CN108061096B - Porous gas static pressure rotary platform - Google Patents
Porous gas static pressure rotary platform Download PDFInfo
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- CN108061096B CN108061096B CN201711414623.3A CN201711414623A CN108061096B CN 108061096 B CN108061096 B CN 108061096B CN 201711414623 A CN201711414623 A CN 201711414623A CN 108061096 B CN108061096 B CN 108061096B
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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
- F16C32/0618—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 porous material
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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
- F16C32/0662—Details of hydrostatic bearings independent of fluid supply or direction of load
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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)
- Chemical & Material Sciences (AREA)
- Dispersion Chemistry (AREA)
- Magnetic Bearings And Hydrostatic Bearings (AREA)
Abstract
The invention discloses a porous aerostatic rotary platform, which comprises a rotary body, a radial bearing, an upper thrust bearing part and a lower thrust bearing part, wherein the radial bearing adopts a full-porous aerostatic radial bearing, and the upper thrust bearing part and the lower thrust bearing part both adopt a local porous aerostatic thrust bearing structure; the upper and lower thrust bearing parts are connected with the radial bearing through uniformly distributed connecting threads, and a stable gas film gap is formed by the local porous gas thrust bearing and the revolving body. The full-porous static pressure radial bearing is positioned in the revolving body, and the zero friction rotation of the revolving body is ensured. The invention combines the advantages of the full-porous aerostatic radial bearing and the local porous gas thrust bearing, the porous material has uniform pores and consistent permeability, and the air-flotation rotary platform made of the porous aerostatic bearing has the advantages of high rotary precision, high bearing capacity, high rigidity, good stability and the like.
Description
Technical Field
The invention relates to a gas static pressure precision rotary table, in particular to a porous gas static pressure rotary platform.
Background
The gas static pressure precision turntable is widely applied to the industries of aviation, aerospace, precision machinery, mechanical manufacturing and the like, is an important basic component for ensuring the machining and detection precision, and the precision of the precision directly influences the characteristic dimension precision of a workpiece in the manufacturing process and the detection precision of a manufactured element. Compared with other throttling modes, the porous throttling device has the great advantages of high bearing capacity and rigidity, good dynamic property and damping performance, the gas film formed by using gas as a lubricant has a homogenizing effect, the rotary error caused by manufacturing errors can be compensated, and the gas source is wide and pollution-free.
Disclosure of Invention
Aiming at the prior art, the invention provides a porous aerostatic rotary platform, which combines the advantages of a full-porous hydrostatic radial bearing and a local porous thrust bearing, and the air-flotation rotary platform made of the porous aerostatic bearing has the advantages of high rotary precision, high bearing capacity, high rigidity, good stability and the like.
In order to solve the technical problem, the porous aerostatic rotary platform provided by the invention comprises a rotary body, a radial bearing, an upper thrust bearing part and a lower thrust bearing part, wherein the radial bearing is arranged in the rotary body, the upper thrust bearing part is coaxially fixed above the radial bearing, and the lower thrust bearing part is coaxially fixed below the radial bearing; the radial bearing is a full-porous static pressure radial bearing, and the upper thrust bearing part and the lower thrust bearing part both adopt a local porous static pressure thrust bearing structure; the full-porous static pressure radial bearing comprises a central ventilation ring, wherein the central ventilation ring is sleeved with a porous ring, two ends of the porous ring are respectively provided with an outer ring, and the central ventilation ring is provided with a first central through hole and a radial through hole communicated with the first central through hole; a circle of annular grooves are formed on the outer rotary surface of the central ventilation ring, so that a first annular air chamber communicated with the central through hole is formed between the porous ring and the central ventilation ring; the upper thrust bearing component comprises an upper thrust bearing base body and an upper end cover plate which are coaxially fixed, the upper thrust bearing base body is provided with a second central through hole, the bottom surface of the upper thrust bearing base body is uniformly provided with a plurality of first step through holes, a first annular groove is formed in one end, which is in contact with the upper thrust bearing base body, of the upper end cover plate, the upper end cover plate is provided with a first through hole, the first step through holes and the first through hole are communicated with the first annular groove, the first through hole is connected to the first central through hole from the outer revolution surface of the upper end cover plate, and therefore a second annular air chamber which is communicated with the first through hole and the first step through holes is formed between the upper end cover plate and the upper thrust bearing base body; a first local porous throttler is arranged in the counter bore of each first stepped through hole; the lower thrust bearing component comprises a lower thrust bearing base body and a lower end cover plate which are coaxially fixed, the lower thrust bearing base body is provided with a third central through hole, the top surface of the lower thrust bearing base body is uniformly provided with a plurality of second step through holes, a second annular groove is formed in the surface, contacting with the lower thrust bearing base body, of the lower end cover plate, the lower end cover plate is provided with a second through hole, the second step through holes and the second through hole are communicated with the second annular groove, the second through hole is connected to the first central through hole from the outer revolution surface of the lower end cover plate, and therefore a third annular air chamber which is communicated with the second through hole and the second step through holes is formed between the lower end cover plate and the lower thrust bearing base body; a second local porous throttler is arranged in the counter bore of each second step through hole; the second local porous throttle has a dimension larger than a dimension of the first local porous throttle; two through holes are axially formed in the lower thrust bearing base body and the lower end cover plate in a penetrating mode, and the center distance of the two through holes is equal to the outer diameter of the outer ring; and a radial exhaust groove is formed in the bottom surface of the lower end cover plate and communicated with the two through holes.
