WO2018200427A1 - Turbocompresseur à gaz d'échappement comprenant un bouclier thermique - Google Patents

Turbocompresseur à gaz d'échappement comprenant un bouclier thermique Download PDF

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Publication number
WO2018200427A1
WO2018200427A1 PCT/US2018/028988 US2018028988W WO2018200427A1 WO 2018200427 A1 WO2018200427 A1 WO 2018200427A1 US 2018028988 W US2018028988 W US 2018028988W WO 2018200427 A1 WO2018200427 A1 WO 2018200427A1
Authority
WO
WIPO (PCT)
Prior art keywords
exhaust gas
gas turbocharger
axis
heat shield
rotation
Prior art date
Legal status (The legal status 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 status listed.)
Ceased
Application number
PCT/US2018/028988
Other languages
English (en)
Inventor
Christoph Mueller
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
BorgWarner Inc
Original Assignee
BorgWarner Inc
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 BorgWarner Inc filed Critical BorgWarner Inc
Publication of WO2018200427A1 publication Critical patent/WO2018200427A1/fr
Anticipated expiration legal-status Critical
Ceased legal-status Critical Current

Links

Classifications

    • 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
    • F02C6/00—Plural gas-turbine plants; Combinations of gas-turbine plants with other apparatus; Adaptations of gas-turbine plants for special use
    • F02C6/04—Gas-turbine plants providing heated or pressurised working fluid for other apparatus, e.g. without mechanical power output
    • F02C6/10—Gas-turbine plants providing heated or pressurised working fluid for other apparatus, e.g. without mechanical power output supplying working fluid to a user, e.g. a chemical process, which returns working fluid to a turbine of the plant
    • F02C6/12—Turbochargers, i.e. plants for augmenting mechanical power output of internal-combustion piston engines by increase of charge 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
    • 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
    • F05D2240/10—Stators
    • F05D2240/15—Heat shield
    • 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
    • F05D2260/00—Function
    • F05D2260/20—Heat transfer, e.g. cooling
    • F05D2260/231—Preventing heat transfer

