Turbine drive for rotary atomizers and associated operating methods - Patents.com

Abstract

The invention relates to a turbine drive for a rotary atomizer, comprising a rotatable turbine wheel having a plurality of turbine blades, a first motive nozzle (3) for delivering motive gas, in particular compressed air, to the turbine blades of the turbine wheel to drive the turbine wheel, a first motive gas supply (5) for supplying the motive gas to the first motive gas nozzle (3) and a second motive nozzle (4) for delivering the motive gas to the turbine blades of the turbine wheel to drive the turbine wheel. The invention further provides a second motive gas supply (6) for supplying the motive gas to the second motive nozzle (4), said second motive gas supply (6) being separate from the first motive gas supply (5), so that the second motive nozzle (4) can be supplied with motive gas independently of the first motive nozzle (3). Furthermore, the invention comprises a corresponding method of operation.

Description

[Technical field]

[0001] The present invention relates to a turbine drive for a rotary atomizer and a corresponding method of operation. [Background technology]

[0002] In modern painting facilities for painting automotive body parts, rotary sprayers driven by compressed air-driven turbines are usually used as application devices. One such turbine is known, for example from DE 10 200 03 133 A1. The known turbine has a rotatably mounted turbine wheel with an innumerable number of turbine blades distributed around the circumference of the turbine wheel. To drive the rotary sprayers, the turbine blades are supplied with compressed air, which leaves from a number of drive nozzles distributed around the circumference of the turbine wheel. The turbine wheel can also be braked. For this purpose, brake air is discharged from the brake nozzles in the opposite direction onto the turbine blades. Although the known turbines already function satisfactorily, there is still interest in increasing the efficiency of the turbines.

[0003] See also U.S. Patent Nos. 5,393,633, 5,496,703, 5,597,103, and 5,633,974 for prior art. [Prior art documents] [Patent documents]

[0004] [Patent Document 1] European Patent Application Publication No. 1388372 [Patent Document 2] International Publication No. 2016 / 062365 [Patent Document 3] European Patent Application Publication No. 1384516 [Patent Document 4] DE 4425229 A1 [Patent Document 5] DE 10115469 A1 Summary of the Invention [Problem to be solved by the invention]

[0005] In view of the above, the present invention is based on the problem of providing a correspondingly improved turbine drive for a rotary atomizer. Furthermore, the present invention is also based on the problem of specifying a corresponding operating method for such a turbine drive. [Means for solving the problem]

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

[0007] The present invention is based on the technical physical understanding that the turbine in a rotary atomizer is often not operated at the optimum load point (which is determined by speed and torque) during operation.

[0008] For example, when painting the inside surfaces of automobile body parts, only a relatively small paint flow is produced, requiring a correspondingly low turbine mechanical drive force.

[0009] On the other hand, when painting the exterior of motor vehicle body parts, relatively large areas are painted, which results in correspondingly large paint flows being applied, which in turn require relatively high mechanical drive forces for the turbines of the rotary atomizers.

[0010] The invention is based on the fact that the various load points occurring during the operation of a rotary atomizer mean that the turbine is not always operated at its optimum load point, since the turbine nozzle in terms of shape and nozzle cross section can only be optimized at a certain load point. However, operating the turbine at a non-optimum load point leads to a decrease in the efficiency of the turbine. For example, optimizing the turbine for an external coating leads to a relatively poor efficiency for an internal coating. In contrast, optimizing the turbine for an internal coating leads to a relatively poor efficiency for an external coating.

[0011] The present invention therefore provides a turbine having various motive nozzles which can be supplied with their own motive gas (e.g. compressed air) from separate motive gas supply lines, so that the various motive nozzles can be activated or deactivated independently of one another, and depending on the respective load points one or the other motive nozzle can be activated, so that the turbine can be operated at optimum operating conditions even at varying load points, thereby increasing the efficiency of the turbine at varying load points.

[0012] For example, one motive nozzle may be optimized for exterior coating and another motive nozzle may be optimized for interior coating, and for exterior coating, the motive nozzle optimized for exterior coating is selected, while for interior coating, the aforementioned motive nozzle optimized for interior coating is specifically selected.

