CN114165464A - Air compressor and fuel cell system - Google Patents

Air compressor and fuel cell system Download PDF

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Publication number
CN114165464A
CN114165464A CN202111348762.7A CN202111348762A CN114165464A CN 114165464 A CN114165464 A CN 114165464A CN 202111348762 A CN202111348762 A CN 202111348762A CN 114165464 A CN114165464 A CN 114165464A
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CN
China
Prior art keywords
annular
impeller
air
thrust bearing
air compressor
Prior art date
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Pending
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CN202111348762.7A
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Chinese (zh)
Inventor
陈振宇
张虎
熊万里
高卫华
张显
黄腾晖
汤智锋
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Guangzhou Haozhi Electromechanical Co Ltd
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Guangzhou Haozhi Electromechanical Co Ltd
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Application filed by Guangzhou Haozhi Electromechanical Co Ltd filed Critical Guangzhou Haozhi Electromechanical Co Ltd
Priority to CN202111348762.7A priority Critical patent/CN114165464A/en
Publication of CN114165464A publication Critical patent/CN114165464A/en
Pending legal-status Critical Current

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    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D17/00—Radial-flow pumps, e.g. centrifugal pumps; Helico-centrifugal pumps
    • F04D17/08—Centrifugal pumps
    • F04D17/10—Centrifugal pumps for compressing or evacuating
    • F04D17/12—Multi-stage pumps
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D25/00—Pumping installations or systems
    • F04D25/02—Units comprising pumps and their driving means
    • F04D25/06—Units comprising pumps and their driving means the pump being electrically driven
    • F04D25/0606—Units comprising pumps and their driving means the pump being electrically driven the electric motor being specially adapted for integration in the pump
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D29/00—Details, component parts, or accessories
    • F04D29/08—Sealings
    • F04D29/16—Sealings between pressure and suction sides
    • F04D29/161—Sealings between pressure and suction sides especially adapted for elastic fluid pumps
    • F04D29/162—Sealings between pressure and suction sides especially adapted for elastic fluid pumps of a centrifugal flow wheel
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D29/00—Details, component parts, or accessories
    • F04D29/26—Rotors specially for elastic fluids
    • F04D29/28—Rotors specially for elastic fluids for centrifugal or helico-centrifugal pumps for radial-flow or helico-centrifugal pumps
    • F04D29/284—Rotors specially for elastic fluids for centrifugal or helico-centrifugal pumps for radial-flow or helico-centrifugal pumps for compressors
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D29/00—Details, component parts, or accessories
    • F04D29/40—Casings; Connections of working fluid
    • F04D29/42—Casings; Connections of working fluid for radial or helico-centrifugal pumps
    • F04D29/4206—Casings; Connections of working fluid for radial or helico-centrifugal pumps especially adapted for elastic fluid pumps
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D29/00—Details, component parts, or accessories
    • F04D29/58—Cooling; Heating; Diminishing heat transfer
    • F04D29/5806—Cooling the drive system
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D29/00—Details, component parts, or accessories
    • F04D29/58—Cooling; Heating; Diminishing heat transfer
    • F04D29/582—Cooling; Heating; Diminishing heat transfer specially adapted for elastic fluid pumps
    • F04D29/584—Cooling; Heating; Diminishing heat transfer specially adapted for elastic fluid pumps cooling or heating the machine
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D29/00—Details, component parts, or accessories
    • F04D29/66—Combating cavitation, whirls, noise, vibration or the like; Balancing
    • F04D29/661—Combating cavitation, whirls, noise, vibration or the like; Balancing especially adapted for elastic fluid pumps
    • F04D29/662—Balancing of rotors
    • H—ELECTRICITY
    • H01—ELECTRIC ELEMENTS
    • H01M—PROCESSES OR MEANS, e.g. BATTERIES, FOR THE DIRECT CONVERSION OF CHEMICAL ENERGY INTO ELECTRICAL ENERGY
    • H01M8/00—Fuel cells; Manufacture thereof
    • H01M8/04—Auxiliary arrangements, e.g. for control of pressure or for circulation of fluids
    • H01M8/04082—Arrangements for control of reactant parameters, e.g. pressure or concentration
    • H01M8/04089—Arrangements for control of reactant parameters, e.g. pressure or concentration of gaseous reactants
    • H01M8/04111—Arrangements for control of reactant parameters, e.g. pressure or concentration of gaseous reactants using a compressor turbine assembly
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02E—REDUCTION OF GREENHOUSE GAS [GHG] EMISSIONS, RELATED TO ENERGY GENERATION, TRANSMISSION OR DISTRIBUTION
    • Y02E60/00—Enabling technologies; Technologies with a potential or indirect contribution to GHG emissions mitigation
    • Y02E60/30—Hydrogen technology
    • Y02E60/50—Fuel cells

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Thermal Sciences (AREA)
  • Physics & Mathematics (AREA)
  • Sustainable Energy (AREA)
  • Sustainable Development (AREA)
  • Chemical & Material Sciences (AREA)
  • Chemical Kinetics & Catalysis (AREA)
  • Electrochemistry (AREA)
  • General Chemical & Material Sciences (AREA)
  • Manufacturing & Machinery (AREA)
  • Life Sciences & Earth Sciences (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)

