WO1990002265A1 - Partial height blades in a compressor impeller - Google Patents

Partial height blades in a compressor impeller Download PDF

Info

Publication number
WO1990002265A1
WO1990002265A1 PCT/US1989/003437 US8903437W WO9002265A1 WO 1990002265 A1 WO1990002265 A1 WO 1990002265A1 US 8903437 W US8903437 W US 8903437W WO 9002265 A1 WO9002265 A1 WO 9002265A1
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WO
WIPO (PCT)
Prior art keywords
blades
height
partial
impeller
height blades
Prior art date
Application number
PCT/US1989/003437
Other languages
French (fr)
Inventor
Colin Osborne
Original Assignee
Dresser-Rand Company
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 Dresser-Rand Company filed Critical Dresser-Rand Company
Publication of WO1990002265A1 publication Critical patent/WO1990002265A1/en

Links

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
    • F04D29/32—Rotors specially for elastic fluids for axial flow pumps
    • F04D29/321—Rotors specially for elastic fluids for axial flow pumps for axial flow compressors
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/02—Blade-carrying members, e.g. rotors
    • F01D5/04—Blade-carrying members, e.g. rotors for radial-flow machines or engines
    • F01D5/043—Blade-carrying members, e.g. rotors for radial-flow machines or engines of the axial inlet- radial outlet, or vice versa, type
    • F01D5/048—Form or construction
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • 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

Definitions

  • This invention pertains to radial or axial turbomachinery rotors, and more particularly to an impeller having partial height blades between full height blades.
  • the present invention is directed towards improving the flow field within the passages of an axial or centrifugal turbomachine, for example, a centrifugal impeller.
  • the invention is intended to reduce the extent of separated flow or wake regions within the impeller and at the same time reduce the blade surface area and the associated frictional effects. Reduced wake at the impeller exit and in the downstream components of flow increase efficiency and extend range.
  • An impeller is improved by providing partial height blades between full blades.
  • FIGURE 1 shows in cross section a centrifugal compressor impeller incorporating the improvement of the present invention.
  • FIGURES 2-4 show in cross section, a portion of a centrifugal compressor impeller incorporating alternate expressions of the present invention.
  • FIGURE 5 shows a front plan view of a centrifugal compressor impeller, illustrating suitable locations for the partial height blades of the present invention.
  • FIGURES 6-8 shows a cross section of a centrifugal compressor impeller, wherein partial height blades of different shapes and locations are illustrated.
  • FIGURE 9 shows in front plan view a shrouded impeller incorporating partial height blades on both the hub and shroud surfaces.
  • FIGURE 10 shows in cross section, a shrouded impeller incorporating partial height blades.
  • FIGURES 11 a, b and c show in cross section variants of the present invention, wherein the leading edge or trailing edge of the partial height blade, or both, extend beyond the full height blades.
  • an impeller 10 As shown in FIGURE 1, an impeller 10 according to the improvements of the present invention generally includes a hub 11 defined by an intake 12 and an exit 13.
  • the hub has an outer surface 14.
  • a plurality of full height blades 15 are located about the outer surface 14.
  • the inventive aspect of the device shown in FIGURE 1 is the inclusion of partial height blades 18 between adjacent full height blades. The height of a blade is measured with reference to an imaginary line tangent to the outer surface 14.
  • a partial height blade is one which is between 5 and 85 percent the height of an adjacent full height blade at any point.
  • Partial height blades increase the efficiency and range of the compressor to which the improved impeller is affixed.
  • the partial height blade 18 includes a leading edge 19 and a trailing edge 20.
  • the leading edge is both tapered and located somewhat away from the intake 12 and is thus said to be intermediate the intake and the exit.