Further, according to the porous aerostatic rotary platform, an outer chamfer is arranged at the bottom of an outer ring at the lower end of the porous ring, an inner chamfer is arranged at the bottom of the rotary body, an annular groove is formed between the outer chamfer and the inner chamfer, and the tops of the two through holes are communicated with the annular groove.
In the invention, an air supply channel to the first annular air chamber is formed from the first through hole to the radial through hole after sequentially passing through the second central through hole and the first central through hole and from the second through hole to the radial through hole after sequentially passing through the third central through hole and the first central through hole.
In the present invention, a gas supply passage to the first local porous restrictor is formed from the first through hole to the first stepped through hole through the second annular gas chamber.
In the present invention, a gas supply passage to the second local porous restrictor is formed from the second through hole to the second stepped through hole through the third annular gas chamber.
In the present invention, an exhaust passage is formed from the annular groove to the two through holes and then to the radial exhaust passage, and the second partial porous throttle and the full porous hydrostatic radial bearing are formed.
In the invention, the outer ring and the central ventilation ring and the outer ring and the porous ring are connected by adopting viscose glue.
Compared with the prior art, the invention has the beneficial effects that:
the porous aerostatic rotary platform provided by the invention adopts a structure of a local porous hydrostatic thrust bearing and a full porous hydrostatic radial bearing, wherein the local porous hydrostatic thrust bearing mainly plays a role in supporting a rotary part and providing axial bearing capacity and rigidity, the full porous hydrostatic radial bearing plays a role in isolating the rotary part and providing radial bearing capacity and rigidity, and the rotary part can realize ultralow friction and high-precision rotary motion in a ventilation state. The upper and lower thrust bearing parts and the full-porous static pressure radial bearing adopt the air supply form of the same air passage, the air passage has ingenious structure, the rotating part is completely suspended in the ventilation state, the high processing precision and the homogenization effect of an air film are added, the obtained rotating precision is very high, and the bearing capacity and the rigidity are high in the axial direction and the radial direction, and the stability is also good.
Drawings
FIG. 1 is an exploded view of a porous aerostatic rotary platform according to the present invention;
FIG. 2 is a cross-sectional view of a porous aerostatic rotary platform of the present invention;
FIG. 3 is a full cross-sectional view of the upper thrust bearing assembly of FIG. 2 taken in another direction;
FIG. 4 is a full cross-sectional view of the lower thrust bearing assembly shown in FIG. 2 in another cutaway orientation;
fig. 5 is a perspective view of the upper end cap plate 1 shown in fig. 1;
figure 6 is a perspective view of the central venting ring 5 shown in figure 1;
fig. 7 is a perspective view of the lower end cap plate 10 shown in fig. 1;
fig. 8 is a schematic view of the machining accuracy of the rotary body 4 in the present invention;
fig. 9 is a schematic view of the machining accuracy of the all-porous hydrostatic radial bearing of the present invention.
