CN112196908A - Heat radiation structure of dynamic pressure bearing, dynamic pressure thrust bearing and air compressor - Google Patents
Heat radiation structure of dynamic pressure bearing, dynamic pressure thrust bearing and air compressor Download PDFInfo
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- CN112196908A CN112196908A CN202011092843.0A CN202011092843A CN112196908A CN 112196908 A CN112196908 A CN 112196908A CN 202011092843 A CN202011092843 A CN 202011092843A CN 112196908 A CN112196908 A CN 112196908A
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- 230000005855 radiation Effects 0.000 title claims description 3
- 239000011888 foil Substances 0.000 claims abstract description 104
- 238000009423 ventilation Methods 0.000 claims abstract description 37
- 230000017525 heat dissipation Effects 0.000 claims abstract description 28
- 238000005516 engineering process Methods 0.000 abstract description 2
- 239000007789 gas Substances 0.000 description 20
- 239000000112 cooling gas Substances 0.000 description 7
- 238000000034 method Methods 0.000 description 6
- 239000011248 coating agent Substances 0.000 description 4
- 238000000576 coating method Methods 0.000 description 4
- 238000001816 cooling Methods 0.000 description 4
- 230000001050 lubricating effect Effects 0.000 description 4
- 230000009471 action Effects 0.000 description 3
- 230000008569 process Effects 0.000 description 3
- 230000009467 reduction Effects 0.000 description 3
- UFHFLCQGNIYNRP-UHFFFAOYSA-N Hydrogen Chemical compound [H][H] UFHFLCQGNIYNRP-UHFFFAOYSA-N 0.000 description 2
- 238000005299 abrasion Methods 0.000 description 2
- 238000013016 damping Methods 0.000 description 2
- 239000000446 fuel Substances 0.000 description 2
- 239000001257 hydrogen Substances 0.000 description 2
- 229910052739 hydrogen Inorganic materials 0.000 description 2
- 238000004519 manufacturing process Methods 0.000 description 2
- 230000002035 prolonged effect Effects 0.000 description 2
- 230000007704 transition Effects 0.000 description 2
- 238000003466 welding Methods 0.000 description 2
- 230000004888 barrier function Effects 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 238000010438 heat treatment Methods 0.000 description 1
- 239000002184 metal Substances 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 238000003825 pressing Methods 0.000 description 1
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Classifications
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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
- F16C37/00—Cooling of bearings
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
- F04B—POSITIVE-DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS
- F04B39/00—Component parts, details, or accessories, of pumps or pumping systems specially adapted for elastic fluids, not otherwise provided for in, or of interest apart from, groups F04B25/00 - F04B37/00
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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
- F16C17/00—Sliding-contact bearings for exclusively rotary movement
- F16C17/04—Sliding-contact bearings for exclusively rotary movement for axial load only
- F16C17/042—Sliding-contact bearings for exclusively rotary movement for axial load only with flexible leaves to create hydrodynamic wedge, e.g. axial foil bearings
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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
- F16C17/00—Sliding-contact bearings for exclusively rotary movement
- F16C17/04—Sliding-contact bearings for exclusively rotary movement for axial load only
- F16C17/08—Sliding-contact bearings for exclusively rotary movement for axial load only for supporting the end face of a shaft or other member, e.g. footstep bearings
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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
- F16C2300/00—Application independent of particular apparatuses
- F16C2300/20—Application independent of particular apparatuses related to type of movement
- F16C2300/22—High-speed rotation
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- Engineering & Computer Science (AREA)
- General Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Physics & Mathematics (AREA)
- Fluid Mechanics (AREA)
- Support Of The Bearing (AREA)
Abstract
The application relates to the air bearing technology, and provides a heat dissipation structure of a dynamic pressure bearing, a dynamic pressure thrust bearing and an air compressor. The heat dissipation structure of the dynamic pressure bearing comprises a plurality of blades and a ventilation channel; the blades are arranged on a rotor of the dynamic pressure bearing, the ventilation channel is positioned between the rotor and a rotor of the dynamic pressure bearing, the ventilation channel comprises an air inlet and an air outlet, the blades are positioned in the ventilation channel, the air outlet is communicated with a space between a thrust disc of the dynamic pressure bearing and a bearing seat, and the blades are driven by the rotor to rotate so as to form bias voltage from the air inlet to the air outlet, so that air flow is driven to blow to the air outlet. The blown gas can take away the heat generated on the parts such as the top foil, the arch foil, the thrust bearing and the like of the axial bearing.