Definitions

  • the present invention relates to an exhaust gas turbocharger with a heat shield.
  • Exhaust gas turbochargers are known, for example, in which a turbine with a turbine wheel is driven by the exhaust gas flow of the internal combustion engine.
  • a compressor wheel which is arranged with a turbine wheel on a mutual rotor, compresses the fresh air taken in for the engine.
  • the air or oxygen amount, available to the engine for combustion is increased, which in turn leads to an increased output of the internal combustion engine.
  • Known turbochargers comprise a turbine housing with a turbine wheel arranged therein, a compressor housing with a compressor wheel arranged therein, and a bearing housing in which the rotor is mounted.
  • a heat shield is provided between the turbine housing and the bearing housing.
  • the heat shield may, for example, be rigidly clamped between the turbine housing and the bearing housing via a direct force fit.
  • the material costs for this type of incorporated heat shields are relatively high since high-precision materials must be used.
  • the heat shield may also be mounted between the bearing housing and the turbine housing via a force shunt.
  • the risk exists in this case that the heat shield will rotate during operation of the exhaust gas turbocharger and wear arises in the area of the heat shield over time. In the worst case, the entire exhaust gas turbocharger may fail.
  • the object of the present invention is consequently to provide an exhaust gas turbocharger with a heat shield which eliminates the risk of wear in the area of the heat shield and despite this is relatively inexpensive to produce.
  • the present invention relates to an exhaust gas turbocharger according to Claim 1.
  • the exhaust gas turbocharger comprises a turbine housing, a bearing housing, a rotor which is rotatably mounted in the bearing housing and defines an axis of rotation of the exhaust gas turbocharger, and a heat shield which is arranged between the turbine housing and the bearing housing.
  • the heat shield has a central hole for positioning in the exhaust gas turbocharger; the center of the hole is positioned eccentric to the axis of rotation to prevent a rotation of the heat shield. Due to this type of configuration and arrangement of the heat shield, the heat shield does not have to be rigidly clamped between the bearing housing and the turbine housing. A fixing of the heat shield via a direct force fit is not necessary, for which reason a less expensive material may be selected for the heat shield. In spite of this, a rotation of the heat shield is prevented via the eccentric positioning of the hole, by which means the risk of wear in this area is eliminated.
  • the heat shield may, for example, be configured as pot- shaped.
  • a center axis of the heat shield may coincide with the axis of rotation of the exhaust gas turbocharger.
  • the center of the bore hold may have a distance dl to the central axis of at least 0.5 mm, preferably from 0.5 mm to 3.5 mm, in particular from 1 mm to 2 mm.
  • the bearing housing may have an axially extending dome extension. The dome extension may be arranged at least partially in the hole.
  • the dome extension may be arranged around the axis of rotation of the turbocharger, wherein an outer surface of the dome extension may describe a cylinder with a cylinder axis which is arranged eccentric to the axis of rotation.
  • An inner surface of the dome extension may describe a cylinder or a cone which is arranged concentric to the axis of rotation.
  • the cylinder axis of the outer surface may, for example, have a distance d2 to the axis of rotation of at least 0.5 mm, preferably 0.5 to 3.5 mm, in particular from 1 mm to 2 mm.
  • the distances dl, d2 of the cylinder axis of the outer surface of the dome extension to axis of rotation 500 and of the center of the hole to the axis of rotation may be aligned to one another, for example, to be approximately the same.
  • the heat shield may have a plurality of tabs in a radially outer area.
  • the plurality of tabs may comprise at least one flat tab and a least one curved tab.
  • the configuration with flat and curved tabs has the advantage that the heat shield may contact a flat lateral surface of the bearing housing and despite that a spring effect is still achieved at the same time due to the curved tab(s), so that there is a biasing of the heat shield (due to the turbine housing) in the installed state between the bearing housing and the turbine housing.
  • a recess concentric to the axis of rotation may be provided in a side wall of the bearing housing, in which recess at least the flat tabs may be arranged and may contact the side wall. An interaction between at least the flat tabs with an inner wall of the recess prevents a rotation of the heat shield.
  • the turbine housing may have a step concentric to the axis of rotation, in which area at least one part of the heat shield may be arranged, wherein an interaction of the tabs with the turbine housing in the area of the step prevents a rotation of the heat shield.
  • notches may be provided between the tabs.
  • the notches are advantageous for manufacturing and reduce the risk of cracking during deep drawing of the heat shield.
  • two, three, four, or more flat tabs may be provided.
  • two, three, four, or more curved tabs may be provided.
  • the flat tabs and the curved tabs may be arranged distributed uniformly and alternatingly along the periphery of the heat shield.
  • the curved tabs are curved in the direction toward the turbine housing and away from the bearing housing.
  • the curved tabs may be curved in the direction toward the bearing housing and away from the turbine housing.
  • Figure 1 shows a section of a cutaway view through one embodiment of the exhaust gas turbocharger according to the invention
