Classifications

• • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
  • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
  • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
  • F04D29/00—Details, component parts, or accessories
  • F04D29/40—Casings; Connections of working fluid
  • F04D29/42—Casings; Connections of working fluid for radial or helico-centrifugal pumps
  • F04D29/44—Fluid-guiding means, e.g. diffusers
  • F04D29/441—Fluid-guiding means, e.g. diffusers especially adapted for elastic fluid pumps
  • F04D29/444—Bladed diffusers
• • B—PERFORMING OPERATIONS; TRANSPORTING
  • B60—VEHICLES IN GENERAL
  • B60H—ARRANGEMENTS OF HEATING, COOLING, VENTILATING OR OTHER AIR-TREATING DEVICES SPECIALLY ADAPTED FOR PASSENGER OR GOODS SPACES OF VEHICLES
  • B60H1/00—Heating, cooling or ventilating [HVAC] devices
  • B60H1/00457—Ventilation unit, e.g. combined with a radiator
  • B60H1/00471—The ventilator being of the radial type, i.e. with radial expulsion of the air
• • 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
  • F04D29/40—Casings; Connections of working fluid
  • F04D29/42—Casings; Connections of working fluid for radial or helico-centrifugal pumps
  • F04D29/4206—Casings; Connections of working fluid for radial or helico-centrifugal pumps especially adapted for elastic fluid pumps
  • F04D29/4226—Fan casings
  • F04D29/4253—Fan casings with axial entry and discharge
• • B—PERFORMING OPERATIONS; TRANSPORTING
  • B60—VEHICLES IN GENERAL
  • B60H—ARRANGEMENTS OF HEATING, COOLING, VENTILATING OR OTHER AIR-TREATING DEVICES SPECIALLY ADAPTED FOR PASSENGER OR GOODS SPACES OF VEHICLES
  • B60H1/00—Heating, cooling or ventilating [HVAC] devices
  • B60H1/00007—Combined heating, ventilating, or cooling devices
  • B60H1/00021—Air flow details of HVAC devices
  • B60H2001/00078—Assembling, manufacturing or layout details
  • B60H2001/00092—Assembling, manufacturing or layout details of air deflecting or air directing means inside the device

Definitions

• the present invention relates to the field of ventilation, heating and/or air conditioning systems intended to be integrated into vehicles, and more particularly ventilation devices integrated into such systems.
• Vehicles conventionally comprise a ventilation, heating and/or air conditioning system intended for the heat treatment of a flow of air sent into a passenger compartment of this vehicle.
• These ventilation, heating and/or air conditioning systems comprise at least one casing in which are received at least one heat exchanger and at least one ventilation device.
• a heat transfer fluid i.e. a fluid capable of capturing, transporting and releasing calories, circulates in this heat exchanger.
• This heat exchanger is also crossed by a flow of air which, in doing so, sees its temperature modified before being sent into the passenger compartment so as to heat treat its volume.
• the ventilation, heating and/or air conditioning system generally comprises at least one ventilation device which comprises at least one fan housed in a casing, this propeller being driven in rotation by a moving member which can also be housed in the housing.
• the ventilation devices currently used comprise an axial air inlet, that is to say a mouth which allows the air flow to enter the ventilation device in a direction parallel, or substantially parallel, to a axis of rotation of the propeller of this ventilation device, and a radial air outlet where the air flow exits following a direction radial to the propeller.
• a ventilation device is conventionally arranged in a volute so that the air flow enters the ventilation device in a first direction and leaves this housing in a second direction perpendicular to the first direction.
• the propeller of such a ventilation device conventionally comprises a central body from which extends radially a plurality of blades.
• the plurality of blades is rotatable around the direction of rotation and forces the circulation of the air flow through the ventilation device.
• the air flow then passes through a member of guide configured to cause the circulation of the air flow towards an air outlet of the housing.
