Turbine, fluid-spraying device, associated facility and manufacturing method

Abstract

The invention relates to a turbine (25) for a fluid-spraying device (20) comprising a turbine body (50) and a rotor (45) rotating a bowl (30) relative to the body (50) about an axis (A), the rotor (45) being surrounded by the turbine body (50) in a plane perpendicular to the common axis (A), the turbine body (50) guiding the rotation of the rotor (45), the rotor (45) being rotated by a stream of gas, the turbine body (50) receiving the stream of gas at the outlet of the rotor (45), and delimiting at least one outlet duct configured to guide a first portion of the received stream into a space delimited in a plane perpendicular to the common axis by the bowl (30) and the skirt (35).

Description

[0001] The present invention relates to a turbine and a fluid projection device. The present invention also relates to a fluid projection installation and a method for manufacturing such an installation.

[0002] Fluid spraying systems comprising a spray device mounted on a movable arm are used in numerous applications. These spray devices frequently include a rotating bowl driven by a turbine, an injector to inject the fluid into the bottom of the bowl, and a skirt to generate air jets that shape the sprayed fluid flow.

[0003] These various components are mounted to one end of the moving arm, for example, by screwing them in. Specifically, one end of the injector fits into a cavity in the arm, opposite the inlet channels for the fluid to be sprayed. The turbine is attached to the arm around the injector, opposite the turbine's drive air inlet channels. The skirt surrounds the turbine and is itself attached to the arm, opposite the shaping air inlet channels. The bowl is attached to the end of the turbine rotor, the bowl being surrounded by the skirt.

[0004] However, the various components of the fluid spray system have complex geometries, making them difficult to position relative to one another. In particular, the relative positioning of the skirt and the bowl is challenging to control, as the bowl is mounted at one end of the injector, while the skirt and injector are positioned relative to each other by their attachment to the arm at the other end. Therefore, even small variations in the arm's positioning can cause significant variations in the relative positioning of the bowl and the skirt.

[0005] However, any misalignment of these parts relative to each other can lead to an imperfect conformation of the projected fluid flow, particularly if the rotating bowl and skirt are incorrectly positioned. Furthermore, such a fluid projection device is frequently disassembled and reassembled, whether to replace worn parts, modify the device's characteristics, or because ducts are blocked. The conformation of the projected fluid is therefore likely to vary significantly during the device's use, depending on the various disassembly and reassembly cycles.

[0006] Document FR 2 906 162 A1 discloses a rotary coating product sprayer comprising a pneumatic turbine for rotating a rotary spraying element and means for supplying a skirt airflow to the vicinity of the rotary element. The turbine exhaust gas flows, at least in part, towards the front of the sprayer. The volume of exhaust gas flowing towards the front of the sprayer is located radially within a skirt airflow volume.

[0007] Therefore, there is a need for a turbine that enables a fluid projection device in which the conformation of the projected fluid is better controlled.

[0008] For this purpose, a turbine is proposed according to claim 1.

[0009] According to advantageous but not mandatory embodiments, the turbine comprises one or more of the features of claims 2 to 5.

[0010] A fluid projection device is also proposed according to claim 6.

[0011] According to advantageous but not mandatory embodiments, the fluid projection device comprises one or more of the features of claims 7 to 11.

[0012] A complete installation is also proposed, comprising a mobile arm and a fluid projection device in which the turbine body is mounted directly on the arm.

[0013] A method for manufacturing an installation according to claim 13 is also proposed.

[0014] Some features and advantages of the invention will become apparent from the following description, given solely by way of non-limiting example, and made with reference to the accompanying drawings, in which: there figure 1 is a cross-sectional view of a fluid projection device according to the invention, this device comprising a threaded tube and a turbine body having a flange, the figure 2 is an enlarged view of frame II of the figure 1 , there figure 3 is a perspective view of a fluid projection device, the figure 4 is a perspective view of the flask of the figure 1 , there figure 5 is a cross-sectional view of the threaded tube of the figure 1 , there figure 6 is a perspective view of the threaded tube of the figure 5 , there figure 7 is a perspective view of the projection device of the figure 1 , and the figure 8 is a perspective view of a tool designed to rotate the threaded tube of the figure 5 relative to the turbine body.

[0015] A fluid projection installation 10 is partially shown on the figure 1 .

[0016] Installation 10 is configured to project a fluid F.

[0017] As seen at the figure 3 Installation 10 is connected to a support which is attached to a robot. The assembly forms a "sprayer".

[0018] The installation 10 includes a part 15 and a projection device 20 for fluid F.

[0019] Fluid F is, in particular, a coating product such as a paint or varnish. For example, fluid F is a paint or varnish intended to at least partially coat an automotive body panel.

[0020] 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.

[0021] Part 15 is, for example, an articulated arm comprising actuators capable of rotating the different segments of the arm 15 relative to each other in order to move and orient the device 20 in space.

[0022] Part 15 is further intended to supply device 20 with an electrical voltage or current, with at least one flow of gas G and with a flow of the fluid F to be projected.

[0023] Gas G is, for example, air.

[0024] Part 15, for example, has a substantially flat mounting face 22. The device 20 is mounted on the mounting face 22.

[0025] The fixing face 22 is, for example, traversed by a plurality of supply conduits for the part 15 with gas G and fluid F, and by electrical supply conductors for the device 20.

[0026] Device 20 is configured to project fluid F. Device 20 includes a turbine 25, a bowl 30, a skirt 35 and an injector 40.

[0027] The turbine 25 is configured to drive the bowl 30 in rotation around an axis A, called the "common axis". In particular, the turbine 25 is configured to receive a first gas flow G from part 15 and to drive the bowl 30 in rotation around the common axis A under the effect of the first gas flow G.

[0028] The turbine 25 comprises a rotor 45 and a body 50, also sometimes referred to as a "stator".

[0029] An upstream direction D1 and a downstream direction D2, represented on the figure 1 , are defined for the common axis A. The upstream direction D1 and the downstream direction D2 are collinear and opposite to each other.