  • Figure 2 shows a cutaway view of the heat shield from the embodiment of the exhaust gas turbocharger according to the invention from Figure 1;
  • FIG 3 shows a top view of the heat shield from the embodiment of the exhaust gas turbocharger according to the invention from Figure 1.
  • radial surfaces/lateral surfaces refer to surfaces that are arranged in the planes that are perpendicular to axis of rotation 500 of the exhaust gas turbocharger.
  • FIG. 1 shows a section of cutaway view of one embodiment of the exhaust gas turbocharger according to the invention.
  • the exhaust gas turbocharger comprises a turbine housing 200, a bearing housing 300, and a rotor 400 which is rotatably mounted in bearing housing 300 and defines an axis of rotation 500 of the exhaust gas turbocharger.
  • Rotor 400 comprises on a first end a turbine wheel 600 which is arranged in turbine housing 200, and on a second end a compressor wheel which is arranged in a compressor housing (not shown in the figures).
  • the exhaust gas turbocharger additionally has a heat shield 100 which is arranged between turbine housing 200 and bearing housing 300.
  • Heat shield 100 has a central hole 110 for positioning in the exhaust gas turbocharger; the center 112 of the hole is positioned eccentric to axis of rotation 500 to prevent a rotation of heat shield 100 during operation of the exhaust gas turbocharger. Due to this type of configuration and arrangement of heat shield 100 in the exhaust gas turbocharger, heat shield 100 does not have to be rigidly clamped between bearing housing 300 and turbine housing 200. A fixing of heat shield 100 via a direct force fit is not necessary, for which reason a less expensive material may be selected for heat shield 100. In spite of this, a rotation of heat shield 100 is prevented via the eccentric positioning of hole 110. Thus, the risk of wear of heat shield 100, and thus the risk of exhaust gas turbocharger failing, is eliminated.
  • heat shield 100 is configured approximately pot shaped in the embodiment depicted.
  • Pot-shaped heat shield 100 has a central bottom area 120 extending approximately radially, a first wall area 130 extending approximately axially, a second wall area 140 extending approximately conically, and a tab area 150 lying radially outward.
  • Tab area 150 is also particularly clear in Figure 3, which shows a top view of heat shield 100.
  • a center axis 160 (see e.g. Figure 2) of heat shield 100 coincides in the mounted state of heat shield 100 with axis of rotation 500 (see e.g. Figure 1) of the exhaust gas turbocharger.
  • the inscribed axis includes the reference numerals for axis of rotation 500 and also for center axis 160.
  • Center axis 160 thereby describes that axis to which heat shield 100 is rotationally symmetrical (if central hole 110 and, depending on configuration, tab area 150 were to be left out of consideration).
  • Hole 110 is, in contrast, not arranged in the center of heat shield 100.
  • Center 112 of hole 110 may, for example, have a distance dl (see Figure 2 and Figure 3) to center axis 160 of at least 0.5 mm, preferably from 0.5 mm to 3.5 mm, in particular from 1 mm to 2 mm.
  • bearing housing 300 of the exhaust gas turbocharger additionally has an axially extending dome extension 310.
  • Dome extension 310 is positioned at least partially in hole 110 so that heat shield 100 is arranged virtually on dome extension 310 and is supported by dome extension 310.
  • Dome extension 310 is arranged about axis of rotation 500 of the turbocharger.
  • An outer surface 312 of dome extension 310 describes a cylinder with a cylinder axis 314, wherein cylinder axis 314 is arranged eccentric to axis of rotation 500.
  • an inner surface 316 of dome extension 310 describes a cylinder or a cone (as in the example depicted in Figure 1), which is arranged concentric to axis of rotation 500 of the exhaust gas turbocharger.
  • the eccentricity of outer surface 312 of dome extension 310 is defined over a distance d2 of cylinder axis 314 to axis of rotation 500 of the exhaust gas turbocharger.
  • Cylinder axis 314 of outer surface 312 may, for example, have a distance d2 (see Figure 1) to axis of rotation 500 of at least 0.5 mm, preferably 0.5 to 3.5 mm, in particular from 1 mm to 2 mm.
  • distances dl, d2 of cylinder axis 314 of outer surface 312 of dome extension 310 to axis of rotation 500 and of center 112 of hole 110 to axis of rotation 500 may be aligned to one another.
  • Distances dl and d2 may, for example, be approximately the same size.
  • center 112 of hole 110 of heat shield 100 lies on cylinder axis 314 of the cylinder which is described by outer surface 312 of dome extension 310.
  • heat shield 100 has a plurality of tabs 152, 154 (see Figure 3).
  • the plurality of tabs 152, 154 thereby comprises, in the embodiment shown in Figure 3, two flat tabs 152 and two curved tabs 154.
  • "Flat” means in conjunction with flat tabs 152, that they extend in a radial direction to axis of rotation 500 of the turbocharger so that straight tabs 152 may lie flat on a radial lateral surface of bearing housing 300.
  • curved tabs 154 have an extension radially outward, which does not extend parallel to flat tabs 152.
  • Tab area 150 may also have only one, or three, four, or more flat tabs 152. Likewise, only one, or three, four, or more curved tabs 154 may also be provided.
  • an equal number of flat and curved tabs 152, 154 may be provided.
  • the number of flat tabs 152 may also differ from the number of curved tabs 154.
  • Flat tabs 152 and curved tabs 154 may be arranged (as shown in Figure 3) distributed uniformly and altematingly along the periphery of heat shield 100.
