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
  • 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 present invention relates to the field of turbine pumps for pumping fuel into a tank of a motor vehicle.
• pumps have already been proposed for this purpose. Examples of such known pumps are described in documents FR-A-2,714,121, FR-A-2,711,741, FR-A-2,713,714, FR-A-2,720,118, FR-A-2,722,536 and FR-A-2 685 937.
• these pumps comprise a casing which houses an electric drive motor and a pumping assembly driven by this motor and situated at the base of said casing.
• the main object of the present invention is to propose a new pump making it possible to improve the efficiency compared to known pumps.
• a turbine pump in particular for a motor vehicle fuel tank, comprising a housing forming a stator and a vane rotor mounted for rotation relative to the housing and defining an ascent path. in pressure and flow between an inlet and an outlet, characterized in that the rotor has two annular series of concentric vanes respectively radially internal and radially external, to define a fuel path passing alternately through the passages defined by the blades radially internal and by the passages defined by the radially external vanes so that this path follows a generally helical configuration supported by an annular envelope, the two sets of blades being arranged respectively radially on the inside and on the outside a ring, the series of radially internal vanes ensuring the connection between the periphery rie interior of the ring and the periphery of a central plate such that the blades define an annular series of passages passing through the rotor according to its thickness, and closed at the periphery, while
• the passages formed by the rotor cooperate with auxiliary channels formed in the stator and which have walls inclined relative to a radial direction in order to guide the fuel between the passages defined by the radially internal vanes. and the passages defined by the radially outer vanes.
• the pitch of the walls may be different from that of the blades forming the passages in the rotor.
• auxiliary channels provided with walls in two cups arranged respectively on either side of the rotor.
• the walls provided on the two cups are respectively crossed between them.
• the two series of rotor blades are curved and inclined in directions respectively opposite from one series to another.
• FIG. 1 attached represents a schematic exploded perspective view of the essential means of a pump according to the present invention
• FIG. 2 represents a second schematic exploded perspective view, opposite to that of FIG. 1, of the same essential means of the pump according to the present invention
• FIG. 3 schematically illustrates the path followed by the fuel in the pumping chamber
• FIG. 4 represents a partial view of this path
• FIG. 5 represents a view of a rotor according to the present invention
• FIG. 6 and 7 respectively show internal plan views of lower and upper cup of such a pump according to the present invention.
• FIG. 8a represents an illustration developed on a plane, radially internal vanes observed in lateral view perpendicular to the axis of rotation, according to a first embodiment of the present invention
• FIG. 8b represents a similar illustration developed on a plane, radially external vanes observed in lateral view perpendicular to the axis of rotation, according to the same first embodiment of the present invention
• FIG. 9a represents an illustration developed on a plane, radially internal vanes observed in lateral view perpendicular to the axis of rotation, according to a second embodiment of the present invention
• FIG. 9b represents a similar illustration developed on a plane, radially external vanes observed in lateral view perpendicular to the axis of rotation, according to the same second embodiment of the present invention.
• FIG. 10 represents a partial view in a plane perpendicular to the axis of rotation of the blades in accordance with the present invention
• FIG. 11 represents a similar view in a plane perpendicular to the axis of rotation, of walls in accordance with the present invention, provided on the stator of the pump,
• FIG. 12 illustrates a variant of the blade profile in accordance with the present invention
• FIGS. 13a and 13b show views similar to FIGS. 8 and 9 respectively of radially internal and radially external vanes, in accordance with a variant of the present invention
