US3305166A - Centrifugal compressor - Google Patents

Centrifugal compressor Download PDF

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Publication number
US3305166A
US3305166A US433670A US43367065A US3305166A US 3305166 A US3305166 A US 3305166A US 433670 A US433670 A US 433670A US 43367065 A US43367065 A US 43367065A US 3305166 A US3305166 A US 3305166A
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Prior art keywords
impeller
hub
blades
blade
shroud
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Expired - Lifetime
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US433670A
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William S Castle
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Motors Liquidation Co
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Motors Liquidation Co
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Priority to US433670A priority Critical patent/US3305166A/en
Priority to GB4760/66A priority patent/GB1073490A/en
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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
    • F04D29/285—Rotors specially for elastic fluids for centrifugal or helico-centrifugal pumps for radial-flow or helico-centrifugal pumps for compressors the compressor wheel comprising a pair of rotatable bladed hub portions axially aligned and clamped together

Definitions

  • This invention relates generally to a centrifugal compressor and more particularly to a centrifugal compressor having a rotor comprising an impeller with individually mounted vanes and a separate inducer.
  • a possible solution to the problem of providing these curved radial walls is to design the hub so that its circumferential surface forms the radial contour. This solution is objectionable because too much weight is added to the hub.
  • Another possible solution is to 1 provide some sort of shroud or annulus to establish the radial wall. The second solution is objectionable because assembly of the shroud to the blades and hub would require a segmented type shroud which becomes unduly cumbersome and complicated.
  • Another object is to provide a centrifugal compressor rotor having separate inducer and impeller portions and in which the impeller portion has its vanes separably secured to a hub.
  • Another object is to provide a centrifugal compressor rotor in which the contour of the wall directing air flow through the compressor is established simply and without adding undue weight to the structure.
  • Another object is to provide a centrifugal compressor rotor having an impeller with separate lblades attached to a hub and in which the walls between the blades which direct air radially outwardly are provided in a unique manner and without adding undue weight to the structure.
  • FIGURE 1 is an axial sectional view of a portion of a gas turbine engine including a centrifugal compressor in accordance with the invention.
  • FIGURE 2 is a section taken substantially along the line 22 of FIGURE 1 and looking in the direction of the arrows.
  • FIGURE 3 is a perspective view of the compressor rotor made in accordance with the invention shown in FIGURE 1. It has been partially broken away for clarity.
  • FIGURE 4 is a perspective view of a single impeller blade shown in FIGURE 3.
  • FIGURE 1 a portion of a gas turbine engine is shown which includes an annular inlet 12 and an annular wall 14.
  • the inlet 12 and the wall 14 house a compressor rotor shown generally at 13.
  • the annular wall 14 is mounted on a tubular housing 16 which has an internal shoulder 17 to support a collar 18.
  • a Z-shaped 3385,15 Patented Feb. 21, 1967 ring 20 has its greater diameter mounted within the tubular housing 16 above the collar 18.
  • a split ring retainer 22 holds collar 18 and ring 20 against shoulder 17.
  • the collar 18 has an integral portion 19 of reduced diameter which provides a bearing support for the compressor rotor 13.
  • the compressor rotor which is shown more clearly in FIGURE 3 comprises a separate impeller and inducer, 23 and 36 respectively.
  • the impeller 23 has a hub 24 provided with a plurality of axial dovetail slots 26 equally spaced about its circumference.
  • a plurality of blades 28 have their stalks 30 shaped to fit within the axial slots 26.
  • Each blade has webs 32 projecting circumferentially from each side of the blade.
  • the webs 32 are arcuate in cross section and extend from the leading edge of the blade 28 adjacent the hub 24 to the trailing edge of the blade 28 at its tip. When all of the blades are assembled in the hub 24, each web 32 abuts a second web projecting from an adjacent blade. The abutting webs thus form a wall extending between two adjacent blades.