Description
Technical Field
The present disclosure relates to air bearings, and particularly to a heat dissipation structure of a dynamic pressure bearing, a dynamic pressure thrust bearing, and an air compressor.
Background
The gas dynamic pressure bearing with elastic foil is a special bearing with high rotation speed, high running precision, low loss and high temperature resistance. The elastic foil aerodynamic bearing is composed of a radial elastic foil aerodynamic bearing and an axial elastic foil aerodynamic bearing, the radial bearing is mainly composed of top foil, arch foil, a bearing seat and other parts, and the axial bearing is composed of the top foil, the arch foil, the bearing seat and a thrust bearing.
Each bearing seat is composed of a plurality of fan-shaped arch foils and a plurality of top foils, one ends of the arch foils and the top foils are welded on the bearing seats, the other ends of the arch foils and the top foils are free, and the welding ends are slightly lower than the free ends to form air wedge angles. When the bearing normally runs, a layer of air film is formed between the top foil and the thrust bearing, so that the thrust bearing axially floats. The arched foil is a foil with a plurality of arches, which provides an elastic base for the top foil, determining the supporting stiffness of the top foil surface.
The top foil and the wave foil are both in fan shapes, the surface of the top foil is smooth, and the top foil and the thrust disk rotate relatively to form a circumferential wedge-shaped gap and generate a dynamic pressure air film to provide axial supporting force; the bump foil is arranged below the flat foil and fixedly connected to the bearing seat, and mainly plays a role in providing rigidity and damping.
However, when the axial foil bearing operates at a very high speed, the running clearance between the thrust disk and the axial top foil is generally about 1 to 10 wires (0.01 to 0.1mm), so that serious wind abrasion loss is generated, and the axial bearing generates heat seriously.
Disclosure of Invention
In order to solve the technical problem of poor heat dissipation of the dynamic pressure bearing in the technology, the application provides a heat dissipation structure of the dynamic pressure bearing, a dynamic pressure thrust bearing and an air compressor.
In a first aspect, the present application provides a heat dissipation structure for a hydrodynamic bearing, including a plurality of blades and a ventilation channel; the blades are arranged on a rotor of the dynamic pressure bearing, the ventilation channel is positioned between the rotor and a rotor of the dynamic pressure bearing, the ventilation channel comprises an air inlet and an air outlet, the blades are positioned in the ventilation channel, the air outlet is communicated with a space between a thrust disc of the dynamic pressure bearing and a bearing seat, and the blades are driven by the rotor to rotate so as to form bias voltage from the air inlet to the air outlet, so that air flow is driven to blow to the air outlet.
In an embodiment of the present application, the rotor further includes a shaft sleeve, and the blades are disposed on the shaft sleeve, and the shaft sleeve is fixedly assembled to the rotor.
In an embodiment of the present application, the shaft sleeve further has an air guiding portion, and the air guiding portion is located on a side away from the blade to guide air toward the air outlet.
In an embodiment of the present application, an axis of the air inlet is perpendicular to an axis of the air outlet.
Another aspect of the present application provides a dynamic pressure thrust bearing including the heat dissipating structure of the dynamic pressure bearing as described above.
In an embodiment of the application, the bearing seat further comprises a bearing seat, an arch foil and a top foil, wherein a plurality of groups of the arch foil and the top foil are arranged on one side surface of the bearing seat facing the thrust disk, and a ventilation channel of the heat dissipation structure is formed between the bearing seat and the rotating shaft.
In an embodiment of the present application, there are two sets of the dynamic pressure thrust bearings, which respectively act on two sides of the thrust plate, wherein: the heat dissipation structure is provided with two groups of dynamic pressure bearings, is symmetrically arranged relative to the thrust disk and guides wind from the outer side to the direction of the thrust disk.
