CN113007211A - High-heat-dissipation-rate foil type axial thrust bearing, combined bearing and heat management method - Google Patents
High-heat-dissipation-rate foil type axial thrust bearing, combined bearing and heat management method Download PDFInfo
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- CN113007211A CN113007211A CN202110178029.9A CN202110178029A CN113007211A CN 113007211 A CN113007211 A CN 113007211A CN 202110178029 A CN202110178029 A CN 202110178029A CN 113007211 A CN113007211 A CN 113007211A
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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
- F16C17/26—Systems consisting of a plurality of sliding-contact 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
- F16C37/00—Cooling of 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
- F16C2380/00—Electrical apparatus
- F16C2380/26—Dynamo-electric machines or combinations therewith, e.g. electro-motors and generators
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- General Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Physics & Mathematics (AREA)
- Fluid Mechanics (AREA)
- Support Of The Bearing (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
- Mounting Of Bearings Or Others (AREA)
Abstract
The invention relates to a foil type axial thrust bearing with high heat dissipation rate, a combined bearing and a bearing heat management method.A plane boss is additionally arranged in the center of a base, end face cooling air grooves are additionally arranged on the boss, the number and the positions of the cooling air grooves correspond to the corrugation design and the positions of corrugated elastic foils, the boss provides support for the corrugated elastic foils on one hand, the end face cooling air grooves are convenient to process, the radial cooling of the thrust bearing is convenient to process, and on the other hand, the boss increases the gap between the thrust bearing and the surface of the combined bearing base, so that more choices are provided for the design of a cooling flow channel of the whole bearing system. The end face cooling air groove expands the area of a cooling air flow channel, reduces flow resistance and increases the flow of cooling air, so that the cooling heat transfer effect of the smooth foil and the corrugated elastic foil is enhanced, and the temperature of the thrust bearing is reduced.
Description
Technical Field
The invention relates to the technical field of thermal management of air foil type bearings, in particular to a high-heat-dissipation-rate foil type axial thrust bearing, a combined bearing and a thermal management method.
Background
A fuel cell is a device that directly converts chemical energy of hydrogen and oxygen into electrical energy through an electrode reaction. Wherein, the products after the chemical reaction of hydrogen and oxygen are mainly water and heat. Thus, fuel cells are considered to be a highly likely alternative to conventional fuel as a major source of future automotive power due to their clean nature. Current research and application of fuel cells for automotive power is mainly focused on Proton Exchange Membrane Fuel Cells (PEMFCs). In the core technology of the fuel cell, the electric stack can be compared with the heart of the fuel cell and is the core of generating electric energy, and the air compressor can be called as the lung of the fuel cell and provides proper oxygen for the heart. The air compressor must meet the requirements of oil-free, miniaturization, low cost, low noise and low power consumption. Therefore, the bearing of the air compressor generally adopts a foil type air bearing.
The heat distribution in foil-type aerodynamic bearings is caused by the combined action of internal and external factors. The temperature rise inside the foil type aerodynamic bearing is mainly aerodynamic heat generated by the friction inside the air film when the rotating shaft 404 rotates, the heat capacity of air is low, for the foil type aerodynamic bearing with no cooling design, the unique structure is that the supporting points of the corrugated elastic foil 402 are in line contact with the top smooth foil 403 and the bearing shell 401, as shown in fig. 1 and 2, the concave-convex structure of the corrugated elastic foil 402 separates the top smooth foil 403 from the bearing shell 401 by line contact, the outward (shell direction) conduction of heat is limited, and further, the air film rapidly transfers the heat to the thinner top smooth foil 403, so that most of the heat flows into the rotating shaft 404, as shown in fig. 3, about 80% of the heat is absorbed by the rotating shaft 404 and the bearing through heat conduction, and only about 20% of the heat is dissipated to the surrounding air through side leakage convection. Therefore, a large amount of heat generated in the foil type aerodynamic bearing is difficult to be rapidly conducted out.
