner that the inclination angle of the leading edge is zero or positive on the hub side and gradually increasing toward the shroud and the inclination angle is gradually decreasing from the leading edge toward the trailing edge in the flow direction.
  • the pressure surface of the blade faces the shroud in the portion of the blade from the leading edge to the first half thereof. This can suppress the development of the boundary layer and thus suppress the generation of the energy deficit portion on the blade outlet side, thereby allowing the performance of the centrifugal impeller to be fulfilled sufficiently.
  • FIG. 1 is a longitudinal cross-sectional view of a centrifugal compressor according to the present embodiment.
  • FIG. 2 is a partial enlarged view illustrating an impeller.
  • FIG. 3 is a diagram for explaining an inclination angle of a blade shown on a meridional cross section.
  • FIG. 4 is a diagram illustrating the blade projected on the meridional cross section.
  • FIG. 5 is a diagram illustrating an intake port of the impeller as seen from an axial direction.
  • FIG. 6 is a schematic view illustrating the shape of a leading edge of the blade of the impeller.
  • FIG. 7 is a diagram illustrating a blowoff port of the impeller as seen from a radial direction.
  • FIG. 8 is a diagram illustrating the blowoff port of the impeller as seen from the axial direction.
  • FIG. 9 is a schematic view illustrating the shape of a trailing edge of the blade of the impeller.
  • FIG. 10 is an experimental measurement diagram showing changes in the development of boundary layers due to the shapes of blades in a conventional technique and the present embodiment.
  • FIG. 11 is a schematic view illustrating the shape of a leading edge of a blade in a conventional impeller.
  • FIG. 12 is a schematic view illustrating the shape of a trailing edge of the blade in the conventional impeller.
  • FIG. 1 is a longitudinal cross-sectional view of a centrifugal compressor according to the present embodiment.
  • a centrifugal compressor 1 includes: a casing 2 formed by a combination of a plurality of parts; a rotary shaft 5 supported so as to be rotatable about an axis line L via bearings (not shown) in the casing 2 ; and closed type impellers 6 fixed to the rotary shaft 5 so as to rotate integrally with the rotary shaft 5 .
  • the centrifugal compressor 1 of the present embodiment is a two-stage centrifugal compressor.
  • the rotary shaft 5 is driven by a driving mechanism (not shown) to rotate the impellers 6 . Consequently, fluid, such as gas or air, to be compressed is sucked into the centrifugal compressor 1 via a suction port 10 provided in the casing 2 .
  • An intake passage 11 is connected to the suction port 10 via a suction space 10 A formed in the casing 2 .
  • the intake passage 11 bends along the direction of the axis line L of the rotary shaft 5 (axial direction) and has an opening facing an intake port 6 A of the first-stage impeller 6 .
  • Centrifugal force is imparted to the fluid sucked from the suction port 10 by the rotation of the first-stage impeller 6 .
  • the kinetic energy of such fluid is converted to pressure energy by a first-stage vaneless diffuser 12 provided at a blowoff port 6 B of the impeller 6 .
  • This fluid is further guided to an intake port 6 A of the second-stage impeller 6 , which is the next compression stage, via a return bend 14 and a return vane 15 .
  • centrifugal force is imparted to such compressed fluid by the second-stage impeller 6 .
  • the kinetic energy of such fluid is converted to pressure energy by a second-stage vaneless diffuser 12 and discharged to a scroll 16 as compressed fluid with a higher pressure. Thereafter, the fluid is sent out from the scroll 16 to a discharge pipe (not shown) via a discharge port 17 provided in the casing 2 .
  • the reference numeral 18 in FIG. 1 denotes a balance piston provided for adjusting thrust of the impeller 6 .
  • the impeller 6 will be described next.
  • FIG. 2 is a partial enlarged view illustrating the impeller.
  • the impeller 6 includes: a hub 20 fixed to the rotary shaft 5 ; a shroud 21 disposed with a space from the hub 20 in a radial direction and the axial direction; and a plurality of blades 22 disposed between the hub 20 and the shroud 21 .
  • the blades 22 are disposed radially with a space around the axis line L, although their graphic representation is omitted.
  • a leading edge 22 A of the blade 22 is positioned on the intake port 6 A side of the impeller 6 , and a trailing edge 22 B extends to the blowoff port 6 B of the impeller 6 .
  • a boundary layer is generated on an inner wall surface 21 A of the shroud 21 , which constitutes a fluid passage together with the hub 20 , on the intake port 6 A side of the impeller 6 .
  • This boundary layer grows (develops) on the inner wall surface 21 A of the shroud 21 when the fluid flows from the leading edge 22 A of the blade 22 toward the trailing edge 22 B. Consequently, a large energy deficit is generated at the blowoff port (blade outlet side) 6 B. Thus, it is expected to deteriorate the performance of the impeller.
  • the shape of the blade 22 has the following configuration in order to suppress the growth of the boundary layer.
  • FIG. 3 is a diagram for explaining the inclination angle of the blade shown on a meridional cross section.
  • FIG. 4 is a diagram illustrating the blade projected on the meridional cross section. Since the blade 22 of the impeller 6 has a three-dimensional shape, the inclination angle is expressed with a cylindrical coordinate system shown in FIGS. 3 and 4 .