In an embodiment of the present application, two sets of the dynamic pressure thrust bearings are provided, and are respectively applied to two sides of the thrust plate, a set of the heat dissipation structure of the dynamic pressure bearing is provided, and is located on one side of the thrust plate, and the ventilation channel is simultaneously communicated with dynamic pressure fit spaces on two sides of the thrust plate.
In an embodiment of the present application, the bearing seat inner hole is larger than the outer diameter of the rotating shaft to form the ventilation channel therebetween.
In another aspect of the present application, it is also believed to provide an air compressor including a dynamic pressure thrust bearing as previously described. Specifically, the air compressor may be an ultra-high-speed oil-free air compressor applied to a hydrogen fuel cell engine.
Compared with the prior art, the technical scheme provided by the embodiment of the application has the following advantages:
according to the heat dissipation structure provided by the embodiment of the application, the heat dissipation fan is arranged on one side of the thrust disc, when the rotor runs at a high speed, normal-temperature gas on two sides of the axial bearing is sucked into the axial bearing, and most of the gas entering the axial bearing passes through the space between the arch foil and the top foil and also a small part of the gas enters the space between the top foil of the axial bearing and the thrust bearing. The cooling gas can take away the heat generated on the top foil, the arch foil, the thrust bearing and other parts of the axial bearing. Meanwhile, a small amount of gas entering between the top foil and the thrust bearing can improve the bearing capacity of the axial bearing and reduce the takeoff rotating speed.
Drawings
The accompanying drawings, which are incorporated in and constitute a part of this specification, illustrate embodiments consistent with the invention and together with the description, serve to explain the principles of the invention.
In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings used in the description of the embodiments or the prior art will be briefly described below, and it is obvious for those skilled in the art that other drawings can be obtained according to the drawings without inventive exercise.
Fig. 1 is a schematic cross-sectional view of a dynamic pressure thrust bearing according to an embodiment of the present disclosure.
Fig. 2 is a schematic structural diagram of a heat dissipation portion of a dynamic thrust bearing provided in an embodiment of the present application.
Fig. 3 is a schematic view of cooling air flow of a dynamic pressure thrust bearing provided in an embodiment of the present application.
Detailed Description
In order to make the objects, technical solutions and advantages of the embodiments of the present application clearer, the technical solutions in the embodiments of the present application will be clearly and completely described below with reference to the drawings in the embodiments of the present application, and it is obvious that the described embodiments are some embodiments of the present application, but not all embodiments. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present application.
In a first aspect, the present application provides a heat dissipation structure 2 for a hydrodynamic bearing, which mainly includes a plurality of blades 21 and a ventilation channel. The blades 21 are arranged on a rotor of the dynamic pressure bearing, the ventilation channel is located between the rotor and a rotor of the dynamic pressure bearing, the ventilation channel comprises an air inlet and an air outlet, the blades are located in the ventilation channel, the air outlet is communicated with a space between the thrust disc 6 and the bearing seat 3 of the dynamic pressure bearing, and the blades 21 are driven by the rotor to rotate so as to form bias voltage from the air inlet to the air outlet, so that air flow is driven to blow to the air outlet.
According to the structure of the thrust disc, the two cooling fans are arranged on the two sides of the thrust disc, when the rotor runs at a high speed, normal-temperature gas on the two sides of the axial bearing is sucked into the axial bearing, and most of the gas entering the axial bearing passes through the space between the arch foil and the top foil and also a small part of the gas enters the space between the top foil of the axial bearing and the thrust bearing. The cooling gas can take away the heat generated on the top foil, the arch foil, the thrust bearing and other parts of the axial bearing. Meanwhile, a small amount of gas entering between the top foil and the thrust bearing can improve the bearing capacity of the axial bearing and reduce the takeoff rotating speed.
It will be understood by those skilled in the art that the ventilation passage provided in the embodiments of the present application between the stationary and rotating bearing components generally includes a passage in the axial direction of the rotating shaft (rotating component) and connected to the radial direction fitting gap between the thrust bearing and the thrust disk 6, or referred to as a radial ventilation passage. In the embodiment of the present invention, the plurality of blades 21 are selectively disposed at a position close to the air inlet of the axial passage.
