EP3548705B1 - Turbochargeur - Google Patents

Turbochargeur Download PDF

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Publication number
EP3548705B1
EP3548705B1 EP17768032.9A EP17768032A EP3548705B1 EP 3548705 B1 EP3548705 B1 EP 3548705B1 EP 17768032 A EP17768032 A EP 17768032A EP 3548705 B1 EP3548705 B1 EP 3548705B1
Authority
EP
European Patent Office
Prior art keywords
flange
turbine
housing
bearing housing
nozzle ring
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.)
Active
Application number
EP17768032.9A
Other languages
German (de)
English (en)
Other versions
EP3548705A1 (fr
Inventor
Björn Hossbach
Tobias Weisbrod
Paul Schorer
Lukas BOZEK
Jan REZANINA
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.)
MAN Energy Solutions SE
Original Assignee
MAN Energy Solutions SE
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 MAN Energy Solutions SE filed Critical MAN Energy Solutions SE
Publication of EP3548705A1 publication Critical patent/EP3548705A1/fr
Application granted granted Critical
Publication of EP3548705B1 publication Critical patent/EP3548705B1/fr
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Classifications

    • 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
    • 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
    • F01D25/24—Casings; Casing parts, e.g. diaphragms, casing fastenings
    • F01D25/243—Flange connections; Bolting arrangements
    • 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
    • F01D9/00—Stators
    • F01D9/02—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles
    • F01D9/04—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector
    • F01D9/045—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector for radial flow machines or engines
    • 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
    • F02B37/00—Engines characterised by provision of pumps driven at least for part of the time by exhaust
    • 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
    • F01D25/24—Casings; Casing parts, e.g. diaphragms, casing fastenings
    • F01D25/246—Fastening of diaphragms or stator-rings
    • 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

