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WO2018181086A1 - Roue à aubes, procédé de fabrication de roue à aubes et machine tournante - Google Patents

Roue à aubes, procédé de fabrication de roue à aubes et machine tournante Download PDF

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Publication number
WO2018181086A1
WO2018181086A1 PCT/JP2018/011965 JP2018011965W WO2018181086A1 WO 2018181086 A1 WO2018181086 A1 WO 2018181086A1 JP 2018011965 W JP2018011965 W JP 2018011965W WO 2018181086 A1 WO2018181086 A1 WO 2018181086A1
Authority
WO
WIPO (PCT)
Prior art keywords
impeller
disk
residual stress
blade
compressive residual
Prior art date
Application number
PCT/JP2018/011965
Other languages
English (en)
Japanese (ja)
Inventor
勇哉 紺野
中庭　彰宏
Original Assignee
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 三菱重工コンプレッサ株式会社 filed Critical 三菱重工コンプレッサ株式会社
Priority to US16/487,488 priority Critical patent/US20200063562A1/en
Publication of WO2018181086A1 publication Critical patent/WO2018181086A1/fr

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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
    • F04D29/284—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
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/02—Blade-carrying members, e.g. rotors
    • F01D5/04—Blade-carrying members, e.g. rotors for radial-flow machines or engines
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B24—GRINDING; POLISHING
    • B24C—ABRASIVE OR RELATED BLASTING WITH PARTICULATE MATERIAL
    • B24C1/00—Methods for use of abrasive blasting for producing particular effects; Use of auxiliary equipment in connection with such methods
    • B24C1/10—Methods for use of abrasive blasting for producing particular effects; Use of auxiliary equipment in connection with such methods for compacting surfaces, e.g. shot-peening
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/02—Blade-carrying members, e.g. rotors
    • F01D5/04—Blade-carrying members, e.g. rotors for radial-flow machines or engines
    • F01D5/043—Blade-carrying members, e.g. rotors for radial-flow machines or engines of the axial inlet- radial outlet, or vice versa, type
    • F01D5/048—Form or construction
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/12—Blades
    • F01D5/14—Form or construction
    • F01D5/141—Shape, i.e. outer, aerodynamic form
    • F01D5/142—Shape, i.e. outer, aerodynamic form of the blades of successive rotor or stator blade-rows
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/12—Blades
    • F01D5/14—Form or construction
    • F01D5/147—Construction, i.e. structural features, e.g. of weight-saving hollow blades
    • 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
    • F04D29/02—Selection of particular materials
    • F04D29/023—Selection of particular materials 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
    • F04D29/05—Shafts or bearings, or assemblies thereof, specially adapted for elastic fluid pumps
    • F04D29/053—Shafts
    • F04D29/054—Arrangements for joining or assembling shafts
    • 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
    • F05D2230/00—Manufacture
    • F05D2230/90—Coating; Surface treatment
    • 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
    • F05D2300/00—Materials; Properties thereof
    • F05D2300/70—Treatment or modification of materials
    • F05D2300/702—Reinforcement

