JP4927738B2 - Drive spindle - Google Patents

Description

Detailed Description of the Invention

  The present application relates to drive spindles, and in particular, to rotary atomizer drive spindles and further to rotary atomizers including such drive spindles. The present application further relates to a turbine rotor used in such a drive spindle.

A rotary atomizer is used to spray a substance into a fine particle. One application common to various rotary atomizers is spraying paint.
A rotary atomizer typically includes a supply path for supplying material from a source to a spray bell. The spray bell functions to disperse or atomize a substance from a supply source and to inject the dispersed or atomized substance toward an object. Since the spray bell is rotationally driven, a driving force must be supplied to the spray bell. In recent years, the demand for higher performance rotary atomizers has increased. Specifically, as a rotary sprayer used in the paint spraying industry, a rotary sprayer capable of spraying paint more quickly, that is, a larger paint so that more paint can be sprayed per minute. There is an increasing demand for nebulizers that provide throughput. Many of these rotary sprayers or paint sprayers are electrostatic devices, and a high voltage is applied between the device and an object to attract an atomized material such as paint to the object.

It is an object of the present invention to provide a rotary atomizer drive spindle, as well as a rotary atomizer, and components that provide good performance for the rotary atomizer.
Provided by one aspect of the present invention is a rotary atomizer drive spindle used as part of a rotary atomizer, the drive spindle comprising a shaft supporting a turbine and a body, with respect to the body And a main body having at least one supply passage for supplying gas to the turbine for rotationally driving the shaft.

  In some embodiments, the turbine includes a disk-shaped or ring-shaped rotor body portion and a plurality of blades that protrude from one of the generally flat surfaces of the rotor body portion and are paired by adjacent blades. A plurality of blades forming a generally radial gas passage through the turbine and at least one supply passage having a nozzle portion in use when gas flows from the spindle body toward the turbine, the nozzle comprising an outlet; The cross-sectional area of the gas passage through the nozzle portion decreases monotonically from the inlet to the outlet of the nozzle.

  The turbine may be a reaction turbine. In this specification, the term reaction turbine is used to refer to a turbine that generates at least a specific torque, ie, driving force, by gradually reducing the pressure of the gas from the inlet to the outlet of the turbine. By using a reaction turbine, the efficiency of the rotary atomizer with respect to the throughput of material passing through the rotary atomizer can generally be improved compared to using an impulse turbine. The impulse turbine is a turbine that generates a driving force by directly applying a jet of gas to a blade of the turbine.

  The turbine may include a plurality of blades, and a pair of adjacent blades may form a gas passage through the turbine. The at least one gas passage includes a first portion having a reduced cross-sectional area from the first end to the second end, the first end being the inlet of the turbine rather than the second end. The turbine may be configured to be close to

By reducing the cross-sectional area of the gas passage through the portion of the turbine, the turbine can function as a reaction turbine.
The at least one gas passage includes a second portion having a cross-sectional area that increases from a first end to a second end, the first end being the inlet of the turbine rather than the second end. The turbine may be configured to be close to The second portion may be further from the turbine inlet than the first portion.

The turbine may include a rotor body part and a plurality of blades provided in the rotor body part. The rotor body may be substantially disk-shaped or substantially ring-shaped.
Preferably, the blades have the same shape and dimensions. Preferably, the gas passages have the same shape and dimensions.

  Preferably, the face of the blade that faces each adjacent blade is curved in one improvement and substantially flat in the other improvement. By this curvature, a desired blade shape and a desired gas passage cross section can be obtained, and machining is facilitated by limiting the curvature to one improvement.

  In some embodiments, the blade may protrude from one of the generally flat surfaces of the generally disk-shaped or generally ring-shaped rotor body. In such a case, the faces of the facing blades may be curved in a substantially radial direction and substantially flat in a substantially axial direction.

The turbine blade may have a blade shape. As the gas flows around and between the blades, a driving force can be generated by the wing effect, or “lift”.
The turbine blade may be sized and shaped to maintain laminar flow under a wide range of different operating conditions.

  The turbine may include at least one surface feature that facilitates loss reduction. The surface features may comprise any one of recesses, openings, grooves, or any combination thereof that facilitates loss reduction. Generally, surface features are provided on non-functional surfaces in the turbine. The expression non-functional surface is used to refer to a surface where gas does not need to pass or should not pass through in generating driving force. In one example, each blade may be provided with a substantially axial opening or a stationary recess extending substantially in the axial direction. In another example, a circumferentially extending groove may be provided on the outer curved surface of the turbine. When surface features are obtained by removing turbine components, the additional advantage of reduced weight and / or moment of inertia can be obtained.

The turbine may be a turbine that receives a radial power supply.
The at least one supply path may comprise a nozzle portion through which gas flows from the main body of the spindle toward the turbine in use. The nozzle part may be provided with a throat. As used herein, the expression throat is used to refer to a relatively narrow portion of the nozzle passage between a relatively wide inlet end and a relatively wide outlet end of the nozzle.

  The cross-sectional area of the gas passage passing through the nozzle portion may be monotonously decreased toward the throat. Preferably, the cross-sectional area of the gas passage through the nozzle portion may be monotonously reduced from the nozzle inlet to the throat. The width of the nozzle may be monotonically reduced to provide the desired reduction in cross-sectional area.

  The passage through the nozzle may be partially formed with a suction surface and partially formed with a pressure surface. The suction surface is a surface where the pressure of the gas passing through the nozzle can be lowest, and the pressure surface is a surface where the pressure of the gas passing through the nozzle can be highest. The suction surface may be continuously curved.

  Preferably, a reduction in the nozzle cross-section is achieved while reducing one dimension of the nozzle passage while keeping the other dimension of the passage substantially constant. By achieving reduction in the nozzle cross section in this way, machining becomes easy.

The nozzle may extend along an arcuate path on a plane perpendicular to the spindle base axis.
Preferably, the nozzle outlet is configured to simultaneously supply gas to a plurality of gas passages through the turbine.

Preferably, there are a plurality of nozzles that supply gas to the turbine and thereby drive the turbine.
The spindle body may include a gas supply chamber formed to supply gas to one nozzle or each of a plurality of nozzles.

  The volume of the gas supply chamber may be selected to ensure that sufficient supply of gas is provided to the nozzle. The target operating temperature of the device is one factor that can affect the choice of gas supply chamber dimensions.

The depth of the gas supply chamber in the axial direction of the spindle may be different from the depth of one nozzle or each of the plurality of nozzles in the axial direction of the spindle.
The cross-sectional area of the nozzle may be selected to adjust the input to the turbine. The width and depth of the nozzles may be selected individually.

