EP3008292B1 - Turbocharger with a radial/axial turbine wheel - Google Patents
Turbocharger with a radial/axial turbine wheel Download PDFInfo
- Publication number
- EP3008292B1 EP3008292B1 EP14719804.8A EP14719804A EP3008292B1 EP 3008292 B1 EP3008292 B1 EP 3008292B1 EP 14719804 A EP14719804 A EP 14719804A EP 3008292 B1 EP3008292 B1 EP 3008292B1
- Authority
- EP
- European Patent Office
- Prior art keywords
- exhaust
- sub
- turbine wheel
- rear wall
- gas turbocharger
- 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.)
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- 238000000926 separation method Methods 0.000 claims description 11
- 239000011241 protective layer Substances 0.000 claims description 8
- XLYOFNOQVPJJNP-UHFFFAOYSA-N water Substances O XLYOFNOQVPJJNP-UHFFFAOYSA-N 0.000 claims description 7
- 230000007704 transition Effects 0.000 claims description 4
- 238000005260 corrosion Methods 0.000 claims description 3
- 230000007797 corrosion Effects 0.000 claims description 3
- 239000000463 material Substances 0.000 claims description 3
- 230000003647 oxidation Effects 0.000 claims description 3
- 238000007254 oxidation reaction Methods 0.000 claims description 3
- 239000007789 gas Substances 0.000 description 71
- PXHVJJICTQNCMI-UHFFFAOYSA-N Nickel Chemical compound [Ni] PXHVJJICTQNCMI-UHFFFAOYSA-N 0.000 description 4
- 239000000498 cooling water Substances 0.000 description 3
- 238000001816 cooling Methods 0.000 description 2
- 230000001419 dependent effect Effects 0.000 description 2
- 229910052759 nickel Inorganic materials 0.000 description 2
- 238000013021 overheating Methods 0.000 description 2
- 240000001439 Opuntia Species 0.000 description 1
- 235000004727 Opuntia ficus indica Nutrition 0.000 description 1
- 230000002411 adverse Effects 0.000 description 1
- 238000011161 development Methods 0.000 description 1
- 230000018109 developmental process Effects 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 238000009434 installation Methods 0.000 description 1
- 238000004519 manufacturing process Methods 0.000 description 1
- 239000002184 metal Substances 0.000 description 1
- 229910052751 metal Inorganic materials 0.000 description 1
- 230000000930 thermomechanical effect Effects 0.000 description 1
Images
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
- F01D1/00—Non-positive-displacement machines or engines, e.g. steam turbines
- F01D1/18—Non-positive-displacement machines or engines, e.g. steam turbines without stationary working-fluid guiding means
- F01D1/22—Non-positive-displacement machines or engines, e.g. steam turbines without stationary working-fluid guiding means traversed by the working-fluid substantially radially
-
- 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
- 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
- F01D25/08—Cooling; Heating; Heat-insulation
- F01D25/12—Cooling
-
- 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
- F01D25/16—Arrangement of bearings; Supporting or mounting bearings in casings
-
- 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 an exhaust gas turbocharger having a radial-axial turbine wheel.
- An exhaust gas turbocharger which contains such a radial-axial turbine wheel.
- the turbine housing has a guide element which forms at least part of the rear wall of an inclined or obliquely formed spiral.
- WO 2005/119030 A1 an exhaust gas turbine with a turbine housing and arranged in the turbine housing turbine wheel, wherein the turbine wheel has a hub.
- the turbine housing with a gas inlet-side housing part to the left of the turbine wheel and the gas outlet side housing part together with the hub of the turbine wheel forms a flow channel in which flow through hot exhaust gases during operation of the exhaust gas turbocharger.
- a cooling channel for cooling the hub of the turbine wheel in the turbine housing is arranged opposite a rear wall of the hub of the turbine wheel facing away from the flow channel.
- the FIG. 1 shows a sectional view of this known exhaust gas turbocharger.
- the known exhaust gas turbocharger 1 has a turbine housing 10 with a spiral 16.
- a radial-axial turbine wheel 12 is disposed on a shaft 30.
- the shaft 30 is mounted in a bearing housing 20.
- a guide element 24 is provided, which is a heat shield. This is designed such that it forms a rear wall 26 or a portion 28 of the rear wall of the spiral 16, wherein the part the rear wall or the rear wall is inclined at an inclination angle ⁇ in the direction of the bearing housing.
- the guide element 24 may be pushed or plugged in an end region 32 on a shoulder 34 of the bearing housing.
