EP1488079A1 - Exhaust gas turbocharger in an internal combustion engine - Google Patents
Exhaust gas turbocharger in an internal combustion engineInfo
- Publication number
- EP1488079A1 EP1488079A1 EP03706391A EP03706391A EP1488079A1 EP 1488079 A1 EP1488079 A1 EP 1488079A1 EP 03706391 A EP03706391 A EP 03706391A EP 03706391 A EP03706391 A EP 03706391A EP 1488079 A1 EP1488079 A1 EP 1488079A1
- Authority
- EP
- European Patent Office
- Prior art keywords
- exhaust gas
- section
- inlet cross
- flow inlet
- turbine
- 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.)
- Withdrawn
Links
Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D17/00—Regulating or controlling by varying flow
- F01D17/10—Final actuators
- F01D17/12—Final actuators arranged in stator parts
- F01D17/14—Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits
- F01D17/141—Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits by means of shiftable members or valves obturating part of the flow path
- F01D17/143—Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits by means of shiftable members or valves obturating part of the flow path the shiftable member being a wall, or part thereof of a radial diffuser
-
- 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
- F01D17/00—Regulating or controlling by varying flow
- F01D17/10—Final actuators
- F01D17/12—Final actuators arranged in stator parts
- F01D17/14—Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits
- F01D17/16—Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits by means of nozzle vanes
- F01D17/167—Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits by means of nozzle vanes of vanes moving in translation
-
- 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
- F01D9/026—Scrolls for radial 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
- F02B37/02—Gas passages between engine outlet and pump drive, e.g. reservoirs
- F02B37/025—Multiple scrolls or multiple gas passages guiding the gas to the pump drive
-
- 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
- F01N13/08—Other arrangements or adaptations of exhaust conduits
- F01N13/10—Other arrangements or adaptations of exhaust conduits of exhaust manifolds
- F01N13/107—More than one exhaust manifold or exhaust collector
-
- 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
- F02B37/12—Control of the pumps
- F02B37/22—Control of the pumps by varying cross-section of exhaust passages or air passages, e.g. by throttling turbine inlets or outlets or by varying effective number of guide conduits
-
- 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
-
- 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 invention relates to an exhaust gas turbocharger for an internal combustion engine according to the preamble of claim 1.
- turbocharger comprises an exhaust gas turbine, which in a turbine housing has a turbine wheel which is to be driven by the exhaust gases of the internal combustion engine.
- the exhaust gas is supplied to the turbine wheel via a plurality of spiral channels, which guide the exhaust gas to the turbine wheel via a respective radial flow inlet cross-section.
- DE 42 42 494 Cl embodiments are described with two, three and four spiral channels, each of which radial flow inlet cross sections are assigned distributed in different angular intervals over the circumference of the turbine wheel.
- each flow inlet cross-section is a guide grid, which allows a defined flow of the turbine wheel with adjustable swirl and volume flow.
- a guide grille with a narrow flow cross section can be used to generate a high back pressure.
- a guide grid with a larger flow cross-section may be provided in order to enable a largely throttle-free exhaust gas flow to the turbine wheel, in particular during partial load operation of the internal combustion engine.
- the different baffles are arranged on a common, sleeve-shaped flow control.
- the Strömungsleitapparat is designed to be axially displaceable, which closed-formed, continuous or interruption-free wall sections of the Strömungsleitapparates can be inserted into individual flow inlet cross-sections and the effective flow area can be reduced accordingly.
- the flow conditions in the case of a guide grille which is only partially exposed and an inlet cross section partially closed by the wall of the flow control device can deteriorate significantly, which in particular impairs the efficiency of the exhaust gas turbocharger.
- the flow control device is usually either placed in a position in which the flow inlet cross section is completely closed or in a position in which the guide grid extends over the entire axial width of the flow inlet cross section.
- the invention is based on the problem to provide with simple structural measures additional adjustment options for a generic exhaust gas turbocharger.
- intermediate positions at the axial width of the flow inlet cross-section to the turbine wheel should be infinitely adjustable without impairing the flow conditions.
- the guide-grid ring is held between two walls which delimit the flow-inlet cross-section axially, one of the walls a- xial is carried out slidably and has a receiving opening into which the guide grid is to be pushed or pushed out during an axial movement of this wall. Due to the axial displacement of the movable wall, the axial width of the flow inlet cross sections can be adjusted. In contrast to the state of the art, any intermediate positions are possible without affecting the flow conditions in the turbine flow, since in each position of the axially displaceable wall, the guide grid is effective in the free, effective flow inlet cross section with its defined guide grid geometry influencing the flow.
- sliding wall can be adjusted by the variation of the axial position of the wall of the optimal for each operating point of the engine radial Str ⁇ mungseintrittsquerites without thereby affecting the arrangement of the turbine wheel negative.