  • a sealing ring 35 with an annular flange which is fixed to plate 34 has its outer surface grooved to form a labyrinth seal with the Z-shaped ring 20.
  • the lower end of the hub 24 also carries an L-shaped collar 42 radially inwardly of the ring 35.
  • An inducer 36 comprising a disc 38 with a plurality of radially extending integral vanes 40 is disposed above the impeller 23 and coaxially therewith.
  • the inducer 36 is shown indexed with respect to the impeller 23; however, it may be aligned.
  • the L-shaped collar 42, the hub 24, and the disc 38 are connected for simultaneous rotation by a pair of drive pins 44 spaced apart.
  • the combination of inducer and impeller thus assembled is connected to the turbine shaft 46 by a hollow tiebolt 48.
  • the tiebolt 48 has an upper annular flange 50* with an outer serrated circumferential edge 52.
  • the disc 38 carries a pair of lock pins 54 which engages the serrated edge 52 on the tiebolt flange 50. These lock pins 54 are spaced 180 apart and are biased upwardly by springs 56.
  • the tiebolt 48 has external threads on its lower end which engage internal threads on the upper portion of the shaft 46 concentrically disposed within tubular housing 16.
  • the upper circumferential edge of shaft 46 is serrated and mates with serrations 47 on the lower circumferential edge of the L-shaped collar 42.
  • Torque is transmitted from shaft 46 to impeller 23 and inducer 13 through collar 42 and drive pins '44.
  • the axial portion of the L-shaped collar 42 forms the inner race of a ball bearing 57 whose outer race abuts the reduced portion 19 of collar 18 which is supported by tubular housing 16.
  • the compressor rotor thus connected is disposed between the annular inlet 12 and the wall 14 and is journaled in the wall 14.
  • Above the compressor rotor is a projectile shaped housing 58 which is suspended concentrically within the axial inlet 12 by struts 60.
  • Various accessories 61 for the gas turbine are supported within housing 5 8 and are operatively connected to the shaft 46 by an accessory drive shaft 62 which is splined to an internal tubular portion 64 on tiebolt 48.
  • air flow through the compressor will be through an annular channel formed by an outer wall comprising the annular inlet 12 and by an inner wall comprising the outer surface of projectile housing 58 which is contiguous with the outer circumferential surface of the disc 38, which in turn is contiguous with the u) walls formed by the circumferentially extending webs 32 on the vanes 28.
  • centrifugal compressor which includes an impeller having separably mounted blades with air directing walls provided therebetween in a unique manner and without adding undue weight to the assembly.
  • a centrifugal compressor comprising an annular shroud
  • impeller rotatably mounted in said shroud, said impeller comprising a hub
  • said inducer comprising a disc with radially extending blades
  • annular flow channel through said compressor, said flow channel being bounded by an outer wall comprising said shroud and an inner wall comprising the outer surfaces of said disc and said Walls.
  • a centrifugal compressor comprising an annular shroud
  • impeller rotatably mounted in said shroud, said impeller comprising a hub
  • an inducer rotatably mounted in said shroud coaxially with said impeller, said inducer comprising a disc with radially extending blades,
  • a centrifugal compressor comprising an annular shroud
  • impeller rotatably mounted in said shroud, said impeller comprising a hub
  • an inducer rotatably mounted in said shroud coaxially with said impeller, said inducer comprising a disc with radially extending blades,
  • annular flow channel through said compressor, said flow channel being bounded by an outer wall comprising said shroud and an inner wall comprising a portion of said disc and said radially extending walls.
  • a centrifugal compressor comprising an annular shroud
  • impeller rotatably mounted in said shroud, said impeller comprising a hub
  • each of said walls comprising at least one web extending circumferentially from one of said adjacent blades to the other of said adjacent blades
  • an inducer rotatably mounted in said shroud coaxially with said impeller, said inducer comprising a disc with radial blades,
  • annular flow channel through said compressor, said flow channel being bounded by an outer wall comprising said shroud and an inner wall comprising a portion of said disc and said radially extending walls.

