EP0567874B1 - Machine à courant pour la compression d'un gaz - Google Patents

Machine à courant pour la compression d'un gaz Download PDF

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Publication number
EP0567874B1
EP0567874B1 EP93106279A EP93106279A EP0567874B1 EP 0567874 B1 EP0567874 B1 EP 0567874B1 EP 93106279 A EP93106279 A EP 93106279A EP 93106279 A EP93106279 A EP 93106279A EP 0567874 B1 EP0567874 B1 EP 0567874B1
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EP
European Patent Office
Prior art keywords
blades
radial
chamber
impeller
fluid flow
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Expired - Lifetime
Application number
EP93106279A
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German (de)
English (en)
Other versions
EP0567874A1 (fr
Inventor
Hans-Heinrich Dr. Ing. Henning
Dieter Dipl.-Ing. Frohn
Carldieter Dipl.-Ing. Hollmann
Walter Winkelströter
Frank Dipl.-Ing. Diedrichsen
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Gebr Becker GmbH
Gebr Becker GmbH and Co KG
Original Assignee
Gebr Becker GmbH
Gebr Becker GmbH and Co KG
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
Priority claimed from DE4230770A external-priority patent/DE4230770C2/de
Application filed by Gebr Becker GmbH, Gebr Becker GmbH and Co KG filed Critical Gebr Becker GmbH
Publication of EP0567874A1 publication Critical patent/EP0567874A1/fr
Application granted granted Critical
Publication of EP0567874B1 publication Critical patent/EP0567874B1/fr
Anticipated expiration legal-status Critical
Expired - Lifetime legal-status Critical Current

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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D25/00—Pumping installations or systems
    • F04D25/16—Combinations of two or more pumps ; Producing two or more separate gas flows
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D17/00—Radial-flow pumps, e.g. centrifugal pumps; Helico-centrifugal pumps
    • F04D17/08—Centrifugal pumps
    • F04D17/10—Centrifugal pumps for compressing or evacuating
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D23/00—Other rotary non-positive-displacement pumps
    • F04D23/008—Regenerative pumps

