CN112460047A - Two-stage centrifugal compressor and hydrogen fuel cell system - Google Patents
Two-stage centrifugal compressor and hydrogen fuel cell system Download PDFInfo
- Publication number
- CN112460047A CN112460047A CN202011344936.8A CN202011344936A CN112460047A CN 112460047 A CN112460047 A CN 112460047A CN 202011344936 A CN202011344936 A CN 202011344936A CN 112460047 A CN112460047 A CN 112460047A
- Authority
- CN
- China
- Prior art keywords
- stage
- impeller
- air
- shell
- cooling medium
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Pending
Links
Images
Classifications
-
- 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
- F04D29/5826—Cooling at least part of the working fluid in a heat exchanger
-
- 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
-
- 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
- F04D25/08—Units comprising pumps and their driving means the working fluid being air, e.g. for ventilation
-
- 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
- F04D29/05—Shafts or bearings, or assemblies thereof, specially adapted for elastic fluid pumps
- F04D29/051—Axial thrust balancing
-
- 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
- F04D29/05—Shafts or bearings, or assemblies thereof, specially adapted for elastic fluid pumps
- F04D29/056—Bearings
- F04D29/057—Bearings hydrostatic; hydrodynamic
-
- 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
- F04D29/5846—Cooling; Heating; Diminishing heat transfer specially adapted for elastic fluid pumps cooling by injection
-
- 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
- F04D29/5853—Cooling; Heating; Diminishing heat transfer specially adapted for elastic fluid pumps heat insulation or conduction
-
- 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
-
- 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
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Physics & Mathematics (AREA)
- Thermal Sciences (AREA)
- Life Sciences & Earth Sciences (AREA)
- Fluid Mechanics (AREA)
- Manufacturing & Machinery (AREA)
- Sustainable Development (AREA)
- Sustainable Energy (AREA)
- Chemical & Material Sciences (AREA)
- Chemical Kinetics & Catalysis (AREA)
- Electrochemistry (AREA)
- General Chemical & Material Sciences (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
Abstract
The invention discloses a two-stage centrifugal compressor and hydrogen fuel cell system, comprising: the motor assembly comprises a shell, a rotating shaft, a stator and a rotor, wherein the rotating shaft is rotatably arranged in the shell, the stator is connected with the shell, and the rotor is connected with the rotating shaft; the first-stage compression assembly comprises a first-stage impeller and a current collector, the first-stage impeller is arranged at one end of the rotating shaft, and the current collector is arranged at one end of the shell corresponding to the first-stage impeller; the second-stage compression assembly comprises a second-stage impeller and a volute, the second-stage impeller is arranged at the other end of the rotating shaft, and the volute is arranged at one end of the shell corresponding to the second-stage impeller; the interstage cooling structure is arranged on the shell between the first-stage compression assembly and the second-stage compression assembly and is provided with a gas circuit and a cooling medium channel, the gas circuit is used for communicating an outlet of the current collector with an inlet of the volute, and the gas circuit flows through the area of the cooling medium channel to exchange heat with the cooling medium channel. The shaft power of the two-stage compression system can be reduced to a great extent, and therefore the system efficiency is improved.
Description
Technical Field
The invention is used in the field of fuel cells, and particularly relates to a two-stage centrifugal compressor and a hydrogen fuel cell system.
Background
Hydrogen fuel cells must operate at relatively high gas pressures to achieve high power densities and performance, and therefore require high efficiency, high pressure ratio air compressors to provide high pressure air to the fuel cells. The air compressors adopted by the current hydrogen fuel cells are mainly roots type, vortex type, screw type and centrifugal type. The centrifugal air compressor has the advantages of compact structure, small size, light weight, obvious reduction of vibration and noise, high dynamic response speed and the like, so that the centrifugal fuel cell air compressor is a future development trend.
At present, in the field of fuel cells, in order to obtain a higher air pressure ratio, a centrifugal air compressor mainly adopts a two-stage compression structure form, because of the limitation of a fuel cell space structure, high-temperature and high-pressure air after primary compression is often directly introduced into a two-stage system for compression, because the temperature of air at a secondary inlet is high, the power consumed when the same pressure ratio is reached is larger, and the compression efficiency is low.
Disclosure of Invention
The present invention is directed to solving at least one of the problems of the prior art and to providing a two-stage centrifugal compressor and a hydrogen fuel cell system, which can reduce the shaft power of the two-stage compression system to a great extent, thereby improving the system efficiency.
