CN113550978A - Compact pneumatic high-speed static pressure air main shaft - Google Patents
Compact pneumatic high-speed static pressure air main shaft Download PDFInfo
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- CN113550978A CN113550978A CN202110712090.7A CN202110712090A CN113550978A CN 113550978 A CN113550978 A CN 113550978A CN 202110712090 A CN202110712090 A CN 202110712090A CN 113550978 A CN113550978 A CN 113550978A
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
- F16C—SHAFTS; FLEXIBLE SHAFTS; ELEMENTS OR CRANKSHAFT MECHANISMS; ROTARY BODIES OTHER THAN GEARING ELEMENTS; BEARINGS
- F16C32/00—Bearings not otherwise provided for
- F16C32/06—Bearings not otherwise provided for with moving member supported by a fluid cushion formed, at least to a large extent, otherwise than by movement of the shaft, e.g. hydrostatic air-cushion bearings
- F16C32/0603—Bearings not otherwise provided for with moving member supported by a fluid cushion formed, at least to a large extent, otherwise than by movement of the shaft, e.g. hydrostatic air-cushion bearings supported by a gas cushion, e.g. an air cushion
- F16C32/0614—Bearings not otherwise provided for with moving member supported by a fluid cushion formed, at least to a large extent, otherwise than by movement of the shaft, e.g. hydrostatic air-cushion bearings supported by a gas cushion, e.g. an air cushion the gas being supplied under pressure, e.g. aerostatic bearings
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B05—SPRAYING OR ATOMISING IN GENERAL; APPLYING FLUENT MATERIALS TO SURFACES, IN GENERAL
- B05B—SPRAYING APPARATUS; ATOMISING APPARATUS; NOZZLES
- B05B3/00—Spraying or sprinkling apparatus with moving outlet elements or moving deflecting elements
- B05B3/02—Spraying or sprinkling apparatus with moving outlet elements or moving deflecting elements with rotating elements
- B05B3/10—Spraying or sprinkling apparatus with moving outlet elements or moving deflecting elements with rotating elements discharging over substantially the whole periphery of the rotating member, i.e. the spraying being effected by centrifugal forces
- B05B3/1035—Driving means; Parts thereof, e.g. turbine, shaft, bearings
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B25—HAND TOOLS; PORTABLE POWER-DRIVEN TOOLS; MANIPULATORS
- B25J—MANIPULATORS; CHAMBERS PROVIDED WITH MANIPULATION DEVICES
- B25J11/00—Manipulators not otherwise provided for
- B25J11/0075—Manipulators for painting or coating
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
- F16C—SHAFTS; FLEXIBLE SHAFTS; ELEMENTS OR CRANKSHAFT MECHANISMS; ROTARY BODIES OTHER THAN GEARING ELEMENTS; BEARINGS
- F16C32/00—Bearings not otherwise provided for
- F16C32/06—Bearings not otherwise provided for with moving member supported by a fluid cushion formed, at least to a large extent, otherwise than by movement of the shaft, e.g. hydrostatic air-cushion bearings
- F16C32/0603—Bearings not otherwise provided for with moving member supported by a fluid cushion formed, at least to a large extent, otherwise than by movement of the shaft, e.g. hydrostatic air-cushion bearings supported by a gas cushion, e.g. an air cushion
- F16C32/0614—Bearings not otherwise provided for with moving member supported by a fluid cushion formed, at least to a large extent, otherwise than by movement of the shaft, e.g. hydrostatic air-cushion bearings supported by a gas cushion, e.g. an air cushion the gas being supplied under pressure, e.g. aerostatic bearings
- F16C32/0625—Bearings not otherwise provided for with moving member supported by a fluid cushion formed, at least to a large extent, otherwise than by movement of the shaft, e.g. hydrostatic air-cushion bearings supported by a gas cushion, e.g. an air cushion the gas being supplied under pressure, e.g. aerostatic bearings via supply slits
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
- F16C—SHAFTS; FLEXIBLE SHAFTS; ELEMENTS OR CRANKSHAFT MECHANISMS; ROTARY BODIES OTHER THAN GEARING ELEMENTS; BEARINGS
- F16C32/00—Bearings not otherwise provided for
- F16C32/06—Bearings not otherwise provided for with moving member supported by a fluid cushion formed, at least to a large extent, otherwise than by movement of the shaft, e.g. hydrostatic air-cushion bearings
- F16C32/0681—Construction or mounting aspects of hydrostatic bearings, for exclusively rotary movement, related to the direction of load
- F16C32/0696—Construction or mounting aspects of hydrostatic bearings, for exclusively rotary movement, related to the direction of load for both radial and axial load
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- Engineering & Computer Science (AREA)
- General Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Robotics (AREA)
- Magnetic Bearings And Hydrostatic Bearings (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
Abstract
The invention provides a compact pneumatic high-speed static pressure air main shaft which comprises a main shaft base, a hollow rotating shaft, a worm wheel, an air supply assembly, an air hole compression ring, an air hole flange, an air film copper sleeve assembly and other parts.
