EP0774077B1 - Flow pump for use in pumping fuel from a reservoir to the engine of a motor vehicle - Google Patents

Flow pump for use in pumping fuel from a reservoir to the engine of a motor vehicle Download PDF

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Publication number
EP0774077B1
EP0774077B1 EP96900265A EP96900265A EP0774077B1 EP 0774077 B1 EP0774077 B1 EP 0774077B1 EP 96900265 A EP96900265 A EP 96900265A EP 96900265 A EP96900265 A EP 96900265A EP 0774077 B1 EP0774077 B1 EP 0774077B1
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EP
European Patent Office
Prior art keywords
impeller
blades
rotation
axis
flow pump
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
EP96900265A
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German (de)
French (fr)
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EP0774077B2 (en
EP0774077A1 (en
Inventor
Klaus Dobler
Michael Huebel
Willi Strohl
Jochen Rose
Bernhard Blaettel
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Robert Bosch GmbH
Original Assignee
Robert Bosch GmbH
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Application filed by Robert Bosch GmbH filed Critical Robert Bosch GmbH
Publication of EP0774077A1 publication Critical patent/EP0774077A1/en
Publication of EP0774077B1 publication Critical patent/EP0774077B1/en
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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
    • F04D5/00—Pumps with circumferential or transverse flow
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D5/00—Pumps with circumferential or transverse flow
    • F04D5/002—Regenerative pumps
    • 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
    • F04D29/18—Rotors
    • F04D29/188—Rotors specially for regenerative pumps