Definitions

  • the invention relates to a turbomachine having a radial compressor impeller which has radial blades and feeds a side channel compressor which has a ring of chambers which are separated by chamber blades attached to the impeller, the ring diameter of the side channel of the side channel compressor being equal to or greater than the diameter of the radial blades is the supporting part of the impeller, the chambers having openings on their side adjoining the outer ends of the radial blades and the radial blades continuously merging into the chamber blades in the direction of flow.
  • Turbomachines are generally designed, among other things, as radial compressors or as side channel compressors. Radial compressors are primarily used to generate large volume flows, side channel compressors to generate high pressure differences.
  • a radial vane-supported side channel pump which can also be used for gaseous media, is known, in which the impeller has convexly curved radial vanes on one end face, which convey the conveying medium into one promote spirally widening circumferential channel, from which the pumped medium is passed on to a side channel pump, the radially directed chamber blades of which are attached either on the opposite side of the impeller from the radial blades or according to FIG. 8 there on the outer circumference of the impeller.
  • the medium conveyed to the outside by the radial vanes is conducted over a relatively long path with multiple deflections to the side channel, which considerably reduces the efficiency.
  • DD-PS 4862 discloses a generic multi-stage flow machine, which is, however, intended for liquid media, in which the first stage is designed as a radial compressor, the radial blades of which continuously pass into chamber blades of the second stage designed as a side channel compressor.
  • the chambers of the side channel compressor enclosing the radial blades are open on their side facing the radial blades, so that the pumped medium reaches the chambers of the side channel compressor directly from the flow channels of the radial compressor.
  • the chamber blades are aligned radially, and the radial blades, which are only slightly concavely curved there, merge in a straight line into the chamber blades.
  • a pressure building up in the side channel chambers leads to an unhindered backflow directed radially inward into the flow channels of the radial compressor, which limits the achievable efficiency.
  • a self-priming liquid centrifugal pump is known from the DD-PS 35 450, whose impeller in the central area with convex curved radial blades and in the peripheral area with convex curved chamber blades is provided.
  • the radial blades circulate within a cylindrical intermediate casing which is interrupted only at one point by an elbow of approximately 60 °, so that the liquid flow passes only at this point of interruption from the radial conveyor into the circumferential channel having the chamber blades. Since the radial blades and chamber blades are at a distance of at least the thickness of the intermediate casing, considerable turbulence occurs during the transition, which greatly limits the efficiency that can be achieved.
  • DD-PS 41 513 discloses a combined impeller for pumps, compressors or the like with curved radial blades which convey the medium into the center into a circumferential channel which is equipped with straight, radially directed chamber blades on two opposite sides.
  • the medium flow generated by the radial vanes is divided on the outer circumferential wall of the circumferential channel and deflected towards the chamber vanes, so that two opposing circular flows occur in the circumferential channel, which impinge on the medium flow generated by the radial vanes. Since this medium flow abruptly loses its guidance previously caused by the radial blades when entering the circumferential channel, there is considerable turbulence and a rapid backflow, which is why this known arrangement can only achieve a very limited efficiency.
  • the invention has for its object to provide a turbomachine with high efficiency, which should also be suitable for laser gas circulation.
  • the turbomachine is designed as a gas compression machine in that - in front view - the chamber blades and the radial blades each have opposite curvatures, that the chamber blades and the radial blades at their transition point have a point of curvature and that the blades at the transition point by an angle of the same amount of less than 30 ° degrees, for example of 15 °, with respect to the circumferential tangent at the transition point.
  • the efficiency of the turbomachine can also be increased further in that the radial blades projecting at right angles from the impeller at their radially inner end and the subsequent chamber blades, with their longitudinal extension increasing, give forward over the impeller plane, i.e. are inclined in the direction of rotation of the impeller.
  • the chamber blades of the side channel compressor Due to the large ring diameter of the toroidal side channel, the chamber blades of the side channel compressor have a higher peripheral speed than the radial blades reached. Because of its greater peripheral speed, the side channel compressor is able to take up a quantity of gas supplied by a radial compressor with a large absorption volume, which is then compressed to a high pressure in the side channel compressor as a subsequent work step. Since the amount of gas delivered by the radial compressor already enters the chambers of the side channel compressor at a high speed, a circulation movement occurs immediately in the side channel, so that the side channel compressor is used particularly effectively over its circumference.