Description
Technical Field
The invention relates to a high-rotating-speed main shaft, in particular to a compact pneumatic high-speed static pressure air main shaft.
Background
In the modern society, two technologies, namely air bearing and air motor, are widely used, and the air bearing refers to a technology which uses air as a lubricant and forms a certain amount of air film between two objects moving relative to each other to make the contact friction force zero. The pneumatic motor is a technology which abandons transmission electric drive and utilizes compressed air to blow the fan blades to rotate so as to provide stable rotating speed and torque.
In order to ensure the successful flying of the missile, a heat-proof and antistatic paint layer is required to be used between the composite material shell and the internal filling material of the engine, but the paint has the characteristics of high solid content, high viscosity, light weight, low density and low spraying thickness. The requirements on the spraying process parameters and the spraying operation parameters are high, the glue solution is easy to sag due to the fact that manual painting is not controlled in place, the leveling property is poor, the stability is poor, and the coating quality cannot meet the requirements. Accordingly, a driving device needs to be compact in structure and can stably and accurately control a coating process so as to drive the coating robot to perform high-speed rotation and atomization coating operation on the coating head and the high-viscosity glue solution in a narrow space.
Disclosure of Invention
The invention aims to overcome the defects and provides a compact pneumatic high-speed static pressure air main shaft which comprises a main shaft base, a hollow rotating shaft, a volute fan wheel, an air supply assembly, an air hole compression ring, an air hole flange, an air film copper sleeve assembly and the like.
In order to achieve the above purpose, the invention provides the following technical scheme:
a compact pneumatic high-speed static pressure air main shaft comprises a main shaft base, a hollow rotating shaft, a turbofan wheel, an air supply assembly, an air hole compression ring, a curved air flue flange, an air hole flange and an air film copper sleeve assembly;
the air supply component is of a hollow cylindrical structure; the air supply assembly and the air film copper sleeve assembly are fixedly arranged in the main shaft base;
the hollow rotating shaft is provided with a shaft shoulder, and one end of the hollow rotating shaft, which is positioned at the rear part of the shaft shoulder, is in clearance fit with the air film copper bush component; one end of the shaft shoulder is in interference fit with the worm gear and a curved air flue flange fixedly arranged at the rear end of the worm gear;
the hollow rotating shaft is hermetically assembled at the front end of the main shaft base through an air hole compression ring; the air film copper bush component is compressed and positioned through an air hole flange fixedly arranged in the main shaft base; the air hole compression ring and the air hole flange are in clearance fit with the hollow rotating shaft;
gaps are arranged between the air hole compression ring and the front end face of the turbofan wheel and between the air hole flange and the curved air flue flange;
the air supply assembly is internally provided with a bearing air inlet channel and a turbine air inlet channel; the bearing air inlet channel is respectively communicated with a gap between the air hole compression ring and the front end face of the turbofan wheel and a gap between the air hole flange and the curved surface air flue flange, and compressed air axially limits the turbofan wheel so as to axially limit the hollow rotating shaft;
the bearing air inlet channel is communicated with a gap between the air film copper sleeve assembly and the hollow rotating shaft, and compressed air forms a radial air film to radially support the hollow rotating shaft;
compressed air discharged from the turbine air inlet duct drives the worm fan wheel to rotate so as to drive the hollow rotating shaft to rotate;
the air main shaft is provided with an air leakage channel for discharging air in the air main shaft.