[0030] The upstream direction D1 is such that the turbine 25 is offset relative to the skirt 35 according to the upstream direction D1.

[0031] The downstream direction D2 is such that the skirt 35 is offset along the downstream direction D2 relative to the turbine 25.

[0032] The turbine 25 is interposed between the skirt 35 and the fixing face 22 of the part 15 along the common axis A. In particular, the fixing face 22, the turbine 25 and the skirt 35 are superimposed in that order along the downstream direction D2.

[0033] The rotor 45, the skirt 35 and the injector 40 are directly mounted on the turbine body 50.

[0034] Specifically, "directly mounted" refers to a relationship in which two parts are held in position relative to each other by contact between them. For example, any relative translational movement of these two parts is prevented by this contact. Two parts that are fixed in translation but free to rotate relative to each other around a common axis can be described as "directly mounted" to one another.

[0035] In particular, at least one face of each of the parts is in contact with the other part to ensure that the two parts are fixed to each other.

[0036] A first part screwed to a second part by a screw going through both 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.

[0037] On the contrary, two parts are not directly mounted on one another if they are not in contact with each other but are each fixed to a single other part.

[0038] In particular, when the rotor 45, the skirt 35 and the injector 40 are directly mounted on the turbine body 50, the turbine body 50 is suitable for 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.

[0039] Thus, the turbine body 50, the rotor 45, the skirt 35 and the injector 40 form a set of parts that are fixed together in translation relative to each other.

[0040] In addition, the turbine body 50 has a shape adapted to allow air to be routed to the skirt 35.

[0041] The rotor 45 is directly mounted on the turbine body 50.

[0042] The rotor 45 is mobile in rotation about the common axis A relative to the turbine body 50. The rotor 45 is, in particular, configured to be driven in rotation relative to the turbine body 50 by the first gas flow G.

[0043] The rotor 45 defines a first chamber 52 for receiving the injector 40.

[0044] The rotor 45 comprises a first portion 55 and a second portion 60.

[0045] The first chamber 52 extends along the common axis A.

[0046] The first chamber 52 exhibits, for example, a rotational symmetry about the common axis A. In particular, the first chamber 52 is cylindrical about the common axis A.

[0047] A first internal diameter is defined for the first chamber 52. The first internal diameter is between 10 millimeters (mm) and 20 mm.

[0048] The first chamber 52 passes through the rotor 45 along the common axis A. In particular, the first chamber 52 passes through both the first portion 55 and the second portion 60 along the common axis A.

[0049] The first section 55 is offset along the downstream direction D2 relative to the second section 60. The first section 55 is delimited along the upstream direction D1 by the second section 60.

[0050] The first portion 55 has a first external 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 about the common axis A.

[0051] The first portion 55 has a first downstream end 65 suitable for cooperating 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. Between the first downstream end 65 and the first upstream end 70, the first downstream end 65 is offset along the downstream direction D2 relative to the first upstream end 70.

[0052] The first portion 55 has a cylindrical external face around the common axis A and is adapted to cooperate with the turbine body 50 to guide the rotor 45 in rotation around the common axis A. The external face of the first portion 55 delimits the first portion in a plane perpendicular to the common axis A.

[0053] The second section 60 has a first upstream face 75, a first lateral face 80 and a first downstream face 85.

[0054] The second portion 60 is delimited along the common axis A by the first upstream face 75 and by the first downstream face 85.

[0055] The first upstream face 75 is offset along the upstream direction D1 relative to the first downstream face 85.

[0056] The first upstream face 75 is perpendicular to the common axis A. The first upstream face 75 faces the upstream direction D1.

[0057] The first upstream face 75 is essentially flat.

[0058] The first upstream face 75 is crossed along the common axis by the first chamber 52.

[0059] The first upstream face 75 includes, in a known manner, drive members 88 configured to drive the rotor 45 in rotation when the first gas flow G is directed onto the drive members 88.

[0060] The drive components 88 include, in particular, a set of blades.

[0061] Following the example of the figure 2 , the drive elements 88 are arranged on a perimeter of the first upstream face 75.

[0062] The first lateral face 80 delimits the second portion 60 in a plane perpendicular to the common axis 80.

[0063] The first lateral face 80 is cylindrical around the common axis A.

[0064] The first lateral face 80 has a second external diameter. The second external diameter is between 50 mm and 60 mm.

[0065] The first downstream face 85 surrounds the first portion 55 in a plane perpendicular to the common axis A.

[0066] The first downstream face 85 faces the downstream direction D2.

[0067] The first downstream face 85 is essentially flat.

[0068] The turbine body 50 is directly mounted on the part 15. For example, the turbine body 50 is fixed in rotation and translation to the part 15.

[0069] In particular, the turbine body 50 is fixed to the fixing face 22 of the large part 15, for example by a plurality of screws.

[0070] Thus, the rotor 45, the injector 40 and the skirt 35 are each mounted on the part 15 via the turbine body 50.

[0071] According to the example of projection device 20 shown on the figures 1 And 2 , 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.

[0072] It should be noted that the number and arrangement of the various parts 50A to 50D composing the turbine body 50 are subject to variation. This is particularly true for the third part 50C and the fourth part 50D.

[0073] The flange 50A, the second piece 50B, the third piece 50C and the fourth piece 50D are aligned in this order along the common axis A, the flange 50A being offset along the upstream direction D1 relative to the second piece 50B, which is offset along the upstream direction D1 relative to the third piece 50C, which is itself offset along the upstream direction D1 relative to the fourth piece 50D.

[0074] The flange 50A is interposed between the second part 50B and the fixing face 22.

[0075] 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 end face 95.

[0076] The turbine body 50 is configured to receive the first gas flow G from the part 15, in particular through the mounting face 22, and to supply the rotor 45 with the first gas flow G to drive the rotor 45 into rotation. For example, the turbine body 50 is configured to guide the first gas flow G to the drive members 88.

[0077] The turbine body 50 is also configured to receive the first gas flow G at the outlet of the rotor 45 and to guide the first gas flow G out of the projection device 20.