Foil type aerodynamic bearing performance may be affected in various ways if the local temperature of the air compressor continues to rise:
(1) overheating of the corrugated flex 402 material will result: the corrugated elastic foil 402 is usually made of nickel-based superalloy Inconel, and its elastic modulus decreases with increasing temperature, resulting in a softening effect that increases the flexibility of the foil-type aerodynamic bearing, thereby reducing the maximum load capacity of the foil-type aerodynamic bearing; furthermore, studies have shown that the stiffness (and possibly damping) characteristics of foil-type aerodynamic bearings can vary accordingly, which can have a significant impact on the rotor dynamics of the system.
(2) The top smooth foil 403 coating performance is severely affected; in order to reduce the cost of the fuel cell air compressor, the foil type air power bearing of the fuel cell air compressor generally uses a low-temperature coating with simple process, the working temperature of the low-temperature coating is generally required to be below 200 ℃, and the performance of the coating is reduced and even the coating falls off due to overhigh temperature.
(3) Foil type aerodynamic bearings may also develop self-sustained cycling (i.e. thermal runaway) phenomena, leading to catastrophic failure; since the shaft 404 absorbs most of the heat during the bearing operation, the shaft expands faster than the bearing, thereby increasing the bearing preload, which, as the bearing preload continues to increase, as does the additional radial load between the shaft 4 and the bearing, amplifies the stress on the fluid film and causes additional heat generation and further expansion of the shaft, thereby causing the self-sustained cycle (i.e., thermal runaway) to appear.
(4) In the axial direction, the temperature cannot be timely transferred, an excessive axial thermal gradient is formed from the inner part to the axial edge of the foil type aerodynamic bearing, the excessive axial thermal gradient can cause the top smooth foil to generate distortion deformation, further the formation of the gas film 405 is disturbed or the gas film 405 cannot be completely formed, and the bearing can be failed at high speed and/or high load level.
At present, researches on air foil bearings at home and abroad are on the structural design for improving the bearing capacity of the bearing, the research on internal high temperature mainly focuses on the coating technology, and the technology for carrying out thermal management on the coating technology is basically blank. Although one can achieve bearing cooling by forcing air flow through the bearing gaps, the effect is not very obvious because the gaps are small, the channel flow resistance is large, and the amount of cooling air is too small. Along with the increase of the power of the fuel cell stack, the power of the air compressor motor is increased, and the diameter of the rotating shaft is increased. The aerodynamic heat dissipation of the air bearing is determined by the following equation:
P＝kD4L (1)
wherein P is aerodynamic heat, K is a coefficient related to a specific design and a working medium, D is a diameter of a rotating shaft, and L is a length of a bearing.
From the formula, the aerodynamic heat dissipation power of the air bearing is greatly increased along with the increase of the diameter of the rotating shaft.
Disclosure of Invention
The invention provides a high-heat-dissipation-rate foil type axial thrust bearing, a combined bearing and a heat management method.
The technical scheme of the invention is as follows:
a high-heat-dissipation-rate foil type axial thrust bearing comprises a base body and a plurality of fan-shaped annular foil sets, wherein an annular boss is coaxially arranged on the end face of the base body, and the plurality of fan-shaped annular foil sets are circumferentially and centrally symmetrically arranged on the end face of the annular boss; each fan-ring-shaped foil group comprises a smooth foil and a corrugated elastic foil, and the corrugated elastic foil and the smooth foil are fan-ring-shaped and are sequentially stacked and then fixed on the ring-shaped boss; and the upper surface of the boss is provided with an end face cooling air groove corresponding to the upper convex part of the corrugation elastic foil.
Preferably, a lateral edge of the corrugated elastic foil is provided with a fixed connection part, the fixed connection part is arranged along the radial direction of the boss, convex parts on the corrugation of the corrugated elastic foil are parallel to the fixed connection part, and correspondingly, the end face cooling air groove is parallel to the fixed connection part and extends to the radial outer surface of the boss from the shaft hole of the boss.
Preferably, the corrugated elastic foil includes at least 1 complete corrugated upper protrusion extending from its inner edge to its outer edge, and the end face cooling air groove is opened on the upper surface of the boss corresponding to the position of the complete corrugated upper protrusion.
Preferably, the corrugated flexible foil is divided by one or more fan-shaped annular gaps starting from the fastening portion into a plurality of fan-shaped annular foil flaps distributed radially.
