EP3820623B1 - Turbine pour dispositif de projection de fluide, dispositif de projection de fluide, ainsi qu'ensemble comprenant un tel dispositif et un outil - Google Patents

Turbine pour dispositif de projection de fluide, dispositif de projection de fluide, ainsi qu'ensemble comprenant un tel dispositif et un outil Download PDF

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Publication number
EP3820623B1
EP3820623B1 EP19737758.3A EP19737758A EP3820623B1 EP 3820623 B1 EP3820623 B1 EP 3820623B1 EP 19737758 A EP19737758 A EP 19737758A EP 3820623 B1 EP3820623 B1 EP 3820623B1
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EP
European Patent Office
Prior art keywords
common axis
face
turbine
turbine body
tube
Prior art date
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Active
Application number
EP19737758.3A
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German (de)
English (en)
French (fr)
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EP3820623A1 (fr
Inventor
Denis Vanzetto
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Exel Industries SA
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Exel Industries SA
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Publication of EP3820623A1 publication Critical patent/EP3820623A1/fr
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Classifications

    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B05—SPRAYING OR ATOMISING IN GENERAL; APPLYING FLUENT MATERIALS TO SURFACES, IN GENERAL
    • B05B—SPRAYING APPARATUS; ATOMISING APPARATUS; NOZZLES
    • B05B5/00—Electrostatic spraying apparatus; Spraying apparatus with means for charging the spray electrically; Apparatus for spraying liquids or other fluent materials by other electric means
    • B05B5/025—Discharge apparatus, e.g. electrostatic spray guns
    • B05B5/04—Discharge apparatus, e.g. electrostatic spray guns characterised by having rotary outlet or deflecting elements, i.e. spraying being also effected by centrifugal forces
    • B05B5/0403—Discharge apparatus, e.g. electrostatic spray guns characterised by having rotary outlet or deflecting elements, i.e. spraying being also effected by centrifugal forces characterised by the rotating member
    • B05B5/0407—Discharge apparatus, e.g. electrostatic spray guns characterised by having rotary outlet or deflecting elements, i.e. spraying being also effected by centrifugal forces characterised by the rotating member with a spraying edge, e.g. like a cup or a bell
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B05—SPRAYING OR ATOMISING IN GENERAL; APPLYING FLUENT MATERIALS TO SURFACES, IN GENERAL
    • B05B—SPRAYING APPARATUS; ATOMISING APPARATUS; NOZZLES
    • B05B13/00—Machines or plants for applying liquids or other fluent materials to surfaces of objects or other work by spraying, not covered by groups B05B1/00 - B05B11/00
    • B05B13/02—Means for supporting work; Arrangement or mounting of spray heads; Adaptation or arrangement of means for feeding work
    • B05B13/04—Means for supporting work; Arrangement or mounting of spray heads; Adaptation or arrangement of means for feeding work the spray heads being moved during spraying operation
    • B05B13/0431—Means for supporting work; Arrangement or mounting of spray heads; Adaptation or arrangement of means for feeding work the spray heads being moved during spraying operation with spray heads moved by robots or articulated arms, e.g. for applying liquid or other fluent material to 3D-surfaces
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B05—SPRAYING OR ATOMISING IN GENERAL; APPLYING FLUENT MATERIALS TO SURFACES, IN GENERAL
    • B05B—SPRAYING APPARATUS; ATOMISING APPARATUS; NOZZLES
    • B05B5/00—Electrostatic spraying apparatus; Spraying apparatus with means for charging the spray electrically; Apparatus for spraying liquids or other fluent materials by other electric means
    • B05B5/025—Discharge apparatus, e.g. electrostatic spray guns
    • B05B5/04—Discharge apparatus, e.g. electrostatic spray guns characterised by having rotary outlet or deflecting elements, i.e. spraying being also effected by centrifugal forces
    • B05B5/0403—Discharge apparatus, e.g. electrostatic spray guns characterised by having rotary outlet or deflecting elements, i.e. spraying being also effected by centrifugal forces characterised by the rotating member
    • B05B5/0411—Discharge apparatus, e.g. electrostatic spray guns characterised by having rotary outlet or deflecting elements, i.e. spraying being also effected by centrifugal forces characterised by the rotating member with individual passages at its periphery
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B05—SPRAYING OR ATOMISING IN GENERAL; APPLYING FLUENT MATERIALS TO SURFACES, IN GENERAL
    • B05B—SPRAYING APPARATUS; ATOMISING APPARATUS; NOZZLES
    • B05B5/00—Electrostatic spraying apparatus; Spraying apparatus with means for charging the spray electrically; Apparatus for spraying liquids or other fluent materials by other electric means
    • B05B5/025—Discharge apparatus, e.g. electrostatic spray guns
    • B05B5/04—Discharge apparatus, e.g. electrostatic spray guns characterised by having rotary outlet or deflecting elements, i.e. spraying being also effected by centrifugal forces
    • B05B5/0415—Driving means; Parts thereof, e.g. turbine, shaft, bearings
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B05—SPRAYING OR ATOMISING IN GENERAL; APPLYING FLUENT MATERIALS TO SURFACES, IN GENERAL
    • B05B—SPRAYING APPARATUS; ATOMISING APPARATUS; NOZZLES
    • B05B5/00—Electrostatic spraying apparatus; Spraying apparatus with means for charging the spray electrically; Apparatus for spraying liquids or other fluent materials by other electric means
    • B05B5/025—Discharge apparatus, e.g. electrostatic spray guns
    • B05B5/04—Discharge apparatus, e.g. electrostatic spray guns characterised by having rotary outlet or deflecting elements, i.e. spraying being also effected by centrifugal forces
    • B05B5/0426—Means for supplying shaping gas