In an embodiment of the present application, the heat dissipation structure 2 may further include a shaft sleeve 22 to facilitate manufacturing and assembling, the blade 21 is disposed on the shaft sleeve 22, and the shaft sleeve 22 is fixedly assembled on the rotor. The vanes 21 and the hub 22 may be integrally formed and then fixedly mounted to the shaft by interference fit or other shaft mounting means for rotation with the shaft to facilitate the rotation of the vanes 21 to generate the bias. Wherein the axis of the air inlet of the ventilation channel is perpendicular to the axis of the air outlet, that is, the shape of the blade 21 is selected to be the channel blade shape of the axial flow blade. In yet another embodiment, the blade 21 may be positioned at the junction of the axial and radial passages of the ventilation passage, and may be in the form of a centrifugal blade, which is generally positioned radially outward as much as possible according to the experience of the fan field, so as to obtain a greater centrifugal bias. The shaft sleeve 22 further has a wind guiding portion, and the wind guiding portion 22 is located on a side away from the blades 21 to guide wind toward the wind outlet. In one embodiment, the air guiding portion may be selected as an arc transition from the shaft sleeve 22 to the radial direction, so as to guide the axial wind to the radial air flow.
Another aspect of the present application provides a dynamic pressure thrust bearing including the heat dissipating structure of the dynamic pressure bearing as described above. The dynamic pressure thrust bearing comprises a bearing seat 3, an arch foil 4 and a top foil 5, wherein a plurality of groups of arch foils 4 and top foils 5 are arranged on one side surface of the bearing seat 3 facing the thrust disc 6, and a ventilation channel of the heat dissipation structure is formed between the bearing seat 3 and the rotating shaft 1.
In one embodiment of the present application, there are two sets of the dynamic thrust bearings, which respectively act on two sides of the thrust disk 6, wherein: and the heat dissipation structure is provided with two groups of dynamic pressure bearings, is symmetrically arranged relative to the thrust disk 6 and guides wind from the outer side to the direction of the thrust disk 6.
In an embodiment of the present application, two sets of the dynamic pressure thrust bearings are provided, which act on two sides of the thrust disk 6 respectively, a set of the heat dissipation structure of the dynamic pressure bearing is provided, which is located on one side of the thrust disk 6, and the ventilation channel is simultaneously connected to the dynamic pressure fit space on two sides of the thrust disk 6.
In one embodiment of the present application, the inner hole of the bearing seat 3 is larger than the outer diameter of the rotating shaft 1, so as to form the ventilation channel therebetween.
The structure mainly comprises an axial bearing stator, a thrust bearing, a cooling fan, a rotating shaft and other parts; the axial bearing stator mainly comprises an axial bearing seat 3, a second bearing seat 9, an arch foil 4, a second arch foil 8, a top foil 5 and a second top foil 7, wherein the top foil 5 and the second top foil 7 are provided with a layer of wear-resistant lubricating coating.
The front axial bearing seat 3 and the rear axial second bearing seat 9 are of a disc structure with smooth surfaces, are distributed on two sides of the thrust disc 6, and are supports of front and rear axial foil bearings.
The axial bearing seat on each side is provided with at least three fan-shaped arch foils, each arch foil is uniformly distributed in a circumferential scheme, each arch foil is of an arch structure formed by pressing metal foil, one end of each arch foil is fixed on the bearing seat, the other end of each arch foil is fixed and free, when the arch foils are pressed by the top foils, the arches are compressed downwards and extend towards the free ends of the arch foils, when the rotor has axial vibration, the arch foils are continuously compressed downwards and released upwards, the free ends are continuously extended and contracted to absorb and consume energy from the axial vibration of the rotor, and the rigidity of the axial foil dynamic pressure bearing is provided with damping.
The top layer foil is of a fan-shaped structure with wedge-shaped areas, the top foil is located above the arched foils, the starting positions of the wedge-shaped areas are fixed on the bearing seat, the number of the top layer foils is equal to that of the arched foils, and the top foil is just capable of covering the arched foils in size.
The thrust disc 6 is of a disc structure, is fixed on the rotating shaft, is in interference fit or welding fit with the rotating shaft, rotates at a high speed along with the rotating shaft, drives the gas in the top foil wedge-shaped area to extrude towards the bearing area, and improves the pressure of the top foil bearing area. Thereby axially levitating the thrust disk.