  The number of nozzles and the number of blades may be selected to provide the desired force and other desired characteristics. If there are multiple nozzles, the angular distances of these multiple nozzles may be selected to suit practical problems.

  The rear of the turbine may be used to support an indicator used in the speed detection system. This speed detection system may be, for example, an optical type or a magnetic type.

  The turbine may be arranged in either direction with respect to the spindle body. That is, the blade may be directed in the direction of the bearing or may be directed in the opposite direction of the bearing.

  The spindle body may include an exhaust system that includes at least one exhaust passage for exhausting gas from an outlet of the turbine. The exhaust system may include an exhaust collection chamber between the turbine outlet and the exhaust outlet. This exhaust collection chamber can contribute to slowing the exhaust gas and relieving the pressure in the gas passage from the spindle. Preferably, the exhaust system includes at least one exhaust collection passage for supplying exhaust from the turbine outlet to the exhaust collection chamber, and a plurality of exhaust outlet passages for letting exhaust gas flow out of the exhaust collection chamber. Good.

  The exhaust collection chamber may be provided at a position where the exhaust gas outlet direction must change. For example, the collection chamber may be configured to receive exhaust gas flowing substantially in the axial direction from one direction and exhaust exhaust gas flowing substantially in the axial direction from the opposite direction. The exhaust collection chamber may be provided by machining a member of the spindle body.

The exhaust system may be designed to suppress or prevent the generation of turbulence and / or back pressure to maximize the pressure drop before and after passing through the turbine.
The at least one exhaust passage may pass through the main body of the spindle at a location displaced in the radial direction from the gas supply chamber while being in the vicinity of the gas supply chamber. The at least one exhaust passage may pass through the gas supply chamber on the radially inner side of the gas supply chamber. By passing at least one exhaust passage through the gas supply chamber on the inner side in the radial direction of the gas supply chamber, a compact design is possible. As described above, an appropriate volume is ensured in the gas supply chamber by changing the axial depth of the gas supply chamber so that the axial depth of the gas supply chamber is larger than the axial depth of the nozzle. be able to.

The drive spindle may be an air bearing spindle. The main body may include an air bearing that rotatably supports the shaft therein.
The shape of one nozzle, or the shape of each nozzle, may be substantially determined by the coordinate values shown in Table 1.

The shape of one nozzle or the shape of each nozzle may be determined by each coordinate value within 0.01 difference with respect to the coordinate value shown in Table 1.
The shape of one blade, or the shape of each blade, may be substantially determined by the coordinate values shown in Table 2.

The shape of one blade or each blade may be determined by each coordinate value within 0.01 difference with respect to the coordinate values shown in Table 2.
The spindle body may include a body portion, a spacer ring, a turbine drive ring, and a rear cover. A portion of the nozzle may be formed by a turbine drive ring. A part of the gas supply chamber may be formed by a turbine drive ring. The spacer ring may function to block the nozzle boundary and / or the gas supply chamber boundary. The exhaust collection chamber may be formed by a recess provided in the main body. Another surface of the exhaust collection chamber may be formed by a spacer ring. The exhaust passage and the gas supply passage may be formed by appropriate openings provided in one or more of the main body portion, the spacer ring, the turbine drive ring, and the rear cover.

The tip clearance may be formed between the turbine blade and the spacer ring. This tip clearance can minimize the loss reduction due to leakage.
In some embodiments, multiple turbines may be provided. The plurality of turbines may be provided with the rear portions of each turbine facing each other, or may be provided with the rear portion of one turbine facing the front portion of the other turbine.

Preferably, the rotary sprayer is suitable for use as a paint sprayer.
Another aspect of the present invention provides a rotary atomizer, a drive spindle as defined above, and a conical curtain of small particles that can rotate about a base axis and flow generally toward an object. And a supply channel for supplying a substance capable of generating small particles from a storage source to the bell-shaped member.

  According to yet another aspect of the present invention, there is provided a rotary paint sprayer drive spindle comprising a shaft that supports a turbine and a body that supplies gas to the turbine and rotates the shaft relative to the body. And a main body having at least one supply path for driving.

  Provided by a further aspect of the present invention is an air bearing drive spindle of a rotary paint sprayer comprising a shaft supporting a turbine and a body for supplying gas to the turbine, the shaft being against the body. And a main body having at least one supply path for rotational driving.

  Provided by a further aspect of the invention is a turbine atomizer for a rotary atomizer drive spindle, the turbine rotor comprising a plurality of blades and gas passing through the turbine formed by a pair of adjacent blades The passage is formed such that the at least one gas passage comprises a first portion having a reduced cross-sectional area from the first end to the second end, the first end being a second end It is closer to the turbine inlet than the end.

Another aspect of the present invention provides a turbine rotor for a rotary atomizer drive spindle that is configured to function as a reaction turbine.
A rotary sprayer (eg, paint spray) drive spindle is sometimes assembled to the robot arm. If the orientation of the drive spindle changes and the shaft is rotating at high speed, the shaft will receive a gyro force. This gyro force can be very relevant to the rigidity of the shaft attached to the spindle body. In particular, when an air bearing is used, the couple (rotation moment) acting on the shaft due to the gyro action may exceed the couple that the bearing can withstand. The couple acting on the shaft can exceed the couple that the air bearing can withstand, causing the shaft to tilt within the bearing to contact the bearing member and / or another part of the spindle body. A spindle failure can occur. This factor can in fact be a limiting factor as to how fast (including such a drive spindle) the angle of rotation of the spray head can be changed to perform the desired spray operation. Similarly, this factor can limit the speed at which the shaft can rotate if the spray head needs to be rotated again at a determined rotational speed.

In the development process of the present invention, the structure of the spindle is set to alleviate this problem.
In at least some cases, the structure of these spindles may improve spindle power and allow the shaft to be driven at higher speeds. By allowing the shaft to be driven at higher speeds, additional problems may arise due to the higher heat generated in the spindle. In another development process of the invention, the spindle structure is set to alleviate this problem.

The main body of the spindle may comprise two radial bearings spaced apart from each other. Each radial bearing may comprise an air bearing.
The turbine may be disposed between spaced radial bearings. The shaft may support two turbines disposed between spaced radial bearings. The turbine may be set in an arrangement in which the rear portions of the turbine face each other so that the blades on one bearing face away from the blades on the other bearing.