Preferably, the end face cooling air groove is a wedge-shaped through groove, or a through groove with a semicircular or rectangular axial section.
Preferably, the plurality of foil sets are arranged on the end face of the boss in a central symmetry manner and are not overlapped with each other, and a radial gap is formed between the side edges of the adjacent foil sets.
The utility model provides a high heat dissipation rate foil type combination bearing, includes high heat dissipation rate foil type journal bearing and foretell high heat dissipation rate foil type thrust bearing, high heat dissipation rate foil type thrust bearing's non-working end face with high heat dissipation rate foil type journal bearing's bearing housing side end face is coaxial to be linked to each other, or high heat dissipation rate foil type thrust bearing's non-working end face side is along axial, the outside formation that extends high heat dissipation rate foil type journal bearing's bearing housing.
Preferably, the inner surface of the foil radial bearing is coaxial and is sequentially provided with an axial corrugated elastic foil and an axial smooth foil along the radial direction, the outer surface of the axial smooth foil is in contact with the tops of the corrugated inner convex parts of the axial corrugated elastic foil and corresponds to the corrugated inner convex parts of the axial corrugated elastic foil, the inner surface of the bearing shell is provided with an axial cooling air groove, one side edge of the axial corrugated elastic foil is provided with a fixing part, the fixing part is arranged along the axial direction of the bearing shell, the corrugated inner convex parts of the corrugated elastic foil are all parallel to the axial direction of the bearing shell, and the cooling air groove is parallel to the fixing part and extends from one side end face of the bearing shell to the other side end face.
The utility model provides a high heat dissipation rate foil type bearing heat management method, uses foretell high heat dissipation rate foil type thrust bearing and foretell high heat dissipation rate foil type combination bearing, cooling air current from the rotor shaft warp high heat dissipation rate foil type thrust bearing's terminal surface cooling air groove, with the work terminal surface of high heat dissipation rate foil type thrust bearing carries out the heat exchange and then gets into high heat dissipation rate foil type combination bearing's terminal surface cooling air groove, with high heat dissipation rate foil type combination bearing's work terminal surface carries out the heat exchange, and passes through high heat dissipation rate foil type combination bearing's axial cooling air groove, with the internal surface of bearing housing carries out the discharge after the heat exchange.
Preferably, the end face cooling air groove of the high-heat-dissipation-rate foil type axial thrust bearing and the end face cooling air groove of the high-heat-dissipation-rate foil type combined bearing are oppositely arranged and have opposite rotation directions.
Compared with the prior art, the invention has the advantages that:
1. the axial thrust bearing is used for providing axial thrust for the high-speed rotating structure. Different from a common thrust bearing structure, the high-heat-dissipation-rate foil type axial thrust bearing, the combined bearing and the bearing heat management method are characterized in that a plane boss is additionally arranged in the center of a base, end face cooling air grooves are additionally formed in the boss, the number and the positions of the cooling air grooves correspond to the corrugated design and the positions of the corrugated elastic foils, the boss provides support for the corrugated elastic foils on one hand, the end face cooling air grooves are convenient to process, radial cooling of the thrust bearing is convenient to achieve, gaps between the thrust bearing and the surface of the combined bearing base are increased on the other hand, and more choices are provided for the cooling flow channel design of the whole bearing system. The end face cooling air groove expands the area of a cooling air flow channel, reduces flow resistance and increases the flow of cooling air, so that the cooling heat transfer effect of the smooth foil and the corrugated elastic foil is enhanced, and the temperature of the thrust bearing is reduced.
2. The foil type axial thrust bearing with high heat dissipation rate, the combined bearing and the bearing heat management method enhance the convection cooling and heat transfer effects of the smooth foil and the corrugated elastic foil, and reduce the temperature rise of the rotating shaft, the smooth foil and the corrugated elastic foil caused by the pneumatic heat of the air film; the increase in air flow also reduces the radial temperature difference of the rotating shaft, the smooth foil and the corrugated elastic foil.
