WO2019020288A1 - Turbomachine, notamment pour un système de piles à combustible - Google Patents

Turbomachine, notamment pour un système de piles à combustible Download PDF

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Publication number
WO2019020288A1
WO2019020288A1 PCT/EP2018/066415 EP2018066415W WO2019020288A1 WO 2019020288 A1 WO2019020288 A1 WO 2019020288A1 EP 2018066415 W EP2018066415 W EP 2018066415W WO 2019020288 A1 WO2019020288 A1 WO 2019020288A1
Authority
WO
WIPO (PCT)
Prior art keywords
turbomachine
impeller
fuel cell
shaft
disk
Prior art date
Application number
PCT/EP2018/066415
Other languages
German (de)
English (en)
Inventor
Felix WIEDMANN
Original Assignee
Robert Bosch Gmbh
Priority date (The priority date 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 date listed.)
Filing date
Publication date
Application filed by Robert Bosch Gmbh filed Critical Robert Bosch Gmbh
Publication of WO2019020288A1 publication Critical patent/WO2019020288A1/fr

Links

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
    • F04D29/05—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
    • 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
    • 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
    • F04D25/024—Units comprising pumps and their driving means the driving means being assisted by a power recovery turbine
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
    • F16C—SHAFTS; FLEXIBLE SHAFTS; ELEMENTS OR CRANKSHAFT MECHANISMS; ROTARY BODIES OTHER THAN GEARING ELEMENTS; BEARINGS
    • F16C17/00—Sliding-contact bearings for exclusively rotary movement
    • F16C17/04—Sliding-contact bearings for exclusively rotary movement for axial load only
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
    • F16C—SHAFTS; FLEXIBLE SHAFTS; ELEMENTS OR CRANKSHAFT MECHANISMS; ROTARY BODIES OTHER THAN GEARING ELEMENTS; BEARINGS
    • F16C37/00—Cooling of bearings
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
    • F16C—SHAFTS; FLEXIBLE SHAFTS; ELEMENTS OR CRANKSHAFT MECHANISMS; ROTARY BODIES OTHER THAN GEARING ELEMENTS; BEARINGS
    • F16C2360/00—Engines or pumps
    • F16C2360/44—Centrifugal pumps