Definitions

  • the present invention relates to a turbine for a fluid projection device and an associated fluid projection device.
  • the present invention also relates to an assembly comprising a tool and a fluid projection device.
  • Fluid projection devices are used in numerous applications, in particular for projecting paints and other coating products such as varnishes. These projection devices frequently comprise a rotating bowl driven in rotation by a turbine, an injector for injecting the fluid into the bottom of the bowl and a skirt for generating air jets for shaping the flow of projected fluid.
  • the document US 2016/059248 discloses such a fluid jetting device.
  • the skirt is generally fixed to a robotic arm of a fluid spraying installation, in particular by screwing the skirt onto a thread formed in one end of the arm. Since the skirts generally have an external surface with cylindrical symmetry, relatively smooth in order to limit the grip of the covering products on the skirt, it is often necessary to use for this a specific tool specific to come to grip the skirt on its external surface. and/or to come into engagement in specific notches made on the outer surface of the skirt for this purpose.
  • the tools then used are complex and it is difficult to control the tightening torque applied using these tools, whereas a high tightening torque is often necessary given the size of the skirts and the importance their good fixation on the arm.
  • the notches made on the outer surface form areas for retaining coating products which therefore contribute to accelerated soiling of the skirt and make it difficult to clean.
  • the use of the tools provided for removing the skirt can be difficult when these notches are partially blocked by the coating products.
  • the positioning of the skirt is therefore difficult to control with precision, since the degree of tightening is likely to vary. This may result in a drop in the quality of the layers of coating product deposited, in particular the presence of grains or even the appearance of defects.
  • a turbine for a fluid projection device comprising a body and a rotor configured to drive a bowl in rotation about an axis, called the common axis of rotation, the rotor being surrounded by the body turbine in a plane perpendicular to the common axis, the turbine further comprising a tube having an outer face and an inner face, the tube being mounted coaxially with the turbine body and intended to be mounted coaxially with the skirt, a first portion of the tube being surrounded by the turbine body, a second portion of the tube being intended to be surrounded by the skirt, the second portion being offset in the downstream direction relative to the first portion, the tube being rotatable around the common axis relative to the turbine body, the turbine body being configured to prevent translation of the tube parallel to the common axis with respect to the turbine body, the second portion having, on the outer face, a first thread intended to engage a second thread provided on the skirt to press the skirt against the turbine body.
  • the turbine body has a shape adapted to allow air to be routed towards a skirt.
  • a fluid projection device comprising a bowl, a turbine as previously described, an injector configured to inject the fluid into the bottom of the bowl, and a skirt at least partially surrounding the bowl in a plane perpendicular to the bowl. common axis and configured to eject gas jets to conform the projected fluid.
  • an assembly comprising a device and a tool configured to engage the internal face of the second portion so as to transmit to the tube a force tending to cause the tube to pivot around the common axis with respect to the turbine body.
  • the description also describes a turbine for a fluid projection device comprising a turbine body and a rotor configured to drive a bowl in rotation relative to the body around a common axis of rotation, the rotor being surrounded by the turbine body in a plane perpendicular to the common axis, the turbine body being configured to guide the rotor in rotation, the rotor being configured to be driven in rotation by a flow of gas, the turbine body being configured to receive the flow of gas in outlet from the rotor and delimiting at least one outlet duct configured to guide a first part of the flow received as far as a space delimited in a plane perpendicular to the common axis by the bowl and the skirt.
  • a turbine for a fluid spray device comprising a turbine body and a rotor configured to drive a bowl in rotation relative to the body around a common axis of rotation, the rotor being surrounded by the turbine body in a plane perpendicular to the common axis, the turbine body being configured to guide the rotor in rotation, the turbine body being adapted so that the injector and the skirt are directly mounted on the turbine body, the bowl being directly mounted on the rotor.
  • a fluid projection device comprising a bowl, a turbine, the rotor being surrounded by the turbine body in a plane perpendicular to the common axis, the turbine body being configured to guide the rotor in rotation, an injector configured to inject fluid into the bottom of the bowl, and a skirt at least partially surrounding the bowl in a plane perpendicular to the common axis and configured to eject gas jets to shape the projected fluid.
  • An installation assembly comprising a mobile arm and a fluid projection device in which the turbine body is mounted directly on the arm.
  • a fluid projection installation 10 is shown partially on the figure 1 .
  • the installation 10 is configured to project a fluid F.
  • the installation 10 is connected to a support 12 which is fixed to a robot.
  • the assembly forms a "spray".
  • the installation 10 comprises a part 15 and a device 20 for projecting the fluid F.
  • the fluid F is, in particular, a coating product such as a paint or a varnish.
  • the fluid F is a paint or a varnish intended to at least partially cover an automobile body panel.
  • Part 15 supports device 20.
  • Part 15 is, in particular, configured to move device 20 in space, in particular to orient device 20 in a plurality of directions in space.
  • Part 15 is, for example, an articulated arm comprising actuators suitable for pivoting the various segments of arm 15 relative to each other to move and orient device 20 in space.
  • Part 15 is also provided to supply device 20 with an electric voltage or current, with at least one flow of gas G and with one flow of fluid F to be projected.
  • the gas G is, for example, air.
  • the part 15 has, for example, a fixing face 22 that is substantially planar.
  • the device 20 is mounted on the fixing face 22.
  • the fixing face 22 is, for example, traversed by a plurality of gas G and fluid F part 15 supply ducts, and by electrical supply conductors of the device 20.
  • the device 20 is configured to project the fluid F.
  • the device 20 comprises a turbine 25, a bowl 30, a skirt 35 and an injector 40.
  • the turbine 25 is configured to drive the bowl 30 in rotation around an axis A, called “common axis”.
  • the turbine 25 is configured to receive from the part 15 a first flow of gas G and to rotate the bowl 30 around the common axis A under the effect of the first flow of gas G.
  • the turbine 25 comprises a rotor 45 and a body 50, also sometimes referred to as a “stator”.
  • the upstream direction D1 and the downstream direction D2 are collinear and opposite to each other.
  • the upstream direction D1 is such that the turbine 25 is offset relative to the skirt 35 in the upstream direction D1.
  • the downstream direction D2 is such that the skirt 35 is offset in the downstream direction D2 with respect to the turbine 25.
  • the turbine 25 is interposed between the skirt 35 and the fixing face 22 of the part 15 along the common axis A.
  • the fixing face 22, the turbine 25 and the skirt 35 are superimposed in this order according to the direction downstream D2.
  • the rotor 45, the skirt 35 and the injector 40 are directly mounted on the turbine body 50.
  • directly mounted is understood in particular to mean a relationship in which two parts are held in position with respect to one another by contact between these two parts. For example, any relative translation movement of these two parts is prevented by the contact between these two parts.
  • Two parts integral in translation but mobile in rotation with respect to each other around the common axis are likely to be qualified as “directly mounted” one on the other.
  • At least one face of each of the parts is in contact with the other part to secure the two parts to each other.
  • a first part screwed to a second part by a screw passing jointly through the first part and the second part is, for example, directly mounted on the second part if the two parts are in contact with each other.