  • the Z-axis represents the axis line L of the rotary shaft 5 .
  • An r-Z plane formed by the Z-axis and a straight line r extending from an origin point O at an angle made by a predetermined angle ⁇ from the X-axis represents a predetermined meridional cross section 30 .
  • a broken line denoted by the reference numeral 31 is a line (streamline) dividing a meridional passage into equal areas in a blade span direction.
  • the reference numeral 32 denotes a camber line of the blade (for example, the leading edge) before being projected.
  • a projection line (projection line of the camber line of the blade parallel to the meridional cross section 30 ) 33 is formed.
  • An angle made by the projection line 33 and the camber line 32 is defined as the inclination angle of the blade 22 (inclination angle in a circumferential direction of the blade) ⁇ in the present embodiment.
  • the positive or negative sign of the inclination angle ⁇ is defined in accordance with the rotating direction of the rotary shaft 5 .
  • a direction opposite to the rotating direction is defined to be positive.
  • the reference numeral 34 denotes a projection line of a camber line of the blade perpendicular to the meridional cross section 30 .
  • An angle ⁇ Z made by the above-described projection line 33 and the Z-axis (parallel line Z′ translated onto the meridional cross section 30 ) is defined as an axial tilt angle of the blade projected onto the meridional cross section 30 .
  • FIG. 5 is a diagram illustrating the intake port of the impeller as seen from the axial direction.
  • FIG. 6 is a schematic view illustrating the shape of the leading edge of the blade of the impeller.
  • the leading edge 22 A is formed in a curved manner so as to project more on the inner wall surface 21 A side of the shroud 21 than on a inner wall surface 20 A side of the hub 20 .
  • the camber line 32 of the leading edge 22 A curves in such a manner that the inclination angle ⁇ with respect to the projection line 33 formed on the above-described meridional cross section 30 ( FIG. 3 ) is approximately zero or positive on the hub 20 side and gradually increasing toward the shroud 21 .
  • the shroud 21 side of the leading edge 22 A of the blade 22 inclines in the counter-rotating direction.
  • a pressure surface P of the blade 22 is disposed so as to face the inner wall surface 21 A of the shroud 21 .
  • the leading edge 22 A inclines more on the shroud 21 side, thus facing the inner wall surface 21 A of the shroud 21 in a larger degree. Consequently, gradually toward the shroud 21 , force F generated by the pressure surface P of the blade 22 is headed to the inner wall surface 21 A of the shroud 21 .
  • the curve of the leading edge 22 A may be a curve along a single arc or a curve made by a combination of arcs.
  • the inclination angle ⁇ of the leading edge 22 A in the blade 22 is zero or positive on the hub 20 side and gradually increasing toward the shroud 21 .
  • the pressure surface P of the blade 22 faces the inner wall surface 21 A of the shroud 21 in a portion of the blade 22 from the leading edge 22 A to the first half thereof in a flow direction. Consequently, a boundary layer 35 is pressed against the inner wall surface 21 A of the shroud 21 by the force F of the pressure surface P of the blade 22 , thereby suppressing the development of the boundary layer 35 .
  • a boundary layer 35 generated on the suction surface S is pressed against the suction surface S by centrifugal force F 1 , thereby preventing its movement toward the shroud 21 and thus suppressing the development of the boundary layer 35 .
  • FIG. 7 is a diagram illustrating the blowoff port of the impeller as seen from the radial direction.
  • FIG. 8 is a diagram illustrating the blowoff port as seen from the axial direction.
  • FIG. 9 is a schematic view illustrating the shape of the trailing edge of the blade of the impeller.
  • the trailing edge 22 B side of the blade 22 is formed in such a manner that the inclination angle ⁇ of the camber line 32 with respect to the projection line 33 is approximately zero or positive. Such a positive value is preferably closer to zero.
  • a region between the leading edge 22 A and the trailing edge 22 B in the blade 22 is formed in such a manner that the inclination angle ⁇ gradually decreases (becomes closer to zero) along the flow direction of the fluid.
  • the trailing edge 22 B of the blade 22 erects generally perpendicular to the inner wall surface 20 A of the hub 20 and the inner wall surface 21 A of the shroud 21 , thereby making its height (length) in the direction of the axis line L the shortest distance.
  • FIG. 10 is an experimental measurement diagram showing changes in the development of the boundary layers due to the shapes of the blades in the conventional technique and the present embodiment.
  • a to C show changes in the boundary layer in the configuration using the conventional blade 100 ( FIGS. 11 and 12 ).
  • D to F show changes in the boundary layer in the configuration using the blade 22 of the present embodiment.
  • a and D each illustrate an amount of the boundary layer at a position before the outflow port of the impeller.
  • B and E each illustrate an amount of the boundary layer in midstream to the outflow port of the impeller.
  • C and F each illustrate an amount of the boundary layer in a middle portion of the length of the blade in the flow direction.
  • an amount of the boundary layer 109 increases along the flow direction of the fluid (C ⁇ B ⁇ A).