[0013] The turbine drive according to the invention is designed for a rotary atomizer, as known from the prior art, for example as described in US Pat. No. 5,399,633.

[0014] Thus, like known turbine drives, the turbine drive according to the invention has a rotatable turbine wheel with a number of turbine blades. In a preferred embodiment of the invention, the turbine is designed as a radial turbine, although in principle it is also possible to design the turbine as an axial turbine.

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

[0016] The present invention provides various motive nozzles supplied with motive gas from different motive gas supply lines, which are separate from each other, so that the motive nozzles can be supplied with motive gas independently of each other. This makes it possible to select the most suitable motive nozzle depending on the respective load point of the turbine drive and supply it with motive gas, while the other motive nozzles are deactivated and not supplied with motive gas. Thus, the present invention allows targeted selection and activation or deactivation of individual motive air nozzles depending on the load point, for optimization of the efficiency of the turbine based on the load point.

[0017] In a preferred embodiment of the invention, three different motive nozzles and three motive gas supplies are provided, which are separate from one another and can be operated independently from one another, however, the invention is not limited to a particular number of motive nozzles and separate motive gas supplies, and therefore it is possible to provide more than three motive nozzles and correspondingly more than three motive gas supplies.

[0018] For example, it is possible to provide several groups of motive nozzles, where the motive nozzles of the individual groups are each supplied with motive gas (e.g. compressed air) by a common motive gas supply. For example, a first group of motive nozzles can be optimized for external coating, a second group of motive nozzles can be optimized for internal coating, and depending on the type of coating (external coating / internal coating), one or two groups of motive nozzles are selected and supplied with motive gas, while the motive nozzles of the other groups are switched off.

[0019] It should also be noted that the various motive nozzles are preferably different, for example with respect to their nozzle shape and / or nozzle cross section. This makes sense, so that the optimum motive nozzle for the flow to the turbine blades of the turbine wheel can be selected depending on the respective load point. Here, it should also be noted that in principle not only a single motive nozzle is selected. For example, several motive nozzles can be selected simultaneously depending on the respective load points.

[0020] It is also worth noting that the individual motive nozzles preferably have a convergent-divergent nozzle cross section, which means that the nozzle cross section first narrows in the direction of flow and then diverges again, as is the case for example with a Laval nozzle.

[0021] As already mentioned at the beginning, the turbine wheel can be braked by ejecting a brake gas (e.g. compressed air) from a brake nozzle onto the turbine blades of the turbine wheel, the brake nozzle being aligned opposite to at least one drive nozzle. Such a brake nozzle is also preferably provided in the turbine drive according to the invention, and the brake nozzle is preferably supplied with the respective brake gas (e.g. compressed air) from a brake gas supply via a brake gas control valve.

[0022] Furthermore, as already mentioned above, the motive nozzles are supplied with their respective motive gas (e.g. compressed air) individually or collectively via separate motive gas supply lines. A motive gas control valve is preferably arranged in each of the individual motive gas supply lines, which can be designed, for example, as a proportional valve and is preferably controlled pneumatically. However, instead of pneumatic actuation of the motive gas control valve, an electric or other actuation is alternatively possible.

[0023] Furthermore, within the scope of the invention it is also possible to arrange a bistable spring element in at least one of the drive gas supply lines, which depending on its state either opens or closes the respective drive gas supply line, so that the bistable spring element is a bistable valve, where the bistable spring element is preferably connected to the braking gas supply and changes its state in the event of a pressure pulse in the braking gas supply.

[0024] The bistable spring element concept can also be implemented in multiple motive nozzles, i.e. a bistable spring element can be placed in each of the individual motive gas supply lines, however in this case there is no efficient flow through each motive gas supply as there is only a single damping gas supply.

[0025] Furthermore, the turbine drive according to the present invention may have a gas heater for heating the braking gas (e.g. compressed air) and / or the driving gas upstream of the driving nozzle or upstream of the braking nozzle, where the gas heater is preferably arranged outside the rotary atomizer.

[0026] In one variation of the invention, the gas heater heats only the driving gas in one of the driving gas supply lines, and the driving gas in one or more other driving gas supply lines is not heated by the gas heater.