- the known exhaust-gas turbocharger has a tongue element 14, which is preferably pulled close to the leading edge 18 of the turbine wheel 12, so that the distance a between the tongue element 14 and the leading edge 18 of the turbine wheel 12 is small.
- the heat shield 24 of the exhaust gas turbocharger described above is usually made of sheet metal. This has the disadvantage that the heat shield is additionally subject to deformation during installation due to pressure influences and during operation of the exhaust gas turbocharger due to thermal influences. These can adversely affect the flow of the turbine wheel and thus its thermodynamics. Furthermore, due to these deformations, an undesired collision of the heat shield with the turbine wheel may occur. Furthermore, thermomechanical disadvantages with respect to the functionality and the service life of the exhaust-gas turbocharger occur as a result of the aforementioned deformations.
- the object of the invention is to provide an equipped with a radial-axial turbine exhaust gas turbocharger, in which the disadvantages mentioned above do not occur.
- An exhaust gas turbocharger with the features specified in claim 1 includes a shaft having an axis of rotation, a arranged in a turbine housing and rotatably connected to the shaft radial-axial turbine wheel and a turbine housing adjacent bearing housing, which has a side facing the turbine housing side wall.
- the radial-axial turbine wheel has a back wall with a corner disposed at the radially outer end of the rear wall, with an upper surface of the turbine wheel extending obliquely radially outwardly from the corner of the rear wall.
- a partial region of the turbine housing facing side wall of the bearing housing forms a portion of the rear wall of the turbine housing.
- the partial region of the bearing housing which forms a partial region of the rear wall of the turbine housing has two subsections, of which the first subsection extends obliquely to the axis of rotation of the shaft in the inflow direction of an exhaust gas stream guided into the turbine housing, and the second subsection extends in the radial direction to the axis of rotation of the shaft and parallel to the rear wall of the shaft Turbine wheel runs.
- the two sections are connected to each other via an exhaust flow separation edge of the bearing housing, wherein the exhaust gas flow-off edge has a corner connected to the second section via a flank.
- the first section and the flank includes a corner angle and between the second section and the flank a curved transition region is provided.
- the top of the turbine wheel, from the corner of the exhaust gas flow-off edge in the inflow direction of the exhaust gas flow, at a distance and the flank is parallel to the top of the turbine wheel.
- Such an exhaust gas turbocharger requires no heat shield, which could deform during assembly and operation of the exhaust gas turbocharger by pressure influences and thermal influences in an undesirable manner. This favors the flow of the turbine wheel and improves its thermodynamics. Furthermore, in an exhaust-gas turbocharger with the features according to the invention in its operation, no undesired collisions with the turbine wheel rotating at high speed can occur. This improves the functionality of the exhaust gas turbocharger and increases its service life. Further, in an exhaust gas turbocharger with the features according to the invention, the cavity between the rear wall of the turbine wheel and the adjacent portion of the side wall of the bearing housing, d. H. the Rabineraum be kept small, so that even in this area an occurrence of an undesirable flow with the exhaust stream can be at least greatly reduced.
- FIG. 2 shows a sectional view of a portion of an exhaust gas turbocharger according to an embodiment of the invention.
- This exhaust gas turbocharger has a turbine housing 10 with a spiral 16, which encloses an inflow region 17 for the exhaust gas flow.
- a radial-axial turbine wheel 12 connected to the shaft in a rotationally fixed manner is arranged on a shaft 30.
- the shaft 30 is mounted in a bearing housing 20 which is adjacent to the turbine housing 10.
- the bearing housing 20 has a turbine housing 10 facing side wall.
- the turbine wheel 12 has a rear wall 13 and an upper side OS.
- a portion of the turbine housing facing side wall of the bearing housing forms a portion of the rear wall of the turbine housing.
- the partial region of the bearing housing which forms a partial region of the rear wall of the turbine housing has two partial sections TA1 and TA2.
- the first portion TA1 extends obliquely to the axis of rotation 30a of the shaft 30 in the inflow ZR of the guided into the turbine housing hot exhaust gas stream.
- the second subsection TA2 extends in the radial direction R to the axis of rotation 30a of the shaft 30 and also parallel to the rear wall 13 of the turbine wheel 12.
- the two subsections TA1 and TA2 are connected to one another via an exhaust gas flow separation edge 35 of the bearing housing 20. Between the rear wall 13 of the turbine wheel 12 and the second partial section TA2 extending parallel thereto, there is the Ra07raum 29th
- a water core 36 is disposed, which is the exhaust gas flow edge 35 adjacent. This advantageously has the effect that, during operation of the exhaust-gas turbocharger, the region of the exhaust gas flow-off edge 35 is cooled by a water flow conducted through the water core 36.
