WO2022268588A1

WO2022268588A1 - Ventilation device for a motor vehicle cooling module

Info

Publication number: WO2022268588A1
Application number: PCT/EP2022/066227
Authority: WO
Inventors: Amrid MAMMERI; Kamel Azzouz
Original assignee: Valeo Systemes Thermiques
Priority date: 2021-06-22
Filing date: 2022-06-14
Publication date: 2022-12-29
Also published as: FR3124222B1; FR3124222A1

Abstract

The invention relates to a cooling module (22) for an electric or hybrid motor vehicle (10), said cooling module (22) being intended to have an air flow (F) pass therethrough and comprising: - a set of heat exchangers (23) comprising at least one heat exchanger (23a, 23b, 23c, 23d), - a tangential turbomachine (30) configured to generate the air flow (F), the turbomachine (30) comprising at least two cylindrical turbines (31a, 31b) tangentially arranged along an axis of rotation (A), the turbines (31a, 31b) being independent of each other and each comprising a drive means (35a, 35b).

Description

Ventilation device for motor vehicle cooling module

The invention relates to a cooling module for a motor vehicle, with a tangential turbomachine.

Motor vehicles, whether combustion or electric, need to evacuate the calories generated by their operation and are therefore equipped with heat exchangers. A motor vehicle heat exchanger generally comprises tubes, in which a heat transfer fluid is intended to circulate, in particular a liquid such as water, and heat exchange elements connected to these tubes, often designated by the term " fins” or “spacers”. The fins increase the exchange surface between the tubes and the ambient air.

However, in order to further increase the heat exchange between the heat transfer fluid and the ambient air, it is common for a ventilation device to be used in addition, to generate or increase a flow of air directed towards the tubes and the fins.

In known manner, such a ventilation device comprises a propeller fan.

The airflow generated by the blades of such a fan is turbulent, in particular due to the circular geometry of the propeller, and generally only reaches a part of the surface of the heat exchanger. (circular zone of the exchanger facing the fan blade). The heat exchange is therefore not homogeneous over the entire surface of the tubes and fins.

In addition, when starting the fan is not necessary (typically when heat exchange with non-accelerated ambient air is sufficient to cool the heat transfer fluid circulating in the exchanger), the blades obstruct part of the flow of ambient air towards the tubes and the fins, which hinders the circulation of air towards the exchanger and thus limits the exchange of heat with the heat transfer fluid.

Such a fan is also relatively bulky, in particular because of the necessary dimensions of the propeller to obtain effective engine cooling, which makes it long and tricky to integrate it into a motor vehicle.

To solve this problem, it is known to use a cooling module integrating one or more heat exchangers as well as a tangential turbomachine making it possible to generate an air flow passing through said heat exchangers at low speed or when stopped. of the motor vehicle. Such a turbomachine generally comprises a cylindrical turbine rotated by a drive means such as an electric motor.

However, this solution may not be sufficient in cases where the space plus the integration of such a cooling module is limited, especially since the drive means must be of sufficient power and size to rotate the turbine which is generally very long and therefore relatively heavy.

The object of the invention is to at least partially remedy these drawbacks. And to offer an improved cooling module.

The present invention therefore relates to a cooling module for an electric or hybrid motor vehicle, said cooling module being intended to be traversed by a flow of air and comprising:

- a set of heat exchangers comprising at least one heat exchanger,

- a tangential turbine engine configured to generate the air flow, the turbine engine comprising at least two cylindrical turbines arranged tangentially along an axis of rotation, said turbines being independent and each comprising its own drive means.

According to one aspect of the invention, the turbines of the turbomachine are coaxial.

According to another aspect of the invention, the turbomachine is arranged within an upstream or downstream manifold housing, a first turbine is connected by a first end to a first side of the upstream or downstream manifold housing and by a second end to an intermediate bearing, a second turbine being connected by a first ex tremity to a second side of the upstream or downstream manifold housing, opposite the first side, and by a second end to the intermediate bearing.

According to another aspect of the invention, the drive means of each turbine is arranged on their respective first end.

According to another aspect of the invention, the drive means of the first turbine is arranged on its first end and in that the drive means of the second turbine is arranged on its second end.

According to another aspect of the invention, the turbomachine is arranged within the downstream manifold housing and in that said downstream manifold housing comprises a partition wall extending the intermediate bearing along a plane perpendicular to the axis of rotation of the turbomachine and perpendicular to a guide wall disposed opposite the heat exchanger assembly.

According to another aspect of the invention, the at least two cylindrical turbines each comprise a plurality of blades distributed in stages around their axis of rotation, the first and second turbines comprising an identical number of stages.

According to another aspect of the invention, the at least two cylindrical turbines each comprise a plurality of blades distributed in stages around their axis of rotation, the first and second turbines comprising a distinct number of stages.

According to another aspect of the invention, from one turbine to another, the number of blades per stage, the height, the length, the inclination of the blades as well as the internal and external diameters are identical.

According to another aspect of the invention, from one turbine to another, the number of blades per stage, the height, the length, the inclination of the blades as well as the internal and external diameters are distinct.

Other advantages and characteristics of the invention will appear more clearly on reading the following description given by way of illustrative and non-limiting example, and attached drawings including:

[Fig 1] Figure 1 shows a schematic representation of the front part of a motor vehicle with an electric or hybrid motor, seen from the side,

[Fig 2] Figure 2 shows a schematic representation in perspective of a cooling module,

[Fig 3] The figure shows a schematic representation in perspective of a downstream manifold box of the cooling module of Figure 2,

[Fig 4] Figure 4 shows a schematic representation in perspective and in section of a turbine,

[Fig 5] Figure 5 shows a schematic representation in front view of a downstream manifold box according to a first embodiment,

[Fig 6] Figure 6 shows a schematic representation in front view of turbines according to a second embodiment.

In the various figures, identical elements bear the same reference numbers.

The following achievements are examples. Although the description refers to one or more embodiments, this does not necessarily mean that each reference relates to the same embodiment, or that the characteristics apply only to a single embodiment. Simple features of different embodiments may also be combined and/or interchanged to provide other embodiments.

In the present description, it is possible to index certain elements or parameters, such as for example first element or second element as well as first parameter and second parameter or else first criterion and second criterion, etc. In this case, it is a simple indexing to differentiate and name elements or parameters or criteria that are close, but not identical. This indexing does not imply a priority of one element, parameter or criterion over another and such denominations can easily be interchanged without departing from the scope of the present description. Nor does this indexing imply an order in time, for example, to assess such and such a criterion.

In the present description, the term "upstream" means that one element is placed before another with respect to the direction of circulation of an air flow. On the contrary, by “downstream” we mean that one element is placed after another in relation to the direction of circulation of a flow or a fluid.

In figures 1 to 5, an XYZ trihedron is represented in order to define the orientation of the various elements from each other. A first direction, denoted X, corresponds to a longitudinal direction of the vehicle. It also corresponds to the reverse of the direction of travel of the vehicle. A second direction, denoted Y, is a lateral or transverse direction. Finally, a third direction, denoted Z, is vertical. The directions, X, Y, Z are orthogonal two by two.

Figure 1 schematically illustrates the front part of a motor vehicle 10 with motor 12. The vehicle 10 comprises in particular a body 14 and a bumper 16 carried by a chassis (not shown) of the motor vehicle 10. The body 14 defines a cooling bay 18, that is to say a opening through the body 14. The cooling bay 18 can be unique as in the example illustrated. Alternatively, however, bodywork 14 may define a plurality of cooling bays. Here, the cooling bay 18 is located in the lower part of the front face 14a of the bodywork 14. In the example illustrated, the cooling bay 18 is located under the bumper 16. A grid 20 can be arranged in the cooling bay 18 to prevent projectiles from passing through the cooling bay 18. A cooling module 22 is arranged opposite the cooling bay 18. The grid 20 makes it possible in particular to protect this cooling module 22.

The cooling module 22 is more visible in Figure 2. The cooling module 22 comprises a collector box 24 associated with a set of heat exchangers 23. The cooling module 22 and in particular the set of heat exchangers 23 is in particular intended to be traversed by an air flow F. The collector box 24 is arranged downstream of the set of heat exchangers 23 in the direction of circulation of the air flow F. The cooling module 22 may also include another collector box 25 arranged upstream of the set of heat exchangers 23 in order, for example, to allow the connection with the cooling bay 18 on the front face of the vehicle 10.

This set of heat exchangers 23 comprises at least one heat exchanger having a generally parallelepipedal shape, of which a width L extends parallel to the axis Y, a depth P extends parallel to the axis X and a height H extends parallel to the Z axis.

The heat exchanger or the heat exchangers 23-a, 23b, 23c, 23d delimit(s) a surface S, called the work surface, one section of which is substantially rectangular in a plane Y, Z.

In the case where several exchangers are juxtaposed vertically and/or horizontally, the height of the surface S is the sum of the heights of the exchangers juxtaposed vertically (overlapping), and the length of the surface S is the sum of the lengths of the exchangers juxtaposed horizontally .

In the example illustrated in Figure 2, the set of heat exchangers 23 com carries four heat exchangers 23a, 23b, 23c and 23d. A first heat exchanger 23a can for example be an evapo-condenser intended to be connected to a cooling circuit. A second heat exchanger 23b, disposed downstream of the first heat exchanger 23a in the direction of circulation of the air flow F, can for example be a radiator intended to be connected to a circulation circuit of a first heat-transfer fluid. carrier for the thermal management for example of the batteries of an electric or hybrid vehicle. A third heat exchanger 23c, arranged upstream of the first heat exchanger 23a in the direction of circulation of the air flow F, can for example be a radiator intended to be connected to a circulation circuit of a second heat transfer fluid. for thermal management, for example of the power electronics of an electric or hybrid vehicle. Finally, a fourth heat exchanger 23d, arranged in the same plane as the third heat exchanger 23c, can for example be a sub-cooler intended to be connected to the same cooling circuit as the first heat exchanger 23a. Still according to the example illustrated in FIG. 2, the cooling module 22 also comprises a dehydrating bottle 23e arranged in the same plane as the third 23c and fourth 23d heat exchangers.

The cooling module 22 comprises at least one fan in order to generate the air flow F in particular when the vehicle is traveling at low speed or is stationary. The fan can thus be a tangential turbomachine 30, visible in more detail in Figures 3 and 4. In Figures 2 and 3, this turbomachine 30 is arranged downstream of the set of heat exchangers within the downstream collector housing 24 in order to generate the air flow F by suction. However, it is quite possible to imagine that this turbomachine 30 is arranged upstream of the set of heat exchangers 23 within, for example, the upstream collector box 25.

In the example illustrated in Figures 2 and 3, the cooling module 22 com carries a single turbine engine 30 arranged in the so-called upper part of the downstream manifold housing 24. It is however quite possible to imagine a different position for this turbine engine. 30, for example a low position or even a central position of the downstream manifold housing 24. Similarly, it is quite possible to imagine that the cooling module 22 comprises several turbomachines 30 arranged at separate locations.

In the example illustrated in FIGS. 2 and 3, the downstream manifold housing 24 thus comprises a volute 38 associated with the turbomachine 30. This volute 38 comprises an envelope 40 consisting of a wall shaped to house the turbines 31a, 31b of the turbomachine 30 and guide the air having passed through the exchanger 26 around the turbomachine 30 to an air outlet 44 from the cooling module 22. In known manner, the volute 38 has the shape of a truncated spiral.

The downstream collector box 24 further comprises a guide wall 24a arranged opposite the set of heat exchangers 23. This guide wall 24a makes it possible to guide the flow of air F having passed through the set of heat exchangers 23 towards the turbomachine 30 and the outlet 44. This guide wall 24a may also include flaps (not shown) allowing the air flow F to pass through the said guide wall 24a without passing through the turbomachine 30 and the outlet 44 in particular when the vehicle 10 is rolling and the turbine engine 30 is stationary.

The tangential turbomachine 30 comprises at least two cylindrical turbines 31a, 31b arranged tangentially along an axis of rotation A. These turbines 31a, 31b are preferably coaxial. In the example illustrated in Figures 2 and 3, the axis of rotation A is parallel to the axis Y of the width of the cooling module 22.

Figure 4 shows a 3 lb turbine in more detail in perspective and in cross section. Although not shown, the structure of the turbine 31a is identical to that of the turbine 31b. The turbine 31b comprises a plurality of blades 110 distributed by stages 32b around the axis of rotation A of the turbine 31b. The stages 32b thus form a stack of cylinders along the axis of rotation A in order to form said turbine 31b. The different stages 32b are thus stacked coaxially along the axis of rotation A.

Preferably, the blades 110 of a stage 32b are equally distributed angularly around the axis of rotation. In the example illustrated in Figure A, all the stages 32b have the same number of blades 110. Also, all the blades 110 of the different stages 32b are here identical. The blades 110 can also be angularly offset around the axis of rotation A between two contiguous stages 32b. This offset of the blades 110 makes it possible to reduce the noise generated by the turbine because said blades 110 work in separate groups from one stage to another.

Still according to FIG. 4, each blade 110 has a section with the general shape of a propeller, of which a reference chord, referenced C, is a length between a first edge 110a oriented towards the inside of the turbine 31b and a second edge 110b oriented towards the outside of the turbine 31b. The length C is called blade length 110. The set of second edges 110b of each stage 32b of blades 110 delimits a virtual circle defining an external diameter 0e of the turbine 31b. The set of second edges 110a of each stage 32b of blades 110 delimits a virtual circle defining an internal diameter 0i of the turbine 3 lb.

Each stage 32b has a height corresponding to a height h of the blades 110 composing it. In the embodiment illustrated in FIG. 4, all the stages 32b of the turbine 31b are of the same height h. Nevertheless, the invention is not limited to this configuration, and, depending on the cooling needs, different heights can be envisaged according to the different stages 32b.

From one turbine 31a, 31b to another, the number of stages 32a, 32b as well as the number of blades 110 per stage 32a, 32b can be identical or distinct. Similarly, the height h, the length C, the inclination of the blades 110 as well as the internal diameters 0i and external 0e can be different from one turbine 31a, 31b to another or even identical.

The fact that the turbines 31a, 31b are different from each other makes it possible, in addition to the fact that they are independent, to generate a different air flow F by each of the turbines 31a, 31b. This can make it possible in particular to have a circulation of the air flow F differentiated, for example at the level of heat exchangers having distinct functions and air flow requirements passing through them.

The turbines 31a and 31b are independent of each other and can thus rotate around the axis of rotation A independently. As shown in FIG. 5, a first turbine 31a is connected by a first end 31a-1 to a first side 241 of the downstream manifold housing 24 and by a second end 31a-2 to an intermediate bearing 245. A second turbine 3 lb is itself connected by a first end 3 lb-1 to a second side 242 of the downstream manifold housing 24, opposite the first side 241, and by a second end 31b-2 to the intermediate bearing 245. The intermediate bearing 245 is arranged between the first 241 and the second 242 side of the downstream manifold box 24.

Each turbine 31a, 31b has its own drive means 35a, 35b, for example an electric motor disposed at one of their ends. The fact that the turbines 31a, 3 lb are independent and that they have their own drive means 35a, 35b, allows a reduction in the size as well as the weight of these drive means 35a, 35b. Indeed, the power required to drive each turbine 31a, 31b in rotation is less than that required to drive in rotation a single turbine of a size equivalent to the various turbines 31a, 31b combined. It is thus possible to use drive means 35a, 35b of lower power and therefore smaller and lighter. This also saves space within the cooling module 22.

In addition, these drive means 35a, 35b specific to each turbine 31a, 31b can be controlled jointly so that each of the turbines 31a, 31b rotates at the same speed or else independently, thus making it possible to control the turbines 31a, 31b individually.

According to a first embodiment illustrated in FIG. 5, each turbine 3 la, 3 lb comprises a drive means 35a, 35b arranged at their first end 31a-l and 3 lb-1. The drive means 35a, 35b will then be respectively arranged on the first 241 and the second 242 side of the downstream manifold housing 24.

According to a second embodiment illustrated in Figure 6, a first turbine 31a has its drive means 35a disposed at its first end 31a-l and a second turbine 31b has its drive means 35b disposed at its second end 31b -2. The drive means 35a of the first turbine 31a will then be arranged on one side of the downstream manifold housing 24, here its first side 241, and the drive means 35b of the second turbine 31b will then be arranged at the level of the intermediate bearing 245 .