  Each turbine may be supplied with drive gas by two nozzles. You may provide four nozzles which consist of two nozzles which supply gas to a 1st turbine, and two nozzles which supply gas to a 2nd turbine. The main body of the spindle is configured to supply a first gas supply passage for supplying a driving gas to a first nozzle arranged to supply a gas to the first turbine, and to supply a gas to the second turbine. You may provide the 1st nozzle arrange | positioned. The main body of the spindle is adapted to supply a gas to the second turbine and a second gas supply path for supplying a driving gas to a second nozzle arranged to supply gas to the first turbine. You may provide the 2nd nozzle arrange | positioned. The first gas supply path and / or the second gas supply path may continuously communicate with each nozzle from the outside of the spindle. Instead of supplying the gas directly from the gas supply path to the nozzle, an arrangement without a gas supply chamber set to supply gas to the nozzle may be used.

  The exhaust system may be arranged to cool the spindle with the exhaust gas flowing out. If there are two spaced radial bearings, the exhaust system may be arranged to cool both radial bearings with the exhaust gas flowing out.

At least one portion of the at least one exhaust path may pass in the vicinity of each radial bearing.
The exhaust system may comprise two exhaust collection chambers. The first collection chamber may be provided in the vicinity of the first radial bearing. The second collection chamber may be provided in the vicinity of the second radial bearing. Each collection chamber may be provided in a region toward one end of each radial bearing.

The exhaust system may include a first exhaust collection path for supplying exhaust from the outlet of the first turbine to the first collection chamber.
The exhaust system may include a second exhaust collection path for supplying exhaust from the outlet of the second turbine to the second collection chamber.

There may be a plurality of common exhaust outlet channels arranged so that the exhaust can flow out of both collection chambers.
The two turbines may be arranged such that the exhaust exiting from one turbine moves in approximately the opposite direction of the exhaust exiting from the other turbine.

  The two bearings may be rigidly attached to the rest of the spindle body. Tightening the bearing is in contrast to attaching the bearing to, for example, a soft O-ring of the spindle body, resulting in an elastic mount.

  The spindle body may include all of the first body part, the first spacer ring, at least one turbine drive ring, the second spacer ring, the second body part, and the cover part. These small bonds may be provided.

  The turbine drive ring may form at least a portion of a nozzle arranged to supply gas to the first turbine and the second turbine. Each spacer ring may function to block the nozzle boundary. The first exhaust collection chamber may be formed by a recess provided in the first main body. The second exhaust collection chamber may be formed by a recess provided in the second main body. Another surface of the collection chamber may be formed by each spacer ring. The exhaust passage and the air supply passage are provided in one or a plurality of the first main body portion, the second main body portion, the first spacer ring, the second spacer ring, the turbine drive ring, and the cover portion. It may be formed by a suitable opening.

  The spindle may be at least partially aluminum and leaded gunmetal. Since at least a part of the spindle is made of aluminum and leaded gunmetal, it is possible to ensure good thermal conductivity from the bearing surface to the boundary of the collection chamber.

  Another aspect of the present invention provides a shaft that supports a turbine and a main body, the main body comprising at least one supply path for supplying gas to the turbine to rotationally drive the shaft relative to the main body. A rotary sprayer drive spindle with a body having a bearing, the body being two bearings, the shaft being pivotally supported therein, the two bearings being spaced apart from each other, and a turbine disposed between the two bearings. Two exhaust bearing chambers are provided, and an exhaust system having two exhaust collecting chambers is provided. The two exhaust collecting chambers are arranged in the vicinity of the respective bearings.

Embodiments of the present invention will now be described by way of example only with reference to the accompanying drawings.
FIG. 1 shows a rotary sprayer in the form of a paint sprayer, which comprises a drive spindle 1 for rotationally driving a paint spray bell 2. Further, the paint sprayer shown in FIG. 1 includes a supply path 3 for supplying a substance, that is, paint, from the storage chamber 4 to the bell 2. Can be injected. As is common in such paint sprayers, paint is sprayed towards the surface to be painted by electrostatic forces generated by a high voltage applied between the spindle 1 and the surface to be painted.

  The structure and operation of the paint sprayer at this stage is conventional and such paint sprayers are widely used and well understood in the field. Therefore, since various forms of the paint spraying bell and the supply path 3 will be apparent and well known to those skilled in the art, further description of the paint spraying bell and the supply path 3 is omitted for the sake of simplicity. The drive spindle 1 relevant to the present invention is taken up.

The details of the drive spindle 1 will be described with reference to FIGS.
FIG. 2 is a cross section of the drive spindle 1 showing the main components of the drive spindle 1. At the most overall level, the drive spindle 1 includes a spindle body 101 that is stationary during normal use, and a shaft 102 that is rotatably supported in the spindle body 101.

  The spindle body 101 itself includes a plurality of parts. First, there is a main body 103 that houses an air bearing 103a that supports a shaft 102 therein. A spacer ring 104, a turbine drive ring 105, and a rear cover 106 are assembled to the main body 103.

    3A, 3B, and 3C show details with the main body 103 separated. 4 shows details of the spacer ring 104, FIG. 5 shows details of the turbine drive ring 105, and FIG. 6 shows details of the rear cover 106. The shaft 102 is shown separately in FIG.

  As shown in FIG. 2, the shaft 102 supports the turbine 107 when assembled to a drive spindle. Further, the turbine 107 has an assembly relationship shown in FIG. 5 with respect to the turbine drive ring 105.

  Generally speaking, the drive spindle 1 is operated by air supplied to the turbine 107. That is, the turbine 107 serves to drive the shaft 102 so that the rotary sprayer, more specifically, the paint spraying bell 2 can be driven. Of course, the use of a turbine as a rotational drive source itself is not novel. However, the drive spindle 1 of the present application includes various features, which are considered to be novel at the present time, and exhibit advantageous effects.

  The turbine 107 is a radial flow turbine. The turbine 107 includes a substantially ring-shaped rotor body 1071, and a plurality of substantially blade-shaped blades 1072 are provided on the rotor body 1071. These blades 1072 protrude from one of the non-curved surfaces of the ring-shaped rotor body 1071. A gas passage 1073 through the turbine 107 is formed by each pair of adjacent blades. The turbine is designed as a reaction turbine, not an impulse turbine. That is, at least some driving force is obtained by sequentially extracting energy from the gas flow through the gas passage 1073 rather than simply by the impact of a jet of air impinging on the blade surface. In order to obtain the effect of sequentially extracting energy from the gas stream, the blade is carefully shaped.

  The drive spindle is configured to supply air from the turbine drive ring 105 to the outer periphery of the turbine 107 and to discharge air from the inner periphery of the turbine 107 of the ring-shaped turbine. As seen in FIG. 5, the width of each gas passage 1073 is larger on the inlet side (that is, the outer peripheral side) of the turbine than the intermediate point of the gas passage passing through the turbine. Further, the width of the gas passage 1073 at the outlet side of the turbine is also larger than the width at the intermediate point of the gas passage 1073, but not as large as the width at the inlet side of the gas passage 1073.