Definitions

  • the invention relates to a flow pump for conveying Fuel from a reservoir to the internal combustion engine of a motor vehicle according to the preamble of claim 1.
  • Such a flow pump is known from WO-A-92 00457.
  • This flow pump has a rotating one in a pump chamber Impeller on at least one axially directed Front a ring of circumferentially at a distance has wings arranged to each other.
  • the impeller with the Wing ring acts with an annular conveyor channel for conveying of the fuel together.
  • the wings are in contemplation radial direction with respect to the axis of rotation of the impeller parallel arranged to the axis of rotation of the impeller. Because of this arrangement the wing is not optimal in the known flow pump Delivery pressure and efficiency achieved.
  • a flow pump is known from US-A-1 689 579, at the impeller rotating in a pump chamber on its Frontal wreaths of wings with a annular conveyor channel for conveying a medium work together.
  • the blades of the impeller are radial Consideration of the axis of rotation of the impeller in relation to the Axis of rotation so inclined that it to the front of the Run ahead of the impeller in the direction of rotation of the impeller.
  • DE-A-1 403 575 is also a flow pump known in which the rotating impeller in a pump chamber its front sides has wreaths of wings, which with a annular conveyor channel for conveying a medium work together.
  • the blades of the impeller are radial Consideration of the axis of rotation of the impeller in relation to the Axis of rotation so inclined that it to the front of the Run ahead of the impeller in the direction of rotation of the impeller.
  • the flow pump according to the invention with the features according to Claim 1 has the advantage that the Formation of the wings with their radially outer ends opposite their radially inner ends in the circumferential direction of the Run ahead of the impeller, the delivery pressure and the efficiency are further improved.
  • FIG. 1 shows a flow pump for delivering fuel from a reservoir to the internal combustion engine Motor vehicle in a simplified representation
  • Figure 2 in Enlarged representation of a designated II in Figure 1 Section of the flow pump according to a first Embodiment
  • Figure 3 shows the impeller of the flow pump Figure 2 in a cross section perpendicular to its axis of rotation considered
  • Figure 4 shows the impeller of the flow pump in one Section along line IV-IV in Figure 3
  • Figure 5 the in Figure 1 II marked section of the flow pump according to a second embodiment
  • Figure 6 the impeller Flow pump of Figure 5 in a cross section perpendicular to considered the axis of rotation
  • Figure 7 shows the impeller Flow pump in a section along line VII-VII in Figure 6, FIG.
  • FIG. 8 the impeller of the flow pump according to a first Embodiment in a side view in the direction of viewed its axis of rotation
  • Figure 9 shows the impeller in one Section along line IX-IX in Figure 8
  • Figure 10 a modified version of the impeller of Figure 8
  • Figure 11 das Impeller of the flow pump according to a second Embodiment in a side view in the direction of considered its axis of rotation
  • Figure 12 the impeller in one Section along line XII-XII in Figure 11.
  • FIGS. 1-7 a generic flow pump described.
  • Figures 1-7 do not represent an embodiment of the invention.
  • FIG. 1 shows a simplified representation of an aggregate 10, the in a common housing 12 a flow pump 14 and a Drive motor 15 for the flow pump 14 includes.
  • the aggregate 10 is one in a fuel tank 16 Motor vehicle arranged and the flow pump 14 sucks during the operation of the unit 10 fuel from the Storage container 16 and conveys this via a pressure line 17 to the internal combustion engine 18 of the motor vehicle.
  • the Flow pump 14 has a rotating one in a pump chamber 20 Impeller 22, with the pump chamber 20 in the direction of Axis of rotation 24 of the impeller 22 through a chamber wall 25, 26 in each case is limited.
  • the flow pump 14 is shown in FIGS. 2 to 4 excerpts according to a first embodiment shown on the basis of which the structure as a so-called peripheral side channel pump is explained.
  • the impeller 22 has at its two axially, that is called end faces directed in the direction of its axis of rotation 24 28, 29 each have a ring in the circumferential direction of the impeller 22 wings 30 arranged at a distance from one another. Between Wings 30 are each groove-like spaces 31 and the wings 30 are essentially flat. The reason of the groove-like intermediate spaces 31 is the axis of rotation 24 containing longitudinal sections viewed through the impeller 22 rounded, for example in the form of a Circular section.
  • the wings 30 extend radially Direction with respect to the axis of rotation 24 of the impeller 22 from one radially inner end 30a to a radially outer end 30b on Outer periphery of the impeller 22.
  • the wing rings of the two end faces 28, 29 approximately in the middle the axial width of the impeller 22 separating web 33 up to the end faces 28, 29 of the impeller 22.
  • the wing rings of the impeller 22 act with one in the Pump chamber 20 formed annular delivery channel 34 for Pumping fuel together. Open into the delivery channel 34 the beginning of which has a suction opening 35 and at the end of which one Pressure port 36. The fuel to be pumped flows through the Suction opening 35 into the delivery channel 34 and flows out of this under increased pressure through the pressure opening 36.
  • the Delivery channel 34 extends in the radial direction with respect to Axis of rotation 24 of the impeller 22 starting from the radially inner Ends 30a of the wings 30 to beyond their radially outer ends 30b out. Extends in the direction of the axis of rotation 24 of the impeller 22 the delivery channel 34 each over the end faces 28, 29 of the Impeller 22 addition.
  • the delivery channel 34 is thus in the direction of Axis of rotation 24 of the impeller 22 laterally next to the blades 30 arranged and also extends over the outer circumference of the Impeller 22.
  • the wings 30 are so inclined placed arranged that this starting from the web 33 to respective end faces 28, 29 at which the wings 30 end, Lead ahead in the direction of rotation 21 of the impeller 22.
  • the wing 30 is not parallel to the axis of rotation 24 of the impeller 22 are arranged, that is at right angles to the respective end face 28, 29, but with the axis of rotation 24 one in the circumferential direction 21 of the impeller 22 include directed angle ⁇ .
  • the angle ⁇ is between 25 ° and 60 °, preferably between 30 ° and 55 °. Due to this inclination of the wings 30, these are approximately parallel to that indicated by the arrows 40 in FIG.
  • the flow pump 14 is according to one shown second embodiment, based on which the structure as a so-called Side channel pump is explained.
  • the impeller 122 instructs its two axially directed end faces 128, 129 each a ring in the circumferential direction of the impeller 122 at a distance wings 130 arranged to each other, between each of which groove-like spaces 131 are present.
  • the wings 130 of the two end faces 128, 129 of the impeller 122 are through one Web 133 in the direction of the axis of rotation 24 of the impeller 122 viewed separately from each other and are at their radially outer Ends 130b together by a closed ring 140 connected.
  • the web 133 can in the radial direction with respect to the The axis of rotation 24 of the impeller 122 must be continuous, so that the two end faces 128, 129 of the impeller 122 completely are separated from one another, or the web 133 can be radial Direction end in front of the ring 140, so that between web 133 and Ring 140 in the area of the spaces 131 each have an opening 142 remains through which the two end faces 128, 129 of the Impeller 122 are connected.
  • Chamber walls 125, 126 are each an annular delivery channel 144 and 145 are formed, the delivery channels 144, 145 the respective wreath of wings 130 in the end faces 128, 129 of the Impeller 122 are formed opposite.
  • Delivery channel 144 opens at the beginning of the suction opening 135 and in the other conveyor channel 145 opens at the end of the Pressure opening 136.
  • the two delivery channels 144, 145 have the outer circumference of the impeller 122, that is, over the outer circumference of the ring 140 no connection with each other.
  • the wings 130 are as described in the first embodiment according to FIG 7 arranged so inclined that they start from Web 133 to the respective end face 128, 129, on which the Blade 130 ends, in the direction of rotation 21 of the impeller 122 hurry ahead.
  • the angle ⁇ is between 25 ° and 60 °, preferably between 30 ° and 55 °.
  • the impeller 222 is the flow pump 14 shown according to a first embodiment.
  • the Flow pump 14 is like the second embodiment designed as a side channel pump and there are the two in figure 5 visible delivery channels available, each with the Wing ring of an end face of the impeller 222 with a Conveyor channel interacts.
  • the impeller 222 points to its two axially directed end faces 228, 229 each have a ring of spaced apart in the circumferential direction Wings 230, between each of which groove-like spaces 23i are present, the base of which is rounded, for example in the form a circular section is formed.
  • the wings 230 are on their radially outer ends 230b with one another via a ring 240 connected.
  • edges 232 of the wings 230 with which these do not end at the respective end face 228, 229 of the impeller arranged radially with respect to the axis of rotation 24 of the impeller 222, rather, the edges 232 run at the radially outer ends 230b the wing 230 opposite its arrangement on the radially inner Ends 230a of the blades 230 in the circumferential direction 21 of the impeller 222 ahead.
  • the edges 232 of the wings 230 on the respective Front side 228, 229 of the impeller 222 extend from the radially inner ends 230a of wings 230 to the radially outer ones Ends 230b of the wings 230 rectilinear.
  • the wings 230 are also arranged so that they start in the circumferential direction from the web 233 separating the wings 230 of the two end faces 228, 229 from one another to the respective end face 228, 229 at which the wings 230 end Lead ahead 21 of impeller 222.
  • the vanes 230 are not arranged parallel to the axis of rotation 24 of the impeller 222, but instead form an angle ⁇ directed in the direction of rotation 21 of the impeller 222 with the axis of rotation 24.
  • the angle ⁇ is not constant over the course of the vanes 230 starting from their radially inner end 230a to their radially outer end 230b.
  • the vanes 230 on the respective end face 228, 229 of the impeller 222 with the axis of rotation 24 form an angle ⁇ E directed in the circumferential direction 21 of the impeller 222, which is between 25 ° and 50 °, in particular between 30 ° and 45 ° is.
  • the angle ⁇ E is preferably approximately 37 °.
  • the vanes 230 on the respective end face 228, 229 of the impeller 222 with the axis of rotation 24 form an angle ⁇ A directed in the circumferential direction 21 of the impeller 222, which is between 45 ° and 70 °, in particular between 50 ° and 65 °.
  • the angle ⁇ A is preferably approximately 60 °. Starting from the radially inner ends 230a of the vanes 230, the angle ⁇ increases linearly towards their radially outer ends 230b. This increase in the angle ⁇ starting from the radially inner ends 230a of the vanes 230 to their radially outer ends 230b results in the above-described arrangement of the edges 232 of the vanes 230 in the circumferential direction 21 of the impeller 222 by the angle ⁇
  • the inner ends of web 233 are arranged in the cross section perpendicular to the axis of rotation 24 of the impeller 222, viewed approximately radially with respect to the axis of rotation 24, and are therefore not inclined as on their edge 232 located on the end face.
  • FIG. 10 shows a variant of the impeller 322 Flow pump according to the first embodiment in one Side view shown.
  • the impeller 322 is in the essentially the same as the first Embodiment, however, runs the edge 332 with which the Vane 330 does not end at the front of impeller 322 straight but curved.
  • edge 332 is approximately radial with respect to FIG Axis of rotation 24 of the impeller 322 and the edge 332 extends to the radially outer ends 330b of the wings 330 continuously increasing in the direction of rotation 21 of the impeller 322.
  • the angle ⁇ is the wing 330 with the Include axis of rotation 24 of the impeller 322 starting from the radially inner ends 330a of the wings 330 to their radially outer ends Ends 330b larger.
  • the increase in the size of the angle ⁇ is not linear as in the first embodiment but reinforces to the radially outer ends 330b of FIG Wing 330 back.
  • the inner ends of the wings 330 are perpendicular in cross section viewed approximately radially to the axis of rotation 24 of the impeller 322 with respect to the axis of rotation 24, so they are not as at their on Front edge 332 curved.
  • the impeller 422 is the flow pump 14 according to a second embodiment.
  • the Flow pump 14 is a peripheral side channel pump trained and has a conveyor channel as in the first Embodiment shown in Figure 2.
  • the impeller 422 has 428,429 on its two axially directed end faces in each case a wreath at a distance in the circumferential direction wings 430 arranged to each other, between each of which Spaces 431 are present.
  • the wings 430 extend in the radial direction with respect to the axis of rotation 24 of the impeller 422 from a radially inner end 430a to a radially outer end End 430b on the outer circumference of the impeller 422.
  • the axes of rotation 24 of the impeller 422 extend the blades 430 starting from one the wreaths of the two faces 428,429 approximately in the middle of the axial width of the impeller 422 separating web 433 up to the end faces 428,429 of the impeller 422.
  • the vanes 430 are as in the above described embodiments so inclined arranged that these starting from the web 433 to the respective End face 428,429, on which the wings 430 end, in Lead ahead in the direction of rotation 21 of the impeller 422. This means, that the wing 430 is not parallel to the axis of rotation 24 of the impeller 422 are arranged, but with the axis of rotation 24 one in Direction of rotation 21 of the impeller 422 directed angle ⁇ lock in.
  • the angle ⁇ is between 25 ° and 50 °, especially between 30 ° and 45 °.
  • The is preferably Angle ⁇ about 37 °.
  • the angle ⁇ is over the radial extent the wing 430, that is between its radially inner ends 430a and their radially outer ends 430b approximately constant.
  • the wings 430 extend in the direction of the axis of rotation 24 of the impeller 422 viewed between their radially inner ends 430a and hers radially outer ends 430b curved, but can be at a other version also run in a straight line.
  • the radially inner ends 430a initially run approximately 430 radially with respect to the axis of rotation 24 of the impeller 422 and to the latter radially outer ends 430b take the curvature, that is, the Deviation from the radial arrangement too.
  • the wings 430 In the area of their radially outer ends 430b close the wings 430 with one Axis of rotation 24 of the impeller 422 radial line 450 through the the radially outer ends 430b of the wing 430 is placed one in Direction of rotation 21 directed angle ⁇ .
  • the angle is ⁇ between 30 ° and 60 °, in particular between 40 ° and 55 °.
  • the angle ⁇ is preferably approximately 45 °.
  • the arrangement of the wings 430 is necessary because a peripheral side channel pump the fuel to be pumped like a side channel pump in the radial area inner ends 430a of wings 430 into spaces 431 enters, but exits radially outwards.
  • the wings 430 are in cross section perpendicular to the axis of rotation 24 of the impeller 422 viewed in the area of its inner arranged on the web 433 Ends are also curved in the circumferential direction 21 as at the end faces 428, 429 of the impeller 422.