  • the trailing edge 20 terminates at the exit 13. It should be understood that a variety of leading edge tapers and varying degrees of recession of the leading edge away from the intake will all produce beneficial results.
  • FIGURE 2 shows that the leading edge 19 can terminate at the intake 12, just as the trailing edge 20 terminates at the exit 13.
  • FIGURE 3 A further variation is depicted in FIGURE 3 where it is shown that the trailing edge can be receded from the exit so that it is intermediate the exit 13 and the intake 12.
  • both leading edge 19 and trailing edge 20 are receded and thus both are intermediately located.
  • the partial height blade 47 has a leading edge 41 which is seen as extending beyond the inducer leading edge 42.
  • the partial height trailing edge 43 is shown as extending beyond the trailing edge 44 of the full height blade 48.
  • the partial height blade is depicted as extending beyond the inducer or leading edge 45 of the full height blade 49 and the trailing edge 46 of the full height blade. It will be appreciated that a variety of leading edge and trailing edge variations may be practiced, all having beneficial results over impellers with only full height blades.
  • full height blades are closer together at the intake 12 than at the exit 13.
  • the flow path 21 between adjacent blades is characterized by a centerline which runs along the outer surface 14 and which is equidistant from either adjacent blade 15 at any point.
  • the partial height blade follows the flow path centerline.
  • the present invention is not so limited as circumferential displacement of partial height blades 22, 23 from the centerline in either direction will produce advantages in impeller performance.
  • more than one partial height blade may be interposed between each adjacent pair of full height blades. In such designs, the partial height blades may be either of the same height or of different heights. This is true for all the configurations to follow as well as those previously mentioned.
  • FIGURE 6 shows blades 24, 25 inclined with respect to the radius of the impeller. Inclined blades would take the place of a radially upright blade 18.
  • FIGURE 7 shows a j-shaped blade 26 and alternate J-shaped blade locations 27 and 28. Note that the curved tip 29 of the J-shaped blade points away from the direction of rotation 30 of the hub.
  • FIGURE 8 shows a centrally located pyramidal partial height blade 31 and alternate off-center located blades 32 and 33.
  • a blade is considered pyramidal when the base of the blade 34, at the point of attachment, is wider than the tip portion 35.
  • the partial height blades may take a form considerably different from that of the adjacent full height blades. It is to be understood that more than one partial height blade may be interposed between adjacent full height blade pairs, that such partial height blades may have a different cross section than the full height blades and that they need not be centered between full height blades.
  • FIGURE 9 shows a shrouded impeller 36, generally characterized by a shroud 37 which encloses the flow paths.
  • partial height blades may be located opposite one another along the flow path.
  • one partial height blade 38 is located on the hub, while another partial height blade 39 is located on the shroud.
  • the hub and shroud blades 38, 39 need not be located opposite one another. They may be displaced from one another circumfer- entially.
  • partial height blades should be limited in their combined height to between 5 and 85 percent of the full blade height.
  • any of the aforementioned partial height blade shapes are adaptable to the shrouded impeller application.
  • a partial height blade of any variety 40 can be located on the hub only, thus eliminating the shroud blade 39.
  • a partial height blade of any variety may be located on the shroud only, thus eliminating the hub blade.
  • Partial height blades are, for example, fully utilizable in radial or mixed flow centrifugal compressors, axial compressors, radial turbines and axial turbines.
  • the scope of the invention should not be limited by the examples given, but rather, interpreted by the accompanying claims.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)