Description

Feb. 21, 1967 w, s, CASTLE 3,305,166
CENTRIFUGAL COMPRES SOR Filed Feb. 18, 1965 2 gheets-Sheet 1 58 /Z W W 0 L n A! W M a l if u I f6 2; {/5 5 57 z *wl a L 2'8 2:?
{'9 INVENTOR.
(fly/aim: 5. (as/7e ATTORNEY Feb. 21, 1967 w, s. CASTLE CENTRIFUGAL COMPRESSOR Filed Feb. 18, 1965 2 Sheets-Sheet 2 m m w m United States Patent Ofiice 3,305,166 CENTRIFUGAL COMPRESSGR William S. Castle, Speedway, Ind., assignor to General Motors Corporation, Detroit, Mich., a corporation of Delaware Filed Feb. 18, 1965, Ser. No. 433,670 4 Claims. (Cl. 230-127) This invention relates generally to a centrifugal compressor and more particularly to a centrifugal compressor having a rotor comprising an impeller with individually mounted vanes and a separate inducer.
It has been a standard practice for some time to design a composite centrifugal compressor having the inducer and impeller separate. It is likewise well-known in the art to design a bladed rotor having a separate hub or disc with axial grooves and a plurality of vanes separably secured in the grooves. This type of bladed rotor, even though appreciably less expensive than a rotor machined from a solid block or a cast rotor, however, has not enjoyed widespread use in a centrifugal compressor because of the need for a curved radial wall between adjacent radial compressor blades to direct the incoming air radially outwardly as it flows through the compressor. A possible solution to the problem of providing these curved radial walls is to design the hub so that its circumferential surface forms the radial contour. This solution is objectionable because too much weight is added to the hub. Another possible solution is to 1 provide some sort of shroud or annulus to establish the radial wall. The second solution is objectionable because assembly of the shroud to the blades and hub would require a segmented type shroud which becomes unduly cumbersome and complicated.
It is therefore, an object of this invention to provide a centrifugal compressor having a rotor which is light in weight and relatively inexpensive to manufacture.
Another object is to provide a centrifugal compressor rotor having separate inducer and impeller portions and in which the impeller portion has its vanes separably secured to a hub.
Another object is to provide a centrifugal compressor rotor in which the contour of the wall directing air flow through the compressor is established simply and without adding undue weight to the structure.
Another object is to provide a centrifugal compressor rotor having an impeller with separate lblades attached to a hub and in which the walls between the blades which direct air radially outwardly are provided in a unique manner and without adding undue weight to the structure.
Other objects and advantages of the invention will hereafter become more fully apparent from the following description of the annexed drawings which illustrate a preferred embodiment and wherein:
FIGURE 1 is an axial sectional view of a portion of a gas turbine engine including a centrifugal compressor in accordance with the invention.
FIGURE 2 is a section taken substantially along the line 22 of FIGURE 1 and looking in the direction of the arrows.
FIGURE 3 is a perspective view of the compressor rotor made in accordance with the invention shown in FIGURE 1. It has been partially broken away for clarity.
FIGURE 4 is a perspective view of a single impeller blade shown in FIGURE 3.
Referring now to FIGURE 1, a portion of a gas turbine engine is shown which includes an annular inlet 12 and an annular wall 14. The inlet 12 and the wall 14 house a compressor rotor shown generally at 13. The annular wall 14 is mounted on a tubular housing 16 which has an internal shoulder 17 to support a collar 18. A Z-shaped 3385,15 Patented Feb. 21, 1967 ring 20 has its greater diameter mounted within the tubular housing 16 above the collar 18. A split ring retainer 22 holds collar 18 and ring 20 against shoulder 17. The collar 18 has an integral portion 19 of reduced diameter which provides a bearing support for the compressor rotor 13. The compressor rotor which is shown more clearly in FIGURE 3 comprises a separate impeller and inducer, 23 and 36 respectively. The impeller 23 has a hub 24 provided with a plurality of axial dovetail slots 26 equally spaced about its circumference. A plurality of blades 28 have their stalks 30 shaped to fit within the axial slots 26. Each blade has webs 32 projecting circumferentially from each side of the blade. The webs 32 are arcuate in cross section and extend from the leading edge of the blade 28 adjacent the hub 24 to the trailing edge of the blade 28 at its tip. When all of the blades are assembled in the hub 24, each web 32 abuts a second web projecting from an adjacent blade. The abutting webs thus form a wall extending between two adjacent blades. No connection is provided between the abutting edges of the webs, in order to allow radial growth of the blades 28 without load transfer through the Webs 32. An annular backplate 34, however, is welded to the trailing edge of the hub 24 and the trailing edges of the vanes 28 to reduce air leakage past the unconnected edges of abutting webs 32. A sealing ring 35 with an annular flange which is fixed to plate 34 has its outer surface grooved to form a labyrinth seal with the Z-shaped ring 20. The lower end of the hub 24 also carries an L-shaped collar 42 radially inwardly of the ring 35. An inducer 36 comprising a disc 38 with a plurality of radially extending integral vanes 40 is disposed above the impeller 23 and coaxially therewith. The inducer 36 is shown indexed with respect to the impeller 23; however, it may be aligned. The L-shaped collar 42, the hub 24, and the disc 38 are connected for simultaneous rotation by a pair of drive pins 44 spaced apart.