Abstract

The invention discloses an air compressor and fuel cell system, comprising: the motor comprises a machine body, a motor stator, a motor rotor, a rotating shaft, a radial bearing assembly and a thrust bearing assembly, wherein the thrust bearing assembly is arranged on the machine shell; the compression assembly is arranged at the end part of the machine body and comprises an impeller and a volute, the impeller is connected with the rotating shaft, and a gap is reserved between the back surface of the impeller and the end surface of the machine body; the back of impeller is equipped with a plurality of annular bosses, and the terminal surface of organism is equipped with a plurality of annular grooves, and annular boss inlays and forms seal structure in the annular groove, forms the seal clearance in the root of annular boss between the terminal surface of impeller and organism, and annular groove forms annular cavity at annular boss top, and when the gas flow after the impeller compression was through seal structure, the production acted on the dorsal axial effort of impeller. The back pressure of the impeller can be adjusted through the sealing structure, so that the axial load of the centrifugal impeller is effectively balanced.

Description

Air compressor and fuel cell system
Technical Field
The invention is used in the field of fuel cell engines, and particularly relates to an air compressor and a fuel cell system.
Background
The air compressor provides the hydrogen fuel cell with the high pressure air required for the chemical reaction, which is the "lung" of the hydrogen fuel cell. But at the same time, the fuel cell system is also the most important energy consumption component in the hydrogen fuel cell system, and the parasitic power of the fuel cell system accounts for about 15% -20% of the output power of the fuel cell system. In order to obtain higher pressure ratio and efficiency, the fuel cell mostly adopts a high-speed direct-drive two-stage centrifugal air compressor, and compared with other types of air compressors, the fuel cell has the advantages of high efficiency, small volume, light weight, obvious reduction of vibration and noise, quick dynamic response and the like. However, the centrifugal impeller can generate a large axial load under a high-speed working condition, and if the load can not be effectively reduced or balanced, the thrust bearing can bear the large axial load, so that the bearing abrasion can be aggravated, and even a bearing air film is directly punctured, so that the air compressor is locked.
On the other hand, centrifugal air compressor's rated revolution often reaches more than 90000rpm, and air thrust bearing sends down the heat very big at high rotational speed high load, if can not in time take away the heat, will seriously influence thrust bearing life-span, current technical scheme is mostly from air compressor machine export introduction part compressed air to thrust bearing and motor cooling, and partial compressed gas has been wasted to this kind of scheme, reduces compressor efficiency, and the cooling gas temperature of introducing moreover is high, and the cooling effect is not good.
Disclosure of Invention
An object of the present invention is to solve at least one of the technical problems of the prior art and to provide an air compressor and a fuel cell system which can effectively balance the axial load of a centrifugal impeller by adjusting the pressure of the back side of the impeller through a sealing structure.
The technical scheme adopted by the invention for solving the technical problems is as follows:
in a first aspect, an air compressor includes:
the motor stator is fixedly arranged in an inner cavity of the shell, the motor rotor is connected with the rotating shaft, the rotating shaft is arranged in an inner hole of the shell through the radial bearing assembly, the thrust bearing assembly is arranged on the shell, and the rotating shaft is provided with a flange protrusion matched with the thrust bearing assembly;
the compression assembly is arranged at the end part of the machine body and comprises an impeller and a volute, the impeller is connected with the rotating shaft, and a gap is reserved between the back surface of the impeller and the end surface of the machine body;
the back of the impeller is provided with a plurality of annular bosses, the end face of the machine body is provided with a plurality of annular grooves, the annular bosses are embedded in the annular grooves to form the sealing structure, the impeller and the end face of the machine body form a sealing gap at the root of the annular bosses, the annular grooves form annular cavities at the tops of the annular bosses, and gas compressed by the impeller flows through the sealing structure to generate axial acting force acting on the back side of the impeller.
With reference to the first aspect, in certain implementations of the first aspect, the annular groove is an annular inclined groove inclined to the axis of the rotating shaft in a depth direction, the annular boss has an outer annular surface parallel to the axis of the rotating shaft and an inner annular surface parallel to a wall of the annular inclined groove, and the outer annular surface and the inner annular surface define a wedge-shaped cross section of the annular boss.
With reference to the first aspect and the foregoing implementation manners, in some implementation manners of the first aspect, the compression assembly includes a first-stage compression assembly and a second-stage compression assembly, the first-stage compression assembly is disposed at the front end of the machine body, and the first-stage compression assembly includes a first-stage impeller and a first-stage volute; the second-stage compression assembly is arranged at the rear end of the machine body and comprises a second-stage impeller and a second-stage volute, and an inlet of the second-stage volute is connected with an outlet of the first-stage volute.
With reference to the first aspect and the foregoing implementation manners, in some implementation manners of the first aspect, the thrust bearing assembly is installed in an inner hole at the front end of the casing, the thrust bearing assembly includes a front thrust bearing, a gap isolation plate and a rear thrust bearing, the flange protrusion is installed and limited in an annular air cavity formed by the front thrust bearing and the rear thrust bearing, a gap is left between the back surface of the impeller and the front thrust bearing, and a plurality of annular grooves are formed in the front end surface of the front thrust bearing.
With reference to the first aspect and the foregoing implementation manners, in some implementation manners of the first aspect, the thrust bearing assembly is provided with a cooling gas passage, the casing is provided with a first drainage hole for introducing external gas into the thrust bearing assembly and a second drainage hole for introducing gas for cooling the thrust bearing assembly, a third drainage hole is arranged at an inlet of the first-stage volute, and the third drainage hole is connected with the second drainage hole through a pipeline.
With reference to the first aspect and the foregoing implementation manners, in certain implementation manners of the first aspect, the inlet of the one-stage volute and the inlet of the first flow-guiding hole are both connected with an air filter.
With reference to the first aspect and the foregoing implementation manners, in certain implementation manners of the first aspect, the cooling gas passage includes a first annular gas groove and a plurality of first radial gas introduction grooves provided in a front side end surface of the front thrust bearing, and a second annular gas groove and a plurality of second radial gas introduction grooves provided in a rear side end surface of the rear thrust bearing, and the first annular gas groove and the second annular gas groove are connected by a through hole passing through the gap isolation plate.