The heat dissipation structures 2 are distributed on two sides of the thrust disc 6, fixed on the rotor and in interference fit or welded fixation with the rotor, when the rotating shaft rotates at a high speed, the heat dissipation fan can be driven to rotate at a high speed, gas on two sides of the axial bearing is blown into the axial bearing, and a large amount of heat generated by the axial bearing due to windmilling loss is taken away through the space between the arch foil and the bearing seat, the space between the arch foil and the top foil and the space between the top foil and the bearing seat.
In the dynamic thrust bearing of the present embodiment, the heat dissipating structure 2 mainly includes a plurality of blades 21 and a ventilation passage. The blades 21 are arranged on a rotor of the dynamic pressure bearing, the ventilation channel is located between the rotor and a rotor of the dynamic pressure bearing, the ventilation channel comprises an air inlet and an air outlet, the blades are located in the ventilation channel, the air outlet is communicated with a space between the thrust disc 6 and the bearing seat 3 of the dynamic pressure bearing, and the blades 21 are driven by the rotor to rotate so as to form bias voltage from the air inlet to the air outlet, so that air flow is driven to blow to the air outlet.
According to the structure of the thrust disc, the two cooling fans are arranged on the two sides of the thrust disc, when the rotor runs at a high speed, normal-temperature gas on the two sides of the axial bearing is sucked into the axial bearing, and most of the gas entering the axial bearing passes through the space between the arch foil and the top foil and also a small part of the gas enters the space between the top foil of the axial bearing and the thrust bearing. The cooling gas can take away the heat generated on the top foil, the arch foil, the thrust bearing and other parts of the axial bearing. Meanwhile, a small amount of gas entering between the top foil and the thrust bearing can improve the bearing capacity of the axial bearing and reduce the takeoff rotating speed.
It will be understood by those skilled in the art that the ventilation passage provided in the embodiments of the present application between the stationary and rotating bearing components generally includes a passage in the axial direction of the rotating shaft (rotating component) and connected to the radial direction fitting gap between the thrust bearing and the thrust disk 6, or referred to as a radial ventilation passage. In the embodiment of the present invention, the plurality of blades 21 are selectively disposed at a position close to the air inlet of the axial passage.
In an embodiment of the present application, the heat dissipation structure 2 may further include a shaft sleeve 22 to facilitate manufacturing and assembling, the blade 21 is disposed on the shaft sleeve 22, and the shaft sleeve 22 is fixedly assembled on the rotor. The vanes 21 and the hub 22 may be integrally formed and then fixedly mounted to the shaft by interference fit or other shaft mounting means for rotation with the shaft to facilitate the rotation of the vanes 21 to generate the bias. Wherein the axis of the air inlet of the ventilation channel is perpendicular to the axis of the air outlet, that is, the shape of the blade 21 is selected to be the channel blade shape of the axial flow blade. In yet another embodiment, the blade 21 may be positioned at the junction of the axial and radial passages of the ventilation passage, and may be in the form of a centrifugal blade, which is generally positioned radially outward as much as possible according to the experience of the fan field, so as to obtain a greater centrifugal bias. The shaft sleeve 22 further has a wind guiding portion, and the wind guiding portion 22 is located on a side away from the blades 21 to guide wind toward the wind outlet. In one embodiment, the air guiding portion may be selected as an arc transition from the shaft sleeve 22 to the radial direction, so as to guide the axial wind to the radial air flow.
In another aspect of the present application, it is also believed to provide an air compressor including a dynamic pressure thrust bearing as previously described. Specifically, the air compressor may be an ultra-high-speed oil-free air compressor applied to a hydrogen fuel cell engine.
The dynamic thrust bearing of any of the foregoing embodiments may be applied to a main shaft of an oil-free air compressor, and may be disposed at one axial end of the main shaft, or at both axial ends. The heat dissipation device is applied to the ultra-high-speed oil-free air compressor with better heat dissipation effect, and can obviously improve the stability and the stability duration of the whole machine.