  • curved tabs 154 and flat tabs 152 may also differ in size (e.g. with respect to the angular area that each tab covers) and be arranged distributed non-uniformly and randomly (not necessarily alternating).
  • heat shield 100 with flat and curved tabs 152, 154 has the advantage that heat shield 100 may contact a flat lateral surface of bearing housing 300 and despite that a spring effect is still achieved at the same time due to curved tab(s) 154, so that there is a biasing of heat shield 100 (due to the turbine housing) in the installed state between bearing housing 300 and turbine housing 200.
  • Notches 156 are provided between tabs 152, 154. Notches 156 are advantageous for manufacturing and reduce the risk of cracking during the deep drawing of heat shield 100.
  • curved tabs 154 are curved in the direction toward turbine housing 200 and away from bearing housing 300.
  • tabs 154 may also be curved in the direction toward bearing housing 300 and away from turbine housing 200.
  • a recess 322, concentric to axis of rotation 500, is provided in one lateral wall 320 of bearing housing 300. At least flat tabs 152 are arranged in recess 322 and contact lateral wall 320.
  • Inner wall 324 is the annular inner wall within recess 322, which delimits recess 322 radially outward.
  • flat tabs 152 and at least part of curved tabs 154 are arranged in recess 322 (see Figure 1).
  • Flat tabs 152 thereby lie flat on side wall 320 of bearing housing 300 extending in this area essentially in the radial direction in recess 322, whereas curved tabs 154 are only in line contact with this side wall 320 and the radially outer ends of curved tabs 154 project out beyond recess 322.
  • curved tabs 154 arrive in contact with a radial wall 210 of turbine housing 200 during assembly of the exhaust gas turbocharger so that a biasing of heat shield 100 occurs between turbine housing 200 and bearing housing 300.
  • forces, which would cause a rotation, act on heat shield 100 there is a contact of the outer areas of at least flat tabs 152 with inner wall 324 of recess 322 due to eccentric hole 110, via which heat shield 100 is arranged on dome extension 310 (likewise eccentrically configured). Due to this contact, a rotation of heat shield 100 is prevented.
  • turbine housing 200 may have a step, concentric to axis of rotation 500, in which area at least a part of heat shield 100 is arranged, in particular tab area 150. An interaction of tabs 152, 154 with turbine housing 200 in the area of the step then prevents a rotation of heat shield 100.
  • the step thereby fulfils both the task of recess 322 in bearing housing 300 from the first embodiment shown in the figures, and simultaneously functions as a stop surface for curved tabs 154 in order to facilitate a biasing of heat shield 100 between bearing housing 300 and turbine housing 200.
  • Flat tabs 152 thereby lie, as in the first embodiment, again flat on a radial side wall 320 of bearing housing 300, only not in a recess 322 of bearing housing 300, which may be omitted in this embodiment.
  • An exhaust gas turbocharger comprising
  • a rotor (400) which is rotatably mounted in the bearing housing (300) and defines an axis of rotation (500) of the exhaust gas turbocharger; and a heat shield (100) which is arranged between the turbine housing (200) and the bearing housing (300),
  • the heat shield (100) has a central hole (110) for positioning in the exhaust gas turbocharger; the center (112) of the hole is positioned eccentric to the axis of rotation (500) to prevent a rotation of the heat shield (100).
  • the exhaust gas turbocharger according to Embodiment 1 characterized that the heat shield (100) is configured as pot shaped.
  • the exhaust gas turbocharger according to Embodiment 1 or Embodiment 2 characterized in that a center axis (160) of the heat shield (100) coincides with the axis of rotation (500) of the exhaust gas turbocharger.
  • the exhaust gas turbocharger according to Embodiment 3 characterized in that the center (112) of the hold (110) has a distance (dl) to the center axis (160) of at least 0.5 mm, preferably 0.5 to 3.5 mm, in particular from 1 mm to 2 mm.
  • the exhaust gas turbocharger according to any one of the preceding embodiments characterized in that the bearing housing (300) has an axially extending dome extension (310).
  • the exhaust gas turbocharger according to Embodiment 5 characterized in that the dome extension (310) is arranged at least partially in the hole (110).
  • an inner surface (316) of the dome extension (310) describes a cylinder or a cone which is arranged concentric to the axis of rotation (500).
  • the exhaust gas turbocharger according to any one of Embodiments 7 through 9, characterized in that the distances (dl, d2) of the cylinder axis (314) of the outer surface (312) of the dome extension (310) to the axis of rotation (500) and of the center (112) of the hole (110) to the axis of rotation (500) are aligned with one another, in particular, are approximately the same size.
  • the exhaust gas turbocharger according to any one of the preceding embodiments, characterized in that the heat shield (100) has a plurality of tabs (152, 154) in a radially outer area (150).
  • the exhaust gas turbocharger according to any one of Embodiments 12 through 17, characterized in that the flat tabs (152) and the curved tabs (154) are arranged distributed uniformly and alternatingly along the periphery of the heat shield (100).
  • the exhaust gas turbocharger according to any one of Embodiments 12 through 18, characterized in that the curved tabs (154) are curved in the direction toward turbine housing (200) and away from bearing housing (300).
  • the exhaust gas turbocharger according to any one of Embodiments 12 through 18, characterized in that the curved tabs (154) are curved in the direction toward bearing housing (300) and away from turbine housing (200).