With reference to the first aspect and the foregoing implementation manners, in some implementation manners of the first aspect, a first air outlet hole for guiding air of the cooling air channel to an inner cavity of the motor is disposed between the second drainage hole and the cooling air channel.
With reference to the first aspect and the foregoing implementation manners, in certain implementation manners of the first aspect, the casing is provided with a coolant circulation channel, the second drainage hole includes a radial air hole and an axial air hole, the radial air hole is formed in the rear end of the casing, the rear end of the axial air hole is connected with the radial air hole, the axial air hole extends forward along the casing, is guided out through the second air outlet after exchanging heat with the coolant circulation channel, and is connected with the third drainage hole through the pipeline.
In a second aspect, a fuel cell system includes the air compressor of any one of the implementations of the first aspect.
One of the above technical solutions has at least one of the following advantages or beneficial effects: when the air compressor works, the impeller rotates at a high speed along with the motor rotor to compress air. And the front surface of the impeller is provided with distributed pressure from small to large, and the air is compressed to form high-pressure gas at the outlet of the impeller. Due to the action of the pressure difference, high-pressure gas at the outlet of the impeller leaks to the inner cavity of the motor along the gap on the back of the impeller. When high-pressure air flows through the gap to reach the sealing structure, the pressure is high, and the flow rate is high; when the airflow flows out of the sealing gap and enters the annular cavity, the flow velocity of the airflow is quickly slowed down and forms a vortex due to the sudden amplification of the flow space, so that great pressure loss is caused, and the pressure is obviously reduced; the gas flow is then accelerated through the next seal gap and into the next annular cavity, further reducing the pressure. By analogy, after the air flow passes through the plurality of sealing gaps and the annular air cavity, the pressure is greatly reduced, and the sealing effect is realized. Meanwhile, when the airflow flows through the sealing structure, the pressure is greatly reduced, so that the axial pressure distribution on the back of the impeller can be adjusted by changing the radius of the sealing structure, the size of the sealing gap and the structure of the sealing groove, the axial force on the back of the impeller is further changed, the pressure difference between the front side and the back side of the impeller is in a small state or equal to 0, and the load of a thrust bearing is reduced.
Additional aspects and advantages of the invention will be set forth in part in the description which follows and, in part, will be obvious from the description, or may be learned by practice of the invention.
Drawings
The above and/or additional aspects and advantages of the present invention will become apparent and readily appreciated from the following description of the embodiments, taken in conjunction with the accompanying drawings of which:
fig. 1 is a schematic structural view of an embodiment of an air compressor of the present invention;
FIG. 2 is a schematic view of one embodiment of the sealing structure shown in FIG. 1;
FIG. 3 is a schematic illustration of the pressure distribution across the impeller of the embodiment shown in FIG. 1;
FIG. 4 is a schematic illustration of the pressure distribution across the primary and secondary impellers of the embodiment shown in FIG. 1;
FIG. 5 is a schematic illustration of the cooling of one embodiment of the thrust bearing assembly shown in FIG. 1.
Detailed Description
Reference will now be made in detail to the present preferred embodiments of the present invention, examples of which are illustrated in the accompanying drawings, wherein like reference numerals refer to like elements throughout.
In the present invention, if directions (up, down, left, right, front, and rear) are described, it is only for convenience of describing the technical solution of the present invention, and it is not intended or implied that the technical features referred to must have a specific orientation, be constructed and operated in a specific orientation, and thus, it is not to be construed as limiting the present invention.
In the invention, the meaning of "a plurality" is one or more, the meaning of "a plurality" is more than two, and the terms of "more than", "less than", "more than" and the like are understood to exclude the number; the terms "above", "below", "within" and the like are understood to include the instant numbers. In the description of the present invention, if there is description of "first" and "second" only for the purpose of distinguishing technical features, it is not to be understood as indicating or implying relative importance or implicitly indicating the number of indicated technical features or implicitly indicating the precedence of the indicated technical features.
In the present invention, unless otherwise specifically limited, the terms "disposed," "mounted," "connected," and the like are to be understood in a broad sense, and for example, may be directly connected or indirectly connected through an intermediate; can be fixedly connected, can also be detachably connected and can also be integrally formed; may be mechanically coupled, may be electrically coupled or may be capable of communicating with each other; either as communication within the two elements or as an interactive relationship of the two elements. The specific meaning of the above-mentioned words in the present invention can be reasonably determined by those skilled in the art in combination with the detailed contents of the technical solutions.
Fig. 1 and 5 show reference direction coordinate systems of embodiments of the present invention, and the embodiments of the present invention will be described below with reference to the directions shown in fig. 1 and 5.
The embodiment of the invention provides an air compressor, which comprises a machine body 1, compression assemblies 2 and 3 and sealing structures 5 and 6.
Referring to fig. 1, the machine body 1 includes a casing 101, a motor stator 102, a motor rotor, a rotating shaft 103, a radial bearing assembly and a thrust bearing assembly, the motor stator 102 is fixedly installed in an inner cavity of the casing, the motor rotor is connected with the rotating shaft 103, the rotating shaft 103 is installed in an inner hole of the casing 101 through the radial bearing assembly, and the motor stator 102 and the motor rotor are matched with each other to provide a torque for driving the rotating shaft 103 to rotate. The thrust bearing assembly is mounted on the housing 101, the rotating shaft 103 is provided with a flange protrusion 113 matched with the thrust bearing assembly, and the thrust bearing assembly and the flange protrusion 113 are matched with each other to provide axial support for the rotating shaft 103.
Referring to fig. 1, the radial bearing assembly includes a front radial bearing assembly 105 and a rear radial bearing assembly 107, the front radial bearing assembly 105 is mounted at the front end of the casing 101, the front radial bearing assembly 105 includes a front bearing seat and a front radial foil aerodynamic bearing 106, the rear radial bearing assembly 107 is mounted at the rear end of the casing 101, the rear radial bearing assembly 107 includes a rear bearing seat and a rear radial foil aerodynamic bearing 108, the rotating shaft 103 is mounted in a hollow shaft hole formed by the front radial foil aerodynamic bearing 106 and the rear radial foil aerodynamic bearing 108, and the rotating shaft 103 is supported by the foil aerodynamic bearing, so that stability and efficiency of the rotating shaft 103 in high-speed rotation are improved, and friction loss is reduced.