Definitions

  • Turbomachines designed as turbocompressors for a fuel cell system are known from the prior art, for example from the published patent application DE 10 2012 224 052 A1.
  • the known turbocompressor has one of a
  • a turbomachine designed as a turbocompressor is known from the published patent application DE 10 2008 044 876 A1.
  • Turbocompressor has an impeller arranged on a shaft.
  • the impeller is designed as a radial runner, so is flowed through on its front by a working fluid along a flow path, wherein the flow path is an axial
  • Flowing and a radial flow end comprises.
  • the object of the present invention is the optimization of such thrust washers.
  • the turbomachine according to the invention has a strength and weight-optimized thrust washer.
  • the turbomachine is in one
  • the turbomachine comprises a shaft, an impeller and the thrust washer.
  • the impeller and the thrust washer are arranged on the shaft.
  • At the Axiallagerinstallation is designed a tread for axial storage.
  • the tread forms a thrust bearing with a corresponding bearing surface.
  • the thrust washer has a first cover plate and a second cover disc opposite thereto.
  • the two cover plates are connected by a plurality of ribs.
  • the tread is formed on the first cover plate.
  • the two cover plates are made comparatively thin, preferably with a maximum thickness of 2 mm. Therefore, the weight is the whole
  • the ribs preferably a number of at least 20 ribs, give the thrust washer the necessary strength and rigidity, so that the deformation of the tread - and thus also potential wear - is minimized.
  • the running surface cooperates with the bearing surface, which is formed, for example, stationary on a housing of the turbomachine or on a component connected to the housing.
  • the impeller is designed as a radial rotor.
  • the impeller is flowed through on its front by a working fluid along a flow path.
  • the flow path includes an axial flow end and a radial flow end.
  • the turbomachine has a very high efficiency. Functionally occur on the impeller but then fluidly resulting axial forces, which are supported by the thrust washer.
  • Axiallagerarea is therefore very effective especially for radial runners.
  • the stiffness of the tread is very important to unwanted
  • the impeller is designed as a compressor, wherein the axial
  • the compressor preferably has an electromagnetic drive device.
  • the required power of the drive device is reduced.
  • the axial bearing disk faces the rear side of the rotor wheel. As a result, the thrust washer is space-saving within the
  • the ribs are designed to extend radially outward.
  • the axial bearing disc is comparatively easy to manufacture, for example, as a castable executable. Nevertheless, weight and stiffness are approximate
  • the two cover plates are designed to be rotationally symmetrical.
  • the axial bearing disk has on its inner periphery a hub with an inner bore formed therein.
  • the hub is therefore provided with the smallest possible diameter, but preferably has comparatively much material for increasing the strength. However, since this material is only exposed to a relatively low peripheral speed, the corresponding centrifugal forces are minimized.
  • a further running surface is formed on the second cover disk.
  • the other tread is opposite to the tread. Consequently, the further running surface of the bearing of the thrust washer serves in the
  • the thrust bearing is thus acting in both directions.
  • the bearing forces can be reduced in amount, since not necessarily a single axial effective direction of the force must be maintained, but a sign change is allowed.
  • the turbomachine is arranged in a fuel cell system.
  • the turbomachine is designed as a turbo compressor or the impeller as a compressor.
  • the fuel cell system includes a fuel cell, an air supply passage for supplying an oxidant into the fuel cell, and an exhaust passage for discharging the oxidant from the fuel cell.
  • the compressor is arranged in the air supply line.
  • the air supply line is used In this case, the inflow of the working fluid or oxidant in the fuel cell, and the exhaust pipe is used for removal of the oxidant or the reacted
  • Oxidizing agent or a mixture thereof from the fuel cell is Oxidizing agent or a mixture thereof from the fuel cell.
  • Turbocompressor is designed according to one of the embodiments described above.
  • the impeller is designed as a radial runner.
  • the minimized weight of the thrust washer contributes to increasing the efficiency of the entire turbo compressor. Furthermore, this increases the maximum possible acceleration of the impeller and thus the functionality of the turbocompressor.
  • the fuel cell system has an exhaust gas turbine with a further impeller.
  • the further impeller is also arranged on the shaft.
  • the exhaust gas turbine is arranged in the exhaust pipe.
  • the further impeller of the exhaust gas turbine is arranged opposite to the impeller of the turbocompressor, so that the respective effective resulting axial forces on the two wheels partially compensate each other.
  • the reacted working fluid or oxidizing agent flowing out of the fuel cell can be used very effectively as a power source for the exhaust gas turbine; As a result, the required drive power of the drive device for the turbocompressor is reduced.
  • the fuel cell system may preferably be adapted to a
  • FIG. 1 shows schematically a fuel cell system with a turbocharger compressor
  • FIG. 2 shows schematically a section through a turbomachine according to the invention, wherein only the essential areas are shown.
  • FIG. 3 is a perspective view of an axial bearing disk of a turbomachine.
  • the fuel cell system 1 shows a fuel cell system 1 known from DE 10 2012 224 052 A1.
  • the fuel cell system 1 comprises a fuel cell 2, an air supply line 3, an exhaust pipe 4, a compressor 1 1, an exhaust gas turbine 13, a bypass valve 5 for pressure reduction and a feed line not shown in detail for fuel to the fuel cell 2.
  • the bypass valve 5, for example, a control valve his.
  • a bypass valve 5 for example, a wastegate valve can be used.
