WO2018091629A1 - Coussinet de palier de butée de tourillon de support d'arbre d'un turbocompresseur d'échappement - Google Patents

Coussinet de palier de butée de tourillon de support d'arbre d'un turbocompresseur d'échappement Download PDF

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Publication number
WO2018091629A1
WO2018091629A1 PCT/EP2017/079541 EP2017079541W WO2018091629A1 WO 2018091629 A1 WO2018091629 A1 WO 2018091629A1 EP 2017079541 W EP2017079541 W EP 2017079541W WO 2018091629 A1 WO2018091629 A1 WO 2018091629A1
Authority
WO
WIPO (PCT)
Prior art keywords
bearing bush
bearing
axial
wedge
thrust
Prior art date
Application number
PCT/EP2017/079541
Other languages
English (en)
Inventor
Stefan Körner
Lukas Smilek
D. Subramani
V. Alagarsamy
Original Assignee
Turbo Energy Private Limited
Turbo Energy Germany 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 Turbo Energy Private Limited, Turbo Energy Germany Gmbh filed Critical Turbo Energy Private Limited
Priority to EP17801035.1A priority Critical patent/EP3542078A1/fr
Publication of WO2018091629A1 publication Critical patent/WO2018091629A1/fr

Links

Classifications

    • 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
    • F01D25/16—Arrangement of bearings; Supporting or mounting bearings in casings
    • 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
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02B—INTERNAL-COMBUSTION PISTON ENGINES; COMBUSTION ENGINES IN GENERAL
    • F02B39/00—Component parts, details, or accessories relating to, driven charging or scavenging pumps, not provided for in groups F02B33/00 - F02B37/00
    • F02B39/14—Lubrication of pumps; Safety measures therefor
    • 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
    • F16C17/10—Sliding-contact bearings for exclusively rotary movement for both radial and axial load
    • 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
    • F16C27/00—Elastic or yielding bearings or bearing supports, for exclusively rotary movement
    • F16C27/02—Sliding-contact 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
    • F16C33/1025—Construction relative to lubrication with liquid, e.g. oil, as lubricant
    • F16C33/106—Details of distribution or circulation inside the bearings, e.g. details of the bearing surfaces to affect flow or pressure of the liquid
    • F16C33/1075—Wedges, e.g. ramps or lobes, for generating pressure
    • 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
    • F05D2220/00—Application
    • F05D2220/40—Application in turbochargers
    • 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
    • F16C17/047—Sliding-contact bearings for exclusively rotary movement for axial load only with fixed wedges to generate hydrodynamic pressure
    • 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
    • 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
    • F16C33/1025—Construction relative to lubrication with liquid, e.g. oil, as lubricant
    • F16C33/106—Details of distribution or circulation inside the bearings, e.g. details of the bearing surfaces to affect flow or pressure of the liquid
    • F16C33/1065—Grooves on a bearing surface for distributing or collecting the liquid