[0078] The turbine body 50 is further configured to guide a first portion P1 of the first gas flow G received from the rotor 45 to the skirt 35. For this purpose, the turbine body 50 delimits at least one first outlet duct 97. According to the example shown in the figure 1 , the turbine body 50 delimits two such first outlet conduits 97.

[0079] The turbine body 50 is further configured to receive a second gas flow G from part 15 and to supply the skirt 35 with the second gas flow G without the second gas flow G causing the rotor 45 to rotate.

[0080] The turbine body 50 surrounds the rotor 45 in a plane perpendicular to the common axis A.

[0081] The turbine body 50 is configured to guide the rotation of the rotor 45.

[0082] The turbine body 50 delimits a second receiving chamber for the rotor 45 and a third receiving chamber 57 for the injector 40.

[0083] The turbine body 50 is further configured to guide a second portion P2 of the first gas flow G received from the rotor 45 to the second chamber. For this purpose, the turbine body 50 delimits at least one second outlet duct 100. According to the example shown in the figure 1 , the turbine body 50 delimits two such second outlet conduits 100.

[0084] The first end face 90 is formed in the fourth piece 50D.

[0085] The first end face 90 is offset along the downstream direction D2 relative to the second end face 95. The first end face 90 faces the downstream direction D2.

[0086] The second end face 95 is, in particular, formed in the flange 50A. In particular, the flange 50A is delimited by the second end face 95 along the common axis A.

[0087] The second end face 95 is in contact with the fixing face 22 of the part 15. The second end face 95 is substantially flat.

[0088] The second chamber includes a bearing which is fixed and integral with the turbine body 50.

[0089] The bearing allows the injection and maintenance of an air film with the rotor 45 to allow its rotation at high speed.

[0090] The second chamber also contains a component designed to produce sounds detectable by a microphone, with a specific air injection system. This component allows for the estimation of the turbine 25's speed.

[0091] The first cavity 105 and the second cavity 110 communicate with each other.

[0092] The first cavity 105 and the second cavity 110 are each cylindrical with a circular base around the common axis A.

[0093] The first cavity 105 is offset along the downstream direction D2 relative to the second cavity 110.

[0094] The first cavity 105 accommodates the first portion 55 of the rotor 45.

[0095] The first cavity 105 is configured to guide the rotation of the first portion 55 of the rotor 45.

[0096] The second cavity 110 accommodates the second portion 60 of the rotor 45.

[0097] 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.

[0098] The second cavity 110 is substantially cylindrical around the common axis A.

[0099] The second portion 60 of the rotor 45 is interposed between the second upstream face 115 and the second downstream face 120 along the common axis A. For example, the second portion 60 is enclosed by the second upstream face 115 and the second downstream face 120.

[0100] The second upstream face 115 is, for example, formed in the flange 50A, which is shown alone on the figure 3 .

[0101] In particular, 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 notably 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.

[0102] The second upstream face 115 is offset along the upstream direction D1 relative to the second downstream face 120.

[0103] The second upstream face 115 is opposite the first upstream face 75 of the rotor 45.

[0104] The second upstream face 115 includes, for example, guide elements 125 designed to allow rotation of the rotor 45 relative to the turbine body 50. These guide elements 125 are, for example, micro-perforated parts that create an air film. The guide elements 125 are, for example, housed in an annular channel 127 centered on the common axis and formed in the second upstream face 115.

[0105] The second upstream face 115 is perpendicular to the common axis A.

[0106] The second upstream face 115 has an annular groove 130 and at least one radial groove 135. For example, the second upstream face 115 has two radial grooves 135, one for each first outlet conduit 97.

[0107] The annular groove 130 and the radial groove(s) 135 are provided in the flange 50A.

[0108] The annular groove 130 is configured to collect the first gas flow G at the outlet of the rotor 45. In particular, the annular groove 130 is opposite the drive members 88.

[0109] The annular groove 130 is configured to transmit the first part P1 of each first gas flow G to each first outlet conduit 97. In particular, the annular groove 130 is configured to transmit the first part P1 to each first outlet conduit 97 via the corresponding radial groove 135.

[0110] The annular groove 130 is, moreover, configured to transmit each second part P2 of the first gas flow G received from the rotor 45 to the corresponding second outlet conduit 100.

[0111] The annular groove 130 is centered on the common axis A. In particular, the annular groove 130 is delimited by two cylindrical faces around the common axis A of the turbine body 50.

[0112] The 130 annular groove has an external diameter between 40 mm and 45 mm. The 130 annular groove has an internal diameter between 45 mm and 50 mm.

[0113] The annular groove 130 has a depth, measured along the common axis A, of between 1 mm and 10 mm.

[0114] Each radial groove 135 extends along a straight eigenline L1 contained in a plane perpendicular to the common axis A and concurrent with the common axis A. The eigenlines L1 of the radial grooves 135 are, for example, coincident with each other. In other words, the radial grooves 135 are diametrically opposed.

[0115] 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.

[0116] Each radial groove 135 opens into the annular groove 130.

[0117] 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.

[0118] Each radial groove 135 has a width, measured in a plane perpendicular to the common axis A and along a direction perpendicular to the proper line L1, of between 10 mm and 18 mm.

[0119] 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.

[0120] The second downstream face 120 is perpendicular to the common axis A. The second downstream face 120 is opposite the second upstream face 115.

[0121] The second downstream face 120 is essentially flat.

[0122] The second downstream face 120 is designed to prevent a movement of the rotor 45 along the downstream direction D2 relative to the turbine body 50.

[0123] The second downstream face 120 is supported against the first downstream face 85, for example by means of guiding elements 125.

[0124] Each first outlet duct 97 is, for example, jointly delimited by the second part 50B, the third part 50C and the fourth part 50D. In particular, each first outlet duct 97 comprises a plurality of portions opening into one another, these portions each being delimited by one of the second part 50B, the third part 50C and the fourth part 50D.

[0125] Each first outlet conduit 97 is configured to conduct a first part P1 of the first gas flow G from the annular groove 130 to the skirt 35.