Further, a base air inlet passage connected with the bearing air inlet pore passage is arranged in the main shaft base;
the bearing air inlet channel is communicated with a gap between the air hole compression ring and the front end surface of the turbofan wheel through a first axial air floating channel arranged in the air hole compression ring;
the bearing air inlet pore passage is communicated with a gap between the air hole flange and the curved surface air flue flange through a base air inlet passage and a second axial air floating channel arranged in the air hole flange;
and the bearing air inlet channel is communicated with a gap between the air film copper sleeve assembly and the hollow rotating shaft through the base air inlet passage and a radial air floatation through hole arranged on the side surface of the air film copper sleeve assembly.
Further, the gas film copper sleeve assembly comprises a first gas film copper sleeve and a second gas film copper sleeve which have the same structure and are axially distributed along the hollow rotating shaft; the wall of the cylindrical side surface of the gas film copper sleeve assembly is provided with radial air floatation holes which are through holes with the aperture of 0.1-0.3 mm; and sealing ring caulking grooves are formed in the front end and the rear end of each gas film copper sleeve, and the gas film copper sleeves are fixedly connected with the main shaft base after the sealing ring caulking grooves are matched with the sealing rings.
Furthermore, the worm wheel comprises an annular main body and fan blades, wherein the fan blades are arranged on the main body and distributed along the circumference of the annular end face of the main body; the cross section of the fan blade parallel to the annular end surface of the main body is in a crescent shape surrounded by two curves; the number of the fan blades is 10-50, and the distance between the fan blades is 4-8 mm.
Further, the outlet of the first axial air floatation channel arranged on the air hole compression ring is a blind hole which is arranged on the rear end face of the air hole compression ring and is annularly arranged; the outlet of the second axial air floatation channel arranged on the air hole flange is a blind hole which is arranged on the front end surface of the air hole flange and is distributed along the ring shape;
the diameter of the blind hole is 0.1-0.5 mm.
Further, the air release channel comprises a rotating shaft air release channel and a main shaft base air release channel;
the rotating shaft air leakage channel sequentially passes through a first air exhaust channel arranged in the hollow rotating shaft, a second air exhaust channel arranged in the air hole pressing ring and a third air exhaust channel arranged in the air supply assembly to exhaust air;
the spindle base air leakage channel sequentially passes through a fourth channel arranged at the rear end of the air film copper sleeve assembly and a fifth exhaust channel arranged at the rear end of the spindle base to exhaust air; or the spindle base air leakage channel sequentially passes through a sixth channel arranged at the front end of the air film copper sleeve assembly, a seventh exhaust channel arranged at the front end of the spindle base, an eighth exhaust channel formed between the curved surface air flue flange and the air supply assembly, a channel between fan blades of the turbofan and a third exhaust channel arranged in the air supply assembly to discharge air.
Further, the first exhaust passage is a through hole provided in a side wall of the hollow rotary shaft; the through holes are parallel to the axis of the hollow rotating shaft and are distributed on the shaft shoulder surface along the circumferential direction; the number of the through holes is 5-30, and the diameter is 10-30 mm.
Furthermore, the shape of an eighth exhaust channel formed between the curved air flue flange and the air feeding assembly on the cross section passing through the axis of the air spindle is a curve;
and the seventh exhaust channel arranged at the front end of the spindle base is 2 groups, and the seventh exhaust channel forms an angle of 45 degrees with the axial direction of the air spindle.
