WO2019185351A1 - Turbomachine, en particulier dispositif compresseur - Google Patents

Turbomachine, en particulier dispositif compresseur Download PDF

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Publication number
WO2019185351A1
WO2019185351A1 PCT/EP2019/056255 EP2019056255W WO2019185351A1 WO 2019185351 A1 WO2019185351 A1 WO 2019185351A1 EP 2019056255 W EP2019056255 W EP 2019056255W WO 2019185351 A1 WO2019185351 A1 WO 2019185351A1
Authority
WO
WIPO (PCT)
Prior art keywords
bearing
medium
pressure
turbomachine
shaft
Prior art date
Application number
PCT/EP2019/056255
Other languages
German (de)
English (en)
Inventor
Thomas RACHOW
Peter Philipp
Thomas Lang
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
Priority to EP19711314.5A priority Critical patent/EP3775568B1/fr
Priority to CN201980022187.6A priority patent/CN111936748B/zh
Priority to JP2020550097A priority patent/JP6973981B2/ja
Publication of WO2019185351A1 publication Critical patent/WO2019185351A1/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
    • F04D29/056—Bearings
    • F04D29/057—Bearings hydrostatic; hydrodynamic
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D29/00—Details, component parts, or accessories
    • F04D29/05—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
    • F04D29/00—Details, component parts, or accessories
    • F04D29/05—Shafts or bearings, or assemblies thereof, specially adapted for elastic fluid pumps
    • F04D29/056—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
    • 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