Definitions

  • the invention relates to a turbocharger.
  • a turbocharger has a turbine in which a first medium is expanded. Furthermore, a turbocharger has a compressor in which a second medium is compressed using the energy obtained in the turbine when the first medium is expanded.
  • the turbine of the turbocharger has a turbine housing and a turbine rotor.
  • the compressor of the turbocharger has a compressor housing and a compressor rotor.
  • a bearing housing is positioned between the turbine housing of the turbine and the compressor housing of the compressor, the bearing housing being connected on the one hand to the turbine housing and on the other hand to the compressor housing.
  • a shaft via which the turbine rotor is coupled to the compressor rotor is mounted in the bearing housing.
  • the turbine housing of the turbine namely a so-called turbine inflow housing
  • the bearing housing are connected to one another via a fastening device, which is preferably designed as a clamping claw.
  • a fastening device preferably designed as a clamping claw
  • Such a fastening device is mounted with a first section of the same on a flange of the turbine housing via fastening means and covers a flange of the bearing housing at least in sections with a second section.
  • the assembly or assembly of the bearing housing and the turbine housing is braced by means of such a fastening device, in particular with clamping of a flange of a nozzle ring and possibly a flange of a heat shield between the flange of the turbine housing and the flange of the bearing housing.
  • the turbine housing is filled with the first medium to be expanded, in particular with exhaust gas to be expanded.
  • the turbine inflow housing of the turbine housing directs the exhaust gas towards the turbine rotor.
  • In the turbine inflow housing there is an overpressure in relation to the environment, which is reduced in the turbine while generating energy during the expansion of the first medium. Leakage can occur in the area of the connection point between the turbine housing or the turbine inflow housing and the bearing housing, so that the first medium to be expanded in the turbine can reach the environment via the connection area between the turbine housing and the bearing housing. This is a disadvantage.
  • the tension between the turbine housing or the turbine inflow housing and the bearing housing is increased in practice, in particular by means of higher tightening torques for the fastening means by which the fastening device, which is preferably designed as a clamping claw, is mounted on the turbine housing.
  • This also increases a clamping force between the fastening device and the bearing housing. A contact point between the bearing housing and the fastening device is exposed to high relative movements as a result of the different thermal expansions of the bearing housing and turbine housing or turbine inflow housing.
  • DE 102 97 203 T5 discloses a turbocharger having a compressor, a turbine and a bearing housing.
  • a flange is disclosed in the area of the turbine which is formed at one end of a piston of the turbine. This flange has slots to receive guide vanes.
  • the piston is a sliding piston and can therefore be moved in a sliding manner. The relative position of the flange changes depending on the movement of the piston.
  • the present invention is based on the object of creating a turbocharger with a novel flange connection.
  • a turbocharger according to claim 1. Thereafter, between the flange of the bearing housing and the flange of the turbine housing, between the flange of the bearing housing and the flange of the heat shield, which has a recess, a spring element is positioned in the recess of the flange of the heat shield, which the flange of the heat shield axially against the Flange of the nozzle ring and so presses the flange of the nozzle ring axially against the flange of the turbine housing.
  • This also enables a particularly advantageous sealing of the connection point between the turbine housing or the turbine inflow housing and the bearing housing. The risk is reduced that the medium to be expanded in the turbine gets into the environment via the connection area between the turbine housing and the bearing housing.
  • the invention relates to a turbocharger.
  • a turbocharger has a turbine for expanding a first medium, in particular for expanding exhaust gas from an internal combustion engine. Furthermore, a turbocharger has a compressor for compressing a second medium, in particular charge air, to be precise using the energy obtained in the turbine when the first medium is expanded.
  • the turbine has a turbine housing and a turbine rotor.
  • the compressor has a compressor housing and a compressor rotor. The compressor rotor is coupled to the turbine rotor via a shaft that is journalled in a bearing housing, the bearing housing being positioned between the turbine housing and the compressor housing and being connected to both the turbine housing and the compressor housing.
  • the invention now relates to such details of a turbocharger which connect the turbine housing of a turbine, which is preferably designed as a radial turbine and bearing housings of a turbocharger relate to.
  • a turbocharger which connect the turbine housing of a turbine, which is preferably designed as a radial turbine and bearing housings of a turbocharger relate to.
  • Figs. 1 to 3 different examples of turbochargers described, wherein Figs. 1 to 3 each show corresponding sections from a turbocharger in the area of the connection between the turbine housing and the bearing housing.
  • FIG. 1 An example of a turbocharger not according to the invention is shown Fig. 1 , where in Fig. 1 the connection point between a turbine housing, namely a turbine inflow housing 1 of the turbine housing, and a bearing housing 2 of the exhaust gas turbocharger is shown. Also shows Fig. 1 a nozzle ring 3, a heat shield 4 and a so-called insert 11.
  • the turbine inflow housing 1 is connected to the bearing housing 2 via a fastening device 5 in such a way that the fastening device 5 is mounted on a flange 6 of the turbine inflow housing 1 with a first section 7, namely via several fastening means 8, and that the fastening device 5 with a second section 9 covers a flange 10 of the bearing housing 2 at least in sections.
  • the fastening device 5 is also referred to as a clamping claw and clamps the turbine inflow housing 1 and bearing housing 2 together.
  • the fastening device 5 can be segmented as seen in the circumferential direction.
  • each fastening means 8 comprises a threaded screw 8a screwed into the flange 6 of the turbine inflow housing 1 and a nut 8b engaging the other end of the threaded screw 8a, whereby by tightening the nuts 8b, a defined pretensioning force is exerted on the turbine inflow housing 1 and on the fastening device 5 Bearing housing 10 can be applied.
  • nozzle ring 3 of the turbine is installed in such a way that a flange 13 of the nozzle ring 3 is based on a Flow channel 24 of the turbine, in the region of which the nozzle ring 3 is arranged, is positioned on a side of the flow channel 24 opposite the flange 6 of the turbine inflow housing 1 and thus the flange 10 of the bearing housing 2.
  • the flange 13 of the nozzle ring 3 can be attached to a section 14 of the turbine inflow housing 1, which, like the flange 13 of the nozzle ring 3, is on the opposite side in relation to the flow channel 24 in the bracing area between the flanges 6, 10 of the turbine inflow housing 1 and bearing housing 2 of the flow channel 24 is positioned.
  • the flange 13 of the nozzle ring 3 engages at least in sections in a recess 15 of this section 14 of the turbine inflow housing 1, the flange 13 of the nozzle ring 3 seen in the radial direction with one end at a boundary of this recess 15 of the section 14 of the turbine inflow housing 1 and at one end opposite end on the insert 11 is supported.
  • an elastic spring element 16 is received, which presses against the flange 13 of the nozzle ring 3 in the axial direction.
  • FIG. 2 Another example of a turbocharger not according to the invention is shown Fig. 2 . Also in Fig. 2 the flange 13 of the nozzle ring 3 is positioned on a side of the flow channel 24 of the turbine opposite the bracing area of the flanges 6, 10 of the turbine inflow housing 1 and bearing housing 2.
  • Fig. 2 differs from the example of Fig. 1 by the fact that in Fig. 2 the flange 13 of the nozzle ring 3 is mounted on the section 14 of the bearing housing 1 via a fastening device designed as a feather key 17, which is received in a corresponding recess 18 of the section 14 of the bearing housing 1. Also in Fig. 2 the flange 13 of the nozzle ring 3 protrudes at least in sections into the recess 18 of the section 4 of the turbine inflow housing 1.
  • FIG. 2 Another difference of the example of the Fig. 2 compared to the example of Fig. 1 is that in Fig. 2 the flange 12 of the heat shield 4 is not clamped between the flanges 6, 10 of the turbine inflow housing 1 and the bearing housing 2. Rather, comes in Fig. 2 the flange 10 of the bearing housing 2 directly on the flange 6 of the turbine inflow housing 1 to the plant.
  • a sealing element 19 can also be positioned, which can be a preferably metallic sealing ring in the form of an O-ring or C-ring.
  • the sealing element 19 can also be made of graphite.
  • the sealing element 19 is in a recess 20 of the flange 6 of the turbine inflow housing 1 and seals, in particular in the axial direction, between sealing surfaces of the flanges 6, 10 of the turbine inflow housing 1 and the bearing housing 2 that lie against one another.
  • the nozzle ring 3 is also possible to design the nozzle ring 3 as an integral part of the insert 11. In this case, the nozzle ring 3 does not have to be attached separately to the turbine inflow housing 1. Rather, the insert 11, which provides the nozzle ring 3 as an integral assembly, then takes over the reception of the same in the turbine.
  • Fig. 3 shows an embodiment of a turbocharger according to the invention.
  • the flange 13 of the nozzle ring 3 and the flange 12 of the heat shield 4 both clamped between the flange 10 of the bearing housing 2 and the flange 6 of the turbine inflow housing 1, namely via the clamping device applied via the fastening device 5 Clamping force.
  • a spring element 22 is positioned between the flange 10 of the bearing housing 2 and the flange 6 of the turbine housing 1 and presses the flange 13 of the nozzle ring 3 axially against the flange 6 of the turbine inflow housing 1.
  • this spring element 22 between the flange 10 of the bearing housing 2 and the Flange 12 of the heat shield 4 is arranged so that the spring element 22 presses the flange 12 of the heat shield 4 against the flange 13 of the nozzle ring 3 and thus the flange 13 of the nozzle ring 3 against the flange 6 of the turbine inflow housing 1.
  • the spring element 22 is supported on the one hand on the flange 10 of the bearing housing 2 and on the other hand on the flange 12 of the heat shield 4. As already stated, the spring element 22 presses the flange 13 of the nozzle ring 3 in the axial direction against the flange 6 of the turbine inflow housing 1, whereby, even if these assemblies are subject to different thermal expansion during operation, a good sealing effect is always achieved in the connection area between the bearing housing 2 and the turbine inflow housing 1 is guaranteed, so that there is no risk of exhaust gas flowing out into the environment via this connection area.
  • clamping devices such as clamping claws
  • the flange of the bearing housing is screwed directly to the turbine inflow housing. This results in a clear sealing surface between flange 10 and flange 6, over which the entire force flow of the fastening elements 8 runs.
  • the heat shield and nozzle ring can then be clamped via a spring element 22.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Supercharger (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)