  • the turbine body 50 when the rotor 45, the skirt 35 and the injector 40 are directly mounted on the turbine body 50, the turbine body 50 is capable of allowing relative positioning of the rotor 45, the skirt 35 and the injector 40. In other words, the turbine body 50 holds the rotor 45, the skirt 35 and the injector 40 in position relative to each other.
  • the turbine body 50, the rotor 45, the skirt 35 and the injector 40 form a set of parts integral in translation relative to each other.
  • the turbine body 50 has a shape adapted to allow air to be routed towards the skirt 35.
  • the rotor 45 is directly mounted on the turbine body 50.
  • the rotor 45 is rotatable around the common axis A with respect to the turbine body 50.
  • the rotor 45 is, in particular, configured to be driven in rotation with respect to the turbine body 50 by the first flow of gas G.
  • the rotor 45 delimits a first chamber 52 for receiving the injector 40.
  • the rotor 45 comprises a first portion 55 and a second portion 60.
  • the first chamber 52 extends along the common axis A.
  • the first chamber 52 has, for example, a symmetry of revolution around the common axis A.
  • the first chamber 52 is cylindrical around the common axis A.
  • a first internal diameter is defined for the first chamber 52.
  • the first internal diameter is between 10 millimeters (mm) and 20 mm.
  • the first chamber 52 passes through the rotor 45 along the common axis A.
  • the first chamber 52 passes through both the first portion 55 and the second portion 60 along the common axis A.
  • the first portion 55 is offset in the downstream direction D2 relative to the second portion 60.
  • the first portion 55 is delimited in the upstream direction D1 by the second portion 60.
  • the first portion 55 has a first outer diameter.
  • the first external diameter is between 20 mm and 40 mm.
  • the first portion 55 is configured to drive the bowl 30 in rotation around the common axis A.
  • the first portion 55 has a first downstream end 65 adapted to cooperate with the bowl 30 to secure the first portion 55 and the bowl 30, and a first upstream end 70 fixed to the second portion 60.
  • the first downstream end 65 and the first upstream end 70 is offset in the downstream direction D2 with respect to the first upstream end 70.
  • the first portion 55 has a cylindrical outer face around the common axis A and able to cooperate with the turbine body 50 to guide the rotor 45 in rotation around the common axis A.
  • the outer face of the first portion 55 delimits the first portion in a plane perpendicular to the common axis A.
  • the second portion 60 has a first upstream face 75, a first side face 80 and a first downstream face 85.
  • the second portion 60 is delimited along the common axis A by the first upstream face 75 and by the first downstream face 85.
  • the first upstream face 75 is offset in the upstream direction D1 relative to the first downstream face 85.
  • the first upstream face 75 is perpendicular to the common axis A.
  • the first upstream face 75 faces the upstream direction D1.
  • the first upstream face 75 is substantially planar.
  • the first upstream face 75 is crossed along the common axis by the first chamber 52.
  • the first upstream face 75 comprises, in a known manner, drive members 88 configured to drive the rotor 45 in rotation when the first flow of gas G is directed onto the drive members 88.
  • the drive members 88 include, in particular, a set of blades.
  • the drive members 88 are arranged on a perimeter of the first upstream face 75.
  • the first side face 80 delimits the second portion 60 in a plane perpendicular to the common axis 80.
  • the first side face 80 is cylindrical around the common axis A.
  • the first side face 80 has a second outer diameter.
  • the second external diameter is between 50 mm and 60 mm.
  • the first downstream face 85 surrounds the first portion 55 in a plane perpendicular to the common axis A.
  • the first downstream face 85 faces the downstream direction D2.
  • the first downstream face 85 is substantially planar.
  • the turbine body 50 is directly mounted on the part 15.
  • the turbine body 50 is integral in rotation and in translation with the part 15.
  • the turbine body 50 is fixed to the fixing face 22 of the lar part 15, for example by a plurality of screws.
  • the rotor 45, the injector 40 and the skirt 35 are each mounted on the part 15 via the turbine body 50.
  • the turbine body 50 comprises a first part 50A, called flange 50A, a second part 50B, a third part 50C and a fourth part 50D.
  • the flange 50A, the second part 50B, the third part 50C and the fourth part 50D are aligned in this order along the common axis A, the flange 50A being offset in the upstream direction D1 with respect to the second part 50B, which is offset in the upstream direction D1 with respect to the third part 50C, which is itself offset in the upstream direction D1 with respect to the fourth part 50D.
  • the flange 50A is interposed between the second part 50B and the fixing face 22.
  • the turbine body 50 has a first end face 90 and a second end face 95.
  • the turbine body 50 is delimited along the common axis A by the first end face 90 and by the second face of end 95.
  • the turbine body 50 is configured to receive the first flow of gas G from part 15, in particular through the fixing face 22, and to supply the rotor 45 with the first flow of gas G to drive the rotor 45 in rotation.
  • the turbine body 50 is configured to guide the first flow of gas G to the drive members 88.
  • the turbine body 50 is also configured to receive the first flow of gas G at the outlet of the rotor 45 and to guide the first flow of gas G to the outside of the projection device 20.
  • the turbine body 50 is, moreover, configured to guide a first part P1 of the first flow of gas G received from the rotor 45 to the skirt 35.
  • the turbine body 50 delimits at least a first outlet duct 97.
  • the turbine body 50 delimits two such first outlet ducts 97.
  • the turbine body 50 is furthermore configured to receive a second flow of gas G from part 15 and to supply the skirt 35 with the second flow of gas G without the second flow of gas G driving the rotor 45 in rotation. .
  • the turbine body 50 surrounds the rotor 45 in a plane perpendicular to the common axis A.
  • the turbine body 50 is configured to guide the rotor 45 in rotation.
  • the turbine body 50 delimits a second chamber for receiving the rotor 45 and a third chamber 57 for receiving the injector 40.
  • the turbine body 50 is furthermore configured to guide a second part P2 of the first flow of gas G received from the rotor 45 to the second chamber.
  • the turbine body 50 delimits at least a second outlet duct 100.
  • the turbine body 50 delimits two such second outlet ducts 100.
  • the first end face 90 is made in the fourth part 50D.
  • the first end face 90 is offset in the downstream direction D2 with respect to the second end face 95.
  • the first end face 90 faces the downstream direction D2.
  • the second end face 95 is, in particular, provided in the flange 50A.
  • the flange 50A is delimited by the second end face 95 along the common axis A.
  • the second end face 95 bears against the fixing face 22 of the part 15.
  • the second end face 95 is substantially planar.
  • the second chamber comprises a bearing which is fixed and secured to the turbine body 50.
  • the bearing allows the injection and maintenance of a film of air with the rotor 45 to allow its rotation at high speed.
  • the second chamber also includes an element capable of producing sounds detectable by a microphone, the injection of air being specific.
  • the element makes it possible to estimate the speed of the turbine 25.
  • the first cavity 105 and the second cavity 110 communicate with each other.
  • the first cavity 105 and the second cavity 110 are each cylindrical with a circular base around the common axis A.
  • the first cavity 105 is offset in the downstream direction D2 relative to the second cavity 110.
  • the first cavity 105 accommodates the first portion 55 of the rotor 45.
  • the first cavity 105 is configured to guide the first portion 55 of the rotor 45 in rotation.
  • the second cavity 110 accommodates the second portion 60 of the rotor 45.
  • the second cavity 110 is delimited along the common axis A by a second upstream face 115 and a second downstream face 120 of the turbine body 50.
  • the second cavity 110 is substantially cylindrical around the common axis A.
  • the second portion 60 of the rotor 45 is inserted between the second upstream face 115 and the second downstream face 120 along the common axis A.
  • the second portion 60 is enclosed by the second upstream face 115 and the second downstream face 120.
  • the second upstream face 115 is, for example, provided in the flange 50A, which is represented alone on the picture 3 .
