EP3369938A1 - Verdichterlaufrad und verfahren zur herstellung davon - Google Patents

Verdichterlaufrad und verfahren zur herstellung davon Download PDF

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Publication number
EP3369938A1
EP3369938A1 EP16884910.7A EP16884910A EP3369938A1 EP 3369938 A1 EP3369938 A1 EP 3369938A1 EP 16884910 A EP16884910 A EP 16884910A EP 3369938 A1 EP3369938 A1 EP 3369938A1
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EP
European Patent Office
Prior art keywords
blade
blades
compressor impeller
angle
leading edges
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.)
Granted
Application number
EP16884910.7A
Other languages
English (en)
French (fr)
Other versions
EP3369938B1 (de
EP3369938A4 (de
Inventor
Kenichiro Iwakiri
Isao Tomita
Seiichi Ibaraki
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 Engine and Turbocharger Ltd
Original Assignee
Mitsubishi Heavy Industries Engine and Turbocharger Ltd
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 Engine and Turbocharger Ltd filed Critical Mitsubishi Heavy Industries Engine and Turbocharger Ltd
Publication of EP3369938A1 publication Critical patent/EP3369938A1/de
Publication of EP3369938A4 publication Critical patent/EP3369938A4/de
Application granted granted Critical
Publication of EP3369938B1 publication Critical patent/EP3369938B1/de
Active legal-status Critical Current
Anticipated expiration legal-status Critical

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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
    • 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
    • F04D29/66—Combating cavitation, whirls, noise, vibration or the like; Balancing
    • 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
    • F04D29/661—Combating cavitation, whirls, noise, vibration or the like; Balancing especially adapted for elastic fluid pumps
    • F04D29/666—Combating cavitation, whirls, noise, vibration or the like; Balancing especially adapted for elastic fluid pumps by means of rotor construction or layout, e.g. unequal distribution of blades or vanes
    • 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
    • F05D2240/307—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 tip of a rotor blade

Definitions

  • the present disclosure relates to a compressor impeller and a method for manufacturing the same.
  • Compressors such as a centrifugal compressor, an axial-flow compressor and an axial-flow compressor are configured to apply kinetic energy to a fluid through rotation of a compressor impeller, and convert the kinetic energy into pressure, thereby obtaining a highpressure fluid.
  • Such a compressor is provided with various features to meet the need to improve the pressure ratio and the efficiency in a wide operational range.
  • Patent Document 1 discloses a centrifugal compressor for suppressing rotating stall.
  • Rotating stall is an unstable phenomenon in which a stalling region generated on a blade propagates in the rotational direction from a blade to another blade at a speed lower than the tip speed of the impeller during operation in a low flow-rate range.
  • the compressor disclosed in Patent Document 1 includes a suppressing member for suppressing development of vortices of a fluid formed in the vicinity of a leading edge of a blade, disposed on the inner peripheral surface of the casing or the outer peripheral surface of the rotational shaft of the impeller at the upstream side of the blade leading edge of the impeller and configured to rotate relatively to the blade.
  • Patent Document 1 JP2014-118916A
  • the present invention was made in view of the above issue, and an object is to provide a compressor impeller and a method for manufacturing the same, whereby it is possible to suppress rotating stall with a simplified configuration.
  • a compressor impeller and a method for manufacturing the same, whereby it is possible to suppress rotating stall with a simplified configuration.
  • an expression of relative or absolute arrangement such as “in a direction”, “along a direction”, “parallel”, “orthogonal”, “centered”, “concentric” and “coaxial” shall not be construed as indicating only the arrangement in a strict literal sense, but also includes a state where the arrangement is relatively displaced by a tolerance, or by an angle or a distance whereby it is possible to achieve the same function.
  • an expression of an equal state such as “same” “equal” and “uniform” shall not be construed as indicating only the state in which the feature is strictly equal, but also includes a state in which there is a tolerance or a difference that can still achieve the same function.
  • an expression of a shape such as a rectangular shape or a cylindrical shape shall not be construed as only the geometrically strict shape, but also includes a shape with unevenness or chamfered corners within the range in which the same effect can be achieved.
  • FIG. 1 is an axial-directional view of a compressor impeller 100 (100A) according to an embodiment.
  • FIG. 2 is a meridional cross-sectional view of a part of a compressor impeller 100 (100A) shown in FIG. 1 , taken along the axial direction.
  • the compressor impeller 100 includes a hub 2 and a blade group 6 including a plurality of blades 4 arranged at intervals in the circumferential direction on the outer peripheral surface 2a of the hub 2.
  • the blades 4 are aligned such that the hub-side ends 4A of the leading edges of the respective blade 4 are on the same circle C1 centered at the rotational axis O of the compressor impeller.
  • the blade group 6 is configured such that the hub-side ends 4A of the plurality of blades 4 are at the same position in the axial direction of the compressor impeller 100.
  • the plurality of blades 4 includes at least one first blade 12, and at least one second blade 14 having a different shape from the first blade 12.
  • FIG. 3 is a schematic diagram for describing the shape of the first blade 12 and the second blade 14.
  • FIG. 4 is a blade-row expanded view schematically showing the positional relationship of the plurality of blades 4 on the tip side.
  • FIG. 5 is a blade-row expanded view schematically showing the positional relationship of the plurality of blades 4 on the hub side.
  • the horizontal axis represents the position 'r ⁇ ' in the circumferential direction of the compressor impeller 100
  • the vertical axis represents the distance from the leading edge 12LE in the meridional direction 'm'.
  • the "meridional direction 'm''' refers to the direction along a line connecting points at which the blade height ratio is the same, from the leading edge 12LE to the trailing edge 12TE of the blade 4.
  • blade height ratio is defined as follows. First, as shown in FIG.
  • 'mh' refers to the meridional length from the position of the leading edge 12LE to the position of the trailing edge TE at the hub-side end of the blade 4
  • 'mt' refers to the meridional length from the position of the leading edge LE to the position of the trailing edge TE at the tip-side end of the blade 4.
  • the position P and the position Q are such positions that the ratio of the meridional length from the position of the leading edge 12LE on the hub-side end of the blade 4 to the position P divided by the meridional length 'mh' is equal to the ratio of the meridional length from the position of the leading edge LE on the tip-side end of the blade 4 to the position Q divided by the meridional length 'mh' (e.g. the position P and the position Q where both of the ratios are 20%), the length of the segment connecting the position P and the position Q is defined as the blade height 'h' at a meridional position (%). Further, the value y/h obtained by dividing the distance y from the outer peripheral surface 2a of the hub 2 in the blade height direction along the segment by the blade height 'h' is defined as the blade height ratio.
  • blade angle ⁇ 1 of the leading edge LE of the first blade 12 when comparing the blade angle ⁇ 1 of the leading edge LE of the first blade 12 to the blade angle ⁇ 2 of the leading edge 14LE of the second blade 14 at the same position 'r' with respect to the radial direction of the compressor impeller 100, at least in a partial range w1 in the radial direction of the compressor impeller 100, the blade angle ⁇ 1 of the leading edge LE of the first blade 12 is different from the blade angle ⁇ 2 of the leading edge 14LE of the second blade 14.
  • blade angle ⁇ refers to the angle ⁇ (see FIG.
  • the at least one first blade 12 includes a plurality of first blades 12, and the at least one second blade 14 includes a plurality of second blades 14.
  • the number of second blades 14 in the blade group 6 is smaller than the number of the first blades 12 in the blade group 6.
  • the plurality of second blades 14 includes a pair of second blades 14 between which the first blade 12 is not disposed in the circumferential direction of the compressor impeller 100.
  • the blade group 6 includes six blades 4, and the six blades 4 includes four first blades 12 and two second blades 14. None of the first blades 12 is disposed between the two second blades 14.
  • the second blades 14 relatively fewer than the first blades 12 and having different stalling characteristics from the first blades 12 are aligned continuously in the circumferential direction of the compressor impeller 100, and thus it is possible to enhance the above effect to impair uniform propagation and development of rotating stall.
  • the blade angle ⁇ 1 of the leading edge LE of the first blade 12 when comparing the blade angle ⁇ 1 of the leading edge LE of the first blade 12 to the blade angle ⁇ 2 of the leading edge 14LE of the second blade 14 at the same position 'r' with respect to the radial direction of the compressor impeller 100, at least in the partial range w1 in the radial direction of the compressor impeller 100, the blade angle ⁇ 2 of the leading edge 14LE of the second blade 14 is greater than the blade angle ⁇ 1 of the leading edge 12LE of the first blade 12.
  • the leading edges LE of the second blades 14 have the relatively large blade angle ⁇ 2 matched to the small flow-rate side (less likely to stall even at a small flow rate), and thereby stalling is less likely to occur in the region A on the suction surface side of the second blade 14, which makes it possible to impair propagation and development of rotating stall effectively. Accordingly, as shown in FIG. 7 , as compared to the above comparative embodiment, it is possible to shift the surge line to the small flow-rate side and expand the operational range at the small flow-rate side.
  • leading edges 12LE of the relatively large number of first blades 12 have the relatively small blade angle ⁇ 1 taking account of the intake air amount at the high flow-rate side in the range 21, and thereby it is possible to suppress a decrease in the intake air amount of the compressor impeller 100.
  • the blade angle ⁇ 2 of the tip side ends 14E of the leading edges 14LE of the second blades 14 is greater than the blade angle ⁇ 1 of the tip-side ends 12E of the leading edges 12LE of the first blades 12.
  • the blade angle ⁇ 2 of the tip side ends 14E of the leading edges 14LE of the second blades 14 is greater than the blade angle ⁇ 1 of the tip-side ends 12E of the leading edges 12LE of the first blades 12 by 5 degrees or more.
  • rotating stall of a compressor impeller is likely to occur in a region on the tip side of the leading edge of a blade.
  • the blade angle ⁇ 2 of the tip side ends 14E of the leading edges 14LE of the second blades 14 being greater than the blade angle ⁇ 1 of the tip side ends 12E of the leading edges 12LE of the first blades 12 as described above, it is possible to suppress rotating stall effectively.
  • the blade angle ⁇ 2 of the hub side ends 14A of the leading edges 14LE of the second blades 14 is equal to the blade angle ⁇ 1 of the hub side ends 12A of the leading edges 12LE of the first blades 12.
  • rotating stall of a compressor impeller is likely to occur in the tip-side region of a blade.
  • the blade angle ⁇ 2 of the leading edge LE of the second blade 14 at the hub-side end 14A is greater than the blade angle ⁇ 1 of the leading edge 12LE of each blade 12 at the hub-side end 12A, the effect to suppress rotating stall is relatively small.
  • configuring the second blades 14 to have a large blade angle ⁇ 2 matched to the small flow-rate side in a broad range in the radial direction of the compressor impeller 100 may lead to a decrease in the intake air amount of the compressor impeller 100.
  • the blade angle ⁇ 2 of the leading edge 14LE of the second blade 14 is greater than the blade angle ⁇ 1 of the leading edge LE of the first blade 12 in the range w1 from a predetermined position P1 of not less than 50% of the blade height 'h' of the second blade 14 in the radial direction of the compressor impeller 100 (e.g.
  • rotating stall of a compressor impeller is likely to occur in the tip-side region of the leading edge of a blade.
  • the angle ⁇ 2 of the leading edge LE of the second blade 14 at the hub-side end is greater than the blade angle ⁇ 1 of the leading edge 12LE of the first blade at the hub-side end, the effect to suppress rotating stall is relatively small.