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  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Chemical Kinetics & Catalysis (AREA)
  • General Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Supercharger (AREA)

Abstract

La présente invention concerne un turbocompresseur à gaz d'échappement comprenant un carter de turbine (200), un boîtier de palier (300), un rotor (400) monté rotatif dans le boîtier de palier et définissant un axe de rotation (500) du turbocompresseur à gaz d'échappement, et un bouclier thermique (100) qui est disposé entre le carter de turbine et le boîtier de palier. Le bouclier thermique comporte un trou central (110) pour le positionnement dans le turbocompresseur à gaz d'échappement ; le centre du trou est positionné de manière excentrique par rapport à l'axe de rotation pour empêcher une rotation du bouclier thermique.
PCT/US2018/028988 2017-04-25 2018-04-24 Turbocompresseur à gaz d'échappement comprenant un bouclier thermique Ceased WO2018200427A1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE102017206900 2017-04-25
DE102017206900.7 2017-04-25

Publications (1)

Publication Number Publication Date
WO2018200427A1 true WO2018200427A1 (fr) 2018-11-01

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ID=62117142

Family Applications (1)

Application Number Title Priority Date Filing Date
PCT/US2018/028988 Ceased WO2018200427A1 (fr) 2017-04-25 2018-04-24 Turbocompresseur à gaz d'échappement comprenant un bouclier thermique

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WO (1) WO2018200427A1 (fr)

Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2006046892A1 (fr) * 2004-10-28 2006-05-04 Volvo Lastvagnar Ab Turbocompresseur pour moteur a combustion interne comprenant un bouclier thermique
EP1785613A2 (fr) * 2005-10-21 2007-05-16 Mitsubishi Heavy Industries, Ltd. Turbocompresseur à gaz d'échappement
EP2098703A1 (fr) * 2008-03-06 2009-09-09 Honeywell International Inc. Ensemble turbochargeur doté d'agencement centrant l'écran thermique
DE102015113393A1 (de) * 2015-08-13 2017-02-16 Ihi Charging Systems International Gmbh Abgasturbolader

Patent Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2006046892A1 (fr) * 2004-10-28 2006-05-04 Volvo Lastvagnar Ab Turbocompresseur pour moteur a combustion interne comprenant un bouclier thermique
EP1785613A2 (fr) * 2005-10-21 2007-05-16 Mitsubishi Heavy Industries, Ltd. Turbocompresseur à gaz d'échappement
EP2098703A1 (fr) * 2008-03-06 2009-09-09 Honeywell International Inc. Ensemble turbochargeur doté d'agencement centrant l'écran thermique
DE102015113393A1 (de) * 2015-08-13 2017-02-16 Ihi Charging Systems International Gmbh Abgasturbolader

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