3. According to the high-heat-dissipation-rate foil type axial thrust bearing, the combined bearing and the bearing heat management method, the corrugated elastic foil is divided into a plurality of fan-shaped foil petals which are distributed along the radial direction by one or a plurality of fan-shaped gaps which start from the fixing (welding) part, namely, the corrugated elastic foil is subjected to multi-petal design along the radial direction, so that the flexibility of the foil along the radial direction is increased, all parts of the foil are stressed more uniformly, and local permanent deformation is not easy to generate; meanwhile, the air gap between the smooth foil and the corrugated elastic foil can be increased, and the passing flow of the cooling air flow is further increased from another angle.
4. The foil type axial thrust bearing with high heat dissipation rate, the combined bearing and the bearing heat management method are applied to a fuel cell air compressor or other motors, and the heat convection between a motor rotating shaft outside the bearing and cooling air flow is enhanced, so that the temperature rise of the rotating shaft inside the bearing is greatly reduced, and particularly in the application of the fuel cell air compressor, the heat dissipation efficiency can be increased by 40% by using the foil type axial thrust bearing with high heat dissipation rate, the combined bearing and the bearing heat management method under the condition of discharging cooling air with the same flow through tests.
Drawings
FIG. 1 is a schematic view of the internal heat exchange of a prior art foil type aerodynamic bearing;
FIG. 2 is a schematic view of the external heat exchange of a prior art foil type aerodynamic bearing;
FIG. 3 is a schematic three-dimensional structure diagram of the high heat dissipation rate foil type axial thrust bearing of the present invention
FIG. 4 is a schematic end view of a high heat dissipation rate foil type axial thrust bearing according to the present invention;
FIG. 5 is a schematic view of the surface structure of the corrugated elastic foil of the high heat dissipation rate axial thrust bearing of the present invention;
FIG. 6 is a schematic cross-sectional view of a corrugated elastic foil of the high heat dissipation rate axial thrust bearing of the present invention;
FIG. 7 is a schematic view of the end face structure of the base of the high heat dissipation rate axial thrust bearing of the present invention;
FIG. 8 is an axial cross-sectional view of the base of the high heat dissipation foil type axial thrust bearing of the present invention;
FIG. 9 is a schematic structural diagram of an end face of a bearing housing of the high-heat-dissipation foil-type composite bearing according to the present invention;
FIG. 10 is a schematic diagram of a three-dimensional structure of a bearing housing of the high-heat-dissipation foil-type composite bearing according to the present invention;
FIG. 11 is a schematic axial cross-sectional view of a high-heat-dissipation foil radial bearing of the high-heat-dissipation foil combination bearing of the present invention;
FIG. 12 is a schematic diagram of an end face structure of an axially corrugated flexible foil of the high-heat-dissipation foil-type plain bearing according to the present invention;
FIG. 13 is a schematic side view of an axially corrugated flexible foil of the high-heat-dissipation foil-type plain bearing of the present invention;
fig. 14 is a schematic diagram of a thermal management system of a fuel cell air compressor using the high-heat-dissipation foil bearing thermal management method of the present invention.
The reference numbers are listed below:
1-shell, 11-cooling air inlet,
2-high heat dissipation rate foil axial thrust bearing, 21-base, 211-annular boss, 2111-end face cooling air groove, 22-fan ring foil set, 221-corrugated elastic foil, 2211-corrugated upper projection, 2211' -full corrugated upper projection, 2212-welding part, 2213-fan ring gap, 2214-fan ring foil flap, 22141-second fan ring foil flap, 22142-second fan ring foil flap, 22143-third fan ring foil flap, 222-smooth foil,
3-foil type combined bearing with high heat dissipation rate,
4-high heat dissipation rate foil type radial bearing, 41-bearing shell, 411-axial cooling air groove, 42-axial corrugated elastic foil, 421-axial corrugated inner convex part, 422-fixing part, 423-annular gap, 424-foil flap, 43-axial smooth foil,
5-rotor, 51-thrust disk,
6-exhaust hole, 7-impeller, 8-volute, 9-cooling pipeline.
Detailed Description
In order to facilitate an understanding of the invention, the invention is described in more detail below with reference to the accompanying drawings and specific examples.