Description

Die Erfindung betrifft eine Strömungspumpe zum Fördern von Kraftstoff aus einem Vorratsbehälter zur Brennkraftmaschine eines Kraftfahrzeugs nach der Gattung des Anspruchs 1.The invention relates to a flow pump for conveying Fuel from a reservoir to the internal combustion engine of a motor vehicle according to the preamble of claim 1.

Eine solche Strömungpumpe ist durch die WO-A-92 00457 bekannt. Diese Strömungspumpe weist ein in einer Pumpenkammer umlaufendes Laufrad auf, das an wenigstens einer axial gerichteten Stirnseite einen Kranz von in Umfangsrichtung mit Abstand zueinander angeordneten Flügeln aufweist. Das Laufrad mit dem Flügelkranz wirkt mit einem ringförmigen Förderkanal zum Fördern des Kraftstoffs zusammen. Die Flügel sind bei Betrachtung in radialer Richtung bezüglich der Drehachse des Laufrads parallel zur Drehachse des Laufrads angeordnet. Aufgrund dieser Anordnung der Flügel wird bei der bekannten Strömungspumpe kein optimaler Förderdruck und Wirkungsgrad erreicht.Such a flow pump is known from WO-A-92 00457. This flow pump has a rotating one in a pump chamber Impeller on at least one axially directed Front a ring of circumferentially at a distance has wings arranged to each other. The impeller with the Wing ring acts with an annular conveyor channel for conveying of the fuel together. The wings are in contemplation radial direction with respect to the axis of rotation of the impeller parallel arranged to the axis of rotation of the impeller. Because of this arrangement the wing is not optimal in the known flow pump Delivery pressure and efficiency achieved.

Durch die US-A-1 689 579 ist eine Strömungspumpe bekannt, bei der das in einer Pumpenkammer umlaufende Laufrad an seinen Stirnseiten Kränze von Flügeln aufweist, die mit einem ringförmigen Förderkanal zum Fördern eines Mediums zusammenwirken. Die Flügel des Laufrads sind bei radialer Betrachtung bezüglich der Drehachse des Laufrads bezogen auf die Drehachse derart schräggestellt, daß sie zur Stirnseite des Laufrads hin in Umlaufrichtung des Laufrads vorauseilen. Durch diese Ausbildung der Flügel des Laufrads ist der Förderdruck und der Wirkungsgrad der Strömungspumpe verbessert, jedoch weiterhin nicht optimal.A flow pump is known from US-A-1 689 579, at the impeller rotating in a pump chamber on its Frontal wreaths of wings with a annular conveyor channel for conveying a medium work together. The blades of the impeller are radial Consideration of the axis of rotation of the impeller in relation to the Axis of rotation so inclined that it to the front of the Run ahead of the impeller in the direction of rotation of the impeller. By this design of the blades of the impeller is the delivery pressure and the efficiency of the flow pump improved, but still not optimal.

Durch die DE-A-1 403 575 ist ebenfalls eine Strömungspumpe bekannt, bei der das in einer Pumpenkammer umlaufende Laufrad an seinen Stirnseiten Kränze von Flügeln aufweist, die mit einem ringförmigen Förderkanal zum Fördern eines Mediums zusammenwirken. Die Flügel des Laufrads sind bei radialer Betrachtung bezüglich der Drehachse des Laufrads bezogen auf die Drehachse derart schräggestellt, daß sie zur Stirnseite des Laufrads hin in Umlaufrichtung des Laufrads vorauseilen. DE-A-1 403 575 is also a flow pump known in which the rotating impeller in a pump chamber its front sides has wreaths of wings, which with a annular conveyor channel for conveying a medium work together. The blades of the impeller are radial Consideration of the axis of rotation of the impeller in relation to the Axis of rotation so inclined that it to the front of the Run ahead of the impeller in the direction of rotation of the impeller.

Vorteile der ErfindungAdvantages of the invention

Die erfindungsgemäße Strömungspumpe mit den Merkmalen gemäß Anspruch 1 hat demgegenüber den Vorteil, daß durch die Ausbildung der Flügel, die mit ihren radial äußeren Enden gegenüber ihren radial inneren Enden in Umlaufrichtung des Laufrads vorauseilen, der Förderdruck und der Wirkungsgrad weiter verbessert sind.The flow pump according to the invention with the features according to Claim 1 has the advantage that the Formation of the wings with their radially outer ends opposite their radially inner ends in the circumferential direction of the Run ahead of the impeller, the delivery pressure and the efficiency are further improved.

In den abhängigen Ansprüchen sind vorteilhafte Ausgestaltungen und Weiterbildungen der erfindungsgemäßen Strömungspumpe angegeben. Eine weitere Steigerung von Förderdruck und Wirkungsgrad der Strömungspumpe ist durch die Merkmale gemäß Anspruch 4 ermöglicht. Advantageous embodiments are in the dependent claims and further developments of the flow pump according to the invention specified. A further increase in delivery pressure and Efficiency of the flow pump is according to the characteristics Claim 4 enables.

Zeichnungdrawing

Mehrere Ausführungsbeispiele der Erfindung sind in der Zeichnung dargestellt und in der nachfolgenden Beschreibung erläutert. Es zeigen Figur 1 eine Strömungspumpe zum Fördern von Kraftstoff aus einem Vorratsbehälter zur Brennkraftmaschine eines Kraftfahrzeugs in vereinfachter Darstellung, Figur 2 in vergrößerter Darstellung einen in Figur 1 mit II bezeichneten Ausschnitt der Strömungspumpe gemäß einer ersten Ausführungsform, Figur 3 das Laufrad der Strömungspumpe von Figur 2 in einem Querschnitt senkrecht zu dessen Drehachse betrachtet, Figur 4 das Laufrad der Strömungspumpe in einem Schnitt entlang Linie IV-IV in Figur 3, Figur 5 den in Figur 1 mit II bezeichneten Ausschnitt der Strömungspumpe gemäß einer zweiten Ausführungsform, Figur 6 das Laufrad der Strömungspumpe von Figur 5 in einem Querschnitt senkrecht zu dessen Drehachse betrachtet, Figur 7 das Laufrad der Strömungspumpe in einem Schnitt entlang Linie VII-VII in Figur 6, Figur 8 das Laufrad der Strömungspumpe gemäß einem ersten Ausführungsbeispiel in einer Seitenansicht in Richtung von dessen Drehachse betrachtet, Figur 9 das Laufrad in einem Schnitt entlang Linie IX-IX in Figur 8, Figur 10 eine modifizierte Ausführung des Laufrads von Figur 8, Figur 11 das Laufrad der Strömungspumpe gemäß einem zweiten Ausführungsbeispiel in einer Seitenansicht in Richtung von dessen Drehachse betrachtet und Figur 12 das Laufrad in einem Schnitt entlang Linie XII-XII in Figur 11.Several embodiments of the invention are in the drawing shown and explained in the following description. It 1 shows a flow pump for delivering fuel from a reservoir to the internal combustion engine Motor vehicle in a simplified representation, Figure 2 in Enlarged representation of a designated II in Figure 1 Section of the flow pump according to a first Embodiment, Figure 3 shows the impeller of the flow pump Figure 2 in a cross section perpendicular to its axis of rotation considered, Figure 4 shows the impeller of the flow pump in one Section along line IV-IV in Figure 3, Figure 5 the in Figure 1 II marked section of the flow pump according to a second embodiment, Figure 6, the impeller Flow pump of Figure 5 in a cross section perpendicular to considered the axis of rotation, Figure 7 shows the impeller Flow pump in a section along line VII-VII in Figure 6, FIG. 8 the impeller of the flow pump according to a first Embodiment in a side view in the direction of viewed its axis of rotation, Figure 9 shows the impeller in one Section along line IX-IX in Figure 8, Figure 10 a modified version of the impeller of Figure 8, Figure 11 das Impeller of the flow pump according to a second Embodiment in a side view in the direction of considered its axis of rotation and Figure 12 the impeller in one Section along line XII-XII in Figure 11.