  • the flange 50A is delimited along the common axis A by the second end face 95 and by the second upstream face 115.
  • the flange 50 A is in particular crossed from the second end face 95 to the second upstream face 115 by a set of passages provided to allow the passage of electrical conductors, fluid flow F and gas flow G.
  • the second upstream face 115 is offset in the upstream direction D1 relative to the second downstream face 120.
  • the second upstream face 115 faces the first upstream face 75 of the rotor 45.
  • the second upstream face 115 comprises, for example guide members 125 suitable for allowing rotation of the rotor 45 relative to the turbine body 50.
  • These guide members 125 are for example microperforated parts which make it possible to create a film of air .
  • the guide members 125 are, for example, accommodated in an annular channel 127 centered on the common axis and made in the second upstream face 115.
  • the second upstream face 115 is perpendicular to the common axis A.
  • the second upstream face 115 comprises an annular groove 130 and at least one radial groove 135.
  • the second upstream face 115 comprises two radial grooves 135, one for each first outlet duct 97.
  • the annular groove 130 and the radial groove(s) 135 are made in the flange 50A.
  • the annular groove 130 is configured to collect the first flow of gas G at the outlet of the rotor 45.
  • the annular groove 130 faces the drive members 88.
  • the annular groove 130 is configured to transmit the first part P1 of each first flow of gas G to each first outlet duct 97.
  • the annular groove 130 is configured to transmit the first part P1 to each first outlet duct 97 via the corresponding radial groove 135.
  • the annular groove 130 is, moreover, configured to transmit each second part P2 of the first flow of gas G received from the rotor 45 to the corresponding second outlet duct 100.
  • the annular groove 130 is centered on the common axis A.
  • the annular groove 130 is delimited by two cylindrical faces around the common axis A of the turbine body 50.
  • the annular groove 130 has an outer diameter of between 40 mm and 45 mm.
  • the annular groove 130 has an internal diameter of between 45 mm and 50 mm.
  • the annular groove 130 has a depth, measured along the common axis A, of between 1 mm and 10 mm.
  • Each radial groove 135 extends along a rectilinear clean line L1 contained in a plane perpendicular to the common axis A and is concurrent with the common axis A.
  • the clean lines L1 of the radial grooves 135 are, for example, coincident with the with each other. In other words, the radial grooves 135 are diametrically opposed.
  • Each radial groove 135 extends radially outwards from the annular groove 130.
  • the annular groove 130 is, in particular, interposed between the two radial grooves 135.
  • Each radial groove 135 opens into the annular groove 130.
  • Each radial groove 135 has a length, measured from the annular groove 130 along the proper line L1, of between 15 mm and 20 mm.
  • Each radial groove 135 has a width, measured in a plane perpendicular to the common axis A and in a direction perpendicular to the proper line L1, of between 10 mm and 18 mm.
  • Each radial groove 135 has a depth, measured along the common axis A, of between 5 mm and 15 mm.
  • the depth of the radial groove 135 is, for example, equal to the depth of the annular groove 130.
  • the second downstream face 120 is perpendicular to the common axis A.
  • the second downstream face 120 is opposite the second upstream face 115.
  • the second downstream face 120 is substantially flat.
  • the second downstream face 120 is capable of preventing movement of the rotor 45 in the downstream direction D2 relative to the turbine body 50.
  • the second downstream face 120 bears against the first downstream face 85, for example via guide members 125.
  • Each first outlet duct 97 is, for example, jointly delimited by the second part 50B, the third part 50C and the fourth part 50D.
  • each first outlet duct 97 comprises a plurality of portions opening into each other, these portions each being delimited by one of the second part 50B, the third part 50C and the fourth part 50D.
  • Each first outlet conduit 97 is configured to conduct a first part P1 of the first flow of gas G from the annular groove 130 to the skirt 35.
  • each first outlet duct 97 opens onto the first end face 90, which faces the skirt 35.
  • each first outlet duct 97 is configured to lead the corresponding first part P1 into the free space separating the bowl 30 from the skirt 35.
  • Each first outlet duct 97 opens into the corresponding radial groove 135.
  • Each first outlet duct 97 is entirely delimited by the turbine body 50.
  • each first outlet duct 97 is provided in the turbine body 50 and only in the latter.
  • the first part P1 circulating in the first outlet duct 97 is therefore only in contact with the turbine body 50 while the first part P1 circulates in the first outlet duct 97.
  • Each first outlet duct 97 therefore forms, with the corresponding radial groove 135 and with the annular groove 130, a passage connecting the rotor 45 to the first end face 90. This passage is entirely delimited by the turbine body 50.
  • Each second outlet duct 100 is, for example, made in the flange 50A.
  • Each second outlet duct 100 is configured to transmit a second part P2 of the first flow of gas G from the annular groove 130 to the third chamber 57.
  • Each second outlet duct 100 is entirely delimited by the turbine body 50.
  • each second outlet duct 100 is made in the turbine body 50 and only in the latter.
  • the second part P2 circulating in the second outlet duct 100 is therefore only in contact with the turbine body 50 while the second part P2 circulates in the second outlet duct 100.
  • Each second outlet duct 100 therefore forms, with the annular groove 130, a passage connecting the rotor 45 to the third chamber 57. This passage is entirely delimited by the turbine body 50.
  • the third chamber 57 is made in the flange 50A.
  • the third chamber 57 is configured to partially accommodate the injector 40.
  • the third chamber 57 is offset in the upstream direction D1 relative to the second chamber.
  • the third chamber 57 opens onto the second end face 95 and onto the second upstream face 115.
  • the third chamber 57 therefore communicates with the second chamber, in particular with the second cavity 110 of the second chamber.
  • the third chamber 57 has a third cavity 140 and a fourth cavity 145.
  • Each of the third cavity 140 and the fourth cavity 145 is cylindrical around the common axis A.
  • the third cavity 140 is interposed between the fourth cavity 145 and the second cavity 110.
  • the third cavity 140 has a diameter of between 12 mm and 15 mm.
  • the third cavity 140 has a length, measured along the common axis A, of between 10 mm and 30 mm.
  • Each second outlet duct 100 opens into the third cavity 140.
  • the first support face 150 is annular, and centered on the common axis A.
  • the first support face 150 is substantially planar.
  • the first support face 150 is perpendicular to the common axis A.
  • the first bearing face 150 delimits the fourth cavity 145 in the downstream direction D2.
  • the first bearing face 150 is provided to bear against the injector 40 to prevent the injector 40 from moving in the downstream direction D2 relative to the turbine body 50.
  • the bowl 30 is directly mounted on the rotor 45.
  • the bowl 30 is fixed to the first upstream end 65 of the first portion 55 of the rotor 45.
  • the rotor 45 is then interposed between the bowl 30 and the second upstream face 115 along the common axis A.
  • the bowl 30 is configured to be driven in rotation around the common axis A by the rotor 45 to generate the flow of fluid F to be projected.
  • the bowl 30 is configured to receive the fluid F to be projected from the injector 40 at the level of the bottom 151 of the bowl 30.
  • the bowl 30 protrudes from the skirt 35 in the downstream direction D2.
  • the skirt 35 is configured to generate a set of jets of gas G, these jets being adapted to shape the projected fluid F.
  • the skirt 35 is configured to receive the first flow and the second flow of gas G and to generate the gas jets G from the first and second flows received.
  • the skirt 35 surrounds the bowl 30 in a plane perpendicular to the common axis A.
  • the skirt 35 delimits in particular an opening 152 for receiving the bowl 30. This opening 152 opens onto the face of the skirt which delimits the skirt 35 in the direction downstream D2.
  • the skirt 35 bears against the first end face 90 of the turbine body 50.
  • the turbine body 90 is interposed, along the common axis A, between the fixing face 20 of the part 15 and the skirt 35.