- the depth of the receiving opening on the displaceable wall is advantageously adapted to the axial extent of the guide grid, so that the guide grid can be inserted into the receiving opening until the radial flow inlet cross-section is closed and the flow inlet cross-section is completely closed or except for a residual gap.
- an exhaust turbine designed as a combination turbine which also has a semi-axial flow inlet cross-section in addition to the radial flow inlet cross-section, a complete decoupling from the semi-axial inlet cross-section is possible when the radial inlet cross-sections are closed.
- the combination turbine can thereby be reduced to an axial turbine in certain operating states of the internal combustion engine. the, whereby an increase in efficiency is possible.
- the exhaust gas turbocharger described can be used both in four-cylinder internal combustion engines and in six-cylinder internal combustion engines.
- the exhaust gases of the two middle cylinders are advantageously summarized and fed to a spiral channel and summarized in the same way the exhaust gases of the outer cylinder and fed to the second spiral channel.
- two spiral channels can also be provided, wherein each three cylinders arranged one behind the other are each connected to a spiral channel.
- a separate charge for driving the turbine wheel can advantageously be utilized by the separate combination of the exhaust gases of individual cylinders of the internal combustion engine.
- a high proportion of the kinetic energy can be utilized by passing a pre-charge pressure pulse over the respective spiral channel onto the turbine wheel when opening the exhaust valves.
- FIG. 1 shows a section through an exhaust gas turbine of an exhaust gas turbocharger for an internal combustion engine, with a radial and a semi-axial Str ⁇ mungseintritts- cross section to the turbine wheel, wherein in the radial flow inlet cross section, a guide grid is designed with an axially displaceable wall,
- FIG. 2 is a schematic representation of a four-cylinder internal combustion engine with turbocharger, the exhaust gas turbine is shown in cross section, with two separate spiral channels for supplying exhaust gas to the turbine wheel,
- FIG. 3 is a representation corresponding to FIG. 2, but with a six-cylinder internal combustion engine
- FIG. 4 shows a longitudinal section through an exhaust gas turbine with exclusively radial flow inlet cross section.
- the exhaust gas turbine 1 shown in longitudinal section in FIG. 1 is part of an exhaust gas turbocharger for an internal combustion engine.
- the exhaust gas turbine 1 is arranged in the exhaust line of the internal combustion engine and is driven by the exhaust gases of the internal combustion engine.
- the exhaust gas turbine in turn drives a compressor in the intake tract of the internal combustion engine, compressed via the intake combustion air to an increased boost pressure. tet, under which the combustion air is introduced into the cylinder inlets of the internal combustion engine.
- the exhaust gas turbine 1 is designed as a combination turbine with a semi-axial and a radial flow inlet cross-section.
- the exhaust gas turbine 1 has two separately executed spiral channels 4 and 5, which communicate with the exhaust gas line of the internal combustion engine and can be supplied to the turbine wheel 3 via the exhaust gas of the internal combustion engine.
- Each spiral channel 4, 5 is expediently connected via separate exhaust gas lines to a respective part of the cylinders of the internal combustion engine, so that only the exhaust gas of the relevant cylinder is introduced into the respective spiral channel 4 or 5. This makes it possible to exploit in certain operating states of the internal combustion engine, a supercharger to increase the performance of the exhaust gas turbine.
- the two spiral channels 4 and 5 are advantageously carried out mutually almost str ⁇ mungs- or pressure-tight and each have a radial flow inlet cross-section 6 and 7 and a semi-axial flow inlet cross-section 8 and 9, via which the exhaust gas from the spiral channels 4 and 5 impinges on the turbine wheel 3 and this drives.
- the rotational movement of the turbine wheel 3 about the longitudinal loader axis 12 is transmitted via a shaft 13 to the compressor wheel in the exhaust gas turbocharger. After hitting the turbine wheel 3, the exhaust gas flows axially from the exhaust gas turbine 1 via an outflow channel 14.
- the first spiral channel 4 is assigned a radial flow inlet cross section 6 and a semi-axial flow inlet cross section 8.
- the second spiral channel 5 is assigned a radial flow inlet cross-section 7 and a semi-axial flow inlet cross-section 9.
- the flow inlet cross sections of each spiral channel extend in each case over an angular range of 180 ° about the turbine wheel 3rd
- a radial, extending over the entire circumference Leitgitterring 10 is arranged, which in particular has a plurality of evenly distributed over the circumference guide vanes, via which the flow of the exhaust gas can be positively influenced on the turbine wheel.
- the radial guide-grid ring 10 covers both the radial flow inlet cross section 6 of the first spiral channel 4 and the radial flow inlet cross section 7 of the second spiral channel 5.
