CN112555172A - Centrifugal air compressor and hydrogen fuel cell system - Google Patents
Centrifugal air compressor and hydrogen fuel cell system Download PDFInfo
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- CN112555172A CN112555172A CN202011350395.XA CN202011350395A CN112555172A CN 112555172 A CN112555172 A CN 112555172A CN 202011350395 A CN202011350395 A CN 202011350395A CN 112555172 A CN112555172 A CN 112555172A
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- 239000000446 fuel Substances 0.000 title claims abstract description 20
- UFHFLCQGNIYNRP-UHFFFAOYSA-N Hydrogen Chemical compound [H][H] UFHFLCQGNIYNRP-UHFFFAOYSA-N 0.000 title claims abstract description 11
- 239000001257 hydrogen Substances 0.000 title claims abstract description 11
- 229910052739 hydrogen Inorganic materials 0.000 title claims abstract description 11
- 230000006835 compression Effects 0.000 claims abstract description 40
- 238000007906 compression Methods 0.000 claims abstract description 40
- 239000000498 cooling water Substances 0.000 claims description 16
- 210000001503 joint Anatomy 0.000 claims description 4
- 230000009286 beneficial effect Effects 0.000 abstract description 4
- 239000007789 gas Substances 0.000 description 13
- 230000003068 static effect Effects 0.000 description 4
- 230000003071 parasitic effect Effects 0.000 description 3
- 238000006073 displacement reaction Methods 0.000 description 2
- 239000000463 material Substances 0.000 description 2
- 238000012986 modification Methods 0.000 description 2
- 230000004048 modification Effects 0.000 description 2
- 238000007789 sealing Methods 0.000 description 2
- 238000006467 substitution reaction Methods 0.000 description 2
- 238000006243 chemical reaction Methods 0.000 description 1
- 239000002826 coolant Substances 0.000 description 1
- 238000001816 cooling Methods 0.000 description 1
- 239000000110 cooling liquid Substances 0.000 description 1
- 230000003993 interaction Effects 0.000 description 1
- 230000002452 interceptive effect Effects 0.000 description 1
- 238000005096 rolling process Methods 0.000 description 1
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Classifications
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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
- F04D17/122—Multi-stage pumps the individual rotor discs being, one for each stage, on a common shaft and axially spaced, e.g. conventional centrifugal multi- stage compressors
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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
- 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
- F04D29/0513—Axial thrust balancing hydrostatic; hydrodynamic thrust bearings
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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
- 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
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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
- 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
- F04D29/286—Rotors specially for elastic fluids for centrifugal or helico-centrifugal pumps for radial-flow or helico-centrifugal pumps for compressors multi-stage rotors
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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
- 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
- F04D29/44—Fluid-guiding means, e.g. diffusers
- F04D29/441—Fluid-guiding means, e.g. diffusers especially adapted for elastic fluid pumps
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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
- 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
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- 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
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- 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
- H01M8/24—Grouping of fuel cells, e.g. stacking of fuel cells
- H01M8/2457—Grouping of fuel cells, e.g. stacking of fuel cells with both reactants being gaseous or vaporised
-
- 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)
- Physics & Mathematics (AREA)
- Fluid Mechanics (AREA)
- Life Sciences & Earth Sciences (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)
- Thermal Sciences (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
- Fuel Cell (AREA)
Abstract
The invention discloses a centrifugal air compressor and hydrogen fuel cell system, comprising: the motor assembly comprises a shell, a shaft core, a thrust bearing, a stator and a rotor; the first-stage compression assembly comprises a first-stage impeller and a first-stage volute, the first-stage impeller is arranged at one end of the shaft core, and the first-stage volute 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 second-stage volute, the second-stage impeller is arranged at the other end of the shaft core, and the second-stage volute is arranged at the other end of the shell corresponding to the second-stage impeller; the turbine assembly comprises a turbine and a turbine volute, the turbine is connected to the end portion, deviating from one side of the first-stage impeller, of the shaft core, the turbine volute is installed on the second-stage volute, the turbine and the second-stage impeller are installed on two sides of the thrust bearing back to back, and the back of the turbine and the back of the second-stage impeller are used as thrust surfaces to limit the axial position of the shaft core. The shaft core reduces flying discs, reduces weight, shortens the length of the shaft core and is beneficial to improving the high-speed stability of the shaft core.