[0027] However, in another variation of the invention, the gas heater heats the driving gas in several, preferably all, of the driving gas supply lines.

[0028] The gas heater may be arranged, for example, upstream of the at least one drive gas control valve, although it is also possible that, instead, the gas heater is arranged downstream of the at least one drive gas control valve.

[0029] Furthermore, it is particularly noted that the turbine drive according to the invention preferably also comprises a turbine control device which receives at its input the load points determining the speed and / or torque of the turbine drive and at its output controls the drive gas control valve as a function of the load points, wherein the turbine control device specifically selects the drive nozzles which ensure optimal turbine efficiency at the respective load points.

[0030] For example, the turbine controller can open different numbers of drive gas control valves and close the remaining drive gas control valves depending on the load point, so that the turbine controller can not only select the optimal drive nozzle depending on the load point, but also vary the number of selected drive nozzles according to the load point to increase the efficiency of the turbine.

[0031] For example, with three motive nozzles, the turbine controller may set one of the following operating conditions depending on the respective load points: Only the first drive gas control valve is open, the other drive gas control valves are closed, and only the first drive nozzle emits drive gas. Only the second drive gas control valve is open, the other drive gas control valves are closed, and only the second drive nozzle emits drive gas. Only the third drive gas control valve is open, the other drive gas control valves are closed, and only the third drive nozzle emits drive gas. Only the first and second drive gas control valves are open, the third drive gas control valve is closed, and only the first and second drive nozzles emit drive gas. Only the first drive gas control valve and the third drive gas control valve are open, the second drive gas control valve is closed, and only the first drive nozzle and the third drive nozzle eject drive gas. Only the second drive gas control valve and the third drive gas control valve are open, the first drive gas control valve is closed, and only the second drive nozzle and the third drive nozzle eject drive gas. All drive gas control valves are open and all drive nozzles discharge drive gas.

[0032] Furthermore, the turbine drive according to the invention may have several drive gas shutoff valves for opening or shutting off the drive gas flows individually and independently of each other, in which case a common drive gas proportional valve serving to adjust the sum of the individual drive gas flows is preferably provided and the drive gas proportional valve is arranged upstream of the drive gas shutoff valve.

[0033] The present invention claims protection for the above-mentioned turbine drive, where protection also extends to the individual turbines, rotary atomizers with the turbine drive and said turbine as a whole, which may also include a turbine control device, air heaters and other components.The term turbine drive as used in the context of the present invention can therefore refer to an individual turbine, a rotary atomizer with such a turbine or a set of turbine drives.

[0034] However, the invention also claims protection for a corresponding operating method for driving such a turbine, the individual steps of which are already clear from the above description, so that a separate description is omitted and reference is made to the above description for this purpose.

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

[0036] [Figure 1] FIG. 1 shows a schematic diagram of a turbine drive for a rotary atomizer according to the present invention. [Diagram 2] FIG. 2 shows a modification of FIG. [Diagram 3] FIG. 3 shows a further modification of FIGS. [Figure 4A] 4A-C show various views of a turbine drive for a rotary atomizer according to the present invention. [Figure 4B] See legend to Figure 4A. [Figure 4C] See legend to Figure 4A. [Diagram 5] FIG. 5 shows a schematic diagram of a turbine drive according to the invention which operates the turbine in its optimum operating range depending on the respective load point. [Figure 6] FIG. 6 shows a flow diagram illustrating a method of operation according to the present invention. [Figure 7] FIG. 7 shows a modification of the turbine drive according to the invention. [Figure 8] FIG. 8 shows a further modification of the turbine drive according to the invention. [Figure 9] FIG. 9 shows a modification of the turbine drive according to the invention with a bistable spring element. DETAILED DESCRIPTION OF THE PREFERRED EMBODIMENTS

[0037] In the following, an embodiment of a turbine drive according to the invention shown in FIG. 1 will first be described.

[0038] The turbine drive is used to drive a rotary sprayer 1 which is used in a paint shop to paint automotive body parts. To this end, the rotary sprayer 1 comprises a turbine 2 which is largely of conventional design, e.g. of the above-mentioned US Pat. No. 5,399,433, to which reference is also made.