  • the chambers of the side channel compressor initially take up maximum volume flows from the radial compressor behind the interrupter; the inflowing volume flows decrease - in accordance with the pressure build-up in the side channel - towards the front of the interrupter.
  • the carry-over losses inevitably occurring in the area of the interrupter in the side channel blower are low in the fluid-flow machine according to the invention, since the highly compressed gas quantities carried along by the chambers in the area of the interrupter subsequently do not counteract the suction pressure as in a conventional, single-stage side channel blower, but only against the suction pressure Relax the increased intermediate pressure already generated by the radial compressor.
  • the gas flow undergoes only a relatively small deflection during the transition from the radial compressor to the side channel compressor, since the direction of flow at this transition point remains directed radially outward and the steady, almost circumferential transition between radial blades and chamber blades avoids impact and detachment losses.
  • the turbomachine works with continuous suction pressure and blows off with low pulsation and is therefore relatively quiet. Overall, the invention achieves a low-noise turbomachine with high efficiency.
  • the chamber blades can each have a widening which is directed towards the side channel of the side channel compressor, the chambers being closed radially inward in the region of these widenings by an end wall.
  • the height of the radial blades decreases radially outwards and that the radial blades on their side opposite the impeller are assigned a cover wall on the housing side or a cover disc molded onto the impeller and that the cover wall or cover disc at the same time forms the end wall of the chambers in the area of the widenings.
  • the flow channels lying between two adjacent radial vanes are shaped towards the outside in such a way that the radial compressor feeds into the chambers of the side channel compressor at a high pressure, where the gas fed in is immediately set into the typical circulation movement of a side channel compressor.
  • the height of the radial vanes and the cross section of the flow channels delimited by them are designed to match the optimal volume flow of the side channel compressor.
  • the end face of the impeller carrying the radial blades is advantageously conical, and the radial blades are inclined obliquely in relation to the impeller axis in their longitudinal extent, so that the axially sucked-in gas is only gradually deflected in the radial direction.
  • the fluid flow machine according to the invention can be equipped with only one interrupter, which is recommended for a consumer who has a high, e.g. B. the maximum that can be generated by the turbomachine according to the invention, overpressure.
  • a plurality of interrupters can also be arranged on the side channel compressor, which open into a common collecting annulus in order to supply a consumer with a high volume requirement.
  • each interrupter is assigned its own collecting space with lass, so that several consumers can be supplied simultaneously with the turbomachine. It is possible to divide the side channel, i.e. to choose the angular distances between the interrupters unevenly, so that different pressure / volume flows occur and therefore several consumers of different pressure / volume requirements can be supplied.
  • the turbomachine for gas compression shown in FIGS. 1 and 2 has an impeller 2 enclosed by a housing 1, which has on one end face 3 convexly curved radial blades 4 which continuously radially outwards into concave chamber blades 5 pass over.
  • the chamber blades 5 have an axially directed widening 7 relative to the dimensions of the outer end faces 6 of the radial blades 4, the widenings 7 being directed toward the suction side 8 of the turbomachine.
  • the housing 1 comprises a rear wall 9, in which the impeller 2 is mounted, a front wall 10 with an intake port 11 and a peripheral wall 12.
  • the housing 1, which in practice is made in several parts, is here simplified and shown in one piece.
  • a semicircular side channel 13 is formed in the housing front wall 10, the open side of which lies opposite the chamber blades 5.
  • the bottom 14 of each chamber 15 lying between two adjacent chamber blades 5 has the same radius of curvature as the side channel 13 in its radially outer region.
  • the chamber bottom 14 merges continuously into the end face 3 of the impeller 2 at each transition point between the chamber blades 5 and the radial blades 4, and the chambers 15 are each open to the flow channels S lying between two radial blades 4, cf. Openings 55.
  • the side channel 13 and the chambers 15 form a toroidal space and act as a side channel compressor which is fed by the radial compressor formed by the radial blades 4.
  • the ring diameter D of the toroidal side channel 13 is larger than the diameter d of the radial compressor formed by the radial blades 4.
  • FIG. 1 also shows an interrupter 16 which blocks the side channel at a circumferential point and which directs the gas flow in the side channel 13 in a direction antiparallel to the suction direction into a collecting space 17, to the outlet 18 of which a consumer is connected.
  • the radial blades 4 are covered on the side opposite the impeller 2 by a cover wall 19 fixed to the housing, which at the same time forms a chamber end wall 20 on the radially inner side of the widening 7 of the chamber blades 5.
  • the end wall 20 merges tangentially into the circular wall of the side channel 13.
