CN110541831A - Multi-stage compressor with turbine section for a fuel cell system - Google Patents
Multi-stage compressor with turbine section for a fuel cell system Download PDFInfo
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- CN110541831A CN110541831A CN201811346535.9A CN201811346535A CN110541831A CN 110541831 A CN110541831 A CN 110541831A CN 201811346535 A CN201811346535 A CN 201811346535A CN 110541831 A CN110541831 A CN 110541831A
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- wheel
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- stage
- compressor wheel
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- 239000000446 fuel Substances 0.000 title claims abstract description 55
- 239000012530 fluid Substances 0.000 claims description 11
- 238000005192 partition Methods 0.000 claims description 7
- 239000007789 gas Substances 0.000 description 8
- 125000006850 spacer group Chemical group 0.000 description 4
- QVGXLLKOCUKJST-UHFFFAOYSA-N atomic oxygen Chemical compound [O] QVGXLLKOCUKJST-UHFFFAOYSA-N 0.000 description 3
- 230000005611 electricity Effects 0.000 description 3
- 239000001301 oxygen Substances 0.000 description 3
- 229910052760 oxygen Inorganic materials 0.000 description 3
- UFHFLCQGNIYNRP-UHFFFAOYSA-N Hydrogen Chemical compound [H][H] UFHFLCQGNIYNRP-UHFFFAOYSA-N 0.000 description 2
- 230000006835 compression Effects 0.000 description 2
- 238000007906 compression Methods 0.000 description 2
- 238000010586 diagram Methods 0.000 description 2
- 239000001257 hydrogen Substances 0.000 description 2
- 229910052739 hydrogen Inorganic materials 0.000 description 2
- 238000004519 manufacturing process Methods 0.000 description 2
- 238000000034 method Methods 0.000 description 2
- 238000010146 3D printing Methods 0.000 description 1
- 239000000654 additive Substances 0.000 description 1
- 230000000996 additive effect Effects 0.000 description 1
- 238000005266 casting Methods 0.000 description 1
- 238000006243 chemical reaction Methods 0.000 description 1
- 238000004806 packaging method and process Methods 0.000 description 1
- 238000011084 recovery Methods 0.000 description 1
- 238000007789 sealing Methods 0.000 description 1
- 238000011144 upstream manufacturing Methods 0.000 description 1
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
-
- 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
- F04D17/14—Multi-stage pumps with means for changing the flow-path through the stages, e.g. series-parallel, e.g. side-loads
-
- 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
- F04D29/26—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
-
- 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
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (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)
- Fuel Cell (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
Abstract
The invention relates to a multistage compressor with a turbine section for a fuel cell system. A multi-stage inflator includes a shaft supported for rotation about an axis. The inflator device also includes a first compressor wheel of the first compressor stage. The first compressor wheel is fixed to the shaft. In addition, the charging device also comprises a second compressor wheel of the second compressor stage. The second compressor wheel is fixed to the shaft. In addition, the inflator includes a turbine wheel of the turbine section. The turbine wheel and the second compressor wheel are secured to the shaft in a back-to-back arrangement.
Description
Cross Reference to Related Applications
Priority is claimed below for U.S. provisional patent application No.62/585667, filed on 14/11/2017, the entire disclosure of which is incorporated by reference.
Technical Field
The present disclosure relates generally to a multi-stage compressor and, more particularly, to a multi-stage compressor with a turbine section for a fuel cell system.
Background
Fuel cell systems often include an air charging device (i.e., a fuel cell compressor) for compressing air before it is supplied to the fuel cell stack. This can improve the operating efficiency of the fuel cell system.