• FIGS. 14 and 15 schematically illustrate the path of fuel nets in the pumping chamber, respectively in the absence of walls and in the presence of walls in accordance with the present invention
• FIG. 16 schematically illustrates the structure of a molding tool according to the present invention
• FIG. 17, 18 and 19 show three cross-sectional views of a lower cup according to the present invention according to the views illustrated respectively under the references XVII, XVIII and XIX in Figure 6 ( Figure 17 being on a double scale Figures 18 and 19).
• the pump illustrated in the appended figures comprises a stator 100 and a rotor 200.
• the stator 100 is formed of a ring 110 sandwiched between two flanges or cups 120, 130 respectively upper and lower.
• the stator 100 thus defines a circular chamber centered on a 0-0 axis capable of receiving the rotor 200 rotating around this 0-0 axis.
• the direction of rotation of the rotor 200 is referenced S.
• the ring 110 and the cups 120 and 130 are fixed to each other by any suitable means.
• the rotor 200 is formed of a circular plate 210 whose thickness is equal to the play close to the thickness of the ring 110 and whose largest external radius is equal to the play close to the internal radius of the ring 110.
• the plate 210 is rotated about the axis OO by any suitable means.
• the plate 210 is driven by an electric motor (not shown in the appended figures), the output shaft of which is engaged with the hub of the plate 210.
• the plate 210 is provided in its center with a non-rigid structure symmetrical of revolution 240. It is an orifice delimited by two diametrically opposite planes connected to each other by their ends by semi-cylindrical caps, according to the particular representation given in the appended figures. However, this particular representation is in no way limiting. Naturally at least one of the cups 120, 130 must be provided with a central through hole to allow access and training of this structure 240.
• the plate 210 is provided with two annular series of concentric vanes 220 and 230.
• the vanes 220 and 230 are thus arranged in two annular assemblies respectively internal and external defining each of the series of passages 222, 232 passing through the plate 210 in a general direction corresponding to its thickness.
• the two series of blades 220 and 230 are arranged respectively radially on the inside and on the outside of a ring 250.
• the blades 230 protrude in a generally radial direction on the outer periphery of the ring 250.
• the blades 220 provide the connection between the inner periphery of the ring 250 and the periphery of the central plate 210.
• the vanes 220 define an annular series of passages 222 passing through the rotor 200 according to its thickness, but closed at the periphery.
• the rotor 200 is also provided with an outer ring 260 disposed radially on the outside of the blades 230.
• the blades 230 provide the connection between the outer periphery of the ring 250 and the inner periphery of the ring 260 and the vanes 230 define an annular series of passages 232 passing through the rotor 200 according to its thickness, but also closed radially outwards by the ring 260.
• Such an external ring 260 allows good mechanical strength for the vanes 230 and makes it possible to limit the stresses applied to the ring 110.
• the dimensions of the ring 110 and of the cups 120 and 130 must be adapted accordingly so that channels 122, 132 formed in the cups 120, 130 , whose structure and function will be specified later, are arranged opposite the passages 222, 232 formed by the vanes 220 and 230.
• the two rings 250 and 26 0 can each have a radial dimension of the order of 0.8mm.
• these vanes 220 and 230 are adapted to impose on the fuel put into circulation and under pressure inside the pump, a generally helical path supported by an annular envelope and passing successively and alternately through internal passages 222 and through external passages 232.
• This annular envelope of the path followed by the fuel is defined, for its radially internal portion by the passages 222 delimited by the radially internal vanes 220, for its radially external portion by the passages 232 delimited by the radially external vanes 230, and for its connection zones between these radially internal and external portions, by semi-annular auxiliary channels 122, 132 delimited respectively by the cups 120 and 130, on their opposite faces, directed towards the rotor 200.
• the cross section of the channels 122, 132 can be the subject of various variants.