The machine body 1 further comprises a water jacket 104, wherein the water jacket 104 is assembled in the inner hole of the machine shell 101 in an interference manner, and O-rings are arranged at the front end and the rear end, and the outer surface of the water jacket 104 and the spiral ring groove 112 of the machine shell 101 define a cooling liquid circulation channel. The cooling liquid circulation channel is used for circulating cooling media such as cooling water and the like so as to take away heat generated by the machine body 1 parts such as the motor and the like in the working process.
Referring to fig. 1, the compression assemblies 2 and 3 are disposed at the end of the machine body 1, the compression assemblies 2 and 3 include an impeller and a volute, the impeller is connected to the rotating shaft 103, and a gap 505 is left between the back of the impeller and the end surface of the machine body 1. The impeller rotates along with the rotating shaft 103, continuously sucks air from an air inlet of the volute, and discharges the air through an air outlet of the volute after compression, so that air compression is realized.
Referring to fig. 1 and 2, a plurality of annular bosses 501 are arranged on the back of the impeller, a plurality of annular grooves 502 are correspondingly arranged on the end surface of the machine body 1, and the annular bosses 501 are embedded in the corresponding annular grooves 502 to form sealing structures 5 and 6. Specifically, a sealing gap 503 is formed between the impeller and the end surface of the machine body 1 at the root of the annular boss 501, an annular cavity 504 is formed at the top of the annular boss 501 by the annular groove 502, and when gas compressed by the impeller flows through the sealing structures 5 and 6, the gas flow pressure leaking to the inner cavity of the motor is reduced.
When the air compressor works, the impeller rotates at high speed along with the motor rotor to supply airCompression is performed. And the distributed pressure P from small to large is formed on the front surface of the impellerFAs shown in FIG. 3, a positive axial force F is generated under the distributed pressureFAnd, and:
FF＝2π∫PFRdR
wherein R is the radius of the impeller.
The air forms high-pressure gas at the outlet of the impeller after being compressed, and the pressure is obviously higher than the pressure in the motor air cavity. Due to the action of the pressure difference, high-pressure gas at the outlet of the impeller leaks to the inner cavity of the motor along the gap on the back of the impeller. When high-pressure air flows through the gap to reach the sealing structures 5 and 6, the pressure is high, and the flow rate is high; when the gas flow flows out of the sealing gap 503 and enters the annular cavity 504, the gas flow speed is quickly slowed down and forms a vortex due to the sudden amplification of the flow space, so that great pressure loss is caused, and the pressure is obviously reduced; the gas flow is then accelerated again through the next seal gap 503 and into the next annular cavity 504, further reducing the pressure. By analogy, after the air flow passes through the plurality of sealing gaps 503 and the annular cavity 504, the pressure is greatly reduced, and the sealing effect is realized. Wherein the pressure P of the back of the impellerBDistributed as shown in fig. 3, and under the distributed pressure, a reverse axial force F is formedBAnd, and:
FB＝2π∫PBRdR
in design, referring to fig. 3, the thrust bearing load can be reduced by changing the seal diameter r, the seal gap δ and the structure of the annular groove 502, adjusting the axial pressure distribution on the back face of the impeller, and further changing the axial force on the back face of the impeller, so that the axial load from the front face of the centrifugal impeller and the axial load from the back face of the impeller are balanced or in a state of small difference.
In order to create a greater pressure drop for the gas flow as it flows through the annular cavity 504, and to improve the sealing and pressure regulation capabilities of the sealing structures 5, 6, in some embodiments, referring to fig. 2, the annular groove 502 is formed with an annular chute inclined in the depth direction with respect to the axis of the shaft 103, the groove bottom of the annular chute being offset radially outward with respect to the slot opening, the annular projection 501 has an outer annular surface parallel to the axis of the shaft 103 and an inner annular surface parallel to the groove wall of the annular chute, the outer and inner annular surfaces defining the wedge-shaped cross-section of the annular projection 501. The annular boss 501 and the annular groove 502 can be directly assembled in an axial direction, that is, the annular boss 501 is embedded in the annular groove 502 in the axial direction. After assembly, a sealing gap 503 is formed at the root of the annular boss 501, and an annular cavity 504 is formed between the top of the annular boss 501 and the bottom of the annular groove 502. The annular cavity 504 is biased in a reverse direction radially outward, and after the air flow entering the annular cavity 504 enters the annular cavity 504, the flow space is suddenly enlarged, flows in a reverse direction, further generates vortex, causes great pressure loss, and the pressure is obviously reduced.
It can be understood that, in order to obtain the annular cavity 504 with a suddenly enlarged flow space, a structure form in which the annular groove 502 is set to be closed-up may also be adopted, so as to further enhance the sealing effect and enhance the pressure regulating capability.
The air compressor of the present invention may adopt a single-stage compression structure or a multi-stage compression structure, for example, in some embodiments, referring to fig. 1, the compression assembly includes a first-stage compression assembly 2 and a second-stage compression assembly 3, the first-stage compression assembly 2 is disposed at the front end of the machine body 1, and the first-stage compression assembly 2 includes a first-stage impeller 201 and a first-stage volute 202; the second-stage compression component 3 is arranged at the rear end of the machine body 1, the second-stage compression component 3 comprises a second-stage impeller 301, a second-stage volute 302 and a diffuser 304, and an inlet of the second-stage volute 302 is connected with an outlet of the first-stage volute 202 through an interstage elbow 305. One-level impeller 201 is connected with pivot 103 through lock nut 203, follows pivot 103 and moves together, realizes the one-level compression, and second grade impeller 301 passes through lock nut 303 and is connected with pivot 103, follows pivot 103 and moves together, carries out the second grade compression with the air after the compression of one-level compression subassembly 2 to obtain higher pressure ratio.
Aiming at the two-stage air compressor, the wheel back of the first-stage impeller 201 is provided with an annular boss, the end face of the front thrust bearing is provided with an annular groove 502, and the annular boss and the annular groove 502 are embedded and installed to form a first-stage sealing structure 5. Correspondingly, an annular boss is arranged on the wheel back of the secondary impeller 301, an annular groove 502 is arranged on the diffuser end face of the machine body 1, and the annular boss and the annular groove 502 are mounted in an embedded mode to form a secondary sealing structure 6.
The axial force distribution of the shafting is shown in figure 4, and the final axial force F borne by the shaftingZ：
