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
  • F04D29/26—Rotors specially for elastic fluids
  • F04D29/32—Rotors specially for elastic fluids for axial flow pumps
  • F04D29/325—Rotors specially for elastic fluids for axial flow pumps for axial flow fans
  • F04D29/326—Rotors specially for elastic fluids for axial flow pumps for axial flow fans comprising a rotating shroud
• • 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
  • F04D29/26—Rotors specially for elastic fluids
  • F04D29/32—Rotors specially for elastic fluids for axial flow pumps
  • F04D29/325—Rotors specially for elastic fluids for axial flow pumps for axial flow fans
• • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
  • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
  • F01P—COOLING OF MACHINES OR ENGINES IN GENERAL; COOLING OF INTERNAL-COMBUSTION ENGINES
  • F01P11/00—Component parts, details, or accessories not provided for in, or of interest apart from, groups F01P1/00 - F01P9/00
  • F01P11/10—Guiding or ducting cooling-air, to, or from, liquid-to-air heat exchangers
• • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
  • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
  • F01P—COOLING OF MACHINES OR ENGINES IN GENERAL; COOLING OF INTERNAL-COMBUSTION ENGINES
  • F01P5/00—Pumping cooling-air or liquid coolants
  • F01P5/02—Pumping cooling-air; Arrangements of cooling-air pumps, e.g. fans or blowers
• • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
  • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
  • F01P—COOLING OF MACHINES OR ENGINES IN GENERAL; COOLING OF INTERNAL-COMBUSTION ENGINES
  • F01P5/00—Pumping cooling-air or liquid coolants
  • F01P5/02—Pumping cooling-air; Arrangements of cooling-air pumps, e.g. fans or blowers
  • F01P5/04—Pump-driving arrangements
• • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
  • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
  • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
  • F04D19/00—Axial-flow pumps
  • F04D19/002—Axial flow fans
• • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
  • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
  • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
  • F04D25/00—Pumping installations or systems
  • F04D25/02—Units comprising pumps and their driving means
  • F04D25/06—Units comprising pumps and their driving means the pump being electrically driven
• • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
  • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
  • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
  • F04D25/00—Pumping installations or systems
  • F04D25/02—Units comprising pumps and their driving means
  • F04D25/06—Units comprising pumps and their driving means the pump being electrically driven
  • F04D25/0606—Units comprising pumps and their driving means the pump being electrically driven the electric motor being specially adapted for integration in the pump
  • F04D25/066—Linear Motors
• • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
  • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
  • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
  • F04D25/00—Pumping installations or systems
  • F04D25/02—Units comprising pumps and their driving means
  • F04D25/08—Units comprising pumps and their driving means the working fluid being air, e.g. for ventilation
• • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
  • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
  • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
  • F04D25/00—Pumping installations or systems
  • F04D25/02—Units comprising pumps and their driving means
  • F04D25/08—Units comprising pumps and their driving means the working fluid being air, e.g. for ventilation
  • F04D25/12—Units comprising pumps and their driving means the working fluid being air, e.g. for ventilation the unit being adapted for mounting in apertures
• • 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
  • F04D29/26—Rotors specially for elastic fluids
  • F04D29/32—Rotors specially for elastic fluids for axial flow pumps
  • F04D29/325—Rotors specially for elastic fluids for axial flow pumps for axial flow fans
  • F04D29/329—Details of the hub
• • 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
  • F04D29/26—Rotors specially for elastic fluids
  • F04D29/32—Rotors specially for elastic fluids for axial flow pumps
  • F04D29/38—Blades
  • F04D29/384—Blades characterised by form
• • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
  • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
  • F01P—COOLING OF MACHINES OR ENGINES IN GENERAL; COOLING OF INTERNAL-COMBUSTION ENGINES
  • F01P5/00—Pumping cooling-air or liquid coolants
  • F01P5/02—Pumping cooling-air; Arrangements of cooling-air pumps, e.g. fans or blowers
  • F01P5/04—Pump-driving arrangements
  • F01P2005/046—Pump-driving arrangements with electrical pump drive
• • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
  • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
  • F01P—COOLING OF MACHINES OR ENGINES IN GENERAL; COOLING OF INTERNAL-COMBUSTION ENGINES
  • F01P5/00—Pumping cooling-air or liquid coolants
  • F01P5/02—Pumping cooling-air; Arrangements of cooling-air pumps, e.g. fans or blowers
  • F01P5/06—Guiding or ducting air to, or from, ducted fans
• • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
  • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
  • F05B—INDEXING SCHEME RELATING TO WIND, SPRING, WEIGHT, INERTIA OR LIKE MOTORS, TO MACHINES OR ENGINES FOR LIQUIDS COVERED BY SUBCLASSES F03B, F03D AND F03G
  • F05B2240/00—Components
  • F05B2240/20—Rotors
  • F05B2240/33—Shrouds which are part of or which are rotating with the rotor

Definitions

• the invention relates to all the fans of a motor vehicle and more particularly the propellers of these fans.
• the fans participate, for example, to equip electric motors, motor-fan units or sets intended for ventilation and air conditioning of the passenger compartment.
• the invention finds a particularly advantageous application in the context of a motor-fan unit.
• these fans are arranged under the hood and brews a fluid, such as air.
• a fluid such as air.
• the fan motor unit it is located at the front of the vehicle, and cooperates with a heat exchanger also called radiator. More precisely the fan motor unit is located on the radiator so as to force a flow of air through it, which allows to cool the coolant flowing between the radiator and the engine.
• the motor-fan unit provides an efficient air flow to optimize heat exchange with the radiator.
• the fan motor unit facilitates and supports the management of the engine temperature.
• the motor-fan unit comprises a support, allowing a connection of the motor-fan unit to the vehicle, and on which is mounted a fan comprising a propeller and a drive means of the propeller, such as an electric motor.
• the propeller comprises a central hub housing the electric motor in the center of the propeller, which generates a dead zone, in the sense that the entire surface of the propeller is not used to stir the air. The presence of this dead zone causes a loss of performance of the motor-fan unit. In addition, this dead zone at the central hub generates unwanted turbulence on the blade roots of the propeller.
• the performance of the motor-fan unit is also related to the design of the propeller and its design. If the propeller is too big, it can lead to over-consumption. If the propeller is too small, its performance is insufficient, which leads to a risk of overheating of the engine or a malfunction of the air conditioning. A poorly designed propeller can also make noise and generate vibrations that can lead to a breakdown.
• the invention aims to propose a solution so that the fan propeller can ensure fluid mixing, such as a flow of air, sufficient to avoid the risk of overheating of the engine or electric motor vehicle and / or the dysfunction of the air conditioner.
• a propeller of a motor vehicle fan comprising: a cylindrical crown comprising a center, blades extending from the cylindrical crown and towards the center, each blade having two radially opposite ends, referred to as the blade root end and the blade tip end, the blade root end being directed towards the center and the blade tip end being integral with the cylindrical ring, characterized in that all the blade root ends are free.
• the propeller has no central hub solidarisant the blades around the center of the propeller.
• the absence of such a hub improves the performance of the propeller. Indeed, by removing the hub, it also removes the dead zone located along the axis of rotation which allows to use the entire volume of the propeller and increase the volume of fluid stirred by the propeller.
• the helix comprises a free central zone forming an imaginary circle having a diameter less than or equal to 15% of a diameter of the helix.