• these channels 122, 132 have a cross section in the form of a half-ellipse, that is to say that it has a continuous curvature, of decreasing radius, from the middle of the bottom of said channels towards the free edges thereof coinciding with the internal surface of the cups 120, 130 (as opposed to known channels whose cross section is delimited by a rectilinear base segment extended on both sides and d 'other by sectors of circles).
• the cross section of the channels 122, 132 is preferably symmetrical with respect to a median plane orthogonal to this internal surface of the cups 120, 130.
• the radially internal radius of the channels 122, 132 is complementary to the smallest radially internal radius of the blades 220, while the radially external radius of the channels 122, 132 is complementary to the largest radially external radius of the blades 230.
• An inlet port 134 crosses in a generally axial direction the lower cup 130 and opens onto one end of the channel 132, while an outlet port 124 crosses in a generally axial direction the upper cup 120 and opens onto the other end of channel 122.
• the inlet orifices 134 are inclined on the order of 30 ° to 75 °, very preferably on the order of 53 ° relative to an axis orthogonal to the axis of rotation OO, while the outlet orifices 124 are inclined on the order of 10 ° to 45 °, very preferably on the order of 15 ° to 20 ° relative to an axis orthogonal to the axis of rotation OO.
• the aforementioned inclination of the inlet orifice 1345 can in particular be observed in FIG. 19.
• the channel 132 formed in the lower cup 130 has an initial section 1320 of decreasing section leading to a transition zone referenced 1321, followed by a portion of constant section 1322, to finish with a portion of decreasing section 1323.
• the channel 122 has an initial section of decreasing section 1220, followed by a portion of constant section 1221, to end in a decreasing section 1222.
• the sections 1221 and 1322 may have a slightly decreasing cross-section when moving towards the sections 1220 and 1323 respectively.
• the channel 132 designed to conduct the fuel from the radially external passages 232 to the radially internal passages 222 has a cross section greater than that of the channel 122 formed in the upper cup 120.
• channels 122, 132 cover an angular sector less than 360 ° around the axis O-O.
• the useful sections 1224, 1324 of these semi-annular channels 122 and 132 cover an angle of the order 270 ° around the axis of rotation
• FIGS. 6 and 7 It will be noted in FIGS. 6 and 7 the presence of 4 basins 1201, 1202, 1203 and 1204, 1301, 1302, 1303 and 1304 hollowed out in the internal surfaces of each cup 120, 130. These basins are designed to be placed under fuel pressure from the channels 122, 132 to form hydrostatic bearings supporting the rotor 200 in its rotation about the axis OO.
• the helical-annular path is shown diagrammatically in FIG. 3 and partially illustrated in more detail in FIG. 4.
• the fuel which enters the pump chamber through the inlet 134 first reaches the channel 132 formed in the lower cup 130, and from there gains a passage 222 formed by the vanes 220, then the channel 122 formed in the upper flange 120, a passage 232 formed by the external vanes 230, the channel 132 formed by the lower flange 130, then again a passage 222 and so on until reaching the exit 124.
• the cups 120 and 130 are preferably provided on their external surface with indexing or polarizing means.
• Such means are shown diagrammatically in the appended figures in the form of at least one groove 126, 136 formed in the outer periphery of the cups 120, 130, which grooves are intended to be aligned during assembly and the relative immobilization of the cups 120 and 130 to receive a key.
• the ring 110 is preferably provided with an external groove 112 intended to be aligned with the grooves 126, 136 to receive the aforementioned key.
• the ring 110 can be integrated into one of the cups 120, 130. To prevent the fuel from fully following the rotor
• the auxiliary channels 122 and 132 formed in the cups 120 and 130 of the stator 100 have walls 127, 137 inclined to a radial direction. These walls 127, 137 thus impose on the fuel a path which passes successively through pairs of radially internal and radially external passages 222 and 232.
• FIG. 14 There is thus shown diagrammatically in FIG. 14 the path of fuel nets in the pumping chamber in the absence of such low walls and in FIG. 15 the path of the same fuel nets thanks to the presence of low walls 127, 137.
