EP3548705A1 - Tubocompresseur - Google Patents

Tubocompresseur

Info

Publication number
EP3548705A1
EP3548705A1 EP17768032.9A EP17768032A EP3548705A1 EP 3548705 A1 EP3548705 A1 EP 3548705A1 EP 17768032 A EP17768032 A EP 17768032A EP 3548705 A1 EP3548705 A1 EP 3548705A1
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.)
Granted
Application number
EP17768032.9A
Other languages
German (de)
English (en)
Other versions
EP3548705B1 (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
Active legal-status Critical Current
Anticipated expiration legal-status Critical

Links

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 gained in the turbine during the expansion of the first medium.
  • 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. Between the turbine housing of the turbine and the compressor housing of the compressor, a bearing housing is positioned, wherein the bearing housing is connected on the one hand to the turbine housing and on the other hand to the compressor housing. In the bearing housing, a shaft is mounted, via which the turbine rotor is coupled to the compressor rotor.
  • the turbine housing of the turbine namely a so-called Turbinenzuströmgepuruse
  • the bearing housing are connected to each other via a preferably designed as a clamping claw fastening means.
  • a clamping claw fastening device is mounted with a first portion thereof on a flange of the turbine housing via fastening means and covered with a second portion of a flange of the bearing housing at least in sections.
  • a fastening device of the association or composite of bearing housing and turbine housing is clamped, in particular under clamping a flange of a nozzle ring and optionally 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 relaxed, in particular with relaxing exhaust gas.
  • the Turbinenzuströmgephaseuse the turbine housing directs the exhaust gas in the direction of the turbine rotor.
  • In the turbine inlet housing there is an overpressure on the environment, which is dissipated in the turbine to recover energy during the expansion of the first medium.
  • In the region of the junction of turbine housing or Turbinenzuströmgenosuse and bearing housing can lead to leakage, so that the first, to be relaxed in the turbine medium via the connection area between the turbine housing and bearing housing can get into the environment. This is a disadvantage.
  • the present invention has the object to provide a turbocharger with a novel flange connection.
  • This object is achieved according to a first aspect of the invention by a turbocharger according to claim 1.
  • the nozzle ring is installed such that a flange thereof is positioned relative to a flow channel on a flange of the turbine housing, which is clamped to the flange of the bearing housing, opposite side of the flow channel.
  • This makes a particularly advantageous sealing of the junction of turbine housing or Turbinenzuströmgephinuse and bearing housing possible. It reduces the risk that in the turbine to relaxing medium passes through the connection area between the turbine housing and bearing housing in the environment.
  • this object is achieved by a turbocharger according to claim 10.
  • a spring element is positioned between the flange of the bearing housing and the flange of the turbine housing, which presses the flange of the nozzle ring axially against the flange of the turbine housing.
  • FIG. 2 a partial cross-section through a second turbocharger according to the invention in the region of a connection of a turbine housing to a bearing housing;
  • the invention relates to a turbocharger.
  • a turbocharger has a turbine for relaxing a first medium, in particular for relaxing exhaust gas of an internal combustion engine. Further, a turbocharger has a compressor for compressing a second medium, in particular charge air, using energy obtained in the turbine during the expansion of the first medium.
  • 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 supported in a bearing housing, the bearing housing positioned between the turbine housing and the compressor housing and connected to both the turbine housing and the compressor housing.
  • FIGS. 1 to 3 respectively showing corresponding cutouts from a turbocharger in the region of the connection of the turbine housing to the bearing housing.
  • FIGS. 1 to 3 respectively showing corresponding cutouts from a turbocharger in the region of the connection of the turbine housing to the bearing housing.
  • FIG. 1 shows a first embodiment of a turbocharger according to a first aspect of the invention, Fig. 1, wherein in Fig. 1, the junction between a turbine housing, namely a Turbinenzuströmgephinuse 1 of the turbine housing, and a bearing housing 2 of the exhaust gas turbocharger is shown. Furthermore, Fig. 1 shows a nozzle ring 3, a heat shield 4 and a so-called insert 1 1.
  • the Turbinenzuströmgeophuse 1 is connected to the bearing housing 2 via a fastening means 5 such that the fastening means 5 is mounted on a flange 6 of Turbinenzuströmgeophuses 1 with a first portion 7, via a plurality of fastening means 8, and that the fastening means 5 with a second portion 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 braces the Turbinenzuströmgeophuse 1 and bearing housing 2 together.
  • the fastening device 5 can be segmented in the circumferential direction.