FZ＝(F1B-F1F)-(F2B-F2F)
In the design, the primary sealing structure 5 and the secondary sealing structure 6 can adjust the axial pressure distribution of the back of the impeller by changing the sealing diameter r, the sealing gap delta and the sealing groove structure, so as to change the axial force of the back of the impeller, and enable F to be FZEqual to 0 or in a very small state, reducing the thrust bearing load.
With reference to fig. 1, a thrust bearing assembly is installed in an inner hole at the front end of the casing 101, the thrust bearing assembly includes a front thrust bearing 109, a gap isolation plate 110 and a rear thrust bearing 111, a flange protrusion 113 is installed and limited in an annular air cavity 407 formed by the front thrust bearing 109 and the rear thrust bearing 111, and when the centrifugal air compressor works, an air film is formed between the flange protrusion 113 and the front thrust bearing 109 and the rear thrust bearing 111 to provide axial air-floating support for the rotating shaft 103.
In embodiments of the present invention, the annular groove 502 may be provided on the casing 101, the front thrust bearing 109 or separately added components, and in some embodiments, in order to simplify the structure of the sealing structure 5, 6, referring to fig. 1, the impeller is mounted on the front side of the front thrust bearing 109 with a gap between the back of the impeller and the front thrust bearing 109, and the front side end surface of the front thrust bearing 109 is provided with a plurality of annular grooves 502.
In order to improve the heat dissipation of the thrust bearing assembly, referring to fig. 5, the thrust bearing assembly is provided with a cooling gas channel, the casing 101 is provided with a first flow guide hole 401 for guiding external gas into the thrust bearing assembly and a second flow guide hole for guiding the gas out of the cooling thrust bearing assembly, a third flow guide hole 414 is arranged at the inlet of the first-stage volute 202, and the third flow guide hole 414 is connected with the second flow guide hole through a pipeline 413.
Referring to fig. 5, when the air compressor is in operation, a large amount of air is sucked from the inlet, a local negative pressure is formed at the inlet of the first-stage volute 202, under the traction action of the local negative pressure, cooling air enters from the first flow guiding hole 401, passes through the cooling air channel, cools the front and rear thrust bearings 111 respectively, and then is introduced into the inlet of the air compressor through the pipeline 413. In this embodiment, the third drainage hole 414 is disposed at the inlet of the first-stage volute 202 of the air compressor, and is communicated to the cooling gas channel through the pipeline 413, so that the external normal pressure air is introduced into the air compressor to cool the thrust bearing by using the local negative pressure at the inlet of the impeller. Compared with the prior art, the technical scheme avoids the power waste caused by introducing outlet compressed air into the air compressor, the efficiency is higher, the temperature of introduced cooling gas is low, and the cooling effect is good.
In some embodiments, referring to fig. 5, the inlet of the first-stage volute 202 is connected to an air filter, so that on one hand, air filtration is achieved, and on the other hand, since the air filter installed on the inlet pipeline of the first-stage volute 202 has a certain flow resistance, the local negative pressure formed at the inlet of the first-stage volute 202 can be greatly increased, which can reach-10 kPa at most, and the cooling airflow diversion effect on the thrust bearing assembly is greatly improved.
In addition, in some embodiments, the inlet of the first flow-guide aperture 401 is also connected to an air filter 402 for filtering air entering through the first flow-guide aperture 401.
The cooling gas channel may take various structural forms such as an annular channel, a radial channel, etc. to sufficiently cool the front and rear thrust bearings 109 and 111, for example, in some embodiments, in order to simplify the structure of the cooling gas channel itself, referring to fig. 1 and 5, the cooling gas channel includes a first annular gas groove and a plurality of first radial gas introduction grooves 406 provided on the front side end surface of the front thrust bearing 109, and a second annular gas groove 403 and a plurality of second radial gas introduction grooves 404 provided on the rear side end surface of the rear thrust bearing 111, the first gas introduction holes 401 are communicated with the first annular gas groove or the second annular gas groove 403, the ends of the plurality of second radial gas introduction grooves 404 are connected with the second annular gas groove 403 for introducing the cooling gas into the rear thrust bearing 111, the first annular gas groove and the second annular gas groove 403 are connected through a through hole 405 penetrating through the gap isolation plate 110, the ends of the plurality of first radial gas introduction grooves 406 are connected with the first annular gas groove, for introducing cooling gas into the forward thrust bearing 109.
Further, referring to fig. 5, a first air outlet hole 408 for guiding air of the cooling air channel to the inner cavity of the motor is arranged between the second drainage hole and the cooling air channel, and is used for guiding air flow for cooling the thrust bearing assembly to the inner cavity 409 of the motor so as to cool the motor.
After the motor inner chamber flows through, cooling air at this moment has very high temperature, if direct introduction to the air compressor machine import, will influence the work efficiency of air compressor machine. In view of this, in some embodiments, referring to fig. 5, the second drainage holes include a radial air hole 410 and an axial air hole 411, the radial air hole 410 is disposed at the rear end of the casing 101, the rear end of the axial air hole 411 is connected to the radial air hole 410, the axial air hole 411 extends forward along the casing 101, exchanges heat with the cooling liquid circulation channel, is guided out by the second air outlet hole 412, and is connected to the third drainage hole 414 through a pipe 413. This embodiment is through being guided this high temperature cooling air by axial gas pocket 411, through coolant liquid circulative cooling back, derives by second venthole 412 again, introduces the air compressor machine import via pipeline 413, reduces the adverse effect to air compressor machine work efficiency.
An embodiment of the present invention further provides a fuel cell system, including the air compressor according to any one of the implementation manners of the first aspect, wherein the air compressor provides high-pressure air required by chemical reaction for the hydrogen fuel cell.
In the description herein, references to the description of the term "example," "an embodiment," or "some embodiments," etc., mean that a particular feature, structure, material, or characteristic described in connection with the embodiment or example is included in at least one embodiment or example of the invention. In this specification, the schematic representations of the terms used above do not necessarily refer to the same embodiment or example. Furthermore, the particular features, structures, materials, or characteristics described may be combined in any suitable manner in any one or more embodiments or examples.
The invention is not limited to the above embodiments, and those skilled in the art can make equivalent modifications or substitutions without departing from the spirit of the invention, and such equivalent modifications or substitutions are included in the scope of the claims of the present application.