Further, the air supply assembly also comprises a turbine brake air inlet duct or a speed measurement sensor mounting duct;
the turbine braking air inlet duct is used for discharging air to brake the turbofan wheel; the speed measuring sensor mounting hole is used for mounting a speed measuring sensor for testing the air flow rate.
Further, the overall diameter of the air main shaft is smaller than 80mm, and the length of the air main shaft is smaller than 100 mm.
Compared with the prior art, the invention has the following beneficial effects:
(1) the compact pneumatic high-speed static pressure air main shaft provided by the invention designs the matching mode of each part and the specific structure, shape, angle and the like of a flow passage in each part, so that the volume of the air main shaft provided by the invention is reduced as much as possible on the premise of meeting the air inlet and exhaust functions;
(2) the compact pneumatic high-speed static pressure air main shaft disclosed by the invention realizes the combination of pneumatic and air flotation functions for the first time, so that the polishing and coating head is driven to rotate at a high speed and the atomizing polishing and coating operation is more stable and efficient;
(3) the compact pneumatic high-speed static pressure air main shaft has the overall diameter size of less than 80mm, the length size of less than 100mm and the maximum main shaft rotating speed of 100000r/min, and is suitable for being applied to a coating robot for a curved inner cavity of a missile shell, and the coating robot for a driving cavity performs high-speed rotation and atomization coating operation on a coating head and high-viscosity glue in a narrow space.
Drawings
FIG. 1 is a schematic view of the channels of an air delivery assembly in a compact pneumatic high speed hydrostatic air spindle according to the present invention;
FIG. 2 is a cross-sectional view of a compact pneumatic high-speed hydrostatic air spindle of the present invention;
FIG. 3 is a schematic view of a turbine shaft formed by combining a volute wheel, a hollow rotating shaft and a curved air passage flange of a compact pneumatic high-speed static pressure air main shaft according to the invention;
FIG. 4 is a schematic view of an air film copper sleeve of a compact pneumatic high-speed hydrostatic air spindle of the present invention;
FIG. 5 is a schematic view of a vent flange of a compact pneumatic high speed hydrostatic air spindle of the present invention;
FIG. 6 is a schematic view of an air hole clamp ring of a compact pneumatic high-speed static pressure air spindle according to the present invention
FIG. 7 is a schematic view of a spindle base for a compact pneumatic high speed hydrostatic air spindle of the present invention;
FIG. 8 is a schematic view of a volute gear bidirectional air passage structure of a compact pneumatic high-speed static pressure air spindle according to the present invention;
FIG. 9 is a cross-sectional view of a turbine air inlet duct of the plenum assembly of the present invention;
FIG. 10 is a schematic cross-sectional view of a turbofan according to the invention;
FIG. 11 is a cross-sectional view of the brake air inlet duct of the turbofan of the present invention;
FIG. 12 is a cross-sectional view of the spindle base bleed passage of the present invention;
FIG. 13 is a cross-sectional view of the radial air-floating through holes of the air film copper sleeve and the spindle base of the present invention;
FIG. 14 is a rear end view of a compact pneumatic high speed hydrostatic air spindle of the present invention.
Detailed Description
The features and advantages of the present invention will become more apparent and appreciated from the following detailed description of the invention.
The word "exemplary" is used exclusively herein to mean "serving as an example, embodiment, or illustration. Any embodiment described herein as "exemplary" is not necessarily to be construed as preferred or advantageous over other embodiments. While the various aspects of the embodiments are presented in drawings, the drawings are not necessarily drawn to scale unless specifically indicated.
The invention discloses a compact pneumatic high-speed static pressure air main shaft applied to a coating robot for a curved surface inner cavity of a missile shell, which can perform high-speed rotation and atomization coating operation on a coating head and high-viscosity glue solution in a narrow space.