However, conventional inflators suffer from various drawbacks, and thus the operating efficiency of the fuel system may be affected. In addition, the fuel cell compressor may be relatively bulky and/or heavy. Others may produce a significant amount of undesirable noise. In addition, some fuel cell compressors may be relatively expensive to manufacture.
accordingly, it is desirable to provide a fuel cell compressor that improves the efficiency of the fuel cell system. It is also desirable to provide a fuel cell compressor that is compact, quiet, and cost effective. Other desirable features and characteristics of the present disclosure will become apparent from the subsequent detailed description and the appended claims, taken in conjunction with the accompanying drawings and this background.
disclosure of Invention
In one embodiment, a multi-stage inflator is disclosed. The inflator includes a shaft supported for rotation about an axis. The inflator device also includes a first compressor wheel of the first compressor stage. The first compressor wheel is fixed to the shaft. In addition, the charging device also comprises a second compressor wheel of the second compressor stage. The second compressor wheel is fixed to the shaft. In addition, the inflator includes a turbine wheel of the turbine section. The turbine wheel and the second compressor wheel are secured to the shaft in a back-to-back arrangement.
In another embodiment, a multi-stage inflator is disclosed. The inflator includes a shaft supported for rotation about an axis. Furthermore, the charging device comprises a first compressor wheel of the first compressor stage. The first compressor wheel is fixed to the shaft. In addition, the inflator device also includes a second compressor wheel of the second compressor stage. The second compressor is fixed to the shaft. In addition, the inflator includes a turbine wheel of the turbine section. The turbine wheel is fixed to the shaft. The turbine wheel is disposed along the axis between the first compressor wheel and the second compressor wheel.
In another embodiment, a multi-stage inflator for a fuel cell system with a fuel cell stack is disclosed. The inflator device includes a first compressor stage defined by the first compressor wheel in cooperation with the first compressor housing. The inflator device also includes a motor section with a stator and a rotor. Further, the inflator device includes a second compressor stage cooperatively defined by a second compressor wheel and a second compressor housing. Further, the inflator includes a turbine section defined by the turbine wheel in cooperation with the turbine housing. The first compressor wheel, the rotor, the second compressor wheel, and the turbine wheel are fixed to the shaft for rotation as a unit relative to the first compressor housing, the stator, the second compressor housing, and the turbine housing. The first compressor stage is configured to compress an incoming fluid flow and direct a low pressure fluid flow toward the second compressor stage. The second compressor stage is configured to compress the low pressure fluid flow to direct the high pressure fluid flow toward the fuel cell stack. In addition, the turbine wheel is configured to be rotationally driven by the exhaust gas flow from the fuel cell stack. Furthermore, the turbine wheel and the second compressor wheel are fixed on the shaft in a back-to-back arrangement.
drawings
The present disclosure will hereinafter be described in conjunction with the following drawing figures, wherein like numerals denote like elements, and wherein:
FIG. 1 is a schematic diagram of a fuel cell system including an inflator according to an exemplary embodiment of the present disclosure;
FIG. 2 is a cross-sectional view of a rotating assembly of an inflator of the fuel system of FIG. 1; and
FIG. 3 is a schematic view of a fuel cell system with a rotating assembly of an inflator shown in accordance with additional embodiments of the present disclosure.
Detailed Description
The following detailed description is merely exemplary in nature and is not intended to limit the disclosure or the application and uses of the disclosure. Furthermore, there is no intention to be bound by any theory presented in the preceding background or the following detailed description.
broadly, exemplary embodiments disclosed herein include a fuel cell system with an inflator having a plurality of compression stages and a turbine section. In a rotating assembly of the inflator device, the turbine wheel of the turbine section may be arranged in a back-to-back configuration with the compressor wheel of one of the compressor stages.
FIG. 1 is a schematic diagram of a fuel cell system 100 with an example inflator 102 of the present disclosure. In some embodiments, the fuel cell system 100 may be included in a vehicle, such as an automobile, truck, sport utility vehicle, van, motorcycle, or the like. However, it should be appreciated that the fuel cell system 100 may be configured for different uses without departing from the scope of the present disclosure.
The fuel cell system 100 may include a fuel cell stack 104 including a plurality of fuel cells. Hydrogen may be supplied to the fuel cell stack 104 from the tank 106, and oxygen may be supplied to the fuel cell stack 104 to generate electricity through known chemical reactions. The fuel cell stack 104 may generate electricity for electrical devices such as an electric motor 105. As described above, the fuel cell system 100 may be included in a vehicle; thus, in some embodiments, the electric motor 105 may convert electrical power into mechanical power to drive and rotate the axle (and thus one or more wheels) of the vehicle.
