WO2018009644A1 - Appareil permettant de raccorder deux carters de turbine d'un système turbocompresseur à deux étages - Google Patents

Appareil permettant de raccorder deux carters de turbine d'un système turbocompresseur à deux étages Download PDF

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Publication number
WO2018009644A1
WO2018009644A1 PCT/US2017/040875 US2017040875W WO2018009644A1 WO 2018009644 A1 WO2018009644 A1 WO 2018009644A1 US 2017040875 W US2017040875 W US 2017040875W WO 2018009644 A1 WO2018009644 A1 WO 2018009644A1
Authority
WO
WIPO (PCT)
Prior art keywords
turbine housing
flange
projection
turbine
turbocharger system
Prior art date
Application number
PCT/US2017/040875
Other languages
English (en)
Inventor
Laurent KUHN
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.
Priority to EP17740580.0A priority Critical patent/EP3482054A1/fr
Priority to KR1020197002980A priority patent/KR20190026802A/ko
Priority to JP2019500430A priority patent/JP2019525055A/ja
Priority to CN201780042290.8A priority patent/CN109415969A/zh
Priority to US16/315,198 priority patent/US20200011192A1/en
Publication of WO2018009644A1 publication Critical patent/WO2018009644A1/fr

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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
    • F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
    • F01D11/005—Sealing means between non relatively rotating elements
    • 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
    • F02B37/004—Engines characterised by provision of pumps driven at least for part of the time by exhaust with exhaust drives arranged in series
    • 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
    • F01D13/00—Combinations of two or more machines or engines
    • F01D13/02—Working-fluid interconnection of machines or engines
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01N—GAS-FLOW SILENCERS OR EXHAUST APPARATUS FOR MACHINES OR ENGINES IN GENERAL; GAS-FLOW SILENCERS OR EXHAUST APPARATUS FOR INTERNAL COMBUSTION ENGINES
    • F01N13/00—Exhaust or silencing apparatus characterised by constructional features ; Exhaust or silencing apparatus, or parts thereof, having pertinent characteristics not provided for in, or of interest apart from, groups F01N1/00 - F01N5/00, F01N9/00, F01N11/00
    • F01N13/18—Construction facilitating manufacture, assembly, or disassembly
    • F01N13/1805—Fixing exhaust manifolds, exhaust pipes or pipe sections to each other, to engine or to vehicle body
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01N—GAS-FLOW SILENCERS OR EXHAUST APPARATUS FOR MACHINES OR ENGINES IN GENERAL; GAS-FLOW SILENCERS OR EXHAUST APPARATUS FOR INTERNAL COMBUSTION ENGINES
    • F01N13/00—Exhaust or silencing apparatus characterised by constructional features ; Exhaust or silencing apparatus, or parts thereof, having pertinent characteristics not provided for in, or of interest apart from, groups F01N1/00 - F01N5/00, F01N9/00, F01N11/00
    • F01N13/18—Construction facilitating manufacture, assembly, or disassembly
    • F01N13/1861—Construction facilitating manufacture, assembly, or disassembly the assembly using parts formed by casting or moulding
    • 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
    • F02B67/00—Engines characterised by the arrangement of auxiliary apparatus not being otherwise provided for, e.g. the apparatus having different functions; Driving auxiliary apparatus from engines, not otherwise provided for
    • F02B67/10—Engines characterised by the arrangement of auxiliary apparatus not being otherwise provided for, e.g. the apparatus having different functions; Driving auxiliary apparatus from engines, not otherwise provided for of charging or scavenging apparatus