Claims (10)

1. An air compressor machine, its characterized in that includes:
the motor stator is fixedly arranged in an inner cavity of the shell, the motor rotor is connected with the rotating shaft, the rotating shaft is arranged in an inner hole of the shell through the radial bearing assembly, the thrust bearing assembly is arranged on the shell, and the rotating shaft is provided with a flange protrusion matched with the thrust bearing assembly;
the compression assembly is arranged at the end part of the machine body and comprises an impeller and a volute, the impeller is connected with the rotating shaft, and a gap is reserved between the back surface of the impeller and the end surface of the machine body;
the back of the impeller is provided with a plurality of annular bosses, the end face of the machine body is provided with a plurality of annular grooves, the annular bosses are embedded in the annular grooves to form the sealing structure, the impeller and the end face of the machine body form a sealing gap at the root of the annular bosses, the annular grooves form annular cavities at the tops of the annular bosses, and gas compressed by the impeller flows through the sealing structure to generate axial acting force acting on the back side of the impeller.
2. The air compressor as claimed in claim 1, wherein said annular groove is formed with an annular inclined groove inclined to said axis of said rotary shaft in a depth direction, said annular projection has an outer circumferential surface parallel to said axis of said rotary shaft and an inner circumferential surface parallel to walls of said annular inclined groove, and said outer circumferential surface and said inner circumferential surface define a wedge-shaped cross section of said annular projection.
3. The air compressor as claimed in claim 1 or 2, wherein the compression assembly includes a first-stage compression assembly and a second-stage compression assembly, the first-stage compression assembly is disposed at the front end of the machine body, and the first-stage compression assembly includes a first-stage impeller and a first-stage volute; the second-stage compression assembly is arranged at the rear end of the machine body and comprises a second-stage impeller and a second-stage volute, and an inlet of the second-stage volute is connected with an outlet of the first-stage volute.
4. The air compressor as claimed in claim 3, wherein the thrust bearing assembly is installed in an inner hole formed in a front end of the casing, the thrust bearing assembly includes a front thrust bearing, a gap isolation plate and a rear thrust bearing, the flange protrusion is installed and limited in an annular air cavity formed by the front thrust bearing and the rear thrust bearing, a gap is left between a back surface of the impeller and the front thrust bearing, and a plurality of annular grooves are formed in a front end surface of the front thrust bearing.
5. The air compressor as claimed in claim 4, wherein the thrust bearing assembly is provided with a cooling gas passage, the casing is provided with a first flow guide hole for guiding external gas into the thrust bearing assembly and a second flow guide hole for guiding gas for cooling the thrust bearing assembly, a third flow guide hole is arranged at an inlet of the first-stage volute, and the third flow guide hole is connected with the second flow guide hole through a pipeline.
6. The air compressor as claimed in claim 5, wherein the inlet of the first-stage volute and the inlet of the first flow-guiding hole are connected to an air filter.
7. The air compressor as claimed in claim 5, wherein the cooling air passage includes a first annular air groove and a plurality of first radial air introduction grooves provided on a front end surface of the front thrust bearing, and a second annular air groove and a plurality of second radial air introduction grooves provided on a rear end surface of the rear thrust bearing, the first annular air groove and the second annular air groove being connected by a through hole passing through the gap isolation plate.
8. The air compressor as claimed in claim 5, wherein a first air outlet hole is provided between the second flow guiding hole and the cooling air channel for guiding air in the cooling air channel to the inner cavity of the motor.
9. The air compressor as claimed in claim 8, wherein the casing has a coolant circulation channel, the second drainage holes include radial air holes and axial air holes, the radial air holes are formed in a rear end of the casing, a rear end of the axial air hole is connected to the radial air holes, and the axial air holes extend forward along the casing, are guided out through the second air outlet holes after exchanging heat with the coolant circulation channel, and are connected to the third drainage holes through the pipes.
10. A fuel cell system, characterized by comprising the air compressor of any one of claims 1 to 9.
CN202111348762.7A 2021-11-15 2021-11-15 Air compressor and fuel cell system Pending CN114165464A (en)