[0039] The turbine 2 thus comprises a rotatably mounted turbine wheel having an innumerable number of turbine blades distributed around its circumference, the turbine blades of which can be supplied with compressed air from two drive nozzles 3, 4 in order to drive the turbine wheel and thus the rotary atomizer 1.

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

[0041] A drive gas control valve 9, 10 is arranged in each of the two drive gas supply lines 5, 6, which are able to control independently of one another the flow of drive gas to the individual drive nozzles 3, 4. In this design example, the drive gas control valves 9, 10 are designed as proportional valves which can be actuated, for example, pneumatically or electrically.

[0042] And, in order to control the two motive nozzles 3, 4 accordingly, the motive gas control valves 9, 10 are controllable independently of each other depending on the respective load points. The control is performed so that the optimum efficiency of the turbine 2 is achieved depending on the load point.

[0043] Furthermore, the turbine 2 has a braking nozzle 11, which makes it possible to brake the turbine wheel by blowing compressed air against the turbine blades of the turbine wheel. The braking nozzle 11 is therefore aligned in the opposite direction to the two driving nozzles 3, 4.

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

[0045] The embodiment of FIG. 2 corresponds to a large extent to the embodiment shown in FIG. 1 and described above, so that to avoid repetition reference is made to that description and the same reference numbers are used for corresponding individual features.

[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 shown in FIG. 1 the two drive gas control valves 9, 10 are located downstream of the air heater 7.

[0047] A further special feature of this embodiment is that the air heater 7 heats only the compressed air in the drive gas supply 5, whilst the other drive gas supply 6 is bypassed by the air heater 7.

[0048] The embodiment of FIG. 3 corresponds to the embodiment shown in FIGS. 1 and 2 and described above in large part, so that to avoid repetition reference is made to the above description and the same reference numbers are used for corresponding details.

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

[0050] 4A-4C show different views of a turbine 14 according to the invention, which is known in a similar form from US Pat. No. 5,399,323, reference being therefore also made to said publication.

[0051] The turbine 14 thus has a number of housing parts 15-18 which, when assembled, house a turbine wheel 19 having a turbine shaft 20 and a number of turbine blades 21, the turbine blades 21 being distributed around the circumference of the turbine wheel 19.

[0052] 4C shows that, as known from the prior art, the individual turbine blades 21 of the turbine wheel 19 can be supplied with compressed air from three motive nozzles 22-24 in order to drive the turbine wheel 19. The motive 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 motive nozzle 22-24.

[0053] Furthermore, three separate and mutually separated motive gas supply lines 25-27 are present in the housing part 16 in order to be able to supply the three motive nozzles 22-24 with compressed air independently of one another, which makes it possible to select one or more of the motive nozzles 22-24 depending on the respective load points of the turbine 14 in order to achieve the maximum possible efficiency of the turbine 14.

[0054] Furthermore, as can be seen from Figure 4C, a braking nozzle 28 is also formed in the housing part 16 of the turbine 14, which is supplied with compressed air from a braking gas supply 29. The braking nozzle 28 on the one hand and the driving nozzles 22-24 on the other hand are aligned in opposite directions according to their function (driving or braking).

[0055] FIG. 5 shows a schematic diagram of a turbine drive according to the present invention having three proportional valves 30-32 for controlling three motive nozzles (not shown for simplicity).

[0056] Additionally, a damping valve 33 is shown for supplying compressed air to a damping nozzle (not shown for simplicity).

[0057] The proportional valves 30-32 and damping valve 33 are controlled by a turbine controller 34 according to their respective load points so that the turbine operates at its maximum possible efficiency.

[0058] FIG. 6 shows a flow chart illustrating the operating method according to the present invention.

[0059] In a first step S1, the respective load points of the turbine, defined by torque and speed, are first determined.

[0060] In the next step S2, the optimum combination of motive nozzle and motive air volume for the load point is determined.

[0061] In the next step S3, the proportional valves for the individual driving nozzles are controlled according to the aforementioned optimum combination.

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

[0063] FIG. 7 shows a schematic diagram of a turbine drive according to the invention having three motive nozzles 35-37 supplied with compressed air via three separate motive gas supply lines 38-40.