    • 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
    • F16B—DEVICES FOR FASTENING OR SECURING CONSTRUCTIONAL ELEMENTS OR MACHINE PARTS TOGETHER, e.g. NAILS, BOLTS, CIRCLIPS, CLAMPS, CLIPS OR WEDGES; JOINTS OR JOINTING
    • F16B7/00—Connections of rods or tubes, e.g. of non-circular section, mutually, including resilient connections
    • F16B7/04—Clamping or clipping connections
    • F16B7/0406—Clamping or clipping connections for rods or tubes being coaxial
    • F16B7/0413—Clamping or clipping connections for rods or tubes being coaxial for tubes using the innerside thereof
    • 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
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01N—GAS-FLOW SILENCERS OR EXHAUST APPARATUS FOR MACHINES OR ENGINES IN GENERAL; GAS-FLOW SILENCERS OR EXHAUST APPARATUS FOR INTERNAL COMBUSTION ENGINES
    • F01N13/00—Exhaust or silencing apparatus characterised by constructional features ; Exhaust or silencing apparatus, or parts thereof, having pertinent characteristics not provided for in, or of interest apart from, groups F01N1/00 - F01N5/00, F01N9/00, F01N11/00
    • F01N13/18—Construction facilitating manufacture, assembly, or disassembly
    • F01N13/1805—Fixing exhaust manifolds, exhaust pipes or pipe sections to each other, to engine or to vehicle body
    • F01N13/1827—Sealings specially adapted for exhaust systems
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01N—GAS-FLOW SILENCERS OR EXHAUST APPARATUS FOR MACHINES OR ENGINES IN GENERAL; GAS-FLOW SILENCERS OR EXHAUST APPARATUS FOR INTERNAL COMBUSTION ENGINES
    • F01N13/00—Exhaust or silencing apparatus characterised by constructional features ; Exhaust or silencing apparatus, or parts thereof, having pertinent characteristics not provided for in, or of interest apart from, groups F01N1/00 - F01N5/00, F01N9/00, F01N11/00
    • F01N13/18—Construction facilitating manufacture, assembly, or disassembly
    • F01N13/1838—Construction facilitating manufacture, assembly, or disassembly characterised by the type of connection between parts of exhaust or silencing apparatus, e.g. between housing and tubes, between tubes and baffles
    • F01N13/1844—Mechanical joints
    • F01N13/1855—Mechanical joints the connection being realised by using bolts, screws, rivets or the like
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01N—GAS-FLOW SILENCERS OR EXHAUST APPARATUS FOR MACHINES OR ENGINES IN GENERAL; GAS-FLOW SILENCERS OR EXHAUST APPARATUS FOR INTERNAL COMBUSTION ENGINES
    • F01N2450/00—Methods or apparatus for fitting, inserting or repairing different elements
    • F01N2450/18—Methods or apparatus for fitting, inserting or repairing different elements by using quick-active type locking mechanisms, e.g. clips
    • 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
    • F02B37/013—Engines characterised by provision of pumps driven at least for part of the time by exhaust with exhaust-driven pumps arranged in series
    • 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
    • F16B—DEVICES FOR FASTENING OR SECURING CONSTRUCTIONAL ELEMENTS OR MACHINE PARTS TOGETHER, e.g. NAILS, BOLTS, CIRCLIPS, CLAMPS, CLIPS OR WEDGES; JOINTS OR JOINTING
    • F16B2200/00—Constructional details of connections not covered for in other groups of this subclass
    • F16B2200/99—Fasteners with means for avoiding incorrect assembly or positioning
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
    • Y02T10/00—Road transport of goods or passengers
    • Y02T10/10—Internal combustion engine [ICE] based vehicles
    • Y02T10/12—Improving ICE efficiencies

