Turbine drive for a rotary atomizer and related method of operation

Abstract

A turbine drive for a rotary atomizer, with a rotatable turbine wheel with a plurality of turbine blades, a first drive nozzle (3) for outputting a drive gas, in particular compressed air, onto the turbine blades of the turbine wheel in order to drive the turbine wheel, a first drive gas supply (5) for supplying the drive gas to the first drive nozzle (3), and with a second drive nozzle (4) for outputting the drive gas onto the turbine blades of the turbine wheel in order to drive the turbine wheel. The invention additionally provides a second drive gas supply (6) for supplying the drive gas to the second drive nozzle (4), wherein the second drive gas supply (6) is separate from the first drive gas supply (5), with the result that the second drive nozzle (4) can be supplied with the drive gas independently of the first drive nozzle (3). The invention also relates to a corresponding operating method.

Description

Field of invention

[0001] The invention relates to a turbine drive for a rotary atomizer and a corresponding operating method. Background of the invention

[0002] In modern paint shops for painting automotive body components, rotary atomizers driven by compressed air turbines are commonly used as application devices. Such a turbine is known, for example, from EP 1 388 372 A1. This known turbine has a rotatably mounted turbine wheel with numerous turbine blades distributed around its circumference. Compressed air, exiting from several drive nozzles distributed around the circumference of the turbine wheel, drives the rotary atomizer. The turbine wheel can also be braked. For this purpose, braking air is discharged in the opposite direction from a braking nozzle onto the turbine blades. This known turbine already operates satisfactorily; however, there is still interest in increasing its efficiency.

[0003] Regarding the state of the art, reference should also be made to WO 2016 / 062365 A1, EP 1 384 516 A2 and DE 44 25 229 A1, WO 2006 / 024861 A1, WO 2016 / 116275 A1, WO 2016 / 062365 A1, and DE 101 15 469 A1.

[0004] Finally, US 2005 / 258270 A1 discloses a turbine drive according to the preamble of claim 1. However, this known turbine drive is also not yet fully satisfactory. Description of the invention

[0005] The invention is therefore based on the objective of creating a correspondingly improved turbine drive for a rotary atomizer. Furthermore, the invention also aims to provide a suitable operating method for such a turbine drive.

[0006] This problem is solved by a turbine drive according to the invention or by a corresponding operating method according to the independent claims.

[0007] The invention is based on the technical-physical insight that the turbine in a rotary atomizer is often not operated at an optimal load point during operation, the load point being determined by the rotational speed and the torque.

[0008] For example, when painting the interior surfaces of motor vehicle body components, only a relatively small flow of paint is emitted, so that a correspondingly low mechanical drive power of the turbine is required.

[0009] In contrast, when painting the exterior of motor vehicle body components, relatively large areas are painted, which is why a correspondingly large flow of paint is applied, which in turn requires a relatively large mechanical drive power for the turbine of the rotary atomizer.

[0010] The invention is based on the fact that turbine nozzles can only be optimized for a specific load point with regard to shape and nozzle cross-section. Therefore, the various load points occurring during the operation of a rotary atomizer mean that the turbine is not always operated at its optimal load point. However, operating the turbine at a suboptimal load point leads to a reduction in turbine efficiency. Thus, optimizing the turbine for exterior painting results in relatively poor efficiency for interior painting. Conversely, optimizing the turbine for interior painting results in relatively poor efficiency for exterior painting.

[0011] The invention therefore provides that the turbine has several drive nozzles, each supplied with its respective drive gas (e.g., compressed air) from separate drive gas feeds, allowing the different drive nozzles to be activated or deactivated independently. Depending on the load point, one or the other drive nozzles can then be activated. This enables the turbine to operate in an optimal state even under changing load points, thereby increasing the turbine's efficiency under varying load conditions.

[0012] For example, certain nozzles may be optimized for exterior painting, while others are optimized for interior painting. For exterior painting, the nozzles optimized for exterior applications are selected. Conversely, for interior painting, the nozzles optimized for interior applications are specifically chosen.