Abstract

An improved compressor impeller (10) has partial height blades (18) between full height blades (15). The invention is adaptable to radial or mixed flow centrifugal compressors, axial compressors, radial turbines and axial turbines.

Description

PARTIAL HEIGHT BLADES IN A COMPRESSOR IMPELLER
FIELD OP THE INVENTION
This invention pertains to radial or axial turbomachinery rotors, and more particularly to an impeller having partial height blades between full height blades.
BACKGROUND OF THE INVENTION
The present invention is directed towards improving the flow field within the passages of an axial or centrifugal turbomachine, for example, a centrifugal impeller. Specifically, the invention is intended to reduce the extent of separated flow or wake regions within the impeller and at the same time reduce the blade surface area and the associated frictional effects. Reduced wake at the impeller exit and in the downstream components of flow increase efficiency and extend range.
SUMMARY OF THE INVENTION
An impeller is improved by providing partial height blades between full blades.
BRIEF DESCRIPTION OF THE DRAWINGS
FIGURE 1 shows in cross section a centrifugal compressor impeller incorporating the improvement of the present invention. FIGURES 2-4 show in cross section, a portion of a centrifugal compressor impeller incorporating alternate expressions of the present invention.
FIGURE 5 shows a front plan view of a centrifugal compressor impeller, illustrating suitable locations for the partial height blades of the present invention.
FIGURES 6-8 shows a cross section of a centrifugal compressor impeller, wherein partial height blades of different shapes and locations are illustrated.
FIGURE 9 shows in front plan view a shrouded impeller incorporating partial height blades on both the hub and shroud surfaces.
FIGURE 10 shows in cross section, a shrouded impeller incorporating partial height blades.
FIGURES 11 a, b and c show in cross section variants of the present invention, wherein the leading edge or trailing edge of the partial height blade, or both, extend beyond the full height blades.
DESCRIPTION OF THE PREFERRED EMBODIMENT
As shown in FIGURE 1, an impeller 10 according to the improvements of the present invention generally includes a hub 11 defined by an intake 12 and an exit 13. The hub has an outer surface 14. A plurality of full height blades 15 are located about the outer surface 14. As the hub spins about a shaft 16 which turns about a central axis 17, fluid enters the intake 12, passes along the flow path between adjacent blades 15 and is ejected under pressure from the exit 13. The inventive aspect of the device shown in FIGURE 1 is the inclusion of partial height blades 18 between adjacent full height blades. The height of a blade is measured with reference to an imaginary line tangent to the outer surface 14. For the present purposes, a partial height blade is one which is between 5 and 85 percent the height of an adjacent full height blade at any point. Partial height blades increase the efficiency and range of the compressor to which the improved impeller is affixed. The partial height blade 18 includes a leading edge 19 and a trailing edge 20. In the example of FIGURE 1, it can be seen that the leading edge is both tapered and located somewhat away from the intake 12 and is thus said to be intermediate the intake and the exit. The trailing edge 20 terminates at the exit 13. It should be understood that a variety of leading edge tapers and varying degrees of recession of the leading edge away from the intake will all produce beneficial results. FIGURE 2 shows that the leading edge 19 can terminate at the intake 12, just as the trailing edge 20 terminates at the exit 13. A further variation is depicted in FIGURE 3 where it is shown that the trailing edge can be receded from the exit so that it is intermediate the exit 13 and the intake 12. In FIGURE 4, both leading edge 19 and trailing edge 20 are receded and thus both are intermediately located. In FIGURE
11a, the partial height blade 47 has a leading edge 41 which is seen as extending beyond the inducer leading edge 42. In FIGURE lib, the partial height trailing edge 43 is shown as extending beyond the trailing edge 44 of the full height blade 48. In FIGURE lie, the partial height blade is depicted as extending beyond the inducer or leading edge 45 of the full height blade 49 and the trailing edge 46 of the full height blade. It will be appreciated that a variety of leading edge and trailing edge variations may be practiced, all having beneficial results over impellers with only full height blades.
As seen in FIGURE 5, full height blades are closer together at the intake 12 than at the exit 13. However, the flow path 21 between adjacent blades is characterized by a centerline which runs along the outer surface 14 and which is equidistant from either adjacent blade 15 at any point. In the preferred embodiment, the partial height blade follows the flow path centerline. However, the present invention is not so limited as circumferential displacement of partial height blades 22, 23 from the centerline in either direction will produce advantages in impeller performance. Moreover, more than one partial height blade may be interposed between each adjacent pair of full height blades. In such designs, the partial height blades may be either of the same height or of different heights. This is true for all the configurations to follow as well as those previously mentioned.
The exact shape or cross section of the partial height blade is also variable. FIGURE 6 shows blades 24, 25 inclined with respect to the radius of the impeller. Inclined blades would take the place of a radially upright blade 18. FIGURE 7 shows a j-shaped blade 26 and alternate J-shaped blade locations 27 and 28. Note that the curved tip 29 of the J-shaped blade points away from the direction of rotation 30 of the hub.
Pyramidal partial height blades are contemplated as well. FIGURE 8 shows a centrally located pyramidal partial height blade 31 and alternate off-center located blades 32 and 33. A blade is considered pyramidal when the base of the blade 34, at the point of attachment, is wider than the tip portion 35. Thus, it can be appreciated that the partial height blades may take a form considerably different from that of the adjacent full height blades. It is to be understood that more than one partial height blade may be interposed between adjacent full height blade pairs, that such partial height blades may have a different cross section than the full height blades and that they need not be centered between full height blades.
Finally, it should be mentioned that the aforestated improvements pertaining to partial height blades are equally applicable to shrouded impellers. FIGURE 9 shows a shrouded impeller 36, generally characterized by a shroud 37 which encloses the flow paths. In the shrouded impeller situation, partial height blades may be located opposite one another along the flow path. Thus, one partial height blade 38 is located on the hub, while another partial height blade 39 is located on the shroud. Note that the hub and shroud blades 38, 39 need not be located opposite one another. They may be displaced from one another circumfer- entially. In the case of the shrouded impeller, partial height blades should be limited in their combined height to between 5 and 85 percent of the full blade height. Any of the aforementioned partial height blade shapes are adaptable to the shrouded impeller application. As seen in FIGURE 10, a partial height blade of any variety 40 can be located on the hub only, thus eliminating the shroud blade 39. Similarly, a partial height blade of any variety may be located on the shroud only, thus eliminating the hub blade.
While the present invention has been described in conjunction with specific equipment, it should be noted that the principles of practicing the invention are widely applicable to a variety of full height and partial height blade configurations as well as a variety of rotor designs for turbine and compressor configurations. Partial height blades are, for example, fully utilizable in radial or mixed flow centrifugal compressors, axial compressors, radial turbines and axial turbines. Thus, the scope of the invention should not be limited by the examples given, but rather, interpreted by the accompanying claims.