Description
Technical Field
The invention is used in the field of fuel cells, and particularly relates to a centrifugal air 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 cell.
In the prior art, the shaft core of the traditional fuel cell centrifugal air compressor is provided with a structure of a flying disc, and is used for realizing the axial positioning of the shaft core. But the arrangement of the flying disc structure makes the shaft core heavier, and the flying disc and the thrust bearing occupy a large space in the axial direction, thereby increasing the length of the shaft core, being not beneficial to the high-speed rotation of the shaft core and also increasing the volume of the whole compressor.
In addition, conventional fuel cell centrifugal air compressors are primarily single stage compression and two stage compression. The single-stage compression has limited compression efficiency and low pressure ratio, the existing two-stage compression efficiency is improved relative to the single-stage compression pressure ratio, but the structure is bloated, the two-stage compression is difficult, the efficiency is low, and the compression power consumption is high.
Disclosure of Invention
The invention aims to solve at least one of the technical problems in the prior art, and provides a centrifugal air compressor and a hydrogen fuel cell system, which reduces flying discs, reduces weight, shortens the length of a shaft core, is beneficial to improving the high-speed stability of the shaft core, and is more compact after the flying discs are eliminated.
The technical scheme adopted by the invention for solving the technical problems is as follows:
in a first aspect, a centrifugal air compressor comprises:
the motor assembly comprises a shell, a shaft core, a thrust bearing, a stator and a rotor, wherein the shaft core is rotatably arranged in the shell, the stator is connected with the shell, and the rotor is connected with the shaft core;
the first-stage compression assembly comprises a first-stage impeller and a first-stage volute, the first-stage impeller is mounted at one end of the shaft core, and the first-stage volute is mounted at one end of the shell corresponding to the first-stage impeller;
the second-stage compression assembly comprises a second-stage impeller and a second-stage volute, the second-stage impeller is mounted at the other end of the shaft core, and the second-stage volute is mounted at the other end of the shell corresponding to the second-stage impeller;
the turbine assembly comprises a turbine and a turbine volute, the turbine is connected to the end part, deviating from the first-stage impeller, of the shaft core on one side of the second-stage impeller, the turbine volute is installed on the second-stage volute, the turbine and the second-stage impeller are installed on two sides of the thrust bearing in a back-to-back mode, and the axial position of the shaft core is limited by using the back parts of the turbine and the second-stage impeller as thrust surfaces.
With reference to the first aspect, in certain implementations of the first aspect, the casing is provided with a cooling water jacket, an air path is provided inside the casing, the air path communicates the first-stage volute outlet with the second-stage volute inlet, and the air path flows through a region of the cooling water jacket to exchange heat with the cooling water jacket.
With reference to the first aspect and the foregoing implementation manners, in certain implementation manners of the first aspect, a front radial bearing and a rear radial bearing are mounted at two ends of the housing, and the shaft core penetrates through the front radial bearing, the stator and the rear radial bearing.
With reference to the first aspect and the foregoing implementations, in certain implementations of the first aspect, the front radial bearing and the rear radial bearing both employ aerodynamic bearings.
With reference to the first aspect and the foregoing implementation manners, in some implementation manners of the first aspect, the cooling water jacket surrounds an outer side of the stator, the gas path includes a plurality of axial holes formed in a housing outside the cooling water jacket, an outlet of a first-stage volute installed in the housing is in butt joint with one end of the axial hole, and an inlet of a second-stage volute installed in the housing is in butt joint with the other end of the axial hole.
With reference to the first aspect and the foregoing implementation manners, in some implementation manners of the first aspect, a first-stage diffuser is disposed at an outlet of the first-stage impeller.