Oxygen may be provided at least in part by the inflator 102 to the fuel cell stack 104. As will be discussed, the inflator 102 may compress air as it flows to the fuel cell stack 104 for improving the operating efficiency of the fuel cell system 100.
The inflator 102 may be configured as a multi-stage fuel cell compressor. As shown in FIG. 1, the inflator 102 may generally include a rotation assembly 118 and a housing 119. The rotating assembly 118 may include a shaft 150 and various other components fixedly supported on the shaft 150 for rotation within the housing 119 by bearings 121, such as slide bearings, air bearings, and/or oil free bearings.
the rotating assembly 118 and the housing 119 may cooperate to define the first compressor stage 110, the motor section 112, the second compressor stage 114, and the turbine section 116 of the inflator 102. In some embodiments, the first compressor stage 110 may be referred to as a "low pressure compressor stage" and the second compressor stage 114 may be referred to as a "high pressure compressor stage" for reasons that will become apparent. As will be discussed in detail below, the motor section 112 may include a motor 199, the motor 199 including a stator 146 and a rotor 148, and which drives the rotating assembly 118 and rotates the rotating assembly 118 about the axis 120. Accordingly, the inlet airflow (represented by arrow 122) may be compressed by the first compressor stage 110 (i.e., the low pressure compressor stage). The low pressure air stream (represented by arrow 124) may be directed to the second compressor stage 114 (i.e., the high pressure compressor stage) for further compression. The high pressure air flow (represented by arrow 126) from the second compressor stage 114 may be directed to an intercooler 128, and then to the fuel cell stack 104. Thus, the battery stack 104 may generate electricity from the hydrogen provided from the tank 106 and the oxygen provided in the high pressure air stream 126.
Further, exhaust gas flow (represented by arrow 130) from the fuel cell stack 104 may be directed back to the turbine section 116 of the inflator 102. The exhaust flow 130 may drive at the turbine section 116 and rotate the rotating assembly 118 to assist the motor section 112. In some embodiments, exhaust flow 130 may be directed toward turbine section 116 by a variable nozzle device 132 (i.e., a variable nozzle turbine or VNT).
Various components of the fuel cell system 100 may be controlled by a control system 134. The control system 134 may be a computerized system with a processor, various sensors, and other components for electrically controlling the operation of the fuel cell stack 104, the motor section 112, the motor 105, the variable nozzle device 132, and/or other features of the system 100. In some embodiments, the control system 134 may define or may be part of an Electrical Control Unit (ECU) of the vehicle.
It should be appreciated that the multi-stage compressor of the inflator 102 allows for a higher pressure ratio during operation. Further, the turbine section 116 provides energy recovery for the inflator 102.
moreover, as will be discussed in detail, the turbine section 116 may be disposed immediately adjacent at least one of the compressor stages. As shown, for example, in the illustrated embodiment, one or more components of the turbine section 116 may be disposed in a back-to-back arrangement with components of the second compressor stage 114. (however, it should be appreciated that the turbine section 116 may be disposed in a back-to-back arrangement with the components of the first compressor stage 110 without departing from the scope of the present disclosure.)
The inflator 102 will now be discussed in greater detail according to an example embodiment. The housing 119 will be discussed with reference to fig. 1, and the rotating assembly 118 will be discussed with reference to fig. 1 and 2.
As shown, the housing 119 may include a hollow cylindrical motor housing 144. The motor housing 144 may extend longitudinally along the axis 120 between the first and second compressor stages 110, 114. The motor housing 144 may house a stator 146 that may be secured inside the motor housing 144. The rotor 148 may be secured to a shaft 150 of the rotating assembly 118 and may be received within the stator 146.
Moreover, the housing 119 may include a first compressor housing member 136 defining an axial inlet 138, a shroud member 139, and a volute member 140. The volute component 140 may be fixedly attached to one end of the motor housing 144 or other portion of the motor section 112. The axial inlet 138 may be straight and centered on the axis 120. The shroud member 139 may be inversely shaped depending on the components of the rotation assembly 118. The volute component 140 may define a volute channel 142 therein that extends about the axis 120. As will be discussed, during operation of the inflator 102, the inlet air flow 122 may flow into the inlet 138, through the shroud member 139, and into the volute passage 142.