Example 1
As shown in fig. 3-8, a high heat dissipation rate foil axial thrust bearing 2 includes a base 21 and 6 fan-shaped annular foil groups 22, an annular boss 211 is coaxially disposed on an end surface of the base 21, and the 6 fan-shaped annular foil groups 22 are circumferentially arranged on an end surface of the annular boss 211 in a central symmetry manner and are not overlapped with each other; and a radial gap is formed between the side edges of the adjacent fan-shaped annular foil groups. Each fan-ring-shaped foil group 22 comprises a smooth foil 222 and a corrugated elastic foil 221, the corrugated elastic foil 221 and the smooth foil 222 are fan-ring-shaped and are sequentially stacked and then welded on the upper surface of the ring-shaped boss 211, that is, the corrugated elastic foil 221 is clamped between the boss 211 and the smooth foil 222; and corresponding to the upper corrugated convex portion 2211 of the corrugated elastic foil 221, the upper surface of the boss 211 is provided with an end face cooling air groove 2111. The annular boss 211 provides support for the corrugated elastic foil 221, facilitates machining of the end face cooling air groove 2111, and facilitates radial cooling of the axial thrust bearing, and the annular boss 211 increases the gap between the base 21 and the base surface of the combined bearing 3, and provides more choices for the cooling flow channel design of the whole bearing system. The end face cooling air groove 2111 expands the area of a cooling air flow passage, reduces flow resistance, and increases the flow rate of cooling air, thereby enhancing the cooling heat transfer effect on the smooth foil piece 222 and the corrugated elastic foil piece, and reducing the temperature of the thrust bearing. The outer and inner in the present invention mean that the position close to the axis of the member is inner and the position far from the axis is outer.
Preferably, a welding portion 2212 (i.e. a fixed portion) is provided at an edge of the corrugated elastic foil 221, the corrugated elastic foil 221 is welded to the annular boss 211 through the welding portion 2212, the welding portion 2212 is arranged along a radial direction of the boss 211, the corrugated upper protrusions 2211 of the corrugated elastic foil 221 are each disposed parallel to the welding portion 2212, and the corresponding end face cooling air groove 2111 is disposed parallel to the welding portion 2212 and extends from a shaft hole position of the boss 211 to a radial outer surface of the boss 211. Preferably, the end face cooling air groove 2111 is a wedge-shaped through groove, or a through groove having a semicircular or rectangular axial cross-sectional shape.
Preferably, the corrugated elastic foil 221 includes at least 1 complete corrugated upper protrusion 2211 'extending from its inner edge to its outer edge, the corrugated elastic foil 221 as shown in fig. 5 includes 3 complete corrugated upper protrusions 2211' extending from its inner edge to its outer edge, the upper surface of the boss 211 corresponding to the complete corrugated upper protrusion 2211 'is opened with an end face cooling air groove 2111 as shown in fig. 7, and since 6 fan-ring-shaped foil groups 22 are circumferentially and centrally symmetrically arranged on the end face of the ring-shaped boss 211, the complete corrugated upper protrusion 2211' of the corrugated elastic foil 221 of each fan-ring-shaped foil group 22 corresponds to one of the end face cooling air grooves 2111. Since the corrugated upper projections 2211 of the corrugated elastic foil 221 are all disposed parallel to the welding portion 2212, the end face cooling air grooves 2111 may be disposed both clockwise and counterclockwise on the annular projection 211.
Preferably, as shown in fig. 5, the corrugated flexible foil 221 is divided into 3 fan-shaped ring-shaped foil segments 2214 distributed in the radial direction by 2 fan-shaped gaps 2213 starting from the fixing (welding) portion. That is, the corrugated elastic foil 221 includes a first annular foil segment 22141, a second annular foil segment 22142 and a third annular foil segment 22143 having the same central angle and sequentially increasing radius, the inner radius of the third annular foil segment 22143 is slightly larger than the outer radius of the second annular foil segment 22142, the inner radius of the second annular foil segment 22142 is slightly larger than the outer radius of the first annular foil segment 22141, and the lower edges of the first annular foil segment 22141, the second annular foil segment 22142 and the third annular foil segment 22143 are all welded portions thereof and are disposed on the same diameter of the substrate 21.