With reference to the first aspect and the foregoing implementation manners, in certain implementation manners of the first aspect, a second-stage diffuser is disposed at an outlet of the second-stage impeller.
With reference to the first aspect and the implementations described above, in certain implementations of the first aspect, a nozzle is provided at the turbine inlet.
In a second aspect, a hydrogen fuel cell system includes:
a stack having an air outlet and an air inlet;
in the centrifugal air compressor according to any one of the first to the second aspects, the outlet of the two-stage scroll communicates with the air inlet, and the air outlet communicates with the inlet of the turbine scroll.
One of the above technical solutions has at least one of the following advantages or beneficial effects:
during operation, air enters the first-stage compression assembly, is compressed by the first-stage impeller and then is discharged from the first-stage volute, enters the second-stage compression assembly, and a higher air pressure ratio is obtained by adopting a two-stage compression structure form.
The turbine assembly drives the turbine 10 to do work by recovering air discharged by the stack, and then the air is discharged into the air after being expanded by the turbine. The turbine assembly reduces the parasitic power consumption of the air compressor by recovering high-temperature and high-pressure air exhausted by the electric pile, thereby improving the overall efficiency of the fuel cell system.
The flying disc on the shaft core is eliminated, and the back of the secondary impeller and the back of the turbine are used as thrust surfaces. The thrust bearing is arranged between the secondary impeller and the turbine, the gas dynamic pressure bearings are arranged on the front face and the rear face of the thrust bearing, and the secondary impeller and the turbine can generate a certain bearing gas model to balance the axial force of the shaft core when driven to rotate at a high speed by the motor, so that the axial displacement of the shaft core is limited. The shaft core reduces flying discs, the weight is reduced, the length of the shaft core is shortened, the high-speed stability of the shaft core is improved, and the whole machine is more compact after the flying discs are eliminated.
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 one embodiment of a centrifugal air compressor of the present invention;
fig. 2 is a schematic structural view of one embodiment of a hydrogen fuel cell system of the present invention.
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.
Referring to fig. 1, an embodiment of the present invention provides a centrifugal air compressor, including a motor assembly, a first-stage compression assembly, a second-stage compression assembly and a turbine assembly, where the motor assembly includes a housing 1, a shaft core 2, a thrust bearing 12, a stator 3 and a rotor, the first-stage compression assembly includes a first-stage impeller 4 and a first-stage volute 5, and the second-stage compression assembly includes a second-stage impeller 6 and a second-stage volute 7.
Specifically, referring to fig. 1, a shaft core 2 is rotatably installed in a housing 1, a stator 3 is connected to the housing 1, a rotor is connected to the shaft core 2, and the shaft core 2 can rotate at a high speed under the interaction of the stator 3 and the rotor, so as to provide power for a centrifugal air compressor and realize air compression.
Referring to fig. 1, a first-stage impeller 4 is mounted at one end of a shaft core 2, and a first-stage volute 5 is mounted at one end of a housing 1 corresponding to the first-stage impeller 4. The second-stage impeller 6 is arranged at the other end of the shaft core 2, and the second-stage volute 7 is arranged at the other end of the shell 1 corresponding to the second-stage impeller 6. In other words, the first-stage compression assembly and the second-stage compression assembly are respectively located at two ends of the shell 1, and the stator 3 and the rotor are arranged between the first-stage compression assembly and the second-stage compression assembly. When the first-stage impeller 4 rotates along with the shaft core 2, air is continuously sucked in from the inlet of the first-stage volute 5 and is discharged from the outlet of the first-stage volute 5 after being compressed, so that first-stage compression is realized. The air compressed by the first stage further enters the second stage volute 7, and is discharged from the outlet of the second stage volute 7 after being compressed. Meanwhile, air is compressed in two stages, and the pressure ratio is greatly improved.