• a disadvantage of these ventilation devices is that they are particularly bulky due to the radial character of the air flow at the outlet of the device. They cannot therefore be easily installed in particularly cramped ventilation systems. In addition, it is known that these ventilation devices are noisy and can inconvenience the driver and/or the passengers present in the passenger compartment of the vehicle.
• the present invention proposes a new design of radial propeller ventilation device so that it takes up less space than the concepts of the prior art.
• the invention also aims to improve on the one hand the energy efficiency necessary to set the propeller in rotation, and on the other hand, the acoustics produced by the ventilation device.
• the main object of the present invention is a ventilation device for a ventilation, heating and/or air conditioning system of a vehicle, comprising at least one casing which comprises at least one wall participating in delimiting a volume internal in which are received at least one radial propeller and a guide member, the radial propeller being configured to be driven in rotation about an axis of rotation, the radial propeller comprising a plurality of blades each at least delimited by a first axial end and by a second axial end, the guide member comprising a plurality of vanes at least delimited by a leading edge and by a trailing edge, the radial propeller and the guide member being configured to forcing the circulation of an air flow through the casing along the axis of rotation between an air inlet mouth and an air outlet mouth of the ventilation device, characterized in that a organ height guide ne measured along a direction parallel to the axis of rotation between a first plane passing through the leading edge of the plurality of blades and a second plane passing through the trail
• a first height is measured between the leading edge and the trailing edge of the plurality of blades along a direction parallel to the axis of rotation
• a second height being measured between the end of the plurality of blades of the radial propeller closest to the guide member and the air outlet mouth along a direction parallel to the axis of rotation, the first height being at least 50% from the second height
• the first plane, the second plane, the third plane and the fourth plane extend parallel to each other and perpendicular to the axis of rotation.
• radial propeller means a propeller in which the air flow enters in a first direction, in this case parallel to the axis of rotation of this propeller, and leaves it in a second transverse direction, for example perpendicular , to the axis of rotation of this propeller.
• the radial propeller within the meaning of the invention, comprises an axial air inlet and a radial air outlet.
• the shape of the housing of this ventilation device and the shape of the airflow guide member received in this ventilation device make it possible, together, to channel the airflow generated by the rotation of the radial helix of so that the overall size of this ventilation device compared to the ventilation devices of the prior art is reduced.
• the air outlet of the ventilation device according to the invention can thus be placed in the axial extension of the radial helix, which makes it possible to reduce the radial bulk of such a device.
• the ventilation device according to the invention can be installed more easily in small-sized vehicles, such as for example vehicles powered at least in part by electricity.
• the ventilation device makes it possible to obtain a homogeneous distribution of the flow of air over an entire surface of the outlet mouth formed in the wall of the housing, by tilting the flow of air so that it joins the part of the outlet mouth where the axis of rotation of the radial propeller passes.
• the plurality of vanes is fixed and integral with the wall of the casing. It is understood that the plurality of blades is not driven in rotation around the axis of rotation and keeps the same position to guide the flow of air towards the air outlet mouth and towards the axis of rotation of the radial helix.
• the height of the guide member is between 6o and 85 mm. Preferably, the height of the guide member is approximately 70 mm, plus or minus 1 mm.
• the height of the guide member represents between 60 and 65% of the dimension measured between the third plane passing through the end of the plurality of blades closest to the guide and the fourth plane in which the air outlet is inscribed.
• the height of the guide member represents approximately 63%, plus or minus 1%, of the dimension measured between the third plane passing through the end of the plurality of blades closest to the guide member and the fourth plane in which the air outlet mouth fits.
• At least two successive blades overlap at least partially, along a direction parallel to the axis of rotation of the radial propeller. It is understood from this that a portion of a first vane at least partially covers a portion of the second vane successive to the first vane, and that the overlapping portions of the vanes are aligned along a direction parallel to the axis rotation.