Definitions

  • the present invention relates to an impeller used for a rotating machine.
  • Rotating machines such as industrial compressors, turbo refrigerators, and small gas turbines are equipped with an impeller in which a plurality of blades are attached to a disk fixed to a rotating shaft. This rotating machine gives pressure energy and velocity energy to gas by rotating an impeller.
  • an object of this invention is to provide the impeller excellent in fatigue strength, and its manufacturing method.
  • the impeller of the present invention includes a disk portion fixed to a rotating shaft that rotates about an axis, a cover portion that is disposed to face the disk portion, and a plurality of blade portions that are provided between the disk portion and the cover portion, Is provided.
  • the impeller of the present invention is characterized in that a compressive residual stress layer is provided on the surface layer of the boundary portion with the disk portion and the surface layer of the boundary portion with the cover portion at the tip of each blade portion.
  • the blade part and the disk part can be integrally formed or joined to the boundary part with the disk part. Joining is based on the premise that the disk portion and the blade portion are manufactured separately. The same applies to the boundary portion with the cover portion, and the blade portion and the cover portion can be formed integrally or can be joined. Joining is based on the premise that the blade part and the cover part are produced separately.
  • the present invention includes a disk portion fixed to a rotating shaft that rotates around an axis, a cover portion that is disposed to face the disk portion, and a plurality of blade portions that are provided between the disk portion and the cover portion.
  • An impeller manufacturing method is provided.
  • the impeller manufacturing method of the present invention is characterized in that compressive residual stress is applied by shot peening to the surface layer of the boundary portion with the disk portion and the surface portion of the boundary portion with the cover portion at the blade tip of the blade portion.
  • the application of compressive residual stress by shot peening according to the present invention includes a first step using a first shot having a first particle size and a second shot having a second particle size smaller than the first particle size. It is preferably performed in at least two steps of two steps.
  • a rotating machine including the impeller described above is provided.
  • the residual compressive stress layer is provided at the tip of the blade, which is likely to be damaged by fatigue, so that the fatigue strength against continuous operation of the impeller can be improved. Further, according to the impeller manufacturing method of the present invention, the compressive residual stress is applied by shot peening, so that even if it is a closed impeller, the compressive residual stress can be easily applied only to the tip.
  • the centrifugal compressor 100 As shown in FIG. 1, the centrifugal compressor 100 according to the first embodiment includes a casing 102 and a rotating shaft 101 that is pivotally supported on the casing 102 via a journal bearing 103 and a thrust bearing 104.
  • the rotating shaft 101 is supported so as to be rotatable around the axis O, and a plurality of impellers 1 are attached to the rotating shaft 101 side by side in the direction of the axis O.
  • each impeller 1 has a substantially disk shape.
  • the impeller 1 discharges the fluid sucked from the introduction port 3 opened on one side in the direction of the axis O from the discharge port 4 on the outer side in the radial direction through the flow path 105 formed inside the impeller 1. Is configured to do.
  • Each impeller 1 compresses the gas G supplied from the upstream flow path 105 formed in the casing 102 into the downstream flow path 105 in a stepwise manner using centrifugal force generated by the rotation of the rotary shaft 101. Shed.
  • the casing 102 is formed with a suction port 106 for allowing the gas G to flow in from the outside on the front side (F) in the direction of the axis O of the rotary shaft 101. Further, the casing 102 is formed with a discharge port 107 for allowing the gas G to flow out to the outside on the rear side (B) in the direction of the axis O.
  • FIG. 1 shows an example in which six impellers 1 are provided in series on the rotating shaft 101, it is sufficient that at least one impeller 1 is provided on the rotating shaft 101.
  • FIG. 1 shows an example in which six impellers 1 are provided in series on the rotating shaft 101, it is sufficient that at least one impeller 1 is provided on the rotating shaft 101.
  • FIG. 1 shows an example in which six impellers 1 are provided in series on the rotating shaft 101, it is sufficient that at least one impeller 1 is provided on the rotating shaft 101.
  • only one impeller 1 is provided on the rotating shaft 101 will be described.
  • the impeller 1 includes a disk unit 30, a blade unit 40, and a cover unit 50.
  • the disk part 30 is attached to the rotating shaft 101 by being fitted from the outside in the radial direction.
  • the disk unit 30 includes a first disk unit 31 and a second disk unit 35 that are divided into two in the direction of the axis O by a bonding layer CL orthogonal to the axis O.
  • the first disk part 31 and the second disk part 35 are joined by a joining layer CL.