In the figure: 1-upper end cover plate, 11-second annular air chamber, 12-first through hole, 2-upper thrust bearing base body, 21-second central through hole, 3-first local porous restrictor, 4-revolving body, 5-central ventilation ring, 51-first central through hole, 52-radial through hole, 53-first annular air chamber, 6-porous ring, 7-outer ring, 8-second local porous restrictor, 9-lower thrust bearing base body, 91-third central through hole, 10-lower end cover plate, 13-second through hole, 14-radial exhaust groove, 15-through hole, 16-third annular air chamber, and 17-viscose.
Detailed Description
The technical solutions of the present invention are further described in detail below with reference to the drawings and specific embodiments, which are only illustrative of the present invention and are not intended to limit the present invention.
The design idea of the porous aerostatic rotary platform is as follows: the structure of the local porous static pressure thrust bearing and the full porous static pressure radial bearing is adopted, the local porous static pressure thrust bearing mainly plays a role in supporting the rotary part and providing axial bearing capacity and rigidity, the full porous static pressure radial bearing plays a role in isolating the rotary part and providing radial bearing capacity and rigidity, and ultralow friction and high-precision rotary motion of the rotary part can be realized in a ventilation state.
The invention provides a porous gas static pressure rotary platform which comprises a rotary body, a radial bearing, an upper thrust bearing part and a lower thrust bearing part, wherein the upper thrust bearing part is coaxially fixed above the radial bearing, the lower thrust bearing part is coaxially fixed below the radial bearing, and the contact surfaces of the upper thrust bearing part and the rotary body, the upper thrust bearing part and the lower thrust bearing part and the rotary body are ground and polished, so that the porous gas static pressure rotary platform has high surface roughness and flatness.
The upper thrust bearing component and the lower thrust bearing component both adopt a local porous static pressure thrust bearing structure.
As shown in fig. 1 and 2, the radial bearing is a full-porous hydrostatic radial bearing disposed in the rotor 4, the full-porous hydrostatic radial bearing includes a central ventilation ring 5, a porous ring 6 is sleeved on the central ventilation ring 5, outer rings 7 are disposed at both ends of the porous ring 6, and the outer rings 7 and the central ventilation ring 5 and the outer rings 7 and the porous rings 6 are connected by adhesives 17. The central ventilation ring 5 is provided with a first central through hole 51 and a radial through hole 52 communicated with the first central through hole 51; a circle of annular grooves are arranged on the outer rotary surface of the central ventilation ring 5, so that a first annular air chamber 53 which is communicated with the central through hole 51 is formed between the porous ring 6 and the central ventilation ring 5.
As shown in fig. 2 and 3, the upper thrust bearing component includes an upper thrust bearing base 2 and an upper end cover plate 1, which are coaxially fixed, the upper thrust bearing base 2 is provided with a second central through hole 21, the bottom surface of the upper thrust bearing base 2 is uniformly provided with a plurality of first stepped through holes, a first annular groove is formed at one end of the upper end cover plate 1, which is in contact with the upper thrust bearing base 2, the upper end cover plate 1 is provided with a first through hole 12, the plurality of first stepped through holes and the first through hole 12 are all communicated with the first annular groove, the first through hole 12 is connected to the first central through hole 51 from the outer revolution surface of the upper end cover plate 1, so that a second annular air chamber 11 which is simultaneously communicated with the first through hole 12 and the plurality of first stepped through holes is formed between the upper end cover plate 1 and the upper thrust bearing base 2; and a first local porous throttler 3 is arranged in the counter bore of each first stepped through hole through viscose. The upper end cover plate 1 is connected with the upper thrust bearing base body 2 through threads.