  • the fuel cell 2 is a galvanic cell that converts chemical reaction energy of a fuel supplied via the not shown fuel supply line and an oxidizing agent into electric energy shown in FIG.
  • Embodiment is intake air, which is supplied via the air supply line 3 of the fuel cell 2.
  • the fuel may preferably be hydrogen or methane or methanol. Accordingly, the exhaust gas is water vapor or water vapor and carbon dioxide.
  • the fuel cell 2 is set up, for example
  • the electrical energy generated by the fuel cell 2 drives an electric motor of the
  • the compressor 1 1 is arranged in the air supply line 3.
  • the exhaust gas turbine 13 is arranged in the exhaust pipe 4.
  • the compressor 1 1 and the exhaust gas turbine 13 are mechanically connected via a shaft 14.
  • the shaft 14 is electrically driven by a drive device 20.
  • the exhaust gas turbine 13 serves to support the drive device 20 for driving the shaft 14 or the compressor 11.
  • the compressor 1 1, the shaft 14 and the exhaust gas turbine 13 together form a turbomachine 10.
  • turbomachine 10 schematically shows a longitudinal section of a turbomachine 10, in particular for use in a fuel cell system 1.
  • the turbomachine 10 is designed in this embodiment as a turbocompressor 10 and has an arranged on the shaft 14 impeller 15, which acts as a compressor 1 1 and compressor.
  • the turbomachine 10 optionally has the exhaust gas turbine 13, which on the shaft 14 arranged further impeller 13 includes a.
  • the further impeller 13 a and the impeller 15 are positioned on the opposite ends of the shaft 14.
  • the turbomachine 10 is arranged in the fuel cell system 1, so that the impeller 15 of the compressor 1 1 is arranged in the air supply line 3 and so that the further impeller 13a of the exhaust gas turbine 13 is arranged in the exhaust pipe 4.
  • the impeller 15 is executed in the embodiment of Figure 2 as a radial rotor, so in the case of use as turbo compressor or compressor 1 1 flows axially and flows radially.
  • the impeller 15 has on its front side 15a a flow path 16, which comprises an axial flow end 18 and a radial flow end 17.
  • a flow path 16 which comprises an axial flow end 18 and a radial flow end 17.
  • the direction of a working fluid flowing through the impeller 15 changes by approximately 90 ° in the sectional view.
  • the impeller 15 On its front side 15a, the impeller 15 is at the pressure of the working fluid
  • Turbomachine 10 both as a turbocompressor and as a turbine.
  • the turbomachine 10 When using the turbomachine 10 as a turbine, only the direction of the flow path 16 is reversed, namely from the radial flow end 17 to the axial flow end 18; however, the qualitative pressure ratios on the front side 15a are the same as those of the turbo-compressor.
  • the rear side 15b of the impeller 15 is constantly acted upon by the high pressure of the radial flow end 17. This results in a resulting fluidic force on the impeller 15, which acts in FIG. 2 to the left.
  • the thrust bearing 35 comprises an axial bearing washer 30 arranged on the shaft 14.
  • the axial bearing washer 30 can be pressed onto the shaft 14, for example, or, as shown in FIG. 2, by means of a nut 49 with the impeller 15 interposed against a shoulder of the shaft 14 be tense.
  • the thrust bearing 30 has a preferably hardened and ground running surface 31 for the thrust bearing 35, which cooperates with a bearing surface 81 which is formed in the embodiment of Figure 2 on a housing 8 of the turbomachine 10.
  • the housing 8 can also be designed in several parts or the bearing surface 81 may be formed on a further connected to the housing 8 component.
  • a further running surface 32 is formed on the axial bearing disk 30, opposite and opposite to the running surface 31, which has a further bearing surface 82
  • the further bearing surface 82 is formed on the housing 8, but may alternatively also be formed on a further component connected to the housing 8.
  • the drive device 20 of the turbomachine 10 embodied as a turbocompressor is designed as an electric motor, arranged between the compressor 11 and the exhaust gas turbine 13 and comprises a rotor 21 and a stator 22.
  • the rotor 21 is likewise arranged on the shaft 14.
  • the stator 22 is stationarily positioned in the only partially illustrated housing 8 of the turbocompressor 10.
  • the housing 8 can also be designed in several parts.
  • the shaft 14 is rotatably mounted on both sides of the drive device 20 by means of a respective radial bearing 41, 42.
  • the drive device 20 is positioned between the two radial bearings 41, 42.
  • the impeller 15 is disposed at one end and the other impeller 13 a, which forms the exhaust gas turbine 13 at the other end.
  • FIG. 3 shows a perspective view of the axial bearing disk 30 of the turbomachine 10.
  • the axial bearing disk 30 comprises two cover disks: a first cover disk 34 and a second cover disk 35.
  • the two cover disks 34, 35 are arranged opposite one another and by a multiplicity of radial ribs 36 connected with each other.
  • the thrust washer 30 On its inner circumference, the thrust washer 30 has a hub 37 with an inner bore 38 formed therein. At the inner bore 38 is the
  • Thrust washer 30 arranged on the shaft 14, for example, pressed onto this.
  • the hub 37 and the two shrouds 34, 35 are preferably
  • the ribs 36 extend radially outward, so are arranged in a star shape.
  • the Tread 31 is formed on the outer end face of the first cover plate 34.
  • the further running surface 32 is formed on the outer end face of the second cover disk 35, so that the axial bearing disk 30 is suitable for supporting both axial directions.
  • the ribs 36 which advantageously have a number of at least 20, give the thrust washer 30 a very high strength with minimum weight.
  • the use of only a single cover plate would have insufficient rigidity for the two treads 31, 32; only with a very thick - and thus very heavy - cover disc this would be possible.
  • the use of the two relatively thin cover plates 34, 35 reduces the mass of the thrust washer 30 and thus the centrifugally induced stresses in the hub 37 significantly, which in particular reduces the stress on the hub 37 and thus increases the life of the thrust washer 30.