Definitions

  • the invention relates to a bearing bush for a shaft of a turbo charger according to the type further defined in the preamble of claim 1 .
  • the invention further relates to a turbo charger with such a bearing bush.
  • Turbo chargers are known from the general prior art. They typically comprise a continuing shaft on the one end of which a turbine is mounted and on the other end of which at least one compressor wheel is mounted.
  • Bearing bushes have long been known for supporting the shaft in the housing of the turbo charger, which comprise axial bearing surfaces or radial bearing surfaces, in particular. Reference can be made in an exemplary manner to a bearing bush of this type in the disclosure of US 4,240,678 A.
  • a deciding factor for such bearing bushes is its bearing function as an axial bearing on the one hand, and in particular as a radial bearing for the shaft of the turbo charger typically running very fast with several 1 ,000 rpm.
  • Such bushes can be designed in one part. Reference can be made in an exemplary manner to the structure in US 6,017,184 A to that end.
  • EP 1 998 009 B1 shows a structure, in which a divided bush is formed, for example. Said bush divided in two parts essentially has a similar structure, both of the radial bearing surfaces inside the two bushes as well as of the two axial bearing surfaces at in each case one front face of the bush.
  • US 9,140,185 B2 shows beneath the main object of the patent dealing with an asymmetric opening to achieve a locating pin to fix the bearing bush in the housing of a turbo charger further an axial bearing surface.
  • This axial bearing surface is shown e.g. in figure 2. It consists of thrust surfaces and wedge surfaces following one another in circumferential direction. Beneath those are additional grooves in radial direction ascending from the inner diameter to the outer diameter with two different shapes. The shape of the whole axial bearing surface is very complex and difficult to manufacture. Furthermore, there are a lot of edges producing a relatively high friction.
  • the international patent application WO 2014/055255 A1 is showing a journal bearing with an axial bearing surface.
  • the axial bearing surface consists of one planar surface with thrust producing means at the inner diameter of the ring- shaped surface.
  • Those thrust providing means do not extend to the outer diameter of the surface. They were used for providing oil as a lubricant to the planar surface.
  • the problem with this idea is the relatively big planar surface which increases the friction.
  • It is the object of the invention to provide an improved bearing bush for the shaft of a turbo charger which allows a good thrust capacity together with minimal friction and acceptable oil consumption.
  • the object is achieved by a bearing bush with the features in claim 1 .
  • the object is achieved by a turbo charger including such a bearing bush.
  • the bearing bush according to the invention comprises at its axial bearing surface an arrangement of a number of wedge surfaces following each other in circumferential direction.
  • Each of the wedge surfaces starts in one plane vertical to the central axis of the bearing bush. It decreases from that plane in axial direction along the circumferential direction, wherein each of the wedge surfaces ends on an edge of the adjacent wedge surface with a step in axial direction below the plane.
  • This complex three dimensional surface allows a design with a minimal number of edges. Therefore as much thrust as possible can be provided with minimal distribution of the flow of lubricant on and in the region of the axial bearing surface. A good bearing capacity together with a low friction is therefore achieved.
  • the axial bearing surface comprises an alternating arrangement of wedge surfaces and thrust surfaces with respect to the circumferential direction.
  • the thrust surfaces are co-planar in one plane. This plane is vertical to a central axis of the bearing bush.
  • Each of the wedge surfaces is starting adjacent to one edge of the thrust surfaces in the same plane. It then decreases in axial direction along the circumferential direction from that plane wherein the wedge surfaces end on the other edge of the next thrust surface in circumferential direction with a step in axial direction below the planar thrust surface.
  • the height of the step at the inner diameter of the axial bearing surface is bigger than on the outer diameter of the axial bearing surface.
  • the height at the inner diameter is at least three times, preferably more than five times higher than the height of the step at the outer diameter. This allows a good supply of oil as a lubricant from the inside of the bearing bush to the wedge surfaces. On the other hand it decreases the amount of lubricant flowing to the outer diameter and be spilled of by the rotating elements.
  • the wedge surface has a continuously curved shape. There are no edges in the wedge surface. The transition from the planar thrust surface into the wedge surface might be unsteady. The rest of the shape of the wedge surface is a three dimensional steady or rather continuously curved shape. The curve is preferably steady in radial as well as in circumferential direction. This allows a minimum resistance for the lubricant and enables good thrust producing capacities.
  • the axial bearing surface comprises at least three, preferably four, thrust surfaces. With such a relatively small number of thrust surfaces the friction between the axial bearing surface and its counterpart is reduced. Although in a preferred embodiment of this idea the overall area of the thrust surfaces is smaller than those of the wedge surfaces the carrying capacity of the axial bearing surface might be improved.
  • the relation between the thrust surfaces on the one hand and the wedge surfaces on the other hand might be about 1 :2, or smaller. This helps to reduce the friction on the one hand and enables through the special design of the wedge surfaces an acceptable carrying capacity of the axial bearing surface on the other hand.
  • edges between the thrust surfaces and the wedge surfaces run in radial direction.