- the turbine housing facing side wall of the bearing housing in the region of the first section TA1 and the second section TA2 is coated with a protective layer.
- This protective layer preferably consists of a high temperature, oxidation and corrosion resistant material, such as nickel. Because of this protective layer, said subsections TA1 and TA2 and in particular also the exhaust gas flow tearing edge 35 of the bearing housing connecting the two subsections are protected against the high temperatures occurring in these regions during operation of the exhaust gas turbocharger, so that the probability of deformation of these regions is reduced.
- the provided on the bearing housing 20 Abgasströmungsabrisskante 35 is designed such that it withstands the high loads occurring during operation of the exhaust gas turbocharger and that occurring in the region of this Abgasströmungsabrisskante turbulence of the supplied hot exhaust gas flow are kept small, so that the hydrodynamic efficiency of the exhaust gas turbocharger can be increased. This will be explained below with reference to FIGS. 3 and 4 explained in more detail.
- FIG. 3 shows a sketch to illustrate the flow of the turbine wheel of the exhaust gas turbocharger with the hot exhaust gas flow.
- the hot exhaust gas stream enters the nozzle formed between the side wall of the bearing housing 20 and the turbine housing, not shown, and is supplied along the section TA1 to the turbine wheel 12 and its vanes. Thereby, the turbine wheel is rotated together with the shaft 30, wherein this rotation takes place about the rotation axis 30a.
- the bearing housing 20 has an exhaust gas flow separation edge 35 between the first subsection TA1 and the second subsection TA2.
- This exhaust gas flow edge 35 and the adjacent turbine wheel 12 are designed and arranged relative to one another in such a way that the turbulences of the exhaust gas flow which occur in the region of the exhaust gas flow separation edge 35 be kept small and that the Abgasströmungsabrisskante 35 withstand the loads occurring during operation of the exhaust gas turbocharger. Also contributing to this is the water core 36 positioned near the exhaust gas flow tearing edge 35, through which cooling water is passed during operation of the exhaust gas turbocharger which cools the region of the exhaust gas flow tearing edge 35.
- the turbine wheel 12 at the radially upper end of its rear wall 13 has a corner E2, from which the top OS of the turbine wheel or the top of its blades obliquely, with respect to the axis of rotation 30a in the radial direction (R) to the outside , ie in the presentation of the FIG. 2 up, runs.
- the corner E2 of the rear wall 13 of the turbine wheel 12 has a distance b in the radial direction from a radially arranged above corner E1 of the Abgasströmungsabrisskante 35 of the bearing housing 20 in the radial direction.
- the upper side OS of the turbine wheel 12 has a distance c from the corner E1 of the exhaust gas flow separation edge 35 of the bearing housing in the inflow direction ZR of the exhaust gas flow.
- the rear wall 13 of the turbine wheel 12 has a distance a from the second partial section TA2 running parallel thereto.
- the first section TA1 of the bearing housing 20 also extends in the inflow ZR of the exhaust stream, has an angle ⁇ relative to the radial direction R and ends at the corner E1 of the exhaust flow separation edge 35 of the bearing housing.
- corner E1 of the Abgasströmungsabrisskante 35 and the second portion TA2 is an outgoing of the corner E1 edge F which is connected to the second portion TA2 via a bent transition region U formed.
- the flank F runs parallel to the top side OS of the turbine wheel 12.
- the first section TA1 and the flank F At the corner E1 of the exhaust gas flow edge 35, a corner angle ⁇ is included.
- the water core 36 through which cooling water flows during operation of the exhaust gas turbocharger, extends into the immediate vicinity of the Abgasströmungsabrisskante 35, so that it is cooled by the cooling water in operation and can not be destroyed by overheating.
- the side wall of the bearing housing 20 facing the turbine housing 10 is provided with a protective layer in the region of the first part section TA1, the second part section TA2 and the flank F.
- This protective layer is preferably made of a high temperature, oxidation and corrosion resistant material, such as nickel.
- the distance b of the corner E1 of the Abgasströmungsabrisskante 35 from the corner E2 of the upper end portion of the rear wall 13 of the turbine wheel 12 in the radial direction is in a defined ratio to the measured in the radial direction R diameter DTR of the rear wall 13 of the turbine wheel 12. It is preferably: 0.005 ⁇ b / DTR ⁇ 0.025.
