WO2020148029A1 - Système de palier de rotor pour une turbomachine - Google Patents

Système de palier de rotor pour une turbomachine Download PDF

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Publication number
WO2020148029A1
WO2020148029A1 PCT/EP2019/084622 EP2019084622W WO2020148029A1 WO 2020148029 A1 WO2020148029 A1 WO 2020148029A1 EP 2019084622 W EP2019084622 W EP 2019084622W WO 2020148029 A1 WO2020148029 A1 WO 2020148029A1
Authority
WO
WIPO (PCT)
Prior art keywords
rotor
film
bearing system
axial
air bearing
Prior art date
Application number
PCT/EP2019/084622
Other languages
German (de)
English (en)
Inventor
Felix WIEDMANN
Felix FOERSTER
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 WO2020148029A1 publication Critical patent/WO2020148029A1/fr

Links

Classifications

    • 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
    • F16C17/042—Sliding-contact bearings for exclusively rotary movement for axial load only with flexible leaves to create hydrodynamic wedge, e.g. axial foil bearings
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
    • F01D25/18—Lubricating arrangements
    • F01D25/22—Lubricating arrangements using working-fluid or other gaseous fluid as lubricant
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
    • F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
    • F02C7/06—Arrangements of bearings; Lubricating
    • 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
    • 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
    • F16C33/00—Parts of bearings; Special methods for making bearings or parts thereof
    • F16C33/02—Parts of sliding-contact bearings
    • F16C33/04—Brasses; Bushes; Linings
    • F16C33/06—Sliding surface mainly made of metal
    • F16C33/10—Construction relative to lubrication
    • F16C33/1005—Construction relative to lubrication with gas, e.g. air, as lubricant
    • F16C33/101—Details of the bearing surface, e.g. means to generate pressure such as lobes or wedges
    • F16C33/1015—Pressure generating grooves
    • 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
    • F16C33/00—Parts of bearings; Special methods for making bearings or parts thereof
    • F16C33/02—Parts of sliding-contact bearings
    • F16C33/04—Brasses; Bushes; Linings
    • F16C33/06—Sliding surface mainly made of metal
    • F16C33/14—Special methods of manufacture; Running-in
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2240/00—Components
    • F05D2240/50—Bearings
    • F05D2240/52—Axial thrust bearings
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2240/00—Components
    • F05D2240/50—Bearings
    • F05D2240/53—Hydrodynamic or hydrostatic 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
    • F16C2220/00—Shaping
    • F16C2220/60—Shaping by removing material, e.g. machining
    • 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
    • F16C2360/23—Gas turbine engines
    • F16C2360/24—Turbochargers