The technical scheme adopted by the invention for solving the technical problems is as follows:
in a first aspect, a two-stage centrifugal compressor comprises:
the motor assembly comprises a shell, a rotating shaft, a stator and a rotor, wherein the rotating shaft is rotatably arranged in the shell, the stator is connected with the shell, and the rotor is connected with the rotating shaft;
the primary compression assembly comprises a primary impeller and a current collector, the primary impeller is arranged at one end of the rotating shaft, and the current collector is arranged at one end of the shell corresponding to the primary impeller;
the second-stage compression assembly comprises a second-stage impeller and a volute, the second-stage impeller is mounted at the other end of the rotating shaft, and the volute is mounted at one end of the shell corresponding to the second-stage impeller;
an interstage cooling structure disposed in the housing between the first stage compression assembly and the second stage compression assembly, the interstage cooling structure having a gas path and a cooling medium passage, the gas path communicating an outlet of the collector and an inlet of the volute, the gas path flowing through a region of the cooling medium passage to exchange heat with the cooling medium passage.
With reference to the first aspect, in certain implementations of the first aspect, the casing includes an inner casing and an outer casing, the interstage cooling structure includes an inner partition ring and an outer partition ring, the inner partition ring is sleeved outside the inner casing, a first cooling medium channel is defined between the inner partition ring and the inner casing, the outer partition ring is disposed inside the outer casing, a second cooling medium channel is defined between the outer partition ring and the outer casing, and the annular gas path is formed between the inner partition ring and the outer partition ring.
With reference to the first aspect and the foregoing implementation manners, in some implementation manners of the first aspect, a spiral groove for circulating a cooling medium is formed in an outer circle of the inner shell, the inner spacer is sleeved outside the inner shell and is connected with the inner shell in an interference fit manner, and sealing rings are arranged at two ends of the inner shell; the hole of shell body is provided with the helicla flute that supplies the cooling medium circulation, outer spacer ring sets up at the shell body inboard, and with shell body interference fit connects, and both ends are provided with the sealing washer.
With reference to the first aspect and the foregoing implementation manners, in certain implementation manners of the first aspect, a heat dissipation fin is disposed between the inner spacer ring and the outer spacer ring, an outer circumferential surface of the heat dissipation fin is connected to an inner hole surface of the outer spacer ring, and an inner circumferential surface of the heat dissipation fin is connected to an outer circumferential surface of the inner spacer ring.
With reference to the first aspect and the foregoing implementation manners, in certain implementation manners of the first aspect, a blade tip of the first-stage impeller and the collector inner contour surface form a first impeller seal gap, a blade tip of the second-stage impeller and the volute inner contour surface form a second impeller seal gap, and the first impeller seal gap and the second impeller seal gap are a same-direction gap.
With reference to the first aspect and the implementations described above, in certain implementations of the first aspect, the motor assembly further includes a forward radial bearing assembly, a rearward radial bearing assembly, and a thrust bearing assembly, the forward radial bearing assembly is mounted to the forward end of the housing, the forward radial bearing assembly including a forward bearing seat and a forward radial foil air bearing, the aft radial bearing assembly is mounted to the aft end of the housing, the aft radial bearing assembly including an aft bearing seat and an aft radial foil air bearing, the thrust bearing assembly is arranged in the front bearing seat, the thrust bearing assembly comprises a front thrust bearing, a rear thrust bearing and a clearance isolation plate, the rotating shaft is arranged in a hollow shaft hole formed by the front radial foil air bearing and the rear radial foil air bearing, the front end of the rotating shaft is provided with a flange bulge, and the flange bulge is installed and limited in an annular air cavity formed by the front thrust bearing and the rear thrust bearing.
With reference to the first aspect and the foregoing implementation manners, in some implementation manners of the first aspect, the first-stage compression assembly further includes a first-stage diffuser installed at a radial outlet of the first-stage impeller, and the first-stage diffuser is connected to a front bearing seat; the second-stage compression assembly further comprises a second-stage diffuser arranged at the radial outlet of the second-stage impeller, and the second-stage diffuser is connected with the volute.
With reference to the first aspect and the foregoing implementation manners, in certain implementation manners of the first aspect, an annular channel of a primary compressed gas is formed by an inner annular surface of the current collector and an outer annular surface of the front bearing seat, the annular channel is in butt joint with the gas circuit, a sealing ring groove is formed in the back of the primary impeller, the sealing ring groove and a surface protrusion of the front thrust bearing form an axial sealing structure, and a sealing ring groove is formed in the back of the secondary impeller and forms an axial sealing structure with a surface protrusion of the rear cover.