- a circumferential, semi-axial Leitgitterring 11 is also in the semi-axial flow inlet cross sections 8 and 9 of the two spiral channels 4 and 5 introduced.
- the semi-axial Leitgitterring improves the flow of the turbine wheel 3 and can be performed either similar or different over both semi-axial flow inlet cross sections.
- the two Leitgitterringe 10 and 11 are advantageously fixed or invariable. However, it may also be expedient to design at least one of the guide ring rings to realize a variable turbine geometry adjustable, in particular to carry out with adjustable guide vanes.
- the two Leitgitterringe 10 and 11 are held on a circumferential, fixed housing wall 15, which is radially in the two spiral channels 4 and 5 extends and is arranged in the intermediate region between the two Leitgitterringen.
- the radially outer region of the housing-fixed wall 15 has a streamlined contour in order to allow optimum inflow into the radial or semi-axial flow inlet cross sections 6 and 7 or 8 and 9.
- the radial flow inlet cross sections 6 and 7 are axially limited on the housing-fixed wall 15 opposite end face of a second axially displaceable wall 16 which is designed to be displaceable in the direction of the longitudinal axis of the loader.
- the displaceable wall 16 is connected to a sliding sleeve 17, which is disposed in the Abstr ⁇ mkanal 14 a- xial displaceable and actuated via an actuating element.
- the displaceable wall 16 has on its side facing the housing 15 fixed side one or a plurality of receiving openings 18 which extend over the circumference of the wall 16 and extend in the axial direction.
- These receiving openings 18 are used in an axial approximation of the sliding wall 16 to the housing-fixed wall 15 for receiving the Leitgitterringes 10 and the vanes of the Leitgitterringes 10. In this way it is possible to reduce the distance between the walls 15 and 16 so far that both walls 15 and 16 are in contact with each other and the radial flow inlet cross-sections 6 and 7 are completely closed or up to a remaining gap. This allows the combination turbine to be reduced to a semi-axial turbine. About the insertion of the radial Leitgitterringes 10 in the receiving openings 18, the radial flow inlet cross sections 6 and 7 are continuously adjusted. In order to ensure an optimum flow onto the radial guide-grid ring 10 and the turbine wheel 3, regardless of the axial position of the adjustable wall 16, the adjustable bare wall 16 on its radially outer side a streamlined contour.
- the adjustable wall 16 can be displaced so far axially outward that the radial Leitgitterring 10 is not in contact with the wall 16 and given a direct obstacle-free flow path between the two spiral channels 4 and 5 and the discharge channel 14 is. In this way, a blow-off function can be realized, bypassing the flow path via the Leitgitterringe.
- the exhaust gas turbine 1 of the exhaust gas turbocharger is shown in section, the associated, connected via the shaft 13 to the turbine wheel compressor 20, however, is shown only schematically.
- the exhaust gas of the internal combustion engine 19 is supplied to the spiral channels 4 and 5 of the exhaust gas turbine 1, whereby the turbine wheel is set in motion and the Turbinenradamba is transmitted via the shaft 13 to the compressor wheel in the compressor 20.
- the intake combustion air is compressed to an increased pressure, then cooled in a charge air cooler 21 and finally fed to the cylinder inlets of the internal combustion engine 19 with a desired charge pressure.
- the engine 19 is designed as a four-cylinder engine with cylinders Z lr Z 2 , Z 3 and Z 4 , which are arranged in series.
- the exhaust gas of the outer cylinder Zi and Z 4 is combined and fed together to the first spiral channel 4 of the exhaust gas turbine 1.
- the exhaust gas of the middle cylinder Z 2 and Z 3 is summarized and fed to the second spiral channel 5.
- the two spiral channels 4 and 5 are fluid-tight against each other separated.
- a housing-fixed ring 22 is arranged coaxially to the loader axis in the turbine housing, on which radially outward separating tongues 23 and 24 extend in front of the Halbaxialgitter 11, via which a separation of Str ⁇ mungswege in the spiral channels 4 and 5 is to produce. Furthermore, with the separating tongues 23 and 24 cooperating separating tongues 25 and 26 are provided, which are integrally formed with the spiral channels 4 and 5 and have the function of mutual sealing by means of a minimum gap to the wall 16. Each spiral channel 4 or 5 opens over an angular section of 180 ° in the inflow region to the turbine wheel.
- Fig. 3 corresponds to that of FIG. 2, but with the difference that in Fig. 3, the internal combustion engine 19 is designed as a six-cylinder in-line engine with cylinders ___, to Z 6 .
- the exhaust gases of the first three consecutive cylinders Z_ . to Z 3 are summarized and fed to the first spiral channel 4 of the exhaust gas turbine 1.
- the exhaust gases of the successive, remaining cylinders Z to Z s are also combined and fed to the second spiral channel 5. Also on this summary is a cheap shock charge to realize.