The embodiment of the application solves the problem that the axial bearing generates heat seriously due to the ultra-high-speed operation of the thrust bearing. The heat dissipation fans on the two sides of the thrust disc can take away a large amount of heat generated on the thrust bearing and the bearing stator when the rotor runs at a high speed, so that failure of a lubricating coating caused by overhigh temperature rise of a top layer foil is avoided, and reduction and even locking of an axial gap caused by overhigh temperature rise of the thrust bearing and the axial bearing (thermal barrier shrinkage of a part, reduction of the axial gap of the part when the temperature rises) are also avoided.
The structure of the embodiment of the application increases the bearing capacity of the axial bearing and reduces the takeoff rotating speed of the axial bearing. Because a part of cooling gas passes through the wedge-shaped area between the thrust bearing and the top foil, the pressure of the wedge-shaped area and the pressure of the bearing area are higher, the bearing capacity of the bearing is increased, and the takeoff rotating speed of the bearing is reduced.
When the axial bearing structure provided by the embodiment of the application runs at a high speed, the heat dissipation fans fixed on two sides of the thrust plate can blow a large amount of cooling gas into the axial bearing, and the cooling gas can carry away a large amount of heat through the space between the arch foil and the bearing seat, the space between the arch foil and the top foil and the space between the top foil and the thrust plate, so that the overhigh temperature rise caused by large windmilling loss during the running of the axial bearing is avoided; the lubricating coating on the top foil can be prevented from losing efficacy, and the service life of the lubricating coating is prolonged, so that the service life of the axial bearing is prolonged; the locking of the axial bearing caused by overhigh temperature rise can be avoided (the clearance of the axial bearing is dozens of microns, and when the temperature is overhigh, the axial bearing stator and the thrust disc expand due to heating to cause the clearance of the axial bearing to be reduced or even locked), and the reliability of the bearing is improved. Because part of gas enters a wedge-shaped area and a bearing area between the top foil and the thrust bearing, the bearing capacity of the axial bearing can be improved by more than 20 percent, the takeoff rotating speed is reduced by more than 20 percent, the bearing capacity of the axial bearing is greatly improved, and the reliability is improved; the reduction of the takeoff rotating speed is beneficial to reducing the dry friction of the bearing before takeoff, reducing the friction and abrasion of the bearing and prolonging the service life of the bearing.
Compared with the prior art, the technical scheme provided by the embodiment of the application has the following advantages:
according to the heat dissipation structure provided by the embodiment of the application, the heat dissipation fan is arranged on one side of the thrust disc, when the rotor runs at a high speed, normal-temperature gas on two sides of the axial bearing is sucked into the axial bearing, and most of the gas entering the axial bearing passes through the space between the arch foil and the top foil and also a small part of the gas enters the space between the top foil of the axial bearing and the thrust bearing. The cooling gas can take away the heat generated on the top foil, the arch foil, the thrust bearing and other parts of the axial bearing. Meanwhile, a small amount of gas entering between the top foil and the thrust bearing can improve the bearing capacity of the axial bearing and reduce the takeoff rotating speed.
It is noted that, in this document, relational terms such as "first" and "second," and the like, may be used solely to distinguish one entity or action from another entity or action without necessarily requiring or implying any actual such relationship or order between such entities or actions. Also, the terms "comprises," "comprising," or any other variation thereof, are intended to cover a non-exclusive inclusion, such that a process, method, article, or apparatus that comprises a list of elements does not include only those elements but may include other elements not expressly listed or inherent to such process, method, article, or apparatus. Without further limitation, an element defined by the phrase "comprising an … …" does not exclude the presence of other identical elements in a process, method, article, or apparatus that comprises the element.
The foregoing are merely exemplary embodiments of the present invention, which enable those skilled in the art to understand or practice the present invention. Various modifications to these embodiments will be readily apparent to those skilled in the art, and the generic principles defined herein may be applied to other embodiments without departing from the spirit or scope of the invention. Thus, the present invention is not intended to be limited to the embodiments shown herein but is to be accorded the widest scope consistent with the principles and novel features disclosed herein.
Claims (10)
1. A heat radiation structure of a dynamic pressure bearing is characterized by comprising a plurality of blades (21) and a ventilation channel; the blades (21) are arranged on a rotor of the dynamic pressure bearing, the ventilation channel is located between a rotor and a rotor of the dynamic pressure bearing, the ventilation channel comprises an air inlet and an air outlet, the blades are located in the ventilation channel, the air outlet leads to a space between a thrust disc (6) and a bearing seat (3) of the dynamic pressure bearing, and the blades (21) are driven by the rotor to rotate so as to form bias voltage from the air inlet to the air outlet, so that air flow is driven to blow to the air outlet.