  • the bonding layer CL is preferably constituted by an adhesive and friction welding.
  • the first disk portion 31 has a substantially cylindrical shape with the axis O as the center.
  • the first disk portion 31 includes a grip portion A that is fitted to the rotating shaft 101 with a tightening margin on the front end portion 33 side on the front side (F) of the axis O.
  • cold fitting or shrink fitting can be applied.
  • the impeller 1 in this embodiment is fixed to the rotating shaft 101 only by the grip portion A.
  • the first disk portion 31 includes an outer peripheral surface 34 that gradually increases in diameter toward the rear side (B) of the axis O. This outer peripheral surface 34 is a concave curved surface toward the outside in a cross section including the axis O.
  • the rear end surface 32 of the rear side (B) of the axis O is bonded to the second disk portion 35 via a bonding layer CL formed by friction welding.
  • the second disk portion 35 is formed in a disc shape extending from the rear end portion 36 side opposite to the front end portion 33 side in the direction of the axis O toward the radially outer side.
  • the inner diameter side region 38 of the front end surface 37 is bonded to the rear end surface 32 of the first disk portion 31 via the bonding layer CL.
  • the rear end face 32 and the inner diameter side region 38 of the front end face 37 constitute a bonding layer CL orthogonal to the axis O.
  • a plurality of blade parts 40 are arranged at predetermined intervals in the circumferential direction of the disk part 30.
  • the blade portion 40 is formed with a substantially constant plate thickness and protrudes from the front end surface 37 of the disk portion 30 toward the front side (F) in the direction of the axis O.
  • the blade portion 40 has a slightly tapered shape toward the outside in the radial direction in a side view.
  • each blade portion 40 is formed so as to go to the rear side in the rotation direction R of the impeller 1 as it goes to the outer side in the radial direction of the disk portion 30 when viewed from the direction of the axis O.
  • Each blade portion 40 is formed to be concavely curved toward the rear side in the rotational direction R when viewed from the direction of the axis O.
  • the blade portion 40 only needs to extend to the rear side in the rotational direction R toward the outer side in the radial direction.
  • the blade portion 40 may be formed linearly when viewed from the direction of the axis O.
  • the cover portion 50 covers the blade portion 40 from the front end portion 33 side in the direction of the axis O.
  • the cover portion 50 has a rear end surface 52 in the direction of the axis O formed integrally with the front edge 41 of the blade portion 40.
  • the cover part 50 is formed in a plate shape having a slightly thinner outer thickness in the radial direction, like the disk parts 30 arranged to face each other.
  • the cover part 50 has a bent part 51 bent toward the front side in the direction of the axis O at the position of the inner end 42 of the blade part 40.
  • the bonding layer CL is disposed inside the blade portion 40 in the radial direction. Further, the front end portion 33 of the first disk portion 31 is disposed so as to protrude forward (F) in the direction of the axis O from the front end edge 53 of the bent portion 51. Further, the impeller 1 has a flow path 105 through which the gas G flows by the outer peripheral surface 34 of the first disk portion 31, the front end surface 37 of the second disk portion 35, the side surface 43 of the blade portion 40, and the rear end surface 52 of the cover portion 50. Is formed.
  • a compressive residual stress layer is provided on the surface of the boundary portion with the disk part 30 (second disk part 35) at the discharge port 107 side of the flow path 105, that is, at the tip E of the blade part 40.
  • the impeller 1 is provided with a compressive residual stress layer on the surface layer at the boundary portion with the cover portion 50 at the tip E of the blade portion 40.
  • the region where the compressive residual stress layer is provided is shown as CRS in FIGS.
  • FIG. 2 shows an example in which a crack C has occurred at the boundary between the blade portion 40 and the disk portion 30.
  • a compressive residual stress CRS is applied to the portion of the impeller 1.
  • Fracture failure is broadly divided into crack initiation and propagation processes. Residual stress mainly affects the crack growth process. The mechanism of crack growth due to fatigue is due to repeated crack opening due to plastic slip at the crack edge (blunting), resharpening of the crack edge due to reverse stress, and new plastic slip due to the next cyclic stress. . Therefore, if a new plastic slip occurs at the crack edge, it can be said that the crack does not progress. The compressive residual stress improves the fatigue strength by closing the crack, thereby suppressing the progress of the crack.
  • the compressive residual stress shows a peak at a certain depth from the surface layer, but the value of the compressive residual stress decreases when the depth becomes deeper than the position where the peak is shown, and when the depth exceeds a certain depth, the tensile residual stress It turns into residual stress.
  • the impeller 1 prevents or suppresses the generation
  • a positive value of residual stress indicates tension, and a negative value indicates compression.
  • compressive residual stress is applied by shot peening.