[0064] A motive gas control valve 41-43 is disposed in each motive gas supply line 38-40, respectively, so that the motive nozzles 35-37 are controlled independently of each other. Gas heaters may be connected upstream or downstream in separate chambers.

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

[0066] FIG. 8 shows a schematic diagram of a turbine drive according to the invention, which corresponds in large part to the above-described embodiment, so that to avoid repetition reference is made to the above description and the same reference numbers are used for corresponding details.

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

[0068] Finally, FIG. 9 shows a further embodiment of a turbine drive according to the invention, which corresponds to a large extent to the embodiment described above, so that to avoid repetition reference is made to the above description and the same reference numbers are used for corresponding details.

[0069] A particular feature of this embodiment is that the bistable spring element 46 is arranged in one drive gas supply 6, which is connected to the braking gas supply 12 and switches between two stable states when a pressure pulse occurs in the braking gas supply 12, in particular between a first state in which the bistable spring element 46 closes the drive gas supply 6 and a second state in which the bistable spring element 46 opens the drive gas supply 6.

[0070] The present invention is not limited to the above-described preferred embodiment. Rather, numerous variations and modifications are possible that utilize the concept of the present invention and are therefore within the scope of protection. In particular, the present invention claims protection for the subject matter and features of the dependent claims independently of the respective claims to which they refer, and in particular without the features of the main claim. Thus, the present invention encompasses various aspects that enjoy protection independent of each other.

[0071] [Note] [Appendix 1] A turbine drive for a rotary atomizer, comprising: a) a rotatable turbine wheel (19) having a plurality of turbine blades (21); b) a first motive nozzle (3; 22) for delivering a motive gas, in particular compressed air, to the turbine blades (21) of the turbine wheel (19) in order to drive the turbine wheel (19), said motive gas optionally coming from a compressed air container, a compressed air compressor or a pressure vessel; c) a first drive gas supply (5; 25) for supplying said drive gas to said first drive nozzle (3; 22); d) a second motive nozzle (4; 23) for delivering said motive gas to said turbine blades (21) of said turbine wheel (19) to drive said turbine wheel (19); Including, e) a turbine drive, characterised by a second motive gas supply (6; 26) for supplying the motive gas to the second motive nozzle (4; 23), the second motive gas supply (6; 26) being separate from the first motive gas supply (5; 25), so that the second motive nozzle (4; 23) can be supplied with the motive gas independently of the first motive nozzle (3; 22).

[0072] [Appendix 2] a) a third motive nozzle (24) for delivering the motive gas to the turbine blades (21) of the turbine wheel (19) to drive the turbine wheel (19); b) a third driving gas supply (27) for supplying the driving gas to the third driving nozzle (24), the third driving gas supply (27) being separate from the first driving gas supply (25) and the second driving gas supply (26) such that the third driving nozzle (24) can be supplied with the driving gas independent of the first driving nozzle (22) and the second driving nozzle (23); and Including, 2. A turbine drive as described in appendix 1.

[0073] [Appendix 3] a) said first motive nozzle (3; 22), said second motive nozzle (4; 23) and / or said third motive nozzle (24) preferably differ with respect to their nozzle shape and / or their nozzle cross-section, and / or b) said first motive nozzle (3; 22) and / or said second motive nozzle (4; 23) and / or said third motive nozzle (24) have a convergent-divergent nozzle cross section, in particular in the form of a Laval nozzle, 3. A turbine drive according to claim 1 or 2.

[0074] [Appendix 4] a) at least one braking nozzle (11; 28) for delivering a braking gas, in particular compressed air, to the turbine blades (21) of the turbine wheel (19) in order to brake the turbine wheel (19), the braking nozzle (11; 28) facing in a direction opposite to the at least one motive nozzle (3, 4; 22-24); and b) preferably a brake gas control valve (13) for controlling the flow of the brake gas to the brake nozzle (11; 28), the brake gas control valve (13) being preferably arranged outside the rotary sprayer (1); c) preferably a damping gas supply (12) for supplying said damping gas; Including, 4. A turbine drive according to any one of claims 1 to 3.