Further, the housing 119 may include a second compressor housing member 152 defining a radial inlet 154, a shroud member 156, and a volute member 158. The second compressor housing member 152 may be fixedly connected to the motor housing 144 or other portion of the motor section 112 on an end opposite the first compressor housing member 136. The radial inlet 154 may extend radially in a downstream direction toward the axis 120 and may taper in cross-sectional area. The inlet 154 may also be turned in a direction generally parallel to the axis 120 and may be fluidly connected to the diffuser section 155. The shroud member 156 may be contoured and shaped according to the components of the rotating assembly 118. The volute component 158 may define a volute passage 160 therein that extends about the axis 120. As will be discussed, the low pressure air stream 124 may flow into the inlet 154, through the shroud member 156, and into the volute passage 160. From the volute passage 160, the high pressure air stream 126 may flow to the intercooler 128 and then to the fuel cell stack 104.
In some embodiments, the inflator 102 may also include an interstage conduit 162. The interstage duct 162 may be elongated having a first end 164 connected to the volute component 140 of the first compressor stage 110 and a second end 166 connected to the radial inlet 154 of the second compressor stage 114. Thus, the inter-stage duct 162 may direct the flow of the low pressure air stream 124 from the first compressor stage 110 through the motor casing 114 and to the second compressor stage 114.
moreover, the housing 119 of the inflator 102 may include a turbine housing member 168. The turbine housing member 168 may be fixed to the second compressor housing member 152 on an end opposite the motor section 112. The turbine housing member 168 may define a volute inlet member 170 with a circumferential passage 171 and a radial passage 173 formed therein. The circumferential channel 171 may receive the exhaust flow 130 from the fuel cell stack 104, and the circumferential channel 171 may direct the flow of gas radially inward along a radial channel 173 toward an axial outlet 172 of the turbine housing member 168. As described above, the rotating assembly 118 may be rotationally driven by the exhaust flow 130 at the turbine section 116. The resulting exhaust flow 176 may exit the inflator 102 via the axial outlet 172.
In some embodiments, the housing 119 may further include a partition member 193. The partition member 193 may be a relatively flat plate with a first surface 191 and an opposing second surface 189. The partition member 193 may separate the turbine section 116 from the second compressor stage 114. In other words, the partition member 193 may define boundaries for the turbine section 116 and the second compressor stage 114. In some embodiments, the partition member 193 may be fixed and sandwiched between the turbine housing member 168 and the second compressor housing member 152. Moreover, the first surface 191 may define a portion of the radial passages 173 and the circumferential passages 171 of the turbine section 116. Further, the second surface 189 may define the diffuser section 155 and a portion of the volute channel 160.
It should be understood that the housing 119 and/or other portions of the inflator 102 may include many additional components that are not described in detail. For example, the housing 119 may include a number of fasteners, fluid seals, heat shields, and/or other components for maintaining efficient and effective operation of the inflator device 102.
referring now to fig. 1 and 2, the rotation assembly 118 will be discussed in more detail. As shown, the rotating assembly 118 may include a first compressor wheel 180. The first compressor wheel 180 may include a support structure 182 and a plurality of blades 184. As shown in fig. 2, the support structure 182 may include a first end 186 and a second end 188 spaced apart along the axis 120. The support structure 182 may taper radially outward along the axis 120 from a smaller second end 188 to a larger disc-shaped first end 186. The vanes 184 may be relatively thin members that protrude from the support structure 182. The vanes 184 may project radially outward from the axis 120. The vanes 184 may also extend helically about the axis 120. The first compressor wheel 180 may be secured to one end of the shaft 150 in the first compressor stage 110 with the second end 118 and the blades 184 facing in an upstream direction of the axial inlet 138. The first compressor wheel 180 may be substantially centered about the axis 120. Moreover, as shown in FIG. 1, the first compressor wheel 180 and the shroud member 139 may cooperate to at least partially define the first compressor stage 110. As such, during operation of the inflator 102, the first compressor wheel 180 may rotate relative to the shroud member 139 to compress the inlet airflow 122 and move the low pressure airflow 124 toward the second compressor stage 114 via the inter-stage conduit 162.