[0126] In particular, each first outlet conduit 97 opens onto the first end face 90, which is opposite the skirt 35. According to the embodiment shown in the figures 1 And 2 , each first outlet conduit 97 is configured to conduct the corresponding first part P1 into the free space separating the bowl 30 from the skirt 35.

[0127] Each first outlet conduit 97 opens into the corresponding radial groove 135.

[0128] Each first outlet duct 97 is entirely enclosed by the turbine housing 50. In other words, each first outlet duct 97 is formed within the turbine housing 50 and only within it. The first portion P1 flowing in the first outlet duct 97 is therefore only in contact with the turbine housing 50 while the first portion P1 flows in the first outlet duct 97.

[0129] Each first outlet conduit 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.

[0130] Each second outlet conduit 100 is, for example, provided in the flange 50A.

[0131] Each second outlet conduit 100 is configured to transmit a second part P2 of the first gas flow G from the annular throat 130 to the third chamber 57.

[0132] Each second outlet conduit 100 is entirely enclosed by the turbine housing 50. In other words, each second outlet conduit 100 is contained within the turbine housing 50 and only within it. The second portion P2 flowing in the second outlet conduit 100 is therefore only in contact with the turbine housing 50 while the second portion P2 flows in the second outlet conduit 100.

[0133] Each second outlet conduit 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.

[0134] The third chamber 57 is provided in the flange 50A.

[0135] The third chamber 57 is configured to partially accommodate injector 40.

[0136] The third chamber 57 is offset along the upstream direction D1 relative to the second chamber.

[0137] 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.

[0138] The third chamber 57 has a third cavity 140 and a fourth cavity 145.

[0139] Each of the third cavity 140 and the fourth cavity 145 is cylindrical around the common axis A.

[0140] The third cavity 140 is interposed between the fourth cavity 145 and the second cavity 110.

[0141] The third cavity 140 has a diameter between 12 mm and 15 mm. The third cavity 140 has a length, measured along the common axis A, between 10 mm and 30 mm. Each second outlet conduit 100 opens into the third cavity 140.

[0142] The first bearing face 150 is annular and centered on the common axis A. The first bearing face 150 is substantially flat. The first bearing face 150 is perpendicular to the common axis A.

[0143] The first support face 150 delimits the fourth cavity 145 according to the downstream direction D2.

[0144] The first support face 150 is designed to bear against the injector 40 to prevent movement of the injector 40 in the downstream direction D2 relative to the turbine body 50.

[0145] The bowl 30 is directly mounted on the rotor 45. In particular, 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.

[0146] The bowl 30 is configured to be driven in rotation around the common axis A by the rotor 45 to generate the fluid flow F to be projected.

[0147] Bowl 30 is configured to receive the fluid F to be projected from the injector 40 at the bottom 151 of bowl 30.

[0148] Bowl 30 protrudes from skirt 35 in the downstream direction D2.

[0149] The skirt 35 is configured to generate a set of jets of gas G, these jets being adapted to conform to the projected fluid F. For example, the skirt 35 is configured to receive the first and second flows of gas G and to generate the jets of gas G from the first and second received flows.

[0150] 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 downstream direction D2.

[0151] The skirt 35 is supported 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.

[0152] The skirt 35 is fixed to the turbine body 50 in such a way as to eliminate all degrees of freedom between the turbine body and the skirt 50.

[0153] Injector 40 is configured to inject the fluid flow F to be projected into the bottom 151 of bowl 30.

[0154] The injector 40 is mounted directly on the turbine body 50. In particular, the injector 40 is received at least partially in the third chamber 57.

[0155] 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 prevented.

[0156] Optionally, the injector 40 is further fixed to the turbine body 50 by means of fixing 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.

[0157] The injector 40 is received in the first chamber 52 provided in the rotor 45.

[0158] The injector 40 is configured to allow relative rotational movement around the common axis A between the rotor 45 and the injector 40. In particular, the injector 40 is not in contact with the walls of the rotor 45 which delimit the first chamber 52.

[0159] The rotor 45 and the injector 40 define a free volume, which corresponds to the portion of the first chamber 52 that is complementary to the injector 40.

[0160] Injector 40 comprises an injection unit 155 and an injector body 160.

[0161] The injector 40 is configured so that the free volume is in communication with the bottom 151 of the bowl 30. For example, 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.

[0162] Furthermore, the injector 40 is configured so that each second outlet conduit 100 is in communication with the free space. Thus, the second outlet conduit 100 and the free space form an auxiliary conduit suitable for transmitting the second part P2 of the first gas flow G from the annular groove 130 to the bottom 151 of the bowl 30.

[0163] The injection member 155 is configured to inject the fluid flow F to be projected into the bottom 151 of the bowl 30.

[0164] The injection unit 155 is offset along the second direction D2 relative to the injector body 160.

[0165] The injector body 160 is configured to receive the flow of fluid to be projected F from the part 15, and to transmit the flow of fluid to be projected F to the injection member 155.

[0166] The injector body 160 comprises a third portion 165, a fourth portion 170, a fifth portion 172 and a collar 175.

[0167] The third section 165, the fourth section 170, the fifth section 172 and the collar 175 are offset in that order from each other according to the upstream direction D1.

[0168] The injection unit 155 is mounted on the third portion 165.

[0169] 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.

[0170] The diameter of the third portion 165 is between 5 mm and 15 mm.

[0171] The fourth portion 170 is delimited along the common axis A by the collar 175 and by the fifth portion 172.

[0172] The fourth portion 170 is accommodated in the third cavity 140.

[0173] The fourth portion 170 is cylindrical around the common axis A.

[0174] The diameter of the fourth portion 170 is strictly greater than the diameter of the third portion 165.

[0175] 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 opposite the fifth portion 172.

[0176] The fifth portion 172 is interposed along the common axis A between the third portion 135 and the fourth portion 170.

[0177] The fifth portion 172 is delimited along the common axis A by the third portion 135 and the fourth portion 170.

[0178] 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.

[0179] In particular, with regard to the end of each second outlet conduit 100 which opens into the third cavity 140, the diameter of the fifth portion 172 is strictly less than the diameter of this third cavity.