• a person skilled in the art will understand on the comparative examination of FIGS. 14 and 15 that the walls 127 and 137 impose a circulation of the fuel through the passages 222 and 232 and consequently a rise in fuel pressure greater than the rise in pressure likely to 'be obtained in the absence of such walls.
• the walls 127 and 137 are formed of planar walls parallel to the axis of rotation O-O and inclined relative to a radial direction, as indicated above. It is thus defined between two adjacent walls 127 or 137 inclined with respect to a radial direction, grooves 128, 138 capable of guiding the fuel between the passages 222 defined by the radially internal vanes 220 and the passages 232 defined by the radially external vanes 230.
• the cross section of the grooves 128, 138 can be the subject of numerous variants depending on the geometry of the bottom wall thereof. It is thus possible to design grooves 128, 138 of triangular or semi-circular or rounded cross section, in particular.
• the grooves 128 and 138 have a cross section of rectangular outline, delimited by a base surface perpendicular to the axis of rotation O-O and two flanks defined by the walls 127 or 137.
• each of the auxiliary channels 122 and 132 is provided with such walls 127, 137.
• the pitch of the walls 127, 137 can be identical to that of the vanes 220, 230. However, this equality of pitch is not compulsory in the context of the present invention.
• These walls 127, 137 provided on the two cups 120, 130 are respectively crossed between them, preferably substantially at 45 °, to ensure correct fuel guidance.
• the low walls 137 provided on the lower cup 130 in a direction going from the upper cup 120 towards the lower cup 130, the low walls 137 deploy in an anti-trigonometric direction when we move radially towards outside.
• the walls 127 provided on the upper cup 120 observed in the same direction are deployed in a trigonometric direction when one moves radially outwards.
• the walls 127 guide the fuel from the outlet of a radially internal passage 222, towards the inlet of a radially external passage 232, while the walls 137 guide the fuel from the outlet of a radially external passage 232, towards the entrance to a passage 232 radially internal.
• the number of low walls 127 and 137 is 16 on each cup 120, 130,
• the entry C1 and exit C2 angles of the walls 127 and 137 are between -90 ° and + 90 ° relative to a tangent to the periphery of the channels 122 and 132, preferably being of the order of + 45 ° with respect to this tangent,
• the thicknesses of the walls forming the low walls 127, 137 at the entry and at the exit are of the order of 0.3 mm
• the walls 127, 137 are connected to the internal wall of the channels 122, 132 with a fillet of the order of 0.2 mm and - the open angle D defined between two adjacent walls 127 or 137, from the axis OO, is around 12 °.
• the top of the walls 127, 137 is not coplanar with the surfaces internal of the cups 120, 130, but situated behind these internal surfaces, for example by an interval of the order of 0.1 mm, as seen for example in FIG. 17.
• concentric vanes 220 and 230 are curved and inclined in opposite directions respectively from one series to another.
• the internal vanes 220 are deployed in the direction S when one moves from the upper cup 120 towards the lower cup 130.
• the external vanes 230 are deployed in the opposite direction to S, that is to say in a clockwise direction, when one moves in the same way from the upper cup 120 towards the lower cup 130.
• the inclination of the blades is reversed if one of the direction of rotation S of the rotor or of the propeller is reversed.
• the blades 220, 230 have their concavity directed towards the front, with reference to the direction of movement S of the rotor 200.
• the lower surface 2200, 2300 and upper surface 2202, 2302 of the vanes 220 and 230 are preferably defined by rectilinear generators, radial with respect to the axis of rotation OO and which are based on curves when said generatrices moved along the OO axis.
• leading edges of the vanes 220 and 230 are referenced 2204 and 2304, while the trailing edges of the same blades 220 and 230 are referenced 2206 and 2306.
• leading edges 2204 are located on the lower surface of the rotor 200, while the trailing edges 2206 are located on the upper surface of the rotor 200.
• leading edges 2304 are located on the upper surface of the rotor 200 , while the trailing edges 2306 are located on the lower surface of the rotor 200.
• the lower surface 2200 and 2300 and the upper surface 2202 and 2302 have identical curvatures.