The combination of inducer and impeller thus assembled is connected to the turbine shaft 46 by a hollow tiebolt 48. The tiebolt 48 has an upper annular flange 50* with an outer serrated circumferential edge 52. The disc 38 carries a pair of lock pins 54 which engages the serrated edge 52 on the tiebolt flange 50. These lock pins 54 are spaced 180 apart and are biased upwardly by springs 56. The tiebolt 48 has external threads on its lower end which engage internal threads on the upper portion of the shaft 46 concentrically disposed within tubular housing 16. The upper circumferential edge of shaft 46 is serrated and mates with serrations 47 on the lower circumferential edge of the L-shaped collar 42. Torque is transmitted from shaft 46 to impeller 23 and inducer 13 through collar 42 and drive pins '44. The axial portion of the L-shaped collar 42 forms the inner race of a ball bearing 57 whose outer race abuts the reduced portion 19 of collar 18 which is supported by tubular housing 16. The compressor rotor thus connected is disposed between the annular inlet 12 and the wall 14 and is journaled in the wall 14. Above the compressor rotor is a projectile shaped housing 58 which is suspended concentrically within the axial inlet 12 by struts 60. Various accessories 61 for the gas turbine are supported within housing 5 8 and are operatively connected to the shaft 46 by an accessory drive shaft 62 which is splined to an internal tubular portion 64 on tiebolt 48. As can be seen in FIGURE 1, air flow through the compressor will be through an annular channel formed by an outer wall comprising the annular inlet 12 and by an inner wall comprising the outer surface of projectile housing 58 which is contiguous with the outer circumferential surface of the disc 38, which in turn is contiguous with the u) walls formed by the circumferentially extending webs 32 on the vanes 28.
Thus it can be seen that I have invented a centrifugal compressor which includes an impeller having separably mounted blades with air directing walls provided therebetween in a unique manner and without adding undue weight to the assembly.
It should be understood, of course, that the foregoing disclosure relates to only a prefered embodiment of the invention and that it is intended to cover all changes and modifications of the example of the invention herein disclosed which are within the spirit and scope of the invention.
I claim:
1. A centrifugal compressor comprising an annular shroud,
an impeller rotatably mounted in said shroud, said impeller comprising a hub,
a plurality of circumferentially spaced blades individually mounted on said hub and extending radially therefrom,
a pair of radially arcuate webs extending circumferentially in opposite directions from each blade and extending radially from the leading edge of said blade adjacent said hub to the trailing edge of said blade adjacent its tip, said webs abutting webs extending from adjacent blades to form walls between said blade and said adjacent blades,
an inducer rotatably mounted in said shroud coaxially with said impeller,
said inducer comprising a disc with radially extending blades,
means to drivingly connect said inducer to said impeller,
and
an annular flow channel through said compressor, said flow channel being bounded by an outer wall comprising said shroud and an inner wall comprising the outer surfaces of said disc and said Walls.
2. A centrifugal compressor comprising an annular shroud,
an impeller rotatably mounted in said shroud, said impeller comprising a hub,
a plurality of circumferentially spaced blades individually mounted on said hub and extending radially therefrom,
a pair of radially arcuate webs extending circumferentially in opposite directions from each blade, said webs abutting webs extending from adjacent blades to form walls between said blade and said adjacent blades,
an inducer rotatably mounted in said shroud coaxially with said impeller, said inducer comprising a disc with radially extending blades,
means to drivingly connect said inducer to said impeller,
and
an annular flow channel through said compressor, said flow channel being bounded by an outer wall com- 4, prising said shroud and an inner wall comprising a portion of said disc and said walls. I
3. A centrifugal compressor comprising an annular shroud,
an impeller rotatably mounted in said shroud, said impeller comprising a hub,
a plurality of circumferentially spaced radial blades individually mounted on said hub,
at least one web extending circumferentially from each blade to form a radially extending wall between said blade and an adjacent blade,
an inducer rotatably mounted in said shroud coaxially with said impeller, said inducer comprising a disc with radially extending blades,
means to drivingly connect said inducer to said impeller, and
an annular flow channel through said compressor, said flow channel being bounded by an outer wall comprising said shroud and an inner wall comprising a portion of said disc and said radially extending walls.
4. A centrifugal compressor comprising an annular shroud,
an impeller rotatably mounted in said shroud, said impeller comprising a hub,
a plurality of circumferentially spaced radial blades individually mounted on said hub,
radially extending walls between adjacent blades of said plurality of blades, each of said walls comprising at least one web extending circumferentially from one of said adjacent blades to the other of said adjacent blades,
an inducer rotatably mounted in said shroud coaxially with said impeller, said inducer comprising a disc with radial blades,
means to drivingly connect said inducer to said impeller for rotation therewith, and
an annular flow channel through said compressor, said flow channel being bounded by an outer wall comprising said shroud and an inner wall comprising a portion of said disc and said radially extending walls.
References Cited by the Examiner UNITED STATES PATENTS 958,129 5/1910 Huguenin 230-134 2,216,747 10/1940 Klimek 103-115 2,317,543 4/ 1943 Livingston 230-134 2,745,597 5/ 1956 Sinclair et al 230-134 2,889,107 6/ 1959 Stalker 230-134 FOREIGN PATENTS 614,865 2/ 1961 Canada. 1,337,094 7/1963 France.
908,424 10/ 1962 Great Britain.
D-ONLEY I. STOCKING, Primary Examiner. HENRY F. RADUAZO, MARK NEWMAN, Examiners.