[0180] In this way, the second part P2 of the first gas flow G is likely to be delivered by the second outlet conduit 100 into the free volume.

[0181] The collar 175 is cylindrical around the common axis A.

[0182] The collar 175 has a thickness, measured along the common axis, substantially equal to the length of the fourth cavity 145.

[0183] The diameter of the flange 175 is approximately equal to the diameter of the fourth cavity 180. The flange 175 has a second bearing face 180 and a third bearing face 185. The flange 175 is delimited along the common axis A by the second and third bearing faces 180 and 185. The thickness of the flange 175 is measured between the second and third bearing faces 180 and 185.

[0184] The second support face 180 is perpendicular to the common axis A.

[0185] The second support face 180 is in contact with the first support face 150. Thus, a translation of the injector 40 along the downstream direction D2 relative to the turbine body 50 is prevented.

[0186] The third bearing face 180 is, for example, in contact with the fixing face 22 of the part 15 when the projection device 20 is fixed to the part 15, so that the collar 75 is clamped between the fixing face 22 and the first bearing face 150 provided in the turbine body 50. In particular, the third bearing face 180 and the second end face 95 are coplanar.

[0187] It should be noted that in some envisaged embodiments, 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 in contact with the fixing face 22.

[0188] A manufacturing process for installation 10 will now be described.

[0189] In a first step, the rotor 45, the skirt 35 and the injector 40 are mounted directly on the turbine body 50.

[0190] For example, the second, third, and fourth parts 50B, 50C, and 50D are fixed to each other. The rotor 45 is then inserted into the second chamber by a translation along the downstream direction D2, and 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 thus fixed to the turbine body 50 by a mechanical linkage allowing only one degree of freedom, which is rotation about the common axis A.

[0191] The injector 40 is inserted into the second and third chambers 52, 57 by a translational movement along the downstream direction D2 until the second support face 180 is pressed against the first support face 150. The injector 40 is then fixed to the turbine body by a mechanical link allowing only a relative translation along the upstream direction D1 between these two parts, and optionally a relative rotation around the common axis A.

[0192] Optionally, the injector 40 is further fixed to the turbine body 50 by fastening devices so as to eliminate all remaining degrees of freedom between these two parts.

[0193] The skirt 35 is then positioned against the turbine body 50 in such a way that the skirt 35 is in contact with the first end face 90. The skirt 35 is fixed to the turbine body 50 in such a way as to eliminate all degrees of freedom between the skirt 35 and the turbine body 50.

[0194] Thus, at the end of the first stage, an assembly is obtained comprising the turbine body 50, the rotor 45, the skirt 35 and the injector 40. The different elements of this assembly are fixed together in translation.

[0195] In a second step, the bowl 30 is mounted on the rotor 45 to form the projection device 20.

[0196] The third step is implemented after the first step.

[0197] In a third step, the assembly comprising the turbine body 50, the rotor 45, the skirt 35 and the injector 40 is mounted on the part 15.

[0198] In particular, 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 turbine body 50. Thus, the turbine body 50 and the part 15 form a mechanical connection eliminating all degrees of freedom between the turbine body 50 and the part 15.

[0199] According to one embodiment, the third step is implemented after the second step. For example, the projection device 20, further comprising the bowl 30, is attached to the part 15.

[0200] Since the rotor 45, skirt 35, and injector 40 are all directly mounted on the turbine housing 50, the relative positioning of these parts is improved. Similarly, the positioning accuracy of the skirt 35 and injector 40 relative to the bowl 30 is improved, particularly compared to known designs where the skirt 35 and injector 40 are attached to part 15 and not to the turbine housing 50. Indeed, the number of parts involved in positioning the bowl 30 relative to the skirt 35 and injector 40 is reduced, since only the turbine housing 50 and the rotor 45 connect the bowl 30 to the skirt 35 and injector 40.

[0201] Improving the positioning of the bowl 30 relative to the skirt 35 and the injector 40 allows better control of the conformation of the projected fluid F, since the gas jets G to conform the fluid jet F are better positioned relative to the bowl 30.

[0202] Furthermore, 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 way on the part 15, by only fixing the turbine body 50 to the part 15.

[0203] The presence of the first conduit 97 allows the first part P1 of the first flow G to be injected 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 the injection of skirt airs.

[0204] This allows the air to be diverted directly into the turbine. This results in improved delayed differentiation across all the different sprayer bodies. Furthermore, eliminating grooves in the plastic body increases its strength and allows for greater positioning and angle of drilling, thus freeing up space in smaller bodies. This also prevents very cold exhaust air from entering an area where metal inserts for high voltage and plastic are mixed, with all the stresses associated with the different expansions of the materials.

[0205] More specifically, the cold airflow circulating internally within the turbine, which can reach temperatures as low as -40°C, does not come into contact with any interface between plastic and metal components. This is because the two materials have different coefficients of thermal expansion, and exposure to such cold air could lead to sealing problems.

[0206] Also, notwithstanding the fact that using a metal turbine as a reference allows for increased accuracy, the chosen turbine conformation also improves the durability of the seal in the sprayer.

[0207] The auxiliary passage allows the second part P2 to be injected 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.

[0208] Furthermore, part 15 and in particular the fixing face 22 are simplified when the conduits 97 and 100 are provided in the turbine body 50, since it is the turbine body 50 which receives the first gas flow G at the outlet of the rotor 45. It is therefore not necessary to shape the fixing face 22 to receive and discharge the first gas flow G at the outlet of the rotor.

[0209] Furthermore, 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 gas flow G, exiting the rotor 45, between the first part P1 and the second part P2.

[0210] According to some embodiments, 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 conduit 97 and the size of the auxiliary passage.

[0211] The annular groove 130 allows for the collection of the first gas flow G at the outlet of the rotor 45 with a very small axial footprint. The dimensions of the projection device 20 are therefore reduced.