Definitions

  • the present invention relates to an apparatus for connecting two turbine housings, a two-stage turbocharger system, and a method for assembling a two- stage turbocharger system.
  • Regulated two-stage turbocharging systems are being developed in order to resolve this conflict. Systems of this kind allow for the continuously variable adaptation of the turbine and compressor sides of the system for each engine operating point.
  • the regulated two-stage turbocharger system consists of two turbochargers of different sizes connected in series that utilize bypass regulation.
  • the exhaust gas mass flow coming from the cylinders first reaches the exhaust manifold.
  • HP high pressure turbine
  • LP low pressure turbine
  • the entire exhaust mass flow is then utilized again by the low pressure turbine (LP).
  • the entire fresh air flow is initially compressed by the low pressure stage. Further compression subsequently occurs in the high-pressure stage.
  • Regulated two-stage turbocharging therefore allows for continuous adaptation on the turbine and compressor sides to the requirements of the operating engine.
  • turbocharging systems of this sort must be designed to be as small as possible.
  • the two turbine housings are to be joined directly together. Since both the two turbine housings as well as the two compressor housings must be fluidically connected with each other, this can lead to problems during assembly. In addition, it is difficult to position the two housings correctly in relation to one another and to join them together in a fluid- tight manner.
  • the object of the present invention is therefore to provide an apparatus for connecting two turbine housings which permits simple assembly and, at the same time, precise positioning and fluid-tight joining of the turbine housings.
  • the present invention relates to an apparatus for connecting an exhaust gas outlet of a first turbine housing with an exhaust gas inlet of a second turbine housing according to claim 1, a two-stage turbocharger system according to claim 6, and a method for assembling a two-stage turbocharger system according to claim 14.
  • the apparatus according to the invention for connecting an exhaust gas outlet of a first turbine housing with an exhaust gas inlet of a second turbine housing of a two-stage turbocharger system features a pocket, which is situated in the area of a first flange on the first turbine housing, and a projection, which is situated in the area of a second flange on the second turbine housing and is able to be inserted into the pocket.
  • the projection is designed such that, after the projection has been inserted into the pocket, the first and second turbine housings can be tilted in relation to each other in order to establish a flush connection between the first flange and the second flange.
  • One advantage of this apparatus is that the two turbocharger assemblies can be assembled and calibrated separately from one another. As a result of the tilting movement, significant pressure can in a simple manner be exerted against a seal between the two turbine housings. The risk of leakage is consequently reduced.
  • this apparatus allows for accomplishing the connection between the turbine housings as well as the connection between the two compressor housings by way of a single motion during assembly.
  • the pocket can be situated in a wall of the first turbine housing extending from the first flange.
  • the projection may be designed in the form of a strip extending in a linear direction from an outer wall of the second turbine housing and running approximately parallel to a plane along which lies a connection area for the second flange.
  • the projection can have a lower side, which is disposed opposite a connection area on the first flange and features a chamfer.
  • the chamfer may have a chamfer angle of from 2° to 7°, in particular from 4° to 5°.
  • connection means may be provided in order to attach the second turbine housing to the first turbine housing.
  • a seal can be situated between the first flange and the second flange. Through the tilting motion, both connection areas of the first and second flanges are pressed together with significant force. In the process, the seal is compressed between the two connection areas. The risk of leakage is consequently decreased.
  • At least one locating pin may be provided in order to establish the position of the second turbine housing in relation to the first turbine housing during assembly.
  • the locating pin may be situated in the connection area of the first flange and interact with the projection in order to position the first and second turbine housings in relation to one another.
  • the invention furthermore comprises a two-stage turbocharger system having a first exhaust gas turbocharger with a first turbine housing and having a second exhaust gas turbocharger with a second turbine housing.
  • the first turbine housing features a pocket, into which projects a projection, which is situated in the area of a second flange on the second turbine housing.
  • the projection is designed such that, after the projection has been inserted into the pocket, the first and second turbine housings can be tilted in relation to each other in order to establish a flush connection between the first flange and the second flange.
  • the pocket can be situated in a wall of the first turbine housing extending from the first flange.