  • the skirt 35 is fixed to the turbine body 50 so as to eliminate all the degrees of freedom between the turbine body and the skirt 50.
  • the injector 40 is configured to inject the flow of fluid F to be projected into the bottom 151 of the bowl 30.
  • the injector 40 is directly mounted on the turbine body 50.
  • the injector 40 is received at least partially in the third chamber 57.
  • the injector 40 is configured so that, when the injector 40 is received in the third chamber 57, a relative translational movement of the injector 40 with respect to the turbine body 50 in a plane perpendicular to the common axis A is stop.
  • the injector 40 is, in addition, fixed to the turbine body 50 by fixing means such as screws to prevent a respective rotation of the injector 40 and the turbine body 50 around the common axis A, and/or to prevent a relative translation of these two parts along the common axis A.
  • the injector 40 is received in the first chamber 52 formed in the rotor 45.
  • the injector 40 is configured to allow a relative movement of rotation around the common axis A between the rotor 45 and the injector 40.
  • the injector 40 is not in contact with the walls of the rotor 45 which delimit the first chamber 52.
  • the rotor 45 and the injector 40 delimit a free volume, which corresponds to the portion of the first chamber 52 which is complementary to the injector 40.
  • the injector 40 comprises an injection member 155 and an injector body 160.
  • the injector 40 is configured so that the free volume is in communication with the bottom 151 of the bowl 30.
  • the injection member 155 is received in a cavity of the bowl 30 opening into the bottom 151 of the bowl 30, and has an external diameter strictly inside the internal diameter of this cavity, so that a gas, in particular gas G, is able to circulate from the free volume to the bottom 151 of the bowl 30 in the interval between the walls of this cavity and the injection member 155.
  • the injector 40 is configured so that each second outlet pipe 100 is in communication with the free space.
  • the second outlet duct 100 and the free space form an auxiliary duct suitable for transmitting the second part P2 of the first flow of gas G from the annular groove 130 to the bottom 151 of the bowl 30.
  • the injection member 155 is configured to inject the flow of fluid F to be projected into the bottom 151 of the bowl 30.
  • the injection member 155 is offset in the second direction D2 relative to the injector body 160.
  • the injector body 160 is configured to receive the flow of fluid to be projected F from part 15, and to transmit the flow of fluid to be projected F to the injection member 155.
  • the injector body 160 comprises a third portion 165, a fourth portion 170, a fifth portion 172 and a collar 175.
  • the third portion 165, the fourth portion 170, the fifth portion 172 and the flange 175 are offset in this order relative to each other in the upstream direction D1.
  • the injection member 155 is mounted on the third portion 165.
  • the third portion 165 is cylindrical around the common axis A.
  • the third portion 165 is delimited along the common axis by the injection member 155 and by the fifth portion 172.
  • the diameter of the third portion 165 is between 5 mm and 15 mm.
  • the fourth portion 170 is delimited along the common axis A by the collar 175 and by the fifth portion 172.
  • the fourth portion 170 is accommodated in the third cavity 140.
  • the fourth portion 170 is cylindrical around the common axis A.
  • the diameter of the fourth portion 170 is strictly greater than the diameter of the third portion 165.
  • the fourth portion 170 has a length, measured along the common axis, strictly less than the distance between the end of each second conduit 100 and the fourth cavity 145, so that each second conduit 100 opens into the third cavity 140 facing of the fifth portion 172.
  • the fifth portion 172 is interposed along the common axis A between the third portion 135 and the fourth portion 170.
  • the fifth portion 172 is delimited along the common axis A by the third portion 135 and the fourth portion 170.
  • the fifth portion 172 is in the shape of a truncated cone centered on the common axis A.
  • the diameter of the fifth portion 172 decreases from one end delimited by the fourth portion 170 to another end delimited by the third portion 165.
  • the diameter of the fifth portion 172 is strictly less than the diameter of this third cavity.
  • the second part P2 of the first flow of gas G is capable of being delivered by the second outlet duct 100 into the free volume.
  • the collar 175 is cylindrical around the common axis A.
  • the collar 175 has a thickness, measured along the common axis, substantially equal to the length of the fourth cavity 145.
  • the diameter of the collar 175 is substantially equal to the diameter of the fourth cavity 180.
  • the collar 175 has a second bearing face 180 and a third bearing face 185.
  • the collar 175 is delimited along the common axis A by the second and third bearing faces 180 and 185.
  • the thickness of the collar 175 is measured between the second and third bearing faces 180 and 185.
  • the second support face 180 is perpendicular to the common axis A.
  • the second support face 180 bears against the first support face 150. Thus, a translation of the injector 40 in the downstream direction D2 with respect to the turbine body 50 is prevented.
  • the third bearing face 180 is, for example, bearing against the fixing face 22 of the part 15 when the projection device 20 is fixed from the part 15, so that the collar 75 is clamped between the fixing face 22 and the first bearing face 150 formed in the turbine body 50.
  • the third bearing face 180 and the second end face 95 are coplanar.
  • the thickness of the collar 175 is strictly less than the length of the fourth cavity 145, so that the third bearing face 180 is not bearing against the face fixing 22.
  • the rotor 45, the skirt 35 and the injector 40 are mounted directly on the turbine body 50.
  • the second, third and fourth pieces 50B, 50C and 50D are attached to each other.
  • the rotor 45 is then inserted into the second chamber by a translation in the downstream direction D2, then the flange 50A is fixed to the second part 50B to enclose the second portion 60 of the rotor 45.
  • the rotor 45 is therefore fixed to the turbine body 50 by a mechanical connection allowing a single degree of freedom , which is a rotation along the common axis A.
  • the injector 40 is inserted into the second and third chambers 52, 57 by a translation movement in the downstream direction D2 until the second bearing face 180 is pressed against the first bearing face 150. injector 40 is then fixed to the turbine body by a mechanical connection allowing only relative translation in the upstream direction D1 between these two parts, and optionally relative rotation around the common axis A.
  • the injector 40 is, in addition, fixed to the turbine body 50 by fixing members so as to eliminate all the degrees of freedom remaining between these two parts.
  • the skirt 35 is then positioned against the turbine body 50 in such a way that the skirt 35 bears against the first end face 90.
  • the skirt 35 is fixed to the turbine body 50 so as to eliminate all the degrees of freedom between the skirt 35 and the turbine body 50.
  • an assembly comprising the turbine body 50, the rotor 45, the skirt 35 and the injector 40.
  • the various elements of this assembly are integral in translation with each other. .
  • the bowl 30 is mounted on the rotor 45 to form the projection device 20.
  • the third step is implemented after the first step.
  • the assembly comprising the turbine body 50, the rotor 45, the skirt 35 and the injector 40 is mounted on the part 15.
  • the turbine body 50 is mounted directly on the part 15, for example by pressing the second end face 95 against the fixing face 22 and by screws passing jointly through the part 15 and the body of the turbine. turbine 50.
  • the turbine body 50 and the part 15 form a mechanical connection eliminating all the degrees of freedom between the turbine body 50 and the part 15.
  • the third step is implemented after the second step.
  • the projection device 20, further comprising the bowl 30 is fixed to the part 15.
  • the relative positioning of these parts is improved.
  • the precision of the positioning of the skirt 35 and the injector 40 relative to the bowl 30 is improved, in particular compared to known devices where the skirt 35 and the injector 40 are fixed to the part 15 and not to the turbine body 50.
  • the number of parts involved in the positioning of the bowl 30 with respect to the skirt 35 and the injector 40 is reduced, since only the turbine body 50 and the rotor 45 connect the bowl 30 to the skirt 35 and to the injector 40.