Claims

WHAT IS CLAIMED IS:
1. In an impeller having a central axis, an intake, an exit, an outer surface and a plurality of full height blades disposed about the outer surface, where adjacent blades define a flow path having a centerline, the improvement comprising: partial height blades located between the full height blades.
2. The improved impeller of Claim 1 wherein the partial height blade is located along the centerline and extends from the outer surface to a height of from 5-85 percent of the height of the full height blade.
3. The improved impeller of Claim 2 wherein the partial height blade further comprises a leading edge and a trailing edge, the leading edge terminating at the intake of the impeller.
4. The improved impeller of Claim 2 wherein the leading edge is located intermediate the intake end and the exit.
5. The improved impeller of Claim 3 or 4 wherein the trailing edge is located intermediate the intake and the exit.
6. The improved impeller of Claim 3 or 4 wherein the trailing edge terminates at the exit of the impeller.
7. The improved impeller of Claim 1 wherein the partial height blade is circumferentially displaced from the centerline and extends from the outer surface to a height of from 5-85 percent of the height of the full height blade.
8. The improved impeller of Claim 7 wherein the partial height blade further comprises a leading edge and a trailing edge, the leading edge terminating at the intake of the impeller.
9. The improved impeller of Claim 7 wherein the leading edge is located intermediate the intake end and the exit.
10. The improved impeller of Claim 8 or 9 wherein the trailing edge is located intermediate the intake and the exit.
11. The improved impeller of Claim 8 or 9 wherein the trailing edge terminates at the exit of the impeller.
12. In an impeller having a central axis, an intake region, an exit, an outer surface and a plurality of full height blades disposed about the outer surface, where adjacent blades define a flow path having a centerline, the improvement comprising: a plurality of partial height blades between adjacent full height blades.
13. The improved impeller of Claim 12, wherein the partial height blades are of equal height.
14. In a turbomachine having a central axis, a rotor intake, a rotor exit, a rotor outer surface and a plurality of full height blades disposed about an outer surface of the rotor, where adjacent blades define a flow path having a centerline, the improvement comprising: partial height blades located between the full height blades.
15. In a turbomachine rotor having a central axis, an intake region, an exit, an outer surface and a plurality of full height blades disposed about the outer surface, where adjacent blades define a flow path having a centerline, the improvement comprising: partial height blades located between the full height blades; and full height blades having leading edges, the partial height blades terminating at one end axially beyond the leading edges of the full height blades.
16. The improved turbomachine of Claim 15, wherein: the full height blades further comprise trailing edges, the partial height blades terminating, at the other end, beyond the trailing edges of the full height blades.
17. In a turbomachine rotor having a central axis, an intake, an exit, an outer surface and a plurality of full height blades disposed about the outer surface, where adjacent blades define a flow path having a centerline, the improvement comprising: partial height blades located between the full height blades; and full height blades having trailing edges, the partial height blades terminating beyond the trailing edges of the full height blades.
18. In a turbomachine having a central axis, an intake, an exit, a rotor outer surface and a plurality of full height blades disposed about the outer surface, where adjacent blades define a flow path having a centerline, the improvement comprising: a plurality of partial height blades located between adjacent full height blades.
19. The improved turbomachine of Claim 18, wherein at least one partial height blade between adjacent full height blades is of a different height than the other partial height blades therebetween.
20. In a turbomachine rotor having a central axis, an intake, an exit, an outer surface and a plurality of full height blades disposed about the outer surface, where adjacent blades define flow paths having centerlines, the improvement comprising: partial height blades located between the full height blades; wherein the partial height blades are circumferentially disposed from the centerlines of the flow paths.
21. In an impeller having a central axis, an intake region, an exit, a shroud, an outer surface and a plurality of full height blades disposed between the outer surface and the shroud, where adjacent blades define a flow path having a centerline, the improvement comprising: one or more partial height blades between adjacent full height blades.
22. The improved impeller of Claim 21, wherein all the partial height blades are of equal height.
23. The improved impeller of Claim 21, wherein the partial height blades are located on both the hub and the* shroud.
24. The improved impeller of Claim 21, wherein the partial height blades on the hub are circumferentially displaced from the partial height blades on the shroud.
25. The improved impeller of Claim 21, wherein partial height blades are provided on the hub and have a different cross-section than partial height blades provided on the shroud.
26. The improved impeller of Claim 21, wherein partial height blades are provided only on the hub.
27. The improved impeller of Claim 21, wherein partial height blades are provided only on the shroud.
PCT/US1989/003437 1988-08-16 1989-08-15 Partial height blades in a compressor impeller WO1990002265A1 (en)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
US23278788A 1988-08-16 1988-08-16
US232,787 1994-04-22