Referring to fig. 1, the turbine assembly includes a turbine 10 and a turbine volute 11, the turbine 10 is mounted on the shaft core 2, and the turbine volute 11 is mounted on the housing 1 and is matched with the turbine 10; the turbine assembly drives the turbine 10 to do work by recovering air discharged from the stack, and then the air is expanded by the turbine 10 and then discharged into the air. The turbine assembly reduces the parasitic power consumption of the air compressor by recovering high-temperature and high-pressure air exhausted by the electric pile, thereby improving the overall efficiency of the fuel cell system.
The turbine 10 is connected to the end portion, facing away from the first-stage impeller 4, of the shaft core 2 on one side of the second-stage impeller 6, the turbine volute 11 is installed on the second-stage volute 7, the turbine 10 and the second-stage impeller 6 are installed on two sides of the thrust bearing 12 in a back-to-back mode, the thrust bearing 12 is installed between the second-stage impeller 6 and the turbine 10, and the axial position of the shaft core 2 is limited by using the back portions of the turbine 10 and the second-stage impeller 6. The scheme eliminates a flying disc on the shaft core 2 and utilizes the back surfaces of the secondary impeller 6 and the turbine 10 as thrust surfaces. The thrust bearing 12 is arranged between the secondary impeller 6 and the turbine 10, the gas dynamic pressure bearings are arranged on the front face and the rear face of the thrust bearing 12, and the secondary impeller 6 and the turbine 10 can generate a certain bearing gas model to balance the axial force of the shaft core 2 when being driven by the motor to rotate at a high speed, so that the axial displacement of the shaft core 2 is limited. The shaft core 2 reduces flying discs, the weight is reduced, meanwhile, the length of the shaft core 2 is shortened, the high-speed stability of the shaft core 2 is improved, and the whole machine is more compact after the flying discs are eliminated.
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 4 can reach 120-150 ℃ (when the ambient temperature is 25 ℃), and at this time, if the compressed air at the temperature is directly introduced into the second-stage compression component for compression, the shaft power burden of the second-stage compression component is increased to a great extent, and then the motor power output is increased, so that the compressor system is low in efficiency. 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, in some embodiments of the present application, referring to fig. 1, the housing 1 is provided with a cooling water jacket 8, the housing 1 is internally provided with an air passage 9, the air passage communicates the first-stage volute outlet and the second-stage volute inlet, and the air passage 9 of the housing 1 flows through the area of the cooling water jacket 8 to exchange heat with the cooling water jacket 8. The air is cooled by the cooling liquid passing through the inside of the shell 1 before entering the secondary impeller 6, 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 9 is arranged inside the shell 1, so that the structure of the gas path 9 between the first-stage compression assembly and the second-stage compression assembly 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.
In some embodiments, referring to fig. 1, a front radial bearing 13 and a rear radial bearing 14 are installed at two ends of the housing 1, the shaft core 2 passes through the front radial bearing 13, the stator 3 and the rear radial bearing 14, and both the front radial bearing 13 and the rear radial bearing 14 adopt aerodynamic bearings. In high-speed rotation, the front radial bearing 13 and the rear radial bearing 14 can generate air films with certain bearing capacity to support the shaft core 2 to rotate, the rotation precision of the shaft core 2 is better, and friction and vibration are smaller.
It is understood that the shaft core 2 may be supported by the housing 1 by a rolling bearing, a sliding bearing, a gas static pressure bearing, or the like to achieve high-speed rotation.
Referring to fig. 1, a cooling water jacket 8 surrounds the stator 3, and a cooling medium flows through the cooling water jacket 8 to continuously remove heat generated by the operation of the centrifugal air compressor and heat of air compressed by the primary compression. The air path 9 may be provided with a path and a specific structure in the housing 1 as needed. For example, in some embodiments shown in fig. 1, the gas path 9 includes a plurality of axial holes formed in the housing outside the cooling water jacket 8, the axial holes are formed between the front and rear end faces of the housing 1, so that the forming is more convenient, and the axial holes are more easily butted with the first-stage volute 5 and the second-stage volute 7, as shown in fig. 1, an outlet of the first-stage volute 5 mounted on the housing 1 is butted with one end of the axial hole, and an inlet of the second-stage volute 7 mounted on the housing 1 is butted with the other end of the axial hole. In order to ensure the sealing performance between the first-stage volute 5 and the second-stage volute 7 and the shell 1, sealing rings can be arranged at the interface.