Beschreibung der AusführungsbeispieleDescription of the embodiments

Anhand der Figuren 1-7 wird zunächst der grundsätzliche Aufbau einer gattungsgemäßen Strömungspumpe beschrieben. Die Figuren 1-7 stellen keine Ausführungsform der Erfindung dar.The basic structure is shown first with reference to FIGS. 1-7 a generic flow pump described. Figures 1-7 do not represent an embodiment of the invention.

Figur 1 zeigt in vereinfachter Darstellung eine Aggregat 10, das in einem gemeinsamen Gehäuse 12 eine Strömungspumpe 14 und einen Antriebsmotor 15 für die Strömungspumpe 14 umfaßt. Das Aggregat 10 ist in einem Kraftstoffvorratsbehälter 16 eines Kraftfahrzeugs angeordnet und die Strömungspumpe 14 saugt während des Betriebs des Aggregats 10 Kraftstoff aus dem Vorratsbehälter 16 an und fördert diesen über eine Druckleitung 17 zur Brennkraftmaschine 18 des Kraftfahrzeugs. Die Strömungspumpe 14 weist ein in einer Pumpenkammer 20 umlaufendes Laufrad 22 auf, wobei die Pumpenkammer 20 in Richtung der Drehachse 24 des Laufrads 22 durch jeweils eine Kammerwand 25,26 begrenzt ist.Figure 1 shows a simplified representation of an aggregate 10, the in a common housing 12 a flow pump 14 and a Drive motor 15 for the flow pump 14 includes. The aggregate 10 is one in a fuel tank 16 Motor vehicle arranged and the flow pump 14 sucks during the operation of the unit 10 fuel from the Storage container 16 and conveys this via a pressure line 17 to the internal combustion engine 18 of the motor vehicle. The Flow pump 14 has a rotating one in a pump chamber 20 Impeller 22, with the pump chamber 20 in the direction of Axis of rotation 24 of the impeller 22 through a chamber wall 25, 26 in each case is limited.

In den Figuren 2 bis 4 ist die Strömungspumpe 14 ausschnittsweise gemäß einer ersten Ausführungsform dargestellt anhand derer der Aufbau als sogenannte Peripheral-Seitenkanalpumpe erläutert wird. Das Laufrad 22 weist an seinen beiden axial, das heißt in Richtung seiner Drehachse 24 gerichteten Stirnseiten 28,29 jeweils einen Kranz von in Umfangsrichtung des Laufrads 22 mit Abstand zueinander angeordneten Flügeln 30 auf. Zwischen den Flügeln 30 sind jeweils nutartige Zwischenräume 31 vorhanden und die Flügel 30 sind im wesentlichen eben ausgebildet. Der Grund der nutartigen Zwischenräume 31 ist in den die Drehachse 24 enthaltenden Längsschnitten durch das Laufrad 22 betrachtet gerundet ausgebildet, beispielsweise in Form eines Kreisabschnitts. Die Flügel 30 erstrecken sich in radialer Richtung bezüglich der Drehachse 24 des Laufrads 22 von einem radial inneren Ende 30a bis zu einem radial äußeren Ende 30b am Außenumfang des Laufrads 22. In Richtung der Drehachse 24 des Laufrads 22 erstrecken sich die Flügel 30 ausgehend von einem die Flügelkränze der beiden Stirnseiten 28,29 etwa in der Mitte der axialen Breite des Laufrads 22 voneinander trennenden Steg 33 bis zu den Stirnseiten 28,29 des Laufrads 22.The flow pump 14 is shown in FIGS. 2 to 4 excerpts according to a first embodiment shown on the basis of which the structure as a so-called peripheral side channel pump is explained. The impeller 22 has at its two axially, that is called end faces directed in the direction of its axis of rotation 24 28, 29 each have a ring in the circumferential direction of the impeller 22 wings 30 arranged at a distance from one another. Between Wings 30 are each groove-like spaces 31 and the wings 30 are essentially flat. The reason of the groove-like intermediate spaces 31 is the axis of rotation 24 containing longitudinal sections viewed through the impeller 22 rounded, for example in the form of a Circular section. The wings 30 extend radially Direction with respect to the axis of rotation 24 of the impeller 22 from one radially inner end 30a to a radially outer end 30b on Outer periphery of the impeller 22. In the direction of the axis of rotation 24 of the Impeller 22 extend from a wing 30 the wing rings of the two end faces 28, 29 approximately in the middle the axial width of the impeller 22 separating web 33 up to the end faces 28, 29 of the impeller 22.

Die Flügelkränze des Laufrads 22 wirken mit einem in der Pumpenkammer 20 ausgebildeten ringförmigen Förderkanal 34 zum Fördern von Kraftstoff zusammen. In den Förderkanal 34 münden an dessen Anfang eine Saugöffnung 35 und an dessen Ende eine Drucköffnung 36. Der zu fördernde Kraftstoff strömt durch die Saugöffnung 35 in den Förderkanal 34 ein und strömt aus diesem unter erhöhtem Druck durch die Drucköffnung 36 ab. Der Förderkanal 34 erstreckt sich in radialer Richtung bezüglich der Drehachse 24 des Laufrads 22 ausgehend von den radial inneren Enden 30a der Flügel 30 bis über deren radial äußere Enden 30b hinaus. In Richtung der Drehachse 24 des Laufrads 22 erstreckt sich der Förderkanal 34 jeweils über die Stirnseiten 28,29 des Laufrads 22 hinaus. Der Förderkanal 34 ist somit in Richtung der Drehachse 24 des Laufrads 22 seitlich neben den Flügeln 30 angeordnet und erstreckt sich außerdem über den Außenumfang des Laufrads 22.The wing rings of the impeller 22 act with one in the Pump chamber 20 formed annular delivery channel 34 for Pumping fuel together. Open into the delivery channel 34 the beginning of which has a suction opening 35 and at the end of which one Pressure port 36. The fuel to be pumped flows through the Suction opening 35 into the delivery channel 34 and flows out of this under increased pressure through the pressure opening 36. The Delivery channel 34 extends in the radial direction with respect to Axis of rotation 24 of the impeller 22 starting from the radially inner Ends 30a of the wings 30 to beyond their radially outer ends 30b out. Extends in the direction of the axis of rotation 24 of the impeller 22 the delivery channel 34 each over the end faces 28, 29 of the Impeller 22 addition. The delivery channel 34 is thus in the direction of Axis of rotation 24 of the impeller 22 laterally next to the blades 30 arranged and also extends over the outer circumference of the Impeller 22.