• the diameter of the helix corresponds to an inner diameter of the cylindrical crown. Indeed, this inner diameter is related to the available surface of stirring of the propeller. Depending on the application of the propeller, this inner diameter is between 25 and 40 centimeters.
• NACA 65 Each blade follows an aerodynamic profile NACA 65 (24) 10.
• NACA profiles are aerodynamic profiles designed for aircraft wings that have been developed by the National Aeronautical Advisory Committee (NACA). The shape of the NACA profiles is described using a series of numbers following the word "NACA”. The parameters in the numerical code can be entered into the equations to accurately generate the section of a blade and calculate its properties.
• the 6 refers to the 6 series
• the 5 corresponds to the position relative to the rope of the minimum pressure on the upper surface (ie 50% of the rope, usually at this point on also has the maximum thickness)
• 24 corresponds to the coefficient of zero incidence lift
• the aerodynamic camber coefficient (multiplied by 10) denoted Cz ⁇ O
• 10 corresponds to the maximum thickness relative to the rope (in percent ).
• the blades are distributed symmetrically on the propeller. By this is meant that the distance separating the same point of several blades is constant.
• the propeller comprises at least six blades. Such a number of blades can transfer more power to the fluid stirred by the propeller, here air.
• Each blade has a rope that increases regularly from the blade root end to the blade tip end.
• the rope corresponds to the straight line connecting the leading edge and the trailing edge in a straight section of the blade.
• the blade root end has a lower rope than a rope from the blade tip end. It is then understood that the blade root end is smaller than the blade tip end.
• the blade root end has a non-zero rope. Thus, it is ensured that the tip of the blade root is not pointed.
• the blade root end has a rope forming an angle of 0 to 80 degrees with the axis of rotation of the propeller.
• the wedge angle of the blade root end is between 0 and 80 degrees.
• the tip end of blade has a rope forming an angle of 40 to 90 degrees with the axis of rotation of the propeller.
• the wedging angle of the blade tip end is between 40 and 90 degrees.
• the end of the blade tip is not inclined to the cylindrical ring.
• the cylindrical ring has a width, measured along an axis of rotation of the helix, such that the blades are entirely contained in a volume defined by the cylindrical ring. It is then understood that the blades do not protrude from the crown, in particular in a direction parallel to the axis of rotation of the helix.
• the blades have a twisted profile from the end of the blade tip to the blade root end, the auger being defined about a torsion axis.
• the propeller comprises at least one electromagnetic element for participating in a drive of the rotating propeller.
• the at least one electromagnetic element is located on the cylindrical crown of the propeller.
• the propeller is configured to cooperate with a belt for participating in a drive of the rotating propeller. More specifically, the cylindrical ring is configured to receive the belt.
• the cylindrical crown of the helix comprises one or more grooves or one or more shoulders making it possible to hold the belt in place on the ring without this generating displacements of the helix with respect to its axis of rotation.
• the helix is configured to cooperate with at least one gear intended to participate in driving the rotating propeller. More specifically, the cylindrical ring is configured to cooperate with at least one of the gears.
• the cylindrical crown of the propeller is intended to receive a toothed rim in order to be able to rotate the propeller by the at least one gear.
• the cylindrical crown of the helix is toothed in order to be rotated by the at least one gear.
• the invention further proposes, according to a second embodiment, a propeller of a motor vehicle fan comprising:
• the diameter of the central hub is less than or equal to 15% of the diameter of the cylindrical ring.
• the propeller has a central hub of small size relative to the size of the helix.
• a central hub which is reduced compared to the prior art, has the sole role of maintaining the propeller on its axis of rotation and is not intended to support or accommodate a motor for rotating the propeller.
• a drive motor of the propeller is necessary but, it will be located at the periphery of the propeller.
• the brewing surface of the propeller available to stir the fluid is increased over the prior art.
• the performance of the propeller is then improved. In this way, it is not necessary to oversize the outer diameter of the propeller to increase the amount of air stirred by the propeller.
• the problems of bulk under hood are avoided, because at equal size, the propeller according to the invention has improved performance.
• the hub is defined as the central part on which the parts, such as the blades, which must rotate about an axis, are assembled.
• Each blade has two radially opposite ends, called blade root end and blade tip end, the blade root end being integral with the central hub and the blade end end being integral with the cylindrical ring.
• the central hub is in the form of a ring in which a zone is left free to form a passage allowing a through of a fluid through the central hub.
• the central hub only serves to secure the blades of the propeller between them.
• the diameter of the cylindrical crown is less than or equal to 43 centimeters. Such a dimension of the propeller is particularly suitable for application to a motor-fan unit fan.
• the diameter of the central hub is between 3 and 4 centimeters. More specifically, the measurement is made at the outer diameter of the central hub.
• the central hub is intended to receive a pin around which the propeller is free to rotate.
• the central hub is intended to receive at least one rotational bearing providing a connection between the central hub and the pin.
• the presence of a rotational bearing allows the propeller to be rotatable relative to the pin integral with a support, unless the rotation bearing is mounted tightly.
• the central hub comprises at least one countersink for receiving the rotation bearing.
• the countersink is concentric with the central hub.
• the central hub is intended to be secured in rotation with a shaft intended to participate in a drive of the rotating propeller.
• the cylindrical ring has a width, measured along an axis of rotation of the helix, such that the blades are entirely contained in a volume defined by the cylindrical ring. It is then understood that the blades do not protrude from the crown, in particular in a direction parallel to the axis of rotation of the helix.
• the central hub has the same width as the width of the cylindrical ring.
• the blades have a twisted profile from the end of the blade tip to the blade root end, the auger being defined about a torsion axis.
• the torsion axis around which the blades have a twisted profile coincides with a radius of the propeller.
• Each blade has a rope that increases regularly from the blade root end to the blade tip end.
• the rope corresponds to the straight line connecting the leading edge and the trailing edge in a straight section of the blade.
• NACA 65 Each blade follows an aerodynamic profile NACA 65 (24) 10.
• NACA profiles are aerodynamic profiles designed for aircraft wings that have been developed by the National Aeronautical Advisory Committee (NACA). The shape of the NACA profiles is described using a series of numbers following the word "NACA”. The parameters in the numerical code can be entered into the equations to accurately generate the section of a blade and calculate its properties.
• the 6 refers to the 6 series
• the 5 corresponds to the position relative to the rope of the minimum pressure on the upper surface (ie 50% of the rope, usually at this point on also has the maximum thickness)
• 24 corresponds to the coefficient of zero incidence lift
• the aerodynamic camber coefficient (multiplied by 10) denoted Cz ⁇ O
• 10 corresponds to the maximum thickness relative to the rope (in percent ).
• the blades are distributed symmetrically on the propeller. By this is meant that the distance separating the same point of several blades is constant.
• the propeller comprises at least six blades. Such a number of blades makes it possible to transfer more power to the fluid stirred by the propeller, here air.
• the blade root end has a lower rope than a rope from the blade tip end. It is then understood that the blade root end is smaller than the blade tip end.
• the blade root end has a non-zero rope. Thus, it is ensured that the tip of the blade root is not pointed.
• the blade root end has a rope forming an angle of 0 to 80 degrees with the axis of rotation of the propeller.
• the wedge angle of the blade root end is between 0 and 80 degrees.
• the tip end of blade has a rope forming an angle of 40 to 90 degrees with the axis of rotation of the propeller.