Definitions

  • the invention relates to a turbomachine, in particular a Ver Whyreinrich device, with the features of the preamble of claim 1.
  • Such a turbomachine with a compressor device such as is part of a turbomachine, has a shaft to be stored, wherein in the storage area, the shaft typically has a peripheral speed of more than 100 meters per second and / or a speed of more than
  • Supply device is supplied in the form of a pressure source in a bearing bore of the bearing device.
  • a pressure source for supplying the bearing device with compressed air consists for example of a separate
  • a generic turbomachine which does not require an additional separate supply device or compressed air source for providing the gaseous medium for the storage facility, since the compressor stage in the region of a pressure outlet, where increased by the compressor stage Pressure of the medium or the air is applied, with a supply device in the form of a Pressure accumulator is coupled, which in turn provides the air for the bearings of the storage facility or supplies them with pressurized air.
  • Compressor stage in particular in the form of a compressor wheel to store rotatably in a housing. Between the housing and the compressor stage design-related gaps are formed, can flow through the pressurized medium or gas. Although it is attempted to seal these leakage gaps in particular by means of separate sealing elements, since leakage losses are synonymous with an efficiency reduction of the compressor device. However, such sealing elements require an additional
  • the turbomachine according to the invention in particular Ver Whyreinrich device, with the features of claim 1 has the advantage that the (gaseous) medium with little device complexity of the at least one bearing device can be fed.
  • a leakage gap is formed between the at least one flow element and the housing in a region in which the medium has an increased pressure, wherein the medium from the leakage gap is at least indirectly fed to the at least one bearing device, and / / or that the least one flow element has at least one pressure outlet bore for the medium via which the medium can be supplied, at least indirectly, to the at least one bearing device.
  • turbomachinery leakage gap as a source for the under elevated pressure medium
  • Turbine rad a special structural design of the flow element (compressor stage or Turbine rad) by at least one pressure outlet bore, wherein on the Druckauslass- bore the compressed in relation to an original state compressed medium of at least one bearing device can be fed.
  • such a structural design of the turbomachine or compressor device has the particular advantage that the otherwise existing sealing devices are designed to be particularly simple in construction or to avoid leakage losses can even be omitted entirely, while in a solution in which at least one pressure outlet hole is provided in the region of the flow element, it is possible in a particularly simple manner, by a corresponding positioning and number or cross section of the Druckauslassbohritch both the amount, and the Pressure of the storage of the wave required Medi order to influence or adjust in a particularly simple manner.
  • the leakage gap is connected via at least one pressure line for the medium immedi applicable to the at least one bearing device.
  • the connection between the leakage gap and the bearing device takes place exclusively via a corresponding (pressure) line and, in contrast to the aforementioned prior art, for example, no pressure accumulator designed as a separate component is required.
  • At least one pressure outlet hole in a preferred embodiment that the at least one pressure outlet bore is connected via at least one pressure line for the medium immedi applicable to the at least one bearing device.
  • the pressure or the amount of the provided by the Strö determination machine or compressor device medium for we least one storage device may vary, it may alternatively be provided that in the flow path of the at least one pressure line as a separate component trained pressure accumulator is arranged.
  • the pressure accumulator ensures that at times small amounts or low pressures of the medium sufficient (gaseous) medium is ready for storage of the shaft.
  • the we least one storage device a pressure regulating device is connected upstream, which regulates the pressure or the amount of medium which can be supplied to the bearing device. In this way, in particular, the bearing of the shaft is negatively influenced, excessive pressures of the medium are avoided.
  • the Strö tion machine in particular compressor device, it may be provided in particular in a variant in which the medium from the region of the leakage gap is Won, that the area of the leakage gap is formed dichtungsele mentfree.
  • the separate component ring-shaped or disc-shaped and is arranged stationarily in relation to the flow element that the least one pressure outlet hole is formed as a through hole extending between two opposite axial end faces of the flow element extends, and that the annular groove is designed as a radially encircling the axis of rotation, circular-shaped annular groove.
  • Such a configuration in particular special of the annular groove has the advantage that during the entire rotation of the flow element about its axis of rotation always a pneumatic connection between the at least one pressure outlet bore and the bearing means via the annular groove can be formed.
  • a further structural design which reduces the expense of the bearing device provides that the bearing device is a thrust bearing which acts on opposite end faces of a bearing disc connected to the shaft, and that the medium acts only on the end face of the bearing disc facing the flow element.
  • the bearing device is either supplied via a different medium source, or else via a bearing element of a different construction, e.g. a foil bearing, a storage via spiral grooves or the like has.
  • Each lb a simplified longitudinal section in the region of a Ver emphasizerein direction, is provided in the gaseous medium for supplying a ger ger or radial bearing designed as Axialla or radial bearing from the range of a leakage gap,
  • FIGS. 1 and 2 shows a longitudinal section through a modified compressor device, is provided in the medium for a storage facility in the range of Druckauslassboh ments on a compressor wheel
  • Fig. 3 shows a detail of a comparison with FIGS. 1 and 2 modified compressor device using an intermediate Druckspei Chers and
  • Fig. 4 is a comparison with FIGS. 1 and 2 modified compressor device, wherein the bearing device is supplied only at one end face with medium from the compressor device.
  • the turbomachine shown greatly simplified in FIGS. 1a and 1b is, for example, part of a fuel cell system, an air conditioning system, a heat pump, a turbocharger, a turbine for a fuel cell system or a heat recovery turbine.
  • the turbomachine in the form of a compressor device 10 is.
  • the compressor device 10 comprises a shaft 14 which is mounted in a rotation axis 12 and to which an end face of a compressor stage 16 in the form of a compressor wheel 18 of radial design is connected in a rotationally fixed manner to the shaft 14.
  • the compressor stage 16 or the compressor wheel 18 is surrounded by a housing 20 having an inlet region 22, is sucked through the gaseous medium, in particular air, in the compressor device 10, and upon rotation of the shaft 14 about the axis of rotation 12 through the compressor stage 16 is compressed or increased in pressure so that it exits in the region of an outlet region 24 of the housing 20 under increased pressure and can be supplied to a consumer, not shown.
  • a radially encircling leakage gap 30 is formed, via which the pressure in its increased pressure relative to the inlet portion 22 increased medium can escape.
  • the region of the leakage gap 30 on the side facing away from the Ge 20 of an annular, to the leakage gap 30 back open collecting element 32 is surrounded, via which the leaking from the leakage gap 30 medium via at least one pressure line 34 directly to a La ger worn 36 for the shaft 14 can be fed.
  • the bearing device 36 is formed in FIG. La as a thrust bearing and has two opposite end faces of a non-rotatably connected to the shaft 14 nen NEN bearing plate 38 arranged, annular bearing elements 40, 42.
  • the two bearing elements 40, 42 each have feed holes 44, 46, via which the pressurized medium from the pressure line 34 acts on the end faces of the bearing ring 38 and provides a corresponding pressure pad to an axial bearing of the shaft 14 to the housing 20th to enable.
  • the bearing means 36a in contrast forms out as a radial bearing and comprises a shaft 14 radially enclosing bearing element 48, the supply via feed bores 50, 52 and the at least one pressure line 34 immediacy bar with pressurized medium from the leakage gap 30 can be supplied ,
  • a modified compressor device 10 in which a compressor 55 at least one, but preferably a plurality of evenly spaced on a pitch circle diameter about the axis of rotation 12 arranged Druckauslassbohronne 56 in the form of through holes 58 which are parallel to the shaft 14 extend.
  • the Druckauslassbohrun conditions 56 connect the housing 20 facing the end face of the compressor wheel 55, which is present at the medium under pressure, with the rear end face 60 of the compressor 55th
  • the radial distance of the pressure outlet bores 56 from the axis of rotation 12 determines the level of pressure of the medium for the bearing means 36a.
  • the compressor 55 is positioned on the side facing away from the housing 20 at least in the region of the pressure outlet bores 56 in register with a ringförmi gene, stationarily arranged element 62.
  • the element 62 has a radial on the same pitch circle diameter as the pressure outlet bores 56 circumferential annular groove 64, which in turn is arranged via at least one pressure line 66 with the bearing means 36a in operative connection.
  • Fig. 3 the case is shown, in which the at least one pressure line 34, 66 with the interposition of a pressure accumulator 70 and a Druckregelein device 72 with the bearing means 36, 36 a is connected.
  • FIG. 4 shows the case in which the bearing ring 38 of the bearing device 36 b has a bearing element 40 on one of the compressor stages 16, which is supplied with pressurized medium by the compressor device 10, while the other Front side of the bearing ring 38 with the bearing element 76 either via a different (pressure) source 74 in the direction of the housing 20 is subjected to force.
  • the Lagerele element 76 may also be a bearing element 76, which is not designed as gasticianbeaufschlagtes bearing element 76.
  • the compressor device 10 described so far can be modified or modified in many ways, without dodging from the idea of the invention.
  • the compressor stage 16 may have a compressor wheel designed in an axial construction.
  • the principle of action can also on one
  • Turbine or working machine are applied.
  • a work stage or a turbine wheel is used accordingly.