It is also quite possible to imagine an alternative embodiment (not shown) in which the turbines 31a, 31b all have their drive means 35a, 25b disposed at their second end 31a-2, 31b-2.

The downstream manifold housing 24 may also include a separation wall 24b, extending the intermediate bearing 245 along a plane perpendicular to the axis of rotation A of the turbomachine and perpendicular to the guide wall 24a. This separation wall 24b extends within the downstream collector housing 24 and makes it possible to divide the latter into two circulation zones of the air flow F each comprising a turbine 31a, 31b.

Thus it is clear that the cooling module 22 according to the invention with at least two turbines 31a, 31b independent and each provided with a drive means ment 335a, 35b clean, allows to have a turbomachine 30 extending over the entire width L of the cooling module 32 and this by limiting the size and weight of said drive means 35a, 35b and therefore those of the cooling module 22.

Claims

[Claim 1] Cooling module (22) for an electric or hybrid motor vehicle (10), said cooling module (22) being intended to be traversed by a flow of air (F) and comprising:

- a set of heat exchangers (23) comprising at least one heat exchanger (23a, 23b, 23c, 23d),

- a tangential turbomachine (30) configured to generate the air flow (F), characterized in that the turbomachine (30) comprises at least two cylindrical turbines (31a, 31b) arranged tangentially along an axis of rotation ( A), said turbines (31a, 31b) being independent and each comprising its own drive means (35a, 35b).

[Claim 2] Cooling module (22) according to the preceding claim, characterized in that the turbines (31a, 31b) of the turbomachine (30) are coaxial.

[Claim 3] Cooling module (22) according to any one of the preceding claims, characterized in that the turbomachine (30) is arranged within an upstream (25) or downstream (24) manifold box, a first turbine (31a) is connected by a first end (31a-l) to a first side (241) of the upstream (25) or downstream (24) manifold housing and by a second end (31a-2) to an intermediate bearing (245) , a second turbine (31b) being itself connected by a first end (3 lb- 1) to a second side (242) of the upstream (25) or downstream (24) collector box, opposite the first side (241), and by a second end (31b-2) to the intermediate bearing (245).

[Claim 4] Cooling module (22) according to claim 3, characterized in that the drive means (35a, 35b) of each turbine (31a, 31b) is arranged on their first end (31a-1, 3 lb - 1) respectively.

[Claim 5] Cooling module (22) according to claim 3, characterized in that the drive means (35a) of the first turbine (31a) is arranged on its first end (31a-1) and in that the drive means (35b) of the second turbine (31b) is arranged on its second end (31b-2).

[Claim 6] Cooling module (22) according to any one of Claims 3 to 5, characterized in that the turbomachine (30) is arranged within the downstream manifold housing (24) and in that the said downstream manifold housing ( 24) comprises a partition wall (24b) extending the intermediate bearing (245) along a plane perpendicular to the axis of rotation (A) of the turbomachine and perpendicular to a guide wall (24a) arranged opposite of the heat exchanger assembly (23).

[Claim 7] Cooling module (22) according to any one of Claims 1 to 6, characterized in that the at least two cylindrical turbines (31a, 31b) each comprise a plurality of blades (110) distributed by stages (32a , 32b) around their axis of rotation (A), the first (3 la) and second (3 lb) turbines comprising a number of stages (32a, 32b) identical.

[Claim 8] Cooling module (22) according to any one of Claims 1 to 6, characterized in that the at least two cylindrical turbines (31a, 31b) each comprise a plurality of blades (110) distributed by stages (32a , 32b) around their axis of rotation (A), the first (31a) and second (31b) turbines comprising a distinct number of stages (32a, 32b).

[Claim 9] Cooling module (22) according to any one of Claims 7 to 8, characterized in that, from one turbine (31a, 31b) to the other, the number of blades (110) per stage ( 32a, 32b), the height (h), the length (C), the inclination of the blades (110) as well as the internal (0i) and external (0e) diameters are identical.

[Claim 10] Cooling module (22) according to any one of Claims 7 to 8, characterized in that, from one turbine (31a, 31b) to the other, the number of blades (110) per stage ( 32a, 32b), the height (h), the length (C), the inclination of the blades (110) as well as the internal (0i) and external (0e) diameters are distinct.