• the wedging angle of the blade tip end is between 40 and 90 degrees.
• the end of the blade tip is not inclined to the cylindrical ring.
• the propeller comprises at least one electromagnetic element for participating in a drive of the rotating propeller.
• the at least one electromagnetic element is located on the cylindrical crown of the propeller.
• the propeller is configured to cooperate with a belt for participating in a drive of the rotating propeller. More specifically, the cylindrical ring is configured to receive the belt.
• the cylindrical crown of the helix comprises one or more grooves or one or more shoulders making it possible to hold the belt in place on the ring without this generating displacements of the helix with respect to its axis of rotation.
• the propeller is configured to cooperate with at least one gear for participating in a drive of the rotating propeller. More specifically, the cylindrical ring is configured to cooperate with at least one of the gears.
• the cylindrical crown of the propeller is intended to receive a notched rim in order to drive the propeller in rotation by the at least one gear.
• the cylindrical crown of the helix is notched so as to be rotated by the at least one gear.
• the propeller is of the axial type. This means that it is brewing a stream of air in one direction collinear to the direction by which the airflow is sucked.
• the invention also relates to a motor vehicle fan unit comprising a support on which a fan is mounted, the fan comprising a propeller and a device for rotating the propeller, characterized in that the propeller is as defined previously.
• a motor vehicle fan unit comprising a support on which a fan is mounted, the fan comprising a propeller and a device for rotating the propeller, characterized in that the propeller is as defined previously.
• Such fan motor unit optimizes the mixing of an air flow to a heat exchanger for regulating the engine temperature.
• the drive device is located at the periphery of the propeller on the support and cooperates with the cylindrical crown of the propeller. Thus, it is ensured that the drive device does not generate a dead zone in front of the propeller.
• the propeller equipping the motor-fan unit has an outer diameter less than or equal to 40 centimeters.
• the helix has a diameter equal to 40 cm, with manufacturing tolerances.
• FIGS. 1A and 1B are respectively front and perspective views of a first exemplary embodiment of a motor vehicle fan propeller according to the present invention according to a first embodiment, called the first propeller, and in which the ends of FIG. foot of free blade are twisted to the maximum;
• FIGS. 1C to 1E are section and section views from different viewing angles and where the sections were made at different blade heights of the first helix;
• FIG. 1F represents a superposition of the three blade sections visible in FIGS. 1C to 1E;
• FIG. 2A is a perspective view of a second embodiment of a motor vehicle fan propeller according to the present invention according to the first embodiment, called the second propeller and wherein the free blade foot ends are less twisted as the blades of the first propeller;
• FIG. 2B is a superposition of three sections of one of the blades of the second propeller
• FIGS. 3A to 3E are graphical representations showing the evolution of certain geometric characteristics of the first helix as a function of the evolution of the radius of the helix;
• FIGS. 4A to 4E are graphical representations showing the evolution of certain geometrical characteristics of the second helix as a function of the evolution of the radius of the helix;
• FIG. 5 is a perspective view illustrating a motor-fan unit equipped with a propeller according to the present invention according to the first embodiment, and in which a device for driving the propeller comprises electromagnetic elements;
• FIG. 6 is a perspective view illustrating an alternative embodiment of the motor-fan unit equipped with a propeller according to the present invention according to the first embodiment, and in which a device for driving the propeller comprises gears;
• FIG. 7 is a perspective view illustrating an alternative embodiment of the motor-blower unit equipped with a propeller according to the present invention according to the first embodiment, and in which a device for driving the propeller comprises a belt;
• FIGS. 8A to 8D are perspective views taken at different angles of view or in section of a first exemplary embodiment of a motor vehicle fan propeller according to the present invention according to a second embodiment, called third helix;
• FIGS. 9A and 9B are respectively front and perspective views of a second exemplary embodiment of a motor vehicle fan propeller according to the present invention according to the second embodiment, called the fourth helix and in which the ends of FIG. foot of blade are twisted to the maximum;
• FIGS. 9C to 9E are section and section views from different viewing angles and where the sections were made at different blade height of the third helix;
• FIG. 9F represents a superposition of the three blade sections visible in FIGS. 2C to 2E;
• FIG. 10A is a perspective view of a third embodiment of a motor vehicle fan propeller according to the present invention according to the second embodiment, called the fifth helix and wherein the blade foot ends are less twisted that the blades of the fourth helix;
• FIG. 10B is a superposition of three sections of one of the blades of the fifth helix
• FIGS. 11A to 11E are graphical representations showing the evolution of certain geometric characteristics of the fourth helix as a function of the evolution of the radius of the helix;
• FIGS. 12A to 12E are graphical representations showing the evolution of certain geometric characteristics of the fifth helix as a function of the evolution of the radius of the helix;
• FIG. 13A is a perspective view illustrating a first exemplary embodiment of a motor-fan unit equipped with a propeller according to the present invention according to the second embodiment, and in which a device for driving the propeller comprises electromagnetic elements;
• FIG. 13B is a perspective view illustrating an alternative embodiment of the first embodiment motor-fan unit illustrated in FIG. 13A;
• FIG. 14 is a perspective view illustrating a second exemplary embodiment of the motor-fan unit equipped with a propeller according to the present invention according to the second embodiment, and in which a device for driving the propeller comprises gears; ;
• FIG. 15 is a perspective view illustrating a third exemplary embodiment of the motor-fan unit equipped with a propeller according to the present invention according to the second embodiment, and in which a device for driving the propeller comprises a belt. cooperating with the cylindrical crown of the propeller;
• FIG. 16A is a perspective view illustrating a fourth exemplary embodiment of the motor-fan unit equipped with a propeller according to the present invention according to the second embodiment, and in which a drive device of the propeller comprises a belt. cooperating with the central hub of the propeller;
• Figure 16B is a sectional view of the fourth embodiment of the motor-fan unit of Figure 16A.
• Figure lA shows the helix la, also called the first helix la, of a motor vehicle fan comprising the cylindrical ring 2 having a center P, coincides with that of the helix la.
• the inner radius RA of the cylindrical ring 2 is then coincident with the inner radius of the helix la.
• the propeller comprises blades 3 extending from the cylindrical ring 2 and direction of the center P.
• Each blade 3 has two radially opposite ends, called blade root end 4 and end of blade blade 5 ⁇
• blade root end 4 By radially opposed means that according to a radius RA of the helix or the cylindrical crown 2, the end of the blade tip 5 is located furthest from the center P while the blade root end 4 is located closest to the center P, for the same blade 3 ⁇
• the end of 5 blade end is integral with the cylindrical ring 2.
• the blades 3 and the cylindrical ring 2 are molded in one piece so as to form the helix la.
• the cylindrical ring 2 has an outside diameter of between 38 and 42 centimeters and a width L of between 2 and 5 centimeters, the width L being measured in a direction along the axis of rotation RO of the helix la (see Figure 2).
• the fluid stirred by the propeller is air.
• the blade root ends 4 that is to say the ends directed towards the center P, are free.
• the helix la has no central hub solidarisant the blades 3 around the center P of the helix la.
• the absence of such a hub makes it possible to eliminate the dead zone located along the axis of rotation RO, which makes it possible to increase the volume of fluid stirred by the helix la and to overcome undesired turbulence.
• the fact that the blade foot ends 4 are free defines a free central zone around the center P of the helix la.