Definitions

  • the present invention relates to a rotor bearing system for a turbomachine.
  • the axial air bearings essentially comprise a cover film, a spring film and a thrust washer, on which the spring film and the cover film are arranged.
  • a rotor rotates and, due to its drag flow and the ramp geometry of the axial air bearing, builds up a gas film between the rotor and the cover film, which carries the axial forces of the rotor.
  • the spring film has the task of compensating for misalignment and conicity between the housing and the rotor and at the same time generating an air gap geometry that is favorable for the construction of the gas film. This is through the
  • Stiffness distribution achieved in the spring film which is adjusted by the geometry of the springs formed by the spring film and the film thickness.
  • Thrust washer and a first hump of the spring film has a curved convex shape.
  • the background of the invention is that rotor bearing systems which have an axial film-air bearing generally have a low load capacity.
  • Axial film-air bearings which have a higher load capacity are usually complex and therefore expensive to manufacture. It is therefore the object of the present invention to provide a rotor bearing system with an axial film-air bearing which has a higher load capacity and which is also economically producible.
  • the invention specifies a rotor bearing system for a turbomachine.
  • the rotor bearing system according to the invention comprises at least one axial film-air bearing with at least one cover film, which is provided axially spaced from a support means and with at least one spring film, which is arranged between the cover film and the support means, and a rotor, which is on the cover film of the axial film-air bearing and is rotatable relative to the axial film-air bearing, material recess areas being arranged in a gap between the rotor and the axial film-air bearing, via which an increase in pressure between the rotor and the axial film-air - Bearings can be generated.
  • a support means in the sense of the invention means a component which forms a fixed support for the spring foil. This can be, for example, a disc or part of a housing. When not in operation, the rotor lies directly against the cover film at at least one point.
  • Material recess areas are completely in contact, not possible even when not in operation, so that there is a gap between the rotor and the cover film. This gap increases in operation due to a gas film generated between the rotor and the cover film, so that the rotor is completely detached from the cover film.
  • the material recess areas are arranged in this gap.
  • a material recess area is understood to mean an area in which part of the original material has been removed.
  • the invention has the advantage that an increased load-bearing capacity is generated by the material recess areas. Bearings with such a high load capacity are regularly sensitive to tolerances. This means that the components rotating relative to one another must be aligned particularly precisely with respect to one another.
  • the axial foil-air bearing has the advantage that it is relative
  • Material recess areas are at least partially ramp-shaped.
  • a height adjustment which extends over an area is referred to as ramp-shaped in the sense of the invention. With such ramps, flow losses in the gap can be reduced. Also are
  • Material recess areas compared to adjacent areas, levels. Levels in the sense of the invention are understood to mean sudden changes in height. With such steps, material is preferably removed uniformly only in one area. In contrast to a ramp-shaped design, stages are easier and therefore more economical to produce. With the steps, a pressure increase between the rotor and the axial film-air bearing can be effectively achieved.
  • the steps are preferably designed as Rayleigh steps.
  • the Rayleigh steps are a specific shape of the steps with which a high effect is achieved with regard to the improvement in the load capacity.
  • the material recess areas are formed by the rotor. In comparison to material recess areas on the cover film, this has the advantage that the height of the material recesses essentially does not change due to the wear of the cover film. The effect of the material recess areas can thereby be permanently ensured. In addition, a longer durability of such a rotor bearing system can be achieved.
  • the material recess areas are advantageously formed on the part of the cover film. Due to the material recess areas, no embossing steps stiffening the cover film are necessary, so that the cover film can be better adapted to different operating conditions.
  • the invention is further enhanced by a method of making the
  • Rotor bearing system according to the invention solved for a turbomachine.
  • the method comprises at least the step that
  • Material recess areas, in a gap between the rotor and the axial film-air bearing, are formed by a material removal step.
  • a material removal step is understood to mean any processing step in which part of the original material is removed. As a result, the material recess areas can be formed without reshaping or embossing. Such a material removal step simplifies the manufacture of such a rotor bearing system and thus leads to one
  • At least one is preferably used as the material removal step
  • An etching processing step has the advantage that material can be selectively removed and thus the
  • Material recess areas can be manufactured with high precision in any desired shape. Such a processing step is also quick and economical.
  • At least one laser processing step is used as the material removal step.
  • a laser processing step has the advantage that it is cost-effective even with small quantities.
  • this processing step is very precise and extremely flexible in the form to be achieved.
  • the invention is achieved by a fuel cell system which comprises the rotor bearing system according to the invention. The advantages mentioned for the rotor bearing system are achieved with such a fuel cell system.
  • Figure 1 sectional view of a first embodiment of the
  • FIG. 1 top view of a cover sheet of the rotor bearing system according to the first
  • Figure 3 is a sectional view of a second embodiment of the
  • FIG. 4 top view of a rotor of the rotor bearing system according to the second
  • FIG. 1 shows a sectional view of a first exemplary embodiment of a rotor bearing system 10 according to the invention.
  • the rotor bearing system 10 comprises an axial film-air bearing 14 which has a support means 18 which in this exemplary embodiment is fixedly connected to a housing 22.
  • a cover film 26 is axially spaced from the support means 18 in some areas.
  • the cover film 26 is connected to the support means 18 at a radial outer end.
  • a spring film 30 is arranged between the cover film 26 and the support means 18, which in this exemplary embodiment is formed by a wavy structure. Axial forces can be absorbed via the spring film 30.
  • the rotor bearing system 10 additionally comprises a rotor 34, which is arranged rotatable about a central axis 38 with respect to the axial film-air bearing 14.
  • the rotor 34 lies against the cover film 26 of the axial film-air bearing 14.
  • In this figure shows a gap 42 formed by a drag flow between rotor 34 and cover film 26. The axial forces of the rotor 34 are borne by the gas film present in the gap 42.
  • the cover film 26 has in the first embodiment
  • Material recess areas 46 have been formed by a material removal step, such as, for example, etching or laser processing. This means that a depression is formed in the cover film 26 in this material recess area 46.
  • a pressure increase between the rotor 34 and the axial film-air bearing 14 can be generated via the material recess areas 46, so that a higher axial load can be borne by the rotor bearing system 10.
  • Figure 2 shows a plan view of the cover sheet 26 of the rotor bearing system 10 according to the first embodiment.
  • the cover sheet 26 has in this
  • Embodiment a retaining ring 50, via which the cover sheet 26 can be connected to the support means 18.
  • An inner part of the cover film 26 is connected to the retaining ring 50 via retaining webs 54.
  • Material recess areas 46 and areas 58 without material recesses are alternately arranged on the cover film 26 in the circumferential direction. In this case, steps 62 are arranged between the material recess areas 46 and the areas 58 without material recesses
  • Embodiment are designed as Rayleigh steps. This
  • Material recess areas 46 can be by means of a
  • Material removal step can be easily formed. Instead of the steps 62, a transition between the material recess areas 46 and the area 58 can be made in an embodiment not shown
  • FIG. 3 shows a sectional view of a second exemplary embodiment of the rotor bearing system 10 according to the invention.
  • This exemplary embodiment differs from the exemplary embodiment in FIG. 1 in that the material recess regions 46 are arranged in a part of the rotor 34 which bears against the cover film 26 instead of in the cover film 26. Since the rotor 34 has a greater hardness than the cover film 26, this has the advantage that a Height h of the material recess areas 46 is not reduced by wear of the cover film 26. The function of the material recess areas 46 can thereby be permanently ensured.
  • Figure 4 shows a plan view of the rotor 34 of the rotor bearing system 10 according to the second embodiment. In this figure, as in FIG. 2, the material recess areas 46 are designed with Rayleigh steps. These material recess areas 46 can be by means of a
  • Material removal step can be easily formed. Ramps can also be formed here instead of steps 62.