Die Flügel 30 sind, wie in Figur 4 deutlich wird, derart schräg gestellt angeordnet, daß diese ausgehend vom Steg 33 zur jeweiligen Stirnseite 28,29 hin, an denen die Flügel 30 enden, in Umlaufrichtung 21 des Laufrads 22 vorauseilen. Dies bedeutet, daß die Flügel 30 nicht parallel zur Drehachse 24 des Laufrads 22 angeordnet sind, also rechtwinklig zur jeweiligen Stirnseite 28,29, sondern mit der Drehachse 24 einen in Umlaufrichtung 21 des Laufrads 22 gerichteten Winkel α einschließen. Der Winkel α beträgt zwischen 25° und 60°, vorzugsweise zwischen 30° und 55°. Durch diese Schrägstellung der Flügel 30 sind diese etwa parallel zur in Figur 4 durch die Pfeile 40 angedeuteten Relativströmung des in die Zwischenräume 31 zwischen den Flügeln 30 einströmenden Kraftstoffs angeordnet, wodurch an den entgegen der Umlaufrichtung 21 des Laufrads 22 weisenden Rückseiten der Flügel 30 ein Abreißen der Strömung und somit eine Wirbelbildung vermieden wird. Es werden dadurch die sogenannten Stoßverluste eliminiert und eine Erhöhung des Zirkulationsstroms erzielt, der für den fluidmechanischen Energietransport zwischen Laufrad 22 und Förderkanal 34 verantwortlich ist. As is clear in FIG. 4, the wings 30 are so inclined placed arranged that this starting from the web 33 to respective end faces 28, 29 at which the wings 30 end, Lead ahead in the direction of rotation 21 of the impeller 22. This means, that the wing 30 is not parallel to the axis of rotation 24 of the impeller 22 are arranged, that is at right angles to the respective end face 28, 29, but with the axis of rotation 24 one in the circumferential direction 21 of the impeller 22 include directed angle α. The angle α is between 25 ° and 60 °, preferably between 30 ° and 55 °. Due to this inclination of the wings 30, these are approximately parallel to that indicated by the arrows 40 in FIG. 4 Relative flow of the in the spaces 31 between the wings 30 inflowing fuel arranged, thereby counter to the the circumferential direction 21 of the impeller 22 facing rear sides of the Wing 30 a break in the flow and thus a vortex formation is avoided. This results in the so-called shock losses eliminated and an increase in the circulation flow achieved for fluid mechanical energy transport between impeller 22 and conveyor channel 34 is responsible.

In den Figuren 5 bis 7 ist die Strömungspumpe 14 gemäß einer zweiten Ausführungsform dargestellt, anhand derer der Aufbau als sogenannte Seitenkanalpumpe erläutert wird. Das Laufrad 122 weist dabei an seinen beiden axial gerichteten Stirnseiten 128,129 jeweils einen Kranz von in Umfangsrichtung des Laufrads 122 mit Abstand zueinander angeordneten Flügeln 130 auf, zwischen denen jeweils nutartige Zwischenräume 131 vorhanden sind. Die Flügel 130 der beiden Stirnseiten 128,129 des Laufrads 122 sind durch einen Steg 133 in Richtung der Drehachse 24 des Laufrads 122 betrachtet voneinander getrennt und sind an ihren radial äußeren Enden 130b durch einen geschlossenen Ring 140 miteinander verbunden. Der Steg 133 kann in radialer Richtung bezüglich der Drehachse 24 des Laufrads 122 durchgehend ausgebildet sein, so daß die beiden Stirnseiten 128,129 des Laufrads 122 völlig voneinander getrennt sind, oder der Steg 133 kann in radialer Richtung vor dem Ring 140 enden, so daß zwischen Steg 133 und Ring 140 im Bereich der Zwischenräume 131 jeweils eine Öffnung 142 verbleibt, durch die die beiden Stirnseiten 128,129 des Laufrads 122 miteinander in Verbindung stehen.In Figures 5 to 7, the flow pump 14 is according to one shown second embodiment, based on which the structure as a so-called Side channel pump is explained. The impeller 122 instructs its two axially directed end faces 128, 129 each a ring in the circumferential direction of the impeller 122 at a distance wings 130 arranged to each other, between each of which groove-like spaces 131 are present. The wings 130 of the two end faces 128, 129 of the impeller 122 are through one Web 133 in the direction of the axis of rotation 24 of the impeller 122 viewed separately from each other and are at their radially outer Ends 130b together by a closed ring 140 connected. The web 133 can in the radial direction with respect to the The axis of rotation 24 of the impeller 122 must be continuous, so that the two end faces 128, 129 of the impeller 122 completely are separated from one another, or the web 133 can be radial Direction end in front of the ring 140, so that between web 133 and Ring 140 in the area of the spaces 131 each have an opening 142 remains through which the two end faces 128, 129 of the Impeller 122 are connected.

In den den Stirnseiten 128,129 des Laufrads 122 zugewandten Kammerwänden 125,126 ist jeweils ein ringförmiger Förderkanal 144 bzw. 145 ausgebildet, wobei die Förderkanäle 144,145 dem jeweiligen Kranz der Flügel 130 in den Stirnseiten 128,129 des Laufrads 122 gegenüberliegend ausgebildet sind. In den einen Förderkanal 144 mündet an dessen Anfang die Saugöffnung 135 und in den anderen Förderkanal 145 mündet an dessen Ende die Drucköffnung 136. Die beiden Förderkanäle 144,145 weisen über den Außenumfang des Laufrads 122, das heißt über den Außenumfang des Rings 140 keine Verbindung miteinander auf. Die Flügel 130 sind wie bei der ersten Ausführungsform beschrieben gemäß Figur 7 derart schräg gestellt angeordnet, daß diese ausgehend vom Steg 133 zur jeweiligen Stirnseite 128,129 hin, an denen die Flügel 130 enden, in Umlaufrichtung 21 des Laufrads 122 vorauseilen. Dies bedeutet, daß die Flügel 130 nicht parallel zur Drehachse 24 des Laufrads 122 angeordnet sind, sondern mit der Drehachse 24 einen in Umlaufrichtung 21 des Laufrads 122 gerichteten Winkel α einschließen. Der Winkel α beträgt zwischen 25° und 60°, vorzugsweise zwischen 30° und 55°.In the faces 128, 129 of the impeller 122 Chamber walls 125, 126 are each an annular delivery channel 144 and 145 are formed, the delivery channels 144, 145 the respective wreath of wings 130 in the end faces 128, 129 of the Impeller 122 are formed opposite. In one Delivery channel 144 opens at the beginning of the suction opening 135 and in the other conveyor channel 145 opens at the end of the Pressure opening 136. The two delivery channels 144, 145 have the outer circumference of the impeller 122, that is, over the outer circumference of the ring 140 no connection with each other. The wings 130 are as described in the first embodiment according to FIG 7 arranged so inclined that they start from Web 133 to the respective end face 128, 129, on which the Blade 130 ends, in the direction of rotation 21 of the impeller 122 hurry ahead. This means that the wings 130 are not parallel are arranged to the axis of rotation 24 of the impeller 122, but with the axis of rotation 24 one in the circumferential direction 21 of the impeller 122 include directed angle α. The angle α is between 25 ° and 60 °, preferably between 30 ° and 55 °.