• the lower surface 2200 and the upper surface 2202 of the internal vanes 220 are identical to each other, while the lower surface 2300 and the upper surface 2302 of the external vanes 230 have curvatures identical to each other, but with a radius different from that of the lower surface 2200 and the upper surface 2202 of the above-mentioned internal vanes 220.
• the internal vanes 220 and the external vanes 230 have thicknesses "e" identical at their leading edge 2204, 2304 and at their trailing edge 2206, 2306 (The term “thickness” here means the transverse dimension "e” of the vanes 220, 230 considered in a plane perpendicular to the axis of rotation OO).
• the internal vanes 220 have identical thicknesses e1 at their leading edge 2204 and at their trailing edge 2206.
• the external vanes 230 have thicknesses e2 identical at their leading edge 2304 and at their trailing edge 2306, but the thickness e2 of the external vanes 230 is different (greater) than that e1 of the internal vanes 220.
• the lower surface 2200, 2300, at the leading edge 2204, 2304 is preferably inclined at an angle between 130 ° and 170 ° relative to a plane perpendicular to the axis of rotation OO, while the same lower surface 2200, 2300 at the trailing edge 2206, 2306 is preferably inclined on the order of 90 ° relative to a plane perpendicular to the axis of rotation OO (that is to say that the lower surface 2200, 2300 at the trailing edge 2206, 2306 is preferably parallel to the axis of rotation OO).
• the leading edge 2204, 2304 of the vanes 220 and 230 is shown tapered.
• this leading edge 2204, 2304 can be rounded for reasons of mechanical strength.
• the radius of such a rounded leading edge can be of the order of 0.15 mm.
• each blade 220 and 230 is defined by a constant wall thickness "e", considered in a plane perpendicular to the axis of rotation O-O. As can be seen in the figures, particularly in FIG. 9b, this however leads to a weakening of the blades 220, 230 at the level of the leading edge 2204, 2304.
• the blades have different thicknesses "e3" and "e4" (considered in a plane perpendicular to the axis of rotation), respectively at the edge d attack and at the trailing edge.
• this dimension Y is of the order of 0.3 mm.
• the blades 220, 230 have widths "L" (considered parallel to the axis of rotation O-O) identical and constant over their entire radial extension. This width L of the vanes 220, 230 is equal to the thickness of the rotor 200.
• the internal vanes 220 and the external vanes 230 preferably have the same radial extension.
• the internal radius r1 of the vanes 220 is of the order of 13 mm
• the external radius r2 of the vanes 220 is of the order of 14mm
• the internal radius r3 of the blades 230 is of the order of 15 mm
• the external radius r4 of the vanes 230 is of the order of 16 mm, (the radii r1, r2, r3 and r4 are each reduced by 0.8 mm in the case where the rotor 200 has an external ring 260)
• the radially internal and radially external widths L of the vanes 220 and 230 are of the order of 2mm
• - the angles A1 and A2 of the vanes 220 and 230, considered in a perpendicular plane to the axis of rotation OO are 90 ° relative to the periphery of the rotor 200
• the angle B1 of the lower surface 2200 of the vanes 220 at the leading edge 2204 is of the order of 140 ° relative to a plane perpendicular to the axis of rotation O-O,
• the angle B2 of the trailing edge 2206 of the vanes 220 on the lower surface 2200 is of the order of 90 ° relative to a plane perpendicular to the axis of rotation O-O,
• the angle B3 of the lower surface 2300 of the blades 230 at the leading edge 2304 is of the order of 140 ° relative to a plane perpendicular to the axis of rotation O-O,
• the angle B4 of the trailing edge 2306 of the vanes 230 on the lower surface 2300 is of the order of 90 ° relative to a plane perpendicular to the axis of rotation OO, - the thickness e of the wall forming the blades 220 and 230 is of the order of 0.3mm,
• the radial thickness of the support ring 250 is of the order of 0.8mm. According to the second embodiment illustrated in FIGS. 9a and 9b:
• the internal radius r1 of the blades 220 is of the order of 13 mm
• the external radius r2 of the blades 220 is of the order of 14mm
• the internal radius r3 of the blades 230 is of the order of 15 mm
• the external radius r4 of the blades 230 is of the order of 16 mm
• the radii r1, r2, r3 and r4 are each reduced by 0.8mm in the case where the rotor 200 has an external ring 260) - the radially internal and radially external widths L of the blades 220 and 230 (which correspond to the thickness of the rotor 200) are of the order of 2 mm,