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Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN114673681A (en) * 2022-04-22 2022-06-28 天津捷强动力装备股份有限公司 Axial balance and sealing structure of high-speed air suspension fan
CN114810624A (en) * 2022-05-02 2022-07-29 烟台东德实业有限公司 Bilateral two-stage internal circulation high-speed centrifugal air compressor
CN115853798A (en) * 2022-11-26 2023-03-28 黑龙江云造科技有限公司 Centrifugal air compressor for fuel cell

Citations (22)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JPH06173883A (en) * 1992-10-06 1994-06-21 Toyo Denki Kogyosho:Kk Submerged pump
CN1221068A (en) * 1997-12-23 1999-06-30 亚瑞亚·勃朗勃威力有限公司 Method and device for non-contact sealing between rotor and stator
CN104121225A (en) * 2014-08-06 2014-10-29 南京磁谷科技有限公司 Centrifugal blower with rotor axial force control device
CN204061283U (en) * 2014-08-06 2014-12-31 南京磁谷科技有限公司 A kind of centrifugal blower with rotor axial force control device
US20150008771A1 (en) * 2013-07-05 2015-01-08 Korea Institute Of Science And Technology Motor having cooling means
CN104334887A (en) * 2012-05-29 2015-02-04 普莱克斯技术有限公司 Compressor thrust bearing surge protection
CN205371095U (en) * 2015-12-11 2016-07-06 石家庄金士顿轴承科技有限公司 Centrifugal blower rotor forced air cooling system
CN205779869U (en) * 2016-05-06 2016-12-07 亿昇(天津)科技有限公司 A kind of magnetic suspension blower fan sealing structure and there is this sealing structure
CN106246596A (en) * 2016-09-26 2016-12-21 南京磁谷科技有限公司 A kind of adjustable impeller assembly of axial force and method of work thereof
CN206206268U (en) * 2016-09-26 2017-05-31 南京磁谷科技有限公司 A kind of adjustable impeller assembly of axial force
CN107313989A (en) * 2016-11-28 2017-11-03 盾石磁能科技有限责任公司 Magnetic suspension cfentrifugal blower air cooling system
CN109026761A (en) * 2018-10-18 2018-12-18 毕森机械（上海）有限公司 A kind of compressor host
CN109268287A (en) * 2018-09-11 2019-01-25 朴昌金 The unpowered cooling device of direct-connected drive-type twocouese blower
CN110094236A (en) * 2019-04-16 2019-08-06 西安航天动力研究所 A kind of helium turbine shaft architecture
CN209781242U (en) * 2019-08-29 2019-12-13 势加透博洁净动力如皋有限公司 Centrifugal electronic air compressor machine that directly drives of two-stage gas suspension
CN111478497A (en) * 2020-04-21 2020-07-31 北京稳力科技有限公司 Two-stage series centrifugal gas compressor and motor thereof
CN112253493A (en) * 2020-10-15 2021-01-22 上海发电设备成套设计研究院有限责任公司 Air compressor for hydrogen fuel cell
CN112460047A (en) * 2020-11-26 2021-03-09 广州市昊志机电股份有限公司 Two-stage centrifugal compressor and hydrogen fuel cell system
CN112460056A (en) * 2020-11-26 2021-03-09 广州市昊志机电股份有限公司 Centrifugal air compressor and hydrogen fuel cell
CN112943642A (en) * 2021-04-15 2021-06-11 河北金士顿科技有限责任公司 Air compressor shell using closed-loop cooling and air compressor
CN213598241U (en) * 2020-11-20 2021-07-02 无锡宜友机电制造有限公司 Composite sealing structure of high-speed motor direct-drive centrifugal blower
CN213717784U (en) * 2020-10-15 2021-07-16 河北金士顿科技有限责任公司 Cooling system of two-stage air suspension centrifugal permanent magnet motor direct-drive air compressor