- the distance a between the rear wall 13 of the turbine wheel 12 and the second portion TA2 is also in a defined ratio to the diameter measured in the radial direction DTR of the rear wall 13 of the turbine wheel 12. It also applies here preferably the following relationship: 0.005 ⁇ a / DTR ⁇ 0.025.
- the invention provides after all an exhaust gas turbocharger, which is equipped with an axial-radial turbine wheel, in which the exhaust gas flow in the turbine housing without use of a separate guide element is guided through a nozzle to the turbine wheel.
- a side wall of this nozzle is from a first Part of the section of the turbine housing facing side wall of the bearing housing formed, which extends in the inflow direction of the exhaust stream.
- the other side wall of the nozzle is formed by a wall of the turbine housing.
- the first section TA1 of the turbine housing facing side wall of the bearing housing is connected via an exhaust gas flow edge 35 with a second portion TA2, which runs parallel to the rear wall of the turbine wheel.
- Such a design of the side facing the turbine housing side wall of the bearing housing creates the conditions that the Abgasströmungsabrisskante the bearing housing withstand the high loads occurring during operation of the exhaust gas turbocharger, so that the thermodynamic efficiency of the exhaust gas turbocharger can be increased. If, in addition to this embodiment of the turbine housing facing side wall of the bearing housing one or more of the features specified in the dependent claims used, then the functionality of the exhaust gas turbocharger is further increased during operation. Contributing in particular the shape of the bearing housing in the region of the Abgasstromabrißkante, the positioning of the water core, the use of a protective layer and the dimensioning of the distances a and b described above at.
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Supercharger (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
Description
Die Erfindung betrifft einen Abgasturbolader, welcher ein Radial-Axial-Turbinenrad aufweist.The invention relates to an exhaust gas turbocharger having a radial-axial turbine wheel.
Aus der
Weiterhin offenbart das Dokument
Die
Das Hitzeschild 24 des vorstehend beschriebenen Abgasturboladers besteht in der Regel aus Blech. Dies hat den Nachteil, dass das Hitzeschild während der Montage durch Druckeinflüsse und im Betrieb des Abgasturboladers zusätzlich durch thermische Einflüsse Verformungen unterliegt. Diese können die Anströmung des Turbinenrades und damit dessen Thermodynamik negativ beeinflussen. Des Weiteren kann es aufgrund dieser Verformungen zu einer unerwünschten Kollision des Hitzeschildes mit dem Turbinenrad kommen. Ferner kommt es aufgrund der genannten Verformungen zu thermomechanischen Nachteilen in Bezug auf die Funktionalität und die Lebensdauer des Abgasturboladers. Fertigungsbedingt entsteht an der dem Turbinenradrücken nächstgelegenen Stelle des Hitzeschildes ein Eckenradius, der die Anströmung des Turbinenrades und damit die Thermodynamik des Abgasturboladers negativ beeinflusst, da die Abgasströmung nicht sauber ablöst bzw. abreißt. Des Weiteren kommt es in der Praxis zu einer unerwünschten Durchströmung des Hohlraumes zwischen dem Rücken des Turbinenrades und dem Hitzeschild, welche ebenfalls mit Verlusten verbunden ist. Ferner muss aufgrund der genannten, im Betrieb auftretenden temperaturbedingten Verformungen des Hitzeschildes ein vergleichsweise großer Radrückenraum vorgesehen sein. Auch dies führt im Betrieb zu einer starken und ungünstigen Durchströmung mit heißem Abgas.The
Die Aufgabe der Erfindung besteht darin, einen mit einem Radial-Axial-Turbinenrad ausgestatteten Abgasturbolader anzugeben, bei dem die vorstehend angegebenen Nachteile nicht auftreten.The object of the invention is to provide an equipped with a radial-axial turbine exhaust gas turbocharger, in which the disadvantages mentioned above do not occur.
Diese Aufgabe wird durch einen Abgasturbolader mit den im Patentanspruch 1 angegebenen Merkmalen gelöst. Vorteilhafte Ausgestaltungen und Weiterbildungen der Erfindung sind in den abhängigen Patentansprüchen angegeben.This object is achieved by an exhaust gas turbocharger with the features specified in claim 1. Advantageous embodiments and further developments of the invention are specified in the dependent claims.