• This free central zone is in the form of an imaginary circle ⁇ , represented in dashed lines in FIG. 1, having a diameter ⁇ .
• the blade root ends 4 are such that the diameter ⁇ of the imaginary circle ⁇ is less than 15% of the inner diameter of the helix la. Such a ratio makes it possible to ensure that the free central zone around the center P of the helix la is not too large and that air is stirred through this free central zone.
• the propeller comprises six blades 3, such a number of blades 3 can transfer more power to the fluid stirred by the helix la and thus increase the volume of fluid stirred by the helix la.
• the number of blades 3 equipping the propeller la can be revised upwards or downwards.
• a number of blades 3 equal to six represents an optimum in terms of fluid mixing and for the dimensioning of the helix la.
• the propeller is of axial type in the sense that it brews a flow of air in a direction collinear with the direction by which the air flow is sucked.
• the six blades 3 are distributed symmetrically on the helix la. We hear by that the blades 3 are regularly spaced from each other by a distance D for the same point. The distance D is smaller at the blade root ends 4 than at the blade tip ends. According to one embodiment, the blades 3 are arranged asymmetrically to reduce or avoid line noise. for this distance D is different from one blade 3 to another.
• the blades 3 are entirely comprised within the cylindrical ring 2 and do not protrude beyond the cylindrical ring 2, in particular in a radial direction.
• the width L of the cylindrical ring 2, measured along the axis of rotation RO of the wavelet la, is such that the blades 3 are entirely contained in the interior volume delimited by the cylindrical ring 2. It is understood while the blades 3 do not exceed the cylindrical ring 2, in particular in a direction parallel to the axis of rotation RO of the la la la.
• the cylindrical ring 2 has a width L of 4.5 centimeters.
• FIGS. 1B to 1F show that the blades 3 have a twisted profile from the end of the blade tip 4 to the end of the blade root 5, the twist being defined around a torsion axis T.
• the torsion axis T around which the blades 3 are twisted is coincident with a radius RA of the wavelet la or the cylindrical ring 2.
• twist means that each blade 3 has a profile that has undergone a deformation by a rotation about an axis, here the radial axis RA of the la la la.
• the wire la shown in FIGS. 1A to 1F, has blade root ends 4 which have undergone greater torsions than the blade tip ends. Indeed, as can be seen in the section shown in FIG. 1C, the blade root end 4 has a chord C1 parallel to the rotation axis RO of the la la la.
• the rope C of a blade 3 corresponds to the straight line connecting the leading edge 6 and the trailing edge 7 of the blade 3 in a straight section of the blade 3 ⁇
• the leading edge 6 of a blade 3 is the edge which splits the air when the belice is rotating, in other words the leading edge 6 corresponds to the first edge of the blade 3 in contact with the air, and the trailing edge 7 corresponds to the last edge of the blade.
• wedging angle A the angle formed by the rope Cl and the axis of rotation RO of the la la bice, also called wedging angle A, is zero, the spin is therefore maximum.
• the blade root end 4 has a wedging angle A of between 0 and 10 degrees. The measurement of this wedging angle A is done by projection on a median plane of the belice containing it entirely the axis of rotation RO.
• the rope C1 of this blade root end 4 is equal to 2.5 centimeters. In the context of an application to a motor-fan unit, the rope C1 of the blade root end 4 is between 2 and 3 centimeters. The rope C1 of the blade root end 4 being non-zero, it is ensured that this end of the blade root 4 is not in position. point.
• FIG. 1D shows a blade section 3 taken between the blade root end 4 and the blade end end 5. It can be seen that the spin has opened with respect to the section of FIG. 1C. More precisely, the section shown in FIG. 1D shows a rope C2 forming a 60 ° angle of pitch A with the axis of rotation RO, within manufacturing tolerances.
• FIG. 1E shows that the section of the end of the blade end 5 has a rope C3 forming a pitch angle A of 75 degrees with the axis of rotation RO, within manufacturing tolerances.
• the end of blade end 5 has a rope C3 forming a wedging angle A of between 40 and 80 degrees with the axis of rotation RO of the la la la. It is then understood that, the closer one gets to the end of the blade tip 5, along a given blade 3, the more the wedging angle A increases and the spin decreases.
• the blade root end 5 has a rope C3 perpendicular to the axis of rotation RO of the yarn 1a, this means that the end of blade tip 5 is not inclined to the cylindrical ring 2.
• the rope C3 of this blade tip end 5 is equal, according to the example illustrated in FIG. 1E, to 8.5 centimeters. In the context of an application to a motor-fan unit, the rope C3 of the end of blade tip 5 is between 8 and 13 centimeters. It is then observed that the blade root end 4 has a rope C1 less than the rope C3 of the end of blade tip 5 ⁇ It is then understood that the blade root end 4 is smaller than the end. end of blade 5 ⁇
• FIG. 1F showing the different sections of FIGS. 1C to 1E superimposed on each other, shows the evolution of the rope C1, C2, C3 along the blade 3 and around the torsion axis T.
• a wedging angle A, along a blade 3, is therefore between 0 and 80 degrees, with manufacturing tolerances.
• each blade 3 follows an aerodynamic profile NACA 65 (24) 10.
• NACA profiles are aerodynamic profiles designed for aircraft wings that have been developed by the National Aeronautical Advisory Committee (NACA). The shape of the NACA profiles is described using a series of numbers following the word "NACA”. The parameters in the numerical code can be entered into equations to precisely generate the section of a blade 3 and calculate its properties.
• NACA 65 (24) 10 the 6 refers to the 6 series, the 5 corresponds to the position relative to the rope of the minimum pressure on the upper surface, ie 50% of the rope, usually at this point. also has the maximum thickness, the 24 is the coefficient of zero incidence lift, the coefficient of aerodynamic camber multiplied by 10 noted Cz ⁇ O, and finally 10 corresponds to the maximum thickness relative to the rope in percentage.
• FIGS 2A and 2B illustrate an alternative embodiment of the helix la according to the invention, which will be called second helix in the following description.
• This second helix lb has a free central zone, also comprises six blades 3 inscribed in the cylindrical ring 2 which is identical with that of the first helix 1a illustrated in Figures lA to lF.
• the blades 3 of this second propeller lb also have free blade leg ends 4.
• these blades 3 are all identical to each other and also follow an aerodynamic profile NACA type 65 (24) 10.
• this second propeller 1b has blades 3 less twisted than the blades 3 of the first propeller 1a, which has the consequence that the blade root ends 4 of the second propeller 1b are more loaded than the foot ends. of blade 4 of the first helix la.
• the dimensions of the ropes are also different between the first and the second propeller la, lb.
• the rope C4 of the blade root end 4 is, according to this illustrated example, equal to 3 centimeters, with manufacturing tolerances, and the rope C6 of the blade end end 5 is equal to twelve centimeters, manufacturing tolerances close.
• the cords C4, C6 of the ends 4, 5 of the blades 3 of the second propeller lb are larger than the strings C1, C3 of the ends 4, 5 of the blades 3 of the first helix la.
• FIGS. 3A to 3E represent the characteristics of the first helix la while the graphs of FIGS. 4A to 4E represent the characteristics of the second helix 1b.
• These figures illustrate the evolution of certain geometric characteristics of the helix la, lb as a function of the radius RA of the helix la, lb, expressed in meters.