In den Figuren 8 und 9 ist das Laufrad 222 der Strömungspumpe 14 gemäß einem ersten Ausführungsbeispiel dargestellt. Die Strömungspumpe 14 ist dabei wie bei der zweiten Ausführungsform als Seitenkanalpumpe ausgebildet und es sind die beiden in Figur 5 ersichtlichen Förderkanäle vorhanden, wobei jeweils der Flügelkranz einer Stirnseite des Laufrads 222 mit einem Förderkanal zusammenwirkt. Das Laufrad 222 weist an seinen beiden axial gerichteten Stirnseiten 228,229 jeweils einen Kranz von in Umfangsrichtung mit Abstand zueinander angeordneten Flügeln 230 auf, zwischen denen jeweils nutartige Zwischenräume 23i vorhanden sind, deren Grund gerundet, beispielsweise in Form eines Kreisabschnitts ausgebildet ist. Die Flügel 230 sind an ihren radial äußeren Enden 230b über einen Ring 240 miteinander verbunden. In der Seitenansicht des Laufrads 222 gemäß Figur 8 betrachtet sind die Kanten 232 der Flügel 230, mit denen diese an der jeweiligen Stirnseite 228,229 des Laufrads enden, nicht radial bezüglich der Drehachse 24 des Laufrads 222 angeordnet, sondern die Kanten 232 eilen an den radial äußeren Enden 230b der Flügel 230 gegenüber ihrer Anordnung an den radial inneren Enden 230a der Flügel 230 in Umlaufrichtung 21 des Laufrads 222 voraus. Die Kanten 232 der Flügel 230 an der jeweiligen Stirnseite 228,229 des Laufrads 222 verlaufen ausgehend von den radial inneren Enden 230a der Flügel 230 zu den radial äußeren Enden 230b der Flügel 230 geradlinig. Bezogen auf eine durch die Mitte der Kanten 232 am radial inneren Ende 230a der Flügel 230 gelegte bezüglich der Drehachse 24 des Laufrads 222 radiale Linie 250 sind die Kanten 232 um einen Winkel β in Umlaufrichtung 21 des Laufrads 222 geneigt angeordnet. Der Winkel β beträgt zwischen 20° und 45°, vorzugsweise zwischen 25° und 40°. In FIGS. 8 and 9, the impeller 222 is the flow pump 14 shown according to a first embodiment. The Flow pump 14 is like the second embodiment designed as a side channel pump and there are the two in figure 5 visible delivery channels available, each with the Wing ring of an end face of the impeller 222 with a Conveyor channel interacts. The impeller 222 points to its two axially directed end faces 228, 229 each have a ring of spaced apart in the circumferential direction Wings 230, between each of which groove-like spaces 23i are present, the base of which is rounded, for example in the form a circular section is formed. The wings 230 are on their radially outer ends 230b with one another via a ring 240 connected. In the side view of the impeller 222 according to FIG. 8 considered are the edges 232 of the wings 230 with which these do not end at the respective end face 228, 229 of the impeller arranged radially with respect to the axis of rotation 24 of the impeller 222, rather, the edges 232 run at the radially outer ends 230b the wing 230 opposite its arrangement on the radially inner Ends 230a of the blades 230 in the circumferential direction 21 of the impeller 222 ahead. The edges 232 of the wings 230 on the respective Front side 228, 229 of the impeller 222 extend from the radially inner ends 230a of wings 230 to the radially outer ones Ends 230b of the wings 230 rectilinear. Relating to one by the Center of the edges 232 at the radially inner end 230a of the wings 230 placed radial with respect to the axis of rotation 24 of the impeller 222 Line 250 is the edges 232 at an angle β in Circumferential direction 21 of the impeller 222 is arranged inclined. The Angle β is between 20 ° and 45 °, preferably between 25 ° and 40 °.

Die Flügel 230 sind außerdem wie bei der ersten und zweiten Ausführungsform gemäß Figur 9 derart schräggestellt angeordnet, daß diese ausgehend von dem die Flügel 230 der beiden Stirnseiten 228,229 voneinander trennenden Steg 233 zur jeweiligen Stirnseite 228,229 hin, an denen die Flügel 230 enden, in Umlaufrichtung 21 des Laufrads 222 vorauseilen. Dies bedeutet, daß die Flügel 230 nicht parallel zur Drehachse 24 des Laufrads 222 angeordnet sind, sondern mit der Drehachse 24 einen in Umlaufrichtung 21 des Laufrads 222 gerichteten Winkel α einschließen. Der Winkel α ist jedoch über den Verlauf der Flügel 230 ausgehend von deren radial innerem Ende 230a zu deren radial äußerem Ende 230b nicht konstant. Im Bereich ihrer radial inneren Enden 230a bilden die Flügel 230 an der jeweiligen Stirnseite 228,229 des Laufrads 222 mit der Drehachse 24 einen in Umlaufrichtng 21 des Laufrads 222 gerichteten Winkel αE, der zwischen 25° und 50°, insbesondere zwischen 30° und 45° beträgt. Vorzugsweise beträgt der Winkel αE etwa 37°. Im Bereich ihrer radial äußeren Enden 230b bilden die Flügel 230 an der jeweiligen Stirnseite 228,229 des Laufrads 222 mit der Drehachse 24 einen in Umlaufrichtung 21 des Laufrads 222 gerichteten Winkel αA, der zwischen 45° und 70° beträgt, insbesondere zwischen 50° und 65°. Vorzugsweise beträgt der Winkel αA etwa 60°. Der Winkel α nimmt ausgehend von den radial inneren Enden 230a der Flügel 230 zu deren radial äußeren Enden 230b hin linear zu. Durch diese Zunahme des Winkels α ausgehend von den radial inneren Enden 230a der Flügel 230 zu deren radial äußeren Enden 230b ergibt sich die vorstehend beschriebene in Umlaufrichtung 21 des Laufrads 222 um den Winkel β vorgeneigte Anordnung der Kanten 232 der Flügel 230. Im Bereich ihrer am Steg 233 angeordneten inneren Enden verlaufen die Flügel 230 im Querschnitt senkrecht zur Drehachse 24 des Laufrads 222 betrachtet etwa radial bezüglich der Drehachse 24, sind also nicht wie an ihrer an der Stirnseite liegenden Kante 232 geneigt. As in the first and second embodiment according to FIG. 9, the wings 230 are also arranged so that they start in the circumferential direction from the web 233 separating the wings 230 of the two end faces 228, 229 from one another to the respective end face 228, 229 at which the wings 230 end Lead ahead 21 of impeller 222. This means that the vanes 230 are not arranged parallel to the axis of rotation 24 of the impeller 222, but instead form an angle α directed in the direction of rotation 21 of the impeller 222 with the axis of rotation 24. However, the angle α is not constant over the course of the vanes 230 starting from their radially inner end 230a to their radially outer end 230b. In the area of their radially inner ends 230a, the vanes 230 on the respective end face 228, 229 of the impeller 222 with the axis of rotation 24 form an angle α E directed in the circumferential direction 21 of the impeller 222, which is between 25 ° and 50 °, in particular between 30 ° and 45 ° is. The angle α E is preferably approximately 37 °. In the area of their radially outer ends 230b, the vanes 230 on the respective end face 228, 229 of the impeller 222 with the axis of rotation 24 form an angle α A directed in the circumferential direction 21 of the impeller 222, which is between 45 ° and 70 °, in particular between 50 ° and 65 °. The angle α A is preferably approximately 60 °. Starting from the radially inner ends 230a of the vanes 230, the angle α increases linearly towards their radially outer ends 230b. This increase in the angle α starting from the radially inner ends 230a of the vanes 230 to their radially outer ends 230b results in the above-described arrangement of the edges 232 of the vanes 230 in the circumferential direction 21 of the impeller 222 by the angle β The inner ends of web 233 are arranged in the cross section perpendicular to the axis of rotation 24 of the impeller 222, viewed approximately radially with respect to the axis of rotation 24, and are therefore not inclined as on their edge 232 located on the end face.

Durch die vorstehend beschriebene Ausbildung der Flügel 230 mit dem ausgehend von deren radial inneren Enden 230a zu deren radial äußeren Enden 230b hin zunehmenden Winkel α werden der Förderdruck und der Wirkungsgrad der Strömungspumpe weiter gesteigert. Dies ergibt sich durch die weitere Steigerung der Dralländerung der Strömung des Kraftstoffs, die im Bereich der radial inneren Enden 230a der Flügel 230 in die Zwischenräume 231 eintritt und aus den Zwischenräumen 231 im Bereich der radial äußeren Enden 230b der Flügel 230 wieder austritt. Vom Eintritt zum Austritt erfährt die Strömung des Kraftstoffs eine zusätzliche Dralländerung, die zu einer Steigerung des Drucks und des Wirkungsgrads führt.Through the above-described formation of the wing 230 with from their radially inner ends 230a to their radially outer ends 230b increasing angle α become the Delivery pressure and the efficiency of the flow pump continue increased. This results from the further increase in Swirl change in the flow of fuel that is in the range of radially inner ends 230a of wings 230 into the spaces 231 enters and from the spaces 231 in the area of radially outer ends 230b of the wing 230 emerges again. From The flow of fuel experiences an entry to exit additional swirl change leading to an increase in pressure and efficiency.