  • an amount of the boundary layer 35 (a portion with a particularly large pressure loss in an accumulated development portion of the boundary layer) slightly increases along the flow direction of the fluid (F ⁇ E ⁇ D)
  • the amount of the boundary layer is reduced significantly as compared to the conventional configuration.
  • the impeller 6 is configured to include the hub 20 , the shroud 21 , and the plurality of blades 22 disposed between the hub 20 and the shroud 21 and blow out the fluid in the radial direction by the rotation of the rotary shaft 5 fixed to the hub 20 .
  • the angle made by the projection line 33 that is obtained by projecting the camber line 32 of the blade 22 onto the predetermined meridional cross section 30 and the camber line 32 is defined as the inclination angle ⁇ and an inclination in the direction opposite to the rotating direction of the rotary shaft 5 is defined to be positive
  • the inclination angle ⁇ of the leading edge 22 A in the blade 22 is zero or positive on the hub 20 side and gradually increasing toward the shroud 21 .
  • the pressure surface P of the blade 22 faces the inner wall surface 21 A of the shroud 21 in the portion of the blade 22 from the leading edge 22 A to the first half thereof. Consequently, the boundary layer 35 is pressed against the inner wall surface 21 A of the shroud 21 by the force F of the pressure surface P of the blade 22 , thereby suppressing the development of the boundary layer 35 .
  • the boundary layer 35 is pressed against the suction surface S by the centrifugal force F 1 , thereby preventing its movement toward the shroud 21 and thus suppressing the development of the boundary layer 35 .
  • the blade 22 is formed in such a manner that the inclination angle ⁇ is gradually decreasing from the leading edge 22 A toward the trailing edge 22 B. Consequently, the surface area of the blade 22 in the latter half of the blade 22 is reduced, and thus the amount of the boundary layer developed over the blade surface in the latter half of the blade 22 can be reduced. This can suppress the generation of the energy deficit portion on the blade outlet side, thereby allowing the performance of the impeller 6 to be fulfilled sufficiently.
  • the inclination angle ⁇ of the trailing edge 22 B in the blade 22 is zero or positive over the region from the hub 20 side to the shroud 21 side according to the present embodiment.
  • the height (length) of the trailing edge 22 B of the blade 22 in the direction of the axis line L can be made the shortest distance. Consequently, the amount of the wake flow due to the thickness of the trailing edge 22 B of the blade 22 can be minimized.
  • the reduced surface area of the blade 22 in the latter half of the blade 22 can significantly reduce the amount of the boundary layer developed over the blade surface in the latter half of the blade 22 as compared to the conventional technique.
  • the provision of the above-described impeller 6 in the centrifugal compressor 1 of the present embodiment can suppress the generation of the energy deficit portion on the outlet side of the blade 22 , thus improving the compression efficiency of the centrifugal compressor 1 .
  • the present invention is not limited by the above details.
  • the above-described embodiment has described the configuration in which the inclination angle ⁇ of the trailing edge 22 B in the blade 22 is zero or positive over a region from the hub 20 side to the shroud 21 side.
  • the inclination angle ⁇ of the trailing edge in the blade 22 may be zero or positive on the hub 20 side and may be gradually increasing toward the shroud 21 .
  • the pressure surface P of the blade 22 faces the inner wall surface 21 A of the shroud 21 also in the latter half of the blade 22 . Consequently, the boundary layer 35 is pressed against the shroud 21 by the force of the pressure surface P of the blade 22 , thereby suppressing the development of the boundary layer 35 more effectively.
  • leading edge 22 A of the blade 22 when projected onto the meridional cross section, has the shape in which the hub 20 and the shroud 21 are generally straight lines in the above-described embodiment.
  • the leading edge 22 A may have a protruding shape protruded toward the upstream side in the flow direction of the fluid between the hub 20 and the shroud 21 . According to such a configuration, the area of a portion of the leading edge 22 A of the blade 22 facing the shroud 21 can be increased, thereby more effectively suppressing the development of the boundary layer 35 accordingly.
  • the leading edge of the blade 22 in the present embodiment is configured such that the inclination angle ⁇ curves with a gradually larger degree from the hub 20 side toward the shroud 21
  • the present invention is not limited thereto.
  • the inclination may be configured to increase (bend) sharply so as to turn outwardly (configuration provided with a discontinuous portion somewhere in the span direction). In this case, not a single but a plurality of bent portions (discontinuous portions) may be provided.
  • the impeller 6 in the present embodiment is provided in the two-stage centrifugal compressor 1
  • the impeller 6 can be applied to a single-stage centrifugal compressor or a multistage centrifugal compressor including three or more stages as long as the compressor includes an impeller.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
US15/503,806 2014-09-18 2015-03-26 Centrifugal impeller and centrifugal compressor Abandoned US20170260998A1 (en)