Additionally, the rotating assembly 118 may include an inlet spacer 179 and a second compressor wheel 190. The second compressor wheel 190 may include a support structure 192 and a plurality of blades 194. The support structure 192 and the blades 194 may share one or more common features with the support structure 182 and the blades 184, respectively, of the first compressor wheel 180 as discussed above. However, the support structure 192 and the vanes 194 may have different sizes, dimensions, arrangements, etc. as compared to the support structure 182 and the vanes 184. As shown, the support structure 192 may include a first end 198 (i.e., a rear end) and a second end 197 spaced apart along the axis 120. The support structure 192 may taper radially outward along the axis 120 from the smaller second end 197 to the larger first end 198. The blades 194 may extend radially from the axis 120 and may extend helically relative to the axis 120.
The inlet spacer 179 and the second compressor wheel 190 may be fixed to the shaft 150 in the second compressor stage 114. The second compressor wheel 190 may be secured to the shaft 150 with the second end 197 disposed between the motor section 112 and the first end 198. Also, in this position, the second compressor wheel 190 may be oriented with the blades 194 generally facing toward the motor section 112 and the first compressor wheel 180. The second compressor wheel 190 may be substantially centered about the axis 120. Moreover, as shown in FIG. 1, the second compressor wheel 190 and the shroud member 156 may cooperate to at least partially define the second compressor stage 114. Thus, during operation of the inflator device 102, the inlet spacer 179 and the second compressor wheel 190 may rotate relative to the shroud member 156. The inlet spacer 179 may direct the air flow 124 toward the second compressor wheel 190, and the second compressor wheel 190 may compress the air flow 124 and move the high pressure air flow 126 toward the fuel cell stack 104.
Also, the rotating assembly 118 may include a turbine wheel 161. The turbine wheel 161 may include a support structure 163 and a plurality of blades 165. As shown, the support structure 163 may include a first end 196 (i.e., a rear end) and a second end 195 spaced apart along the axis 120. The support structure 163 may taper radially outward along the axis 120 from the smaller second end 195 to the larger first end 196. The blades 165 may extend radially from the axis 120 and may extend helically relative to the axis 120.
The support structure 163 may be fixedly connected to the support structure 192 of the second compressor wheel 190. The turbine wheel 161 may be fixed to the shaft 150 in the turbine section 116. The turbine wheel 161 may be secured to the shaft 150 in such a manner that the first end 196 of the turbine wheel 161 is disposed between the first end 198 of the second compressor wheel 190 and the second end 195 of the turbine wheel 161. Also, in this position, the turbine wheel 161 may be oriented with the blades 165 facing generally in an opposite direction (relative to the axis 120) and away from the blades 194 of the second compressor wheel 190. Moreover, the first end 196 of the turbine wheel 161 may be disposed proximate to the first end 198 of the second compressor wheel 190, and in some embodiments may be disposed proximate to the first end 198 of the second compressor wheel 190. Thus, the turbine wheel 161 and the second compressor wheel 190 may be disposed in a back-to-back arrangement.
Moreover, in some embodiments represented by fig. 1 and 2, the turbine wheel 161 and the second compressor wheel 190 may be integrally connected so as to be a single, unitary, one-piece member 168. In some embodiments, turbine wheel 161 and second compressor wheel 190 may be formed at the same time and integrally connected together (i.e., inseparable without significant damage to one or both). For example, the monolithic member 169 may be formed via a casting process, via an additive manufacturing (3D printing) process, or another suitable process.
However, it should be appreciated that the turbine wheel 161 and the second compressor wheel 190 may be separate, independent components without departing from the scope of the present disclosure. For example, the turbine wheel 161 and the second compressor wheel 190 may be connected by fasteners, press fit, or the like. In some embodiments, turbine wheel 161 and second compressor wheel 190 are removably connected to each other and to shaft 150 such that these parts may be disassembled, for example, for repair and replacement.