Landscapes

  • Engineering & Computer Science (AREA)
  • General Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • Physics & Mathematics (AREA)
  • Fluid Mechanics (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
  • Support Of The Bearing (AREA)

Abstract

La présente invention concerne un système de palier de rotor (10) pour une turbomachine. Le système de palier de rotor (10) comprend au moins un palier axial à feuilles et à air (14) pourvu d'au moins une feuille de recouvrement (26), qui est située axialement à distance d'un moyen de support (18), et d'au moins une feuille élastique (30), qui est disposée entre la feuille de recouvrement (26) et le moyen de support (18), et un rotor (34), lequel s'applique contre la feuille de recouvrement (26) du palier axial à feuilles et à air (14) et peut tourner par rapport au palier axial à feuilles et à air (14), des zones d'évidement de matériau (46), par l'intermédiaire desquelles une augmentation de pression entre le rotor (34) et le palier axial à feuilles et à air (14) peut être produite, étant disposées dans une fente (42) entre le rotor (34) et le palier axial à feuilles et à air (14).
PCT/EP2019/084622 2019-01-14 2019-12-11 Système de palier de rotor pour une turbomachine WO2020148029A1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE102019200330.3A DE102019200330A1 (de) 2019-01-14 2019-01-14 Rotorlagersystem für eine Turbomaschine
DE102019200330.3 2019-01-14

Publications (1)

Publication Number Publication Date
WO2020148029A1 true WO2020148029A1 (fr) 2020-07-23

Family

ID=69055968

Family Applications (1)

Application Number Title Priority Date Filing Date
PCT/EP2019/084622 WO2020148029A1 (fr) 2019-01-14 2019-12-11 Système de palier de rotor pour une turbomachine

Country Status (2)

Country Link
DE (1) DE102019200330A1 (fr)
WO (1) WO2020148029A1 (fr)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN113569361A (zh) * 2021-08-26 2021-10-29 北京动力机械研究所 一种径向波箔动压气体轴承承载力的预测方法

Families Citing this family (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE102022210412A1 (de) 2022-09-30 2024-04-04 Robert Bosch Gesellschaft mit beschränkter Haftung Folienaxiallager und Verfahren zum Montieren eines Folienaxiallagers
DE102023201450A1 (de) 2023-02-20 2024-08-22 Robert Bosch Gesellschaft mit beschränkter Haftung Axialfolienlager
DE102023201452A1 (de) 2023-02-20 2024-08-22 Robert Bosch Gesellschaft mit beschränkter Haftung Axialfolienlager

Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JP2005155802A (ja) * 2003-11-26 2005-06-16 Koyo Seiko Co Ltd スラスト動圧軸受
JP2006183786A (ja) * 2004-12-27 2006-07-13 Toyota Central Res & Dev Lab Inc 流体スラスト軸受
US7731476B2 (en) * 2007-01-30 2010-06-08 Technology Commercialization Corp. Method and device for reducing axial thrust and radial oscillations and rotary machines using same
US20120207414A1 (en) 2009-10-07 2012-08-16 Neuros Co., Ltd. Thrust Foil Air Bearing
JP2013053645A (ja) * 2011-09-01 2013-03-21 Ntn Corp スラストフォイル軸受

Patent Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JP2005155802A (ja) * 2003-11-26 2005-06-16 Koyo Seiko Co Ltd スラスト動圧軸受
JP2006183786A (ja) * 2004-12-27 2006-07-13 Toyota Central Res & Dev Lab Inc 流体スラスト軸受
US7731476B2 (en) * 2007-01-30 2010-06-08 Technology Commercialization Corp. Method and device for reducing axial thrust and radial oscillations and rotary machines using same
US20120207414A1 (en) 2009-10-07 2012-08-16 Neuros Co., Ltd. Thrust Foil Air Bearing
JP2013053645A (ja) * 2011-09-01 2013-03-21 Ntn Corp スラストフォイル軸受

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN113569361A (zh) * 2021-08-26 2021-10-29 北京动力机械研究所 一种径向波箔动压气体轴承承载力的预测方法

Also Published As

Publication number Publication date
DE102019200330A1 (de) 2020-07-16

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