Example 2
The utility model provides a high heat dissipation rate foil type combination bearing 3, as shown in fig. 9-13, includes high heat dissipation rate foil type journal bearing 4 and foretell high heat dissipation rate foil type axial thrust bearing 2, the non-working end face of high heat dissipation rate foil type axial thrust bearing 2 (do not fix one side of fan ring shape foil group 22) with bearing housing 41 side end face coaxial linking to each other of high heat dissipation rate foil type journal bearing 4, or the non-working end face side of high heat dissipation rate foil type axial thrust bearing 2 is along axial, outside extension formation bearing housing 41 of foil type journal bearing 4.
Preferably, the inner surface of the high heat dissipation rate foil radial bearing 4 is coaxially and sequentially provided with an axial corrugated elastic foil 42 and an axial smooth foil 43 along the radial direction thereof, the outer surface of the axial smooth foil 43 is in contact with the top of the axial corrugated inner convex portion 421 of the axial corrugated elastic foil 42, and the inner surface of the bearing housing 41 is provided with an axial cooling air groove 411 corresponding to the axial corrugated inner convex portion 421 of the axial corrugated elastic foil.
Preferably, the axial cooling air groove 411 may also be an oblique through groove or a wedge-shaped through groove or a spiral through groove extending from one side end surface to the other side end surface of the bearing housing. As long as the cooling gas can be extended from one end surface to the other end surface of the bearing housing. The cross-sectional shape of the axial cooling air groove 411 is a wedge-shaped semicircle or a rectangle.
Preferably, one side edge of the axially corrugated elastic foil 42 is provided with a fixing portion 422 as shown in fig. 11 or 12, the fixing portion 422 may be a welded joint, which may also be referred to as a welded portion 422, the fixing portion 422 is arranged along the axial direction of the bearing housing 41, the axially corrugated inner convex portions 421 of the axially corrugated elastic foil 42 are all arranged parallel to the axial direction of the bearing housing 41, and the axially cooling air groove 411 is arranged parallel to the fixing portion 422 and extends from one side end face to the other side end face of the bearing housing 41.
Preferably, as shown in fig. 13, the axially corrugated flexible foil 42 is divided into 4 foil flaps 424 in an average manner by 3 annular slits 423 starting from the fixing portion 422 in the axial direction. Namely, the axial corrugated elastic foil 42 is designed to be multi-lobed in the axial direction, so that the flexibility of the foil in the axial direction is increased, all parts of the foil are stressed uniformly, and local permanent deformation is not easy to generate; while increasing the air gap between the axially smooth foil 43 and the axially corrugated flexible foil 42 further increases the cooling air flow through from another angle.
Preferably, as shown in fig. 11, four axially corrugated elastic foils 42 that do not overlap with each other circumferentially fill the inner surface of the bearing housing 41; i.e. each of said axially corrugated flexible foils 42 is laid at an angle of 90 degrees or slightly less than 90 degrees in the circumferential direction as shown in fig. 11 or 12. The inner surface of the bearing housing 41 is provided with the axial cooling air grooves 411 corresponding to each of the axially corrugated inner protrusions 421 of each of the axially corrugated flexible foils 42. Preferably, a plurality of axial cooling air slots 411 are arranged on the inner surface of the bearing housing 41 in a central symmetry manner corresponding to the plurality of axial corrugated inner protrusions 421 of each axial corrugated elastic foil 42, the number of the axial cooling air slots 411 can be designed reasonably according to the heat generation condition, as shown in fig. 10, each axial corrugated elastic foil 42 which is laid in the circumferential direction is represented by 90 degrees or slightly less than 90 degrees, and the corresponding axial cooling air slots 411 are 4.
Example 3
The high heat dissipation rate foil type axial thrust bearing 4 and the high heat dissipation rate foil type combination bearing 3 are assembled between the rotor 5 and the motor housing 1 in an air compressor for a fuel cell, a micro-combustion engine, or an oilless fan, and the application in the air compressor for a fuel cell is shown in fig. 14, and one end of the rotor 5 near the impeller 7 and the volute 8 is provided with a thrust disc 51.