As shown in fig. 2 and 4, the lower thrust bearing component includes a lower thrust bearing base 9 and a lower end cover plate 10 which are coaxially fixed, the lower thrust bearing base 9 is provided with a third central through hole 91, the top surface of the lower thrust bearing base 9 is uniformly provided with a plurality of second stepped through holes, and a second local porous restrictor 8 is arranged in a counter bore of each second stepped through hole through glue. A second annular groove is formed in the lower end cover plate 10 on the surface contacting with the lower thrust bearing base 9, a second through hole 13 is formed in the lower end cover plate 9, the second step through holes and the second through holes 13 are all communicated with the second annular groove, the second through hole 13 is connected to the first central through hole 51 from the outer revolution surface of the lower end cover plate 10, the lower thrust bearing base 9 and the lower end cover plate 10 are fastened and connected through threads, so that a stable third annular air chamber 16 which is simultaneously communicated with the second through hole 13 and the second step through holes is formed between the lower end cover plate 10 and the lower thrust bearing base 9, a stable gas with a certain pressure is provided for the second local porous restrictor 8, in order to discharge the gas smoothly, a groove with a certain width and depth needs to be processed at the bottom of the lower end cover plate 10, as shown in fig. 4, two through holes 15 are axially arranged to penetrate through the lower thrust bearing base 9 and the lower end cover plate 10, and the center distance between the two through holes 15 is equal to the outer diameter of the outer ring 7; the bottom surface of the lower end cover plate 10 is provided with a radial exhaust groove 14, the radial exhaust groove 14 is communicated with the two through holes 15, namely, the bottom of the outer ring 7 at the lower end of the porous ring 6 is provided with an outer chamfer, the bottom of the revolving body 4 is provided with an inner chamfer, an annular groove is formed between the outer chamfer and the inner chamfer, and the tops of the two through holes 15 are communicated with the annular groove. An exhaust channel of the second local porous restrictor 8 and the full-porous hydrostatic radial bearing is formed from the annular groove to the two through holes 15 and then to the radial exhaust groove 14. The through holes 15 are used for smooth discharge of gas, so that a stable gas flow channel is formed.
In the present invention, the second local porous throttle 8 has a larger dimension than the first local porous throttle 3. It is necessary to provide a greater axial load force to suspend the rotary body 4.
As shown in fig. 2, an air supply channel to the first annular air chamber 53 is formed from the first through hole 12 sequentially passing through the second central through hole 21 and the first central through hole 51 to the radial through hole 52 and from the second through hole 13 sequentially passing through the third central through hole 91 and the first central through hole 51 to the radial through hole 52. A gas supply passage to the first local porous restrictor 3 is formed from the first through hole 12 to the first stepped through hole via the second annular gas chamber 11, and a gas supply passage to the second local porous restrictor 8 is formed from the second through hole 13 to the second stepped through hole via the third annular gas chamber 16.
In the present invention, the upper and lower thrust bearing members are separated from the rotating body by a gas film formed by gas passing through the first and second local porous restrictors 3 and 8. The full-porous hydrostatic radial bearing and the rotor are separated from each other by a high-pressure gas through a gas film formed by the full-porous ring 6. In the working state, air is supplied from the air supply holes of the upper thrust bearing part and the lower thrust bearing part, the revolving body 4 can float stably, meanwhile, the full-porous static pressure radial bearing supplies air from the inner center hole to form an air film with the revolving body 4, and ultralow friction and high-precision revolving motion are realized.
The upper thrust bearing base body 2 and the lower thrust bearing base body 9 are both made of stainless steel; the central ventilation ring 5 and the outer ring 7 are both made of aluminum alloy materials.
As shown in fig. 8, the rotor is made of an aluminum alloy material having a lower density, and the machining dimensional accuracy is required to be high, and the bottom end surface a opposed to the lower thrust bearing member is required to have a high surface roughness, and the perpendicularity tolerance of the inner surface B to the bottom end surface a is required to be 0.001, the roundness tolerance thereof is required to be 0.0005, and the coaxiality tolerance of the outer surface C to the inner surface B is required to be 0.001. Evenly distributed threaded holes 19 are machined in the surface opposite to the upper thrust portion.
As shown in fig. 9, the full-porous hydrostatic radial bearing of the present invention requires high machining dimensional accuracy, requires high surface roughness of the bottom end surface D facing the lower thrust bearing member, requires a verticality tolerance of the outer surface E with respect to the bottom end surface D of 0.001, a roundness tolerance of 0.0005, a circle run-out tolerance of 0.001, and a parallelism tolerance of the surface facing the upper thrust bearing member with respect to the bottom end surface D of 0.001.