[0013] The turbine drive according to the invention is designed for a rotary atomizer, as is known per se from the prior art and is described, for example, in EP 1388 372 A1.

[0014] The turbine drive according to the invention, in accordance with the known turbine drive, features a rotatable turbine wheel with several turbine blades. In a preferred embodiment of the invention, the turbine is designed as a radial turbine; however, a design as an axial turbine is also possible in principle.

[0015] Furthermore, the turbine according to the invention, in accordance with the known turbine described above, has at least two drive nozzles to supply the turbine blades of the rotatable turbine wheel with a drive gas (e.g. compressed air) in order to drive the turbine wheel.

[0016] The invention provides that the various drive nozzles are supplied with drive gas from separate drive gas supplies, with the drive gas supplies being separate from one another so that the drive nozzles can be supplied with drive gas independently. This makes it possible to select and supply the most suitable drive nozzle with drive gas depending on the respective load point of the turbine drive, while the other drive nozzles are deactivated and not supplied with drive gas. The invention thus enables a targeted selection and activation or deactivation of the individual drive air nozzles depending on the load point in order to optimize the efficiency of the turbine accordingly.

[0017] In the preferred embodiment of the invention, three different drive nozzles and three drive gas inlets are provided, which are separate from one another and can be operated independently. However, the invention is not limited to a specific number of drive nozzles and separate drive gas inlets. Thus, more than three drive nozzles and, correspondingly, more than three drive gas inlets can also be provided.

[0018] For example, multiple groups of drive nozzles can be provided, with each group's drive nozzles being supplied with drive gas (e.g., compressed air) via a common drive gas supply. For instance, a first group of drive nozzles could be optimized for exterior painting, while a second group is optimized for interior painting. Depending on the type of painting (exterior / interior), the drive nozzles of one of the two groups are then selected and supplied with drive gas, while the drive nozzles of the other group remain inactive.

[0019] Furthermore, it should be noted that the various drive nozzles are preferably different, for example, in terms of their nozzle shape and / or their nozzle cross-section. This is advantageous so that, depending on the respective load point, the most suitable drive nozzle can be selected for the flow towards the turbine blades of the turbine wheel. It should also be mentioned that, as a rule, not just a single drive nozzle is selected. For example, several drive nozzles can be selected simultaneously, depending on the respective load point.

[0020] Furthermore, it should be mentioned that the individual drive nozzles may preferably have a convergent-divergent nozzle cross-section. This means that the nozzle cross-section initially narrows convergently in the flow direction and then widens again divergently, as is the case, for example, with a Laval nozzle.

[0021] As mentioned earlier, the turbine wheel can also be braked by releasing a braking gas (e.g., compressed air) from a braking nozzle onto the turbine blades of the turbine wheel, with the braking nozzle being oriented opposite to the at least one drive nozzle. The turbine drive according to the invention also preferably provides such a braking nozzle, which is preferably supplied with the respective braking gas (e.g., compressed air) from a braking gas supply via a braking gas control valve.

[0022] Furthermore, as mentioned above, the drive nozzles are supplied individually or in groups with the respective drive gas (e.g., compressed air) via separate drive gas supplies. Each drive gas supply preferably contains a drive gas control valve, which can, for example, be designed as a proportional valve and is preferably pneumatically actuated. However, instead of pneumatic actuation of the drive gas control valves, electrical or other actuation methods are also possible.

[0023] Furthermore, the invention provides for the possibility of arranging a bistable spring element in at least one of the drive gas supply lines, which either opens or closes the respective drive gas supply line depending on its state. The bistable spring element is thus a bistable valve, wherein the bistable spring element is preferably connected to the brake gas supply line and changes its state upon a pressure impulse in the brake gas supply line.

[0024] The concept of the bistable spring element can also be implemented with multiple drive nozzles, meaning that a bistable spring element can be arranged in each of the individual drive gas inlets. However, in this case, there is no efficient flow via the respective drive gas inlet, since there is only a single brake gas inlet.