The high-heat-dissipation-rate foil type axial thrust bearing 2 is assembled on the right side (where the impeller 7 and the volute 8 are located) of the thrust disk 51, the high-heat-dissipation-rate foil type combined bearing 3 is assembled on the left side of the thrust disk 51, and the working end faces of the high-heat-dissipation-rate foil type axial thrust bearing and the high-heat-dissipation-rate foil type combined bearing 3 face the thrust disk 51. Finally, the high heat dissipation foil radial bearing 4 is assembled between the rotor 5 and the rear end cover of the housing 1 so as to maintain the high-speed operation of the rotor 5.
A gap is arranged between the thrust disc 51 and the housing 1, the flow direction of cooling air flow is indicated by an arrow in fig. 10, the cooling air flow enters the cooling pipeline 9 from the outer side of the air compressor for the fuel cell through the cooling air flow inlet hole 11 on the housing 1, the rotor 5 rotating at high speed sucks the cooling air flow to the rotor shaft, and then enters the working end face of the high-heat-dissipation rate foil type axial thrust bearing 2 through the rotor shaft, the heat generated by the working end face of the high-heat-dissipation rate foil type axial thrust bearing 2 is taken out through the end face cooling air groove 2111, and then enters the end face cooling air groove of the end face axial thrust bearing of the high-heat-dissipation rate foil type combined bearing 3 through the gap between the thrust disc 51 and the housing 1, and enters the shaft hole after exchanging heat with the working end face thereof, and then passes through the axial cooling air groove of the high-heat-dissipation rate foil type combined bearing 3 in the shaft hole, and is discharged leftwards after exchanging heat with The foil radial bearing 4 is finally discharged through the axial cooling air groove 411 of the high heat dissipation foil radial bearing 4. Through the arrangement of the end face cooling air groove and the axial cooling air groove, the heat convection between the motor rotating shaft outside the bearing and cooling air flow is enhanced, and through tests, under the condition of discharging the cooling air with the same flow, the high-heat-dissipation-rate foil type radial bearing, the combined bearing and the bearing heat management method can increase the heat dissipation efficiency by 40 percent, so that the temperature rise of the rotating shaft inside the bearing is greatly reduced.
Preferably, the arrangement mode of the end face cooling air groove of the high-heat-dissipation-rate foil type combination bearing 3 is opposite to that of the end face cooling air groove of the foil type axial thrust bearing 2, that is, the end face cooling air groove of the high-heat-dissipation-rate foil type combination bearing 3 is arranged clockwise on the annular boss, and the end face cooling air groove of the high-heat-dissipation-rate foil type axial thrust bearing 2 positioned on the right side is arranged anticlockwise on the annular boss 211; namely, the welding end of the sector ring-shaped foil group of the high-heat-dissipation-rate foil-type combined bearing 3 is different from the welding end of the sector ring-shaped foil group 23 of the foil-type axial thrust bearing 2, so as to further increase the flow speed of the cooling fluid.
Although embodiments of the present invention have been shown and described above, it is understood that the above embodiments are exemplary and should not be construed as limiting the present invention, and that variations, modifications, substitutions and alterations can be made to the above embodiments by those of ordinary skill in the art within the scope of the present invention.
Claims (10)
1. The high-heat-dissipation-rate foil type axial thrust bearing is characterized by comprising a base body and a plurality of fan-shaped annular foil sets, wherein an annular boss is coaxially arranged on the end surface of the base body, and the plurality of fan-shaped annular foil sets are circumferentially and centrally symmetrically arranged on the end surface of the annular boss; each fan-ring-shaped foil group comprises a smooth foil and a corrugated elastic foil, and the corrugated elastic foil and the smooth foil are fan-ring-shaped and are sequentially stacked and then fixed on the ring-shaped boss; and the upper surface of the boss is provided with an end face cooling air groove corresponding to the upper convex part of the corrugation elastic foil.
2. The high heat dissipation rate foil type axial thrust bearing of claim 1, wherein a lateral edge of the corrugated elastic foil is provided with a fastening portion, the fastening portion is arranged along a radial direction of the boss, the upper convex portions of the corrugations of the corrugated elastic foil are all arranged in parallel with the fastening portion, and the corresponding end face cooling air grooves are arranged in parallel with the fastening portion and extend to the radial outer surface of the boss from the position of the boss shaft hole.