  As shown in FIG. 5, the wall of the blade 1072 in the outer direction of the page is substantially straight. That is, the blade has a uniform cross section in the axial direction of the drive spindle 1. The blades having a uniform cross section in the axial direction of the drive spindle 1 make the machining of the blade 1072 easier and any change in the cross-sectional area of the gas passage 1073 through the turbine 107 is Will be achieved by the shape of the blade in a plane substantially perpendicular to one axis. As described above, each of the blades 1072 has an airfoil shape. Also noteworthy is that the wing shape is asymmetric. Since the blade shape is asymmetric, a desired driving effect and a desired shape of the gas passage 1073 can be achieved.

  Air is supplied to the turbine 107 via an air supply path formed by the opening 1061 of the rear cover 106 and the opening 1051 of the turbine drive ring 105. This air supply path enters the gas supply chamber 1052, and then the gas supply chamber 1052 is fluidly connected to the two drive nozzles 1053. Each nozzle 1053 is formed to follow the passage in a plane substantially perpendicular to the spindle axis. Each nozzle 1053 is transverse to the spindle axis. The passage followed by the nozzle 1053 is arcuate. The nozzle 1053 can be regarded as being spiral toward the axial direction of the spindle. The drive nozzle 1053 is carefully shaped and is sized to supply air to the turbine 107 to provide the desired drive characteristics. In this embodiment, the nozzle 1053 is formed in a plane substantially perpendicular to the axis of the drive spindle 1, and the side wall of the nozzle 1053 is substantially straight in a direction parallel to the axis of the drive spindle 1. It has become. Therefore, the cross-sectional area of the nozzle 1053 in the axial direction is uniform. The nozzle 1053 includes an inlet where the nozzle 1053 reaches the gas supply chamber 1052, and an outlet where the nozzle 1053 reaches the inner wall of the turbine drive ring 105 and supplies gas to the turbine 107. A throat is formed between the inlet and the outlet, and the throat is a portion where the nozzle 1053 is the narrowest. The throat is located on one side of the outlet, and after passing the throat, one side wall of the nozzle 1053 ends, and the nozzle 1053 is integrated with a space surrounding the turbine. Each of the nozzles 1053 is formed such that the width (that is, the cross-sectional area) of the nozzle 1053 monotonously decreases between the inlet and the throat. Since the nozzle 1053 is integrated with the space surrounding the turbine, the gas passage through the nozzle 1053 actually continues to monotonously decrease in cross section until it reaches the outlet. The outlet of each nozzle 1053 is formed so as to supply gas to a plurality of blades 1072 / gas passages 1073 simultaneously. In this case, gas is most usefully supplied to two of these blades 1072 while being constantly supplied by each nozzle to each of the four or five sets of blades.

  It can be considered to provide the nozzle with a suction surface and a pressure surface. The suction surface is the surface where the gas pressure at the nozzle is lowest when in use, and the pressure surface is the surface within the nozzle where the gas pressure is highest. In the nozzle shape illustrated in the present embodiment, the suction surface is the outermost surface in the radial direction of the nozzle 1053. Another feature of this nozzle design is that this radially outer surface has a continuous curvature without having any straight portions.

Features such as monotonically decreasing width (cross-sectional area) and continuous curvature are important to achieve the most efficient turbine operation.
Considering FIG. 2, it can be seen that the ring-shaped turbine 107 is arranged so that the blades 1072 face the opposite direction of the rear cover 106. In FIG. 2, the front of the portion of the blade 1072 can be seen. The portion that can be seen from the front is a portion on the inner periphery of the ring-shaped turbine rotor 107.

  As described above, in operation, gas, typically air, passes through the turbine 107 in a generally radially inward direction, so the exhaust must be exhausted from the central region of the turbine 107. An exhaust passage for exhausting the exhaust from the central region of the turbine 107 is formed by each of the spacer ring 104, the turbine drive ring 105, and the exhaust openings 1041, 1054, 1062 in the rear cover 106. The exhaust collection chamber 1031 is formed by a recess machined in the main body 103 of the drive spindle 1. The range of the exhaust collection chamber 1031 can be most clearly recognized in FIG. 3B. Here, it can be seen that the region covering almost the entire available end face of the main body 103 is rolled outward to form the exhaust collection chamber 1031. The only exception to the formation of the exhaust collection chamber 1031 in this way is a series of columns 1032 that protrude upward from the base of the exhaust collection chamber, and further provide a fixed member and an air supply path to the air bearing 103a. It is to obtain the land 1033 including.

  By providing the exhaust collection chamber 1031, the air exhausted from the turbine can change direction and be decelerated before it flows out of the drive spindle 1 via the rear cover 106. Furthermore, this large exhaust collection chamber allows the exhaust outlet formed to be utilized to the maximum extent possible. All exhausts from the turbine (to the extent practical) are directed to this exhaust collection chamber 1031 and all exhaust outlet channels are connected to this common exhaust collection chamber 1031.

  Here, returning to FIG. 5, it can be noted that the two openings 1054 forming the portions of the respective exhaust outlet passages are provided on the radially inner side of the gas supply chamber 1052. Providing the two openings 1054 at this position contributes to the maximum use of the exhaust path exiting from the spindle, but limits the space that the gas supply chamber 1052 can occupy. For this measure, in this embodiment, the depth of the gas supply chamber 1052 in the axial direction is larger than the depth of the nozzle 1053 in the axial direction. Since the axial depth of the gas supply chamber 1052 is larger than the depth of the nozzle 1053 in the axial direction, the gas supply chamber 1052 has a volume necessary for supplying gas to the turbine via the nozzle 1053. It can be secured. The exact volume of gas supply chamber 1052 required for different applications will vary based on many factors including operating temperature, and this fact will change the depth of gas supply chamber 1052 in the axial direction. Can be considered. Changing the depth of the gas supply chamber 1052 in the axial direction provides a particularly efficient way to change the shape of the turbine drive ring 105.

  Note that a further gas supply nozzle 1055 is provided in the turbine drive ring 105. The supply nozzle 1055 supplies gas in the circumferential direction opposite to the gas supply direction of the two drive nozzles 1053, and brakes the turbine and further the shaft, that is, reduces the rotational speed of the turbine and further the shaft. Used to make

  As described above, the direction of the turbine 107 is set so that the blade 1072 faces the opposite direction of the rear cover 106. That is, the rear portion of the turbine rotor body 1071 faces the rear cover 105, and the rear portion of the turbine rotor body 1071 can be a useful surface for use in the speed detection system. Specifically, an optical indicator, a magnetic indicator, or other indicator can be attached to the rear of the turbine rotor body 1071, and these indicators are suitable sensors (see FIG. (Not shown). If such a function is not required or if such a function is obtained in a different way, it is possible to assemble the turbine 107 with the turbine 107 in the reverse direction, that is, with the blade 1072 facing the rear cover 106. It is. When the turbine 107 is assembled in the opposite direction, the exhaust path can be simplified.