[0025] Furthermore, the turbine drive according to the invention can have a gas heater to heat the drive gas and / or the braking gas (e.g. compressed air) upstream of the drive nozzles or upstream of the braking nozzle, wherein the gas heater is preferably arranged outside the rotary atomizer.

[0026] In one variant of the invention, the gas heater only heats the drive gas in one of the drive gas feeds, while the drive gas in the other drive gas feed(s) is not heated by the gas heater.

[0027] In another embodiment of the invention, the gas heater heats the drive gas in several and preferably in all drive gas feeds.

[0028] The gas heater can, for example, be located upstream of the at least one drive gas control valve. Alternatively, it is also possible for the gas heater to be located downstream of the at least one drive gas control valve.

[0029] Furthermore, it should be mentioned that the turbine drive according to the invention preferably also includes a turbine control unit which receives a load point on the input side, wherein the load point determines the rotational speed and / or torque of the turbine drive. On the output side, the turbine control unit then controls the drive gas control valves depending on the load point. In this process, the turbine control unit specifically selects the drive nozzles that promise optimal turbine efficiency at the respective load point.

[0030] For example, depending on the load point, the turbine control system can open a different number of the drive gas control valves and close the remaining ones. Therefore, depending on the load point, the turbine control system can not only select the most suitable drive nozzle, but also vary the number of selected drive nozzles to increase turbine efficiency.

[0031] For example, the turbine control system with three drive nozzles can set one of the following operating states depending on the respective load point: Only the first drive gas control valve is open, while the other drive gas control valves are closed, so only the first drive nozzle delivers the drive gas. Only the second drive gas control valve is open, while the other drive gas control valves are closed, so only the second drive nozzle delivers the drive gas. Only the third drive gas control valve is open, while the other drive gas control valves are closed, so only the third drive nozzle delivers the drive gas. Only the first and second drive gas control valves are open, while the third drive gas control valve is closed, so only the first and second drive nozzles deliver the drive gas.Only the first and third drive gas control valves are open, while the second drive gas control valve is closed, so only the first and third drive nozzles deliver the drive gas. Only the second and third drive gas control valves are open, while the first drive gas control valve is closed, so only the second and third drive nozzles deliver the drive gas. All drive gas control valves are open, so all drive nozzles deliver the drive gas.

[0032] Furthermore, the turbine drive according to the invention can have several drive gas shut-off valves in order to release or block the drive gas flows separately and independently of one another. In this case, a common drive gas proportional valve is preferably provided, which serves to adjust the sum of the individual drive gas flows, wherein the drive gas proportional valve is then arranged upstream of the drive gas shut-off valves.

[0033] The invention claims, firstly, protection for the turbine drive described above, wherein the protection extends to the individual turbine, the rotary atomizer with such a turbine, and the turbine drive as a whole, which may also include the turbine control, the air heater, and other components. The term "turbine drive" used within the scope of the invention can therefore refer to the individual turbine, the rotary atomizer with such a turbine, or the complete turbine drive.

[0034] However, the invention also claims protection for a corresponding operating method for such a turbine drive, wherein the individual steps of the operating method according to the invention are already evident from the foregoing description, so that a separate description can be dispensed with and reference is made to the foregoing description.

[0035] Other advantageous embodiments of the invention are characterized in the dependent claims or are explained in more detail below together with the description of the preferred embodiments of the invention with reference to the figures. Brief description of the drawings

[0036] Figure 1 shows a schematic representation of a turbine drive according to the invention for a rotary atomizer. Figure 2 shows a variation of Figure 1 . Figure 3 shows another variation of the Figures 1 and 2 . The Figures 4A-4C show different views of a turbine according to the invention for a rotary atomizer. Figure 5 Figure 1 shows a schematic representation of a turbine drive according to the invention, which operates the turbine in an optimal operating range depending on the respective load point. Figure 6 shows a flowchart to illustrate the operating method according to the invention. Figure 7shows a modification of a turbine drive according to the invention. Figure 8 shows a further modification of a turbine drive according to the invention. Figure 9 Finally, a modification of a turbine drive according to the invention with a bistable spring element is shown. Detailed description of the drawings

[0037] The following section describes first an exemplary embodiment of a turbine drive according to the invention. Figure 1 described.