2. The heat dissipating structure of a hydrodynamic bearing as set forth in claim 1, further comprising a boss (22), wherein the vane (21) is disposed on the boss (22), and the boss (22) is fixedly assembled to the rotor.
3. The heat dissipating structure of a dynamic pressure bearing according to claim 2, wherein the boss (22) further has a wind guide portion, and the wind guide portion (22) is located on a side away from the vane (21) to guide wind in the direction of the wind outlet.
4. The heat dissipating structure of a hydrodynamic bearing as claimed in any one of claims 1 to 3, wherein the axis of the air inlet is perpendicular to the axis of the air outlet.
5. A hydrodynamic thrust bearing comprising the heat dissipating structure of a hydrodynamic bearing according to any one of claims 1 to 4.
6. The thrust hydrodynamic bearing according to claim 5, further comprising a bearing seat (3), an arched foil (4) and a top foil (5), wherein a plurality of sets of the arched foil (4) and the top foil (5) are disposed on a side of the bearing seat (3) facing the thrust disk (6), and the ventilation channel of the heat dissipation structure is formed between the bearing seat (3) and the rotating shaft (1).
7. The thrust hydrodynamic bearing according to claim 6, characterized in that there are two groups of thrust hydrodynamic bearings, acting on either side of said thrust disk (6), wherein: the heat dissipation structure is provided with two groups of dynamic pressure bearings, is symmetrically arranged relative to the thrust disc (6), and guides wind from the outer side to the thrust disc (6).
8. The thrust hydrodynamic bearing according to claim 6, characterized in that there are two sets of thrust hydrodynamic bearings acting on both sides of said thrust disk (6), respectively, and there are one set of heat dissipating structures of said thrust hydrodynamic bearings located on one side of said thrust disk (6), said ventilation channels simultaneously communicating with the space for hydrodynamic fit on both sides of said thrust disk (6).
9. The thrust hydrodynamic bearing according to any of the claims 6 to 8, characterized in that the inner bore of the bearing housing (3) is larger than the outer diameter of the rotating shaft (1) to form the ventilation channel therebetween.
10. An air compressor comprising the dynamic pressure thrust bearing of any one of claims 5 to 9.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202011092843.0A CN112196908B (en) | 2020-10-13 | 2020-10-13 | Heat radiation structure of dynamic pressure bearing, dynamic pressure thrust bearing and air compressor |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202011092843.0A CN112196908B (en) | 2020-10-13 | 2020-10-13 | Heat radiation structure of dynamic pressure bearing, dynamic pressure thrust bearing and air compressor |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN112196908A true CN112196908A (en) | 2021-01-08 |
| CN112196908B CN112196908B (en) | 2021-09-14 |
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| CN202011092843.0A Active CN112196908B (en) | 2020-10-13 | 2020-10-13 | Heat radiation structure of dynamic pressure bearing, dynamic pressure thrust bearing and air compressor |
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Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113266533A (en) * | 2021-06-02 | 2021-08-17 | 安徽三联学院 | Aerogenerator gear box with heat radiation structure |
| CN113266596A (en) * | 2021-06-02 | 2021-08-17 | 北京智拓博科技有限公司 | Pneumatic suspension centrifugal refrigeration compressor and axial bearing structure thereof |
| CN114151446A (en) * | 2021-12-15 | 2022-03-08 | 珠海格力电器股份有限公司 | Air suspension bearing assembly, motor and air compressor |
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| CN113266533A (en) * | 2021-06-02 | 2021-08-17 | 安徽三联学院 | Aerogenerator gear box with heat radiation structure |
| CN113266596A (en) * | 2021-06-02 | 2021-08-17 | 北京智拓博科技有限公司 | Pneumatic suspension centrifugal refrigeration compressor and axial bearing structure thereof |
| CN114151446A (en) * | 2021-12-15 | 2022-03-08 | 珠海格力电器股份有限公司 | Air suspension bearing assembly, motor and air compressor |
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