Ein Abgasturbolader mit den im Anspruch 1 angegebenen Merkmalen enthält eine eine Drehachse aufweisende Welle, ein in einem Turbinengehäuse angeordnetes und mit der Welle drehfest verbundenes Radial-Axial-Turbinenrad und ein dem Turbinengehäuse benachbartes Lagergehäuse, welches eine dem Turbinengehäuse zugewandte Seitenwand aufweist. Das Radial-Axial-Turbinenrad weist eine Rückwand, mit einer an dem in Radialrichtung äußeren Ende der Rückwand angeordneten Ecke auf, wobei eine Oberseite des Turbinenrades ausgehend von der Ecke der Rückwand schräg in Radialrichtung nach außen verläuft. Dabei bildet ein Teilbereich der dem Turbinengehäuse zugewandten Seitenwand des Lagergehäuses einen Teilbereich der Rückwand des Turbinengehäuses. Der einen Teilbereich der Rückwand des Turbinengehäuses bildende Teilbereich des Lagergehäuses weist zwei Teilabschnitte auf, von denen der erste Teilabschnitt schräg zur Drehachse der Welle in Zuströmrichtung eines in das Turbinengehäuse geleiteten Abgasstromes verläuft und der zweite Teilabschnitt in Radialrichtung zur Drehachse der Welle und parallel zur Rückwand des Turbinenrades verläuft. Die beiden Teilabschnitte sind über eine Abgasströmungsabrisskante des Lagergehäuses miteinander verbunden, wobei die Abgasströmungsabrisskante eine Ecke aufweist, die mit dem zweiten Teilabschnitt über eine Flanke verbunden ist. Dabei schließt der erste Teilabschnitt und die Flanke einen Eckwinkel ein und zwischen dem zweiten Teilabschnitt und der Flanke ist ein gebogener Übergangsbereich vorgesehen. Des Weiteren weist die Oberseite des Turbinenrades, von der Ecke der Abgasströmungsabrisskante in Zuströmrichtung des Abgasstromes, einen Abstand auf und die Flanke verläuft parallel zur Oberseite des Turbinenrades.An exhaust gas turbocharger with the features specified in claim 1 includes a shaft having an axis of rotation, a arranged in a turbine housing and rotatably connected to the shaft radial-axial turbine wheel and a turbine housing adjacent bearing housing, which has a side facing the turbine housing side wall. The radial-axial turbine wheel has a back wall with a corner disposed at the radially outer end of the rear wall, with an upper surface of the turbine wheel extending obliquely radially outwardly from the corner of the rear wall. In this case, a partial region of the turbine housing facing side wall of the bearing housing forms a portion of the rear wall of the turbine housing. The partial region of the bearing housing which forms a partial region of the rear wall of the turbine housing has two subsections, of which the first subsection extends obliquely to the axis of rotation of the shaft in the inflow direction of an exhaust gas stream guided into the turbine housing, and the second subsection extends in the radial direction to the axis of rotation of the shaft and parallel to the rear wall of the shaft Turbine wheel runs. The two sections are connected to each other via an exhaust flow separation edge of the bearing housing, wherein the exhaust gas flow-off edge has a corner connected to the second section via a flank. In this case, the first section and the flank includes a corner angle and between the second section and the flank a curved transition region is provided. Furthermore, the top of the turbine wheel, from the corner of the exhaust gas flow-off edge in the inflow direction of the exhaust gas flow, at a distance and the flank is parallel to the top of the turbine wheel.
Ein derartiger Abgasturbolader benötigt kein Hitzeschild, das sich während der Montage und im Betrieb des Abgasturboladers durch Druckeinflüsse und thermische Einflüsse in unerwünschter Weise verformen könnte. Dies begünstigt die Anströmung des Turbinenrades und verbessert dessen Thermodynamik. Ferner können bei einem Abgasturbolader mit den erfindungsgemäßen Merkmalen in dessen Betrieb keine unerwünschten Kollisionen mit dem sich mit hoher Geschwindigkeit drehenden Turbinenrad auftreten. Dies verbessert die Funktionalität des Abgasturboladers und erhöht dessen Lebensdauer. Ferner kann bei einem Abgasturbolader mit den erfindungsgemäßen Merkmalen der Hohlraum zwischen der Rückwand des Turbinenrades und dem benachbarten Teilabschnitt der Seitenwand des Lagergehäuses, d. h. der Radrückenraum, klein gehalten werden, so dass auch in diesem Bereich ein Auftreten einer unerwünschten Durchströmung mit dem Abgasstrom zumindest stark reduziert werden kann.Such an exhaust gas turbocharger requires no heat shield, which could deform during assembly and operation of the exhaust gas turbocharger by pressure influences and thermal influences in an undesirable manner. This favors the flow of the turbine wheel and improves its thermodynamics. Furthermore, in an exhaust-gas turbocharger with the features according to the invention in its operation, no undesired collisions with the turbine wheel rotating at high speed can occur. This improves the functionality of the exhaust gas turbocharger and increases its service life. Further, in an exhaust gas turbocharger with the features according to the invention, the cavity between the rear wall of the turbine wheel and the adjacent portion of the side wall of the bearing housing, d. H. the Radrückenraum be kept small, so that even in this area an occurrence of an undesirable flow with the exhaust stream can be at least greatly reduced.