[0075] [Appendix 5] a) a first driving gas control valve (30; 41), in particular as a proportional valve of preferably pneumatically controlled type for controlling the flow of the driving gas through the first driving gas supply (25) to the first driving nozzle (22), the first driving gas control valve (30; 41) being preferably arranged outside the rotary atomizer (1), and / or b) a second driving gas control valve (31; 42), in particular as a proportional valve of preferably pneumatically controlled type for controlling the flow of the driving gas to the second driving nozzle (23) through the second driving gas supply (26), the second driving gas control valve (31; 42) being preferably arranged outside the rotary atomizer (1), and / or c) a third driving gas control valve (32; 43), in particular as a proportional valve of preferably pneumatically controlled type for controlling the flow of the driving gas to the third driving nozzle (24) through the third driving gas supply (32; 43), said third driving gas control valve (32; 43) being preferably arranged outside the rotary atomizer (1); Including, 5. A turbine drive according to any one of claims 1 to 4.

[0076] [Appendix 6] a) a bistable spring element (46) is disposed within at least one of the drive gas supplies, the bistable spring element (46) either opening or closing the respective drive gas supply depending on its state; b) the bistable spring element (46) is preferably connected to the damping gas supply (12) and changes its state when a pressure pulse occurs in the damping gas supply; 6. A turbine drive according to any one of claims 1 to 5.

[0077] [Appendix 7] a gas heater (7) for heating the drive gas and / or the brake gas upstream of the drive nozzle and / or upstream of the brake nozzle, said gas heater (7) being preferably arranged outside the rotary atomizer (1), 7. A turbine drive according to any one of claims 1 to 6.

[0078] [Appendix 8] a) the gas heater (7) heats only the driving gas in one of the driving gas supplies (5,6), and the driving gas in one or more of the other driving gas supplies (5,6) is not heated by the gas heater (7), or b) the gas heater (7) heats the driving gas in a number of, preferably all, driving gas supply lines (5, 6); 7. Turbine drive as described in appendix 7.

[0079] [Appendix 9] a) the gas heater (7) is arranged upstream of at least one of the driving gas control valves (9, 10), or b) the gas heater (7) is arranged downstream of at least one of the drive gas control valves (9, 10), in particular in a separate air chamber; 9. A turbine drive according to claim 7 or 8.

[0080] [Appendix 10] a) the turbine drive has a turbine control device (34); b) the turbine controller (34) receives a load point at an input, the load point determining the speed and / or torque of the turbine drive; c) the turbine control device (34) controls the drive gas control valves (30-32) on the output side in response to the load point; 10. A turbine drive according to any one of claims 1 to 9.

[0081] [Appendix 11] The turbine controller (34) opens a different number of the drive gas control valves (30-32) and closes the remaining drive gas control valves (30-32) depending on the load point. 11. The turbine drive according to claim 10.

[0082] [Appendix 12] The turbine control device, in response to the load point, a) only the first motive gas control valve (30) is open and only the first motive nozzle emits the motive gas; b) only the second driving gas control valve (31) is open and only the second driving nozzle outputs the driving gas; c) only the third motive gas control valve (32) is open and only the third motive nozzle emits the motive gas; d) only the first driving gas control valve (30) and the second driving gas control valve (31) are open, and only the first driving nozzle and the second driving nozzle emit the driving gas; e) only the first motive gas control valve (30) and the third motive gas control valve (32) are open and only the first motive nozzle and the third motive nozzle emit the motive gas; f) only the second driving gas control valve (31) and the third driving gas control valve (32) are open, and only the second driving nozzle and the third driving nozzle emit the driving gas; g) all of the motive gas control valves (30-32) are open and all of the motive nozzles emit the motive gas; Set one of the following operating states: 12. The turbine drive according to claim 10 or 11.

[0083] [Appendix 13] a) a plurality of drive gas shutoff valves (41-43) for individually opening or closing respective drive gas flows independently of one another; b) a common driving gas proportional valve (44) for adjusting the sum of the flows of the individual driving gases, said driving gas proportional valve (44) being disposed upstream of said driving gas shutoff valves (41-43); Including, 13. A turbine drive according to any one of claims 1 to 12.

[0084] [Appendix 14] A rotary atomizer (1) having a turbine drive according to any one of claims 1 to 13.