  In another alternative, multiple turbines 107 may be provided to drive the shaft 102. When a plurality of turbines 107 are provided, these turbines 107 may be arranged with their rear portions facing each other with the blades 1072 facing in opposite directions, or the blades 1072 of one turbine may be disposed. You may arrange | position with the front part of one turbine facing the rear part of the other turbine in the state which faced the rear part of the other turbine.

Here, details of the shapes of the turbine 107 and the turbine drive ring 105 will be described with reference to FIGS.
FIG. 8 illustrates one turbine blade 1072 in the turbine 107, the structure around the turbine drive ring 105, and the spacer ring 104. Also shown in FIG. 8 are various parameters that help explain the setting of the turbine 107 in the spindle 1. R1 is a radius from the rotation center of the shaft 102 to the outermost point of the nozzle 1053. R2 is the inner radius of the nozzle 1053. R3 is the outer radius of the blade 1072. R4 is the inner radius of the blade 1072. In any case, these radii are based on the rotation center of the shaft 102. h is the height of the nozzle, that is, the depth of the nozzle 1053 in the axial direction of the spindle 1, and tc is a tip clearance that is a space between the free plane of the blade 1072 and the facing surface of the spacer ring 104.

  In the sample of the spindle manufactured by the applicant, R1 = 36 mm, R2 = 27.69 mm, R3 = 27.5 mm or a size slightly less than 27.5 mm, R4 = 22 mm, h = 2 mm, tc = 0 .2 mm.

  All of these dimensions can affect the characteristics of the turbine, and tip clearance is particularly important to achieve good efficiency when there is another simple leak path that bypasses the blades.

  FIG. 9A shows the coordinate points of the radially outer surface of nozzle 1053 (ie, suction surface ss) and the radially inner surface of nozzle 1053 (ie, pressure surface ps) in a sample device manufactured by the applicant. . Further, Table 1 below shows the values of the coordinate points of ps and ss plotted in the graph shown in FIG. 9A. The rotation axis of the shaft 102 is always the origin (0, 0) of this coordinate system.

  In the case of a sample spindle manufactured by the applicant, the size of the device is such that one coordinate point corresponds to 1 millimeter. However, it will be appreciated that the actual size of the device may change and the shape is maintained by scaling the coordinates. FIG. 9B shows an alternative end for the pressure surface ps.

  FIG. 10 shows a graph of coordinates resulting in one shape of blade 1072 in a sample turbine manufactured by the applicant. Also in this case, the rotation axis of the shaft 102 is located at the origin (0, 0). Furthermore, Table 2 below shows the coordinate points of the pressure surface (ps) and suction surface (ss) of the blade plotted in FIG. In the apparatus manufactured by the present applicant, one coordinate point represents one millimeter, but in this case, the size represented by one coordinate point can be enlarged and reduced as desired.

  Although nozzles 1053 and blades 1072 having the size and shape determined by the coordinates shown in Tables 1 and 2 give particularly good results, it is understood that some or all of these coordinates are very small. Even if it changes, it is possible to produce devices with similar effects.

  11A and 11B show another form of the turbine rotor. Also in this case, the blade-shaped blade 172 is provided on the ring-shaped rotor body 171. However, in this turbine 107, holes 1074 are passed through each of the blades 1072 substantially in the axial direction, and a wide groove 1075 is machined on the outer peripheral surface of the rotor body 1071. In either case, the holes 1074 are penetrated and the wide groove 1075 is machined to form an additional end through which the air must exit when it exits the desired passage through the turbine. . Thus, when air flows out on the free plane of the blade 1072, the air must pass through the end of each hole 1074. If the air flows out through the outer peripheral surface of the turbine without passing between the blades, the air must pass through the groove 1075.

  In general, providing surface features such as holes 1074 and wide grooves 1075 on non-utilizing surfaces of the turbine contributes to loss reduction. This is due to the fact that the introduction of edges or boundaries increases the resistance to air flow, so that these features can interfere with the outflow of air.

  In this alternative embodiment, these two features have the effect of reducing the weight of the turbine 107 and the polar moment of inertia of the turbine 107. These two factors can reduce undesirable mechanical effects such as gyro reaction and can contribute to reducing acceleration time when the turbine 107 is rotated at the expected speed.

Another surface feature may add a similar effect. For example, instead of providing a shaft hole penetrating the entire turbine 107, a blind hole may be drilled in the flat free surface of the blade 1072.
In this embodiment, the drive spindle is provided with two drive nozzles, but a different number of drive nozzles may be used to obtain the desired output or other desired characteristics. Further, the turbine may be provided with a different number of blades, and the height of the blades in a generally axial direction may be varied to obtain different outputs. Further, the depth of the nozzle 1053 in the substantially axial direction and the width of the nozzle 1053 may be changed to control the output.

  A practical device manufactured according to the above specifications provides a 30% reduction in driving airflow and drives the turbine at the same speed as another device that did not have the nozzle, turbine shape and dimensions described above. It has been found that the air pressure required for this is also reduced.

  Described below with reference to FIGS. 12-18 is another rotary sprayer drive spindle 1 that can be used in a rotary sprayer of the type shown in FIG. 1 instead of the drive spindle described above.

  Many of the components in the other drive spindles shown in FIGS. 12-18 are the same or similar to the components in the drive spindle described above. Thus, for the sake of clarity, the same reference numerals are used to represent corresponding parts in the other drive spindles shown in FIGS. 12-18, and for simplicity, some of the drive spindles shown in FIGS. Detailed description of the components is omitted.

  Perhaps the majority is easily seen in FIG. 15, but in another drive spindle, in this case a shaft 102 with two turbines 107 is assembled. The turbine 107 is assembled so that the rear portions thereof face each other so that the blade 1072 of one turbine faces the opposite direction of the other blade 1072.

  Apart from the fact that there are two turbines 107 assembled on the shaft 102 facing each other rearwardly, each turbine 107 is substantially the same as the turbine 107 described above with respect to FIGS. 1-10 or shown in FIGS. 11A and 11B. It is almost the same as the modified example. Therefore, a detailed description of the structure, shape, and dimensions of the turbine 107 in this drive spindle is omitted.