  • each fastening means 8 comprises a threaded screw 8a screwed into the flange 6 of the turbine inlet housing 1 and a nut 8b engaging at the other end of the threaded bolt 8a, wherein a defined preload force is applied via tightening the nuts 8b
  • Fastening device 5 can be applied to the Turbinenzuströmgephaseuse 1 and on the bearing housing 10.
  • the nozzle ring 3 of the turbine is installed such that a flange 13 of the nozzle ring 3 is arranged in relation to a flow channel 24 of the turbine, in the region of which the nozzle ring 3 is positioned on a flange 6 of the Turbinenzuströmgephinuses 1 and thus the flange 10 of the bearing housing 2 opposite side of the Strömungska- channel 24.
  • only one flange 12 of the heat shield 4 is clamped between the flange 10 of the turbine inlet housing 1 clamped by the fastening device 5 and the flange 10 of the bearing housing 2.
  • the flange 13 of the nozzle ring 3 may be attached to a portion 14 of the Turbinenzuströmgeophuses 1, as well as the flange 13 of the nozzle ring 3, based on the flow channel 24 on the opposite side in Verspann Scheme between the flanges 6, 10 of Turbinenzuströmgeophuse 1 and bearing housing 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 inlet housing 1, with the flange 13 of the nozzle ring 3 having one end at a boundary of this recess 15 in the radial direction Section 14 of Turbinenzuströmgeophuses 1 and at an opposite end on the insert 1 1 is supported.
  • an elastic spring element 16 is received, which presses against the flange 13 of the nozzle ring 3 in the axial direction.
  • this elastic spring element 16 presses against the flange 13 of the nozzle ring 3 such that the nozzle ring 3 is pressed by the spring element 16 in the direction of the connecting region of the flanges 6, 10 of turbine inlet housing 1 and bearing housing 2.
  • the nozzle ring 3 presses against the flange 12 of the heat shield 4.
  • FIG. 2 A second embodiment of a turbocharger according to the first aspect of the invention is shown in FIG. 2. Also in FIG. 2, the flange 13 of the nozzle ring 3 is located on a side of the turbine's flow channel 24 opposite the clamping region of the flanges 6, 10 of turbine inlet housing 1 and bearing housing 2 positioned.
  • FIG. 2 differs from the embodiment of FIG. 1 in 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 Recess 18 of the portion 14 of the bearing housing 1 is received. Also in Fig. 2, the flange 13 of the nozzle ring 3 projects at least in sections into the recess 18 of the section 4 of the Turbinenzuströmgephinuses 1 inside.
  • FIG. 2 A further difference of the embodiment of Fig. 2 compared to the embodiment 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 Turbinenzuströmgeophuse 1 and bearing housing 2. Rather, in Fig. 2, the flange 10 of the bearing housing 2 directly to the flange 6 of Turbinenzuströmgeophuses 1 to the plant.
  • a sealing element 19 may additionally be positioned, which may be a preferably metallic sealing ring in the form of an O-ring or C-ring.
  • the sealing element 19 may also be made of graphite. 2
  • the sealing element 19 is received in a recess 20 of the flange 6 of the Turbinenzuströmgeophuses 1 and seals in particular in the axial direction between sealing surfaces of the adjacent flanges 6, 10 of Turbinenzuströmgephaseuse 1 and bearing housing. 2
  • the flange 12 of the heat shield 4 engages the flange 10 of the bearing housing 2, but, as already stated, is not clamped between the flange 10 of the bearing housing 2 and the flange 6 of the Turbinenzu- strömgeophuses 1. Rather, the flange 12 of the heat shield 4 in FIG. 2 engages via an anti-rotation 21 on the flange 10 of the bearing housing 2. In Fig. 2, the number of components in the clamping dressing between the bearing housing 2 and Turbinenzuströmgepatuse 1 is further reduced.
  • the nozzle ring 3 is also possible to form the nozzle ring 3 as an integral part of the insert 1 1. In this case, then the nozzle ring 3 does not have to be separately attached to the Turbinenzuströmgeophuse 1. Rather, then takes over the insert 1 1, which provides the nozzle ring 3 as an integral assembly, the same recording in the turbine.
  • Fig. 3 shows an embodiment of a turbocharger according to the second aspect of the invention.
  • the flange 13 of the nozzle ring 3 and the flange 12 of the heat shield 4 are both between the flange 13 of the nozzle ring 3 and the flange 12 of the heat shield 4 .
  • this spring element 22 is arranged between the flange 10 of the bearing housing 2 and the flange 12 of the heat shield 4, so that the spring element 22, 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 presses against the flange 6 of the Turbinenzuströmgefituses 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 from.
  • the spring element 22 presses the flange 13 of the nozzle ring 3 in the axial direction against the flange 6 of the Turbinenzuströmgephaseuses 1, whereby even if these modules are subject to a different thermal expansion during operation, always a good sealing effect in the connecting region of the bearing housing 2 and Turbinenzuströmgephase 4, is ensured, so there is no danger that exhaust gas flows through this connection area to the outside into the environment.
  • clamping devices such as clamping claws
  • clamping claws can also be dispensed with.
  • the flange of the bearing housing is bolted directly to the Turbinenzuströmgephaseuse.