Additionally, it should be appreciated that the turbine wheel 161 and the second compressor wheel 190 may be disassembled from one another without departing from the scope of the present disclosure. Both may be secured to the shaft 150 in a back-to-back arrangement as represented in fig. 1 and 2; however, there may also be no direct connection between the turbine wheel 161 and the second compressor wheel 190. The disassembled turbine wheel 161 and second compressor wheel 190 may be in abutting contact with one another, or there may be a gap defined between the first end 198 of the second compressor wheel 190 and the first end 196 of the turbine wheel 161.
As shown in fig. 2, the monolithic member 169 of the turbine wheel 161 and the second compressor wheel 190 may be secured to the end of the shaft 150 opposite the first compressor wheel 180. In some embodiments, the partition member 193 can include an aperture 175 that receives the monolith 169. The inner edge of the aperture 175 may be received in the groove 178 of the monolithic member 169 between the first end 198 of the second compressor wheel 190 and the turbine wheel 161. There may be seals or other components for substantially sealing the interface to prevent leakage between the second compressor stage 114 and the turbine section 116.
Accordingly, the turbine wheel 161 may be disposed within the turbine housing component 168 to define the turbine section 116 of the inflator 102. Also, a second compressor wheel 190 may be disposed within the second compressor housing member 152. Second compressor wheel 190 may be interposed between turbine wheel 161 and first compressor wheel 180 relative to axis 120. Further, the rotor 148 may be interposed between the second compressor wheel 190 and the first compressor wheel 180. The blades 194 of the second compressor wheel 190 may face toward the first side 186 (i.e., the aft side) of the first compressor wheel 180. Moreover, the blades 165 of the turbine wheel 161 may face downstream toward the axial outlet 172.
Circumferential channels 171 and radial channels 173 of turbine section 116 may receive exhaust gas flow 130 from fuel cell stack 104. The turbine wheel 161 may be rotationally driven by the exhaust gas flow 130 to assist the motor 119 in rotating the shaft 150. The exhaust flow 176 may exit the inflator 102 via the axial outlet 172.
additionally, the turbine wheel 161 may be configured as a turbine expander (i.e., a turbo expander, an expansion turbine, etc.). The turbine wheel 161 may expand the gases of the exhaust stream 130 to produce work for assisting the motor 199 in driving the compressor stages 110, 114.
The efficiency of the turbine section 116 may increase with higher temperatures in the region proximate to the turbine wheel 161. Also, by comparison, the temperature near the turbine wheel 161 may be substantially lower than the vicinity of the inflator 102. Thus, in some embodiments, the turbine wheel 161 may absorb heat from the vicinity of the inflator 102. For example, the turbine wheel 161, the inlet into the turbine section 116, and the like may absorb heat from the second compressor wheel 190, the shroud member 156, and/or the volute member 158 of the second compressor stage 114. Thus, the temperature proximate to the turbine wheel 161 may be increased for improved efficiency of the turbine section 116. Also, the temperature near the second compressor wheel 190 may be reduced, which may allow for the use of a lighter weight intercooler 128.
Accordingly, the inflator 102 may provide improved operating efficiency for the fuel cell system 100. The inflator 102 may also be relatively compact. The back-to-back arrangement of the second compressor wheel 190 and the turbine wheel 161 may reduce the amount of suspended mass on the rotating assembly 118. This may improve the dynamic performance of the rotating assembly 118 and enable sub-critical operation. Accordingly, the rotating assembly 118 may be more simply balanced and may reduce noise. These factors may also contribute to a smaller package size and a reduction in the overall cost of the fuel cell system 100.
Referring now to FIG. 3, an inflator 202 is illustrated in accordance with additional embodiments of the present disclosure. The inflator 202 may be substantially similar to the system 100 of fig. 1 and 2, except as noted below. Parts corresponding to those of figures 1 and 2 are indicated with corresponding reference numerals increased by 100.
as shown, the inflator device 202 includes a rotating assembly 218 with a shaft 250, a first compressor wheel 280, a rotor 248, a second compressor wheel 290, and a turbine wheel 216. Like the embodiments discussed above, the turbine wheel 261 and the second compressor wheel 290 may be disposed in a back-to-back arrangement. However, the turbine wheel 261 may be disposed between the first compressor wheel 280 and the second compressor wheel 290 along the axis 220.