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WO1990002265A1 true WO1990002265A1 (en) 1990-03-08

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Cited By (14)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO1992013197A1 (en) * 1991-01-15 1992-08-06 Northern Research & Engineering Corporation Arbitrary hub for centrifugal impellers
US5215439A (en) * 1991-01-15 1993-06-01 Northern Research & Engineering Corp. Arbitrary hub for centrifugal impellers
US5639217A (en) * 1996-02-12 1997-06-17 Kawasaki Jukogyo Kabushiki Kaisha Splitter-type impeller
EP1707824A1 (en) * 2003-12-03 2006-10-04 Mitsubishi Heavy Industries, Ltd. Impeller for compressor
GB2432400A (en) * 2005-11-21 2007-05-23 Schlumberger Holdings Non-axisymmetric pump flow passage
US20110176916A1 (en) * 2010-01-16 2011-07-21 Fu Zhun Precision Industry (Shen Zhen) Co., Ltd. Centrifugal fan and impeller thereof
US20120328444A1 (en) * 2009-12-02 2012-12-27 Mitsubishi Heavy Industries, Ltd. Impeller of centrifugal compressor
WO2014160421A1 (en) * 2013-03-13 2014-10-02 Pentair Water Pool And Spa, Inc. Alternating paddle mechanism for pool cleaner
WO2016017223A1 (en) * 2014-07-31 2016-02-04 株式会社日立製作所 Centrifugal impeller and uniaxial multistage centrifugal compressor using same, and manufacturing method of centrifugal impeller
US20160281730A1 (en) * 2015-03-26 2016-09-29 Deere & Company Centrifugal fan assembly
US9476216B2 (en) 2013-03-11 2016-10-25 Pentair Water Pool And Spa, Inc. Two-wheel actuator steering system and method for pool cleaner
US9874196B2 (en) 2013-03-13 2018-01-23 Pentair Water Pool And Spa, Inc. Double paddle mechanism for pool cleaner
US10774842B2 (en) 2015-04-30 2020-09-15 Concepts Nrec, Llc Biased passages for turbomachinery
WO2020251448A1 (en) 2019-06-13 2020-12-17 Scania Cv Ab Centrifugal compressor impeller for a charging device of an internal combustion engine

Citations (10)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2648493A (en) * 1945-10-23 1953-08-11 Edward A Stalker Compressor
US2920864A (en) * 1956-05-14 1960-01-12 United Aircraft Corp Secondary flow reducer
US3481531A (en) * 1968-03-07 1969-12-02 United Aircraft Canada Impeller boundary layer control device
US3904308A (en) * 1973-05-16 1975-09-09 Onera (Off Nat Aerospatiale) Supersonic centrifugal compressors
US4093401A (en) * 1976-04-12 1978-06-06 Sundstrand Corporation Compressor impeller and method of manufacture
US4195473A (en) * 1977-09-26 1980-04-01 General Motors Corporation Gas turbine engine with stepped inlet compressor
GB2053368A (en) * 1979-06-22 1981-02-04 Klein Schanzlin & Becker Ag An open impeller for a centrifugal pump
SU1059217A1 (en) * 1982-09-08 1983-12-07 Всесоюзный Научно-Исследовательский Институт "Гелиевая Техника" Inward-flow turbine wheel
US4502837A (en) * 1982-09-30 1985-03-05 General Electric Company Multi stage centrifugal impeller
JPS6069211A (en) * 1983-08-26 1985-04-19 Mitsubishi Heavy Ind Ltd Radial turbine