Referring to fig. 1, a first-stage diffuser 15 is disposed at an outlet of the first-stage impeller 4, and the first-stage diffuser 15 is installed between the first-stage volute 5 and the rear radial bearing 14 and is used for converting kinetic energy of air at the outlet of the first-stage impeller 4 into static pressure energy. And a secondary diffuser 16 is arranged at the outlet of the secondary impeller 6, and the secondary diffuser 16 is arranged between the secondary volute 7 and the front radial bearing 13 and is used for converting the kinetic energy of the air at the outlet of the secondary impeller 6 into static pressure energy. The inlet of the turbine 10 is provided with a nozzle 17 for converting static pressure energy of air at the inlet of the turbine 10 into kinetic energy, thereby improving the compression efficiency of the centrifugal air compressor.
Referring to fig. 2, an embodiment of the present invention provides a hydrogen fuel cell system including a stack 18 and the centrifugal air compressor of any one of the above embodiments, the stack 18 having an air outlet and an air inlet, the outlet of the secondary volute 7 communicating with the air inlet, and the air outlet communicating with the inlet of the turbine volute 11. The air is compressed again by the secondary impeller 6 and the secondary diffuser 16, then is discharged through the secondary volute 7, enters the electric pile 18 through an external pipeline, after the electric pile 18 is subjected to chemical reaction, the residual high-temperature and high-pressure gas is discharged, then enters the end of the turbine 10 through an external air pipeline, pushes the turbine 10 to do work, and then is discharged into the air after being expanded through the turbine 10. The parasitic power consumption of the air compressor is reduced by recovering the high-temperature, high-pressure air discharged from the stack 18, thereby improving the overall efficiency of the fuel cell system.
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 (9)
1. A centrifugal air compressor, characterized by comprising:
the motor assembly comprises a shell, a shaft core, a thrust bearing, a stator and a rotor, wherein the shaft core is rotatably arranged in the shell, the stator is connected with the shell, and the rotor is connected with the shaft core;
the first-stage compression assembly comprises a first-stage impeller and a first-stage volute, the first-stage impeller is mounted at one end of the shaft core, and the first-stage volute is mounted at one end of the shell corresponding to the first-stage impeller;
the second-stage compression assembly comprises a second-stage impeller and a second-stage volute, the second-stage impeller is mounted at the other end of the shaft core, and the second-stage volute is mounted at the other end of the shell corresponding to the second-stage impeller;
the turbine assembly comprises a turbine and a turbine volute, the turbine is connected to the end part, deviating from the first-stage impeller, of the shaft core on one side of the second-stage impeller, the turbine volute is installed on the second-stage volute, the turbine and the second-stage impeller are installed on two sides of the thrust bearing in a back-to-back mode, and the axial position of the shaft core is limited by using the back parts of the turbine and the second-stage impeller as thrust surfaces.
2. The centrifugal air compressor as claimed in claim 1, wherein the housing is provided with a cooling water jacket, and an air passage is provided inside the housing, the air passage communicating the primary volute outlet and the secondary volute inlet, the air passage flowing through a region of the cooling water jacket to exchange heat with the cooling water jacket.
3. The centrifugal air compressor as claimed in claim 1, wherein the housing is provided at both ends thereof with front and rear radial bearings, and the shaft core is passed through the front radial bearing, the stator and the rear radial bearing.
4. The centrifugal air compressor as claimed in claim 3, wherein said front and rear radial bearings are each aerodynamic bearings.
5. The centrifugal air compressor as claimed in claim 2, wherein the cooling water jacket surrounds the stator, the air passage includes a plurality of axial holes formed in the housing outside the cooling water jacket, an outlet of the primary volute installed in the housing is in butt joint with one end of the axial holes, and an inlet of the secondary volute installed in the housing is in butt joint with the other end of the axial holes.