With reference to the first aspect and the foregoing implementation manners, in some implementation manners of the first aspect, the secondary compression assembly further includes a backflow device disposed between the rear bearing seat and the volute, an annular channel through which compressed air passes is formed by an outer surface of the backflow device and an inner surface of the volute, the backflow device is provided with a guide vane, the rear bearing seat is provided with an air guide hole at a rear side of the backflow device, the front bearing seat and the rear thrust bearing are provided with an air guide hole, the gap isolation plate, the front bearing seat and the housing are provided with an air outlet hole, and the air guide hole, the motor air gap, the air guide hole, the annular air cavity of the thrust bearing assembly and the air outlet hole form an internal circulation air cooling loop of the motor assembly.
In a second aspect, a hydrogen fuel cell system includes the two-stage centrifugal 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:
an interstage cooling structure is arranged between the first-stage compression component and the second-stage compression component of the two-stage centrifugal compressor, high-temperature air at the outlet of the first-stage compression can be cooled, the air temperature at the inlet of the second-stage compression is reduced, the second-stage compression power is further reduced, and the compression efficiency of the system is improved.
The interstage cooling structure is directly integrated on the shell of the compressor, the structure is simple and compact, the cooling efficiency is high, the space outside the compressor is not occupied, and the structural layout of the fuel cell is convenient.
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 block diagram of one embodiment of a two-stage centrifugal compressor according to the present invention;
FIG. 2 is a schematic illustration of an exemplary interstage cooling configuration shown in FIG. 1;
FIG. 3 is a schematic view of a circulating air cooling circuit within the electric machine assembly of one embodiment 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 shows a reference direction coordinate system of an embodiment of the present invention, and the following describes an embodiment of the present invention with reference to the directions shown in fig. 1.
Referring to fig. 1, an embodiment of the present invention provides a two-stage centrifugal compressor including a motor assembly 2, a one-stage compression assembly 1, a two-stage compression assembly 3, and an interstage cooling structure 4.
The motor assembly 2 comprises a shell, a rotating shaft 204, a stator 203 and a rotor, wherein the rotating shaft 204 is rotatably arranged in the shell, the stator 203 is connected with the shell, the rotor is connected with the rotating shaft 204, and the rotating shaft 204 can rotate at a high speed under the interaction of the stator 203 and the rotor, so that power is provided for the centrifugal compressor, and air compression is realized.
Referring to fig. 1, the primary compression assembly 1 includes a primary impeller 103 and a current collector 105, the primary impeller 103 is mounted at the front end of a rotating shaft 204 through a screw rod one 102 and a nut one 101, and the current collector 105 is mounted at one end, namely the front end, of a shell corresponding to the primary impeller 103; the two-stage compression assembly 3 comprises a two-stage impeller 302 and a volute 304, the two-stage impeller 302 is mounted at the rear end of the rotating shaft 204 through a second screw 307 and a second nut 306, and the volute 304 is mounted at one end, namely the rear end, of the shell corresponding to the two-stage impeller 302. First-level compression component 1, second grade compression component 3 are located the both ends of casing respectively, and motor element 2 sets up between first-level compression component 1, second grade compression component 3. When the primary impeller 103 rotates along with the rotating shaft 204, air is continuously sucked from the inlet of the collector 105, and is discharged from the outlet of the collector 105 after being compressed, so that primary compression is realized. The air compressed by the first stage further enters the volute 304, and is discharged from the outlet of the volute 304 after being compressed. Meanwhile, air is compressed in two stages, and the pressure ratio is greatly improved.