  • the projection may be designed in the form of a strip extending in a linear direction from an outer wall of the second turbine housing and running approximately parallel to a plane along which lies a connection area for the second flange.
  • the projection can have a lower side, which is disposed opposite a connection area on the first flange and features a chamfer.
  • the chamfer may have a chamfer angle of from 2° to 7°, in particular from 4° to 5°.
  • connection means may be provided in order to attach the second turbine housing to the first turbine housing.
  • a seal can be situated between the first flange and the second flange.
  • At least one locating pin may be provided in order to establish the position of the second turbine housing in relation to the first turbine housing during assembly.
  • the locating pin can be situated in the connection area of the first flange and interact with the projection in order to position the first and second turbine housings in relation to one another.
  • the two-stage turbocharger system may furthermore feature a first compressor housing having a compressor inlet and a second compressor housing having a compressor outlet, whereby the compressor inlet and the compressor outlet are connectable with one another by way of a plug connection.
  • the plug connection can be designed to have a tubular shape and feature a rigid center tube as well as a flexible outer casing. There can be a sealing bead at each end of the tube-shaped plug connector.
  • the elastic outer casing has the advantage of being able to compensate for tolerances. On the other hand, it aids in sealing the connection between the two compressor housings.
  • plug connection Due to how the plug connection is constructed (rigid center tube and flexible outer casing), rotating it at an angle of 10° can serve to connect the (compressor) housings with one another. This increases the flexibility of the design with regard to how the two turbocharger assemblies are positioned with respect to one another.
  • the plug connection furthermore allows the two turbocharger assemblies to be connected in a single assembly step, during which a suitably tight fluidic connection is simultaneously made between both turbine housings and both compressor housings.
  • the invention furthermore comprises a method for assembling a two-stage turbocharger system having a first exhaust gas turbocharger with a first turbine housing, and having a second exhaust gas turbocharger with a second turbine housing, whereby the method comprises the following steps: inserting a projection on the second turbine housing into a pocket on the first turbine housing; tilting the first turbine housing and the second turbine housing in relation to one another such that a first flange on the first turbine housing is situated flush against a second flange on the second turbine housing; and attaching the first turbine housing to the second turbine housing.
  • the method may furthermore comprise: connecting a compressor inlet of a first compressor of the two-stage turbocharger system with a compressor outlet of a second compressor of the two-stage turbocharger system by way of a plug connection during the insertion of the projection into the pocket.
  • Fig. l shows a first detail of a section of a first embodiment of the inventive two-stage turbocharger system
  • Fig. 2 shows a second detail of a section of the inventive two- stage turbocharger system according to the first embodiment
  • Fig. 3 shows three section views of the inventive apparatus for connecting two turbine housings in accordance with an embodiment.
  • Fig. 1 and Fig. 2 each show a detail of a section of a two-stage turbocharger system 10.
  • the two-stage turbocharger system 10 comprises a first exhaust gas turbocharger 100 and a second exhaust gas turbocharger 200, each having a turbine and a compressor.
  • the turbocharger system 10 has a first turbine housing 110 and a second turbine housing 210 as well as a first compressor housing 300 and a second compressor housing 400.
  • the two turbine housings 110, 210 shown in the Fig. 1 view are not yet connected with one another.
  • Fig. 1 and Fig. 2 each show a detail of a section of a two-stage turbocharger system 10.
  • the two-stage turbocharger system 10 comprises a first exhaust gas turbocharger 100 and a second exhaust gas turbocharger 200, each having a turbine and a compressor.
  • the turbocharger system 10 has a first turbine housing 110 and a second turbine housing 210 as well as a first compressor housing 300 and a second compressor housing 400.
  • FIG. 3 are three expanded section views of the connecting apparatus, whereby the process for connecting together the first and second turbine housings 110, 210 is shown in chronological sequence.
  • the connecting apparatus features a pocket 130 situated in the area of the first flange 120 of the first turbine housing 110 as well as a projection 230, which is situated in the area of the second flange 220 of the second turbine housing 210.
  • the projection 230 is inserted into the pocket 130 in order to connect the two turbine housings 110, 210.
  • the projection 230 is designed such that, after the projection 230 has been inserted into the pocket 130, the first and second turbine housings 110, 210 can be tilted in relation to each other in order to establish a flush connection between the first flange 120 and the second flange 220. This is made evident by comparing Fig. 1 with Fig. 2: a gap exists at the bottom right of Fig.
  • FIG. 2 the first flange 120 and the second flange 220 are flush against one another and are providing a fluid-tight connection between the first and second turbine housings 110, 210.
  • the two turbocharger assemblies can be assembled and calibrated separately from one another prior to being joined together.
  • significant pressure can in a simple manner be exerted against the seal 600 that is situated between the two turbine housings 110, 210, or, more specifically, between the first flange 120 and the second flange 220.
  • the significant pressure against the seal 600 can, for example, lead to a compression of the seal leading to a reduction of its thickness measuring from 0.1 to 0.3 mm.
  • the connecting apparatus allows for accomplishing the connection between the turbine housings 110, 210 as well as the connection between the two compressor housings 300, 400 by way of a single movement during assembly (more regarding this hereinafter).
  • the pocket 130 can be situated in a wall of the first turbine housing 110 extending from the first flange 120.
  • the pocket 130 is formed as a groove running in a linear direction.
  • the pocket 130 is a straight-line depression running along the border between the first flange 120 and the wall extending from the first flange 120.
  • the cross section of the pocket 130 can be approximately rectangular or u-shaped.
  • the projection 230 is designed in the form of a strip extending in a linear direction from an outer wall 214 of the second turbine housing 210 and running approximately parallel to a plane along which lies a connection area 222 for the second flange 220 (see Fig. 1).
  • the projection 230 has a lower side 232, which is disposed opposite a connection area 122 on the first flange 120 (see Fig. 1) and features a chamfer 234.
  • the chamfer 234 is in particular evident from the illustrations in Fig. 3.
  • the chamfer 234 may, for example, have a chamfer angle of from 2° to 7°, in particular from 4° to 5°.
  • the projection 230 formed as a strip has a lower side 232, at least some extent of which is not exactly parallel to the connection area 222 of the second flange 220, but at least some extent of which is rather inclined slightly upward. The angle of inclination corresponds to the aforementioned chamfer angle.
  • connection means 700 can be put in place in order to attach the second turbine housing 210 to the first turbine housing 110 (see Fig. 2).
  • connection means 700 can be provided that are situated on the approximately opposite sides of the exhaust gas inlet 212.
  • Suitable for use as connection means 700 are, for example, expansion pins, set screws with nuts (as shown in Fig. 2), screws, clamps, brackets, or the like.
  • a seal 600 can be situated between the first flange 120 and the second flange 220.
  • both connection areas 122, 222 of the first and second flanges 120, 220 are pressed together with significant force.
  • the seal is compressed between the two connection areas 122, 222. This readily apparent from the illustration at the bottom of Fig. 3. As a result, the risk of exhaust gases leaking in this connection area is further reduced.
  • the apparatus for connecting the two turbine housings 110, 210 can be provided with at least one locating pin 140 in order to establish the position of the second turbine housing 210 in relation to the first turbine housing 110 during assembly.
  • the locating pin 140 can, for example, be situated in the connection area 122 of the first flange 120 (as indicated in Fig. 1) and interact with the projection 230 (for example a recess in the projection 230) in order to position the first and second turbine housings 110 to 210 in relation to one another.
  • the joining of the compressor inlet 310 of the first compressor housing 300 with the compressor outlet 410 of the second compressor housing 400 will be described in reference to Fig. 1 and Fig. 2 as follows.
  • the compressor inlet 310 is connected with the compressor outlet 410 using a so-called Plug&Seal connection unit.
  • This comprises a tube-shaped plug connector 500 that extends from the compressor inlet 310 into the compressor outlet 410.
  • the plug connector 500 features, for example, a rigid center tube and an elastic outer casing.
  • a sealing bead 510 is provided at each end of the plug connector 500.
  • the center tube can, for example, be manufactured from metal (preferably stainless steel).
  • the outer casing can, for example, be a rubber coating.
  • connection tube 500 in the second compressor housing 400 can, for example, be assembled in advance (see Fig. 1) as well as inserted at an appropriate angle into the first compressor housing 300. In doing so, a gap will remain between the two housings (see Fig. 1 and Fig. 2), which is also still present subsequent to the tilting movement of the two turbine housings 1 10, 210 in relation to one another. In the example shown, this gap is approximately 4-5 mm wide.
  • the gap may be larger or smaller.
  • the length of the connector plug 500 as well as its construction (for example, greater elasticity in order to compensate for the relevant positions of the two turbine housings with respect to each other) can be adjusted accordingly. Due to how the plug connection 500 is constructed (rigid center tube, flexible outer casing, and a sealing bead 510 at both ends), a rotation or an angle of, for example, up to 10° can serve to connect the compressor housings 300, 400 (or rather the inlet 310 and outlet 410 thereof) with one another. The rotation relates in this context to an angle between the central longitudinal axis of the compressor outlet 410 and the central longitudinal axis of the compressor inlet 310.