  • the end face 3 of the impeller 2 is inclined conically in the region of the radial blades 4, the angle of inclination with respect to the impeller axis 21 being approximately 105 °.
  • the axial height h with which the radial blades 4 protrude beyond the end face 3 decreases continuously radially outwards.
  • the radial blades 4 protruding vertically or almost perpendicularly from the impeller 2 at their inner end 22 and the adjoining chamber blades 5 are increasingly inclined and spatially curved over their longitudinal extent relative to the end face 3 of the impeller 2, their free upper edge leading in the direction of rotation U. , see. Fig. 2.
  • the radial blades 4 and the chamber blades 5 each have opposite curvatures over their longitudinal extent, the point of curvature being at their transition point 23.
  • the radial blades 4 and the chamber blades 5 are each inclined by the same amount b in relation to the circumferential tangent T at the turning point.
  • the angle b is approximately 25 °.
  • every second radial blade is a shortened fragment blade 24 trained, which also continuously merge into a chamber blade 5.
  • Fig. 2 only one radial blade 4 with its subsequent chamber blade 5 is shown completely, while the remaining blades 4, 5, 24 are only shown by dash-dotted lines.
  • an interrupter 16 is arranged in the side channel 13, which is indicated schematically in FIG. 2 by two dashed lines.
  • the same impeller as in the exemplary embodiment according to FIGS. 1 and 2 is provided, but here the side channel 13 is interrupted at two diametrically opposite points by an interrupter 16, 25 each.
  • the position of the second interrupter 25 is indicated by dash-dotted lines in FIG. 2.
  • Both interrupters 16, 25 conduct the gas flow into a common annular collecting channel 26, to which a consumer can in turn be connected via the outlet 18.
  • FIG. 4 shows a modified embodiment of an impeller 27, in which two splitter blades 29 are arranged between two radial blades 28.
  • the angle of inclination b of the radial blades 28 or splitter blades 29 and the chamber blades 30 with respect to the circumferential tangent T in the transition region is approximately 15 ° here.
  • the longitudinal extension of the chamber blades 30 here is steeper against the circumferential direction than with the impeller according to FIG. 2.
  • FIG. 5 illustrates an impeller 31 in which two further chamber blades 34 are provided between two, relatively far apart radial blades 32 with a subsequent chamber blade 33; to which no radial blades are assigned.
  • FIG. 6 illustrates an embodiment of the turbomachine, in which the chamber blades 36 adjoining the radial blades 35 are directed toward the rear wall 37 of the housing opposite the suction side 8, in which the side channel 38 is formed.
  • the chambers lying between the chamber blades 36 are closed off from the outside by the housing peripheral wall 39 and to the inside by the impeller body 40.
  • the gas stream supplied by the radial vanes 35 is introduced in the direction of the longitudinal extent of the radial vanes 35 into the chambers and the side channel 38 of the side channel compressor, the gas flow undergoing a much smaller deflection than in the exemplary embodiment according to FIG. 1, where the gas flow when it enters is directed back into the side channel compressor.
  • the side channel 38 widens over its Continuously over the circumference, its smallest cross-section 41 being immediately behind the interrupter 42 and passing over a central cross-section 43 to its largest cross-section 44, which is immediately in front of the interrupter 42, as indicated by dashed lines in FIG. 6.
  • the outlet 18 of the turbomachine lies here on the rear side of the housing opposite the suction side 8. This embodiment is suitable for a multi-stage turbomachine in which several arrangements according to FIG. 6 are connected in series.
  • FIG. 7 shows an embodiment in which the chamber blades 45 protrude radially into a side channel 46.
  • the radial blades 47 and the widenings 48 of the chamber blades 45 are each covered here by a cover plate 49 of the impeller 50.
  • the chamber blades 45 which are rectangular in the view according to FIG. 7 form chambers which are open both radially outwards and in both axial directions towards the side channel 46.
  • the side channel 46 here surrounds the impeller 50 as a peripheral channel and is symmetrical to a diametral plane 51 which runs through the center of the axial extension of the chamber blade In 45.
  • An interrupter 52 engages around the chamber blades 45 on its three free sides and forwards the gas flow to an outlet 54 provided on the housing peripheral wall 53.
  • FIG. 8 shows a modification of the embodiment according to FIG. 7.
  • the flow channels S lying between radial blades 56 open here radially into a peripheral double-sided channel 57, which has two axially adjacent circulation spaces 58, 59, into which the chamber blades 60 each protrude in half, so that the volume flows supplied by the radial compressor are divided into two circulation flows 61, 62.
  • rounded flow formers 64, 65, 66 are formed on the housing wall 63 and on each half of the chamber blades 60, which constrict the double-sided channel 57 in the middle and extend the walls 67, 68 of the circulation spaces 58, 59, which are circular in cross section, in a streamlined manner.
  • the point of curvature between the convexly curved radial blades 4 and the concavely curved chamber blades 5 lies exactly on the outer circumference of the radial compressor, that is to say at the openings 55 according to FIG. 1.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
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Claims (17)