  • configuring the second blades 14 so that the leading edges 14 have a large blade angle ⁇ 2 matched to the small flow-rate side in a broad range in the radial direction of the compressor impeller 100 may lead to a decrease in the intake air amount of the compressor impeller 100.
  • the blade angle ⁇ 2 of the leading edge 14LE of the second blade 14 being greater than the blade angle ⁇ 1 of the leading edge LE of the first blade 12 in the range w1 from the predetermined position P1 of not less than 50% of the blade height h of the second blade 14 in the radial direction of the compressor impeller 100 to the tip side end 14E, and being equal to the blade angle ⁇ 1 of the leading edge LE of the first blade 12 in the range w2 from the hub side end 14A of the second blade 14 in the radial direction of the compressor impeller 100 to the predetermined position PI, it is possible to impair uniform propagation and development of the rotating stall while suppressing a decrease in the intake air amount of the compressor impeller 100.
  • the first blade 12 and the second blade 14 have different shapes only in the upstream region of the reference position P2 in the axial direction of the compressor impeller 100, and have the same shape in the downstream region of the reference position P2 in the axial direction of the compressor impeller 100.
  • the curve of a blade and the blade angle of the trailing edge of a blade have a great impact on the blade element performance, and thus the plurality of blades 4 should have a uniform shape on the trailing edge side. That is, preferably, the shape of the blade 12 at the side of the trailing edge 12TE and the shape of the blade 14 at the side of the trailing edge 14TE are the same.
  • the first blade 12 and the second blade 14 have different shapes only at the side of the leading edge where the shape is likely to contribute to improvement of rotating stall (the shape in the upstream region of the reference position P2 in the axial direction of the compressor impeller 100), and have the same shape at the side of the trailing edge where the shape is less likely to contribute to improvement of rotating stall and more likely to have an impact on the blade element performance (the shape in the downstream region of the reference position P2 in the axial direction of the compressor impeller 100). Accordingly, it is possible to suppress rotating stall while suppressing a decrease in the blade element performance, and thus it is possible to improve the performance of the compressor impeller 100 effectively.
  • the above reference position P2 is upstream of an intersection P3 (throat position of the second blade) between the suction surface 14S of the second blade 2 and a perpendicular line to the suction surface 14S of the second blade 14 from the tip-side end of the leading edge of the blade 4 next to the suction surface 14S of the second blade 4 (the tip side end 12E of the leading edge 12LE of the first blade 12 in the embodiment shown in the drawings).
  • the manufacturing method may include a first blade forming step of forming the plurality of first blades 12 having the same shape, and a second blade forming step of forming at least one second blade 14 by performing a bending process only on a portion 12P (see FIG. 3 ) on the tip side and on the leading edge side of a part of the first blades 12 formed in the first blade forming step so as to curve smoothly toward the pressure surface side in an arc shape.
  • the second blades 14 it is possible to form the second blades 14 by merely performing a bending process on the first blades 12 formed via the first blade forming step, and thus it is possible to manufacture the compressor impeller 100 easily.
  • the first blade 12 and the second blade 12 have different shapes only in the upstream region of the reference position P2 in the axial direction of the compressor impeller 100, and have the same shape in the downstream region of the reference position P2 in the axial direction of the compressor impeller 100.
  • the present invention is not limited to this embodiment.
  • the second blade 14 may have a different shape from the first blade 12 in the entire range of the second blade 14 in the axial direction of the compressor impeller 100. Also in this configuration, it is sufficient if, when comparing the blade angle ⁇ 1 of the leading edge 12LE of the first blade 12 to the blade angle ⁇ 2 of the leading edge 14LE of the second blade 14 at the same position with respect to the radial direction of the compressor impeller 100, at least in a partial range w1 in the radial direction of the compressor impeller 100, the blade angle ⁇ 1 of the leading edge LE of the first blade 12 is different from the blade angle ⁇ 2 of the leading edge 14LE of the second blade 14.
  • the blade angle ⁇ 1 of the leading edge LE of the first blade 12 is different from the blade angle ⁇ 2 of the leading edge 14LE of the second blade 14.
  • the embodiment shown in FIG. 4 it is possible to differentiate the blade angle ⁇ 1 of the first blade 12 from the blade angle ⁇ 2 of the second blade 14 while suppressing a change in the throat width S between the second blade 14 and the blade 4 next to the suction surface 14S of the second blade 14.
  • the embodiment shown in FIG. 4 is more preferable than the embodiment shown in FIG. 9 .