  • the improvement in the positioning of the bowl 30 with respect to the skirt 35 and to the injector 40 allows better control of the conformation of the projected fluid F, since the jets of gas G to conform the jet of fluid F are better positioned with respect to in bowl 30.
  • the replacement of the projection device 20 is made faster since it is possible to pre-assemble the rotor 45, the skirt 35 and the injector 40 on the turbine body 50, and to pre-assemble the bowl 30 on the rotor 45, before fixing the device 20 thus obtained in a simple manner on the part 15, by the single fixing of the turbine body 50 to the part 15.
  • the presence of the first conduit 97 makes it possible to inject the first part P1 of the first flow G between the bowl 30 and the skirt 35, this air serving as compensation air to fill the depression under the bowl linked to the rotation of the bowl and to the injection of skirt tunes.
  • the cold air flow circulating internally in the turbine the cold air flow whose temperature can be as cold as -40°C does not come into contact with an interface between plastic and metal. Indeed, since the two materials have different coefficients of expansion, exposure to cold air could lead to sealing problems.
  • the conformation chosen for the impeller also makes it possible to improve the durability of the seal in the sprayer.
  • the auxiliary passage makes it possible to inject the second part P2 into the bottom 151 of the bowl 30 and thus to fill a depression which could be caused there by the rotation of the bowl 30.
  • the part 15 and in particular the fixing face 22 are simplified when the ducts 97 and 100 are provided in the turbine body 50, since it is the turbine body 50 which receives the first flow of gas G at the outlet of the rotor 45. It is therefore not necessary to conform the fixing face 22 to receive and evacuate the first flow of gas G at the outlet of the rotor.
  • the relative positioning of the injector 40 with respect to the turbine body 50 is better controlled. This results in better control of the distribution of the first flow of gas G, at the outlet of the rotor 45, between the first part P1 and the second part P2.
  • the turbine body 25 is arranged so that in operation, the ratio between the flow rate of the first part P1 of the gas flow and the second part P2 of the gas flow is greater than or equal to 2, preferably greater than or equal to 3 and preferably greater than or equal to 10. Such an effect is obtained in particular by a judicious choice of the size of the outlet duct 97 and of the size of the auxiliary passage.
  • the annular groove 130 allows a collection of the first flow of gas G at the outlet of the rotor 45 with a very reduced axial bulk. The dimensions of the projection device 20 are therefore reduced.
  • the radial grooves 135 make it possible to recover more and more exhaust air without recompressing it so as not to slow down the turbine 25.
  • the radial grooves 135 are diametrically opposed to each other, the first parts P1 of the flow of gases G collected by conduits 97 are equal.
  • the flow of gas G injected between the skirt 35 and the bowl 30 is then more spatially homogeneous.
  • the bearing of the first and second bearing surfaces 150 and 180 allows precise and simple positioning of the injector 40 relative to the turbine body 50.
  • Numerous fastening means are likely to be used to eliminate all the degrees of freedom between the skirt 35 and the turbine body 50, for example screws passing jointly through the skirt 35 and the turbine body 50. It should be noted that other means are likely to be used to directly mount the skirt 35 on the turbine body 50.
  • the skirt 35 and the turbine body 50 have threads complementary to each other to allow a screwing of the skirt 35 on the turbine body 50.
  • the fluid projection device 20 further comprises a threaded tube 190, visible in particular on the figure 2 and represented separately on the figure 4 and 5 .
  • the skirt 35 has an internal face 193.
  • the internal face 193 of the skirt 35 is the face of the skirt 35 which surrounds the bowl 30 and which faces the bowl 30.
  • the internal face 193 delimits the opening 152 in which bowl 30 is received.
  • the internal face 193 has a symmetry of revolution around the common axis A.
  • a minimum diameter is defined for the internal face 193 of the skirt 35.
  • the minimum diameter is measured in a plane perpendicular to the common axis A between the two diametrically opposite points of the internal face 193 which are closest to one of the other.
  • the inner face 193 has a thread 195.
  • the thread 195 surrounds the bowl 30 in a plane perpendicular to the common axis A.
  • the threaded tube 190 is sometimes also referred to as a "nut” or even an “idle nut”.
  • the threaded tube 190 is mounted coaxially to the skirt 35 and to the turbine body 50.
  • the threaded tube 190 is centered on the common axis A.
  • the threaded tube 190 is mounted directly on the turbine body 50.
  • the threaded tube 190 is secured to the turbine body 50 in translation.
  • the turbine body 50 delimits an annular groove 197 receiving at least a portion of the threaded tube 190 and has faces capable of preventing a relative translation of the threaded tube 190 and of the turbine body 50.
  • the annular groove 197 is, for example, made in the third part 50C and extends along the common axis A from a downstream surface of the third part 50C, this downstream surface delimiting the third part in the downstream direction D2 .
  • the threaded tube 190 is rotatable around the common axis A with respect to the turbine body 50.
  • the threaded tube 190 is, for example, made of steel.
  • the threaded tube 190 has a symmetry of revolution around the common axis A.
  • the threaded tube 190 has an internal face 200 and an external face 205.
  • the threaded tube 190 is delimited by the internal face 200 and by the external face 205 in a plane perpendicular to the common axis A.
  • the threaded tube 190 comprises at least a primary portion 210 and a secondary portion 215. According to the example of figure 4 , the threaded tube 190 further comprises a tertiary portion 220 interposed between the primary portion 215 and the secondary portion 215 along the common axis A.
  • the primary portion 210 is offset in the upstream direction D1 relative to the tertiary portion 220.
  • the primary portion 210 is in the form of a cylinder with an annular base.
  • the primary portion 210 is delimited by two cylindrical surfaces each centered on the common axis A.
  • the primary portion 210 is in particular delimited by these two surfaces in a plane perpendicular to the common axis A.
  • the primary portion 210 has a third downstream face 225 and a third upstream face 230.
  • the primary portion 210 is surrounded by the turbine body 50 in a plane perpendicular to the common axis A.
  • the primary portion 210 is in particular accommodated in the opening 152.
  • the primary portion 210 is accommodated in the annular groove 197.
  • the faces of the turbine body 50 which delimit the annular groove 197 in a plane perpendicular to the common axis A are configured to prevent a translation of the threaded tube 190 with respect to to the turbine body 50 in a plane perpendicular to the common axis A.
  • the primary portion 210 has an outer diameter of between 45 mm and 60 mm.
  • the primary portion 210 has an internal diameter of between 40 mm and 55 mm.
  • the primary portion 210 is delimited in the downstream direction D2 by the third downstream face 225.
  • the third downstream face 225 is perpendicular to the common axis A.
  • the third downstream face 225 faces the downstream direction D2.
  • the third downstream face 225 surrounds the tertiary portion 220 in a plane perpendicular to the common axis A.
  • the third downstream face 225 therefore forms a shoulder, since the outer diameter of the tertiary portion 220 is strictly less than the outer diameter of the primary portion 210.
  • the primary portion 210 has a length, measured along the common axis A from the third downstream face 225, of between 5 mm and 20 mm. In particular, the length of the primary portion 210 is greater than or equal to 40 mm.
  • the third downstream face 225 bears against a face 235 of the turbine body 50 to prevent translation of the threaded tube 190 relative to the turbine body 50 in the downstream direction D2.
  • the face 235 is, for example, perpendicular to the common axis A.
  • the face 235 faces the upstream direction D1.
  • the face 235 is, for example, arranged in the fourth part 50D.
  • the face 235 is, along the common axis A, facing the annular groove 197.
  • the face 235 delimits the annular groove 197 along the common axis A, in particular along the downstream direction D2.
  • the secondary portion 215 is offset in the upstream direction D1 relative to the tertiary portion 220.