As shown in fig. 1-14, the technical scheme of the invention is as follows: a compact pneumatic high-speed static pressure air spindle comprises a spindle base 010 shown in figure 7, wherein an air supply assembly is connected to the inside of the spindle base 010 and sequentially comprises an air passage rear ring 007, an air passage middle ring 005 and an air passage front ring 004, and the air supply assembly is located at the front end of the spindle base 010; the airway rear ring 007, the airway middle ring 005 and the airway front ring 004 are all hollow cylindrical structures;
the inside of main shaft base 010 is close to well rear position, and sealed installation has the air film copper sheathing subassembly, contains first air film copper sheathing 011 and second air film copper sheathing 013. The air hole flange 009 is tightly connected with the main shaft base 010 through bolts, and the air hole flange 009 tightly seals the first air film copper bush 011 in the main shaft base 010.
A hollow rotating shaft 012 is arranged in the main shaft base 010 and the air passage rear ring 007, the air passage middle ring 005, the air passage front ring 004, the first air film copper sleeve 011 and the second air film copper sleeve 013 which are assembled with the main shaft base 010; the turbofan 006 is located in the hollow inner cavities of the rear airway ring 007, the middle airway ring 005 and the front airway ring 004; the hollow rotating shaft 012 is in interference fit with a central duct of the turbofan 006 and a curved airway flange 008 arranged at the rear end of the turbofan 006;
the hollow rotating shaft 012 is tightly assembled at the front end of the main shaft base 010 in a sealing manner through the air hole compression ring 002, and the whole structure is tightened and fixed through the spigot assembling flange 001.
In the compact pneumatic high-speed static pressure air main shaft, the high-speed static pressure air main shaft has compact structure, small volume and high rotating speed. The overall diameter size is less than 80mm, the length size is less than 100mm, and the maximum rotating speed of the main shaft can reach 100000 r/min.
In the above compact pneumatic high-speed static pressure air spindle, the rear air passage ring 007, the middle air passage ring 005, and the front air passage ring 004 are all provided with five coaxially aligned air inlet and outlet ducts, as shown in fig. 1, which are respectively: the device comprises a bearing air inlet duct A, a turbine air inlet duct B, a turbine brake air inlet duct C, an air exhaust duct D and a speed measuring sensor mounting duct E.
As shown in fig. 6, an air groove for air intake is designed in the middle of the air hole clamp ring 002, air floating blind holes are annularly arranged on the end surface after assembly, the size of the air hole is 0.2mm, and the air hole clamp ring 002 performs air floating limit on the turbine shaft in the axial positive direction; the turbine shaft comprises a turbofan wheel 006, a curved air duct flange 008 and a hollow rotating shaft 012; the square air bearing is an air bearing in the rear direction, i.e., in the rightward direction in fig. 2.
As shown in fig. 5, an air inlet groove is arranged in the middle of the air hole flange 009, and the air inlet groove and the axis of the air spindle form an included angle of 45 degrees, so that the assembly space is saved, and air can be ensured to flow into the air hole flange 009 from the spindle base 010; the front end face is provided with air floating blind holes which are annularly arranged, the size of each air hole is 0.2mm, the circumferential side face is provided with air passage air holes matched with the air floating blind holes in number, and the end face holes are matched with the circumferential holes in number to form an air hole passage. The air hole flange 009 is further designed with a process threaded hole, and the air hole flange 009 limits the axial negative direction air floatation limit of the turbine shaft.
As shown in fig. 4 and 13, the circumferential side surfaces of the first air film copper sleeve 011 and the second air film copper sleeve 013 are provided with radial air flotation through holes, the hole diameter is 0.2mm, the edges of the through holes are provided with processing process holes, the diameter of each process hole is 2mm and 2mm, the front end and the rear end of each of the first air film copper sleeve 011 and the second air film copper sleeve 013 are provided with arc sealing ring caulking grooves, and the first air film copper sleeve 011 and the second air film copper sleeve 013 limit the radial air flotation limit of the hollow rotating shaft 012.