[0212] The radial grooves 135 allow for the recovery of increasing amounts of exhaust air without recompressing it, thus avoiding slowing down the turbine 25. When the radial grooves 135 are diametrically opposed to each other, the initial portions P1 of the gas flows G collected by the ducts 97 are equal. The gas flow G injected between the skirt 35 and the bowl 30 is then more spatially homogeneous.

[0213] The support of the first and second support faces 150 and 180 allows precise and simple positioning of the injector 40 relative to the turbine body 50.

[0214] To simplify the description of the first example above, it has not been detailed how the skirt 35 is fixed to the turbine body 50 after the skirt 35 is pressed against the first end face 90.

[0215] Numerous fastening methods can be used to eliminate all degrees of freedom between the skirt 35 and the turbine body 50, for example, screws passing through both the skirt 35 and the turbine body 50. It should be noted that other methods can be used to mount the skirt 35 directly onto the turbine body 50. For example, the skirt 35 and the turbine body 50 may have complementary threads to allow the skirt 35 to be screwed onto the turbine body 50.

[0216] According to the particular embodiment shown on the figures 1 And 2 The fluid projection device 20 also includes a threaded tube 190, visible in particular on the figure 2 and represented in isolation on the figures 4 And 5 .

[0217] The skirt 35 has an inner face 193. The inner face 193 of the skirt 35 is the face of the skirt 35 which surrounds the bowl 30 and which is opposite the bowl 30. In particular, the inner face 193 delimits the opening 152 in which the bowl 30 is received.

[0218] The internal face 193 exhibits a rotational symmetry around the common axis A.

[0219] A minimum diameter is defined for the inner 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 inner face 193 that are closest to each other.

[0220] The inner face 193 has a thread 195. The thread 195 surrounds the bowl 30 in a plane perpendicular to the common axis A.

[0221] The 190 threaded tube is sometimes also called a "nut" or even a "free-floating nut".

[0222] The threaded tube 190 is mounted coaxially to the skirt 35 and the turbine body 50. In particular, the threaded tube 190 is centered on the common axis A.

[0223] The threaded tube 190 is mounted directly on the turbine body 50. In particular, the threaded tube 190 is fixed to the turbine body 50 in translation.

[0224] According to one embodiment, the turbine body 50 defines an annular groove 197 receiving at least a portion of the threaded tube 190 and has faces suitable for preventing a relative translation of the threaded tube 190 and the turbine body 50.

[0225] The annular groove 197 is, for example, made in the third piece 50C and extends along the common axis A from a downstream surface of the third piece 50C, this downstream surface delimiting the third piece along the downstream direction D2.

[0226] The threaded tube 190 is mobile in rotation around the common axis A relative to the turbine body 50.

[0227] The 190 threaded tube, for example, is made of steel.

[0228] The threaded tube 190 has rotational symmetry around the common axis A.

[0229] The threaded tube 190 has an inner face 200 and an outer face 205. The threaded tube 190 is delimited by the inner face 200 and by the outer face 205 in a plane perpendicular to the common axis A.

[0230] The threaded tube 190 comprises at least a primary portion 210 and a secondary portion 215. According to the example of the figure 4 , the threaded tube 190 also includes a tertiary portion 220 interposed between the primary portion 215 and the secondary portion 215 along the common axis A.

[0231] The primary portion 210 is offset along the upstream direction D1 relative to the tertiary portion 220.

[0232] The primary portion 210 is cylindrical with an annular base. In other words, the primary portion 210 is bounded by two cylindrical surfaces, each centered on the common axis A. Specifically, the primary portion 210 is bounded by these two surfaces in a plane perpendicular to the common axis A.

[0233] The primary portion 210 has a third downstream face 225 and a third upstream face 230.

[0234] 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 notably accommodated in the opening 152.

[0235] The primary portion 210 is accommodated in the annular groove 197. In particular, 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 relative to the turbine body 50 in a plane perpendicular to the common axis A.

[0236] The primary portion 210 has an external diameter between 45 mm and 60 mm.

[0237] The primary portion 210 has an internal diameter between 40 mm and 55 mm.

[0238] The primary portion 210 is delimited along 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.

[0239] 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 external diameter of the tertiary portion 220 is strictly less than the external diameter of the primary portion 210.

[0240] 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.

[0241] The third downstream face 225 is supported against a face 235 of the turbine body 50 to prevent a translation of the threaded tube 190 relative to the turbine body 50 in the downstream direction D2.

[0242] Face 235 is, for example, perpendicular to the common axis A. Face 235 faces the upstream direction D1. Face 235 is, for example, formed in the fourth part 50D. Face 235 is, along the common axis A, opposite the annular groove 197. Thus, face 235 delimits the annular groove 197 along the common axis A, specifically along the downstream direction D2.

[0243] Secondary section 215 is offset along the upstream direction D1 relative to tertiary section 220.

[0244] The secondary portion 215 is cylindrical with an annular base.

[0245] The secondary portion 215 is surrounded by the skirt 35 in a plane perpendicular to the common axis A. For example, 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.

[0246] The secondary portion 215 has an external diameter between 40 mm and 60 mm.

[0247] The secondary portion 215 has an internal diameter between 30 mm and 55 mm.

[0248] The secondary portion 215 has a length, measured along the common axis A, of between 5 mm and 20 mm.

[0249] The secondary portion 215 has a third end face 237 that delimits 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 the secondary portion 215 along the downstream direction D2. The third end face 237 therefore faces the downstream direction D2.

[0250] The secondary portion 215 has, on its external face 205, a thread 240 configured to engage the thread 195 of the internal 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.

[0251] Thus, since the third downstream face 225 is in contact with the face 235 of the turbine body 50 to prevent a translation of the threaded tube towards the downstream direction D1 relative to the turbine body 50, a force tending to bring the skirt 35 closer to the turbine body 50 along the common axis and therefore to press the skirt 35 against the turbine body 50 is exerted by the tube 190 when the two threads 195 and 240 are engaged with each other.

[0252] 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. In particular, the inner face 200 of the secondary portion 215 does not have a symmetry of revolution around the common axis A.

[0253] The inner face 200 of the secondary portion 215 has, at at least one point, a normal direction perpendicular at that point to the inner face 200, the 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.