[0038] The turbine drive serves to power a rotary atomizer 1, which is used for painting vehicle body components in a paint shop. For this purpose, the rotary atomizer 1 contains a turbine 2, which is largely of conventional design, as described, for example, in EP 1 388 372 A1, and reference is made to this publication for further information.

[0039] Turbine 2 features a rotatably mounted turbine wheel with numerous turbine blades distributed around its circumference. Compressed air can be supplied to the turbine blades from two drive nozzles 3 and 4 to drive the turbine wheel and thus the rotary atomizer 1.

[0040] The two drive nozzles 3, 4 are supplied with compressed air from a compressed air supply 8, which can be referred to as a compressed air reservoir, compressed air compressor or pressure vessel, via separate drive gas supplies 5, 6 and an air heater 7.

[0041] Each of the two drive gas inlets 5, 6 is equipped with a drive gas control valve 9, 10, which can independently control the drive gas flow to the individual drive nozzles 3, 4. In this embodiment, the drive gas control valves 9, 10 are designed as proportional valves, which can be actuated, for example, pneumatically or electrically.

[0042] Depending on the respective load point, the two drive gas control valves 9, 10 can then be controlled independently of each other in order to control the two drive nozzles 3, 4 accordingly. The control is carried out in such a way that optimal efficiency of the turbine 2 is achieved depending on the respective load point.

[0043] Furthermore, turbine 2 has a braking nozzle 11, which makes it possible to slow down the turbine wheel by blowing compressed air onto the turbine blades. The braking nozzle 11 is therefore oriented opposite to the two drive nozzles 3 and 4.

[0044] The brake nozzle 11 is supplied with compressed air via a brake gas supply 12 and a brake gas control valve 13.

[0045] The exemplary embodiment according to Figure 2 largely agrees with the above description and in Figure 1 The embodiment shown is identical, so that to avoid repetition, reference is made to the preceding description, using the same reference numerals for corresponding details.

[0046] A special feature of this embodiment is that the two drive gas control valves 9, 10 are arranged upstream of the air heater 7, whereas in the embodiment according to Figure 1 are located downstream behind air heater 7.

[0047] Another special feature of this embodiment is that the air heater 7 only heats the compressed air in the drive gas supply 5, whereas the other drive gas supply 6 is routed around the air heater 7.

[0048] The exemplary embodiment according to Figure 3 largely agrees with the above-described and in the Figures 1 and 2 The illustrated embodiments correspond to the above description, so that, to avoid repetition, reference is made to the preceding description, using the same reference numerals for corresponding details.

[0049] A special feature of this embodiment is that the air heater 7 enables separate and independent heating of the compressed air in the two drive gas supplies 5, 6. For example, the compressed air in drive gas supply 5 can be heated more than the compressed air in the other drive gas supply 6.

[0050] The Figures 4A-4C The figures show various views of a turbine 14 according to the invention, as is known in a similar form from EP 1 388 372 A1, so that reference is made to this publication in addition.

[0051] Thus, the turbine 14 has several housing parts 15-18 which, when assembled, accommodate a turbine wheel 19 with a turbine shaft 20 and numerous turbine blades 21, the turbine blades 21 being arranged distributed over the circumference of the turbine wheel 19.

[0052] Out of Figure 4CIt is evident that the individual turbine blades 21 of the turbine wheel 19 can be supplied with compressed air from three drive nozzles 22-24 to drive the turbine wheel 19, as is known from the prior art. The drive nozzles 22-24 are arranged in the housing part 16 and are designed differently with regard to number, nozzle cross-section and shape, in order to allow adaptation to the respective load point of the turbine 14 by selecting the appropriate drive nozzle 22-24.