  The present drive spindle further comprises a front body 103 that corresponds very directly to the main body 103 of the drive spindle described above with reference to FIGS. However, the drive spindle also includes a rear body portion 103 ′ that is at least in some sense similar to the front body portion 103.

  The drive spindle includes a turbine drive ring 105 similar to the turbine drive ring of the drive spindle described above with respect to FIGS. However, since there are two turbines 107 in the main drive spindle, the turbine drive ring 105 in the main drive spindle is formed so as to supply air to both turbines 107. The drive spindle has two spacer rings 104 disposed on each side of the turbine drive ring 105. The two spacer rings 104 are similar to each other and similar to the drive spindle spacer ring 104 described above with respect to FIGS.

  The drive spindle also includes a rear cover 106 that is similar to the rear cover of the drive spindle described above with respect to FIGS. In this particular embodiment, a speed ring 108 used in the shaft speed monitoring system is also provided on the spindle.

  As shown in FIGS. 13 and 14, in the assembled spindle, the shaft is supported in two radial air bearings 103a (in the front body 103) and 103′a (in the rear body 103 ′). ing. These air bearings 103a and 103'a are separated from each other. A twin turbine 107 is disposed between the spaced air bearings 103a, 103'a. Furthermore, the separated air bearings 103a, 103'a are separated from each other by a practical distance within the overall dimensions of the spindle. The fact that the air bearings 103a, 103′a are separated from each other by a practical distance within the overall dimensions of the spindle means that the shaft 102 is a “hard” spindle that can counter a relatively large rotational moment acting on the shaft 102. Contribute to bringing

  In the assembled state, the twin turbine 107 is positioned at a predetermined position by the spacer ring 104 so as to coincide with the turbine drive ring 105. On one side of the spacer ring 104 is a front body portion 103 and on the opposite side of the other spacer ring 104 is a rear body portion 103 ′. There is a rear cover portion 106 on the opposite side of the rear body portion 103 ′ from the side facing each spacer ring 104.

  This driving spindle has two turbine gas supply paths F that are provided in the main body of the spindle 4 and supply gas to the turbine 107. One of these gas supply paths F can be referred to in FIG. 13, and the inlet to both of these gas supply paths F can be referred to in FIG. The supply path F is formed by appropriate openings 1061, 1034 ', 1051 provided in the rear cover 106, the rear main body 103', and the turbine drive ring 105, respectively.

  Similarly, a plurality of turbine gas exhaust passages E, in this case four turbine gas exhaust passages E, are provided in the spindle body. One of these exhaust paths E can be referred to in FIG. 14, and the outlets of the four exhaust paths E can be referred to in FIG.

  Again, these exhaust passages E are formed by appropriate openings 1062, 1035 ', 1041, 1054 provided in the rear cover 106, the rear body 103', the spacer ring 104, and the turbine drive ring 105, respectively.

  As briefly shown in FIG. 16, the front body 103 includes an exhaust collection chamber 1031 similar to the exhaust collection chamber of the body 103 in the drive spindle described above with respect to FIGS. However, in the present drive spindle, as shown in FIG. 17, the rear main body portion 103 ′ also includes an exhaust collection chamber 1031 ′. As in the case of the exhaust collection chamber 1031 in the front main body 103, the exhaust collection chamber 1031 'in the rear main body 103' is formed by rolling most of the members in the rear main body 103 '.

  Both of these exhaust collection chambers 1031 and 1031 ′ perform the same function as the function of receiving exhaust gas when exhaust gas (generally air) flows out of each turbine 107. In practice, the exhaust collection chamber 1031 in the front main body 103 receives exhaust gas from the turbine 107 in the vicinity of the front main body 103, and similarly, the exhaust collection chamber 1031 'in the rear main body 103 ′ is the rear main body 103 ′. Accepts exhaust from nearby turbine 107. However, in the exhaust collection chamber 1031 ′ of the rear body portion 103 ′, the exhaust from both turbines 107 can also be mixed or mixed before flowing out through any one of the exhaust passages E.

  The provision of these exhaust collection chambers 1031, 1031 ′ not only contributes to improving the efficiency of the entire spindle (by minimizing any throttle effect of the turbine 107), but also the air bearing 103a. , 103a 'contributes to providing a cooling effect. For example, as shown in FIGS. 14, 16, and 17, the bearings 103 a and 103 a ′ are located near the exhaust collection chambers 1031 and 1031 ′. The cooling function is particularly important for spindles that are configured to operate with a shaft that rotates at a rotational speed high enough to heat the bearing. Furthermore, because of the high efficiency characteristics of the turbine used in the present drive spindle, the turbine drive gas expands significantly as it exits the turbine 107, thereby rapidly cooling. In some embodiments, the turbine drive gas supplied at room temperature can be cooled to near zero degrees Celsius. Therefore, a significant cooling effect can be obtained by circulating the exhaust gas in the vicinity of the air bearings 103a and 103a '.

  In order to enhance this cooling effect, the spindle or at least the portions near the exhaust collection chambers 1031 and 1031 ′ of the spindle are made of aluminum and leaded gunmetal, and the interior of the exhaust collection chambers 1031 and 1031 ′ is excellent from the bearing surface. Thermal conductivity can be secured.

  It should be noted that the air bearings 103a and 103a 'are firmly assembled to the remaining part of the spindle, that is, the front main body 103 and the rear main body 103a'. That is, this assembly does not provide an elastic assembly by providing, for example, an O-ring for assembling the air bearing inside.

  It will be noted that due to the direction of the turbine 107 and the surrounding structure of the turbine 107, the exhaust gas flowing out of one turbine 107 flows in a direction substantially opposite to the direction in which the exhaust gas flows out of the other turbine 107. Therefore, the gas flowing out from the turbine 107 closest to the front main body 103 must change its direction in the vicinity of the collection chamber 1031 in the front main body 103. On the other hand, the gas flowing out of the turbine 107 closest to the rear body portion 103 ′ can flow out of the spindle without changing its direction.

  FIG. 18 shows details of the turbine drive ring 105 in the present drive spindle. The drive ring 105 forms four drive nozzles 1053, each of which is designed similar to any of the drive nozzles 1053 in the drive ring 105 of the drive spindle described above with respect to FIGS. . Two of these drive nozzles 1053 are formed to supply drive gas to one turbine 107, and the remaining two drive nozzles 1053 are formed to supply drive gas to the other turbine 107. Yes. Thus, the drive nozzles 1053 can be considered to be formed in pairs to supply drive gas to the opposite portion of each turbine. A nozzle that supplies gas to one turbine 107 is machined on one side of the turbine drive ring 105, and a nozzle 1053 that supplies gas to the other turbine 107 is machined on the opposite side of the turbine drive ring 105. Yes.

