WO2016042818A1 - 遠心羽根車及び遠心圧縮機 - Google Patents

遠心羽根車及び遠心圧縮機 Download PDF

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Publication number
WO2016042818A1
WO2016042818A1 PCT/JP2015/059344 JP2015059344W WO2016042818A1 WO 2016042818 A1 WO2016042818 A1 WO 2016042818A1 JP 2015059344 W JP2015059344 W JP 2015059344W WO 2016042818 A1 WO2016042818 A1 WO 2016042818A1
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WO
WIPO (PCT)
Prior art keywords
blade
shroud
hub
impeller
boundary layer
Prior art date
Application number
PCT/JP2015/059344
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English (en)
French (fr)
Japanese (ja)
Inventor
穣 枡谷
大輔 平田
Original Assignee
三菱重工業株式会社
三菱重工コンプレッサ株式会社
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 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 EP15841417.7A priority Critical patent/EP3196477A4/en
Priority to CN201580043392.2A priority patent/CN106662117A/zh
Priority to US15/503,806 priority patent/US20170260998A1/en
Publication of WO2016042818A1 publication Critical patent/WO2016042818A1/ja

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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 are used in petrochemical plants and natural gas plants.
  • a centrifugal impeller that includes a hub fixed to a rotating shaft and a plurality of blades disposed on the hub, and blows fluid in a radial direction by rotation of the rotating shaft (for example, see Patent Document 1).
  • the blade 100 of the centrifugal impeller when the blade 100 of the centrifugal impeller is viewed from the suction port 101 side, as illustrated in FIG. 11, the blade 100 includes a camber line 103 of the leading edge 102 and a straight line extending in the radial direction from the rotation center.
  • the angle formed with 104 is formed to be approximately 0 ° from the wall surface 105 on the hub side to the wall surface 106 on the shroud side.
  • the blade latter half portion including the trailing edge 108 faces the negative pressure surface S of the blade 100 and the shroud-side wall surface 106. So that it is tilted diagonally.
  • a boundary layer 109 is generated on the shroud-side wall surface 106 forming a fluid flow path, and this boundary layer 109 is in a deceleration region of the shroud-side wall surface 106 in the front half of the blade.
  • a boundary layer starting from the leading edge 102 develops on the negative pressure surface S that is decelerated more than the positive pressure surface P to which positive pressure is applied by rotation.
  • the boundary layer is sucked upward by a radial force and flows into the boundary layer 109 generated on the shroud-side wall 106, and thereby, the boundary layer 109 of the shroud-side wall 106 further develops.
  • the boundary layer developed in this way further grows in the latter half of the blade and creates a large energy loss portion on the blade outlet side, thus impairing the performance of the centrifugal impeller.
  • the conventional configuration has not been particularly devised to suppress the boundary layer 109 that develops on the shroud-side wall surface 106 in the first half of the blade.
  • the present invention has been made in view of such circumstances, and an object of the present invention is to provide a centrifugal impeller and a centrifugal compressor capable of suppressing the development of the boundary layer and sufficiently exhibiting the performance.
  • a centrifugal impeller of the present invention includes a hub, a shroud, and a plurality of blades disposed between the hub and the shroud, and is fixed to the hub.
  • a centrifugal impeller that blows out fluid in the radial direction by rotating the rotating shaft, and the angle formed by the projection line and the camber line when the camber line of the blade is projected on a predetermined meridional plane section is defined as the inclination angle.
  • the blade When the inclination in the direction opposite to the rotational direction of the shaft is positive, the blade has a leading edge inclination angle of 0 or positive on the hub side, and gradually increases toward the shroud side. The inclination angle gradually decreases from the front edge toward the rear edge.
  • the pressure surface of the blade is shroud from the front edge to the front half of the blade. Opposite. For this reason, the development of the boundary layer can be suppressed by pressing the boundary layer to the shroud side with the force of the pressure surface of the blade. In addition, at the suction surface of the blade, the boundary layer is pressed against the suction surface by centrifugal force, so that the movement toward the shroud side is suppressed, and the development of the boundary layer can be suppressed.