  • the plug connection 500 furthermore allows the two turbocharger assemblies to be connected in a single assembly step, during which a suitably tight fluidic connection is simultaneously made between both turbine housings and both compressor housings.
  • the method for assembling a two-stage turbocharger system will also be briefly discussed as follows. Initially, the two turbocharger assemblies may be assembled completely independently of one another. The first exhaust gas turbocharger 100 is then joined with the first turbine housing 1 10, and the second exhaust gas turbocharger 200 is joined with the second turbine housing 210, whereby the projection 230 of the second turbine housing 210 is inserted into the pocket 130 of the first turbine housing 1 10. This step is apparent in Fig.
  • first turbine housing 1 10 is then tilted in relation to the second turbine housing 210 such that the first flange 120 of the first turbine housing 1 10 is situated flush against the second flange 220 of the second turbine housing 210 (see Fig. 2 and the lower illustration in Fig. 3). Finally, the first turbine housing 1 10 can then be attached to the second turbine housing 210, for example using the connection means 700.
  • the compressor inlet 310 of the first compressor is able to be connected with the compressor outlet 410 of the second compressor of the two-stage turbocharger system 10.
  • This can take place, for example, by way of the plug connector 500.
  • the plug connector 500 can, for example, have been previously inserted into the compressor outlet 410 of the second compressor housing 400.
  • the two compressor housings 300, 400 as well as the two turbine housings 1 10, 210 can then be joined together. This approach not only simplifies assembly, but also reduces assembly time considerably. In addition, it is thereby possible to completely assemble the two turbocharger assemblies separately from one another.
  • Apparatus according to embodiment 4 characterized in that the chamfer (234) has a chamfer angle of from 2° to 7°, in particular from 4° to 5°. 6. Apparatus according to any of the preceding embodiments, characterized in that at least one connection means (700) is provided in order to attach the second turbine housing (210) to the first turbine housing (110).
  • Apparatus according to any of the preceding embodiments characterized in that a seal (600) is situated between the first flange (120) and the second flange (220).
  • Apparatus according to any of the preceding embodiments characterized in that furthermore at least one locating pin (140) is provided in order to establish the position of the second turbine housing (210) in relation to the first turbine housing (110) during assembly.
  • the locating pin (140) is situated in the connection area (122) of the first flange (120) and interacts with the projection (230) in order to position the first and second turbine housings (110, 210) in relation to one another. 10.
  • Two-stage turbocharger system (10) having
  • the first turbine housing (110) features a pocket (130), into which projects a projection (230), which is situated in the area of a second flange (220) on the second turbine housing (210), characterized in that the projection (230) is designed such that, during the connection of the first and second turbine housings (110, 210), after the projection (230) has been inserted into the pocket (130), the first and second turbine housings (110, 210) can be tilted in relation to one another in order to establish a flush connection between the first flange (120) and the second flange (220).
  • Two-stage turbocharger system according to any of the embodiments 10 to 12, characterized in that the projection (230) has a lower side (232), which is disposed opposite a connection area (122) on the first flange (120) and features a chamfer (234).
  • connection means (700) is provided in order to attach the second turbine housing (210) to the first turbine housing (110).
  • locating pin (140) is provided in order to establish the position of the second turbine housing (210) in relation to the first turbine housing (110) during assembly.
  • Two-stage turbocharger system according to any of the embodiments 10 to 18, characterized in that the two-stage turbocharger system (10) furthermore features a first compressor housing (300) having a compressor inlet (310) and a second compressor housing (400) having a compressor outlet (410), wherein the compressor outlet (410) and the compressor inlet (310) are connectable with one another by way of a plug connection (500).
  • Two-stage turbocharger system according to embodiment 20 characterized in that there is a sealing bead (510) at each end of the tube- shaped plug connection (500).
  • a second exhaust gas turbocharger (200), which features a second turbine housing (210), comprising:
  • first turbine housing (110) and the second turbine housing (210) tilting the first turbine housing (110) and the second turbine housing (210) in relation to one another such that the first flange (120) of the first turbine housing (110) is situated flush against the second flange (220) of the second turbine housing (210); and attaching the first turbine housing (110) to the second turbine housing (210).
  • Method according to embodiment 22, furthermore comprising connecting a compressor inlet (310) of a first compressor of the two-stage turbocharger system with a compressor outlet (410) of a second compressor of the two-stage turbocharger system by way of a plug connection (500) during the insertion of the projection (230) into the pocket (130).