In order to obtain a higher air pressure ratio, a centrifugal air compressor mostly adopts a two-stage compression structure, and because of the space structure limitation of a fuel cell, high-temperature and high-pressure air after first-stage compression is often directly introduced into a second-stage system for compression. However, the air temperature at the outlet of the first-stage impeller 103 can reach 120 to 150 ℃ (when the ambient temperature is 25 ℃), and at this time, the higher the gas temperature is, the harder it is to compress, the higher the compressor power required for reaching the same pressure ratio is, and if the compressed air at the temperature is directly introduced into the second-stage compression component 3 for compression, the axial power load of the second-stage compression component 3 will be increased to a great extent, and further the motor power output is increased, resulting in low efficiency of the compressor system. At the moment, if the high-temperature and high-pressure gas at the primary outlet of the air compressor can be cooled, the temperature of the compressed air is reduced, if the compressed air is cooled to 40-60 ℃, the shaft power of a secondary compression system can be reduced to a great extent, and therefore the system efficiency is improved. However, due to the structural space limitations of the fuel cell, it is difficult to provide an efficient cooling structure. In view of this, referring to fig. 1, the present application provides an interstage cooling structure 4 integrated with a centrifugal air compressor, that is, the interstage cooling structure 4 is provided in a housing between the first-stage compression assembly 1 and the second-stage compression assembly 3, the interstage cooling structure 4 is provided with a gas path 404 and a cooling medium passage, the gas path 404 communicates an outlet of the collector 105 with an inlet of the volute 304, and the gas path 404 flows through a region of the cooling medium passage to exchange heat with the cooling medium passage. The cooling medium in the cooling medium channel passes through the air path 404 to cool the high-temperature compressed air, and absorbs the heat of the motor stator 203 through the housing to cool the motor stator 203. The air is cooled by the cooling liquid passing through the inside of the shell before entering the secondary impeller 302, the temperature of the gas entering the secondary impeller is reduced, the secondary compression is easier, the efficiency is higher, the power of the secondary compression is reduced, and the power consumption is lower. Moreover, the gas path 404 is arranged inside the shell, so that the structure of the gas path 404 between the first-stage compression assembly 1 and the second-stage compression assembly 3 is greatly simplified, and the space outside the compressor is not occupied, so that the structures of a centrifugal air compressor, a hydrogen fuel cell and the like are more compact.
The cooling medium passage and the air passage 404 may take various structural forms to meet the purpose of cooling and heat exchange, for example, the cooling medium passage adopts a cooling water jacket disposed in the housing, and the air passage 404 is an air flow through hole disposed outside the cooling water jacket. For example, in some embodiments shown in fig. 1 and 2, the casing includes an inner casing 201 and an outer casing 408, the interstage cooling structure 4 includes an inner partition 403 and an outer partition 406, the inner partition 403 is in a sleeve shape, the inner partition 403 is sleeved outside the inner casing 201, a first cooling medium channel 402 is defined between the inner partition 403 and the inner casing 201, the inner partition 403 is in a sleeve shape, the outer partition 406 is arranged inside the outer casing 408, a second cooling medium channel 407 is defined between the outer partition 406 and the outer casing 408, and an annular air passage 404 is formed between the inner partition 403 and the outer partition 406. The interstage cooling structure 4 forms an inner and outer dual circulation cooling flow path for the cooling medium through the inner casing 201 and the inner spacer ring 403, and the outer casing 408 and the outer spacer ring 406. The cooling medium in the first cooling medium channel 402 absorbs heat of air through the inner partition ring 403 to cool the high-temperature compressed air, and absorbs heat of the motor stator 203 through the inner casing 201 to cool the motor stator 203; the cooling medium in the second cooling medium passage 407 mainly absorbs the heat of the air through the outer spacer ring 406 to cool the high-temperature compressed air in the annular passage. The air path 404 is sandwiched between the cooling medium channels on both sides, and the cooling effect is greatly enhanced.
Further, referring to fig. 1 and 2, the outer circumference of the inner housing 201 is provided with a spiral groove for circulating a cooling medium, and the spiral groove is communicated with the outside through a through hole provided in a flange of the inner housing 201. The inner spacer 403 is sleeved outside the inner shell 201 and is connected with the inner shell 201 in an interference fit manner, and sealing rings are arranged at two ends of the inner spacer to prevent a cooling medium in the spiral groove from leaking. Obviously, the spiral groove on the outer circumference of the inner casing 201 and the inner surface of the inner spacer 403 form the first cooling medium passage 402 with good sealing performance for the cooling medium to flow through. The inner hole of the outer shell 408 is provided with a spiral groove for circulation of a cooling medium, the outer spacer ring 406 is arranged on the inner side of the outer shell 408 and is connected with the outer shell 408 in an interference fit manner, and sealing rings are arranged at two ends of the outer spacer ring to prevent the cooling medium in the spiral groove from leaking. Obviously, the inner circular spiral groove of the outer casing 408 and the outer surface of the outer spacer ring 406 form a second cooling medium passage 407 with good sealing performance for the circulation of the cooling medium. The cooling medium flows along the spiral cooling medium channel, so that the heat exchange effect between the cooling medium and the part to be cooled is prolonged, and the heat exchange is more sufficient.