The upper and lower thrust bearing parts and the full-porous static pressure radial bearing adopt the air supply form of the same air path, the air path structure is ingenious, the revolving body, the upper and lower thrust bearing parts float up by virtue of the porous throttlers uniformly distributed in the revolving body, and the working surfaces of the upper and lower thrust bearing parts are both surfaces which are ground and polished. The working surface of the full-porous hydrostatic radial bearing is an ultraprecisely machined surface, and the verticality tolerance and the roundness tolerance of the end surface of the full-porous hydrostatic radial bearing are high in requirement. The revolving body is completely suspended in a ventilation state, the high processing precision of the revolving body and the homogenization effect of the air film are added, the obtained revolving precision is very high, and the revolving body has high bearing capacity and rigidity in the axial direction and the radial direction and also has good stability.
In summary, the upper and lower thrust bearing components of the present invention are connected to the full-porous hydrostatic radial bearing by uniformly distributed connecting threads, and a stable air film gap is formed by the partial porous thrust bearing and the rotator. The full-porous static pressure radial bearing is positioned in the revolving body, and the zero friction rotation of the revolving part is ensured through the full-porous static pressure radial bearing. The local porous material and the full porous material in the invention have uniform pores and consistent permeability, thereby ensuring that the revolving body has high revolving precision, bearing capacity and static rigidity.
The invention has the outstanding advantages that:
(1) The local porous thrust bearing supports the rotary part, so that the friction between the rotary part and the thrust part is reduced, and the effects of stable support and zero friction are realized theoretically; (2) The full-porous static pressure radial bearing isolates the rotary part through an air film, realizes rotary motion with ultralow friction resistance, and provides high bearing capacity and static rigidity. In addition, the air flow channel structural design of the air floatation rotary platform realizes the unified air supply of the thrust bearing and the radial bearing, and the air flow channel structural design is ingenious, the air exhaust is smooth, and the air floatation rotary platform has the advantages of stable operation and less air consumption.
While the present invention has been described with reference to the accompanying drawings, the present invention is not limited to the above-described embodiments, which are illustrative only and not restrictive, and various modifications which do not depart from the spirit of the present invention and which are intended to be covered by the claims of the present invention may be made by those skilled in the art.
Claims (7)
1. A porous aerostatic rotary platform comprises a rotary body (4), a radial bearing, an upper thrust bearing component and a lower thrust bearing component, and is characterized in that:
the radial bearing is arranged in the revolving body (4), an upper thrust bearing part is coaxially fixed above the radial bearing, and a lower thrust bearing part is coaxially fixed below the radial bearing; the radial bearing is a full-porous static pressure radial bearing, and the upper thrust bearing part and the lower thrust bearing part both adopt a local porous static pressure thrust bearing structure;
the full-porous static pressure radial bearing comprises a central ventilation ring (5), wherein a porous ring (6) is sleeved on the central ventilation ring (5), outer rings (7) are arranged at two ends of the porous ring (6), and the central ventilation ring (5) is provided with a first central through hole (51) and a radial through hole (52) communicated with the first central through hole (51); a circle of annular grooves are formed on the outer rotating surface of the central ventilation ring (5), so that a first annular air chamber (53) communicated with the first central through hole (51) is formed between the porous ring (6) and the central ventilation ring (5);
the upper thrust bearing component comprises an upper thrust bearing base body (2) and an upper end cover plate (1) which are coaxially fixed, wherein the upper thrust bearing base body (2) is provided with a second central through hole (21), the bottom surface of the upper thrust bearing base body (2) is uniformly provided with a plurality of first stepped through holes, a first annular groove is formed in one end, which is in contact with the upper thrust bearing base body (2), of the upper end cover plate (1), a first through hole (12) is formed in the upper end cover plate (1), the plurality of first stepped through holes and the first through hole (12) are communicated with the first annular groove, the first through hole (12) is connected to the first central through hole (51) from the outer revolution surface of the upper end cover plate (1), and therefore a second annular air chamber (11) which is communicated with the first through hole (12) and the plurality of first stepped through holes is formed between the upper thrust bearing base body (2) and the upper end cover plate (1); a first local porous throttler (3) is arranged in the counter bore of each first step through hole;
the lower thrust bearing component comprises a lower thrust bearing base body (9) and a lower end cover plate (10) which are coaxially fixed, a third central through hole (91) is formed in the lower thrust bearing base body (9), a plurality of second stepped through holes are uniformly formed in the top surface of the lower thrust bearing base body (9), a second annular groove is formed in the surface, contacting with the lower thrust bearing base body (9), of the lower end cover plate (10), a second through hole (13) is formed in the lower end cover plate (10), the second stepped through holes and the second through holes (13) are communicated with the second annular groove, the second through holes (13) are connected to the first central through hole (51) from the outer revolution surface of the lower end cover plate (10), and therefore a third annular air chamber (16) which is communicated with the second through holes (13) and the second stepped through holes at the same time is formed between the lower end cover plate (10) and the lower thrust bearing base body (9); a second local porous throttler (8) is arranged in the counter bore of each second step through hole; the second local porous throttle (8) has a dimension larger than that of the first local porous throttle (3);
two through holes (15) are axially formed in the lower thrust bearing base body (9) and the lower end cover plate (10), and the center distance of the two through holes (15) is equal to the outer diameter of the outer ring (7);
the bottom surface of the lower end cover plate (10) is provided with a radial exhaust groove (14), and the radial exhaust groove (14) is communicated with the two through holes (15).