Claims (2)

  1. Turbocompresseur,
    comportant une turbine pour l'expansion d'un premier milieu,
    comportant un compresseur pour comprimer un deuxième milieu en utilisant l'énergie obtenue dans la turbine lorsque le premier milieu est détendu, dans lequel la turbine présente un carter de turbine (1) avec une bride (6) et un rotor de turbine,
    dans lequel le compresseur présente un carter de compresseur et un rotor de compresseur couplé via un arbre avec le rotor de turbine,
    comportant un logement de palier (2) dans lequel l'arbre est monté, dans lequel le logement de palier (2) présente une bride (10),
    comportant un dispositif de fixation (5) qui présente une première section (7) et une deuxième section (9),
    dans lequel le carter de turbine (1) et le carter de compresseur sont respectivement reliés au carter de palier (2) disposé entre eux,
    dans lequel le carter de turbine (1) et le carter de palier (2) via le dispositif de fixation (5) sont reliés de telle sorte que le dispositif de fixation soit monté sur la bride (6) du carter de turbine (1) avec le premier tronçon (7) et recouvre la bride (10) du logement de palier (2) au moins par tronçons avec le second tronçon (9),
    comportant une bague de buse (3) ayant une bride (13),
    comportant un écran thermique (14) ayant une bride (12),
    dans lequel entre la bride (6) du carter de turbine (1) et la bride (10) du logement de palier (2) la bride (13) de la bague de buse (3) et la bride (12) de l'écran thermique (14) sont serrées,
    caractérisé en ce que
    entre la bride (10) du logement de palier (2) et la bride (6) du carter de turbine (1), entre la bride (10) du carter de palier (2) et la bride (12) de l'écran thermique (4), qui présente un évidement, dans l'évidement de la bride (12) de l'écran thermique (4) un élément de ressort (22) est positionné, qui presse axialement la bride (12) de l'écran thermique (14) axialement contre la bride (13) de l'anneau de buse (3) et donc la bride (13) de l'anneau de buse (3) axialement contre la bride (6) du carter de turbine (1).
  2. Turbocompresseur selon la revendication 1, caractérisé en ce que l'élément de ressort (22) prend appui d'une part sur la bride (12) de l'écran thermique (4) et d'autre part sur la bride (10) du logement de palier (2) .
EP17768032.9A 2016-12-01 2017-08-31 Turbochargeur Active EP3548705B1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE102016123250 2016-12-01
PCT/EP2017/071862 WO2018099619A1 (fr) 2016-12-01 2017-08-31 Tubocompresseur

Publications (2)

Publication Number Publication Date
EP3548705A1 EP3548705A1 (fr) 2019-10-09
EP3548705B1 true EP3548705B1 (fr) 2021-03-03

Family

ID=59887214

Family Applications (1)

Application Number Title Priority Date Filing Date
EP17768032.9A Active EP3548705B1 (fr) 2016-12-01 2017-08-31 Turbochargeur

Country Status (6)

Country Link
US (1) US20190301358A1 (fr)
EP (1) EP3548705B1 (fr)
JP (1) JP6858856B2 (fr)
KR (1) KR20190086568A (fr)
CN (1) CN110023589A (fr)
WO (1) WO2018099619A1 (fr)

Families Citing this family (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE102017215539A1 (de) * 2017-09-05 2019-03-07 Man Diesel & Turbo Se Turbolader
DE102017127628A1 (de) * 2017-11-22 2019-05-23 Man Energy Solutions Se Turbine und Turbolader
JP7286017B2 (ja) * 2020-06-04 2023-06-02 三菱重工マリンマシナリ株式会社 タービンハウジングおよび過給機
DE102020213026A1 (de) 2020-10-15 2022-04-21 BMTS Technology GmbH & Co. KG Abgasturbolader mit variabler Turbinengeometrie
DE102021113581A1 (de) 2021-05-26 2022-12-01 Rolls-Royce Solutions GmbH Turbinenanordnung für einen Abgasturbolader
WO2023228467A1 (fr) * 2022-05-25 2023-11-30 株式会社Ihi Turbine et compresseur de suralimentation

Citations (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE10297203T5 (de) * 2001-09-10 2004-08-12 Leavesley, Malcolm George, Bow Turbolader
DE102013002605A1 (de) * 2013-02-15 2014-08-21 Man Diesel & Turbo Se Turbolader und Axiallagerscheibe für einen Turbolader

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Publication number Priority date Publication date Assignee Title
EP0024275A1 (fr) * 1979-08-15 1981-03-04 BBC Aktiengesellschaft Brown, Boveri & Cie. Fixation des anneaux de tuyères
JPH0652048B2 (ja) * 1984-10-04 1994-07-06 三菱重工業株式会社 輻流タ−ボ機械
JPH01134025A (ja) * 1987-11-17 1989-05-26 Honda Motor Co Ltd ターボチャージャのハウジング構造
DE10256418A1 (de) * 2002-12-02 2004-06-09 Abb Turbo Systems Ag Abgasturbinengehäuse
EP1988261A1 (fr) * 2007-05-04 2008-11-05 ABB Turbo Systems AG Joint de boîtier
JP5082991B2 (ja) * 2008-03-31 2012-11-28 株式会社Ｉｈｉ 過給機
JP5151883B2 (ja) * 2008-10-03 2013-02-27 株式会社Ｉｈｉ ターボチャージャ
DE102009024151A1 (de) * 2009-06-05 2010-12-09 Daimler Ag Turbinengehäuse für einen Abgasturbolader sowie Abgasturbolader
JP2013124650A (ja) * 2011-12-16 2013-06-24 Ihi Corp 可変ノズルユニット及び可変容量型過給機
JP5966786B2 (ja) * 2012-09-10 2016-08-10 株式会社Ihi 可変容量型過給機
EP2960460A4 (fr) * 2013-02-21 2016-03-09 Mitsubishi Heavy Ind Ltd Turbocompresseur à géométrie variable
WO2016139799A1 (fr) * 2015-03-05 2016-09-09 三菱重工業株式会社 Turbocompresseur
JP6394791B2 (ja) * 2015-03-31 2018-09-26 株式会社Ihi 可変容量型過給機

Patent Citations (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE10297203T5 (de) * 2001-09-10 2004-08-12 Leavesley, Malcolm George, Bow Turbolader
DE102013002605A1 (de) * 2013-02-15 2014-08-21 Man Diesel & Turbo Se Turbolader und Axiallagerscheibe für einen Turbolader

Also Published As

Publication number Publication date
EP3548705A1 (fr) 2019-10-09
KR20190086568A (ko) 2019-07-22
JP6858856B2 (ja) 2021-04-14
JP2020513500A (ja) 2020-05-14
WO2018099619A1 (fr) 2018-06-07
CN110023589A (zh) 2019-07-16
US20190301358A1 (en) 2019-10-03

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