• the ventilation device comprises at least one air filter having an air inlet which is inscribed in an air flow inlet plane parallel to the plane in which the air outlet mouth of said ventilation device. It is understood that the plane of entry of the air flow into the air filter and the plane in which the air outlet is inscribed are substantially parallel, that is to say that the planes can be inclined relative to each other at an angle of no more than 2 0 .
• the ventilation device comprises at least one air filter having an inlet which is inscribed in an inlet plane of the air flow coinciding with the plane in which the mouth of the air outlet of said ventilation device.
• the ventilation device comprises at least one heat exchanger having an air inlet which is inscribed in an air flow inlet plane parallel to the plane in which the air outlet mouth of said ventilation device. It is understood that the entry plane of the heat exchanger in the air filter and the plane in which the mouth of the air outlet are substantially parallel, that is to say that the planes can be inclined relative to each other at an angle of at most 2°.
• the ventilation device comprises at least one heat exchanger having an inlet which fits in an air flow inlet plane coinciding with the plane in which the outlet mouth fits of air from said ventilation device.
• the guide member comprises a bowl around which the plurality of vanes is arranged in a regular manner, at least one vane of the plurality of vanes comprising a lower surface and an upper surface extending each between a proximal end of the vane in contact with the bowl and a distal end of the vane in contact with the wall of the housing.
• the ventilation device comprises a drive motor for the radial propeller carried by the bowl of the guide member.
• a dimension measured between the proximal end and the distal end of the blade increases in an increasing manner between the leading edge and the trailing edge.
• a distance measured between the proximal end and the distal end of a blade at its leading edge is smaller than a distance measured between the proximal end and the tip distal of this blade at its trailing edge.
• the blade has a first portion, a second portion and a third portion aligned in this order from the proximal end to the distal end, the blade comprising at least one cross section, view in a plane perpendicular to a radial direction of the axis of rotation, which falls along a line of camber between the leading edge and the trailing edge, this line of camber being different in each of the first , second and third portions of dawn.
• a first radius measured between the axis of rotation and the first portion along a direction radial to the axis of rotation is between 75 and 85 mm
• a second radius measured between the axis of rotation and the second portion measured along a direction radial to the axis of rotation is between 85 and 95 mm
• a third radius measured between the axis of rotation and the third portion measured along a direction radial to the axis of rotation is between 100 and 110 mm.
• the line of camber followed by the blade in each portion falls within a circle, a first angle being formed between a tangent to the circle passing through the leading edge and a direction passing by the leading edge and falling on the one hand in a plane perpendicular to the axis of rotation and on the other hand in a plane in which the circle is inscribed, the first angle having a value between 17 0 and 23 0 at the first portion, a value between 14 0 and 19 0 at the second portion and a value between 10 0 and 15 0 at the third portion.
• a second angle being formed between a tangent to the circle passing through the trailing edge and a direction passing through the trailing edge and falling on the one hand in a plane perpendicular to the axis of rotation and on the other hand in a plane in which the circle is inscribed, the second angle having a value between 95 0 and 100° at the level of the first portion, a value comprised between 105° and 110 ° at the level of the second portion and a value comprised between 112 ° and 117 ° at the level of the third portion.
• the invention also relates to a ventilation, heating and/or air conditioning system for a vehicle, comprising at least one ventilation device according to any one of the preceding characteristics.
• FIG. 1 is a perspective representation of a ventilation device according to one embodiment of the invention.
• FIG. 2 is an exploded view of the ventilation device shown in Figure 1;
• FIG. 3 is a section of a radial propeller of the ventilation device represented in FIG. 1 produced in a plane perpendicular to an axis of rotation of the radial propeller;
• FIG. 4 is a representation in perspective and side view of a radial propeller, a drive motor and the guide member of the ventilation device shown in Figure 1;
• FIG. 5 is a representation in perspective and a top view of the guide member shown in Figure 4.
• FIG. 6 is a perspective representation and a bottom view of the guide member shown in Figure 4.
• FIG. 7 is a representation in perspective and a detail view of a blade of the guide member shown in Figure 4.