In operation, the low pressure air stream 224 may flow (through the interstage conduit) to the second compressor wheel 290. The high pressure air stream 226 may flow from the second compressor wheel 290 to the fuel cell stack 204. The exhaust gas flow 230 may then flow to the turbine wheel 261 to rotationally drive the turbine wheel. Next, the exhaust gas flow 276 may flow axially toward the motor housing 244 and then out of the inflator 202.
The back-to-back turbine wheel/second compressor wheel orientation may be constructed in accordance with various considerations. For example, one orientation may provide better thrust balancing along the axis of the shaft of the rotating assembly. Thus, the load on the bearing can be reduced. Further, the orientation may be more compact and/or may provide better packaging, piping, etc. For example, the embodiment of fig. 1 and 2 may provide more space for the variable nozzle device 132 and/or for other features.
While at least one exemplary embodiment has been presented in the foregoing detailed description, it should be appreciated that a vast number of variations exist. It should also be appreciated that the exemplary embodiment or exemplary embodiments are only examples, and are not intended to limit the scope, applicability, or configuration of the disclosure in any way. Rather, the foregoing detailed description will provide those skilled in the art with a convenient road map for implementing an exemplary embodiment of the disclosure. It being understood that various changes may be made in the function and arrangement of elements described in an exemplary embodiment without departing from the scope of the disclosure as set forth in the appended claims.
Claims (20)
1. a multi-stage inflator device comprising:
A shaft supported for rotation about an axis;
a first compressor wheel of a first compressor stage, the first compressor wheel being fixed to the shaft;
A second compressor wheel of a second compressor stage, the second compressor wheel being fixed to the shaft; and
A turbine wheel of the turbine section, the turbine wheel and the second compressor wheel being fixed on the shaft in a back-to-back arrangement.
2. the inflator device of claim 1, wherein the second compressor wheel is disposed along the axis between the first compressor wheel and the turbine wheel.
3. The inflator device of claim 1, wherein the turbine wheel is disposed along the axis between the first compressor wheel and the second compressor wheel.
4. The inflator device of claim 1, wherein the first compressor wheel is included in a low pressure compressor stage and the second compressor wheel is included in a high pressure compressor stage; and is
An interstage duct is also included that directs a flow of fluid from the first compressor wheel to the second compressor wheel.
5. the inflator device of claim 1 wherein the turbine wheel comprises a turbine support structure and a plurality of turbine blades supported by the turbine support structure;
Wherein the second compressor wheel includes a compressor support structure and a plurality of compressor blades supported by the compressor support structure; and is
wherein the turbine support structure is connected to the compressor support structure and the turbine blades face away from the compressor blades about the axis.
6. The inflator of claim 1 wherein the turbine wheel is configured as a turbine expander for receiving exhaust gas from a fuel cell.
7. The inflator device of claim 1, further comprising a motor disposed between the back-to-back arrangement and the first compressor wheel; and is
Wherein the turbine wheel is configured to be rotationally driven by exhaust gas from a fuel cell to assist the motor.
8. the inflator device of claim 1 wherein the turbine wheel is integrally connected and unitary with the second compressor wheel to cooperatively define a one-piece member.
9. the inflator device according to claim 8, further comprising a partition member with an aperture;
Wherein the apertures receive the monolithic members;
wherein the dividing member separates the second compressor stage from the turbine section of the inflator.
10. The inflator device of claim 1, wherein the first compressor wheel cooperates with a first compressor housing to define the first compressor stage;
Wherein the second compressor wheel cooperates with a second compressor housing to define the second compressor stage; and is
Wherein the turbine wheel cooperates with a turbine housing to define the turbine section.
11. a multi-stage inflator device comprising:
a shaft supported for rotation about an axis;
A first compressor wheel of a first compressor stage, the first compressor wheel being fixed to the shaft;
A second compressor wheel of a second compressor stage, the second compressor wheel being fixed to the shaft; and
A turbine wheel of a turbine section, the turbine wheel being fixed on the shaft, the turbine wheel being disposed along the axis between the first compressor wheel and the second compressor wheel.
12. The inflator device of claim 11, wherein the first compressor wheel is included in a low pressure compressor stage and the second compressor wheel is included in a high pressure compressor stage; and is
An interstage duct is also included that directs a flow of fluid from the first compressor wheel to the second compressor wheel.