Landscapes

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

Abstract

L'invention concerne une turbomachine (10), en particulier un dispositif compresseur, pourvu d'au moins un dispositif support (36 ; 36a ; 36b) pour un arbre (14) disposé en rotation. Le ou les dispositifs support (36 ; 36a ; 36b) présentent au moins un élément (40, 42 ; 48) de support pour le support radial et/ou axial de l'arbre (14). L'élément ou les éléments (40, 42 ; 48) de support peuvent être soumis à l'effet d'un milieu gazeux sous pression pour le support de l'arbre (14). L'arbre (14) est relié à un élément d'écoulement (16) entraîné ou pouvant être entraîné, en particulier à une roue (18) de compresseur. L'élément d'écoulement (16) est disposé dans un carter (20) entourant au moins en partie l'élément d'écoulement (16), et le milieu sous pression peut être amené au moins indirectement de la turbomachine (10) à l'élément ou aux éléments (40, 42 ; 48) de support.
PCT/EP2019/056255 2018-03-27 2019-03-13 Turbomachine, en particulier dispositif compresseur WO2019185351A1 (fr)

Priority Applications (3)

Application Number Priority Date Filing Date Title
EP19711314.5A EP3775568B1 (fr) 2018-03-27 2019-03-13 Turbomachine, en particulier dispositif compresseur
CN201980022187.6A CN111936748B (zh) 2018-03-27 2019-03-13 流体机器、尤其是压缩机装置
JP2020550097A JP6973981B2 (ja) 2018-03-27 2019-03-13 流体機械、特にコンプレッサ装置