  • the inclination angle gradually decreases from the leading edge toward the trailing edge, so that the blade surface area in the latter half of the blade is reduced, and the blade surface develops in the latter half of the blade.
  • the amount of boundary layer to be reduced can be reduced.
  • the blade has a trailing edge whose inclination angle is 0 or positive on the hub side and gradually increases toward the shroud side. According to this configuration, even in the latter half of the blade, the pressure surface of the blade is opposed to the shroud. Therefore, the boundary layer is pressed against the shroud by the force of the pressure surface of the blade, so that the development of the boundary layer can be suppressed.
  • the blade has an inclination angle of 0 or positive from the hub side to the shroud side.
  • the positive value is preferably close to 0. According to this configuration, since the length of the trailing edge of the blade is the shortest distance, the amount of wake from the trailing edge thickness of the blade is minimized. Furthermore, by reducing the surface area of the blade in the latter half of the blade, the amount of the boundary layer that develops on the blade surface in the second half of the blade can be made smaller than before.
  • the front edge of the blade shall be straight from the hub side to the shroud side when projected onto the meridional section, or a shape that protrudes upstream in the flow direction between the hub side and the shroud side. Is preferred.
  • wing facing a shroud can be enlarged, and the development of a boundary layer can be suppressed more effectively by that much.
  • the centrifugal compressor includes the centrifugal impeller described above, it is possible to suppress the occurrence of an energy loss portion on the blade outlet side and improve the compression efficiency of the centrifugal compressor.
  • the blade has a leading edge whose inclination angle is 0 or positive on the hub side and gradually increases toward the shroud side, and in the flow direction, from the leading edge to the trailing edge. Since the inclination angle gradually decreases toward the front, the pressure surface of the blade faces the shroud from the front edge to the front half of the blade, so that the development of the boundary layer can be suppressed and the energy on the blade outlet side is reduced. Generation
  • deletion part can be suppressed and the performance of a centrifugal impeller can fully be exhibited.
  • FIG. 1 is a longitudinal sectional view of a centrifugal compressor according to this embodiment.
  • FIG. 2 is a partially enlarged view showing the impeller.
  • FIG. 3 is a diagram for explaining the inclination angle of the blades represented on the meridian plane cross section.
  • FIG. 4 is a diagram showing the blades projected on the meridional section.
  • FIG. 5 is a view of the inlet of the impeller as viewed from the axial direction.
  • FIG. 6 is a schematic diagram showing the shape of the leading edge of the impeller blades.
  • FIG. 7 is a view of the air outlet of the impeller as viewed from the radial direction.
  • FIG. 8 is a view of the air outlet of the impeller as viewed from the axial direction.
  • FIG. 1 is a longitudinal sectional view of a centrifugal compressor according to this embodiment.
  • FIG. 2 is a partially enlarged view showing the impeller.
  • FIG. 3 is a diagram for explaining the inclination angle of
  • FIG. 9 is a schematic diagram showing the shape of the trailing edge of the impeller blades.
  • FIG. 10 is an experimental measurement diagram showing changes in the growth of the boundary layer according to the shape of the blades of the conventional and this embodiment.
  • FIG. 11 is a schematic diagram showing the shape of the leading edge of a blade of a conventional impeller.
  • FIG. 12 is a schematic diagram showing the shape of the trailing edge of a conventional impeller blade.
  • FIG. 1 is a longitudinal sectional view of a centrifugal compressor according to this embodiment.
  • the centrifugal compressor 1 includes a casing 2 configured by combining a plurality of parts, and a rotating shaft 5 that is rotatably supported around the axis L in the casing 2 via a bearing (not shown). And closed type impellers 6 and 6 provided so as to rotate integrally with the rotary shaft 5. That is, the centrifugal compressor 1 of the present embodiment is a two-stage centrifugal compressor.