• FIGS. 3A and 4A show that for a given blade 3, whether for the first or the second helix 1a, 1b, the rope C, expressed in meters, increases regularly from the end of the blade root 4 towards the end 5 ⁇ Thus, in each section of the blade 3 taken since the blade root end 4 towards the blade end end 5, the rope C increases uniformly and regularly.
• FIGS. 3B and 4B show the variation of the angle of registration A, expressed in degrees, on the first worm 1a or on the second waddle 1b as a function of the radius RA of the wafer 1a, 1b given. In both cases, it can be seen that the angle of adjustment A increases as one approaches the end of blade end 5, until reaching a limit value of between 70 and 80 degrees.
• These graphs confirm that the twist of the first or the second coil la, lb opens as the connection with the tip end of blade 5 ⁇
• Figures 3 and 4C show the evolution of the tightening S, without units, the first one or the second bélice bifice lb as a function of the radius RA of the wavelet la, lb given.
• the tightening S is defined for a given blade section 3, as being the ratio between the rope C and the distance D between two identical points on two adjacent blades 3. It can be seen that, for the two belts 1a, 1b, the tightening S decreases progressively with the end end of blade 5 until reaching a limit value of between 0.4 and 0.6 for the first yarn la la and between 0.6 and 0.8 for the second yellel lb.
• FIGS. 3D and 4D show the evolution of the coefficient of lift CZ, without unit, of the first or the second waddle lb along the radius RA of the wafer la, lb given.
• the lift coefficient represents the lift that is exerted perpendicularly to the blade 3 ⁇ It can be seen that, for the first yawel la, the coefficient of lift CZ decreases as one gets closer to the end of the blade tip 5 until reaching a limit value of between 0.5 and 1, while for the second yawel lb, the coefficient of lift CZ increases until reaching a maximum value of between 0.8 and 1 as one close to the end of the blade tip 5.
• FIGS. 3E and 4E show the evolution of the flow angles ⁇ , expressed in degrees, on the leading edge 6 (solid line) or on the trailing edge 7 (dotted line) for a blade 3 of the first belice the second or pelice lb along the radius RA of the wafer la, lb given. It can be seen that for the first yarn la, more twisted than the second yarn lb, the difference between the flow angle ⁇ of the leading edge 6 and the flow angle ⁇ of the trailing edge 7 is more large at the blade root end 4 than at the end of blade blade 5 ⁇ For the second yoke lb, the difference between the flow angle ⁇ of the leading edge 6 and the flow angle ⁇ of the trailing edge 7 remains homogeneous all along the blade 3 ⁇
• FIGS. 5 to 7 will now describe the application of a bead according to the invention in a motor-fan unit 10.
• the motor-fan unit 10 enables to optimize the mixing of an air flow towards a heat exchanger intended to regulate the temperature of an engine.
• the first helix la just like the second propeller lb, is particularly well adapted to be mounted in such a motor-fan unit 10.
• the motor-fan unit 10 comprises a support 11 on which a fan 12 is mounted, with the fan 12 comprising the propeller 1a, 1b, 1c and a rotational drive device 13 of the propeller la, lb. More specifically, the support 11 comprises an opening in which the helix la, lb, is located.
• FIGS. 5 to 7 illustrate three types of driving device 13 possible for driving such a propeller 1a, 1b, having it a free central zone ⁇ and the possible configurations that the propeller 1a, 1b can take in order to cooperate with these training devices 13.
• FIG. 5 shows a first exemplary embodiment of the motor-fan unit 10, in which the drive device 13 comprises electromagnetic or magnetic devices, of coil type 14 or magnet. More specifically, according to this embodiment, the drive device 13 comprises 24 coils 14 distributed uniformly around each other, about the axis of rotation RO of the helix la, lb, the. According to an alternative embodiment, the drive device 13 comprises four coils 14 arranged at 90 degrees from each other about the axis of rotation RO of the helix la, lb, the. The helix la, lb, the, in turn, also comprises electromagnetic or magnetic elements having properties for cooperating with the magnetism induced by the coils 14 of the drive device 13, so that the magnetic field drives in rotation the helix la, lb, the. As shown in Figure 5 the electromagnetic elements 15 of the helix la, lb, are magnets and are located, preferably on the cylindrical ring 2 of the helix la, lb, the.
• FIGS. 6 and 7 differ from the embodiment illustrated in FIG. 5, in the sense that the helix 1a, 1b is driven by a mechanical type drive device.
• FIG. 6 shows a second exemplary embodiment of the motor-fan unit 10, in which the drive device 13 comprises gears 16. More precisely, according to this exemplary embodiment, motorized gears 16 are located on a front face of the support 11 and cooperate with an electric motor (not visible) located on a rear face of the support 11, the front face and the rear face being two faces of the support 11 parallel and opposite to each other along the axis of RO rotation of the propeller la, lb, the.
• the motorized gears 16 and the motor are disposed at the periphery of the propeller 1a, 1b, 1c. By this is meant that this drive device 13 does not occupy space on the available surface of the helix la, lb, the.
• the cylindrical ring 2 which includes the teeth 17 to cooperate with the gears 16.
• the teeth 17 may be constituted by an insert in the form of a cylindrical rim which clipper to the cylindrical crown 2 of the propeller la, lb, the.
• the teeth 17 and the cylindrical ring 2 are formed in one piece.
• FIG. 7 shows a third embodiment of the motor-fan unit 10, in which the drive device 13 comprises a belt 18 for driving the propeller 1a, 1b, 1a and a mechanism 19 for driving the belt.
• the mechanism 19 comprises a motor pinion 19a on which the belt 18 is intended to be driven and an electric motor (not visible) rotating the motor pinion 19a.
• the driving pinion 19a of the mechanism 19 is situated on the front face of the support 11 and cooperates with the electric motor situated on the rear face of the support 11.
• the belt 18 cooperates with the cylindrical crown 2 of the propeller the, lb, the in order to drive it in rotation.
• the helix la, lb, and more precisely the cylindrical ring 2 is configured to receive the belt 18.
• the cylindrical ring 2 of the propeller la, lb comprises a shoulder , such as that shown in FIGS. 1A to 2B, to hold the belt 18 and to prevent clearance of the belt 18 relative to the helix 1a, 1b, 1c.
• the propeller la, lb comprises a groove to accommodate the belt 18 and hold it in place.
• the drive device 13 is situated at the periphery of the propeller 1a, 1b, 1c, on the support 11 and cooperates with the cylindrical ring 2 of the propeller. In other words, the drive device 13 is located outside the opening in which is located the helix la, lb, the. Thus, it is ensured that the drive device 13 does not generate a dead zone in front of the propeller 1a, 1b, 1c.
• FIG. 8A shows the helix 1d, also called third helix 1d, of a motor vehicle fan comprising the cylindrical ring 2 having a diameter D2 and a central hub 20 inscribed in the cylindrical ring 2 having a diameter D20 less than the diameter D2 of the cylindrical ring gear 2.
• the central hub 20 and the cylindrical ring gear 2 are concentric with a center P, which also corresponds to the center of the helix 1d.
• the diameter D2 of the cylindrical ring 2 is an internal diameter, that is to say the diameter of the cylindrical ring 2 the smallest.
• This diameter D2 is representative of the stirring surface of the helix 1d through which the stirred fluid circulates through the helix 1d.
• the inner radius RA of the cylindrical ring 2 coincides with the inner radius of the helix ld.