[0053] Furthermore, the housing section 16 contains three separate and independent drive gas inlets 25-27 to supply the three drive nozzles 22-24 with compressed air independently of each other. This allows for the targeted selection of one or more of the drive nozzles 22-24 depending on the respective load point of the turbine 14, in order to achieve maximum efficiency of the turbine 14.

[0054] Furthermore, it is from Figure 4C It is also evident that a brake nozzle 28 is formed in the housing part 16 of the turbine 14, which is supplied with compressed air from a brake gas supply 29. The brake nozzle 28 on the one hand and the drive nozzles 22-24 on the other hand are oriented in opposite directions according to their function (drive or brake).

[0055] Figure 5 Figure 1 shows a schematic representation of a turbine drive according to the invention with three proportional valves 30-32 for controlling three drive nozzles, which are not shown here for the sake of simplicity.

[0056] Furthermore, a brake valve 33 is shown to supply a brake nozzle with compressed air, although the brake nozzle is not shown here for the sake of simplicity.

[0057] The proportional valves 30-32 and the brake valve 33 are controlled by a turbine control 34 depending on the respective load point in such a way that the turbine has the greatest possible efficiency.

[0058] Figure 6 shows a flowchart to explain the operating method according to the invention.

[0059] In a first step S1, the respective load point of the turbine is determined, which is defined by torque and rotational speed.

[0060] In the next step S2, the optimal combination of drive nozzles and drive air volume for the load point is then determined.

[0061] In the next step S3, the proportional valves for the individual drive nozzles are then controlled according to the optimal combination.

[0062] In this way, the turbine can be operated very efficiently at different load points.

[0063] Figure 7 Figure 1 shows a schematic representation of a turbine drive according to the invention with three drive nozzles 35-37, which are supplied with compressed air via three separate drive gas feeds 38-40.

[0064] Each of the individual drive gas inlets 38-40 is equipped with a drive gas control valve 41-43, so that the drive nozzles 35-37 can be controlled independently of one another. The gas heater can be located upstream or downstream in separate chambers.

[0065] The drive gas supplies 38-40 are combined on the inlet side via a proportional valve 44 and are supplied with compressed air from a common compressed air supply 45.

[0066] Figure 8Figure 1 shows a schematic representation of a turbine drive according to the invention, which largely corresponds to the embodiments described above, so that reference is made to the preceding description to avoid repetition, with the same reference numerals being used for corresponding details.

[0067] A special feature of this embodiment is that the drive gas control valves 41-43 are proportional valves that are pneumatically controlled.

[0068] Finally, it shows Figure 9 Another embodiment of a turbine drive according to the invention, which also largely corresponds to the embodiments described above, so that reference is made to the preceding description to avoid repetition, with the same reference numerals being used for corresponding details.

[0069] A special feature of this embodiment is that a bistable spring element 46 is arranged in one of the drive gas supply lines 6, which is connected to the brake gas supply line 12 and switches between two stable states when a pressure impulse is applied in the brake gas supply line 12, namely between a first state in which the bistable spring element 46 blocks the drive gas supply line 6 and a second state in which the bistable spring element 46 releases the drive gas supply line 6. Reference symbol list:

[0070] 1 Rotary atomizer 2 Turbine 3, 4 Drive nozzles 5, 6 Drive gas inlets 7 Air heater 8 Compressed air inlet 9, 10 Drive gas control valves 11 Brake nozzle 12 Brake gas inlet 13 Brake gas control valve 14 Turbine 15-18 Turbine housing components 19 Turbine wheel 20 Turbine shaft 21 Turbine blades 22-24 Drive nozzles 25-27 Drive gas inlets 28 Brake nozzle 29 Brake gas inlet 30-32 Proportional valves 33 Brake valve 34 Turbine control 35-37 Drive nozzles 38-40 Drive gas inlets 41-43 Drive gas control valves 44 Proportional valve 45 Compressed air inlet 46 Bistable spring element