[0254] In other words, the inner face 200 of the secondary portion 215 deviates by at least 5 degrees from a cylindrical surface around the common axis A at at least one point.

[0255] For example, at least one notch 245 is formed in the inner face 200 of the secondary portion 215. According to the example shown on the figures 4 à 6 , a plurality of notches 245 is provided in the inner 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.

[0256] The projection device 20 is shown on the figure 6 , in a configuration where the bowl 30 has been removed from the projection device 20. The notches 245 are then apparent at the bottom of the opening 152 delimited by the skirt 35.

[0257] Each notch 245 opens onto the third end face 237.

[0258] 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.

[0259] Thus, a tool is likely to be inserted into the notches 245 from the third end face 237 by a translation along the upstream direction D1.

[0260] Each notch 245 has a uniform section along the common axis A. In particular, the shape and dimensions of each notch 245 are invariant under translation along a direction parallel to the common axis A along the notch 245.

[0261] Each notch 245 presents, for example, a circular arc section in a plane perpendicular to the common axis A.

[0262] Each 245 notch has a depth between 0.5 mm and 3 mm.

[0263] Each notch 245 has a background 255. The background 255 is the set of points of the notch 245 arranged at a distance, measured between the point considered and the common axis A in a plane perpendicular to the common axis A, strictly greater than the distances of all other points.

[0264] When the notch 245 has a circular arc section, the bottom 255 is a line extending in a direction parallel to the common axis A.

[0265] 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 inner face of the skirt 35.

[0266] The tertiary portion 220 is cylindrical with an annular base. The tertiary portion 220 connects the primary portion 210 to the secondary portion 215.

[0267] The secondary portion 220 is, in particular, interposed in a plane perpendicular to the common axis A between the second piece 50B and the fourth piece 50D.

[0268] The tool 250 is configured to engage the inner face 200 of the secondary portion 215 to rotate the threaded tube 190 around the common axis A. The tool 250 is specifically configured to transmit to the threaded tube 190 a force tending to rotate the tube 190 around the common axis A relative to the turbine body 50.

[0269] In particular, tool 250 is configured to engage notch(s) 245 to transmit rotational force to threaded tube 190.

[0270] Tool 250 includes a 260 head, visible on the figure 7 and a handful.

[0271] The head 260 comprises a body 265, a base 270 and a set of projections 275.

[0272] The 260 head, for example, is a single piece.

[0273] The head extends along its own axis AP.

[0274] The body 265 has an external face 280 delimiting the body 265 in a plane perpendicular to the proper axis AP.

[0275] The external face 280 is cylindrical around the proper axis AP. The external face 280 has a diameter between 30 mm and 60 mm.

[0276] The base 270 is designed to allow the handle to be attached to the head 260. For example, the base 270 extends from the body 265 along the axis AP and has a recess 285 designed to cooperate with the handle to allow the handle to be attached to the head 260.

[0277] Each projection 275 extends radially outwards from the outer face 280 of the body 265.

[0278] Each projection 275 is configured to engage in a notch 245 to rotate the threaded tube 190. In particular, the projections 275 are configured to engage simultaneously in the notches 245 by a translational movement of the tool 250 about its own axis AP, the own axis AP coinciding with the common axis A of the projection device 20.

[0279] Each projection 275 has a thickness, measured in a plane perpendicular to the proper axis AP, from the external face 280, of between 0.5 mm and 5 mm.

[0280] The handle is designed to be attached to the head and to drive the 260 head in rotation around its own axis AP.

[0281] According to one embodiment, the handle is adapted to allow an operator to control a tightening torque transmitted by the tool 250 to the tube 190. For example, the handle is a torque wrench whose head is engaged in the socket 285 to drive the head 270 in rotation around the proper axis AP.

[0282] It should be noted that other types of tools may be considered to drive the threaded tube 190 into rotation relative to the turbine body 50, particularly if the shape of the threaded tube 190 and in particular the shape and / or number of the notches 245 are modified.

[0283] Thanks to the use of the threaded tube 190, 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 any tool engaging the outside of the skirt 35. The projection device 20 therefore does not require notches to be made on the external surface of the skirt 35.

[0284] On the contrary, the threaded tube 190 is interposed at least partially between the skirt 35 and the bowl 30 and is therefore protected against the deposition of coating products.

[0285] The threaded tube 190 therefore allows for more reproducible clamping of the skirt 35 against the turbine body 50, and more precise positioning.

[0286] The shoulder 225 effectively locks 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 parts 50C and 50D separate from the turbine body 50, allows the tube 190 to be easily fixed to the turbine body by placing the first portion 210 in the groove 197 of the third part 50C and then fixing the fourth part 50D to the third part 50C.

[0287] When the length of the first portion 210 is greater than or equal to 40 mm, the first portion 210 prevents any particles generated by the friction of the shoulder 225 against the fourth piece 50D from being carried away by the gas flows G present in the area between the bowl 30 and the skirt 35.

[0288] The non-cylindrical configuration of the inner face 200 of the second portion 215 allows the tube 190 to be easily maneuvered, and in particular to be rotated around the common axis A relative to the turbine body 50, from the opening 152 of the skirt 35. The fixing and separation of the skirt 35 and the turbine body 50 are therefore simplified.

[0289] The notches 245 allow for efficient and simple manipulation of the threaded tube 190. When they open onto the third end face 237, it is particularly easy to insert the tool 250 by a simple translation along the upstream direction D1.

[0290] This is particularly true when, in addition, the bottom of each notch 245 is positioned at a distance less than or equal to half the minimum diameter of the inner 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 notably allows for a simple geometry of the tool 250, visible on the figure 7 This tool 250 allows for very efficient force transmission since several projections 275 are inserted simultaneously into notches 245.

[0291] It should be noted that the mounting of the skirt 35 on the turbine body 50 via the threaded tube 190 is likely to be implemented in embodiments where the injector 40 is not directly mounted on the turbine body 50.