  • the preferably ring shaped area of the axial bearing surface is therefore divided in radial segments of the wedge surfaces and the thrust surfaces following each another in the alternating arrangement.
  • a bearing bush has only one such axial bearing surface according to an improved embodiment of the idea the bearing bush is characterized by two axial bearing surfaces one of each of its two axial end faces.
  • the bearing bush comprises oil distributing means which are positioned on the inner circumferential surface of the bearing bush.
  • the bearing bush comprises at least one radial bearing surface on its inner surface comprising a groove for oil distribution.
  • a groove in at least one radial bearing surface on the inner circumference of the bearing bush allows oil to be distributed in axial direction from the center of the bearing bush through the radial bearing surface to the region of the axial bearing surface. Therefore the lubrication of the radial bearing surface as well as the axial bearing surface becomes possible.
  • the groove for oil distribution comprised in the radial bearing surface is a helical groove.
  • This helical groove allows, if it is positioned in the needed rotating direction a transportation of oil from the center of the bearing bush in axial direction to the axial bearing surface.
  • a turbo charger includes at least one compressor and a turbine on a common shaft.
  • the turbo charger comprises a housing with a central opening for receiving the shaft in at least one bearing bush.
  • This bearing bush is constructed according to one of the above mentioned embodiments with the axial bearing surface comprising wedge surfaces according to the above mentioned embodiments.
  • Such a turbo charger allows a minimal friction in its axial bearings as well as good thrust capacities with a low consumption of lubricant or rather oil.
  • Figure 1 a section through a part of a turbo charger according to the
  • Figure 2 a sectional illustration of the bearing bush inserted in the housing of the turbo charger
  • Figure 3 a three-dimensional view of a bearing bush according to the
  • Figure 4 a top view on an embodiment of an axial bearing surface according to one embodiment of the invention.
  • Figure 5 a three dimensional view on the axial bearing surface in a first embodiment according to the invention.
  • Figure 6 a three dimensional view on the axial bearing surface in a further embodiment according to the invention.
  • turbo charger 1 In the illustration of figure 1 , it can be discerned a detail of a turbo charger 1 as it can in particular be used as an exhaust gas turbo charger.
  • the core of the turbo charger 1 is formed by a turbine 2 and a compressor 3 on a common shaft 4 with said turbine 2, on the other end of the shaft 4.
  • the turbo charger 1 per se consists of a central housing 5, in which a bearing bush 6 is arranged for supporting the shaft 4.
  • the central housing 5 is then completed by an attached compressor housing 7 in the area of the compressor 3 and by a turbine housing 8 in the area of the turbine 2.
  • the central area of the housing 5 as well as the bearing bush 6 are of interest for radially supporting the shaft 4.
  • a bore 1 1 which is also referred to as oil drain bore 11 , thus comes to a rest over a stepped bore 12 in the housing 5 such that a pin 13, by means of being screwed into a thread of the stepped bore 12, comes to rest with its front end within the oil drain bore 1 1 .
  • the bearing bush 6 is fastened with clearance in axial direction A as well as in radial direction r. Therefore, the bearing bush 6 can still move within the central opening 9, but can, however, no longer move out of the central bore 9.
  • the bearing bush 6 per se has an outer surface 14 as well as an inner surface 15.
  • the outer surface 14 is analogous to the configuration of the central opening 9 outside the grooves 18, 19, 20, which it comprises and configures with the exception of at least one transition 28 toward the front faces with the same diameter d.
  • the housing 5 as it can in turn be seen from figure 2, furthermore comprises an oil supply channel 16 on the side opposing the stepped bore 12, via which lubricating oil, according to the arrow designated with 17 in the illustration of figure 1 , is supplied to the bearing bush 6.
  • the lubricating oil then centrally reaches the area of bearing bush 6.
  • This groove 18 running in the axial direction A also referred to longitudinal groove 18, extends over almost the entire length of the bearing bush 6. Parts of the outer surface 14 are merely located in the axial end areas which are not penetrated by the longitudinal groove 18, so that the longitudinal groove 18 does not open into the area of the front faces.
  • a groove that only runs in an axial direction could be conceivable.
  • Such a groove for example, could run oblique, V- shaped, zigzag, or also helically around the bearing bush 6.
  • essentially the same applies to this groove which is explained here accordingly by way of example of the axial longitudinal groove 18.
  • oil enters the area of the longitudinal groove 18 as well as the central groove 19 as a lubricant, according to the arrow designated with 17 in figure 1 .
  • Part of the oil flows through the longitudinal groove 18 to the two annular grooves 20 and distributes around the circumference of the bearing bush 6.
  • This oil then flows through the radial bores 22 into the area of the radial bearing surfaces 23 and there serves for the lubrication of the radial bearing surfaces 23.
  • the number of radial bores 22 in the area of each of the radial bearing surfaces 23 is ideally evenly distributed over the circumference of the bearing bush 6 or the annular groove 20 in order to ensure a uniform lubrication.
  • a helical groove 29 is arranged in each of the two radial bearing surfaces 23.
  • This helical groove winds along the entire radial bearing surface 23 and is configured in opposite rotational direction, as in the other axial bearing surfaces 23, in the one radial bearing surface 23, as can be taken from the illustration of figure 2.