13. The inflator device of claim 11, wherein the turbine wheel comprises a turbine support structure and a plurality of turbine blades supported by the turbine support structure;
Wherein the second compressor wheel includes a compressor support structure and a plurality of compressor blades supported by the compressor support structure;
Wherein the turbine support structure is connected to the compressor support structure;
Wherein the turbine blades face away from the compressor blades about the axis; and is
Wherein the turbine blades face the first compressor wheel about the axis.
14. The inflator of claim 11 wherein the turbine wheel is configured as a turbine expander for receiving exhaust gas from a fuel cell.
15. the inflator device according to claim 11, further comprising a motor disposed between the turbine wheel and the first compressor wheel; and is
Wherein the turbine wheel is configured to be rotationally driven by exhaust gas from a fuel cell to assist the motor.
16. The inflator device of claim 11, wherein the turbine wheel is integrally connected and integral with the second compressor wheel.
17. The inflator device of claim 11, wherein the first compressor wheel cooperates with a first compressor housing to define the first compressor stage;
Wherein the second compressor wheel cooperates with a second compressor housing to define the second compressor stage; and is
Wherein the turbine wheel cooperates with a turbine housing to define the turbine section.
18. A multi-stage inflator for a fuel cell system with a fuel cell stack, the inflator comprising:
A first compressor stage cooperatively defined by a first compressor wheel and a first compressor housing;
A motor section with a stator and a rotor;
A second compressor stage cooperatively defined by a second compressor wheel and a second compressor housing; and
A turbine section cooperatively defined by a turbine wheel and a turbine housing;
The first compressor wheel, the rotor, the second compressor wheel, and the turbine wheel are fixed to a shaft for rotation as a unit relative to the first compressor housing, the stator, the second compressor housing, and the turbine housing;
the first compressor stage configured to compress an incoming fluid flow and direct a low pressure fluid flow toward the second compressor stage;
the second compressor stage configured to compress the low pressure fluid flow to direct a high pressure fluid flow toward the fuel cell stack;
The turbine wheel is configured to be rotationally driven by an exhaust gas flow from the fuel cell stack; and
the turbine wheel and the second compressor wheel are secured to the shaft in a back-to-back arrangement.
19. The inflator device of claim 18, wherein the second compressor wheel is disposed along the axis between the first compressor wheel and the turbine wheel.
20. The inflator device of claim 18, wherein the turbine wheel is disposed along the axis between the first compressor wheel and the second compressor wheel.
Applications Claiming Priority (2)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| US15/991,344 US11927193B2 (en) | 2017-11-14 | 2018-05-29 | Multi-stage compressor with turbine section for fuel cell system |
| US15/991344 | 2018-05-29 |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN110541831A true CN110541831A (en) | 2019-12-06 |
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ID=68701323
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201811346535.9A Pending CN110541831A (en) | 2018-05-29 | 2018-11-13 | Multi-stage compressor with turbine section for a fuel cell system |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN110541831A (en) |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112983848A (en) * | 2021-02-04 | 2021-06-18 | 北京稳力科技有限公司 | Fuel cell stack and gas supply device |
| CN113833675A (en) * | 2021-09-16 | 2021-12-24 | 势加透博洁净动力如皋有限公司 | Impeller and air compressor with same |
| CN113833676A (en) * | 2021-09-16 | 2021-12-24 | 势加透博洁净动力如皋有限公司 | Air compressor |
-
2018
- 2018-11-13 CN CN201811346535.9A patent/CN110541831A/en active Pending
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112983848A (en) * | 2021-02-04 | 2021-06-18 | 北京稳力科技有限公司 | Fuel cell stack and gas supply device |
| CN112983848B (en) * | 2021-02-04 | 2023-02-10 | 北京稳力科技有限公司 | Fuel cell stack and gas supply device |
| CN113833675A (en) * | 2021-09-16 | 2021-12-24 | 势加透博洁净动力如皋有限公司 | Impeller and air compressor with same |
| CN113833676A (en) * | 2021-09-16 | 2021-12-24 | 势加透博洁净动力如皋有限公司 | Air compressor |
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