Further, according to the needs, in order to increase the heat dissipation, referring to fig. 1 and fig. 2, a heat dissipation fin 405 is disposed between the inner spacer 403 and the outer spacer 406, an outer circumferential surface of the heat dissipation fin 405 is connected with an inner hole surface of the outer spacer 406 and has good heat conductivity, and an inner circumferential surface of the heat dissipation fin 405 is connected with an outer circumferential surface of the inner spacer 403 and has good heat conductivity. In summary, the interstage cooling structure 4 forms an inner and outer dual circulation cooling flow path for the cooling medium through the inner casing 201 and the inner spacer 403, and the outer casing 408 and the outer spacer 406. The cooling medium in the first cooling medium channel 402 absorbs the heat of the heat dissipation fins 405 through the inner partition ring 403 to cool the high-temperature compressed air, and absorbs the heat of the motor stator 203 through the inner shell 201 to cool the motor stator 203; the cooling medium in the second cooling medium passage 407 mainly absorbs the heat of the heat radiating fins 405 through the outer spacer ring 406 to cool the high-temperature compressed air in the annular passage. It is understood that the heat dissipating fins 405 provided in the annular channel may have various configurations, and are designed to have a large heat dissipating area and a small flow resistance.
Referring to fig. 1, a first impeller seal gap is formed between the top of the first-stage impeller 103 and the inner profile surface of the current collector 105, and a second impeller seal gap is formed between the top of the second-stage impeller 302 and the inner profile surface of the volute 304, where the first impeller seal gap and the second impeller seal gap are equidirectional gaps, and when the rotating shaft 204 axially displaces relative to the casing, the seal gaps between the first-stage impeller 103 and the second-stage impeller 302 and the corresponding shrouds change in the same direction, that is, become larger or smaller at the same time, and such a structural layout facilitates the management and control of the seal gaps between the impellers and the shrouds, thereby improving the efficiency of the compression system.
Referring to fig. 1, the motor assembly 2 further includes a front radial bearing assembly mounted at the front end of the housing, the front radial bearing assembly including a front bearing seat 202 and a front radial foil air bearing 207, a rear radial bearing assembly mounted at the rear end of the housing, the rear radial bearing assembly including a rear bearing seat 205 and a rear radial foil air bearing 206, a thrust bearing assembly disposed within the front bearing seat 202, and a thrust bearing assembly including a front thrust bearing 210, a rear thrust bearing 208, and a gap spacer 209, a rotating shaft 204 mounted within a hollow shaft bore formed by the front radial foil air bearing 207 and the rear radial foil air bearing 206, the front end of the rotating shaft 204 being provided with flange protrusions mounted to be confined within an annular air cavity formed by the front thrust bearing 210 and the rear thrust bearing 208.
Further, referring to fig. 1, the first-stage compression assembly 1 further includes a first-stage diffuser 104 installed at a radial outlet of the first-stage impeller 103, and the first-stage diffuser 104 is connected to the front bearing seat 202; the two-stage compression assembly 3 further comprises a two-stage diffuser 303 mounted at the radial outlet of the two-stage impeller 302, the two-stage diffuser 303 being connected to a volute 304.
The inner ring surface of the collector 105 and the outer ring surface of the front bearing seat 202 form a first-stage compressed gas annular channel, the annular channel is in butt joint with the gas circuit 404, the back of the first-stage impeller 103 is provided with a sealing ring groove, the sealing ring groove and the surface protrusion of the front thrust bearing 210 form an axial sealing structure, and the back of the second-stage impeller 302 is provided with a sealing ring groove and forms an axial sealing structure with the surface protrusion of the rear cover.
After the motor is started, the rotating shaft 204 runs under the support of the foil dynamic pressure bearing to drive the first-stage impeller 103 and the second-stage impeller 302 fixed at the front end and the rear end of the rotating shaft 204 to rotate, so that air compression is realized. The high temperature and high pressure air from the outlet of the first stage compressor 1 enters the interstage cooling structure 4 along the annular channel formed by the inner annular surface of the collector 105 and the outer annular surface of the front bearing seat 202. The annular passage formed by the inner and outer spacers 403 and 406 of the interstage cooling structure 4 is provided with heat dissipation fins 405, and when high-temperature gas passes through the heat dissipation fins 405, heat is quickly absorbed by the fins. The heat of the heat dissipation fins 405 is transferred to the cooling medium in the spiral channel formed by the outer casing 408 and the outer spacer 406 through the outer spacer 406 on the one hand, and is transferred to the cooling medium in the spiral channel formed by the inner casing 201 and the inner spacer 403 through the inner spacer 403 on the other hand, so that the heat is rapidly transferred, and the high-temperature compressed air is rapidly cooled. The cooled compressed air enters an inlet of the secondary compression component 3 through the reflux device, and forms high-temperature and high-pressure air after secondary compression, and the air is supplied to a fuel cell and the like.