  • means other than shot peening for example, surface treatment such as quenching or nitriding can be employed.
  • shot peening is effective for applying compressive residual stress only in the vicinity of the tip of the blade portion 40.
  • Shot peening is a kind of machining that causes a large number of minute spherical particles, typically metal spheres, to collide with a metal surface at high speed, and these metal spheres are called shots. Since shots are generally harder than the workpiece, when the shot collides with the surface of the workpiece at a high speed, the surface of the workpiece is dented and a round recess remains. Therefore, the surface subjected to shot peening has a pear-like pattern, but in addition to the compressive residual stress being applied to the surface, the hardness of the surface is increased more than before shot peening. In the present embodiment, by providing the compressive residual stress layer at the tip of the blade portion 40, it is possible to prevent the occurrence or development of cracks in the portion.
  • Shot peening includes an impeller method and a compressed air nozzle method based on a means for projecting a shot, but a compressed air nozzle method is suitable for obtaining a high compressive residual stress.
  • FIG. 4 shows how shot peening is performed on the impeller 1 by the compressed air nozzle method.
  • the air nozzle 110 is disposed toward the impeller 1, and a shot S is projected from the air nozzle 110.
  • the air nozzle 110 is projected toward the boundary portion of the disk portion 30 at the tip E of the blade portion 40.
  • the shot S is projected toward the boundary portion of the cover portion 50 at the tip E of the blade portion 40 with the air nozzle 110.
  • the shot S generally has a particle size in the range of 0.2 mm to 1.2 mm, but fine particle peening (Fine ⁇ ⁇ ⁇ Particle Peening using a finer particle size of 0.04 to 0.2 mm) is used. ) Is also present. In addition, this particle size means a diameter. In the present embodiment, one or both of shot peening and fine particle peening with a general particle size can be applied.
  • the main difference between general shot peening and fine particle peening appears in the depth at which the peak of compressive residual stress occurs. That is, the position where the peak of compressive residual stress is closer to the surface in fine particle peening than in shot peening having a general particle size.
  • the peak depth is about 0.01 mm, for example, whereas in the case of shot peening with the general particle size described above, the peak depth is about 0.05 mm, for example. It is. That is, the compressive residual stress due to fine particle peening is given to a relatively shallow range from the surface layer, and the compressive residual stress due to shot peening due to a general particle size is applied to a relatively deep range from the surface layer.
  • two-stage shot peening in which shots having different particle sizes are projected in two stages.
  • two-stage shot peening As shown in FIG. 5B as “two-stage”, a compressive residual stress in which a compressive residual stress caused by a shot having a general particle diameter and a compressive residual stress caused by a fine particle shot are superimposed. Is granted. That is, since the peak due to the compressive residual stress occurs at two different locations in the depth direction, the compressive residual stress can be applied to a wider range in the depth direction.
  • shot peening is performed with a general particle size (first particle size, first shot) as the first step, and then fine particles (second particle size, second shot) as the second step. ) It is preferable to perform shot peening. Note that three or more stages of shot peening can be performed using shots having different particle sizes.
  • the impeller 1 of the present embodiment is provided with a compressive residual stress layer at the tip E of the blade part 40 and at the boundary part with the first disk part 31 and the boundary part with the cover part 50. Therefore, according to the impeller 1, since the fatigue strength of the boundary portion where cracks are likely to occur due to fatigue is improved and the occurrence and development of cracks can be prevented, the impeller 1 can have a longer life. Moreover, since the compressive residual stress is given to the said boundary part, the corresponding force corrosion cracking property of the said boundary part can be improved. In particular, since the impeller 1 applies compressive residual stress only to the tip portion where cracks are likely to occur, the generation and progress of cracks can be prevented efficiently.
  • the configuration described in the above embodiment can be selected or changed to another configuration as appropriate.
  • the impeller 1 in the present embodiment has the disk part 30 divided into a first disk part 31 and a second disk part 35, and the second disk part 35, the blade part 40, and the cover part 50 are integrally formed. It has a structure.
  • the impeller of the present invention is not limited to this.
  • the present invention can also be applied to an impeller that joins a disk portion and a blade portion that are formed integrally with a cover portion that is formed separately from these.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Architecture (AREA)
  • Physics & Mathematics (AREA)
  • Fluid Mechanics (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)