Patent Citations (22)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JPH06173883A (en) * 1992-10-06 1994-06-21 Toyo Denki Kogyosho:Kk Submerged pump
CN1221068A (en) * 1997-12-23 1999-06-30 亚瑞亚·勃朗勃威力有限公司 Method and device for non-contact sealing between rotor and stator
CN104334887A (en) * 2012-05-29 2015-02-04 普莱克斯技术有限公司 Compressor thrust bearing surge protection
US20150008771A1 (en) * 2013-07-05 2015-01-08 Korea Institute Of Science And Technology Motor having cooling means
CN104121225A (en) * 2014-08-06 2014-10-29 南京磁谷科技有限公司 Centrifugal blower with rotor axial force control device
CN204061283U (en) * 2014-08-06 2014-12-31 南京磁谷科技有限公司 A kind of centrifugal blower with rotor axial force control device
CN205371095U (en) * 2015-12-11 2016-07-06 石家庄金士顿轴承科技有限公司 Centrifugal blower rotor forced air cooling system
CN205779869U (en) * 2016-05-06 2016-12-07 亿昇(天津)科技有限公司 A kind of magnetic suspension blower fan sealing structure and there is this sealing structure
CN106246596A (en) * 2016-09-26 2016-12-21 南京磁谷科技有限公司 A kind of adjustable impeller assembly of axial force and method of work thereof
CN206206268U (en) * 2016-09-26 2017-05-31 南京磁谷科技有限公司 A kind of adjustable impeller assembly of axial force
CN107313989A (en) * 2016-11-28 2017-11-03 盾石磁能科技有限责任公司 Magnetic suspension cfentrifugal blower air cooling system
CN109268287A (en) * 2018-09-11 2019-01-25 朴昌金 The unpowered cooling device of direct-connected drive-type twocouese blower
CN109026761A (en) * 2018-10-18 2018-12-18 毕森机械（上海）有限公司 A kind of compressor host
CN110094236A (en) * 2019-04-16 2019-08-06 西安航天动力研究所 A kind of helium turbine shaft architecture
CN209781242U (en) * 2019-08-29 2019-12-13 势加透博洁净动力如皋有限公司 Centrifugal electronic air compressor machine that directly drives of two-stage gas suspension
CN111478497A (en) * 2020-04-21 2020-07-31 北京稳力科技有限公司 Two-stage series centrifugal gas compressor and motor thereof
CN112253493A (en) * 2020-10-15 2021-01-22 上海发电设备成套设计研究院有限责任公司 Air compressor for hydrogen fuel cell
CN213717784U (en) * 2020-10-15 2021-07-16 河北金士顿科技有限责任公司 Cooling system of two-stage air suspension centrifugal permanent magnet motor direct-drive air compressor
CN213598241U (en) * 2020-11-20 2021-07-02 无锡宜友机电制造有限公司 Composite sealing structure of high-speed motor direct-drive centrifugal blower
CN112460047A (en) * 2020-11-26 2021-03-09 广州市昊志机电股份有限公司 Two-stage centrifugal compressor and hydrogen fuel cell system
CN112460056A (en) * 2020-11-26 2021-03-09 广州市昊志机电股份有限公司 Centrifugal air compressor and hydrogen fuel cell
CN112943642A (en) * 2021-04-15 2021-06-11 河北金士顿科技有限责任公司 Air compressor shell using closed-loop cooling and air compressor

Cited By (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN114673681A (en) * 2022-04-22 2022-06-28 天津捷强动力装备股份有限公司 Axial balance and sealing structure of high-speed air suspension fan
CN114673681B (en) * 2022-04-22 2023-10-20 天津捷强动力装备股份有限公司 Axial balance and sealing structure of high-speed air suspension fan
CN114810624A (en) * 2022-05-02 2022-07-29 烟台东德实业有限公司 Bilateral two-stage internal circulation high-speed centrifugal air compressor
CN115853798A (en) * 2022-11-26 2023-03-28 黑龙江云造科技有限公司 Centrifugal air compressor for fuel cell

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