Claims

1. Turbine drive for a rotary atomizer, comprising a) a rotatable turbine wheel (19) with a plurality of turbine blades (21), b) a first drive nozzle (3; 22) for delivering a drive gas, in particular compressed air, to the turbine blades (21) of the turbine wheel (19) in order to drive the turbine wheel (19), the drive gas optionally originating from a compressed air reservoir, from a compressed air compressor or from a pressure vessel, c) a first drive gas supply (5; 25) for supplying the drive gas to the first drive nozzle (3; 22), and d) a second drive nozzle (4; 23) for delivering the drive gas to the turbine shafts (21) of the turbine wheel (19) in order to drive the turbine wheel (19), and e) a second drive gas supply (6; 26) for supplying the drive gas to the second drive nozzle (4; 23), characterized in f) that the second drive gas supply (6; 26) being separate from the first drive gas supply (5; 25), so that the second drive nozzle (4; 23) can be supplied with the drive gas independently of the first drive nozzle (3; 22).

2. Turbine drive according to claim 1, characterized by a) a third drive nozzle (24) for delivering the drive gas to the turbine blades (21) of the turbine wheel (19) in order to drive the turbine wheel (19), and b) a third drive gas supply (27) for supplying the drive gas to the third drive nozzle (24), the third drive gas supply (27) being separate from the first drive gas supply (25) and from the second drive gas supply (26), so that the third drive nozzle (24) can be supplied with the drive gas independently of the first drive nozzle (22) and independently of the second drive nozzle (23).

3. Turbine drive according to one of the preceding claims, characterized in a) that the first drive nozzle (3; 22), the second drive nozzle (4; 23) and / or the third drive nozzle (24) are different, preferably with respect to their nozzle shape and / or with respect to their nozzle cross-section, and / or b) that the first drive nozzle (3; 22) and / or the second drive nozzle (4; 23) and / or the third drive nozzle (24) has a convergent-divergent nozzle cross-section, in particular in the form of a Laval nozzle.

4. Turbine drive according to one of the preceding claims, characterized by a) at least one brake nozzle (11; 28) for delivering a brake gas, in particular compressed air, to the turbine blades (21) of the turbine wheel (19) in order to brake the turbine wheel (19), the brake nozzle (11; 28) being oriented in the opposite direction to the at least one drive nozzle (3, 4; 22-24), and b) preferably a brake gas control valve (13) for controlling the brake gas flow to the brake nozzle (11; 28), wherein the brake gas control valve (13) is preferably arranged outside the rotary atomizer (1), c) preferably a brake gas supply (12) for supplying the brake gas.

5. Turbine drive according to one of the preceding claims, characterized by a) a first drive gas control valve (30; 41), in particular as a preferably pneumatically controlled proportional valve, for controlling the drive gas flow through the first drive gas supply (25) to the first drive nozzle (22), wherein the first drive gas control valve (30; 41) is preferably arranged outside the rotary atomizer (1), and / or b) a second drive gas control valve (31; 42), in particular as a preferably pneumatically controlled proportional valve, for controlling the drive gas flow through the second drive gas supply (26) to the second drive nozzle (23), wherein the second drive gas control valve (31; 42) is preferably arranged outside the rotary atomizer (1), and / or c) a third drive gas control valve (32; 43), in particular as a preferably pneumatically controlled proportional valve, for controlling the drive gas flow through the third drive gas supply (32; 43) to the third drive nozzle (24), the third drive gas control valve (32; 43) preferably being arranged outside the rotary atomizer (1).

6. Turbine drive according to one of the preceding claims, characterized in a) that a bistable spring element (46) is arranged in at least one of the drive gas supplies, which either releases or blocks the respective drive gas supply depending on its state, b) that the bistable spring element (46) is preferably connected to the brake gas supply (12) and changes its state in the event of a pressure pulse in the brake gas supply.