As shown in fig. 3 and 8, the worm wheel 006 is designed as a half-wheel and half-fan ring-shaped worm fan, which can improve the dynamic balance and stability of the worm fan at high rotation speed on the premise of minimum compression worm fan characteristics and mass, and the shape of the fan blades is crescent, and the fan blades are annularly arranged, and each fan blade has a distance of 6mm, and provides power for the hollow rotating shaft 012 by compressed air in a narrow space. In fig. 9, 10 and 11, the cross-section of the rotating air intake and brake air intake ducts and the fan blades of the worm wheel can be seen;
in the compact pneumatic high-speed static pressure air spindle, as shown in fig. 2, the outer surface of the curved air passage flange 008 is designed to be a curved surface, so that high-pressure air is decompressed and guided.
In the compact pneumatic high-speed static pressure air main shaft, the shoulder surface of the hollow rotating shaft 012 is provided with exhaust through holes along the axial direction, the exhaust through holes are annularly arranged along the shoulder surface, the number of the exhaust through holes is 12, the diameter of the exhaust through holes is 1.5mm, and the exhaust through holes guide the bearing air film between the air film copper sleeve component and the hollow rotating shaft 012.
The middle ring 005 of the air passage is provided with double rows of turbine air inlet channels, which can provide double air to provide power for the rotation of the worm wheel 006.
The air inlet passage of the main shaft base 010 corresponding to the bearing air inlet hole channels in the air passage rear ring 007, the air passage middle ring 005 and the air passage front ring 004 is divided into two paths, one path is transmitted to the air hole flange 009, the other path is transmitted to the first air film copper sleeve 011 and the second air film copper sleeve 013, 2 groups of air film exhaust holes with 45-degree long inclined blind holes are designed in the bearing air outlet hole channels of the main shaft base 010 corresponding to the air passage rear ring 007, the air passage middle ring 005 and the air passage front ring 004, and the whole main shaft base 010 is dense in open holes and compact in structure. The end faces of the front end and the rear end of the first air film copper sleeve 011 and the second air film copper sleeve 013 are provided with sealing positioning holes, so that the first air film copper sleeve 011 and the second air film copper sleeve 013 are prevented from axially rotating.
Air pressure rubber rings are arranged on a bearing air inlet channel A, a turbine air inlet channel B, a turbine brake air inlet channel C and an air exhaust channel D of the air channel front ring 004, and the air tightness of a passage is guaranteed to be good.
Bearing air supply gas circuit principle: compressed air for air supply enters a bearing air inlet channel through an air channel front ring 004 and then is divided into two paths, wherein one path enters an air hole compression ring 002 along a passage to carry out air floatation on a hollow rotating shaft 012 in the axial positive direction; one path enters an air film air inlet hole (namely a base air inlet passage) of the main shaft base 010 along an air hole of the middle ring 005 and the rear ring 007 of the air passage, the air film air inlet passage of the main shaft base 010 is divided into two paths, and one path of air inlet flange 009 performs axial negative air floatation on the hollow rotating shaft 012; one path is provided for the first air film copper sleeve 011 and the second air film copper sleeve 013 to carry out radial air floatation on the hollow rotating shaft 012.
Volute wheel air supply path principle: compressed air for air supply enters the air inlet channel of the turbofan through the front ring 004 of the air channel and then blows the turbofan to rotate at a high speed through the double-row channel of the turbofan air inlet holes of the middle ring 005 of the air channel.
The disappointing passageway of rotation axis includes cavity rotation axis 012 shaft shoulder exhaust hole, and the air of disappointing the passageway through the rotation axis includes: a radial air film between the front end of the first air film copper sleeve 011 and the hollow rotating shaft 12, and an axial air film formed by the air hole flange 009 and the air hole pressing ring 002.