[0085] [Appendix 15] A method for driving a turbine of a rotary atomizer (1), in particular for driving a turbine according to any one of claims 1 to 13, comprising the steps of: a) discharging a first motive gas flow from a first motive nozzle (3; 22) onto turbine blades (21) of a turbine wheel (19) of an atomizer turbine (14); b) discharging a second motive gas flow of said motive gas from a second motive nozzle (4; 23) onto said turbine blades (21) of said turbine wheel (19) of said atomizer turbine (14); Including, c) separately controlling the first driving gas flow independently of the second driving gas flow.

[0086] [Appendix 16] a) discharging a third motive gas flow of the motive gas from a third motive nozzle (24) onto the turbine blades (21) of the turbine wheel (19) of the atomizer turbine; b) individually controlling the third driving gas flow independently of the first driving gas flow and the second driving gas flow; Including, The operating method described in Appendix 15.

[0087] [Appendix 17] a) determining a load point of the turbine drive, the load point determining the speed and / or torque of the turbine drive; b) adjusting the first and second driving gas flows, and optionally the third driving gas flow, in response to the load point; Including, 17. The method of operation according to claim 15 or 16.

[0088] [Appendix 18] A different number of driving gas flows are switched depending on the load point. The operating method described in Appendix 17. [Explanation of symbols]

[0089] 1 Rotary Sprayer 2. Turbine 3, 4 Drive nozzle 5, 6 Drive gas supply line 7 Air heater 8 Compressed Air Supply 9, 10 Drive gas control valve 11 Braking nozzle 12 Brake gas supply 13 Brake gas control valve 14 Turbine 15-18 Turbine housing parts 19 Turbine wheel 20 Turbine shaft 21 Turbine Blade 22-24 Driving nozzle 25-27 Drive gas supply line 28 Braking nozzle 29 Brake gas supply 30-32 Proportional valve 33 Brake valve 34 Turbine control device 35-37 Driving nozzle 38-40 Drive gas supply line 41-43 Drive gas control valve 44 Proportional valve 45 Compressed Air Supply 46 Bistable Spring Element

Claims

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

2. a) a third motive nozzle (24) for delivering the motive gas to the turbine blades (21) of the turbine wheel (19) to drive the turbine wheel (19); 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 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 the second drive nozzle (23); and Including, A turbine drive according to claim 1.

3. a) said first motive nozzle (3; 22), said second motive nozzle (4; 23) and / or said third motive nozzle (24) differ, preferably with respect to their nozzle shape and / or their nozzle cross section, and / or b) the first motive nozzle (3; 22) and / or the second motive nozzle (4; 23) and / or the third motive nozzle (24) have a convergent-divergent nozzle cross section, in particular in the form of a Laval nozzle; A turbine drive according to claim 1.

4. a) at least one braking nozzle (11; 28) for delivering a braking gas, in particular compressed air, to the turbine blades (21) of the turbine wheel (19) in order to brake the turbine wheel (19), the braking nozzle (11; 28) facing in a direction opposite to the at least one motive nozzle (3, 4; 22-24); and b) a brake gas control valve (13) for controlling the flow of the brake gas to the brake nozzle (11; 28), the brake gas control valve (13) being preferably located outside the rotary atomizer (1); c) preferably a damping gas supply (12) for supplying said damping gas; Including, A turbine drive according to claim 1.

5. a) a first drive gas control valve (30; 41), in particular as a proportional valve, preferably pneumatically controlled, for controlling the flow of the drive gas through the first drive gas supply (25) to the first drive nozzle (22), the first drive gas control valve (30; 41) being preferably located outside the rotary atomizer (1); and / or b) a second drive gas control valve (31; 42), in particular as a proportional valve, preferably pneumatically controlled, for controlling the flow of the drive gas through the second drive gas supply (26) to the second drive nozzle (23), the second drive gas control valve (31; 42) being preferably located outside the rotary atomizer (1); and / or c) a third driving gas control valve (32; 43), in particular as a proportional valve, preferably of the pneumatically controlled type, for controlling the flow of the driving gas to the third driving nozzle (24) through the third driving gas supply (32; 43), the third driving gas control valve (32; 43) being preferably located outside the rotary atomizer (1); Including, A turbine drive according to claim 1.