  • the lubricating oil which has reached the area of the radial bearing surfaces 23 via the longitudinal groove 18 and the radial bores 22 is now distributed over the entire radial bearing surfaces 23 by this two helical grooves 29. This ensures a comparatively good lubrication over the entire surface of the radial bearing surfaces 23.
  • Said amount of oil may then flow out through the oil drain opening 1 1 and the pin 13, which has a longitudinally-running through bore 24, as this can be taken from figures 1 and 2.
  • a further part flows outwardly through the radial bearing surfaces 23 and enters the area of the axial bearing surfaces 21 on the front faces of the bearing bush 6. There, it lubricates the axial bearing surfaces 21 and then flows outwardly, as this can be seen in the illustration figure 3. It accumulates in an annular space 25 around the shaft 4 and flows, as this is indicated by the arrows denoted with 26, together with the oil passing through the through bore 24, via a drain opening 27 out of the housing 5.
  • this oil serving for the lubrication of the radial bearing surfaces 23 and the axial bearing surfaces 21 , a part of the oil also flows out through the annular central groove 19 along a gap between the outer surface 14 of the bearing bush 6 and the surface of the central opening 9. By said gap, the oil will also pass through the outside in axial direction a, i.e. in direction to the axial bearing surfaces 21 , respectively.
  • the axial bearing surface 30 has a ring shaped contour and consists of four thrust surfaces 31 and four wedge surfaces 32.
  • the thrust surfaces 31 and the wedge surfaces 32 are following each other in an alternating way around the circumference of the ring shaped axial bearing surface 30.
  • the thrust surfaces 31 are co-planar in one plane in which is vertical orientation to the central axis 10 of the bearing bush 6.
  • the lubricant or oil transported by the helical grooves 29 in the radial bearing surfaces 23 towards the end faces 21 of the bearing bush 6 distributes on the inner diameter d of the axial bearing surface 30, which is shown in figure 4.
  • the area of the co-planar thrust surfaces 31 is smaller than the area of the wedge surfaces 32, which also can be seen very good in the top view of figure 4.
  • the area of the thrust surfaces 31 will be less than 50%, especially less than 33% of the overall area of the axial bearing surface 30.
  • the area of the thrust surfaces 31 is about 25% wherein the area of the wedge surfaces 32 will be about 75% both of the overall area of the axial bearing surface 30..
  • each of the wedge surfaces 32 starts in the same plane as the co-planar thrust surfaces 31 . In the illustration of figure 5 this is always on a radial edge 33 of the thrust surface 31 in clockwise direction. Starting at this edge 33 the wedge surface 32 decreases in axial direction A from this plane vertical to the central axis 10. It decreases on the outer diameter of the ring-shaped axial bearing surface 30 only by a small amount. The amount it decreases on the inner diameter d of the ring-shaped axial bearing surface 30 is higher. This leads to a step 34 on the circumferential end of the wedge surface 32 in clockwise direction.
  • This step 34 which especially extends in radial direction R is a further edge 35 of each of the thrust surfaces 31 .
  • the axial bearing surface 30 as shown in figures 5 and 6 is rotating in anticlockwise direction against a counter surface (not shown) which might be e.g. planar.
  • This rotation of the bearing bush 6 in anticlockwise direction requires an axial bearing surface 30 on the other face end 21 of the bearing bush 6 which is mirrored with respect to the axial bearing surface 30 shown in the figures.
  • a height H at the inner diameter d of the step 34 is much higher than a height h on its outer diameter D. This leads to a three dimensionally curved shape of the wedge surface 32 which is continuously or rather steady, which means that there are no further edges in the shape of the wedge surface 32.
  • the way the wedge surface 32 is dimensioned with respect to the co-planar thrust surfaces is that on the inner diameter d the step 34 is much higher than on the outer diameter D.
  • the height H and the inner diameter is therefore about 3 to 8 times higher than the height h on the outer diameter D.
  • the height h is about 20 to 60 ⁇ , the height H 150 to 300 ⁇ .
  • the thrust surface 31 has the further radial edge 33 which is the edge where the adjacent next wedge surface 32 starts.
  • the combination of the thrust surface 31 , the wedge surface 32 and the step 34 therefore is positioned around the circumference of the ring-shaped axial bearing surface 30 four times in the preferred embodiment and all of their four thrust surfaces 31 as well as wedge surfaces 32 are shaped in the same size to achieve an even fragmentation of the whole area of the axial bearing surface 30.
  • Such an axial bearing surface 30 is positioned at both end faces 21 illustrated in figure 2.
  • the embodiment shown in figure 6 is designed without the thrust surfaces 31 .
  • Four wedge surfaces 32 are following each other in circumferential direction.
  • the step 34 is therefore arranged between the wedge surfaces 32 itself.
  • Each of the wedge surfaces 32 starts in the plane vertical to the central axis 10 of the bearing bush 6.
  • the design of its shape follows the same design principals as the wedge surfaces 32 mentioned before.
  • the surface therefore decreases along the circumferential direction starting in the plane and ending with the step 34 which leads the surface back to the plane. This enables almost the same functionality as in the embodiment mentioned above.
  • the friction can be deceased further.
  • the distribution of oil via the axially running longitudinal groove 18 and the helical grooves 29 in the radial bearing surfaces 23 is only one example of designing the bearing bush 6 with the axial bearing surface 30 according to the invention. It will be well understood for a person skilled in the art that the invention can also be used with other types of oil distribution and/or radial bearing surfaces.