2. The porous aerostatic rotary platform of claim 1, wherein the bottom of the outer ring (7) at the lower end of the porous ring (6) is provided with an outer chamfer, the bottom of the rotary body (4) is provided with an inner chamfer, and an annular groove is formed between the outer chamfer and the inner chamfer, and the top of the two through holes (15) are communicated with the annular groove.
3. The porous aerostatic rotary platform of claim 1, wherein a gas supply channel to the first annular gas chamber (53) is formed from the first through hole (12) through the second central through hole (21) and the first central through hole (51) in order to the radial through holes (52) and from the second through hole (13) through the third central through hole (91) and the first central through hole (51) in order to the radial through holes (52).
4. The porous aerostatic rotary platform of claim 1, wherein a gas supply passage to the first local porous restriction (3) is formed from the first through hole (12) through the second annular gas chamber (11) to the first stepped through hole.
5. The porous aerostatic rotary platform of claim 1, wherein a gas feed passage to the second partial porous restriction (8) is formed from the second through hole (13) through the third annular plenum (16) to the second stepped through hole.
6. The porous aerostatic rotary platform of claim 2, wherein the second local porous restrictor (8) and the exhaust gas passage of the holoporous hydrostatic radial bearing are formed from the annular groove to two through holes (15) and then to the radial exhaust groove (14), respectively.
7. The porous aerostatic rotary platform of claim 1, wherein the outer ring (7) and the central venting ring (5) and the outer ring (7) and the porous ring (6) are connected by a glue (17).
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| Application Number | Priority Date | Filing Date | Title |
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| CN201711414623.3A CN108061096B (en) | 2017-12-22 | 2017-12-22 | Porous gas static pressure rotary platform |
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| CN201711414623.3A CN108061096B (en) | 2017-12-22 | 2017-12-22 | Porous gas static pressure rotary platform |
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| CN108061096A CN108061096A (en) | 2018-05-22 |
| CN108061096B true CN108061096B (en) | 2023-03-14 |
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Families Citing this family (3)
| Publication number | Priority date | Publication date | Assignee | Title |
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| CN109882506A (en) * | 2019-03-28 | 2019-06-14 | 北京工业大学 | A kind of aerostatic bearing structure reducing air film micro-vibration |
| CN114294328A (en) * | 2021-12-28 | 2022-04-08 | 中国航天空气动力技术研究院 | Air-floating type load reversing device with thrust function |
| CN117212338B (en) * | 2023-11-07 | 2024-02-06 | 无锡星微科技有限公司杭州分公司 | High-bearing precision air-floatation turntable |
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| JP2014149056A (en) * | 2013-02-01 | 2014-08-21 | Oiles Ind Co Ltd | Static pressure gas bearing for air spindle |
| CN103111855A (en) * | 2013-02-18 | 2013-05-22 | 哈尔滨工业大学 | Large-diameter-height-ratio ultra-precision hydrostatic pressure rotary table |
| CN104295606A (en) * | 2014-09-23 | 2015-01-21 | 哈尔滨工程大学 | Annular belt compound throttling static-pressure air thrust bearing |
| CN207728729U (en) * | 2017-12-22 | 2018-08-14 | 天津大学 | A kind of porous gas static pressure revolving platform |
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