Applications Claiming Priority (3)

Application Number Priority Date Filing Date Title
JP2014-190468 2014-09-18
JP2014190468A JP2016061241A (ja) 2014-09-18 2014-09-18 遠心羽根車及び遠心圧縮機
PCT/JP2015/059344 WO2016042818A1 (ja) 2014-09-18 2015-03-26 遠心羽根車及び遠心圧縮機

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EP (1) EP3196477A4 (ru)
JP (1) JP2016061241A (ru)
CN (1) CN106662117A (ru)
WO (1) WO2016042818A1 (ru)

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JP7140030B2 (ja) * 2019-03-28 2022-09-21 株式会社豊田自動織機 燃料電池用遠心圧縮機

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DE102014006756A1 (de) * 2014-05-05 2015-11-05 Ziehl-Abegg Se Laufrad für Diagonal- oder Radialventilatoren, Spritzgusswerkzeug zur Herstellung eines solchen Laufrades sowie Gerät mit einem solchen Laufrad

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US20180149158A1 (en) * 2015-05-14 2018-05-31 Denso Corporation Centrifugal blower
US11073159B2 (en) * 2019-02-05 2021-07-27 Mitsubishi Heavy Industries Compressor Corporation Method of manufacturing centrifugal rotary machine and centrifugal rotary machine
US11143201B2 (en) 2019-03-15 2021-10-12 Pratt & Whitney Canada Corp. Impeller tip cavity
US11268536B1 (en) * 2020-09-08 2022-03-08 Pratt & Whitney Canada Corp. Impeller exducer cavity with flow recirculation
US20220074423A1 (en) * 2020-09-08 2022-03-10 Pratt & Whitney Canada Corp. Impeller exducer cavity with flow recirculation

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JP2016061241A (ja) 2016-04-25
EP3196477A1 (en) 2017-07-26
WO2016042818A1 (ja) 2016-03-24
CN106662117A (zh) 2017-05-10

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