Weitere vorteilhafte Eigenschaften der Erfindung ergeben sich aus deren nachfolgender beispielhafter Erläuterung anhand der
- Figur 2
- eine Schnittansicht eines Teils eines Abgasturboladers gemäß einem Ausführungsbeispiel für die Erfindung,
- Figur 3
- eine Skizze zur Veranschaulichung der Anströmung des Turbinenrades mit dem Abgasstrom und
- Figur 4
- eine vergrößerte Darstellung des Detail Z von
Figur 3 .
- FIG. 2
- a sectional view of a portion of an exhaust gas turbocharger according to an embodiment of the invention,
- FIG. 3
- a sketch illustrating the flow of the turbine wheel with the exhaust stream and
- FIG. 4
- an enlarged view of detail Z of
FIG. 3 ,
Die
Ein Teilbereich der dem Turbinengehäuse zugewandten Seitenwand des Lagergehäuses bildet einen Teilbereich der Rückwand des Turbinengehäuses. Der einen Teilbereich der Rückwand des Turbinengehäuses bildende Teilbereich des Lagergehäuses weist zwei Teilabschnitte TA1 und TA2 auf. Der erste Teilabschnitt TA1 verläuft schräg zur Drehachse 30a der Welle 30 in Zuströmrichtung ZR des in das Turbinengehäuse geleiteten heißen Abgasstromes . Der zweite Teilabschnitt TA2 verläuft in Radialrichtung R zur Drehachse 30a der Welle 30 und auch parallel zur Rückwand 13 des Turbinenrades 12. Die beiden Teilabschnitte TA1 und TA2 sind über eine Abgasströmungsabrisskante 35 des Lagergehäuses 20 miteinander verbunden. Zwischen der Rückwand 13 des Turbinenrades 12 und dem parallel dazu verlaufenden zweiten Teilabschnitt TA2 befindet sich der Radrückenraum 29.A portion of the turbine housing facing side wall of the bearing housing forms a portion of the rear wall of the turbine housing. The partial region of the bearing housing which forms a partial region of the rear wall of the turbine housing has two partial sections TA1 and TA2. The first portion TA1 extends obliquely to the axis of
Innerhalb des Lagergehäuses 20 ist ein Wasserkern 36 angeordnet, welcher der Abgasströmungsabrisskante 35 benachbart ist. Dies bewirkt in vorteilhafter Weise, dass im Betrieb des Abgasturboladers der Bereich der Abgasströmungsabrisskante 35 durch einen durch den Wasserkern 36 geleiteten Wasserstrom gekühlt wird.Within the bearing
Des Weiteren ist die dem Turbinengehäuse zugewandte Seitenwand des Lagergehäuses im Bereich des ersten Teilabschnittes TA1 und des zweiten Teilabschnittes TA2 mit einer Schutzschicht überzogen. Diese Schutzschicht besteht bevorzugt aus einem hochtemperatur-, oxidations- und korrosionsbeständigen Material, beispielsweise Nickel. Aufgrund dieser Schutzschicht sind die genannten Teilabschnitte TA1 und TA2 und insbesondere auch die die beiden Teilabschnitte verbindende Abgasströmungsabrisskante 35 des Lagergehäuses gegen die im Betrieb des Abgasturboladers in diesen Bereichen auftretenden hohen Temperaturen geschützt, so dass die Wahrscheinlichkeit einer Deformation dieser Bereiche reduziert ist.Furthermore, the turbine housing facing side wall of the bearing housing in the region of the first section TA1 and the second section TA2 is coated with a protective layer. This protective layer preferably consists of a high temperature, oxidation and corrosion resistant material, such as nickel. Because of this protective layer, said subsections TA1 and TA2 and in particular also the exhaust gas
Des Weiteren sind in der
Die am Lagergehäuse 20 vorgesehene Abgasströmungsabrisskante 35 ist derart ausgebildet, dass sie den im Betrieb des Abgasturboladers auftretenden hohen Belastungen standhält und dass die im Bereich dieser Abgasströmungsabrisskante auftretenden Verwirbelungen des zugeführten heißen Abgasstromes klein gehalten werden, so dass der hydrodynamische Wirkungsgrad des Abgasturboladers gesteigert werden kann. Dies wird nachfolgend anhand der
Die
Diese Abgasströmungsabrisskante 35 und das dieser benachbarte Turbinenrad 12 sind derart ausgebildet und relativ zueinander derart angeordnet, dass die im Bereich der Abgasströmungsabrisskante 35 auftretenden Verwirbelungen des Abgasstromes klein gehalten werden und dass die Abgasströmungsabrisskante 35 den im Betrieb des Abgasturboladers auftretenden Belastungen standhält. Dazu trägt auch der in der Nähe der Abgasströmungsabrisskante 35 positionierte Wasserkern 36 bei, durch welchen im Betrieb des Abgasturboladers Kühlwasser geleitet wird, das den Bereich der Abgasströmungsabrisskante 35 kühlt.This exhaust