Claims (1)

1. A CENTRIFUGAL COMPRESSOR COMPRISING AN ANNULAR SHROUD, AN IMPELLER ROTATABLY MOUNTED IN SAID SHROUD, SAID IMPELLER COMPRISING A HUB, A PLURALITY OF CIRCUMFERENTIALLY SPACED BLADES INDIVIDUALLY MOUNTED ON SAID HUB AND EXTENDING RADIALLY THEREFROM, A PAIR OF RADIALLY ARCUATE WEBS EXTENDING CIRCUMFERENTIALLY IN OPPOSITE DIRECTIONS FROM EACH BLADE AND EXTENDING RADIALLY FROM THE LEADING EDGE OF SAID BLADE ADJACENT SAID HUB TO THE TRAILING EDGE OF SAID BLADE ADJACENT ITS TIP, SAID WEBS ABUTTING WEBS EXTENDING FROM ADJACENT BLADES TO FORM WALLS BETWEEN SAID BLADE AND SAID ADJACENT BLADES, AN INDUCER ROTATABLY MOUNTED IN SAID SHROUD COAXIALLY WITH SAID IMPELLER, SAID INDUCER COMPRISING A DISC WITH RADIALLY EXTENDING BLADES,
US433670A 1965-02-18 1965-02-18 Centrifugal compressor Expired - Lifetime US3305166A (en)

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Cited By (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3642383A (en) * 1968-11-25 1972-02-15 Kongsberg Vapenfab As Arrangement for holding together a turbine rotor and other aligned members of a gas turbine
US4218018A (en) * 1977-08-06 1980-08-19 Robert Bosch Gmbh Arrangement for washing lenses of headlights
DE3334880A1 (en) * 1982-09-30 1984-04-05 General Electric Co., Schenectady, N.Y. MULTI-STAGE RADIAL COMPRESSOR, RADIAL WHEEL AND METHOD FOR COMPRESSING A FLUID
DE3335616A1 (en) * 1983-09-30 1985-04-18 MTU Motoren- und Turbinen-Union München GmbH, 8000 München Radial compressor impeller for turbomachines, especially gas turbine engines
US20100150725A1 (en) * 2008-12-11 2010-06-17 Michael Stephen Krautheim Wheel formed from a bladed ring and disk
WO2016127225A1 (en) * 2015-02-09 2016-08-18 Atlas Copco Airpower, Naamloze Vennootschap Impeller and method for manufacturing such an impeller
US20190285080A1 (en) * 2016-05-12 2019-09-19 Man Energy Solutions Se Radial Compressor
DE102018204503A1 (en) * 2018-03-23 2019-09-26 Robert Bosch Gmbh liquid pump