The disappointing passageway of main shaft base includes 2 groups 45 long oblique blind holes and the circular arc groove of length that main shaft base 010 was established, like fig. 12, the air of disappointing passageway exhaust hole through the main shaft base includes: a radial air film between the rear end of the first air film copper sleeve 011 and the hollow rotating shaft 12, and a radial air film between the front end of the second air film copper sleeve 013 and the hollow rotating shaft 12;
the radial air film between the rear end of the second air film copper sheathing 013 and the hollow rotating shaft 12 is exhausted through a fourth channel located at the rear end of the air film copper sheathing assembly and a fifth exhaust channel located at the rear end of the spindle base 010.
The invention has been described in detail with reference to specific embodiments and illustrative examples, but the description is not intended to be construed in a limiting sense. Those skilled in the art will appreciate that various equivalent substitutions, modifications or improvements may be made to the technical solution of the present invention and its embodiments without departing from the spirit and scope of the present invention, which fall within the scope of the present invention. The scope of the invention is defined by the appended claims.
Those skilled in the art will appreciate that those matters not described in detail in the present specification are well known in the art.
Claims (10)
1. A compact pneumatic high-speed static pressure air main shaft is characterized by comprising a main shaft base (010), a hollow rotating shaft (012), a turbofan wheel (006), an air supply assembly, an air hole compression ring (002), a curved air channel flange (008), an air hole flange (009) and an air film copper sleeve assembly;
the air supply component is of a hollow cylindrical structure; the air supply assembly and the air film copper sleeve assembly are fixedly arranged inside the main shaft base (010);
the hollow rotating shaft (012) is provided with a shaft shoulder, and one end of the hollow rotating shaft positioned at the rear part of the shaft shoulder is in clearance fit with the air film copper bush component; one end of the shaft shoulder is in interference fit with the turbofan wheel (006) and a curved airway flange (008) fixedly arranged at the rear end of the turbofan wheel (006);
the hollow rotating shaft (012) is hermetically assembled at the front end of the main shaft base (010) through an air hole compression ring (002); the air film copper sleeve component is pressed and positioned through an air hole flange (009) fixedly arranged in the main shaft base (010); the air hole compression ring (002) and the air hole flange (009) are in clearance fit with the hollow rotating shaft (012);
gaps are arranged between the air hole compression ring (002) and the front end face of the turbofan wheel (006) and between the air hole flange (009) and the curved air flue flange (008);
the air supply assembly is internally provided with a bearing air inlet channel and a turbine air inlet channel; the bearing air inlet channel is respectively communicated with a gap between the air hole compression ring (002) and the front end face of the turbofan wheel (006) and a gap between the air hole flange (009) and the curved air channel flange (008), and compressed air axially limits the turbofan wheel (006) and further axially limits the hollow rotating shaft (012);
the bearing air inlet pore passage is communicated with a gap between the air film copper sleeve component and the hollow rotating shaft (012), and compressed air forms a radial air film to radially support the hollow rotating shaft (012);
compressed air discharged from the turbine air inlet duct drives the turbofan wheel (006) to rotate, so as to drive the hollow rotating shaft (012) to rotate;
the air main shaft is provided with an air leakage channel for discharging air in the air main shaft.
2. A compact pneumatic high-speed hydrostatic air spindle according to claim 1, wherein the spindle base (010) has therein a base intake passage connected to a bearing air intake port;
the bearing air inlet channel is communicated with a gap between the air hole compression ring (002) and the front end face of the turbofan wheel (006) through a first axial air floatation channel arranged in the air hole compression ring (002);
the bearing air inlet pore passage is communicated with a gap between the air hole flange (009) and the curved air passage flange (008) through a base air inlet passage and a second axial air floating channel arranged in the air hole flange (009);
the bearing air inlet pore passage is communicated with a gap between the air film copper sleeve assembly and the hollow rotating shaft (012) through a base air inlet passage and a radial air floatation through hole arranged on the side surface of the air film copper sleeve assembly.