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE102018204619.0A DE102018204619A1 (de) 2018-03-27 2018-03-27 Strömungsmaschine, insbesondere Verdichtereinrichtung
DE102018204619.0 2018-03-27

Publications (1)

Publication Number Publication Date
WO2019185351A1 true WO2019185351A1 (fr) 2019-10-03

Family

ID=65802081

Family Applications (1)

Application Number Title Priority Date Filing Date
PCT/EP2019/056255 WO2019185351A1 (fr) 2018-03-27 2019-03-13 Turbomachine, en particulier dispositif compresseur

Country Status (5)

Country Link
EP (1) EP3775568B1 (fr)
JP (1) JP6973981B2 (fr)
CN (1) CN111936748B (fr)
DE (1) DE102018204619A1 (fr)
WO (1) WO2019185351A1 (fr)

Citations (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0212091A1 (fr) * 1985-06-10 1987-03-04 INTERATOM Gesellschaft mit beschränkter Haftung Turbo-soufflante avec un palier aérostatique
WO2014000867A1 (fr) * 2012-06-29 2014-01-03 Daimler Ag Turbomachine pour convertisseur d'énergie et dispositif à pile à combustible comprenant une telle turbomachine
US20140352299A1 (en) * 2013-05-31 2014-12-04 GM Global Technology Operations LLC Turbocharger assembly
US20140371919A1 (en) * 2011-12-21 2014-12-18 Venus Systems Limited Centrifugal refrigerant vapour compressors
DE102015007379A1 (de) * 2015-06-10 2016-01-21 Daimler Ag Strömungsmaschine für einen Energiewandler, insbesondere eine Brennstoffzelle
US20160298648A1 (en) * 2011-02-07 2016-10-13 Gregory Graham Centrifugal compressor
DE102017211033A1 (de) 2017-06-29 2019-01-03 Robert Bosch Gmbh Verdichtereinrichtung und elektrische Maschine

Family Cites Families (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE102008038787A1 (de) * 2008-08-13 2010-02-18 Siemens Aktiengesellschaft Fluidenergiemaschine
DE102012211882A1 (de) * 2012-07-06 2014-01-09 Abb Turbo Systems Ag Ölfreies Lager eines Abgasturboladers
US9709068B2 (en) * 2014-02-19 2017-07-18 Honeywell International Inc. Sealing arrangement for fuel cell compressor
CN105889096B (zh) * 2016-05-06 2019-10-18 同济大学 燃料电池发动机的两级串联增压直驱离心式空压机
CN106015032B (zh) * 2016-06-28 2018-05-22 杭州万辰机电科技有限公司 离心压缩机

Patent Citations (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0212091A1 (fr) * 1985-06-10 1987-03-04 INTERATOM Gesellschaft mit beschränkter Haftung Turbo-soufflante avec un palier aérostatique
US20160298648A1 (en) * 2011-02-07 2016-10-13 Gregory Graham Centrifugal compressor
US20140371919A1 (en) * 2011-12-21 2014-12-18 Venus Systems Limited Centrifugal refrigerant vapour compressors
WO2014000867A1 (fr) * 2012-06-29 2014-01-03 Daimler Ag Turbomachine pour convertisseur d'énergie et dispositif à pile à combustible comprenant une telle turbomachine
US20140352299A1 (en) * 2013-05-31 2014-12-04 GM Global Technology Operations LLC Turbocharger assembly
DE102015007379A1 (de) * 2015-06-10 2016-01-21 Daimler Ag Strömungsmaschine für einen Energiewandler, insbesondere eine Brennstoffzelle
DE102017211033A1 (de) 2017-06-29 2019-01-03 Robert Bosch Gmbh Verdichtereinrichtung und elektrische Maschine

Also Published As

Publication number Publication date
CN111936748B (zh) 2022-09-16
EP3775568B1 (fr) 2023-06-28
CN111936748A (zh) 2020-11-13
DE102018204619A1 (de) 2019-10-02
JP2021516311A (ja) 2021-07-01
JP6973981B2 (ja) 2021-12-01
EP3775568A1 (fr) 2021-02-17

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