  • the secondary portion 215 is in the form of a cylinder with an annular base.
  • the secondary portion 215 is surrounded by the skirt 35 in a plane perpendicular to the common axis A.
  • the secondary portion 215 surrounds the bowl 30 in a plane perpendicular to the common axis A.
  • the secondary portion 215 is therefore interposed coaxially between the skirt 35 and the bowl 30.
  • the secondary portion 215 has an outer diameter of between 40 mm and 60 mm.
  • the secondary portion 215 has an internal diameter of between 30 mm and 55 mm.
  • the secondary portion 215 has a length, measured along the common axis A, of between 5 mm and 20 mm.
  • the secondary portion 215 has a third end face 237 delimiting the secondary portion 215 along the common axis A.
  • the third end face 237 is perpendicular to the common axis A.
  • the third end face 237 delimits in particular the secondary portion 215 in the downstream direction D2.
  • the third end face 237 therefore faces the downstream direction D2.
  • the secondary portion 215 has, on its outer face 205, a thread 240 configured to engage the thread 195 of the inner face 193 of the skirt 35 in order to exert on the skirt 35 a force tending to move the skirt 35, relative to the threaded tube 190, in the upstream direction D1.
  • the inner face 200 of the secondary portion 215 is configured to cooperate with a tool 250 for the transmission of a force tending to rotate the threaded tube 190 around the common axis A.
  • the inner face 200 of the secondary portion 215 does not have rotational symmetry around the common axis A.
  • the inner face 200 of the secondary portion 215 has, at at least one point, a normal direction perpendicular at this point to the inner face 200, an angle between this normal direction and a segment connecting this point to the common axis A being strictly greater than 5 degrees. The angle is measured in a plane perpendicular to the common axis A.
  • the internal face 200 of the secondary portion 215 moves away by at least 5 degrees from a cylindrical surface around the common axis A at at least one point.
  • At least one notch 245 is made in the internal face 200 of the secondary portion 215.
  • a plurality of notches 245 are made in the internal face 200 of the secondary portion 215, in particular 25 notches 245. It should be noted that the number of notches 245 is likely to vary.
  • the projection device 20 is represented on the figure 6 , in a configuration where the bowl 30 has been removed from the projection device 20.
  • the notches 245 are then visible at the bottom of the opening 152 delimited by the skirt 35.
  • Each notch 245 opens onto the third end face 237.
  • Each notch 245 extends in a direction parallel to the common axis A. In particular, each notch 245 extends from the third end face 237.
  • a tool is capable of being inserted into the notches 245 from the third end face 237 by a translation in the upstream direction D1.
  • Each notch 245 has a uniform section along the common axis A.
  • the shape and the dimensions of each notch 245 are invariant by translation in a direction parallel to the common axis A along the notch 245.
  • Each notch 245 has, for example, a circular arc section in a plane perpendicular to the common axis A.
  • Each notch 245 has a depth of between 0.5 mm and 3 mm.
  • Each notch 245 has a bottom 255.
  • the bottom 255 is all the points of the notch 245 arranged at a distance, measured between the point in question and the common axis A in a plane perpendicular to the common axis A, strictly greater than the distances from all the other points.
  • the bottom 255 is a line extending in a direction parallel to the common axis A.
  • Each point of the bottom 255 of each notch 245 is disposed at a distance d1 from the common axis A, the distance d1 being less than or equal to half the minimum diameter of the internal face of the skirt 35.
  • the tertiary portion 220 is cylindrical with an annular base.
  • the tertiary portion 220 connects the primary portion 210 to the secondary portion 215.
  • the secondary portion 220 is, in particular, interposed in a plane perpendicular to the common axis A between the second part 50B and the fourth part 50D.
  • the tool 250 is configured to engage the internal face 200 of the secondary portion 215 to rotate the threaded tube 190 around the common axis A.
  • the tool 250 is in particular configured to transmit to the threaded tube 190 a force tending to rotate the tube 190 around the common axis A with respect to the turbine body 50.
  • tool 250 is configured to engage notch(s) 245 to transmit rotational force to threaded tube 190.
  • the tool 250 comprises a head 260, visible on the figure 7 , and a handle.
  • Head 260 includes a body 265, a base 270, and a set of protrusions 275.
  • the head 260 is, for example, in one piece.
  • the head extends along its own axis AP.
  • the body 265 has an outer face 280 delimiting the body 265 in a plane perpendicular to the proper axis AP.
  • the outer face 280 is cylindrical around the proper axis AP.
  • the outer face 280 has a diameter of between 30 mm and 60 mm.
  • the base 270 is suitable for allowing the handle to be attached to the head 260.
  • the base 270 extends from the body 265 along the specific axis AP and has a recess 285 suitable for cooperating with the handle to allow attaching the handle to the head 260.
  • Each projection 275 extends radially outward from outer face 280 of body 265.
  • Each projection 275 is configured to be engaged in a notch 245 to drive the threaded tube 190 in rotation.
  • the projections 275 are configured to be engaged simultaneously in the notches 245 by a translational movement of the tool 250 along the proper axis AP, the proper axis AP being coincident with the common axis A of the projection device 20.
  • Each projection 275 has a thickness, measured in a plane perpendicular to the proper axis AP, from the outer face 280, of between 0.5 mm and 5 mm.
  • the handle is designed to be fixed to the head and to drive the head 260 in rotation around the proper axis AP.
  • the handle is suitable for allowing an operator to control a tightening torque transmitted by the tool 250 to the tube 190.
  • the handle is a torque wrench whose head is engaged in the recess 285 to drive the head 270 in rotation around the own axis AP.
  • the skirt 35 is effectively pressed against the first end face 90 by the engagement of the two threads 195 and 240.
  • the skirt 35 is therefore held in position relative to the turbine body 50 without a tool engaging on the outside of the skirt 35.
  • the projection device 20 therefore does not assume that notches are provided on the outer surface of the skirt 35.
  • the threaded tube 190 is interposed at least in part between the skirt 35 and the bowl 30 and is therefore protected against the deposition of coating products.
  • the threaded tube 190 therefore allows a more reproducible tightening of the skirt 35 against the turbine body 50, and a more precise positioning.
  • the shoulder 225 makes it possible to effectively block the threaded tube 190 in translation along the common axis A while allowing rotation around this axis.
  • a turbine body 50 in which the groove 197 for receiving the first portion 210 is delimited along the common axis A by two separate parts 50C and 50D of the turbine body 50 makes it possible to easily fix the tube 190 to the turbine body by placing the first portion 210 in the groove 197 of the third part 50C then by fixing the fourth part 50D to the third part 50C.
  • the first portion 210 prevents any particles generated by the friction of the shoulder 225 against the fourth part 50D being carried away by the gas flows G present in the area between bowl 30 and skirt 35.
  • the non-cylindrical configuration of the internal face 200 of the second portion 215 makes it possible to easily maneuver the tube 190, and in particular to put it in rotation around the common axis A with respect to the turbine body 50, from the opening 152 of the skirt 35. Fixing and separating the skirt 35 and the turbine body 50 are therefore simplified.
  • the notches 245 make it possible to effectively maneuver the threaded tube 190 in a simple manner. When they emerge on the third end face 237, it is particularly easy to insert the tool 250 by a simple translation in the upstream direction D1.
  • each notch 245 is placed at a distance less than or equal to half the minimum diameter of the internal face 193 of the skirt 35, since the tool 250 is then inserted through the opening 152 of the skirt 35 to insert the projections 275 into the notches 245.
  • This configuration allows in particular a simple geometry of the tool 250, visible on the figure 7 .
  • This tool 250 allows very effective force transmission since several projections 275 are inserted simultaneously into notches 245.