3. A compact pneumatic high-speed hydrostatic air spindle according to claim 2, characterized in that the air film copper bush assembly comprises a first air film copper bush (011) and a second air film copper bush (013) which have the same structure and are axially distributed along the hollow rotating shaft (012); the wall of the cylindrical side surface of the gas film copper sleeve assembly is provided with radial air floatation holes which are through holes with the aperture of 0.1-0.3 mm; and sealing ring caulking grooves are formed in the front end and the rear end of each gas film copper sleeve, and the gas film copper sleeves are fixedly connected with the main shaft base (010) after the sealing ring caulking grooves are matched with the sealing rings.
4. The compact pneumatic high-speed hydrostatic air spindle of claim 1, wherein the turbofan wheel (006) comprises an annular body and fan blades arranged on the body and distributed along a circumference of an annular end surface of the body; the cross section of the fan blade parallel to the annular end surface of the main body is in a crescent shape surrounded by two curves; the number of the fan blades is 10-50, and the distance between the fan blades is 4-8 mm.
5. The compact type pneumatic high-speed static-pressure air spindle as claimed in claim 2, wherein the outlet of the first axial air flotation channel of the air hole clamp ring (002) is a blind hole which is arranged on the rear end face of the air hole clamp ring (002) and is arranged in an annular shape; the outlet of the second axial air floatation channel arranged on the air hole flange (009) is a blind hole which is arranged on the front end surface of the air hole flange (009) and is distributed along the ring shape;
the diameter of the blind hole is 0.1-0.5 mm.
6. The compact pneumatic high-speed hydrostatic air spindle of claim 1, wherein the air escape passage comprises a rotating shaft air escape passage and a spindle base air escape passage;
the rotating shaft air leakage channel sequentially passes through a first air exhaust channel arranged in the hollow rotating shaft (012), a second air exhaust channel arranged in the air hole compression ring (002) and a third air exhaust channel arranged in the air supply assembly to exhaust air;
the spindle base air leakage channel sequentially passes through a fourth channel arranged at the rear end of the air film copper sleeve assembly and a fifth exhaust channel arranged at the rear end of the spindle base (010) to exhaust air; or, the spindle base air leakage channel sequentially passes through a sixth channel arranged at the front end of the air film copper sleeve assembly, a seventh exhaust channel arranged at the front end of the spindle base (010), an eighth exhaust channel formed between the curved surface air flue flange (008) and the air supply assembly, and a channel between fan blades of the turbofan wheel (006) and a third exhaust channel arranged in the air supply assembly discharge air.
7. A compact pneumatic high-speed hydrostatic air spindle according to claim 6, characterized in that the first air discharge channel is a through hole provided in the side wall of the hollow rotary shaft (012); the through holes are parallel to the axis of the hollow rotating shaft (012) and are distributed on the shaft shoulder surface along the circumferential direction; the number of the through holes is 5-30, and the diameter is 10-30 mm.
8. A compact pneumatic high-speed hydrostatic air spindle according to claim 6 in which the eighth exhaust passage formed between the curved airway flange (008) and the plenum assembly is curved in shape in cross-section across the axis of the air spindle;
and the seventh exhaust channel arranged at the front end of the main shaft base (010) is 2 groups, and the seventh exhaust channel forms an angle of 45 degrees with the axial direction of the air main shaft.
9. The compact pneumatic high-speed hydrostatic air spindle of claim 6, wherein the air delivery assembly further comprises a turbine brake air inlet duct or a tacho sensor mounting duct;
the turbine brake air inlet channel is used for discharging air to brake the turbofan wheel (006); the speed measuring sensor mounting hole is used for mounting a speed measuring sensor for testing the air flow rate.
10. A compact pneumatic high velocity static pressure air spindle according to any one of claims 1 to 9 having an overall diameter of less than 80mm and a length of less than 100 mm.
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| CN202110712090.7A CN113550978B (en) | 2021-06-25 | 2021-06-25 | Compact pneumatic high-speed static pressure air main shaft |
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| CN202110712090.7A CN113550978B (en) | 2021-06-25 | 2021-06-25 | Compact pneumatic high-speed static pressure air main shaft |
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| CN113550978B (en) | 2022-11-18 |
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