- a further exhaust gas turbine 1 is shown in a modified embodiment.
- the exhaust gas turbine 1 is designed as a radial turbine with two radial flow inlet cross sections 6 and 7, which are respectively associated with the spiral channels 4 and 5.
- both radial flow inlet cross sections 6 and 7 there is a radial Leitgitterring 10 which is held on the housing-fixed wall 15 and received in a receiving opening 18 in the axially displaceable wall 16.
- the wall 16 is axially displaceable and coupled to the sliding sleeve 17.
- the displaceable wall 16 is to be adjusted between a closed position, in which both radial flow inlet cross sections 6 and 7 are closed, and a maximum opening position, in which the radial flow inlet cross sections with the guide grid ring 10 therein occupy their maximum cross section.
- the guide grid 16 can also be moved so far outward that the radial guide-grid ring 10 without contact to the sliding wall 16, whereby a direct Str ⁇ mungsweg between the spiral channels 4 and 5 and the Abstr ⁇ mkanal 14 is formed to realize a Abblasungs- function.
- more than two spiral channels are provided in the exhaust gas turbine, for example, three spiral channels, each of which the exhaust gas of a certain number of cylinders of the internal combustion engine is to be supplied and each of which opens a defined angle segment in the Str ⁇ mungseintrittsquer- section to the turbine wheel.
Abstract
Description
Claims
Applications Claiming Priority (3)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
DE10212675A DE10212675B4 (en) | 2002-03-22 | 2002-03-22 | Exhaust gas turbocharger in an internal combustion engine |
DE10212675 | 2002-03-22 | ||
PCT/EP2003/000826 WO2003080999A1 (en) | 2002-03-22 | 2003-01-28 | Exhaust gas turbocharger in an internal combustion engine |
Publications (1)
Publication Number | Publication Date |
---|---|
EP1488079A1 true EP1488079A1 (en) | 2004-12-22 |
Family
ID=27798026
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
EP03706391A Withdrawn EP1488079A1 (en) | 2002-03-22 | 2003-01-28 | Exhaust gas turbocharger in an internal combustion engine |
Country Status (5)
Country | Link |
---|---|
US (1) | US7047739B2 (en) |
EP (1) | EP1488079A1 (en) |
JP (1) | JP4085280B2 (en) |
DE (1) | DE10212675B4 (en) |
WO (1) | WO2003080999A1 (en) |
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DE19816645B4 (en) * | 1998-04-15 | 2005-12-01 | Daimlerchrysler Ag | Turbocharger turbine |
DE19905637C1 (en) * | 1999-02-11 | 2000-08-31 | Daimler Chrysler Ag | Exhaust gas turbocharger for an internal combustion engine |
US6715288B1 (en) * | 1999-05-27 | 2004-04-06 | Borgwarner, Inc. | Controllable exhaust gas turbocharger with a double-fluted turbine housing |
DE19961613A1 (en) * | 1999-12-21 | 2001-07-19 | Daimler Chrysler Ag | Exhaust gas turbine of an exhaust gas turbocharger for an internal combustion engine |
DE10029807C1 (en) * | 2000-06-16 | 2002-03-21 | Daimler Chrysler Ag | Exhaust gas turbocharger for IC engine has turbine wheel provided with hollow space between hub base and hub envelope |
DE10152804B4 (en) * | 2001-10-25 | 2016-05-12 | Daimler Ag | Internal combustion engine with an exhaust gas turbocharger and an exhaust gas recirculation device |
DE10228003A1 (en) * | 2002-06-22 | 2004-01-15 | Daimlerchrysler Ag | Turbine for an exhaust gas turbocharger |
-
2002
- 2002-03-22 DE DE10212675A patent/DE10212675B4/en not_active Expired - Fee Related
-
2003
- 2003-01-28 EP EP03706391A patent/EP1488079A1/en not_active Withdrawn
- 2003-01-28 JP JP2003578707A patent/JP4085280B2/en not_active Expired - Fee Related
- 2003-01-28 WO PCT/EP2003/000826 patent/WO2003080999A1/en not_active Application Discontinuation
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2004
- 2004-09-21 US US10/946,375 patent/US7047739B2/en not_active Expired - Fee Related
Non-Patent Citations (1)
Title |
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See references of WO03080999A1 * |
Also Published As
Publication number | Publication date |
---|---|
US7047739B2 (en) | 2006-05-23 |
JP4085280B2 (en) | 2008-05-14 |
JP2005527728A (en) | 2005-09-15 |
DE10212675B4 (en) | 2006-05-18 |
DE10212675A1 (en) | 2003-10-02 |
US20050056015A1 (en) | 2005-03-17 |
WO2003080999A1 (en) | 2003-10-02 |
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