  1. Turbomachine à rotor de compresseur radial (2, 27,31, 40, 50) comprenant des aubes radiales (4, 28, 32, 35, 47) alimentant un compresseur à canal latéral qui comprend une couronne de chambres (15), qui sont séparées par des aubes de chambre (5, 30, 33, 36, 45) montées sur le rotor, le diamètre annulaire (D) du canal latéral (13, 38, 46) du compresseur à canal latéral étant égal ou supérieur au diamètre (d) de la partie de rotor (2, 27, 31, 40, 50) portant les aubes radiales (4, 28, 32, 35, 47), les chambres (15) étant munies, sur leur face délimitant sur les extrémités extérieures (6) les aubes radiales (4, 28, 32, 35, 47), d'ouvertures (55), et dans laquelle les aubes radiales (4, 28, 32, 35, 47) se prolongent en continu dans la direction d'écoulement par les aubes de chambres (5, 30, 33, 36, 45), caractérisée
    - en ce que la turbomachine est réalisée pour constituer un compresseur à gaz
    - en ce que les aubes de chambres (5) et les aubes radiales (4) présentent chacune des courbures de sens opposé, en ce que les aubes, de chambre (5) et les aubes radiales (4) présentent à leur point de transition (23) un point d'inflexion de courbure, et en ce que les aubes (4, 5) sont inclinées au point de transition (23), sensiblement du même angle (b) inférieur à 30°, par exemple de 15°, par rapport à la tangente (T), à la circonférence au point d'inflexion (23).
  2. Turbomachine selon la revendication 1, caractérisée en ce que les aubes radiales (4) et les aubes de chambre (5) qui suivent, partant à leur extrémité radiale intérieure (22) sensiblement à angle droit par rapport au rotor (2), sont inclinées par rapport au plan du rotor vers l'avant, c'est-à-dire dans le sens de rotation (U) du rotor, de façon croissante au cours de leur développement longitudinal.
  3. Turbomachine selon les revendications 1 et 2, caractérisée en ce que les aubes de chambre (5) comportant chacune un évasement (7) qui est orienté vers le canal latéral (13), et en ce que les chambres (15) sont fermées partiellement et radialement vers l'intérieur dans la zone de ces évasements (7), par une paroi d'extrémité (20).
  4. Turbomachine selon les revendications 1 à 3, caractérisée en ce que la hauteur (h) des aubes radiales (4) diminue radialement vers l'extérieur et en ce qu'est associé aux aubes radiales (4), sur leur face opposée au rotor (2), une paroi de couverture (19) du côté du carter ou un disque de couverture (49) formé sur le rotor (15), et en ce que la paroi de couverture (19) ou le disque de couverture (49), forme en même temps la paroi d'extrémité (20) des chambres (15) dans la zone des évasements (7, 48).
  5. Turbomachine selon l'une ou plusieurs des revendications 1 à 4, caractérisée en ce que la face frontale (3) du rotor (2) portant les aubes radiales (4) présente une forme conique et en ce que les aubes radiales (4) sont inclinées obliquement par rapport à l'axe (21) du rotor au cours de leur développement longitudinal.
  6. Turbomachine selon l'une ou plusieurs des revendications 1 à 5, caractérisée en ce que le canal latéral (13) est formé dans la paroi avant (10) du carter comportant le côté d'aspiration (8) du rotor, et est disposé axialement à côte des aubes de chambre (5) (figure 1).
  7. Turbomachine selon l'une ou plusieurs des revendications 1 à 5, caractérisée en ce que le canal latéral (38) est réalisé dans la paroi arrière de carter (37), opposée au côté d'aspiration (8) du rotor et est disposé axialement à côté des aubes de chambre (36) (figure 6).
  8. Turbomachine selon l'une ou plusieurs des revendications 1 à 5, caractérisée en ce que le canal latéral (46) est réalisé dans la paroi périphérique de carter (53) et en ce que les aubes de chambre (45) font saillie radialement vers l'extérieur dans le canal latéral (46) (figure 7).
  9. Turbomachine selon l'une ou plusieurs des revendications 1 à 8, caractérisée en ce que, dans le canal latéral (13) sont répartis plusieurs organes d'interruption (16, 25), à la périphérie selon un agencement compensant leur couple de basculement.
  10. Turbomachine selon la revendication 9, caractérisée en ce que, selon le cas, soit plusieurs organes d'interruption (16, 25) soit chaque organe d'interruption (16), est muni d'une sortie séparée (18), soit tous les organes d'interruption (16, 25) sont raccordés par un canal collecteur (26) de forme annulaire à une sortie commune (18).
  11. Turbomachine selon les revendications 9 ou 10, caractérisée en ce que le canal latéral (38) s'évase de façon continue entre la face arrière d'un organe d'interruption (42) et la face avant de l'organe d'interruption qui suit immédiatement
  12. Turbomachine selon l'une ou plusieurs des revendications 1 à 11, caractérisée en ce que les aubes radiales sont réalisées partiellement sous la forme d'aubes intercalaires (24; 29) raccourciese.
  13. Turbomachine selon l'une ou plusieurs des revendications 1 à 12, caractérisée en ce que, entre les aubes de chambre monobloc (33) munies des aubes radiales (32) sont prévues d'autres aubes de chambre séparées (34) sur le rotor (31).
  14. Turbomachine selon la revendication 8 et l'une ou plusieurs des revendications 9 à 13, caractérisée en ce que les canaux d'écoulement (S) disposés entre deux aubes radiales (56) débouchent radialement dans un canal latéral double périphérique (57) qui comporte deux espaces de circulation (58, 59), disposés l'un à côté de l'autre et dans lesquels les aubes de chambre (60) font saillie chacune par moitié.
  15. Turbomachine selon la revendication 14, caractérisée sur la paroi de carter (63) et sur les aubes de chambre (60) sont formés des organes arrondis d'orientation de l'écoulement (64, 65, 66), qui viennent étrangler au milieu le canal à double face (57) et qui séparent largement l'un de l'autre les deux espaces de circulation (58, 59).
  16. Turbomachine selon la revendication 1, caractérisée en ce que le point d'inflexion de courbure est disposé dans la zone de transition entre les aubes radiales (4) et les aubes de chambre (5).
  17. Turbomachine selon la revendication 1, caractérisée en ce que les aubes radiales (4) sont incurvées de façon convexe et les aubes de chambre (5) sont incurvées de façon concave.
EP93106279A 1992-04-27 1993-04-17 Machine à courant pour la compression d'un gaz Expired - Lifetime EP0567874B1 (fr)