• the propeller 1d comprises blades 3 extending between the cylindrical ring 2 and the central hub 20. More specifically, each blade 3 has two radially opposite ends 4, 5, called the blade root end 4 and the end of the blade end. 5 ⁇
• each blade 3 has two radially opposite ends 4, 5, called the blade root end 4 and the end of the blade end. 5 ⁇
• the blade root end 4 is integral with the central hub 20 while the blade tip end 5 is integral with the cylindrical ring 2.
• the blades 3 and the cylindrical ring 2 are molded in one piece so as to form the ld lug.
• the cylindrical ring 2 has an outside diameter of between 38 and 42 centimeters and a width L of between 2 and 5 centimeters, the width L being measured in a direction along the axis of rotation RO of the wagon ld (see Figure 8D).
• the fluid stirred by the helix ld is air.
• the diameter D20 of the central hub 20 is less than or equal to 15% of the diameter D2 of the cylindrical ring 2.
• central hub 20 The role of such a central hub 20 is to maintain the helix ld on its axis of rotation RO and is not intended to support an electric motor for rotating the helix ld.
• the central hub 20 is defined as a central part of the helix ld on which are assembled the parts, such as the blades 3, which must rotate about the axis of rotation RO.
• a propeller drive motor is required, but as will be described later in connection with Figures 13 to 16, it is located at the periphery of the helix ld.
• the relationship between the two diameters D2, D20 is sufficiently small to overcome the dead zone along the rotation axis RO and to prevent undesired turbulence being generated. Indeed, in the case where the diameter D20 of the central hub is greater than 15% of the D2 diameter of the central ring 2, the dead zone around the axis of rotation RO is generated in which the air does not circulate because not reached by the blades 3 and the air flow stirred. In some cases, it is even preferable that the diameter D20 of the central hub 20 is less than or equal to 10% of the diameter D2 of the cylindrical ring 2 to ensure that air is stirred over the entire brewing surface of the Belice ld. According to a particularly advantageous embodiment, the outer diameter D20 of the central hub 20 is between 3 and 4 centimeters and has the same width as the width L of the cylindrical ring 2.
• FIGs 8B and 8C show an embodiment of the central hub 20 of the ld lice.
• the central hub 20 is intended to receive a fixed pin 21 secured to a fixed support, as will be described below in connection with Figures 13 to 15. So that the wire ld is movable in rotation with respect to the pin 21, the central hub 20 is intended to receive two rotational bearings 22.
• the central hub 20 comprises as much countersink 23 as there is rotation bearing 22 , here two counterscales.
• the countersink 23, the rotation bearing 22 and the pin 21 are concentric, of center P, with the central hub 20.
• the pin 21 is replaced by a shaft 21a rotatable to participate in a drive of the ld lice in rotation.
• the central hub 20 is intended to be integral in rotation with this rotating shaft 21a.
• the central hub 20 is in the form of a ring in which a zone is left free so as to form a passage allowing a fluid to pass through the central hub. .
• the role of the central hub 20 is only to secure the blades 3 of the wagon la between them. The drive of such a ld lice will be described in connection with Figure 14.
• the ld lice shown in Figure 8A, comprises buit blades 3 ⁇
• the number of blades 3 equipping the ld lug can be reviewed at the bend or down.
• the buit 3 blades are distributed symmetrically on the ld lice.
• the blades 3 are regularly spaced from each other by a distance D for the same blade point 3 ⁇
• the distance D is smaller at the blade roots 3 than at the blade tips 3 ⁇
• the ld lice is axial in the sense that it brews a flow of air in a collinear direction to the direction by which the air flow is sucked.
• the blades 3 are entirely within the cylindrical ring 2 and do not protrude beyond the cylindrical ring 2, in particular in a radial direction.
• the width L of the cylindrical ring 2, measured along the axis of rotation RO of the wagon ld, is such that the blades 3 are entirely contained in the interior volume delimited by the cylindrical ring gear 2. It is thus clear that the blades 3 do not protrude from the cylindrical ring gear 2, in particular in a direction parallel to the rotation axis RO of the helix ld.
• the cylindrical crown 2 has a width of 2.5 centimeters.
• the blades 3 are superimposed on each other around the central hub 20 and are inclined by an inclination angle 1 on the cylindrical ring 2.
• the angle of inclination 1 of the blade tip end 5 on the cylindrical ring 2 is equal to 25 degrees, manufacturing tolerances close.
• FIGS. 9A to 9F illustrate an alternative embodiment of the blades 3 of the ld lice.
• the pelice carrying these blades 3 is called the fourth pelice.
• FIGS. 9A and 9B illustrate another variant embodiment of the blades 3 and the coil carrying these blades 3 will be called the fifth wafer 1f in the remainder of the description.
• FIG. 9A illustrates the fourth bead comprising six blades 3 ⁇ It should be noted that in the context of an application to a motor-fan unit, a number of blades 3 equal to six represents an optimum in terms of mixing fluid and for the dimensioning of the pelice the.
• the six blades 3 are distributed symmetrically on the pelice 1c.
• the blades 3 are regularly spaced from each other by a distance D for the same point.
• the distance D being smaller at the blade root ends 4 than at the blade tip ends 5 ⁇
• the blades 3 are arranged asymmetrically to reduce or avoid line noise, for this distance D is different from one blade 3 to another.
• the blades 3 are entirely within the cylindrical ring 2 and do not extend beyond the cylindrical ring 2, in particular in a radial direction.
• the width L of the cylindrical ring 2, measured along the axis of rotation RO of the wafer 1c, is such that the blades 3 are entirely contained in the interior volume delimited by the cylindrical ring 2. It is understood that while the blades 3 do not protrude from the cylindrical ring 2, in particular in a direction parallel to the axis of rotation RO of the wavelet 1c.
• the cylindrical crown 2 has a width of 4.5 centimeters.
• FIGS. 9B to 9F show that the blades 3 have a twisted profile from the blade tip end 4 to the blade root end 5, the twist being defined around an axis of torsion T.
• the torsion axis T around which the blades 3 are twisted coincides with a radius RA of the helix 1c or the cylindrical ring 2.
• twist it is meant that each blade 3 has a profile which has been deformed by a rotation around an axis, here the radial axis RA of the helix 1c.
• the helix 1a shown in FIGS. 9A to 9E, has blade root ends 4 which have undergone greater torsions than the blade tip ends 5 ⁇ Indeed, as can be seen in the section shown in FIG. 9C, the blade root end 4 has a chord C1 parallel to the rotation axis RO of the helix 1c.
• the rope C of a blade 3 corresponds to the straight line connecting the leading edge 6 and the trailing edge 7 of the blade 3 in a straight section of the blade 3 ⁇
• the angle formed by the rope C1 and the RO rotation axis of the helix also called calibration angle A
• the blade root end 4 has a wedging angle A of between 0 and 10 degrees. The measurement of this angle of registration A is made by projection on a median plane of the helix containing it entirely the axis of rotation RO.
• the rope C1 of this blade root end 4 is equal to 2.5 centimeters. In the context of an application to a motor-fan unit, the rope C1 of the blade root end 4 is between 2 and 3 centimeters. The rope C1 of the blade root end 4 is non-zero, it is ensured that this blade root end 4 is not pointed.