• angles A1 and A2 of the vanes 220 and 230, considered in a plane perpendicular to the axis of rotation O-O are 90 ° relative to the periphery of the rotor 200,
• the angle B1 of the lower surface 2200 of the vanes 220 at the leading edge 2204 is of the order of 140 ° relative to a plane perpendicular to the axis of rotation O-O,
• the angle B2 of the trailing edge 2206 of the vanes 220 on the lower surface 2200 is of the order of 90 ° relative to a plane perpendicular to the axis of rotation O-O,
• the angle B3 of the lower surface 2300 of the blades 230 at the leading edge 2304 is of the order of 160 ° relative to a plane perpendicular to the axis of rotation OO
• - the angle B4 of the edge leakage 2306 of the vanes 230 on the lower surface 2300 is of the order of 90 ° relative to a plane perpendicular to the axis of rotation OO
• the thickness e1 of the wall forming the blades 220 is of the order of 0.3 mm
• the thickness e2 of the wall forming the blades 230 is of the order of 0.3mm, - the radial thickness of the support ring 250 is of the order of 0.8mm.
• the pump according to the present invention makes it possible to significantly improve the efficiency obtained.
• the pump according to the present invention achieves a yield of around 24%.
• all the parts of the pump namely the cups 120 and 130, the ring 110 and the rotor 200, are made of plastic.
• the cups 120, 130 can be made of metal, the rotor 200 at least being made of plastic.
• reference 1380 illustrates a degassing orifice passing through the lower cup 130 and opening into the channel 132 downstream of the inlet orifice 134.
• a preferred embodiment of the tool is illustrated in FIG. 16 molding used for the realization of the rotor 200 according to the present invention.
• the channels 222 and 232 formed between the pairs of adjacent blades 220, 230 are each formed by a pair of complementary protrusions 310, 320 linked respectively to each of the molding shells.
• these protuberances 310, 320 are preferably adapted to define joint planes located on the main surfaces of the rotor, orthogonal to the axis of rotation O-O.
• the protrusions 310, 320 are preferably adapted to define joint planes P1, P2 which respectively coincide one with the generatrix of the leading edge located in the plane P3 passing through the tangent axis OO with this leading edge 2204, 2304 and the other with the trailing edge 2206, 2306.
• the blades 220, 230 and the channels 222, 232 formed by them are preferably dimensioned so that the vertices 312, 322 of the protrusions 310, 320 have a minimum width La of the order of 0.5 mm, with a minimum clearance angle De of 6 °.
• the interval 11 between two vanes 220 adjacent at the trailing edge 2206 can be of the order of 2.52 mm, while the interval 12 between two vanes 230 radially external, at the trailing edges 2306 is of the order of 2.94 mm, the projection 13 and 14 of the upper surface sufaces 2202 and 2302 of the blades 220 and 230, on a plane orthogonal to the axis OO being respectively of around 1mm and 1.84mm.
• the present invention is not limited to the embodiment described above, but extends to all variants in accordance with its spirit.
• multicellular pumps that is to say pumps in which the above-mentioned structure is multiplied several times in the form of several chambers arranged fluidly in series (the chambers being stacked coaxially according to the 'axis OO) and each housing a rotor 200 in accordance with the aforementioned provisions.
• a number of radially internal vanes 220 is provided equal to the number of radially external vanes 230.
• this arrangement is not imperative.
• the number of internal vanes 220 can be different from the number of external vanes 230.
• the number of both internal 220 and external vanes 230 is equal to an integer.

Landscapes

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

Applications Claiming Priority (3)

Publications (2)

Family

ID=9510848

Family Applications (1)

Country Status (4)

Families Citing this family (4)

Family Cites Families (14)

• 1997
  • 1997-09-08 FR FR9711128A patent/FR2768192B1/fr not_active Expired - Fee Related
• 1998
  • 1998-09-08 EP EP98943943A patent/EP1012479B1/de not_active Expired - Lifetime
  • 1998-09-08 DE DE69810315T patent/DE69810315T2/de not_active Expired - Lifetime
  • 1998-09-08 WO PCT/FR1998/001917 patent/WO1999013226A1/fr not_active Ceased

Non-Patent Citations (1)

Also Published As

Similar Documents

Legal Events