Landscapes

  • Engineering & Computer Science (AREA)
  • General Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • Physics & Mathematics (AREA)
  • Fluid Mechanics (AREA)
  • Fuel Cell (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)

Abstract

Turbomachine (10), notamment pour un système de piles à combustible (1). La turbomachine (10) comprend un arbre (14), une roue à aubes (15) et un disque de palier axial (30). La roue à aubes (15) et le disque de palier axial (30) sont disposés sur l'arbre (14). Une surface de roulement (31) pour le support axial est formée sur le disque de palier axial (30). La surface de roulement (31) forme avec une surface de palier (81) correspondante un palier axial (35). Le disque de palier axial (30) comprend un premier disque de recouvrement (34) et un deuxième disque de recouvrement (35) lui étant opposé. Les deux disques de recouvrement (34, 35) sont reliés entre eux à travers une pluralité de nervures (36). La surface de roulement (31) est formée sur le premier disque de recouvrement (34).
PCT/EP2018/066415 2017-07-26 2018-06-20 Turbomachine, notamment pour un système de piles à combustible WO2019020288A1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE102017212819.4 2017-07-26
DE102017212819.4A DE102017212819A1 (de) 2017-07-26 2017-07-26 Turbomaschine, insbesondere für ein Brennstoffzellensystem

Publications (1)

Publication Number Publication Date
WO2019020288A1 true WO2019020288A1 (fr) 2019-01-31

Family

ID=62778896

Family Applications (1)

Application Number Title Priority Date Filing Date
PCT/EP2018/066415 WO2019020288A1 (fr) 2017-07-26 2018-06-20 Turbomachine, notamment pour un système de piles à combustible

Country Status (2)

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DE (1) DE102017212819A1 (fr)
WO (1) WO2019020288A1 (fr)

Families Citing this family (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE102019219080A1 (de) 2019-12-06 2021-06-10 Robert Bosch Gmbh Verdichter

Citations (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2799227A (en) * 1954-07-21 1957-07-16 Westinghouse Electric Corp Thrust bearing
JP2002332990A (ja) * 2001-05-09 2002-11-22 Shimadzu Corp ターボ形回転機器
EP2006497A1 (fr) 2007-06-21 2008-12-24 Siemens Aktiengesellschaft Disque de palier axial pour un rotor d'une turbosoufflante et rotor de turbosoufflante
DE102008044876A1 (de) 2008-08-29 2010-03-04 Daimler Ag Luftversorgungseinheit für eine Brennstoffzelle
DE102012211796A1 (de) * 2012-07-06 2014-01-23 Robert Bosch Gmbh Axiallager
DE102012224052A1 (de) 2012-12-20 2014-06-26 Robert Bosch Gmbh Verfahren zur Erfassung eines Verdichterpumpens eines elektrisch angetriebenen Verdichters und Brennstoffzellensystem mit einem elektrisch angetriebenen Verdichter und einem Regelgerät zum Durchführen des Verfahrens
DE102015007379A1 (de) * 2015-06-10 2016-01-21 Daimler Ag Strömungsmaschine für einen Energiewandler, insbesondere eine Brennstoffzelle

Patent Citations (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2799227A (en) * 1954-07-21 1957-07-16 Westinghouse Electric Corp Thrust bearing
JP2002332990A (ja) * 2001-05-09 2002-11-22 Shimadzu Corp ターボ形回転機器
EP2006497A1 (fr) 2007-06-21 2008-12-24 Siemens Aktiengesellschaft Disque de palier axial pour un rotor d'une turbosoufflante et rotor de turbosoufflante
DE102008044876A1 (de) 2008-08-29 2010-03-04 Daimler Ag Luftversorgungseinheit für eine Brennstoffzelle
DE102012211796A1 (de) * 2012-07-06 2014-01-23 Robert Bosch Gmbh Axiallager
DE102012224052A1 (de) 2012-12-20 2014-06-26 Robert Bosch Gmbh Verfahren zur Erfassung eines Verdichterpumpens eines elektrisch angetriebenen Verdichters und Brennstoffzellensystem mit einem elektrisch angetriebenen Verdichter und einem Regelgerät zum Durchführen des Verfahrens
DE102015007379A1 (de) * 2015-06-10 2016-01-21 Daimler Ag Strömungsmaschine für einen Energiewandler, insbesondere eine Brennstoffzelle

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Publication number Publication date
DE102017212819A1 (de) 2019-01-31

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