• FIG. 8 is a section of the blade represented in figure 7.
• variants of the invention may be associated with each other, in various combinations, insofar as they are not incompatible or exclusive with respect to each other.
• variants of the invention may be imagined comprising only a selection of characteristics described below in isolation from the other characteristics described, if this selection of characteristics is sufficient to confer a technical advantage and/or to differentiate the invention. compared to the prior art.
• upstream and downstream used in the rest of the description refer to the direction of circulation of an air flow through the ventilation device.
• FIG. 1 and 2 is illustrated a ventilation device 1 according to one embodiment of the invention comprising at least one radial propeller 2, a guide member 4 and a housing 6 in which is housed the radial propeller 2 and the guide member
• the housing 6 consists of at least one wall 8 delimiting an internal volume 10 in which is received at least the radial propeller 2.
• This type of ventilation device 1 is configured to be integrated in a ventilation, heating and/or air conditioning system intended to be itself integrated into a vehicle, for example an electrically powered vehicle, so as to thermally treat a flow of air before it is sent in a vehicle cabin. In other words, this air flow is used to cool or heat the vehicle cabin.
• the ventilation device i according to the invention is configured to circulate the flow of air through the ventilation, heating and/or air conditioning system.
• the guide member 4 is arranged axially between an air outlet 12 and the radial propeller 2.
• the ventilation device 1 is configured to drive the radial propeller 2 in rotation around an axis of rotation R so as to generate the flow of air and the guide member 4 participates for its part, together with at least a part of the wall 8 of the casing 6, in straightening the flow of air so that the latter presents a general direction of movement, between an air inlet mouth 14 of the ventilation device 1 and the air outlet mouth 12 of the ventilation device 1, parallel to the axis of rotation R of the radial propeller 2 .
• the ventilation device 1 comprises a drive motor 16 for the radial propeller 2 around the axis of rotation R.
• the drive motor 16 is positioned axially between the guide member 4 and the propeller radial 2.
• the drive motor 16 may be an electric motor which comprises at least one stator and at least one rotor, the rotor being connected in rotation with a shaft received in a hub 18 of the radial propeller 2.
• the axis of rotation R of the radial propeller 2 extends parallel to this hub 18 and passes through the center of the latter.
• the ventilation device 1 comprises at least the casing 6 in which are formed at least the air inlet mouth 14 and the air outlet mouth 12. More particularly, the air inlet mouth 14 is inscribed in a plane and the air outlet mouth 12 is inscribed in a plane substantially parallel to the plane in which the air inlet mouth 14 is inscribed. More particularly, the air inlet mouth 14 and the air outlet 12 are respectively formed in the wall 8 of the casing 6.
• the ventilation device 1 comprises an air filter and/or a heat exchanger 20 arranged at the level of the air outlet mouth 12 of the ventilation device 1 so that the flow of air passes at least partly through the air filter and/or the heat exchanger 20.
• the air filter and/or the heat exchanger 20 can partially close the air outlet mouth 12, or advantageously completely close the air outlet mouth 12.
• the air filter and/or the heat exchanger 20 comprises at least one air inlet in a plane substantially parallel to the plane in which the air outlet mouth 12 of the housing 6 is inscribed, the air inlet of the air filter and/or of the heat exchanger 20 being arranged facing the mouth air outlet 12. “Substantially” means that an angle formed between the two planes of 0 to 20 is tolerated.
• the plane in which the air inlet of the air filter and/or of the heat exchanger 20 fits coincides with the plane in which the air outlet mouth 12 of the housing 6 fits, the air flow being guided directly through the air filter and/or the heat exchanger 20 downstream of the guide member 4 before circulating towards the passenger compartment of the vehicle.
• the housing 6, and more specifically the wall 8 of this housing 6, has a generally bell-shaped shape, that is to say that this housing 6 has a section seen in a plane perpendicular to the axis of rotation R of the radial propeller 2, the dimensions of which increase from the air inlet mouth 14 towards the air outlet mouth 12.