Referring to fig. 1 and 3, the two-stage compression assembly 3 further includes a flow reverser 301 disposed between the rear bearing housing 205 and the scroll 304, an annular passage through which compressed air passes is formed by an outer surface of the flow reverser 301 and an inner surface of the scroll 304, and guide vanes are disposed on the flow reverser 301. In order to improve the heat dissipation of the bearing and the motor, an air guide hole 211 is arranged on the rear bearing seat 205 and behind the reflux device 301, an air guide hole 213 is arranged on the front bearing seat 202 and the rear thrust bearing 208, air outlet holes 215 are arranged on the gap isolation plate 209, the front bearing seat 202 and the shell, and an internal circulation air cooling loop of the motor assembly 2 is formed by the air guide hole 211, the motor air gap, the air guide hole 213, the annular air cavity of the thrust bearing assembly and the air outlet holes 215. The first-stage compressed air cooled by the interstage cooling structure can be partially introduced into the motor body, so that the motor and the bearing are cooled internally.
Embodiments of the present invention provide a hydrogen fuel cell system comprising a two-stage centrifugal compressor as in any of the above embodiments. The cooling device solves the problems of interstage cooling of the two-stage air compressor of the fuel cell and cooling of the motor.
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. A two-stage centrifugal compressor, comprising:
the motor assembly comprises a shell, a rotating shaft, a stator and a rotor, wherein the rotating shaft is rotatably arranged in the shell, the stator is connected with the shell, and the rotor is connected with the rotating shaft;
the primary compression assembly comprises a primary impeller and a current collector, the primary impeller is arranged at one end of the rotating shaft, and the current collector is arranged at one end of the shell corresponding to the primary impeller;
the second-stage compression assembly comprises a second-stage impeller and a volute, the second-stage impeller is mounted at the other end of the rotating shaft, and the volute is mounted at one end of the shell corresponding to the second-stage impeller;
an interstage cooling structure disposed in the housing between the first stage compression assembly and the second stage compression assembly, the interstage cooling structure having a gas path and a cooling medium passage, the gas path communicating an outlet of the collector and an inlet of the volute, the gas path flowing through a region of the cooling medium passage to exchange heat with the cooling medium passage.
2. The two-stage centrifugal compressor according to claim 1, wherein said casing comprises an inner casing and an outer casing, said interstage cooling structure comprising an inner spacer ring and an outer spacer ring, said inner spacer ring being nested outside said inner casing, said inner spacer ring and said inner casing defining a first cooling medium passage therebetween, said outer spacer ring being disposed inside said outer casing, said outer spacer ring and said outer casing defining a second cooling medium passage therebetween, said inner spacer ring and said outer spacer ring forming said gas path therebetween in an annular shape.
3. The two-stage centrifugal compressor according to claim 2, wherein the outer circle of the inner shell is provided with a spiral groove for circulating a cooling medium, the inner spacer ring is sleeved outside the inner shell and is connected with the inner shell in an interference fit manner, and two ends of the inner shell are provided with sealing rings; the hole of shell body is provided with the helicla flute that supplies the cooling medium circulation, outer spacer ring sets up at the shell body inboard, and with shell body interference fit connects, and both ends are provided with the sealing washer.
4. A two-stage centrifugal compressor according to claim 2, wherein heat dissipating fins are provided between said inner and outer distance rings, the outer circumferential surfaces of said heat dissipating fins being connected to the inner bore surface of said outer distance ring, and the inner circumferential surfaces of said heat dissipating fins being connected to the outer circumferential surface of said inner distance ring.
5. A two-stage centrifugal compressor according to claim 1 wherein said first stage impeller has a blade tip portion that forms a first impeller seal gap with said collector inner profile and said second stage impeller has a blade tip portion that forms a second impeller seal gap with said volute inner profile, said first and second impeller seal gaps being co-directional gaps.
6. The two-stage centrifugal compressor of claim 1, wherein the motor assembly further comprises a forward radial bearing assembly, an aft radial bearing assembly, and a thrust bearing assembly, the forward radial bearing assembly is mounted to the forward end of the housing, the forward radial bearing assembly including a forward bearing seat and a forward radial foil air bearing, the aft radial bearing assembly is mounted to the aft end of the housing, the aft radial bearing assembly including an aft bearing seat and an aft radial foil air bearing, the thrust bearing assembly is arranged in the front bearing seat, the thrust bearing assembly comprises a front thrust bearing, a rear thrust bearing and a clearance isolation plate, the rotating shaft is arranged in a hollow shaft hole formed by the front radial foil air bearing and the rear radial foil air bearing, the front end of the rotating shaft is provided with a flange bulge, and the flange bulge is installed and limited in an annular air cavity formed by the front thrust bearing and the rear thrust bearing.