Landscapes

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

Abstract

L'invention concerne un appareil permettant de raccorder une sortie de gaz d'échappement d'un premier carter de turbine à une entrée de gaz d'échappement d'un second carter de turbine d'un système turbocompresseur à deux étages, qui présente une poche située dans la zone d'une première bride sur le premier carter de turbine et qui présente une saillie disposée dans la zone d'une seconde bride sur le second carter de turbine et pouvant être insérée dans la poche. La saillie est conçue de telle sorte que, une fois que la saillie a été insérée dans la poche, les premier et second carters de turbine peuvent être inclinés l'un par rapport à l'autre afin d'établir un raccordement affleuré entre la première bride et la seconde bride.
PCT/US2017/040875 2016-07-07 2017-07-06 Appareil permettant de raccorder deux carters de turbine d'un système turbocompresseur à deux étages WO2018009644A1 (fr)

Priority Applications (5)

Application Number Priority Date Filing Date Title
EP17740580.0A EP3482054A1 (fr) 2016-07-07 2017-07-06 Appareil permettant de raccorder deux carters de turbine d'un système turbocompresseur à deux étages
KR1020197002980A KR20190026802A (ko) 2016-07-07 2017-07-06 2단 터보차저 시스템의 2개의 터빈 하우징용의 접속장치
JP2019500430A JP2019525055A (ja) 2016-07-07 2017-07-06 ２段ターボチャージャーシステムの２つのタービンハウジング用の接続装置
CN201780042290.8A CN109415969A (zh) 2016-07-07 2017-07-06 用于连接两级涡轮增压器系统的两个涡轮壳体的设备
US16/315,198 US20200011192A1 (en) 2016-07-07 2017-07-06 Apparatus for connecting two turbine housings of a two-stage turbocharger system

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE102016212440.4 2016-07-07
DE102016212440 2016-07-07

Publications (1)

Publication Number Publication Date
WO2018009644A1 true WO2018009644A1 (fr) 2018-01-11

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PCT/US2017/040875 WO2018009644A1 (fr) 2016-07-07 2017-07-06 Appareil permettant de raccorder deux carters de turbine d'un système turbocompresseur à deux étages

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Country Link
US (1) US20200011192A1 (fr)
EP (1) EP3482054A1 (fr)
JP (1) JP2019525055A (fr)
KR (1) KR20190026802A (fr)
CN (1) CN109415969A (fr)
WO (1) WO2018009644A1 (fr)

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* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP3967858A1 (fr) * 2020-09-14 2022-03-16 ABB Schweiz AG Système de turbocompresseur à étages multiples