• the wall 8 of the casing 6 defines the internal volume 10 of the ventilation device 1 which houses at least the radial propeller 2 configured to generate the air flow and the guide member 4 configured to direct at least part of the air flow generated by the rotation of the radial propeller 2 in the direction of the axis of rotation R of this radial propeller 2, after it has passed through the guide member 4.
• radial propeller 2 is adapted to be driven in rotation by the drive motor 16 received in the ventilation device 1.
• the housing 6 comprises at least an upper part 19 which houses the radial propeller 2 and a lower part 21 which houses the guide member 4 of the air flow.
• the upper part 20 and the lower part 21 of this casing 6 form two parts of the casing 6 cooperating with each other, that is to say that they are assembled with each other. to form the housing 6 in a plane close to the guide member 4.
• radial propeller 2 means a propeller in which the air enters in a direction parallel to the axis of rotation R of this propeller and leaves it in a direction transverse to the axis of rotation R of the 'helix.
• the axis of rotation R of the propeller radial 2 in the example shown is also parallel to a main extension axis of the housing 6.
• the propeller 2 comprises a plurality of blades 22 each at least delimited by a first axial end 24 and by a second axial end 26.
• the first axial end 24 of each blade 22 is oriented towards the axis of rotation R and the hub 18 of the propeller 2 while the second axial end 26 of each blade 22 is arranged opposite the first axial end 24 and participates in delimiting a radial outlet 25 of the air flow.
• each blade 22 also includes an upper line 28 and a lower line 30, each of these lines 28, 30 extending between the first axial end 24 and the second axial end 26.
• each blade 22 comprises a portion partially opposite the air inlet 14 of the ventilation device 1, in particular close to the first axial end 24, and another portion in contact with and integral with a covering wall 32 of the propeller 2 extending in a ring partially over the upper lines 28 of the plurality of blades 22.
• the lower line 30 of each blade 22 is in contact and integral with a support 34 of the propeller 2 advantageously taking the form of a bowl .
• at least one blade 22 of the radial propeller 2 comprises a concave face 31 and a convex face 33 each extending between along a direction parallel to the axis of rotation R between the lower line 30 and the upper line 28.
• each blade 22 of the radial propeller 2 comprises these concave 31 and convex 33 faces so that a concave face 31 of a blade 22 faces a convex face 33 of a blade 22 successive to said blade 22.
• the plurality of blades 22 force the circulation of the air flow from the air inlet mouth 14 of the ventilation device 1, advantageously disposed at the level of the upper part 19 of the housing 6, towards the radial outlet 25 of the air flow formed by the second axial ends 26 of the blades 22.
• the air flow first circulates along 'a direction substantially parallel to the axis of rotation R, then in a direction extending substantially radially from the axis of rotation R towards the radial outlet 25 of the propeller 2.
• a thickness Ai, A2 of at least one blade 22 of the radial propeller 2 measured along a direction perpendicular to the axis of rotation R is increasing from the first axial end 24 towards the second axial end 26 of this blade 22, a passage section 35 between at least two successive blades 22 of the radial propeller 2 being constant between two ends 24, 26.
• a distance Di between the concave face 31 of a first blade 22a of the radial propeller 2 and the convex face 33 of a second blade 22b successive to this first blade 22a is constant between the first axial end 24 and the second axial end 26 of each of these two blades 22a, 22b. It is understood that the distance Di separating the concave face 31 of a blade 22 with the convex face 33 of the successive blade 22 is constant, that is to say that it does not vary, along a radial direction to the axis of rotation R and along which the two blades 22 substantially extend.
• the distance Di measured between the upper lines 28 of two blades 22 adjacent to each other is identical to a dimension measured between the lower lines 30 of these two successive blades 22 . It is understood that the distance Di separating the concave face 31 of a blade 22 with the convex face 33 of the successive blade 22 is constant along a direction parallel to the axis of rotation R between the upper lines 28 and lower lines 30 of these two successive blades 22.
• each passage section 35 of the air flow of the plurality of blades 22 of the radial propeller 2 has the same dimension.
• the dimensions of the passage section 35 which separates the concave face 31 of the first blade 22a from the convex face 33 of the second blade 22b are similar to the dimensions of a passage section 35 between the concave face 31 of the second blade 22b and the convex face 33 of a third blade 22c which immediately succeeds the second blade 22b.
• the blades 22 are thus distributed evenly around the hub 18.
• the thickness Ai, A2 of each of these blades 22 tends to widen towards the second axial end 26 as one moves away from the first axial end 24.
• This thickness Ai, A2 is measured, for each of the blades 22, along a direction perpendicular to a radius of the radial propeller 2 passing through the center of the blade 22, this direction also being perpendicular to the axis of rotation R of the radial propeller 2.
• the thickness of at least one blade 22 of the radial propeller 2 increases from the first axial end 24 of the blade 22 towards the second axial end 26 of this blade. 22, the thickness being measured as a reminder along a direction perpendicular on the one hand to a radius of the radial propeller 2 passing through the center of the blade 22 and on the other hand to the axis of rotation R.
• a first thickness Ai measured at the level of the first axial end 24 of the blade 22 has a dimension less than the dimension of a second thickness A2 of the blade 22 measured at the level of the second axial end 26 of the blade 22.
• each of these thicknesses Ai, A2 is measured between the concave face 31 and the convex face 33 of the blade 22.
• At least one blade 22 of the radial propeller 2 comprises a recess 37 at its second axial end 26, the recess 37 extending substantially over the entire thickness of the blade 22.
• each blade 22 of the radial propeller 2 comprises this recess 37.
• the recess 37 has a section in the shape of a "U" seen in a plane perpendicular to the axis of rotation R.
• the blade 22 comprising a recess 37 thus comprises a first end 39 and a second end 41 constituting the second axial end 26 of the blade 2, the first end 39 being arranged at the level of the concave face 31 of said blade while the second end 41 is arranged at the level of the convex face 33 of said blade.
• the airflow would not flow through the recess 37 of the blades 22.
• each blade 22 includes the first end 39 and the second end 41.
• the guide member 4 for its part comprises a plurality of vanes 36 at least delimited by a leading edge 38 and by a trailing edge 40 guiding the flow of air circulated by the propeller 2 through the ventilation device 1 towards the axis of rotation R. It is understood from this that the flow of air, circulated by the propeller 2, is guided towards the air outlet mouth 12 of the ventilation device 1 through the guide member 4 and that the plurality of blades 36 refocuses the circulation of the air flow towards the axis of rotation R, the air flow coming into contact with a blade 36 of the plurality of blades 36 at the level with its leading edge 38 and then circulates towards its trailing edge 40. For this, the leading edge 38 of a blade 36 faces the propeller 2 while its trailing edge 40 faces from the air outlet vent 12.
• the plurality of vanes 36 comprises five vanes 36.
• a plurality of vanes 36 comprising at least two vanes 36 would not depart from the scope of the invention.
• a more detailed description of the blade 36 will be made in the following description.
• a height Hi of the guide member 4 measured along a direction parallel to the axis of rotation R between a first plane Ai passing through the leading edge 38 of the plurality of blades 36 and a second plane A2 passing through the trailing edge 40 of the plurality of blades 36 represents at least 55% of a dimension H2 measured between a third plane A3 passing through the end of the plurality of blades 22 closest to the guide member 4 and a fourth plane A4 in which the air outlet mouth 12 fits.
• a first height Hi is measured along a direction parallel to the axis of rotation R between the leading edge 38 and the trailing edge 40 of the plurality of blades 36, a second height H2 being measured along a direction parallel to the axis of rotation R between a corner formed between the lower line 30 and the second axial end 26 of the plurality of blades 22 and the air outlet mouth 12 of the device ventilation 1, the first height Hi representing at least 50% of the second height H2.
• This ratio is necessary to optimize the guiding of the air flow by the guide member 4 from the propeller 2 towards the air outlet mouth 12 and towards the axis of rotation R.
• the first height Hi thus corresponding to the height Hi of the guide member 4, represents between 60 and 65% of the dimension H2 measured between the third plane A3 passing through the end of the plurality of blades 22 furthest close of the guide member 4 and the fourth plane A4 in which the air outlet mouth 12 fits, the dimension H2 corresponding to the second height H2 defined above.
• the height Hi of the guide member 4 is between 60 and 85 mm.
• the second height H2, measured between the corner formed between the lower line 30 and the second axial end 26 of the plurality of blades 22 and the air outlet mouth 12 of the guide device is for its part between 90 and 135 mm. .
• the plurality of vanes 36 is fixed and integral with the wall 8 of the housing 6. It is understood from the foregoing that the plurality of vanes 36 is not not driven in rotation around the axis of rotation R and remains in position to guide the flow of air towards the air outlet mouth 12 and towards the axis of rotation R.
• the guide member 4 comprises a bowl 42 around which the plurality of vanes 36 are regularly arranged.
• This bowl 42 as seen in FIG. 2, is centered with respect to the axis of rotation R , that is to say that the axis of rotation R passes through the center of the bowl 42. It is moreover in this bowl 42 that at least a part of the drive motor 16 of the propeller 2 is lodged.
• At least one blade 36 of the plurality of blades 36 comprises an underside 44 and an upper surface 46 each extending between a proximal end 48 of the blade 36 in contact with the bowl 42 and a distal end 50 of the blade 36 in contact with the wall 8 of the housing 6. It is understood that the proximal end 48 is positioned closest to the axis of rotation R while the distal end 50 is arranged opposite, each of these two ends 48 , 50 extending between the leading edge 38 and the trailing edge 40 of the blade 36.
• the lower surface 44 of a first blade 36a faces the upper surface 46 of a second successive blade 36b, the lower surface 44 of the second blade 36b being opposite the upper surface 46 of a third blade 36c successive to the second blade 36b.
• each of the blades 36 comprises a leading edge 38, a trailing edge 40, an underside 44, an extrados 46, a proximal end 48 and a distal end 50 as described above.
• the description of a characteristic of one of the blades 36 of the plurality of blades 36 in the following description is also valid for the other blades 36 of the plurality of blades 36 unless otherwise stated.
• a dimension measured between the proximal end 48 and the distal end 50 of the blade 36 increases in an increasing manner between the leading edge 38 and the edge of the blade. leak 40.
• the proximal end 48 and the distal end 50 of the vane 36 tend to move away from each other as one moves away from the edge. leading edge 38 and approaching the trailing edge 40 along a direction parallel to the axis of rotation R.
• first width Li of the blade 36 measured the proximal end 48 and the distal end 50 of the blade 36 at the level of its leading edge 38
• second width L2 measured between the end proximal 48 of the blade 36 and the distal end 50 of the blade 36 at its trailing edge 40
• At least two successive blades 36 overlap at least partially, along a direction parallel to the axis of rotation R of the radial propeller. It is understood that at least a portion of the first blade 36a overlaps with a portion of the second blade 36b along a direction parallel to the axis of rotation R, one of the two portions hiding the other portion when the guide member 4 is observed from above or from below.
• the portion of the second blade 36b superimposed on the first blade 36a has been represented by dashes in Figure 5.
• the overlapping portions of the first vane 36a and the second vane 36b are located close to the proximal end 48 of each of the vanes 36.
• the portion of the first vane 36a overlapping the portion of the second vane 36b is located at the level of the leading edge 38 of the first vane 36a, while the portion of the second vane 36b overlapping the portion of the first vane 36a is located at the level of the trailing edge 40 of the second dawn 36b.
• Figures 7 and 8 is illustrated a cross section of a first portion Si of one of its blades 36, a cross section of a second portion S2 of the same vane 36 and a cross section of a third portion S3 of this vane 36, the S2 of the same vane 36 and one and a cross section of a third portion S3 of this vane 36.
• the cross section of the first portion Si is made in a transverse plane Pi located at a first distance Ri from the axis of rotation R passing through the center of the guide member 4, the cross section of the second portion S2 being made in a transverse plane P2 located at a second distance R2 from the axis of rotation R passing through the center of the guide member 4, and the cross section of the third portion S3 being produced in a transverse plane P3 located at a third distance R3 from the axis of rotation R passing through the center of the guide member 4.
• the first transverse plane Pi, the second transverse plane P2 and the third transverse plane P3 are each perpendicular with respect to a radial direction of the axis of rotation R. .
• the first distance Ri measured between the first transverse plane Pi and the axis of rotation R is between 75 and 85 mm, this first distance Ri being the smallest distance measured between the first transverse plane Pi and the axis of rotation R.
• this first distance Ri is about 78 mm.
• the second distance R2 measured between the second transverse plane P2 and the axis of rotation R is between 85 and 95 mm, this second distance R2 being the smallest distance measured between the second transverse plane P2 and the axis of rotation R.
• this second distance R2 is approximately 90 mm.
• the third distance R3 measured between the third transverse plane P3 and the axis of rotation R is between 100 and 110 mm, this third distance R3 being the smallest distance measured between the third transverse plane P3 and the axis of rotation R.
• this third distance R3 is approximately 105 mm.
• the blade 36 extends along a line of camber CA between its leading edge 38 and its trailing edge 40, this line of camber CA being different in each first, second and third portions Si, S2, S3 of blade 36. It will be understood that in each of these portions Si, S2, S3, blade 36 does not extend in one plane.
• the line of camber CA followed by the blade 36 in each portion Si, S2, S3 falls within a circle C. In other words, the blade 36 extends along a line of camber CA s inscribing in a different circle C in each portion Si, S2, S3.
• a first angle bi is formed between a tangent to the circle passing through the leading edge 38 and a direction passing through the leading edge 38 and falling on the one hand in a plane perpendicular to the axis of rotation R and on the other hand in a plane in which the circle C is inscribed, the first angle bi having a value between 17 0 and 23 0 at the level of the first portion Si, a value between 14 0 and 19 0 at the level of the second portion S2 and a value comprised between 10° and 15 0 at the level of the third portion S3.
• the first angle bi has a value of approximately 20° at the level of the first portion S1, of approximately 17 ° at the level of the second portion S2 and of approximately 13 ° at the level of the third portion S3.
• a second angle b2 is formed between a tangent to the circle passing through the trailing edge 40 and a direction passing through the trailing edge 40 and falling on the one hand in a plane perpendicular to the axis of rotation R and on the other hand in a plane in which the circle C is inscribed, the second angle b2 having a value comprised between 95 ° and ioo° at the level of the first portion Si, a value comprised between 105° and 110 ° at the level of the second portion S2 and a value comprised between 112 0 and 117 0 at the level of the third portion S3.
• the second angle b2 has a value of approximately 98° at the level of the first portion S1, of approximately 109° at the level of the second portion S2 and of approximately 115 ° at the level of the third portion S3.
• the present invention cannot however be limited to the means and configurations described and illustrated here and it also extends to any equivalent means and configuration as well as to any technically effective combination of such means.
• the number of blades 36 of the plurality of blades 36 can vary without departing from the scope of the invention, as long as the guide member 4 continues to guide the flow of air towards the outlet mouth of air 12 and the axis of rotation R.

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

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• 2022
  • 2022-07-26 WO PCT/EP2022/070972 patent/WO2023006764A1/fr active Application Filing
  • 2022-07-26 EP EP22748375.7A patent/EP4377572A1/de active Pending
  • 2022-07-26 CN CN202280052755.9A patent/CN117716136A/zh active Pending

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