  • the compressor impeller 100 includes a single blade group 6 (which includes a plurality of blades 4 arranged at intervals in the circumferential direction on the outer peripheral surface 2a of the hub 2, and in which the blades 4 are aligned such that the hub-side ends 4A of the leading edges of the respective blades 4 are on the same circle C1 centered at the rotational axis O of the compressor impeller).
  • the compressor impeller 100 may include a plurality of blade groups.
  • the compressor impeller 100 (100B) includes two blade groups: a full blade group 6f and a splitter blade group 6s.
  • the full blade group 6f includes a plurality of full blades 4f disposed at intervals in the circumferential direction on the outer peripheral surface 2a of the hub 2.
  • the hub-side ends 4Af of the leading edges of the respective full blades 4f are aligned on the same circle Cf centered at the rotational axis O of the compressor impeller.
  • the splitter blade group 6s includes a plurality of splitter blades 4s disposed at intervals in the circumferential direction on the outer peripheral surface 2a of the hub 2.
  • the splitter blades 4s have a shorter blade length than the full blades 4f, and each of the plurality of splitter blades 4s is disposed between two adjacent full blades 4f.
  • the hub-side ends 4As of the leading edges of the plurality of splitter blades 4s are aligned on the same circle Cs centered at the rotational axis O of the compressor impeller 100.
  • the hub-side ends 4As of the leading edges of the plurality of splitter blades 4s are disposed downstream of the hub-side ends 4Af of the leading edges of the plurality of full blades 4f. That is, the circle Cs has a greater radius than the circle Cf, and is positioned downstream of the circle Cf with respect to the intake direction of the compressor impeller 100.
  • the invention according to the blade group 6 of the compressor impeller 100 (100A) described with reference to FIGs. 1 to 9 may be applied only to the full blade group 6f as shown in FIG. 12 , or only to the splitter blade group 6s as shown in FIG. 13 , or to both of the full blade group 6f and the splitter blade group 6s as shown in FIG. 14 .
  • the plurality of full blades 4f constituting the full blade group 6f includes at least one first blade 12f, and at least one second blade 14f having a different shape from the first blade 12f. Furthermore, when comparing the blade angle ⁇ 1f of the leading edge 12LEf of the first blade 12f to the blade angle ⁇ 2f of the leading edge 14LEf of the second blade 14f at the same position with respect to the radial direction of the compressor impeller 100, at least in a partial range (see the range w1 in FIG. 3 ) in the radial direction of the compressor impeller 100, the blade angle ⁇ 1f of the leading edge 21LEf of the first blade 12f is different from the blade angle ⁇ 2f of the leading edge 14LEf of the second blade 14f.
  • the plurality of splitter blades 4 constituting the splitter blade group 6s includes at least one first blade 12s, and at least one second blade 14s having a different shape from the first blade 12s. Furthermore, when comparing the blade angle ⁇ 1s of the leading edge 12LEs of the first blade 12s to the blade angle ⁇ 2s of the leading edge 14LEs of the second blade 14s at the same position with respect to the radial direction of the compressor impeller 100, at least in a partial range (see the range w1 in FIG. 3 ) in the radial direction of the compressor impeller 100, the blade angle ⁇ 1s of the leading edge 21LEs of the first blade 12s is different from the blade angle ⁇ 2s of the leading edge 14LEs of the second blade 14s.
  • the plurality of full blades 4f constituting the full blade group 6f includes at least one first blade 12f, and at least one second blade 14f having a different shape from the first blade 12f. Furthermore, when comparing the blade angle ⁇ 1f of the leading edge 12LE of the first blade 12f to the blade angle ⁇ 2f of the leading edge 14LEf of the second blade 14f at the same position with respect to the radial direction of the compressor impeller 100, at least in a partial range (see the range w1 in FIG.
  • the blade angle ⁇ 1f of the leading edge 21LEf of the first blade 12f is different from the blade angle ⁇ 2f of the leading edge 14LEf of the second blade 14f.
  • the plurality of splitter blades 4s constituting the splitter blade group 6s includes at least one first blade 12s, and at least one second blade 14s having a different shape from the first blade 12s. Furthermore, when comparing the blade angle ⁇ 1s of the leading edge 12LEs of the first blade 12s to the blade angle ⁇ 2s of the leading edge 14LEs of the second blade 14s at the same position with respect to the radial direction of the compressor impeller 100, at least in a partial range (see the range w1 in FIG. 3 ) in the radial direction of the compressor impeller 100, the blade angle ⁇ 1s of the leading edge 21LEs of the first blade 12s is different from the blade angle ⁇ 2s of the leading edge 14LEs of the second blade 14s.
  • centrifugal compressor is described as an example in the above embodiment, the present invention is not limited to a centrifugal compressor and may be applied to an axial-flow compressor or a mixed-flow compressor, for instance.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
EP16884910.7A 2016-01-14 2016-01-14 Verdichterlaufrad und verfahren zur herstellung davon Active EP3369938B1 (de)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
PCT/JP2016/050923 WO2017122307A1 (ja) 2016-01-14 2016-01-14 圧縮機インペラ及びその製造方法