7. The two-stage centrifugal compressor of claim 6, wherein the one-stage compression assembly further comprises a one-stage diffuser mounted at a radial outlet of the one-stage impeller, the one-stage diffuser coupled to a forward bearing seat; the second-stage compression assembly further comprises a second-stage diffuser arranged at the radial outlet of the second-stage impeller, and the second-stage diffuser is connected with the volute.
8. A two-stage centrifugal compressor according to claim 6, wherein the inner annular surface of said collector and the outer annular surface of the front bearing seat form an annular passage for the primary compressed gas, said annular passage being in abutment with said gas path, the back of said primary impeller being provided with a sealing ring groove, said sealing ring groove forming an axial seal with a surface projection of the front thrust bearing, and the back of said secondary impeller being provided with a sealing ring groove forming an axial seal with a surface projection of the back cover.
9. The two-stage centrifugal compressor according to claim 6, wherein the two-stage compression assembly further comprises a return device disposed between the rear bearing seat and the scroll casing, an annular passage through which compressed air passes is formed by an outer surface of the return device and an inner surface of the scroll casing, the return device is provided with guide vanes, the rear bearing seat is provided with air guide holes at a rear side of the return device, the front bearing seat and the rear thrust bearing are provided with air guide holes, the gap isolation plate, the front bearing seat and the casing are provided with air outlet holes, and an internal circulation air cooling loop of the motor assembly is formed by the air guide holes, a motor air gap, the air guide holes, an annular air cavity of the thrust bearing assembly and the air outlet holes.
10. A hydrogen fuel cell system comprising a two-stage centrifugal compressor according to any one of claims 1 to 9.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202011344936.8A CN112460047A (en) | 2020-11-26 | 2020-11-26 | Two-stage centrifugal compressor and hydrogen fuel cell system |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202011344936.8A CN112460047A (en) | 2020-11-26 | 2020-11-26 | Two-stage centrifugal compressor and hydrogen fuel cell system |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN112460047A true CN112460047A (en) | 2021-03-09 |
Family
ID=74808422
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202011344936.8A Pending CN112460047A (en) | 2020-11-26 | 2020-11-26 | Two-stage centrifugal compressor and hydrogen fuel cell system |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN112460047A (en) |
Cited By (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112879318A (en) * | 2021-04-02 | 2021-06-01 | 烟台东德实业有限公司 | High-speed centrifugal compressor |
| CN114165464A (en) * | 2021-11-15 | 2022-03-11 | 广州市昊志机电股份有限公司 | Air compressor and fuel cell system |
| CN114165462A (en) * | 2021-11-01 | 2022-03-11 | 广州市昊志机电股份有限公司 | Centrifugal air compressor and fuel cell system |
| CN114278604A (en) * | 2022-01-05 | 2022-04-05 | 北京临近空间飞艇技术开发有限公司 | Helium gas compressor of anti-surge start-up under high back pressure |
| CN114278589A (en) * | 2022-01-05 | 2022-04-05 | 北京临近空间飞艇技术开发有限公司 | Helium gas compressor |
| CN114370416A (en) * | 2021-12-27 | 2022-04-19 | 广州市昊志机电股份有限公司 | Air compressor and fuel cell system |
| DE102021121424A1 (en) | 2021-08-18 | 2023-02-23 | Zf Cv Systems Global Gmbh | Multi-stage, electrically driven compressor |
| CN116335968A (en) * | 2023-03-27 | 2023-06-27 | 广州汽车集团股份有限公司 | Air compressor and fuel cell |
| CN118008893A (en) * | 2024-03-26 | 2024-05-10 | 合肥德顺机电设备有限公司 | Energy-saving two-stage centrifugal air compressor |
Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4125345A (en) * | 1974-09-20 | 1978-11-14 | Hitachi, Ltd. | Turbo-fluid device |
| US20120017617A1 (en) * | 2010-07-20 | 2012-01-26 | Beers Craig M | Centrifugal compressor cooling path arrangement |
| CN107725174A (en) * | 2016-05-11 | 2018-02-23 | 株式会社马勒滤清*** | Turbocharger |
| CN109072928A (en) * | 2016-11-22 | 2018-12-21 | 填易涡轮机械商贸有限公司 | Turbo-compressor including intercooler |