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DE3302105A1 (de) * 1982-01-28 1983-07-28 MacGregor International S.A., 4002 Basel Schnell zusammenfuegbares bauprofil insbesondere fuer verwendung als wandungsbauteil, wie mit diesem bauprofil hergestellte obere abschlussplatte eines lukendeckels, fussboeden, waende oder decken
DE4205454A1 (de) * 1992-02-22 1993-08-26 H J Kuepper Gmbh & Co Kg Einrichtung zum anschliessen eines rohrkruemmers an einen zylinderkopf
US5918912A (en) * 1996-12-21 1999-07-06 Daimler-Benz Ag Arrangement for mounting a pipe end flange
FR2897893A1 (fr) * 2006-02-27 2007-08-31 Renault Sas Dispositif de fixation de turbocompresseur
EP2163746A2 (fr) * 2008-09-10 2010-03-17 BorgWarner Inc. Couplage de turbocompresseurs pour la contre-rotation passive avant tourbillonnement
US20130038028A1 (en) * 2011-08-08 2013-02-14 Carl Freudenberg Kg Seal and Associated Sealing Arrangement
US20150010397A1 (en) * 2012-01-17 2015-01-08 Borgwarner Inc. Exhaust turbocharger
US20150052891A1 (en) * 2013-08-26 2015-02-26 Mazda Motor Corporation Turbocharging device of engine for vehicle
WO2015088397A1 (fr) * 2013-12-13 2015-06-18 Ab Volvo Penta Agencement, procédé et composant de fixation de moteur à combustion interne
DE102014218345A1 (de) * 2014-09-12 2016-03-17 Ford Global Technologies, Llc Aufgeladene Brennkraftmaschine mit in Reihe angeordneten Abgasturboladern

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DE1005319B (de) * 1952-11-03 1957-03-28 Kloeckner Humboldt Deutz Ag Rohrgelenkverbindung fuer Auspuff- und Ansaugeleitungen von Brennkraftmaschinen
DE3302105A1 (de) * 1982-01-28 1983-07-28 MacGregor International S.A., 4002 Basel Schnell zusammenfuegbares bauprofil insbesondere fuer verwendung als wandungsbauteil, wie mit diesem bauprofil hergestellte obere abschlussplatte eines lukendeckels, fussboeden, waende oder decken
DE4205454A1 (de) * 1992-02-22 1993-08-26 H J Kuepper Gmbh & Co Kg Einrichtung zum anschliessen eines rohrkruemmers an einen zylinderkopf
US5918912A (en) * 1996-12-21 1999-07-06 Daimler-Benz Ag Arrangement for mounting a pipe end flange
FR2897893A1 (fr) * 2006-02-27 2007-08-31 Renault Sas Dispositif de fixation de turbocompresseur
EP2163746A2 (fr) * 2008-09-10 2010-03-17 BorgWarner Inc. Couplage de turbocompresseurs pour la contre-rotation passive avant tourbillonnement
US20130038028A1 (en) * 2011-08-08 2013-02-14 Carl Freudenberg Kg Seal and Associated Sealing Arrangement
US20150010397A1 (en) * 2012-01-17 2015-01-08 Borgwarner Inc. Exhaust turbocharger
US20150052891A1 (en) * 2013-08-26 2015-02-26 Mazda Motor Corporation Turbocharging device of engine for vehicle
WO2015088397A1 (fr) * 2013-12-13 2015-06-18 Ab Volvo Penta Agencement, procédé et composant de fixation de moteur à combustion interne
DE102014218345A1 (de) * 2014-09-12 2016-03-17 Ford Global Technologies, Llc Aufgeladene Brennkraftmaschine mit in Reihe angeordneten Abgasturboladern

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* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP3967858A1 (fr) * 2020-09-14 2022-03-16 ABB Schweiz AG Système de turbocompresseur à étages multiples
WO2022053634A1 (fr) * 2020-09-14 2022-03-17 Turbo Systems Switzerland Ltd. Agencement de turbocompresseur à étages multiples

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EP3482054A1 (fr) 2019-05-15
US20200011192A1 (en) 2020-01-09
KR20190026802A (ko) 2019-03-13
JP2019525055A (ja) 2019-09-05
CN109415969A (zh) 2019-03-01

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