3. The high heat dissipation rate foil axial thrust bearing of claim 2, wherein said corrugated flexible foil comprises at least 1 full corrugated upper protrusion extending from an inner edge to an outer edge thereof, and said end face cooling air groove is formed on an upper surface of said protrusion corresponding to a position of said full corrugated upper protrusion.
4. High heat dissipation foil axial thrust bearing according to claim 2 or 3, wherein the corrugated flexible foil is divided by one or more fan-shaped annular gaps starting from the fastening portion into a plurality of fan-shaped annular foil lobes distributed radially.
5. The high heat dissipation foil axial thrust bearing of any one of claims 1 to 4, wherein the end face cooling air grooves are wedge-shaped through grooves, or through grooves having an axial cross-sectional shape of a semicircle or a rectangle.
6. The high heat dissipation rate foil axial thrust bearing of claim 5, wherein a plurality of said foil sets are arranged on the end surface of said boss in a manner of being centrosymmetric and not overlapping each other, and a radial gap is formed between the side edges of the adjacent foil sets.
7. A high heat dissipation rate foil type combination bearing, which is characterized by comprising a high heat dissipation rate foil type radial bearing and the high heat dissipation rate foil type axial thrust bearing as recited in one of claims 1 to 6, wherein the non-working end surface of the high heat dissipation rate foil type axial thrust bearing is coaxially connected with one side end surface of a bearing shell of the high heat dissipation rate foil type radial bearing, or the non-working end surface side of the high heat dissipation rate foil type axial thrust bearing is formed by extending along the axial direction and the outward direction to form the bearing shell of the high heat dissipation rate foil type radial bearing.
8. The high heat dissipation rate foil type combination bearing of claim 7, wherein the inner surface of the foil type radial bearing is coaxially and sequentially provided with an axial corrugated elastic foil and an axial smooth foil along a radial direction thereof, an outer surface of the axial smooth foil is in contact with tops of the corrugated inner convex portions of the axial corrugated elastic foil, corresponding to the corrugated inner convex portions of the axial corrugated elastic foil, the inner surface of the bearing housing is provided with an axial cooling air groove, one side edge of the axial corrugated elastic foil is provided with a fixing portion, the fixing portion is arranged along an axial direction of the bearing housing, the corrugated inner convex portions of the corrugated elastic foil are all arranged in parallel to the axial direction of the bearing housing, and the cooling air groove is arranged in parallel to the fixing portion and extends from one side end face to the other side end face of the bearing housing.
9. A high-heat-dissipation-rate foil type bearing heat management method is characterized in that the high-heat-dissipation-rate foil type axial thrust bearing in any one of claims 1 to 6 and the high-heat-dissipation-rate foil type combined bearing in any one of claims 7 and 8 are used, cooling air flows from a rotor shaft through an end face cooling air groove of the high-heat-dissipation-rate foil type axial thrust bearing, enters the end face cooling air groove of the high-heat-dissipation-rate foil type combined bearing after heat exchange with a working end face of the high-heat-dissipation-rate foil type combined bearing, exchanges heat with the working end face of the high-heat-dissipation-rate foil type combined bearing, passes through the axial cooling air groove of the high-heat-dissipation-rate foil type combined bearing, and is discharged after heat exchange with the inner surface of a bearing shell.
10. The method of claim 9, wherein the end cooling air slots of the high-heat-dissipation foil axial thrust bearing are oppositely disposed and rotated in opposite directions with respect to the end cooling air slots of the high-heat-dissipation foil combination bearing.
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| CN202110178029.9A CN113007211B (en) | 2021-02-07 | 2021-02-07 | High-heat-dissipation-rate foil type axial thrust bearing, combined bearing and heat management method |
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| CN202110178029.9A CN113007211B (en) | 2021-02-07 | 2021-02-07 | High-heat-dissipation-rate foil type axial thrust bearing, combined bearing and heat management method |
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| CN113007211B CN113007211B (en) | 2021-11-26 |
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| CN113007211B (en) | 2021-11-26 |
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