| CN109268295A (en) * | 2018-11-20 | 2019-01-25 | 势加透博（北京）科技有限公司 | A kind of two-stage air compression system with diameter axial direction diffuser |
| 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 |
-
2020
- 2020-11-26 CN CN202011344936.8A patent/CN112460047A/en active Pending
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4125345A (en) * | 1974-09-20 | 1978-11-14 | Hitachi, Ltd. | Turbo-fluid device |
| US20120017617A1 (en) * | 2010-07-20 | 2012-01-26 | Beers Craig M | Centrifugal compressor cooling path arrangement |
| CN107725174A (en) * | 2016-05-11 | 2018-02-23 | 株式会社马勒滤清*** | Turbocharger |
| CN109072928A (en) * | 2016-11-22 | 2018-12-21 | 填易涡轮机械商贸有限公司 | Turbo-compressor including intercooler |
| CN109268295A (en) * | 2018-11-20 | 2019-01-25 | 势加透博（北京）科技有限公司 | A kind of two-stage air compression system with diameter axial direction diffuser |
| 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 |
Cited By (10)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112879318A (en) * | 2021-04-02 | 2021-06-01 | 烟台东德实业有限公司 | High-speed centrifugal compressor |
| DE102021121424A1 (en) | 2021-08-18 | 2023-02-23 | Zf Cv Systems Global Gmbh | Multi-stage, electrically driven compressor |
| CN114165462A (en) * | 2021-11-01 | 2022-03-11 | 广州市昊志机电股份有限公司 | Centrifugal air compressor and fuel cell system |
| CN114165462B (en) * | 2021-11-01 | 2023-11-14 | 广州市昊志机电股份有限公司 | Centrifugal air compressor and fuel cell system |
| CN114165464A (en) * | 2021-11-15 | 2022-03-11 | 广州市昊志机电股份有限公司 | Air compressor and fuel cell system |
| CN114370416A (en) * | 2021-12-27 | 2022-04-19 | 广州市昊志机电股份有限公司 | Air compressor and fuel cell system |
| CN114278604A (en) * | 2022-01-05 | 2022-04-05 | 北京临近空间飞艇技术开发有限公司 | Helium gas compressor of anti-surge start-up under high back pressure |
| CN114278589A (en) * | 2022-01-05 | 2022-04-05 | 北京临近空间飞艇技术开发有限公司 | Helium gas compressor |
| CN116335968A (en) * | 2023-03-27 | 2023-06-27 | 广州汽车集团股份有限公司 | Air compressor and fuel cell |
| CN118008893A (en) * | 2024-03-26 | 2024-05-10 | 合肥德顺机电设备有限公司 | Energy-saving two-stage centrifugal air compressor |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN112460047A (en) | Two-stage centrifugal compressor and hydrogen fuel cell system | |
| CN112460056A (en) | Centrifugal air compressor and hydrogen fuel cell | |
| CN112503025A (en) | Air compressor and vehicle | |
| KR20180124402A (en) | Turbo compressor | |
| CN113339285A (en) | Fuel cell centrifugal air compressor and fuel cell system | |
| CN110594170B (en) | Centrifugal compressor and hydrogen fuel cell system | |
| CN218669849U (en) | Fuel cell and centrifugal air compressor thereof | |
| CN114165462B (en) | Centrifugal air compressor and fuel cell system | |
| CN113809885A (en) | Compressor and air conditioner and automobile with same | |
| CN114165464A (en) | Air compressor and fuel cell system | |
| CN215762310U (en) | Two-stage centrifugal compressor with intermediate cooling | |
| CN114165463A (en) | Centrifugal air compressor and fuel cell system | |
| CN117040200A (en) | Motor for air compressor, air compressor and automobile | |
| CN114810673B (en) | Two-stage compression backflow internal circulation air cooling system of high-speed centrifugal compressor | |
| CN116538110A (en) | Magnetic suspension air compressor | |
| CN115898903A (en) | Fuel cell and centrifugal air compressor thereof | |
| CN215444442U (en) | Fuel cell centrifugal air compressor and fuel cell system | |
| CN211820078U (en) | Air compressor's drive casing, air compressor and vehicle | |
| CN112761972B (en) | Air compressor for fuel cell | |
| US20020094289A1 (en) | Scroll-type compressor with cooling fins included inside a discharge port of a compressed gas | |
| CN219993997U (en) | Centrifugal compressor cooling system with graphene-assisted cooling function | |
| CN219045467U (en) | Air suspension centrifugal refrigeration compressor | |
| CN116742879B (en) | Air-cooled heat radiation structure and magnetic levitation motor | |
| CN220726662U (en) | Centrifugal blower | |
| CN218829490U (en) | Fuel cell and centrifugal air compressor with double cooling systems |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination |