US20180266442A1 - Compressor impeller and method for manufacturing same - Google Patents

Compressor impeller and method for manufacturing same Download PDF

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Publication number
US20180266442A1
US20180266442A1 US15/779,114 US201615779114A US2018266442A1 US 20180266442 A1 US20180266442 A1 US 20180266442A1 US 201615779114 A US201615779114 A US 201615779114A US 2018266442 A1 US2018266442 A1 US 2018266442A1
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United States
Prior art keywords
blade
blades
compressor impeller
angle
leading edges
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Abandoned
Application number
US15/779,114
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English (en)
Inventor
Kenichiro Iwakiri
Isao Tomita
Seiichi Ibaraki
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Mitsubishi Heavy Industries Engine and Turbocharger Ltd
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Mitsubishi Heavy Industries Engine and Turbocharger Ltd
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Assigned to Mitsubishi Heavy Industries Engine & Turbocharger, Ltd. reassignment Mitsubishi Heavy Industries Engine & Turbocharger, Ltd. ASSIGNMENT OF ASSIGNORS INTEREST (SEE DOCUMENT FOR DETAILS). Assignors: IBARAKI, SEIICHI, IWAKIRI, KENICHIRO, TOMITA, ISAO
Publication of US20180266442A1 publication Critical patent/US20180266442A1/en
Abandoned legal-status Critical Current

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    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D29/00—Details, component parts, or accessories
    • F04D29/26—Rotors specially for elastic fluids
    • F04D29/28—Rotors specially for elastic fluids for centrifugal or helico-centrifugal pumps for radial-flow or helico-centrifugal pumps
    • F04D29/284—Rotors specially for elastic fluids for centrifugal or helico-centrifugal pumps for radial-flow or helico-centrifugal pumps for compressors
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D29/00—Details, component parts, or accessories
    • F04D29/26—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 high-pressure 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.
  • 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 includes: a hub; and a blade group including a plurality of blades arranged along a circumferential direction on an outer peripheral surface of the hub, the blade group being configured such that hub-side ends of leading edges of the respective blades are aligned on the same circle.
  • the plurality of blades include at least one first blade and at least one second blade having a different shape from the at least one first blade, and, when comparing a blade angle of a leading edge of the at least one first blade to a blade angle of a leading edge of the at least one second blade at the same position in a radial direction of the compressor impeller, the blade angle of the leading edge of the at least one first blade is different from the blade angle of the leading edge of the at least one second blade, at least in a partial range in the radial direction of the compressor impeller.
  • the blade angle of the leading edge of the first blade is different from the blade angle of the leading edge of the second blade. Accordingly, for the plurality of blades arranged so that the hub-side ends of the leading edges align on the same circle, it is possible to differentiate the stall characteristics between the first blade and the second blade.
  • the at least one first blade includes a plurality of first blades
  • the at least one second blade includes a plurality of second blades
  • the number of the second blades in the blade group is smaller than the number of the first blades in the blade group
  • the plurality of second blades include a pair of second blades between which the first blade is not disposed.
  • the second blades relatively fewer than the first blades and having different stalling characteristics from the first blades are aligned continuously in the circumferential direction of the compressor impeller, and thus it is possible to enhance the above effect to impair uniform propagation and development of rotating stall.
  • the number of the second blades in the blade group is smaller than the number of the first blades in the blade group, and, when comparing the blade angle of the leading edges of the first blades to the blade angle of the leading edges of the second blades at the same position in the radial direction of the compressor impeller, the blade angle of the leading edges of the second blades is greater than the blade angle of the leading edges of the first blades at least in a partial range in the radial direction of the compressor impeller.
  • the blade angle of the leading edges of the relatively large number of first blades is a relatively small blade angle taking into account the intake air amount of the high-flow rate side
  • the blade angle of the leading edges of the relatively small number of second blades is a relatively large blade angle matched to the small flow rate side (less likely to cause stalling even at a low flow rate).
  • the blade angle of the tip-side ends of the leading edges of the second blades is greater than the blade angle of the tip-side ends of the leading edges of the first blades.
  • rotating stall of the compressor impeller is likely to occur in a region on the tip side of a blade.
  • the blade angle of the tip-side ends of the leading edges of the second blades is greater than the blade angle of the tip-side ends of the leading edges of the first blades by five degrees or more.
  • the blade angle of hub-side ends of the leading edges of the second blades is equal to the blade angle of hub-side ends of the leading edges of the first blades.
  • rotating stall of the compressor impeller is likely to occur in the tip-side region of a blade.
  • the angle of the leading edge of the second blade at the hub-side end is greater than the blade angle of the leading edge of the first blade at the hub-side end, the effect to suppress rotating stall is relatively small.
  • configuring the second blades to have a large blade angle matched to the small flow-rate side in a broad range in the radial direction of the compressor impeller may lead to a decrease in the intake air amount of the compressor impeller.
  • the blade angle of the leading edges of the second blades on the tip side end being greater than the blade angle of the leading edges of the first blades on the tip side end
  • the blade angle of the leading edges of the second blades on the hub-side end being equal to the blade angle of the leading edges of the first blades on the hub-side end as in the above (6)
  • the blade angle of the leading edges of the second blades when comparing the blade angle of the leading edges of the first blades to the blade angle of the leading edges of the second blades at the same position in the radial direction of the compressor impeller, is greater than the blade angle of the leading edges of the first blades in a range to the tip-side ends from a predetermined position of not less than 50% of a blade height of the second blades in the radial direction of the compressor impeller, and is equal to the blade angle of the leading edges of the first blades in a range to the predetermined position from the hub-side ends of the second blades in the radial direction of the compressor impeller.
  • the first blades and the second blades have different shapes only in an upstream region of a reference position in an axial direction of the compressor impeller, and have the same shape in a downstream region of the reference position in the axial direction of the compressor impeller.
  • the first blade and the second blade 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 in the axial direction of the compressor impeller), 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 in the axial direction of the compressor impeller). 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 effectively.
  • the reference position is a position upstream of an intersection between a suction surface of the second blade and a perpendicular line to the suction surface of the second blade from the tip-side end of the leading edge of the blade next to the suction surface of the second blade.
  • a method for manufacturing the compressor impeller according to any one of the above (1) to (9) includes: a first blade forming step of forming a plurality of first blades having the same shape; and a second blade forming step of forming at least one second blade by performing a bending process on a leading-edge side portion of a part of the first blades formed in the first blade forming step.
  • a compressor impeller and a method for manufacturing the same, whereby it is possible to suppress rotating stall with a simplified configuration.
  • FIG. 1 is an axial-directional view of a compressor impeller 100 ( 100 A) according to an embodiment.
  • FIG. 2 is a meridional cross-sectional view of a part of a compressor impeller 100 ( 100 A) according to an embodiment, taken along the axial direction.
  • 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.
  • the line indicating each blade 4 is the camber line connecting the middle points of the suction surface and the pressure surface of the blade 4 .
  • FIG. 5 is a blade-row expanded view schematically showing the positional relationship of the plurality of blades 4 on the hub side.
  • the line indicating each blade 4 is the camber line connecting the middle points of the suction surface and the pressure surface of the blade 4 .
  • FIG. 6 is a diagram schematically showing a rotating stall state in a comparative embodiment.
  • the line indicating each blade 4 is the camber line connecting the middle points of the suction surface and the pressure surface of the blade 4 .
  • FIG. 7 is a diagram schematically showing a rotating stall state in an embodiment.
  • the line indicating each blade 4 is the camber line connecting the middle points of the suction surface and the pressure surface of the blade 4 .
  • FIG. 8 is a view showing comparison of surge lines in an embodiment and a comparative embodiment.
  • FIG. 9 is a schematic diagram for describing another example of the shape of the first blade 12 and the second blade 14 .
  • the line indicating each blade 4 is the camber line connecting the middle points of the suction surface and the pressure surface of the blade 4 .
  • FIG. 10 is an axial-directional view of a compressor impeller 100 ( 100 B) according to an embodiment.
  • FIG. 11 is a meridional cross-sectional view of a part of a compressor impeller 100 ( 100 B) according to an embodiment, taken along the axial direction.
  • FIG. 12 is a blade-row expanded view schematically showing an example of the positional relationship of a plurality of full blades 4 f and a plurality of splitter blades 4 s on the tip side.
  • the line indicating each blade 4 ( 4 f , 4 s ) is the camber line connecting the middle points of the suction surface and the pressure surface of the blade 4 .
  • FIG. 13 is a blade-row expanded view schematically showing an example of the positional relationship of a plurality of full blades 4 f and a plurality of splitter blades 4 s on the tip side.
  • the line indicating each blade 4 ( 4 f , 4 s ) is the camber line connecting the middle points of the suction surface and the pressure surface of the blade 4 ( 4 f , 4 s ).
  • FIG. 14 is a blade-row expanded view schematically showing an example of the positional relationship of a plurality of full blades 4 f and a plurality of splitter blades 4 s on the tip side.
  • the line indicating each blade 4 ( 4 f , 4 s ) is the camber line connecting the middle points of the suction surface and the pressure surface of the blade 4 ( 4 f , 4 s ).
  • FIG. 15 is a partial meridional cross-sectional view of a compressor impeller 100 according to an embodiment, taken along the axial direction.
  • 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 ( 100 A) according to an embodiment.
  • FIG. 2 is a meridional cross-sectional view of a part of a compressor impeller 100 ( 100 A) 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 2 a of the hub 2 .
  • the blades 4 are aligned such that the hub-side ends 4 A of the leading edges of the respective blade 4 are on the same circle C 1 centered at the rotational axis O of the compressor impeller.
  • the blade group 6 is configured such that the hub-side ends 4 A 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 12 LE 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 12 LE to the trailing edge 12 TE 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 12 LE 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 12 LE 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 2 a 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 14 LE 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 w 1 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 14 LE of the second blade 14 .
  • blade angle ⁇ refers to the angle ⁇ (see FIG.
  • ⁇ tan - 1 ⁇ d ⁇ ( r ⁇ ⁇ ⁇ ) d ⁇ ⁇ m .
  • the at least one first blade 12 includes a plurality of first blades 12
  • 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
  • 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 14 LE 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 w 1 in the radial direction of the compressor impeller 100 , the blade angle ⁇ 2 of the leading edge 14 LE of the second blade 14 is greater than the blade angle ⁇ 1 of the leading edge 12 LE 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.
  • the leading edges 12 LE 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 14 E of the leading edges 14 LE of the second blades 14 is greater than the blade angle ⁇ 1 of the tip-side ends 12 E of the leading edges 12 LE of the first blades 12 .
  • the blade angle ⁇ 2 of the tip side ends 14 E of the leading edges 14 LE of the second blades 14 is greater than the blade angle ⁇ 1 of the tip-side ends 12 E of the leading edges 12 LE 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 14 E of the leading edges 14 LE of the second blades 14 being greater than the blade angle ⁇ 1 of the tip side ends 12 E of the leading edges 12 LE 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 14 A of the leading edges 14 LE of the second blades 14 is equal to the blade angle ⁇ 1 of the hub side ends 12 A of the leading edges 12 LE 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 14 A is greater than the blade angle ⁇ 1 of the leading edge 12 LE of each blade 12 at the hub-side end 12 A, 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 14 LE 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 w 1 from a predetermined position P 1 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 12 LE 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 14 LE 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 w 1 from the predetermined position P 1 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 14 E, and being equal to the blade angle ⁇ 1 of the leading edge LE of the first blade 12 in the range w 2 from the hub side end 14 A of the second blade 14 in the radial direction of the compressor impeller 100 to the predetermined position P 1 , 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 P 2 in the axial direction of the compressor impeller 100 , and have the same shape in the downstream region of the reference position P 2 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 12 TE and the shape of the blade 14 at the side of the trailing edge 14 TE 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 P 2 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 P 2 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 P 2 is upstream of an intersection P 3 (throat position of the second blade) between the suction surface 14 S of the second blade 2 and a perpendicular line to the suction surface 14 S of the second blade 14 from the tip-side end of the leading edge of the blade 4 next to the suction surface 14 S of the second blade 4 (the tip side end 12 E of the leading edge 12 LE 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 12 P (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 P 2 in the axial direction of the compressor impeller 100 , and have the same shape in the downstream region of the reference position P 2 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 .
  • 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 14 LE 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 14 S 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 2 a of the hub 2 , and in which the blades 4 are aligned such that the hub-side ends 4 A of the leading edges of the respective blades 4 are on the same circle C 1 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 ( 100 B) includes two blade groups: a full blade group 6 f and a splitter blade group 6 s.
  • the full blade group 6 f includes a plurality of full blades 4 f disposed at intervals in the circumferential direction on the outer peripheral surface 2 a of the hub 2 .
  • the hub-side ends 4 Af of the leading edges of the respective full blades 4 f are aligned on the same circle Cf centered at the rotational axis O of the compressor impeller.
  • the splitter blade group 6 s includes a plurality of splitter blades 4 s disposed at intervals in the circumferential direction on the outer peripheral surface 2 a of the hub 2 .
  • the splitter blades 4 s have a shorter blade length than the full blades 4 f , and each of the plurality of splitter blades 4 s is disposed between two adjacent full blades 4 f .
  • the hub-side ends 4 As of the leading edges of the plurality of splitter blades 4 s are aligned on the same circle Cs centered at the rotational axis O of the compressor impeller 100 .
  • the hub-side ends 4 As of the leading edges of the plurality of splitter blades 4 s are disposed downstream of the hub-side ends 4 Af of the leading edges of the plurality of full blades 4 f . 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 ( 100 A) described with reference to FIGS. 1 to 9 may be applied only to the full blade group 6 f as shown in FIG. 12 , or only to the splitter blade group 6 s as shown in FIG. 13 , or to both of the full blade group 6 f and the splitter blade group 6 s as shown in FIG. 14 .
  • the plurality of full blades 4 f constituting the full blade group 6 f includes at least one first blade 12 f , and at least one second blade 14 f having a different shape from the first blade 12 f . Furthermore, when comparing the blade angle ⁇ 1 f of the leading edge 12 LEf of the first blade 12 f to the blade angle ⁇ 2 f of the leading edge 14 LEf of the second blade 14 f at the same position with respect to the radial direction of the compressor impeller 100 , at least in a partial range (see the range w 1 in FIG.
  • the blade angle ⁇ 1 f of the leading edge 21 LEf of the first blade 12 f is different from the blade angle ⁇ 2 f of the leading edge 14 LEf of the second blade 14 f.
  • the plurality of splitter blades 4 constituting the splitter blade group 6 s includes at least one first blade 12 s , and at least one second blade 14 s having a different shape from the first blade 12 s . Furthermore, when comparing the blade angle ⁇ 1 s of the leading edge 12 LEs of the first blade 12 s to the blade angle ⁇ 2 s of the leading edge 14 LEs of the second blade 14 s at the same position with respect to the radial direction of the compressor impeller 100 , at least in a partial range (see the range w 1 in FIG.
  • the blade angle ⁇ 1 s of the leading edge 21 LEs of the first blade 12 s is different from the blade angle ⁇ 2 s of the leading edge 14 LEs of the second blade 14 s.
  • the plurality of full blades 4 f constituting the full blade group 6 f includes at least one first blade 12 f , and at least one second blade 14 f having a different shape from the first blade 12 f . Furthermore, when comparing the blade angle ⁇ 1 f of the leading edge 12 LE of the first blade 12 f to the blade angle 62 f of the leading edge 14 LEf of the second blade 14 f at the same position with respect to the radial direction of the compressor impeller 100 , at least in a partial range (see the range w 1 in FIG.
  • the blade angle 61 f of the leading edge 21 LEf of the first blade 12 f is different from the blade angle ⁇ 2 f of the leading edge 14 LEf of the second blade 14 f .
  • the plurality of splitter blades 4 s constituting the splitter blade group 6 s includes at least one first blade 12 s , and at least one second blade 14 s having a different shape from the first blade 12 s .
  • the blade angle ⁇ 1 s of the leading edge 12 LEs of the first blade 12 s is different from the blade angle ⁇ 2 s of the leading edge 14 LEs of the second blade 14 s.
  • 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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US15/779,114 2016-01-14 2016-01-14 Compressor impeller and method for manufacturing same Abandoned US20180266442A1 (en)

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EP3951188A1 (en) * 2020-08-07 2022-02-09 Honeywell International Inc. Compressor impeller with partially swept leading edge surface
US11506059B2 (en) 2020-08-07 2022-11-22 Honeywell International Inc. Compressor impeller with partially swept leading edge surface

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US11525457B2 (en) * 2017-10-11 2022-12-13 Mitsubishi Heavy Industries Engine & Turbocharger, Ltd. Impeller for centrifugal turbomachine and centrifugal turbomachine
SE1950700A1 (en) * 2019-06-13 2020-12-01 Scania Cv Ab Centrifugal Compressor Impeller for a Charging Device of an Internal Combustion Engine

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US20130202444A1 (en) * 2012-02-02 2013-08-08 Mtu Aero Engines Gmbh Blade cascade and turbomachine

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP3951188A1 (en) * 2020-08-07 2022-02-09 Honeywell International Inc. Compressor impeller with partially swept leading edge surface
US11506059B2 (en) 2020-08-07 2022-11-22 Honeywell International Inc. Compressor impeller with partially swept leading edge surface

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EP3369938A4 (en) 2018-12-05
WO2017122307A1 (ja) 2017-07-20
CN108603513A (zh) 2018-09-28
JPWO2017122307A1 (ja) 2018-07-05
CN108603513B (zh) 2020-08-25
EP3369938B1 (en) 2019-12-04
EP3369938A1 (en) 2018-09-05
JP6559805B2 (ja) 2019-08-14

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