Claims

1. A turbine (25) for a fluid-spraying device (20) comprising a bowl (30), an injector (40) configured to inject the fluid in the bottom (151) of the bowl (30), and a skirt (35) at least partially surrounding the bowl (30) in a plane perpendicular to a common axis (A) and configured to eject jets of gas in order to mold the sprayed fluid, the turbine (25) comprising a turbine body (50) and a rotor (45) configured to rotate the bowl (30) relative to the body (50) about the common axis of rotation (A), the rotor (45) being surrounded by the turbine body (50) in a plane perpendicular to the common axis (A), the turbine body (50) being configured to guide the rotation of the rotor (45), the rotor (45) being configured to be rotated by a stream of gas, the turbine body (50) being configured to receive the stream of gas at the outlet of the rotor (45), and delimiting at least one outlet duct (97) configured to guide a first portion (P1) of the received stream into a space delimited in a plane perpendicular to the common axis by the bowl (30) and the skirt (35), the turbine body (50) including a first end face (90) delimiting the turbine body (50) along the common axis (A), the turbine body (50) being configured so that the skirt (35) bears against the first end face (90), each outlet duct (97) extending between two ends, the turbine body (50) delimiting each of the outlet ducts (97) from one of their ends to the other end, each outlet duct (97) opening onto the first end face (90).

2. The turbine according to claim 1, wherein the turbine body (50) includes the first end face (90) and a second end face (95), the two end faces (90, 95) delimiting the body of the turbine (50) along the common axis (A), the ratio between the gas stream flow rate passing through the second end face (95) and the gas stream flow rate of the first portion of the stream (P1) being less than 1 / 100.

3. The turbine (25) according to claim 1 or 2, wherein the turbine (25) at least partially delimits an auxiliary passage able to conduct a second portion (P2) of the stream of gas from the rotor (45) to the bottom (151) of the bowl (30).

4. The turbine (25) according to claim 3, wherein the turbine body (50) is arranged so that during operation, the ratio between the flow rate of the first portion (P1) of the stream of gas and the second portion (P2) of the stream of gas is greater than or equal to 2, preferably greater than or equal to 3 and preferably greater than or equal to 10.

5. The turbine (25) according to any one of claims 1 to 4, wherein the turbine body (50) includes a or the second end face (95) delimiting the turbine body (50) along the common axis (A), an opening (57) arranged in the second end face (95) being configured to receive the injector (40), the opening (57) having a first bearing face (150) perpendicular to the common axis (A), the first bearing face (150) being configured to be bearing against a second bearing face (180) of the injector (40).

6. Fluid-spraying device (20), comprising: • a bowl (30), • a turbine (25) according to any one of claims 1 to 5, the rotor (45) being surrounded by the turbine body (50) in a plane perpendicular to the common axis (A), • an injector (40) configured to inject the fluid in the bottom (151) of the bowl (30), and • a skirt (35) at least partially surrounding the bowl (30) in a plane perpendicular to the common axis (A) and configured to eject jets of gas in order to mold the sprayed fluid.

7. The fluid-spraying device according to claim 6, wherein an upstream direction (D1) and a downstream direction (D2) are defined for the common axis (A), the skirt (35) being offset toward the downstream direction (D2) relative to the turbine body (50), the rotor (45) having a first upstream face (75) delimiting the rotor (45) along the common axis (A), the turbine body (50) delimiting a receiving chamber of the rotor (45), the chamber including a second upstream face (115) delimiting the chamber along the common axis (A), the second upstream face (115) facing the first upstream face (75) and being offset along the upstream direction (D2) relative to the first upstream face (75), an annular groove (130) centered on the common axis (A) being arranged in the second upstream face (115), the annular groove (130) being configured to receive the stream of gas and to transmit the first portion (P1) of the stream of gas to each outlet duct (97).

8. The device according to claim 7, wherein the second upstream face (115) includes, for each outlet duct (97), a radial groove (135) extending radially outward from the annular groove (130) and configured to guide the first portion (P1) of the stream of gas from the annular groove (130) to the outlet duct (97).

9. The fluid-spraying device according to claim 8, including two outlet ducts (97), the radial grooves (135) each extending from the annular groove (130) along a rectilinear specific line (L1), the two specific lines (L1) being combined.

10. The fluid-spraying device according to any one of claims 6 to 9, at least partially delimiting an auxiliary passage able to conduct a second portion (P2) of the stream of gas from the rotor (45) to the bottom (151) of the bowl (30), at least one section (100) of the auxiliary passage being arranged in the turbine body (50).

11. The fluid-spraying device according to claim 10, wherein the injector (40) is surrounded by the rotor (45) in a plane perpendicular to the common axis (A), a free volume separating the rotor (45) and the injector (40) in a plane perpendicular to the common axis (A), the auxiliary passage comprising a duct (100) configured to guide the second portion (P2) of the stream of gas to the free volume, the free volume being able to guide the second portion (P2) of the stream of gas to the bottom (151) of the bowl (30).

12. A facility (10), including a moving arm (15) and a fluid-spraying device (20) according to any one of claims 6 to 11, wherein the turbine body (50) is mounted directly on the arm (15).

13. A method for manufacturing a facility (10) comprising a moving arm (15) and a fluid-spraying device (20) including: • a bowl (30), • a turbine (25) comprising a turbine body (50) and a rotor (45) configured to rotate the bowl (30) relative to the body (50) about a common axis of rotation (A), the rotor (45) being surrounded by the turbine body (50) in a plane perpendicular to the common axis (A), the turbine body (50) being configured to guide the rotation of the rotor (45), the turbine (25) being according to any one of claims 1 to 5, • an injector (40) configured to inject the fluid in the bottom (151) of the bowl (30), and • a skirt (35) at least partially surrounding the bowl (30) in a plane perpendicular to the common axis (A) and configured to eject jets of gas adapted to mold the sprayed fluid, the method including the following steps: a) assembling the rotor (45), the injector (40) and the skirt (35) directly on the turbine body (50), b) assembling the bowl (30) directly on the rotor (45), and c) assembling the turbine body (50) directly on the arm (15), step c) is implemented after step a).

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