Der in der
Aus der
Zwischen der Ecke E1 der Abgasströmungsabrisskante 35 und dem zweiten Teilabschnitt TA2 ist eine von der Ecke E1 ausgehende Flanke F vorgesehen, welche mit dem zweiten Teilabschnitt TA2 über einen gebogen ausgebildeten Übergangsbereich U verbunden ist. Die Flanke F verläuft parallel zur Oberseite OS des Turbinenrades 12. Der erste Teilabschnitt TA1 und die Flanke F schließen an der Ecke E1 der Abgasströmungsabrisskante 35 einen Eckwinkel α ein.Between the corner E1 of the
Der Wasserkern 36, durch welchen im Betrieb des Abgasturboladers Kühlwasser fließt, reicht bis in die unmittelbare Nähe der Abgasströmungsabrisskante 35, so dass diese im Betrieb durch das Kühlwasser gekühlt wird und nicht durch eine Überhitzung zerstört werden kann.The
Um eine Überhitzung der Abgasströmungsabrisskante 35 zu verhindern, ist des Weiteren die dem Turbinengehäuse 10 zugewandte Seitenwand des Lagergehäuses 20 im Bereich des ersten Teilabschnittes TA1, des zweiten Teilabschnittes TA2 und der Flanke F mit einer Schutzschicht versehen. Diese Schutzschicht besteht vorzugsweise aus einem hochtemperatur-, oxidations- und korrosionsbeständigen Material, beispielsweise Nickel.In order to prevent overheating of the exhaust gas flow tear-
Der Abstand b der Ecke E1 der Abgasströmungsabrisskante 35 von der Ecke E2 des oberen Endbereiches der Rückwand 13 des Turbinenrades 12 in Radialrichtung steht in einem definierten Verhältnis zum in Radialrichtung R gemessenen Durchmesser DTR der Rückwand 13 des Turbinenrades 12. Es gilt vorzugsweise:
Der Abstand a zwischen der Rückwand 13 des Turbinenrades 12 und dem zweiten Teilabschnitt TA2 steht ebenfalls in einem definierten Verhältnis zum in Radialrichtung gemessenen Durchmesser DTR der Rückwand 13 des Turbinenrades 12. Es gilt auch hier vorzugsweise folgende Beziehung:
Die Erfindung stellt nach alledem einen Abgasturbolader bereit, welcher mit einem Axial-Radial-Turbinenrad ausgestattet ist, bei welchem die Abgasströmung im Turbinengehäuse ohne Verwendung eines gesonderten Leitelementes durch eine Düse zum Turbinenrad geführt wird. Eine Seitenwand dieser Düse wird von einem ersten Teilabschnitt der dem Turbinengehäuse zugewandten Seitenwand des Lagergehäuses gebildet, welcher in Zuströmrichtung des Abgasstromes verläuft. Die andere Seitenwand der Düse wird von einer Wand des Turbinengehäuses gebildet. Der erste Teilabschnitt TA1 der dem Turbinengehäuse zugewandten Seitenwand des Lagergehäuses ist über eine Abgasströmungsabrisskante 35 mit einem zweiten Teilabschnitt TA2 verbunden, welcher parallel zur Rückwand des Turbinenrades verläuft.The invention provides after all an exhaust gas turbocharger, which is equipped with an axial-radial turbine wheel, in which the exhaust gas flow in the turbine housing without use of a separate guide element is guided through a nozzle to the turbine wheel. A side wall of this nozzle is from a first Part of the section of the turbine housing facing side wall of the bearing housing formed, which extends in the inflow direction of the exhaust stream. The other side wall of the nozzle is formed by a wall of the turbine housing. The first section TA1 of the turbine housing facing side wall of the bearing housing is connected via an exhaust