  In this embodiment, the turbine supply path F is formed to supply the drive gas directly to the nozzle 1053, and therefore, this drive spindle is provided with the gas provided in the spindle described above with reference to FIGS. There is no supply room. Providing such a gas supply chamber 1052 has been considered to be important for smoothly driving the turbine and, for example, changing the pressure of the supplied gas. Surprisingly, however, it has been found that smooth drive can be achieved even without such a gas supply chamber. The smooth drive that can be achieved without the gas supply chamber is probably that there is a sufficient volume of gas in the turbine supply path F itself to provide the required cooling effect. The elimination of the gas supply chamber (in at least some embodiments) provides the advantage that a larger space can be secured in the spindle body to provide an exhaust outlet. Accordingly, the spindle described above with respect to FIGS. 1-11B was provided with two exhaust outlets, whereas the drive spindle is provided with four exhaust outlets.

  It should be noted that one turbine supply path F supplies drive gas to two of the circularly arranged nozzles 1053, while the other turbine supply path F has a circularly arranged nozzle. The other pair of 1053 is to supply gas. Accordingly, each turbine supply path F supplies gas to drive both turbines 107.

  When assembling such a drive spindle for use in a rotary sprayer (specifically a paint sprayer), two separate air supply sources are connected to the inlet of the supply path F using a flexible supply tube. .

  As described above in the introduction herein, providing a spindle in which the shaft 102 is relatively rigidly assembled to the rest of the spindle means, for example, that high speed rotation of a spray head including the spindle There is an advantage that a large gyro force that causes a large rotational moment to act on the shaft can be generated. If the spindle, i.e., the bearing structure, does not have sufficient strength to prevent the shaft 102 from tilting with respect to the bearing to such an extent that the shaft 102 contacts the bearing member, such a large gyro force can cause failure. Can be invited.

1 shows a rotary sprayer in the form of a paint sprayer. 2 shows a section through the drive spindle of the rotary atomizer shown in FIG. It is a perspective view of the main-body part in the drive spindle shown by FIG. It is a top view of the main-body part shown by FIG. 3A. 3C is a cross-sectional view taken along line IIIC-IIIC in the main body shown in FIG. 3B. FIG. 3 is a cross-sectional view of a spacer ring in the drive spindle shown in FIG. 2. FIG. 3 is a plan view of a turbine drive ring and a turbine in the drive spindle shown in FIG. 2. FIG. 3 is a perspective view of a rear cover in the drive spindle shown in FIG. 2. FIG. 3 is a sectional view of a shaft of the drive spindle shown in FIG. 2. FIG. 6 is a schematic diagram useful for determining various dimensional measurements in the turbine and turbine drive ring shown in FIG. 5. 6 more accurately illustrates the shape of the gas supply nozzle in the turbine drive ring shown in FIG. 6 more accurately illustrates the shape of the blades in the turbine shown in FIG. Each is a plan view and a perspective view of another turbine rotor. FIG. 2 shows an end view of another rotary atomizer drive spindle that can be used with a rotary atomizer of the type shown in FIG. 1. FIG. 12 shows a cross-sectional view along line XIII-XIII in the drive spindle shown in FIG. 12, which shows the turbine drive air supply path in the drive spindle. FIG. 12 is a sectional view taken along line XIV-XIV in the drive spindle shown in FIG. 12, and this sectional view shows a part of the exhaust system in the drive spindle. FIG. 13 shows an exploded view of the main components of the drive spindle shown in FIG. 12. FIG. 13 is a three-dimensional view of the lower surface of the front main body portion of the drive spindle shown in FIG. 12. FIG. 13 is a bottom view of a rear main body portion of the drive spindle shown in FIG. 12. 13 shows a turbine drive ring in the drive spindle shown in FIG.

Claims (44)