In Figur 10 ist eine Variante des Laufrads 322 der Strömungspumpe gemäß dem ersten Ausführungsbeispiel in einer Seitenansicht dargestellt. Das Laufrad 322 ist dabei im wesentlichen gleich ausgebildet wie beim ersten Ausführungsbeispiel, jedoch verläuft die Kante 332, mit der die Flügel 330 an der Stirnseite des Laufrads 322 enden, nicht geradlinig sondern gekrümmt. Im Bereich der radial inneren Enden 330a der Flügel 330 ist die Kante 332 etwa radial bezüglich der Drehachse 24 des Laufrads 322 angeordnet und die Kante 332 verläuft zu den radial äußeren Enden 330b der Flügel 330 kontinuierlich zunehmend in Umlaufrichtung 21 des Laufrads 322. Entsprechend wird der Winkel α den die Flügel 330 mit der Drehachse 24 des Laufrads 322 einschließen ausgehend von den radial inneren Enden 330a der Flügel 330 zu deren radial äußeren Enden 330b hin größer. Die Zunahme der Größe des Winkels α erfolgt dabei nicht linear wie beim ersten Ausführungsbeispiel sondern verstärkt sich zu den radial äußeren Enden 330b der Flügel 330 hin. Im Bereich ihrer am Steg 333 angeordneten inneren Enden verlaufen die Flügel 330 im Querschnitt senkrecht zur Drehachse 24 des Laufrads 322 betrachtet etwa radial bezüglich der Drehachse 24, sind also nicht wie an ihrer an der Stirnseite liegenden Kante 332 gekrümmt.FIG. 10 shows a variant of the impeller 322 Flow pump according to the first embodiment in one Side view shown. The impeller 322 is in the essentially the same as the first Embodiment, however, runs the edge 332 with which the Vane 330 does not end at the front of impeller 322 straight but curved. In the area of the radially inner ends 330a of wing 330, edge 332 is approximately radial with respect to FIG Axis of rotation 24 of the impeller 322 and the edge 332 extends to the radially outer ends 330b of the wings 330 continuously increasing in the direction of rotation 21 of the impeller 322. Accordingly, the angle α is the wing 330 with the Include axis of rotation 24 of the impeller 322 starting from the radially inner ends 330a of the wings 330 to their radially outer ends Ends 330b larger. The increase in the size of the angle α is not linear as in the first embodiment but reinforces to the radially outer ends 330b of FIG Wing 330 back. In the area of their arranged on the web 333 The inner ends of the wings 330 are perpendicular in cross section viewed approximately radially to the axis of rotation 24 of the impeller 322 with respect to the axis of rotation 24, so they are not as at their on Front edge 332 curved.

In den Figuren 11 und 12 ist das Laufrad 422 der Strömungspumpe 14 gemäß einem zweiten Ausführungsbeispiel dargestellt. Die Strömungspumpe 14 ist dabei als Peripheral-Seitenkanalpumpe ausgebildet und weist einen Förderkanal wie bei der ersten Ausführungsform in Figur 2 dargestellt auf. Das Laufrad 422 weist an seinen beiden axial gerichteten Stirnseiten 428,429 jeweils einen Kranz von in Umfangsrichtung mit Abstand zueinander angeordneten Flügeln 430 auf, zwischen denen jeweils Zwischenräume 431 vorhanden sind. Die Flügel 430 erstrecken sich in radialer Richtung bezüglich der Drehachse 24 des Laufrads 422 von einem radial inneren Ende 430a bis zu einem radial äußeren Ende 430b am Außenumfang des Laufrads 422. In Richtung der Drehachse 24 des Laufrads 422 erstrecken sich die Flügel 430 ausgehend von einem die Flügelkränze der beiden Stirnseiten 428,429 etwa in der Mitte der axialen Breite des Laufrads 422 voneinander trennenden Steg 433 bis zu den Stirnseiten 428,429 des Laufrads 422. Die Flügel 430 sind wie bei den vorstehend beschriebenen Ausführungsformen derart schräg gestellt angeordnet, daß diese ausgehend vom Steg 433 zur jeweiligen Stirnseite 428,429 hin, an denen die Flügel 430 enden, in Umlaufrichtung 21 des Laufrads 422 vorauseilen. Dies bedeutet, daß die Flügel 430 nicht parallel zur Drehachse 24 des Laufrads 422 angeordnet sind, sondern mit der Drehachse 24 einen in Umlaufrichtung 21 des Laufrads 422 gerichteten Winkel α einschließen. Der Winkel α beträgt zwischen 25° und 50°, insbesondere zwischen 30° und 45°. Vorzugsweise beträgt der Winkel α etwa 37°. Der Winkel α ist über die radiale Erstreckung der Flügel 430, das heißt zwischen deren radial inneren Enden 430a und deren radial äußeren Enden 430b etwa konstant.In FIGS. 11 and 12, the impeller 422 is the flow pump 14 according to a second embodiment. The Flow pump 14 is a peripheral side channel pump trained and has a conveyor channel as in the first Embodiment shown in Figure 2. The impeller 422 has 428,429 on its two axially directed end faces in each case a wreath at a distance in the circumferential direction wings 430 arranged to each other, between each of which Spaces 431 are present. The wings 430 extend in the radial direction with respect to the axis of rotation 24 of the impeller 422 from a radially inner end 430a to a radially outer end End 430b on the outer circumference of the impeller 422. In the direction of The axes of rotation 24 of the impeller 422 extend the blades 430 starting from one the wreaths of the two faces 428,429 approximately in the middle of the axial width of the impeller 422 separating web 433 up to the end faces 428,429 of the impeller 422. The vanes 430 are as in the above described embodiments so inclined arranged that these starting from the web 433 to the respective End face 428,429, on which the wings 430 end, in Lead ahead in the direction of rotation 21 of the impeller 422. This means, that the wing 430 is not parallel to the axis of rotation 24 of the impeller 422 are arranged, but with the axis of rotation 24 one in Direction of rotation 21 of the impeller 422 directed angle α lock in. The angle α is between 25 ° and 50 °, especially between 30 ° and 45 °. The is preferably Angle α about 37 °. The angle α is over the radial extent the wing 430, that is between its radially inner ends 430a and their radially outer ends 430b approximately constant.

Wie in Figur 12 dargestellt eilen die radial äußeren Enden 430b der Flügel 430 gegenüber ihren radial inneren Enden 430a in Umlaufrichtung 21 des Laufrads 422 voraus. Die Flügel 430 verlaufen in Richtung der Drehachse 24 des Laufrads 422 betrachtet zwischen ihren radial inneren Enden 430a und ihren radial äußeren Enden 430b gekrümmt, können aber bei einer anderen Ausführung auch geradlinig verlaufen. Im Bereich ihrer radial inneren Enden 430a verlaufen die Flügel 430 zunächst etwa radial bezüglich der Drehachse 24 des Laufrads 422 und zu deren radial äußeren Enden 430b hin nimmt die Krümmung, das heißt die Abweichung von der radialen Anordnung zu. Im Bereich ihrer radial äußeren Enden 430b schließen die Flügel 430 mit einer zur Drehachse 24 des Laufrads 422 radialen Linie 450, die durch die radial äußeren Enden 430b der Flügel 430 gelegt ist, einen in Umlaufrichtung 21 gerichteten Winkel γ ein. Der Winkel γ beträgt zwischen 30° und 60°, insbesondere zwischen 40° und 55°. Vorzugsweise beträgt der Winkel γ etwa 45°. Die vorstehend erläuterte Anordnung der Flügel 430 ist erforderlich, da bei einer Peripheral-Seitenkanalpumpe der zu fördernde Kraftstoff zwar wie bei einer Seitenkanalpumpe im Bereich der radial inneren Enden 430a der Flügel 430 in die Zwischenräume 431 eintritt, aus diesen aber radial nach außen austritt. Die Flügel 430 sind im Querschnitt senkrecht zur Drehachse 24 des Laufrads 422 betrachtet im Bereich ihrer am Steg 433 angeordneten inneren Enden ebenso in Umlaufrichtung 21 gekrümmt ausgebildet wie an den Stirnseiten 428,429 des Laufrads 422.As shown in Figure 12, the radially outer ends 430b hurry wing 430 opposite its radially inner ends 430a in Direction of rotation 21 of the impeller 422 ahead. The wings 430 extend in the direction of the axis of rotation 24 of the impeller 422 viewed between their radially inner ends 430a and hers radially outer ends 430b curved, but can be at a other version also run in a straight line. In the area of their The radially inner ends 430a initially run approximately 430 radially with respect to the axis of rotation 24 of the impeller 422 and to the latter radially outer ends 430b take the curvature, that is, the Deviation from the radial arrangement too. In the area of their radially outer ends 430b close the wings 430 with one Axis of rotation 24 of the impeller 422 radial line 450 through the the radially outer ends 430b of the wing 430 is placed one in Direction of rotation 21 directed angle γ. The angle is γ between 30 ° and 60 °, in particular between 40 ° and 55 °. The angle γ is preferably approximately 45 °. The above The arrangement of the wings 430 is necessary because a peripheral side channel pump the fuel to be pumped like a side channel pump in the radial area inner ends 430a of wings 430 into spaces 431 enters, but exits radially outwards. The wings 430 are in cross section perpendicular to the axis of rotation 24 of the impeller 422 viewed in the area of its inner arranged on the web 433 Ends are also curved in the circumferential direction 21 as at the end faces 428, 429 of the impeller 422.