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  • Engineering & Computer Science (AREA)
  • General Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • Chemical & Material Sciences (AREA)
  • Oil, Petroleum & Natural Gas (AREA)
  • Combustion & Propulsion (AREA)
  • Sliding-Contact Bearings (AREA)
  • Supercharger (AREA)

Abstract

L'invention concerne un coussinet de palier (6) destiné à un arbre d'un turbocompresseur, le coussinet ayant une face d'appui axiale annulaire (30) comprenant un certain nombre de faces de coin (32) se succédant dans la direction circonférentielle. Les faces de coin (32) commencent dans un plan vertical par rapport à l'axe central du coussinet de palier et diminuent à partir dudit plan dans la direction axiale dans la direction circonférentielle, chacune des faces de coin (32) se terminant sur le bord de la face de coin adjacente (32) avec une surépaisseur (34) en dessous du plan dans la direction axiale. Selon un autre mode de réalisation, les faces de coin sont en agencement alterné avec des faces de poussée. Dans ce cas, une surépaisseur est disposée entre une face de coin et un bord de la face de poussée adjacente.
PCT/EP2017/079541 2016-11-17 2017-11-17 Coussinet de palier de butée de tourillon de support d'arbre d'un turbocompresseur d'échappement WO2018091629A1 (fr)

Priority Applications (1)

Application Number Priority Date Filing Date Title
EP17801035.1A EP3542078A1 (fr) 2016-11-17 2017-11-17 Coussinet de palier de butée de tourillon de support d'arbre d'un turbocompresseur d'échappement

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE102016222625.8 2016-11-17
DE102016222625.8A DE102016222625A1 (de) 2016-11-17 2016-11-17 Lagerbuchse für eine Welle eines Turboladers

Publications (1)

Publication Number Publication Date
WO2018091629A1 true WO2018091629A1 (fr) 2018-05-24

Family

ID=60409287

Family Applications (1)

Application Number Title Priority Date Filing Date
PCT/EP2017/079541 WO2018091629A1 (fr) 2016-11-17 2017-11-17 Coussinet de palier de butée de tourillon de support d'arbre d'un turbocompresseur d'échappement

Country Status (3)

Country Link
EP (1) EP3542078A1 (fr)
DE (1) DE102016222625A1 (fr)
WO (1) WO2018091629A1 (fr)

Cited By (3)

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Publication number Priority date Publication date Assignee Title
EP3511532A1 (fr) * 2018-01-15 2019-07-17 Garrett Transportation I Inc. Turbocompresseur avec douille-palier et goupille de positionnement
WO2019155797A1 (fr) * 2018-02-08 2019-08-15 株式会社Ihi Structure de palier
JP2020051392A (ja) * 2018-09-28 2020-04-02 ダイハツ工業株式会社 排気ターボ過給機の軸受の構造

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DE102019001167A1 (de) * 2019-02-16 2020-08-20 Mtu Friedrichshafen Gmbh Abgasturbolader
US11719127B2 (en) * 2019-10-23 2023-08-08 Raytheon Technologies Corporation Oil drainback assembly for a bearing compartment of a gas turbine engine

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