A rotary sprayer drive spindle used as a part of the rotary sprayer,
The drive spindle is
A shaft that supports the turbine;
A main body comprising at least one supply passage for supplying gas to the turbine for rotationally driving the shaft relative to the main body ;
The turbine is
A disk-shaped or ring-shaped rotor body,
A plurality of blades formed by pairs of adjacent blades having a substantially radial gas passage through the turbine and projecting from one of the substantially flat surfaces of the rotor body;
With
The at least one supply path includes a nozzle portion that, in use, allows gas to flow from the body of the spindle toward the turbine;
The nozzle portion includes an outlet,
The rotary sprayer drive spindle according to claim 1, wherein a cross-sectional area of the gas passage passing through the nozzle portion monotonously decreases from an inlet to an outlet of the nozzle portion . A rotary atomizer drive spindle according to claim 1,
The rotary sprayer-driven spindle, wherein the at least one supply path includes a nozzle portion that, when used, allows gas to flow from the main body of the spindle toward the turbine. A rotary atomizer drive spindle according to claim 2 ,
The nozzle unit includes a throat. A rotary sprayer drive spindle. A rotary atomizer drive spindle according to claim 3 ,
A rotary sprayer drive spindle, wherein a cross-sectional area of a gas passage passing through the nozzle portion monotonously decreases toward the throat. A rotary atomizer drive spindle according to claim 4 ,
The rotary sprayer drive spindle according to claim 1, wherein the cross-sectional area of the gas passage passing through the nozzle portion monotonously decreases from the inlet of the nozzle portion to the throat. A rotary atomizer drive spindle according to any one of claims 1 to 5,
The gas passage passing through the nozzle part is partly formed by a suction surface, partly by a pressure surface,
The suction surface of the rotary sprayer is characterized in that the suction surface has a continuous curvature. A rotary atomizer drive spindle according to any one of claims 1 to 6,
It reduced small in the cross-sectional area of the gas passage through the nozzle portion, while reducing small one dimension of the gas passage is achieved by fastening a substantially constant remaining dimensions of the gas passage A rotary atomizer drive spindle characterized by that. A rotary atomizer drive spindle according to any one of claims 1 to 7,
The rotary sprayer drive spindle, wherein the nozzle portion continues in an arcuate path in a plane perpendicular to the spindle main axis. A rotary atomizer drive spindle according to any one of claims 1 to 8,
The rotary sprayer drive spindle is characterized in that the outlet of the nozzle portion is formed so as to simultaneously feed gas into a plurality of gas passages passing through the turbine. A rotary sprayer drive spindle according to any one of claims 1 to 9 ,
The rotary sprayer drive spindle, wherein the turbine is a reaction turbine. A rotary sprayer drive spindle according to any one of claims 1 to 10 ,
The turbine comprises a plurality of blades having gas passages through the turbine formed by pairs of adjacent blades. A rotary atomizer drive spindle. A rotary atomizer drive spindle according to claim 11 ,
The turbine is formed such that at least one gas passage comprises a first portion having a reduced cross-sectional area from a first end to a second end;
The rotary sprayer-driven spindle, wherein the first end is closer to the turbine inlet than the second end. A rotary atomizer drive spindle according to claim 11 or claim 12 ,
The turbine is formed such that the at least one gas passage includes a second portion that increases in cross-sectional area from a first end to a second end;
The rotary sprayer-driven spindle, wherein the first end is closer to the turbine inlet than the second end. A rotary atomizer drive spindle according to claim 13 when dependent on claim 12 , comprising:
The rotary sprayer-driven spindle, wherein the second part is further from the turbine inlet than the first part. A rotary atomizer drive spindle according to any one of claims 11 to 14,
A rotary atomizer drive spindle characterized in that the face of the blade facing each of the adjacent blades is curved on one improvement and substantially flat on the other improvement. A rotary atomizer drive spindle according to claim 15 ,
The blades protrude from one of the substantially flat surfaces of the substantially disk-shaped or ring-shaped rotor body, and the opposing surfaces between the blades are curved in a substantially radial direction and are substantially axially upward. A rotary atomizer drive spindle, characterized in that it is substantially flat. A rotary atomizer drive spindle according to any one of claims 11 to 16,
The turbine blade has a blade shape. A rotary sprayer drive spindle, wherein: A rotary atomizer drive spindle according to any one of claims 11 to 17,
The turbine blade has an asymmetric shape. A rotary atomizer drive spindle, wherein: A rotary atomizer drive spindle according to any one of claims 11 to 18,
The rotary atomizer drive spindle, wherein the turbine blade is sized and shaped to maintain laminar flow under a wide range of different operating conditions. A rotary atomizer drive spindle according to any of claims 1 to 19 ,
The turbine is provided with at least one surface feature, such as a recess, an opening, or a groove, that contributes to loss reduction. A rotary atomizer drive spindle according to claim 20 ,
The surface atomizing feature is provided on a non-functional surface of the turbine. A rotary atomizer drive spindle according to claim 20 or claim 21 ,
Each blade is provided with a substantially axial opening or a blind hole extending substantially in the axial direction. A rotary atomizer drive spindle according to claim 20 or claim 21 or claim 22 ,
A groove that extends in the circumferential direction is provided on the outer curved surface of the turbine. A rotary sprayer drive spindle according to any of claims 1 to 23 ,
The spindle main body includes an exhaust system including at least one exhaust passage for exhausting gas from an outlet of the turbine. A rotary atomizer drive spindle according to claim 24 ,
The rotary sprayer drive spindle, wherein the exhaust system includes an exhaust collection chamber between an outlet of the turbine and an outlet of the exhaust system. A rotary atomizer drive spindle according to claim 25 ,
The exhaust system is
At least one exhaust collection passage for supplying exhaust from the turbine outlet to the exhaust collection chamber;
A rotary sprayer drive spindle, comprising: a plurality of exhaust outlet passages for allowing exhaust gas to flow out from the collection chamber to the outside. A rotary atomizer drive spindle according to claim 25 or claim 26 ,
The exhaust spray chamber is provided at a position where the outflow direction of the exhaust gas must be changed. A rotary sprayer drive spindle according to any of claims 24 to 27 ,
The rotary sprayer-driven spindle, wherein the exhaust system is designed to maximize pressure drop before and after passing through the turbine by suppressing or preventing generation of turbulence and / or back pressure. A rotary sprayer drive spindle according to any of claims 24 to 28 ,
The exhaust sprayer is configured so that the exhaust gas flowing out cools the spindle. A rotary sprayer drive spindle according to any of claims 1 to 29 ,
The rotary sprayer-driven spindle, wherein the main body of the spindle includes two radial bearings spaced apart from each other. A rotary atomizer drive spindle according to claim 30 ,
The turbine is disposed between the spaced radial bearings. A rotary sprayer drive spindle. The rotary sprayer drive spindle according to any one of claims 1 to 31 , wherein the shaft supports two turbines. A rotary atomizer drive spindle according to claim 31 ,
The rotary sprayer-driven spindle, wherein the shaft supports two turbines disposed between the spaced radial bearings. A rotary atomizer drive spindle according to any one of claims 30 , 31 , 33 when dependent on claim 29 , comprising:
The rotary sprayer drive spindle, wherein the exhaust system is formed so that exhaust gas flowing out cools both the radial bearings. A rotary atomizer drive spindle according to claim 34 ,
At least one part in at least one exhaust passage passes in the vicinity of each radial bearing. A rotary atomizer drive spindle according to claim 34 or claim 35 ,
The exhaust system includes two exhaust collection chambers. A rotary sprayer drive spindle. The rotary atomizer drive spindle of claim 36 ,
The first collection chamber is provided near the first radial bearing;
The second spray chamber is provided in the vicinity of the second radial bearing. A rotary sprayer drive spindle. A rotary atomizer drive spindle according to claim 36 or claim 37 ,
With two turbines,
The exhaust system is
A first exhaust collection path for supplying exhaust from the outlet of the first turbine to the first collection chamber;
A rotary sprayer drive spindle, comprising: a second exhaust collection path for supplying exhaust from the outlet of the second turbine to the second collection chamber. A rotary atomizer drive spindle according to any of claims 31 to 38 when dependent on claim 30 ,
The rotary sprayer drive spindle, wherein the two bearings are firmly assembled to the remaining part of the spindle body. A rotary atomizer drive spindle according to any of claims 1 to 39 ,
The shape of one nozzle section or each nozzle section is substantially determined by the coordinate values shown in Table 1. A rotary sprayer drive spindle, wherein: A rotary atomizer drive spindle according to any of claims 1 to 40 ,
The shape of one nozzle part or each nozzle part is determined by each coordinate value within 0.01 difference with respect to the coordinate value shown in Table 1. The rotary sprayer drive spindle characterized by the above. A rotary sprayer drive spindle according to any of claims 1 to 41 ,
One of the blades or the shape of each blade is substantially determined by the coordinate values shown in Table 2. A rotary sprayer-driven spindle. A rotary atomizer drive spindle according to any of claims 1 to 42 ,
The shape of each of the one blade or the plurality of blades is determined by each coordinate value within 0.01 difference with respect to the coordinate values shown in Table 2. A rotary atomizer,
A drive spindle according to any one of claims 1 to 43 ;
A bell-shaped member configured to inject a conical curtain made of small particles that can rotate about a base axis and flow substantially toward an object;
A rotary sprayer comprising: a supply path for supplying a substance capable of generating the small particles from a storage source to the bell-shaped member.

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