Patent Citations (10)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2648493A (en) * 1945-10-23 1953-08-11 Edward A Stalker Compressor
US2920864A (en) * 1956-05-14 1960-01-12 United Aircraft Corp Secondary flow reducer
US3481531A (en) * 1968-03-07 1969-12-02 United Aircraft Canada Impeller boundary layer control device
US3904308A (en) * 1973-05-16 1975-09-09 Onera (Off Nat Aerospatiale) Supersonic centrifugal compressors
US4093401A (en) * 1976-04-12 1978-06-06 Sundstrand Corporation Compressor impeller and method of manufacture
US4195473A (en) * 1977-09-26 1980-04-01 General Motors Corporation Gas turbine engine with stepped inlet compressor
GB2053368A (en) * 1979-06-22 1981-02-04 Klein Schanzlin & Becker Ag An open impeller for a centrifugal pump
SU1059217A1 (en) * 1982-09-08 1983-12-07 Всесоюзный Научно-Исследовательский Институт "Гелиевая Техника" Inward-flow turbine wheel
US4502837A (en) * 1982-09-30 1985-03-05 General Electric Company Multi stage centrifugal impeller
JPS6069211A (en) * 1983-08-26 1985-04-19 Mitsubishi Heavy Ind Ltd Radial turbine

Cited By (22)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO1992013197A1 (en) * 1991-01-15 1992-08-06 Northern Research & Engineering Corporation Arbitrary hub for centrifugal impellers
US5215439A (en) * 1991-01-15 1993-06-01 Northern Research & Engineering Corp. Arbitrary hub for centrifugal impellers
US5639217A (en) * 1996-02-12 1997-06-17 Kawasaki Jukogyo Kabushiki Kaisha Splitter-type impeller
EP1707824A1 (en) * 2003-12-03 2006-10-04 Mitsubishi Heavy Industries, Ltd. Impeller for compressor
EP1707824A4 (en) * 2003-12-03 2007-05-09 Mitsubishi Heavy Ind Ltd Impeller for compressor
US7326037B2 (en) 2005-11-21 2008-02-05 Schlumberger Technology Corporation Centrifugal pumps having non-axisymmetric flow passage contours, and methods of making and using same
GB2432400B (en) * 2005-11-21 2008-10-01 Schlumberger Holdings Centrifugal oilfield pumping systems, and methods of making and using same
GB2432400A (en) * 2005-11-21 2007-05-23 Schlumberger Holdings Non-axisymmetric pump flow passage
US20120328444A1 (en) * 2009-12-02 2012-12-27 Mitsubishi Heavy Industries, Ltd. Impeller of centrifugal compressor
US9140271B2 (en) * 2009-12-02 2015-09-22 Mitsubishi Heavy Industries, Ltd. Impeller of centrifugal compressor
US20110176916A1 (en) * 2010-01-16 2011-07-21 Fu Zhun Precision Industry (Shen Zhen) Co., Ltd. Centrifugal fan and impeller thereof
US9476216B2 (en) 2013-03-11 2016-10-25 Pentair Water Pool And Spa, Inc. Two-wheel actuator steering system and method for pool cleaner
US10156082B2 (en) 2013-03-11 2018-12-18 Pentair Water Pool And Spa, Inc. Two-wheel actuator steering system and method for pool cleaner
WO2014160421A1 (en) * 2013-03-13 2014-10-02 Pentair Water Pool And Spa, Inc. Alternating paddle mechanism for pool cleaner
US9850672B2 (en) 2013-03-13 2017-12-26 Pentair Water Pool And Spa, Inc. Alternating paddle mechanism for pool cleaner
US9874196B2 (en) 2013-03-13 2018-01-23 Pentair Water Pool And Spa, Inc. Double paddle mechanism for pool cleaner
WO2016017223A1 (en) * 2014-07-31 2016-02-04 株式会社日立製作所 Centrifugal impeller and uniaxial multistage centrifugal compressor using same, and manufacturing method of centrifugal impeller
US20160281730A1 (en) * 2015-03-26 2016-09-29 Deere & Company Centrifugal fan assembly
US9920768B2 (en) * 2015-03-26 2018-03-20 Deere & Company Centrifugal fan assembly
US10774842B2 (en) 2015-04-30 2020-09-15 Concepts Nrec, Llc Biased passages for turbomachinery
WO2020251448A1 (en) 2019-06-13 2020-12-17 Scania Cv Ab Centrifugal compressor impeller for a charging device of an internal combustion engine
EP3983684A4 (en) * 2019-06-13 2023-07-12 Scania CV AB Centrifugal compressor impeller for a charging device of an internal combustion engine

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