Claims (11)

  1. Flow pump for supplying fuel from a reservoir (16) to the internal combustion engine (18) of a motor vehicle, having an impeller (222;322;422) which rotates in a pump chamber (20) and has on at least one axially directed end face (228;229;428;429) a rim of blades (230;330;430) which are arranged with a spacing from one another in the circumferential direction and co-operate with an annular supply channel (34;144;145) in order to supply the fuel, characterized in that, when viewed in the radial direction in relation to the axis of rotation (24) of the impeller (222;322;422), the blades (230;330;430) are obliquely positioned with reference to the axis of rotation (24) in such a way that, towards the at least one axially directed end face (228,229;428,429) of the impeller (222;322;422), they lead in the circumferential direction (21) of the impeller (222;322;422), and in that, on the at least one axially directed end face (228,229;428,429) of the impeller (222;322;422), the blades (230;330;430) lead in the circumferential direction (21) of the impeller (222;322;422) with their radially outer ends (230b;330b;430b) with respect to their radially inner ends (230a;330a;430a).
  2. Flow pump according to Claim 1, characterized in that the blades (330;430) enclose with the axis of rotation (21) of the impeller an angle (α) which is directed in the circumferential direction (21) of the impeller and is between 25° and 70°.
  3. Flow pump according to Claim 1, characterized in that, on the at least one axially directed end face (228,229) of the impeller (222;322), the blades (230;330) are arranged, starting from their radially inner end (230a;330a), inclined in the circumferential direction (21) by an angle (β) in relation to an imaginary radial arrangement (250), the angle (β) being between 20° and 45°.
  4. Flow pump according to one of the preceding claims, characterized in that, starting from the radially inner ends (230a;330a) of the blades (230;330), the angle (α) at which the blades (230;330) are inclined to the axis of rotation (24) of the impeller (222;322) increases towards the radially outer ends (230b;330b) of said blades.
  5. Flow pump according to Claim 4, characterized in that, in the region of their radially inner ends (230a,330a), the blades (230) are inclined at an angle (αE) to the axis of rotation (24) of the impeller (222) which is between 25° and 50°, and in that, in the region of their radially outer ends (230b;330b), the blades (230) are inclined at an angle (αA) to the axis of rotation (24) of the impeller (222) which is between 45° and 70°.
  6. Flow pump according to one of the preceding claims, characterized in that the blades are essentially of flat construction.
  7. Flow pump according to one of Claims 1 to 5, characterized in that, starting from their radially inner ends (330a,430a), the blades (330;430) run in a curved fashion in the circumferential direction (21) of the impeller (322;422) towards their radially outer ends (330b;430b).
  8. Flow pump according to Claim 7, characterized in that, in the region of their radially inner ends (330a;430a), the blades (330;430) run approximately radially in relation to the axis of rotation (24) of the impeller (322;422).
  9. Flow pump according to one of the preceding claims, characterized in that the blades (230;330) are connected to one another at their radially outer ends (230b;330b) via a closed ring (240), and in that the annular supply channel (145,146) is constructed in a chamber wall (125,126) limiting the pump chamber (20) in the direction of the axis of rotation (24) of the impeller (222;322), and extends in the radial direction in relation to the axis of rotation (24) between the radially inner ends (230a;330a) and the radially outer ends (230b;330b) of the blades (230;330).
  10. Flow pump according to one of Claims 1 to 8, characterized in that the impeller (422) in each case has a rim of blades (430) on its two axially directed end faces (28,29), and in that the supply channel (34) extends on both sides of the end faces (28,29) of the impeller (422) and over the outer circumference thereof.
  11. Flow pump according to Claim 10, characterized in that the blades (430) of the impeller (422) enclose with the axis of rotation (24) of the impeller an angle (α) which is directed in the circumferential direction (21) of the impeller and is between 25° and 50°, and in that, when viewed in a cross section situated perpendicular to the axis of rotation (24), in the region of their radially outer ends (430b) the blades (430) lead in the circumferential direction (21) of the impeller (422) by an angle (γ) with respect to an arrangement (450) which is radial relative to the axis of rotation (24), the angle (γ) being between 30° and 60°.
EP96900265A 1995-02-08 1996-01-10 Flow pump for use in pumping fuel from a reservoir to the engine of a motor vehicle Expired - Lifetime EP0774077B2 (en)

Applications Claiming Priority (3)

Application Number Priority Date Filing Date Title
DE19504079 1995-02-08
DE19504079A DE19504079B4 (en) 1995-02-08 1995-02-08 Flow pump for delivering fuel from a reservoir to the internal combustion engine of a motor vehicle
PCT/DE1996/000024 WO1996024769A1 (en) 1995-02-08 1996-01-10 Flow pump for use in pumping fuel from a reservoir to the engine of a motor vehicle

Publications (3)

Publication Number Publication Date
EP0774077A1 EP0774077A1 (en) 1997-05-21
EP0774077B1 true EP0774077B1 (en) 2000-08-23
EP0774077B2 EP0774077B2 (en) 2006-04-05

Family

ID=7753421

Family Applications (1)

Application Number Title Priority Date Filing Date
EP96900265A Expired - Lifetime EP0774077B2 (en) 1995-02-08 1996-01-10 Flow pump for use in pumping fuel from a reservoir to the engine of a motor vehicle

Country Status (8)

Country Link
US (1) US5807068A (en)
EP (1) EP0774077B2 (en)
JP (1) JPH09511812A (en)
KR (1) KR100382681B1 (en)
CN (1) CN1071420C (en)
BR (1) BR9605117A (en)
DE (2) DE19504079B4 (en)
WO (1) WO1996024769A1 (en)

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Also Published As

Publication number Publication date
CN1145659A (en) 1997-03-19
KR100382681B1 (en) 2003-08-21
US5807068A (en) 1998-09-15
EP0774077B2 (en) 2006-04-05
BR9605117A (en) 1997-10-07
DE19504079A1 (en) 1996-08-14
DE19504079B4 (en) 2004-11-04
CN1071420C (en) 2001-09-19
EP0774077A1 (en) 1997-05-21
KR970702436A (en) 1997-05-13
JPH09511812A (en) 1997-11-25
DE59605787D1 (en) 2000-09-28
WO1996024769A1 (en) 1996-08-15

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