  • the centrifugal compressor 1 is driven by a driving device (not shown), and the impellers 6 and 6 are rotated to rotate the impellers 6 and 6 through a suction port 10 provided in the casing 2. Etc. are sucked.
  • a suction passage 11 is connected to the suction port 10 via a suction space 10A formed in the casing 2, and the suction passage 11 bends along the axis L direction (axial direction) of the rotary shaft 5.
  • the first stage impeller 6 is opened facing the suction port 6A.
  • Centrifugal force is applied to the fluid sucked from the suction port 10 by the rotation of the first stage impeller 6, and the kinetic energy is pressured by the first stage vaneless diffuser 12 provided at the outlet 6 ⁇ / b> B of the impeller 6. Converted into energy. Further, this fluid is guided through the return bend 14 and the return vane 15 to the suction port 6A of the second stage impeller 6 which is the next stage compression stage.
  • the compressed fluid is similarly given a centrifugal force by the second stage impeller 6, and the kinetic energy is converted into pressure energy by the second stage vaneless diffuser 12, and further becomes a high pressure compressed fluid to the scroll 16. Discharged.
  • the scroll 16 is then sent to a discharge pipe (not shown) via a discharge port 17 provided in the casing 2.
  • symbol 18 in FIG. 1 is a balance piston provided in order to adjust the thrust of the impeller 6. FIG. Next, the impeller 6 will be described.
  • FIG. 2 is a partially enlarged view showing the impeller.
  • the impeller 6 includes a hub 20 that is fixed to the rotary shaft 5, a shroud 21 that is disposed with a gap in the radial direction and the axial direction with respect to the hub 20, and the hub 20 and the shroud 21. And a plurality of blades 22 arranged between the two. Although not shown, the blades 22 are arranged radially around the axis L at intervals. Further, the front edge 22A of the blade 22 is located on the inlet 6A side of the impeller 6, and the rear edge 22B extends to the air outlet 6B of the impeller 6.
  • a boundary layer is generated on the inner wall surface 21A of the shroud 21 that forms a fluid flow path together with the hub 20.
  • This boundary layer grows (develops) on the inner wall surface 21A of the shroud 21 when a fluid flows from the leading edge 22A to the trailing edge 22B of the blade 22, and causes a large energy deficiency at the outlet (blade outlet side) 6B.
  • the shape of the blade 22 has the following configuration.
  • FIG. 3 is a view for explaining the inclination angle of the blades shown on the meridional section
  • FIG. 4 is a view showing the blades projected on the meridional section. Since the blades 22 of the impeller 6 have a three-dimensional shape, the inclination angle is expressed using the cylindrical coordinate system shown in FIGS.
  • the Z axis indicates the axis L of the rotating shaft 5.
  • An rZ plane formed by the Z axis and a straight line r extending from the origin O at an angle formed by the predetermined angle ⁇ from the X axis indicates a predetermined meridian plane cross section 30.
  • the broken line indicated by reference numeral 31 is a line (streamline) obtained by dividing the meridional flow path into equal areas in the blade span direction.
  • reference numeral 32 denotes a camber line of a blade (for example, a leading edge) before projection.
  • a projection line 33 projection line of the camber line of the blade parallel to the meridional section 30.
  • the angle formed by the projection line 33 and the camber line 32 is defined as the inclination angle (inclination angle of the blade in the circumferential direction) ⁇ of the blade 22 of the present embodiment.
  • the positive / negative of inclination-angle (gamma) (theta) is prescribed
  • Reference numeral 34 denotes a projection line of a camber line of a blade perpendicular to the meridional section 30, and an angle ⁇ Z formed by the projection line 33 and the Z axis (parallel line Z ′ translated to the meridional section 30). Is the tilt angle in the axial direction of the blade projected onto the meridional section 30.
  • FIG. 5 is a view of the inlet of the impeller as viewed from the axial direction
  • FIG. 6 is a schematic diagram showing the shape of the leading edge of the impeller blades.
  • the front edge 22 ⁇ / b> A is curved so as to protrude from the inner wall surface 20 ⁇ / b> A of the hub 20 toward the inner wall surface 21 ⁇ / b> A of the shroud 21.
  • the camber line 32 of the leading edge 22A has an inclination angle ⁇ with respect to the projection line 33 onto the meridional section 30 (FIG. 3) is substantially 0 or positive on the hub 20 side, and is on the shroud 21 side.
  • the front edge 22 ⁇ / b> A of the blade 22 is disposed so that the positive pressure surface P of the blade 22 faces the inner wall surface 21 ⁇ / b> A of the shroud 21 by tilting the shroud 21 side in the counter-rotating direction. Furthermore, since the inclination angle ⁇ gradually increases toward the shroud 21, the front edge 22 ⁇ / b> A is inclined toward the shroud 21 and is more opposed to the inner wall surface 21 ⁇ / b> A of the shroud 21. For this reason, the force F generated by the pressure surface P of the blade 22 gradually moves toward the inner wall surface 21A of the shroud 21 toward the shroud 21 side.
  • the curvature of the front edge 22A may be curved along one arc, or may be curved by combining a plurality of arcs.
  • the blade 22 has an inclination angle ⁇ of the front edge 22A that is 0 or positive on the hub 20 side and gradually increases toward the shroud 21 side. Therefore, from the front edge 22A of the blade 22 in the flow direction.
  • the pressure surface P of the blade 22 faces the inner wall surface 21 ⁇ / b> A of the shroud 21 over the front half. For this reason, the development of the boundary layer 35 can be suppressed by pressing the boundary layer 35 against the inner wall surface 21 ⁇ / b> A of the shroud 21 with the force F of the pressure surface P of the blade 22.
  • the boundary layer 35 generated on the suction surface S is pressed against the suction surface S by the centrifugal force F ⁇ b> 1, so that the movement to the shroud 21 side is suppressed and the development of the boundary layer 35 is suppressed. Can be suppressed.
  • FIG. 7 is a view of the air outlet of the impeller as viewed from the radial direction
  • FIG. 8 is a view of the air outlet as viewed from the axial direction
  • FIG. 9 is a schematic diagram showing the shape of the trailing edge of the impeller blades. It is.
  • the rear edge 22B side of the blade 22 is formed so that the inclination angle ⁇ of the camber line 32 with respect to the projection line 33 is substantially 0 or positive. This positive value is preferably close to zero.
  • the inclination angle ⁇ is gradually reduced (approached to 0) along the fluid flow direction.
  • the rear edge 22B of the blade 22 is erected substantially perpendicularly to the inner wall surface 20A of the hub 20 and the inner wall surface 21A of the shroud 21, so that the height (length) in the axis L direction is minimized. Because of the distance, the amount of wake from the thickness of the trailing edge 22B of the blade 22 is minimized.
  • FIG. 10 is an experimental measurement diagram showing changes in the growth of the boundary layer according to the shape of the blades of the conventional and this embodiment.
  • a to C show changes in the boundary layer in the configuration using the conventional blades 100 (FIGS. 11 and 12)
  • D to F are boundary layers in the configuration using the blades 22 of the present embodiment. Shows changes.
  • a and D respectively indicate the amount of the boundary layer before the outlet of the impeller.
  • B and E show the quantity of the boundary layer in the middle part which goes to the outflow port of an impeller, respectively.
  • C and F respectively show the amount of the boundary layer at the middle part of the length in the flow direction of the blades.
  • the amount of the boundary layer 109 increases along the fluid flow direction (C ⁇ B ⁇ A).
  • the amount of the boundary layer 35 is slightly increased along the fluid flow direction (F ⁇ E ⁇ D).
  • the hub 20, the shroud 21, and the rotating shaft that is fixed to the hub 20 includes the plurality of blades 22 disposed between the hub 20 and the shroud 21.
  • 5 is an impeller 6 that blows out fluid in the radial direction by rotation of 5, and an angle formed by the projection line 33 and the camber line 32 when the camber line 32 of the blade 22 is projected onto a predetermined meridional section 30 is an inclination angle ⁇ .
  • the blade 22 has the inclination angle ⁇ of the front edge 22A being 0 or positive on the hub 20 side and gradually toward the shroud 21 side.
  • the pressure surface P of the blade 22 faces the inner wall surface 21 ⁇ / b> A of the shroud 21 from the front edge 22 ⁇ / b> A to the front half of the blade 22. For this reason, the development of the boundary layer 35 can be suppressed by pressing the boundary layer 35 toward the inner wall surface 21 ⁇ / b> A of the shroud 21 with the force F of the pressure surface P of the blade 22. Moreover, in the suction surface S of the blade
  • the inclination angle ⁇ is formed to gradually decrease from the front edge 22A toward the rear edge 22B. Therefore, by reducing the surface area of the blade 22 in the latter half of the blade 22, the blade The amount of the boundary layer that develops on the blade surface in the latter half of 22 can be reduced. Thereby, generation
  • the blade 22 has an inclination angle ⁇ of the trailing edge 22B that is 0 or positive from the hub 20 side to the shroud 21 side, so that the height in the axis L direction at the trailing edge 22B of the blade 22 ( Therefore, the amount of the wake from the thickness of the trailing edge 22B of the blade 22 is minimized. Furthermore, by reducing the surface area of the blade 22 in the latter half of the blade 22, the amount of the boundary layer that develops on the blade surface in the latter half of the blade 22 can be significantly reduced as compared with the conventional case.
  • the centrifugal compressor 1 of the present embodiment includes the impeller 6 described above, it is possible to suppress the occurrence of an energy loss portion on the blade 22 outlet side and improve the compression efficiency of the centrifugal compressor 1.
  • this invention is not limited by the above-mentioned content.
  • the configuration in which the inclination angle ⁇ of the trailing edge 22B of the blade 22 is 0 or positive from the hub 20 side to the shroud 21 side has been described. It may be 0 or positive on the side and gradually increase toward the shroud 21 side.
  • the pressure surface P of the blade 22 faces the inner wall surface 21 ⁇ / b> A of the shroud 21 even in the latter half of the blade 22, so that the boundary layer 35 is pressed against the shroud 21 by the force of the pressure surface P of the blade 22.
  • the development of the boundary layer 35 can be more effectively suppressed.
  • the front edge 22A of the blade 22 has a shape in which the hub 20 and the shroud 21 are substantially straight when projected onto the meridional section, but this is not a limitation. Between the hub 20 and the shroud 21, the front edge 22A may have a convex shape that protrudes upstream in the fluid flow direction. According to this configuration, the area of the front edge 22A portion of the blade 22 facing the shroud 21 can be increased, and the development of the boundary layer 35 can be more effectively suppressed accordingly.
  • the front edge of the blade 22 is configured so that the inclination angle ⁇ is gradually and gradually curved from the hub 20 side toward the shroud 21 side. It is also possible to adopt a configuration (a configuration in which a discontinuous portion is provided somewhere in the span direction) that suddenly increases (bends). In this case, a plurality of bent portions (discontinuous portions) may be provided instead of one.
  • the impeller 6 is provided in the two-stage centrifugal compressor 1.
  • the compressor includes an impeller, a single-stage centrifugal compressor or three or more stages of multistage centrifugal compression is used. It is possible to apply to the machine.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
PCT/JP2015/059344 2014-09-18 2015-03-26 遠心羽根車及び遠心圧縮機 WO2016042818A1 (ja)

Priority Applications (3)

Application Number Priority Date Filing Date Title
EP15841417.7A EP3196477A4 (en) 2014-09-18 2015-03-26 Centrifugal impeller and centrifugal compressor
CN201580043392.2A CN106662117A (zh) 2014-09-18 2015-03-26 离心叶轮以及离心压缩机
US15/503,806 US20170260998A1 (en) 2014-09-18 2015-03-26 Centrifugal impeller and centrifugal compressor

Applications Claiming Priority (2)

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

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WO2016042818A1 true WO2016042818A1 (ja) 2016-03-24

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

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JP7161419B2 (ja) * 2019-02-05 2022-10-26 三菱重工コンプレッサ株式会社 遠心回転機械の製造方法、及び遠心回転機械
US11143201B2 (en) 2019-03-15 2021-10-12 Pratt & Whitney Canada Corp. Impeller tip cavity
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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US20170260998A1 (en) 2017-09-14
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JP2016061241A (ja) 2016-04-25
EP3196477A4 (en) 2018-05-02

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