Abstract

L'invention concerne une roue à aubes (1) présentant une excellente résistance à la fatigue. La roue à aubes (1) est caractérisée en ce qu'elle comprend une partie disque (30) fixée à un arbre de rotation (101) tournant autour d'un axe (O), une partie couvercle (50) agencée en regard de la partie disque (30) et de multiples parties pales (40) agencées entre la partie disque (30) et la partie couvercle (50). Au niveau des pointes de chaque partie pale (40), une couche de contrainte résiduelle de compression est agencée sur la couche de surface au niveau de la limite avec la partie disque (30) et sur la couche de surface au niveau de la limite avec la partie couvercle (50). <u /> <u />
PCT/JP2018/011965 2017-03-30 2018-03-26 Roue à aubes, procédé de fabrication de roue à aubes et machine tournante WO2018181086A1 (fr)

Priority Applications (1)

Application Number Priority Date Filing Date Title
US16/487,488 US20200063562A1 (en) 2017-03-30 2018-03-26 Impeller, impeller manufacturing method, and rotating machine

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
JP2017066763A JP2018168761A (ja) 2017-03-30 2017-03-30 インペラ、インペラの製造方法、及び、回転機械
JP2017-066763 2017-03-30

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Publication Number Publication Date
WO2018181086A1 true WO2018181086A1 (fr) 2018-10-04

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US (1) US20200063562A1 (fr)
JP (1) JP2018168761A (fr)
WO (1) WO2018181086A1 (fr)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN116127653A (zh) * 2023-04-13 2023-05-16 西北工业大学 提高疲劳强度的叶片形性优化设计方法、叶片和离心叶轮

Families Citing this family (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JP7204585B2 (ja) * 2019-06-17 2023-01-16 株式会社東芝 表面処理条件導出装置、表面処理システムおよび表面処理方法

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JPH06145785A (ja) * 1992-11-06 1994-05-27 Toyota Motor Corp 浸炭鋼材のショットピーニング法
JPH08299850A (ja) * 1995-05-12 1996-11-19 Hitachi Koki Co Ltd 遠心機用ロータの製造法
JP2000018191A (ja) * 1998-07-03 2000-01-18 Hitachi Ltd 羽根車
JP2000052248A (ja) * 1998-08-07 2000-02-22 Komatsu Ltd ショットピーニング方法およびその装置並びに得られる機械部品
US6164931A (en) * 1999-12-15 2000-12-26 Caterpillar Inc. Compressor wheel assembly for turbochargers
US20080008595A1 (en) * 2004-11-13 2008-01-10 Mckenzie David Compressor wheel
JP2011122457A (ja) * 2009-12-08 2011-06-23 Yamada Seisakusho Co Ltd クローズドインペラ
US20110200439A1 (en) * 2008-10-23 2011-08-18 Akihiro Nakaniwa Impeller, compressor, and method for producing impeller
JP2014094433A (ja) * 2012-11-09 2014-05-22 Mitsubishi Heavy Ind Ltd 遠心回転機のインペラの製造方法
JP2017035712A (ja) * 2015-08-10 2017-02-16 株式会社東芝 ピーニング処理方法およびタービンロータホイール

Patent Citations (10)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JPH06145785A (ja) * 1992-11-06 1994-05-27 Toyota Motor Corp 浸炭鋼材のショットピーニング法
JPH08299850A (ja) * 1995-05-12 1996-11-19 Hitachi Koki Co Ltd 遠心機用ロータの製造法
JP2000018191A (ja) * 1998-07-03 2000-01-18 Hitachi Ltd 羽根車
JP2000052248A (ja) * 1998-08-07 2000-02-22 Komatsu Ltd ショットピーニング方法およびその装置並びに得られる機械部品
US6164931A (en) * 1999-12-15 2000-12-26 Caterpillar Inc. Compressor wheel assembly for turbochargers
US20080008595A1 (en) * 2004-11-13 2008-01-10 Mckenzie David Compressor wheel
US20110200439A1 (en) * 2008-10-23 2011-08-18 Akihiro Nakaniwa Impeller, compressor, and method for producing impeller
JP2011122457A (ja) * 2009-12-08 2011-06-23 Yamada Seisakusho Co Ltd クローズドインペラ
JP2014094433A (ja) * 2012-11-09 2014-05-22 Mitsubishi Heavy Ind Ltd 遠心回転機のインペラの製造方法
JP2017035712A (ja) * 2015-08-10 2017-02-16 株式会社東芝 ピーニング処理方法およびタービンロータホイール

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN116127653A (zh) * 2023-04-13 2023-05-16 西北工业大学 提高疲劳强度的叶片形性优化设计方法、叶片和离心叶轮

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JP2018168761A (ja) 2018-11-01

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