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)

Abstract

L'invention concerne un turbocompresseur comprenant une turbine, un compresseur et un carter de palier (2), la turbine présentant un carter de turbine (1), une couronne directrice (3) et un rotor de turbine. En outre, le turbocompresseur comprend un dispositif de fixation (5) pourvu d'une première et d'une deuxième partie (7,9) Le carter de turbine (1) et le carter de palier (2) sont raccordés par l'intermédiaire d'un dispositif de fixation (5) de telle sorte que le dispositif de fixation (5) est monté sur une bride (6) du carter de turbine (1) par une première partie (7) et recouvre, au moins par endroits, la bride (10) du carter de palier (2) par une seconde partie (9), La couronne directrice (3) est montée de telle sorte qu'une bride (13) de celle-ci est positionnée par rapport à un canal d'écoulement (24) sur un côté du canal d'écoulement (24) opposé à la bride (6) du carter de turbine (1). Cette structure permet d'éviter des effets de tranchée et de réduire ainsi les fuites entre le carter de turbine et le carter de palier.
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 true EP3548705A1 (fr) 2019-10-09
EP3548705B1 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

Family Cites Families (15)

* Cited by examiner, † Cited by third party
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
GB0121864D0 (en) * 2001-09-10 2001-10-31 Leavesley Malcolm G Turbocharger apparatus
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
DE102013002605A1 (de) 2013-02-15 2014-08-21 Man Diesel & Turbo Se Turbolader und Axiallagerscheibe für einen Turbolader
WO2014128894A1 (fr) * 2013-02-21 2014-08-28 三菱重工業株式会社 Turbocompresseur à géométrie variable
EP3267010B1 (fr) * 2015-03-05 2019-05-08 Mitsubishi Heavy Industries Engine & Turbocharger, Ltd. Turbocompresseur
WO2016159004A1 (fr) * 2015-03-31 2016-10-06 株式会社Ihi Dispositif de suralimentation à déplacement variable

Also Published As

Publication number Publication date
JP6858856B2 (ja) 2021-04-14
WO2018099619A1 (fr) 2018-06-07
US20190301358A1 (en) 2019-10-03
EP3548705B1 (fr) 2021-03-03
KR20190086568A (ko) 2019-07-22
CN110023589A (zh) 2019-07-16
JP2020513500A (ja) 2020-05-14

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