6. The centrifugal air compressor as claimed in claim 1, wherein a first-stage diffuser is provided at an outlet of the first-stage impeller.
7. The centrifugal air compressor as claimed in claim 1, wherein a secondary diffuser is provided at an outlet of the secondary impeller.
8. The centrifugal air compressor as claimed in claim 1, wherein a nozzle is provided at the inlet of said turbine.
9. A hydrogen fuel cell system, characterized by comprising:
a stack having an air outlet and an air inlet;
the centrifugal air compressor as claimed in any one of claims 1-8, wherein an outlet of said two-stage volute is in communication with said air inlet, and said air outlet is in communication with an inlet of a turbine volute.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202011350395.XA CN112555172A (en) | 2020-11-26 | 2020-11-26 | Centrifugal air compressor and hydrogen fuel cell system |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202011350395.XA CN112555172A (en) | 2020-11-26 | 2020-11-26 | Centrifugal air compressor and hydrogen fuel cell system |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN112555172A true CN112555172A (en) | 2021-03-26 |
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| CN202011350395.XA Pending CN112555172A (en) | 2020-11-26 | 2020-11-26 | Centrifugal air compressor and hydrogen fuel cell system |
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Cited By (7)
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| CN114645859A (en) * | 2022-05-02 | 2022-06-21 | 烟台东德实业有限公司 | Bilateral two-stage high-speed centrifugal air compressor and expander integrated system |
| CN114876826A (en) * | 2022-05-02 | 2022-08-09 | 烟台东德实业有限公司 | Unilateral two-stage high-speed centrifugal air compressor and expander integrated system |
| CN115111151A (en) * | 2022-06-30 | 2022-09-27 | 势加透博（北京）科技有限公司 | Air compressor and control method thereof |
| CN115628232A (en) * | 2022-05-17 | 2023-01-20 | 安徽工业技术创新研究院六安院 | Composite channel housing for a two-stage centrifugal air compressor |
| CN116207291A (en) * | 2022-12-29 | 2023-06-02 | 北京航空航天大学 | A high temperature proton exchange membrane fuel cell system |
| CN117823452A (en) * | 2023-12-12 | 2024-04-05 | 南京磁谷科技股份有限公司 | Low axial load impeller mounting structure, magnetic suspension compressor and air inlet compression method |
| WO2025187848A1 (en) * | 2024-03-06 | 2025-09-12 | 엘지전자 주식회사 | Turbo compressor |
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| CN107725174A (en) * | 2016-05-11 | 2018-02-23 | 株式会社马勒滤清系统 | Turbocharger |
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Cited By (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114645859A (en) * | 2022-05-02 | 2022-06-21 | 烟台东德实业有限公司 | Bilateral two-stage high-speed centrifugal air compressor and expander integrated system |
| CN114876826A (en) * | 2022-05-02 | 2022-08-09 | 烟台东德实业有限公司 | Unilateral two-stage high-speed centrifugal air compressor and expander integrated system |
| CN115628232A (en) * | 2022-05-17 | 2023-01-20 | 安徽工业技术创新研究院六安院 | Composite channel housing for a two-stage centrifugal air compressor |
| CN115111151A (en) * | 2022-06-30 | 2022-09-27 | 势加透博（北京）科技有限公司 | Air compressor and control method thereof |
| CN116207291A (en) * | 2022-12-29 | 2023-06-02 | 北京航空航天大学 | A high temperature proton exchange membrane fuel cell system |
| CN117823452A (en) * | 2023-12-12 | 2024-04-05 | 南京磁谷科技股份有限公司 | Low axial load impeller mounting structure, magnetic suspension compressor and air inlet compression method |
| WO2025187848A1 (en) * | 2024-03-06 | 2025-09-12 | 엘지전자 주식회사 | Turbo compressor |
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Application publication date: 20210326 |