• FIG. 9D shows a blade section 3 taken between the blade root end 4 and the blade tip end 5. It can be seen that the spin has opened with respect to the section of FIG. 9C. More precisely, the section shown in FIG. 9D presents a rope C2 forming an angle of alignment A of 60 degrees with the axis of rotation RO, with manufacturing tolerances.
• FIG. 9E shows that the section of the end of blade end 5 has a rope C3 forming an angle of adjustment A of 75 degrees with the axis of rotation RO, with manufacturing tolerances.
• the end of blade tip 5 has a rope C3 forming a wedge angle A of between 40 and 80 degrees with the axis of rotation RO of the helix 1c. It is then understood that, the closer one gets to the end of the blade tip 5, along a given blade 3, the more the wedging angle A increases and the spin decreases.
• the blade root end 5 has a rope C3 perpendicular to the rotation axis RO of the helix 1c, this means that the end of the blade tip 5 is not inclined on the cylindrical ring 2.
• the rope C3 of this blade tip end 5 is equal, according to the example illustrated in FIG. Figure 9E, at 8.5 centimeters. In the context of an application to a motor-fan unit, the rope C3 of the end of blade tip 5 is between 8 and 13 centimeters. It is then observed that the blade root end 4 has a rope C1 less than the rope C3 of the end of blade tip 5 ⁇ It is then understood that the blade root end 4 is smaller than the end. end of blade 5 ⁇
• FIG. 9F shows the evolution of the rope C1, C2, C3 along the blade 3 and around the torsion axis T.
• a wedging angle A, along a blade 3, is therefore between 0 and 80 degrees, with manufacturing tolerances.
• each blade 3 follows an aerodynamic profile NACA 65 (24) 10.
• NACA profiles are aerodynamic profiles designed for aircraft wings that have been developed by the National Aeronautical Advisory Committee (NACA). The shape of the NACA profiles is described using a series of numbers following the word "NACA”. The parameters in the numerical code can be entered into equations to precisely generate the section of a blade 3 and calculate its properties.
• NACA 65 (24) 10 the 6 refers to the 6 series, the 5 corresponds to the position relative to the rope of the minimum pressure on the upper surface, ie 50% of the rope, usually at this point. also has the maximum thickness, the 24 corresponds to the coefficient of zero incidence lift, the aerodynamic camber coefficient multiplied by 10 noted Cz ⁇ O, and finally 10 corresponds to the maximum thickness relative to the rope in percentage.
• FIGS. 9A and 9B illustrate an alternative embodiment of the ld and the wavelet according to the invention, which will be called fifth wafer lf in the following description.
• This fifth wafer lf also comprises six blades 3 inscribed in the cylindrical ring 2 which is identical in all respects with that of the fourth worm illustrated in FIGS. 9A to 9E.
• the blades 3 of this fifth wafer also have free 4 blade foot ends.
• these blades 3 are all identical to each other and also follow an aerodynamic profile NACA type 65 (24) 10.
• the fourth yoke reside in the dimensions of the blades 3 and the angle of rigging A.
• the superposition of the three blade sections 3 of the fifth yarn lf shows that the rope C4 of the blade root end 4 forms a pitch angle A of 30 degrees with the axis of rotation RO of the belfice lf, the rope C5 of the section taken between the two ends 4, 5 of the blades 3 form a stitching angle A of 70 degrees with the axis of rotation RO and the rope C6 of the blade root end 4 forms an angle of adjustment A of 80 degrees with the axis of rotation RO of the belfice lf.
• the wedging angle A changes from 30 degrees to 80 degrees. It is understood that this fifth whale lf has blades 3 less As a result, the blade tips 4 of the fifth helix 1f are more loaded than the blade root ends 4 of the fourth helix 1c.
• the dimensions of the strings are also different between the fourth and the fifth helix le, lf.
• the rope C4 of the blade root end 4 is, according to this illustrated example, equal to 3 centimeters, with manufacturing tolerances, and the rope C6 of the blade end end 5 is equal to twelve centimeters, manufacturing tolerances close.
• the strings C4, C6 of the ends 4, 5 of the blades 3 of the fifth helix lf are larger than the strings C1, C3 of the ends 4, 5 of the blades 3 of the fourth helix 1c.
• FIGS. 11A and 12A show that for a given blade 3, whether for the fourth or the fifth helix 1a, 1f, the rope C, expressed in meters, increases regularly from the blade root end 4 towards the Thus, in each section of the blade 3 taken from the blade root end 4 towards the blade tip end 5, the rope C increases uniformly and evenly.
• FIGS. 11B and 12B show the evolution of the angle of adjustment A, expressed in degrees, on the fourth helix 1a or the fifth helix 1f as a function of the radius RA of the helix 1a, 1f given. In both cases, it can be seen that the angle of adjustment A increases as one approaches the end of blade end 5, until reaching a limit value of between 70 and 80 degrees. These graphs confirm that the spin of the fourth or the fifth helix 1a, 1f opens as it approaches the end of the blade end.
• FIGS 11C and 12C show the evolution of the S tightening, without units, the fourth helix or the fifth helix lf according to the radius RA of the helix le, lf given.
• the tightening S is defined for a given blade section 3, as being the ratio between the rope C and the distance D between two identical points on two adjacent blades 3. It can be seen that, for the two propellers 1a, 1f, the tightening S decreases as it approaches the end end of the blade 5 until reaching a limit value of between 0.4 and 0.6 for the fourth helix le and between 0.6 and 0.8 for the fifth helix lf.
• FIGS. 11D and 12D show the evolution of the coefficient of lift CZ, without unit, of the fourth helix or the fifth helix lf along the radius RA of the helix le, lf given.
• the coefficient of lift CZ represents the lift which is exerted perpendicularly to the blade 3 ⁇ It can be seen that, for the fourth helix 1c, the coefficient of lift CZ decreases as one approaches the end of the blade tip. 5 to reach a limit value between 0.5 and 1, while for the fifth helix lf, the coefficient of lift CZ increases until reaching a maximum value of between 0.8 and 1 as one approaches the end of the blade tip 5.
• FIGS. 11E and 12E show the evolution of the flow angles ⁇ , expressed in degrees, on the leading edge 6 (solid line) or on the trailing edge 7 (dashed line) for a blade 3 of the fourth helix or the fifth helix lf along the radius RA of the helix le, lf given.
• FIGS. 13A to 16B will now describe the application of a propeller 1d, 1a, 1f according to the invention, in a motor-fan unit 10.
• the motor-fan unit 10 optimizes the mixing of an air flow towards a heat exchanger intended to regulate the temperature of an engine.
• the fourth helix 1c just like the fifth helix 1f, is particularly well adapted to be mounted in such a motor-fan unit 10, but the following exemplary embodiments are given with the integration of the fifth helix ld. and variants of this fifth helix ld.
• the motor-fan unit 10 comprises a support 11 on which a fan 12 is mounted, with the fan 12 comprising the helix 1d, the, 1f and a rotational driving device 13 of FIG. the helix ld, the. More specifically, the support 11 comprises an opening 31 in which the helix ld, the, lf is located.
• FIGS. 13A to 16B illustrate five types of driving device 13 possible for driving such a helix 1d, 1a, 1f having a central hub 20 whose diameter D20 is less than or equal to 15% of the diameter D2 of the cylindrical ring 2 and the possible configurations that the helix ld, the, lf can take in order to cooperate with these drive devices 13.