Families Citing this family (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
IT1159048B (en) * 1983-08-01 1987-02-25 Coral Spa IMPELLER FOR CENTRIFUGAL FANS AND COMPRESSORS
GB2344384B (en) * 1998-12-02 2003-02-26 Sunonwealth Electr Mach Ind Co Fan wheel structures

Citations (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US958129A (en) * 1907-11-05 1910-05-17 Albert Huguenin Construction of rotating wheels for rotary fluid-compressors.
US2216747A (en) * 1935-09-06 1940-10-08 Gustav A Klimek Blade construction for fluid power transmitter
US2317543A (en) * 1943-04-27 Suction cleaner
US2745597A (en) * 1953-01-13 1956-05-15 Harvey Whipple Inc Fan
US2889107A (en) * 1955-01-03 1959-06-02 Stalker Corp Fluid rotor construction
CA614865A (en) * 1961-02-21 E. Becker John Fluid couplings
GB908424A (en) * 1960-04-12 1962-10-17 Daimler Benz Ag Improvements relating to the rotors of flow machines
FR1337094A (en) * 1962-10-24 1963-09-06 Cem Comp Electro Mec Fan training

Patent Citations (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2317543A (en) * 1943-04-27 Suction cleaner
CA614865A (en) * 1961-02-21 E. Becker John Fluid couplings
US958129A (en) * 1907-11-05 1910-05-17 Albert Huguenin Construction of rotating wheels for rotary fluid-compressors.
US2216747A (en) * 1935-09-06 1940-10-08 Gustav A Klimek Blade construction for fluid power transmitter
US2745597A (en) * 1953-01-13 1956-05-15 Harvey Whipple Inc Fan
US2889107A (en) * 1955-01-03 1959-06-02 Stalker Corp Fluid rotor construction
GB908424A (en) * 1960-04-12 1962-10-17 Daimler Benz Ag Improvements relating to the rotors of flow machines
FR1337094A (en) * 1962-10-24 1963-09-06 Cem Comp Electro Mec Fan training

Cited By (12)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3642383A (en) * 1968-11-25 1972-02-15 Kongsberg Vapenfab As Arrangement for holding together a turbine rotor and other aligned members of a gas turbine
US4218018A (en) * 1977-08-06 1980-08-19 Robert Bosch Gmbh Arrangement for washing lenses of headlights
DE3334880A1 (en) * 1982-09-30 1984-04-05 General Electric Co., Schenectady, N.Y. MULTI-STAGE RADIAL COMPRESSOR, RADIAL WHEEL AND METHOD FOR COMPRESSING A FLUID
DE3335616A1 (en) * 1983-09-30 1985-04-18 MTU Motoren- und Turbinen-Union München GmbH, 8000 München Radial compressor impeller for turbomachines, especially gas turbine engines
US20100150725A1 (en) * 2008-12-11 2010-06-17 Michael Stephen Krautheim Wheel formed from a bladed ring and disk
US8814524B2 (en) * 2008-12-11 2014-08-26 Rolls-Royce Corporation Wheel formed from a bladed ring and disk
WO2016127225A1 (en) * 2015-02-09 2016-08-18 Atlas Copco Airpower, Naamloze Vennootschap Impeller and method for manufacturing such an impeller
CN107250553A (en) * 2015-02-09 2017-10-13 阿特拉斯·科普柯空气动力股份有限公司 The method of impeller and this impeller of manufacture
US20180051709A1 (en) * 2015-02-09 2018-02-22 Atlas Copco Airpower, Naamloze Vennootschap Impeller and method for producing such an impeller
US11098728B2 (en) * 2015-02-09 2021-08-24 Atlas Copco Airpower, Naamloze Vennootschap Impeller and method for producing such an impeller
US20190285080A1 (en) * 2016-05-12 2019-09-19 Man Energy Solutions Se Radial Compressor
DE102018204503A1 (en) * 2018-03-23 2019-09-26 Robert Bosch Gmbh liquid pump

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