Applications Claiming Priority (4)

Application Number Priority Date Filing Date Title
DE4213765 1992-04-27
DE4213765 1992-04-27
DE4230770 1992-09-15
DE4230770A DE4230770C2 (de) 1992-04-27 1992-09-15 Kreiselverdichter zur Gasverdichtung

Publications (2)

Publication Number Publication Date
EP0567874A1 EP0567874A1 (fr) 1993-11-03
EP0567874B1 true EP0567874B1 (fr) 1995-09-06

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EP93106279A Expired - Lifetime EP0567874B1 (fr) 1992-04-27 1993-04-17 Machine à courant pour la compression d'un gaz

Country Status (3)

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US (1) US5364228A (fr)
EP (1) EP0567874B1 (fr)
JP (1) JP3342914B2 (fr)

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US5527149A (en) * 1994-06-03 1996-06-18 Coltec Industries Inc. Extended range regenerative pump with modified impeller and/or housing
US6422808B1 (en) 1994-06-03 2002-07-23 Borgwarner Inc. Regenerative pump having vanes and side channels particularly shaped to direct fluid flow
ES2136963T3 (es) * 1996-02-21 1999-12-01 Esam Spa Maquina rotativa de soplido y succion.
US7267524B2 (en) * 2004-05-10 2007-09-11 Ford Motor Company Fuel pump having single sided impeller
US7008174B2 (en) * 2004-05-10 2006-03-07 Automotive Components Holdings, Inc. Fuel pump having single sided impeller
JP2006250017A (ja) * 2005-03-10 2006-09-21 Matsushita Electric Ind Co Ltd ポンプ及びそれを備えた液体供給装置
JP4801377B2 (ja) * 2005-05-31 2011-10-26 三菱重工業株式会社 ターボ圧縮機
EP3150805B1 (fr) * 2005-11-25 2020-09-23 BorgWarner, Inc. Aube de guidage de turbocompresseur à géométrie variable et turbocompresseur
US11359635B2 (en) * 2019-04-14 2022-06-14 Hamilton Sundstrand Corporation Power modules with regenerative compressor wheels

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JPH0610880A (ja) 1994-01-21
EP0567874A1 (fr) 1993-11-03
JP3342914B2 (ja) 2002-11-11
US5364228A (en) 1994-11-15

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