Landscapes

  • Engineering & Computer Science (AREA)
  • Robotics (AREA)
  • Nozzles (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Electrostatic Spraying Apparatus (AREA)
  • Projection Apparatus (AREA)
  • Cathode-Ray Tubes And Fluorescent Screens For Display (AREA)
  • Wind Motors (AREA)
EP19737758.3A 2018-07-13 2019-07-12 Turbine pour dispositif de projection de fluide, dispositif de projection de fluide, ainsi qu'ensemble comprenant un tel dispositif et un outil Active EP3820623B1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR1856517A FR3083722B1 (fr) 2018-07-13 2018-07-13 Turbine pour dispositif de projection de fluide, dispositif de projection de fluide, ainsi qu'ensemble comprenant un tel dispositif et un outil
PCT/EP2019/068799 WO2020011969A1 (fr) 2018-07-13 2019-07-12 Turbine pour dispositif de projection de fluide, dispositif de projection de fluide, ainsi qu'ensemble comprenant un tel dispositif et un outil

Publications (2)

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EP3820623A1 EP3820623A1 (fr) 2021-05-19
EP3820623B1 true EP3820623B1 (fr) 2022-07-06

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EP19737758.3A Active EP3820623B1 (fr) 2018-07-13 2019-07-12 Turbine pour dispositif de projection de fluide, dispositif de projection de fluide, ainsi qu'ensemble comprenant un tel dispositif et un outil

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US (1) US11819866B2 (ko)
EP (1) EP3820623B1 (ko)
JP (1) JP7374983B2 (ko)
KR (1) KR102603123B1 (ko)
CN (1) CN112368081B (ko)
ES (1) ES2923955T3 (ko)
FR (1) FR3083722B1 (ko)
WO (1) WO2020011969A1 (ko)

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* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US11110475B2 (en) * 2018-12-19 2021-09-07 Foreman Technologies Inc. Modular paint spraying system
CN112007775B (zh) * 2020-09-04 2021-05-28 郑州工业应用技术学院 一种喷涂范围可调式建筑装修装饰用喷涂机

Family Cites Families (12)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4589597A (en) * 1983-10-03 1986-05-20 Graco Inc. Rotary atomizer spray painting device
US4927081A (en) 1988-09-23 1990-05-22 Graco Inc. Rotary atomizer
US5397063A (en) * 1992-04-01 1995-03-14 Asahi Sunac Corporation Rotary atomizer coater
JPH08224505A (ja) * 1995-02-22 1996-09-03 Mazda Motor Corp ベル型塗装装置
JPH1052656A (ja) * 1996-08-12 1998-02-24 Nissan Motor Co Ltd 静電塗装装置
FR2840890B1 (fr) * 2002-06-14 2004-10-15 Valois Sa Organe de fixation et distributeur de produit fluide comprenant un tel organe de fixation
JP4964721B2 (ja) 2007-09-20 2012-07-04 本田技研工業株式会社 塗装装置
EP3031532B1 (en) * 2013-07-12 2018-08-15 Abb K.K. Rotating atomizer head coater
EP3040128B1 (en) * 2013-08-26 2018-04-25 Abb K.K. Coating machine having rotary atomizing head
WO2016163178A1 (ja) 2015-04-08 2016-10-13 Abb株式会社 回転霧化頭型塗装機
US9375734B1 (en) * 2015-06-16 2016-06-28 Efc Systems, Inc. Coating apparatus turbine having internally routed shaping air
FR3048896B1 (fr) * 2016-03-21 2018-04-13 Exel Industries Pulverisateur de produit de revetement, procede de montage et de demontage

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CN112368081B (zh) 2022-01-28
US20210252532A1 (en) 2021-08-19
WO2020011969A1 (fr) 2020-01-16
US11819866B2 (en) 2023-11-21
EP3820623A1 (fr) 2021-05-19
KR102603123B1 (ko) 2023-11-16
JP2021524557A (ja) 2021-09-13
KR20210030350A (ko) 2021-03-17
ES2923955T3 (es) 2022-10-03
CN112368081A (zh) 2021-02-12
FR3083722A1 (fr) 2020-01-17
JP7374983B2 (ja) 2023-11-07
FR3083722B1 (fr) 2020-10-09

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