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EP3369938A1 true EP3369938A1 (de) 2018-09-05
EP3369938A4 EP3369938A4 (de) 2018-12-05
EP3369938B1 EP3369938B1 (de) 2019-12-04

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US (1) US20180266442A1 (de)
EP (1) EP3369938B1 (de)
JP (1) JP6559805B2 (de)
CN (1) CN108603513B (de)
WO (1) WO2017122307A1 (de)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2020251448A1 (en) * 2019-06-13 2020-12-17 Scania Cv Ab Centrifugal compressor impeller for a charging device of an internal combustion engine

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Publication number Priority date Publication date Assignee Title
US11525457B2 (en) * 2017-10-11 2022-12-13 Mitsubishi Heavy Industries Engine & Turbocharger, Ltd. Impeller for centrifugal turbomachine and centrifugal turbomachine
US11506059B2 (en) 2020-08-07 2022-11-22 Honeywell International Inc. Compressor impeller with partially swept leading edge surface
EP3951188B1 (de) * 2020-08-07 2024-05-29 Honeywell International Inc. Verdichterlaufrad mit teilweise überströmter vorderkante

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JPS58128243A (ja) * 1982-01-27 1983-07-30 Nippon Light Metal Co Ltd 羽根車の製造方法
JPH0222700U (de) * 1988-07-29 1990-02-15
JP4075264B2 (ja) * 2000-01-28 2008-04-16 セイコーエプソン株式会社 軸流ファン、遠心力ファン、およびこれらを用いた電子機器
JP3794543B2 (ja) * 2000-03-06 2006-07-05 株式会社石垣 遠心圧縮機
JP2003214390A (ja) * 2002-01-25 2003-07-30 Nippon Densan Corp ファンモータ
US8167540B2 (en) * 2008-01-30 2012-05-01 Hamilton Sundstrand Corporation System for reducing compressor noise
EP2623793B1 (de) * 2012-02-02 2016-08-10 MTU Aero Engines GmbH Strömungsmaschine mit Schaufelgitter
JP6109548B2 (ja) * 2012-11-30 2017-04-05 三菱重工業株式会社 圧縮機
JP5980671B2 (ja) 2012-12-18 2016-08-31 三菱重工業株式会社 回転機械

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2020251448A1 (en) * 2019-06-13 2020-12-17 Scania Cv Ab Centrifugal compressor impeller for a charging device of an internal combustion engine

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JP6559805B2 (ja) 2019-08-14
EP3369938B1 (de) 2019-12-04
JPWO2017122307A1 (ja) 2018-07-05
CN108603513B (zh) 2020-08-25
CN108603513A (zh) 2018-09-28
WO2017122307A1 (ja) 2017-07-20
US20180266442A1 (en) 2018-09-20
EP3369938A4 (de) 2018-12-05

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