6. a) a bistable spring element (46) is disposed within at least one of said drive gas supplies, said bistable spring element (46) either opening or closing the respective drive gas supply depending on its state; b) the bistable spring element (46) is preferably connected to the damping gas supply (12) and changes its state when a pressure pulse occurs in the damping gas supply; A turbine drive according to claim 1.

7. a gas heater (7) for heating the drive gas and / or the brake gas upstream of the drive nozzle and / or upstream of the brake nozzle, said gas heater (7) being preferably arranged outside the rotary atomizer (1); A turbine drive according to claim 1.

8. a) the gas heater (7) heats only the driving gas in one of the driving gas supplies (5, 6), and the driving gas in one or more other driving gas supplies (5, 6) is not heated by the gas heater (7), or b) the gas heater (7) heats the drive gas in a plurality, preferably all, of the drive gas supply lines (5, 6); A turbine drive according to claim 7.

9. a) the gas heater (7) is arranged upstream of at least one of the driving gas control valves (9, 10), or b) the gas heater (7) is arranged downstream of at least one of the driving gas control valves (9, 10), in particular in a separate air chamber; A turbine drive according to claim 7.

10. a) the turbine drive has a turbine control device (34); b) the turbine controller (34) receives a load point at an input, the load point determining the speed and / or torque of the turbine drive; c) the turbine control device (34) controls the drive gas control valves (30-32) on the output side in response to the load point; A turbine drive according to claim 1.

11. The turbine control device (34) opens different numbers of the drive gas control valves (30-32) and closes the remaining drive gas control valves (30-32) depending on the load point. A turbine drive according to claim 10.

12. The turbine control device, in response to the load point, a) only the first motive gas control valve (30) is open and only the first motive nozzle emits the motive gas; b) only the second motive gas control valve (31) is open and only the second motive nozzle emits the motive gas; c) only the third motive gas control valve (32) is open and only the third motive nozzle emits the motive gas; d) only the first motive gas control valve (30) and the second motive gas control valve (31) are open, and only the first motive nozzle and the second motive nozzle emit the motive gas; e) only the first motive gas control valve (30) and the third motive gas control valve (32) are open, and only the first motive nozzle and the third motive nozzle emit the motive gas; f) only the second driving gas control valve (31) and the third driving gas control valve (32) are open, and only the second driving nozzle and the third driving nozzle emit the driving gas; g) all motive gas control valves (30-32) are open and all motive nozzles emit said motive gas; Set one of the following operating states: A turbine drive according to claim 10.

13. a) a plurality of drive gas shut-off valves (41-43) for individually opening or closing the respective drive gas flows independently of one another; b) a common driving gas proportional valve (44) for adjusting the sum of the flows of the individual driving gases, the driving gas proportional valve (44) being located upstream of the driving gas shut-off valves (41-43); Including, A turbine drive according to claim 1.

14. A rotary atomizer (1) with a turbine drive according to any one of claims 1 to 13.

15. 14. A method for operating a turbine drive of a rotary atomizer (1), in particular for a turbine drive according to any one of claims 1 to 13, comprising: a) discharging a first motive gas flow of motive gas from a first motive nozzle (3; 22) onto turbine blades (21) of a turbine wheel (19) of an atomizer turbine (14); b) discharging a second motive gas flow of said motive gas from a second motive nozzle (4; 23) onto said turbine blades (21) of said turbine wheel (19) of said atomizer turbine (14); Including, c) separately controlling said first driving gas flow independently of said second driving gas flow.

16. a) discharging a third motive gas flow of said motive gas from a third motive nozzle (24) onto said turbine blades (21) of said turbine wheel (19) of said atomizer turbine; b) independently controlling the third driving gas flow independently of the first driving gas flow and the second driving gas flow; Including, 16. The operating method according to claim 15.

17. a) determining a load point of the turbine drive, the load point determining the speed and / or torque of the turbine drive; b) adjusting the first and second driving gas flows, and optionally the third driving gas flow, in response to the load point; Including, 16. The operating method according to claim 15.

18. A different number of driving gas flows are switched depending on the load point.

18. The method of claim 17.

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