7. Turbine drive according to one of the preceding claims, characterized by a gas heater (7) for heating the drive gas and / or the brake gas upstream of the drive nozzles and / or upstream of the brake nozzle, the gas heater (7) preferably being arranged outside the rotary atomizer (1).

8. Turbine drive according to claim 7, characterized in a) that the gas heater (7) a1) only heats the drive gas in one of the drive gas supplies (5, 6), while the drive gas in the other drive gas supply or supplies (5, 6) is not heated by the gas heater (7), or a2) heats the drive gas in several and preferably all drive gas supply lines (5, 6), and / or b) that the gas heater (7) b1) is arranged upstream of the at least one drive gas control valve (9, 10) or b2) is arranged downstream behind the at least one drive gas control valve (9, 10), in particular in separate air chambers.

9. Turbine drive according to one of the preceding claims, characterized in a) that the turbine drive has a turbine controller (34), b) in that the turbine controller (34) receives a load point on the input side, the load point determining the speed and / or the torque of the turbine drive, and c) that the turbine controller (34) controls the drive gas control valves (30-32) on the output side as a function of the load point, d) that the turbine controller (34) preferably opens a different number of the drive gas control valves (30-32) as a function of the load point and closes the remaining drive gas control valves (30-32).

10. Turbine drive according to claim 9, characterized in that the turbine controller sets one of the following operating states as a function of the load point: a) only the first drive gas control valve (30) is open, so that only the first drive nozzle discharges the drive gas, b) only the second drive gas control valve (31) is open, so that only the second drive nozzle emits the drive gas, c) only the third drive gas control valve (32) is open, so that only the third drive nozzle emits the drive gas, d) only the first drive gas control valve (30) and the second drive gas control valve (31) are open, so that only the first drive nozzle and the second drive nozzle emit the drive gas, e) only the first drive gas control valve (30) and the third drive gas control valve (32) are open, so that only the first drive nozzle and the third drive nozzle emit the drive gas, f) only the second drive gas control valve (31) and the third drive gas control valve (32) are open, so that only the second drive nozzle and the third drive nozzle emit the drive gas, g) all drive gas control valves (30-32) are open so that all drive nozzles release the drive gas.

11. Turbine drive according to one of the preceding claims, characterized by a) a plurality of drive gas shut-off valves (41-43) for separately releasing or blocking the individual drive gas flows independently of one another, and b) a common drive gas proportional valve (44) for adjusting the sum of the individual drive gas flows, wherein the drive gas proportional valve (44) is arranged upstream of the drive gas shut-off valves (41-43).

12. Rotary atomizer (1) with a turbine drive according to one of the preceding claims.

13. Operating method for a turbine drive of a rotary atomizer (1), in particular for a turbine drive according to one of the preceding claims, comprising the following steps: a) discharging a first drive gas flow of a drive gas from a first drive nozzle (3; 22) onto turbine blades (21) of a turbine wheel (19) of an atomizer turbine (14), and b) discharging a second drive gas flow of the drive gas from a second drive nozzle (4; 23) onto the turbine blades (21) of the turbine wheel (19) of the atomizer turbine (14), characterized by the following step: c) separately controlling the first drive gas flow independently of the second drive gas flow.

14. Operating method according to claim 13, characterized by the following steps: a) discharging a third drive gas flow of the drive gas from a third drive nozzle (24) onto the turbine blades (21) of the turbine wheel (19) of the atomizer turbine, and b) separate control of the third drive gas flow independently of the first drive gas flow and independently of the second drive gas flow.

15. Operating method according to claim 13 or 14, characterized by the following steps: a) determining a load point of the turbine drive, the load point determining the speed and / or torque of the turbine drive, and b) adjusting the first drive gas flow and the second drive gas flow and optionally also the third drive gas flow as a function of the load point, wherein a different number of the drive gas flows is preferably switched on as a function of the load point.

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