• FIGS. 13A and 13B show a first exemplary embodiment of the motor-fan unit 10, in which the drive device 13 comprises electromagnetic or magnetic devices, of coil type 14 or magnet. More precisely, according to this exemplary embodiment, the drive device 13 comprises 24 coils 14 distributed uniformly among each other. other, around the axis of rotation RO of the helix ld, le, lf. According to an alternative embodiment, the drive device 13 comprises four coils 14 arranged at 90 degrees from each other about the axis of rotation RO of the helix 1d, 1a, 1f.
• the propeller 1d, 1a, 1f for its part, also comprises electromagnetic or magnetic elements having properties that make it possible to cooperate with the magnetism induced by the coils 14 of the drive device 13, so that the magnetic field drives in rotation.
• the helix ld, le, lf As shown in FIGS. 13A and 13B, the electromagnetic elements 15 of the helix 1d, 1c, 1f are magnets and are preferably located on the cylindrical ring 2 of the helix 1d, 1a, 1f.
• the central hub 20 cooperates with the pin 21, which is in the context of this immovable and integral embodiment of the arms 30 participating in the centering of the helix 1d, 1c, 1f in the opening 31 of the support 11.
• the pin 21 is in the context of this immovable and integral embodiment of the arms 30 participating in the centering of the helix 1d, 1c, 1f in the opening 31 of the support 11.
• six arms 31 extend from the support 11 in the direction of the central hub 20.
• the propeller ld, the, lf driven in rotation by the field induced magnetic, turns around the motionless pawn 21.
• FIG. 13B shows a support 11 not equipped with arms 30.
• the helix 1d, 1c, 1f is then supported only by its cylindrical ring 2 in the support 11 and the central hub 20 serves only to secure the blades 3 between them.
• the central hub is preferably hollow so as to allow air to pass through the central hub 20 and more particularly through its free central zone. This is called an annular central hub and has a diameter D20 less than or equal to 15% of the diameter D2 of the cylindrical ring 2.
• FIGS. 14 to 16 differ from the exemplary embodiments illustrated in FIGS. 13A and 13B, in the sense that the helix 1d, the 1f is driven by a mechanical and non-magnetic type drive device. electromagnetic.
• FIG. 14 shows a second exemplary embodiment of the motor-fan unit 10, in which the drive device 13 comprises gears 16. More precisely, according to this exemplary embodiment, motorized gears 16 are located on a front face of the support 11 and cooperate with an electric motor (not visible) located on a rear face of the support 11 from which the arms 30 extend, the front face and the rear face being two faces of the support 11 parallel and opposite one to the other along the axis of rotation RO of the helix ld, le, lf.
• the motorized gears 16 and the motor are disposed at the periphery of the helix 1d, 1c, 1f. By this is meant that this drive device 13 does not occupy space on the available surface of the helix ld, the, lf.
• the helix 1d, 1c, 1f In order for the helix 1d, 1c, 1f to be rotated by these motorized gears 16, this comprises teeth 17. More precisely, it is the cylindrical ring 2 which comprises the teeth 17 to cooperate with the gears 16.
• the teeth 17 may be constituted by an insert in the form of a cylindrical rim which closes to the cylindrical ring 2 of the helix ld, le, lf. According to an alternative embodiment, the teeth 17 and the cylindrical ring 2 are formed in one piece.
• the central hub 20 cooperates with the pin 21, which is in the context of this embodiment immovable and integral arms 30 participating in the centering of the worm ld, the, lf in the opening 31 of support 11.
• FIG. 15 shows a third exemplary embodiment of the motor-fan unit 10, in which the drive device 13 comprises a drive belt 18 for driving the worm ld, the, lf and a mechanism 19 for driving the belt.
• the mechanism 19 comprises a motor pinion 19a on which the belt 18 is intended to be driven and an electric motor (not visible) rotating the motor pinion 19a.
• the motor pinion 19a of the mechanism 19 is situated on the front face of the support 11 and cooperates with the electric motor situated on the rear face of the support 11.
• the belt 18 cooperates with the cylindrical crown 2 of the belice ld, le, lf to rotate it.
• the yarn ld, the, lf and more precisely the cylindrical ring 2 is configured to receive the belt 18.
• the cylindrical ring 2 of the ld lice, the, lf comprises a shoulder , such as that visible in FIGS. 8A to 8B, to hold the belt 18 and to prevent the belt 18 from being disengaged with respect to the ld, lc, lf.
• the waddle ld, the, lf comprises a groove to accommodate the belt 18 and hold it in place.
• the central hub 20 cooperates with the pin 21, which is in the context of this embodiment immovable and integral arms 30 participating in the centering of the worm ld, the, lf in the opening 31 of support 11.
• FIGS. 16A and 16B illustrate a fourth exemplary embodiment of the motor-fan unit 10, in which the drive device 13 comprises a drive belt 18 for driving the disk 1d, 1c, 1f and a mechanism 19 for driving the motor the belt 18. More specifically, the mechanism 19 comprises a motor pinion 19a on which the belt 18 is intended to be driven and an electric motor (not visible) rotating the motor pinion 19a. According to this exemplary embodiment, the driving pinion 19a of the mechanism 19 is situated on the front face of the support 11 and cooperates with the electric motor situated on the rear face of the support 11.
• the belt 18 cooperates with a central gear 19b having an axis of rotation coinciding with the axis of rotation RO of the worm ld, the, lf.
• the central gear 19b is located in a zone Z where all the arms 30 meet.
• this zone Z comprises a housing 35 comprising at least a first opening so that the belt 18 can circulate in the housing 35 in order to rotate the central gear 19b and a second opening 35b traversed by a shaft. 21a.
• the particularity of this fourth embodiment lies in the fact that the pin 21 is replaced by a shaft 21a mobile in rotation. More specifically, the shaft 21a is integral in rotation with the central pinion 19b.
• the shaft 21a when the central gear 19b rotates, the shaft 21a also rotates.
• the, lf the shaft 21a In order to drive in rotation the worm ld, the, lf the shaft 21a is also integral in rotation with the waddle ld, the, lf.
• the rotation bearings 22 are mounted tight.
• the rotational bearings 22 are absent and the shaft 21a is in contact with the coil ld, the, lf in order to drive it in rotation.
• the central hub 20 cooperates with a shaft 21a, which is rotatable.
• this example is different from the others in that the central gear 19b rotating the worm ld, the, lf is located on the rear face of the support 11 from which the arm 30 extend.
• the drive device 13 is located in the periphery of the ld, lc, lf, on the support 11 and cooperates with the cylindrical ring 2 of the lice washer ld, lc, or with its central hub 20. In all cases, the drive device 13 is located in the opening of the opening 31 in which is located the ld, lf, lf. Thus, it is ensured that the drive device 13 does not generate a dead zone in front of the wagon ld, le, lf.

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• Engineering & Computer Science (AREA)
• Mechanical Engineering (AREA)
• General Engineering & Computer Science (AREA)
• Chemical & Material Sciences (AREA)
• Combustion & Propulsion (AREA)
• Structures Of Non-Positive Displacement Pumps (AREA)

Applications Claiming Priority (3)

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• 2018
  • 2018-06-12 EP EP18729685.0A patent/EP3759352A1/de not_active Withdrawn
  • 2018-06-12 US US16/621,508 patent/US11313380B2/en active Active
  • 2018-06-12 WO PCT/EP2018/065560 patent/WO2018229081A1/fr unknown

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