Eine derartige Ausbildung der dem Turbinengehäuse zugewandten Seitenwand des Lagergehäuses schafft die Voraussetzungen dafür, dass die Abgasströmungsabrisskante des Lagergehäuses den im Betrieb des Abgasturboladers auftretenden hohen Belastungen standhält, so dass der thermodynamische Wirkungsgrad des Abgasturboladers gesteigert werden kann. Werden zusätzlich zu dieser Ausgestaltung der dem Turbinengehäuse zugewandten Seitenwand des Lagergehäuses eine oder mehrere der in den abhängigen Ansprüchen angegebenen Merkmale eingesetzt, dann wird die Funktionalität des Abgasturboladers im Betrieb weiter erhöht. Dazu tragen insbesondere die Formgebung des Lagergehäuses im Bereich der Abgasströmungsabrisskante, die Positionierung des Wasserkernes, die Verwendung einer Schutzschicht und die Dimensionierung der oben beschriebenen Abstände a und b bei.Such a design of the side facing the turbine housing side wall of the bearing housing creates the conditions that the Abgasströmungsabrisskante the bearing housing withstand the high loads occurring during operation of the exhaust gas turbocharger, so that the thermodynamic efficiency of the exhaust gas turbocharger can be increased. If, in addition to this embodiment of the turbine housing facing side wall of the bearing housing one or more of the features specified in the dependent claims used, then the functionality of the exhaust gas turbocharger is further increased during operation. Contributing in particular the shape of the bearing housing in the region of the Abgasstromabrißkante, the positioning of the water core, the use of a protective layer and the dimensioning of the distances a and b described above at.
Untersuchungen haben gezeigt, dass die Funktionalität eines Abgasturboladers gemäß der Erfindung im Betrieb auch beim Vorliegen von hohen Abgaseintrittstemperaturen gegeben ist, die größer sind als 1050°C.Studies have shown that the functionality of an exhaust gas turbocharger according to the invention in operation is given even in the presence of high exhaust gas inlet temperatures which are greater than 1050 ° C.
Claims (11)
- Exhaust-gas turbocharger having a shaft (30) which has an axis of rotation (30a), having a radial-axial turbine wheel (12) which is arranged in a turbine housing (10) and which is connected rotationally conjointly to the shaft (30), and having a bearing housing (20) which is arranged adjacent to the turbine housing and which comprises a side wall facing toward the turbine housing, characterized in that- the radial-axial turbine wheel (12) has a rear wall (13) with a corner (E2) arranged at the outer end of the rear wall (13) in a radial direction, wherein a top side (OS) of the turbine wheel runs obliquely outward in the radial direction proceeding from the corner (E2) of the rear wall (13),- a sub-region of that side wall of the bearing housing (20) which faces toward the turbine housing forms a sub-region of the rear wall of the turbine housing (10),- that sub-region of the bearing housing which forms a sub-region of the rear wall of the turbine housing has two sub-portions (TA1, TA2), of which- the first sub-portion (TA1) runs obliquely with respect to the axis of rotation (30a) of the shaft (30) in the inflow direction (ZR) of an exhaust-gas flow conducted into the turbine housing,- the second sub-portion (TA2) runs in a radial direction (R) with respect to the axis of rotation (30a) of the shaft (30) and parallel to the rear wall (13) of the turbine wheel (12), and- the two sub-portions (TA1, TA2) are connected to one another via an exhaust-gas flow separation edge (35) of the bearing housing (20),- wherein the exhaust-gas flow separation edge (35) has a corner (E1) which is connected to the second sub-portion (TA2) via a flank (F), wherein the first sub-portion (TA1) and the flank (F) enclose a corner angle (α) and a curved transition region (U) is provided between the second sub-portion (TA2) and the flank (F),- wherein the top side (OS) of the turbine wheel (12) has a spacing (c) to the corner (E1) of the exhaust-gas flow separation edge (35) in the inflow direction (ZR) of the exhaust-gas flow and the flank (F) runs parallel to the top side (OS) of the turbine wheel (12).
- Exhaust-gas turbocharger according to Claim 1, characterized in that the first sub-portion (TA1) ends at the corner (E1).
- Exhaust-gas turbocharger according to Claim 2, characterized in that the first sub-portion (TA1) is of rectilinear form.
- Exhaust-gas turbocharger according to Claim 2, characterized in that the first sub-portion (TA1) is of curved form.
- Exhaust-gas turbocharger according to one of Claims 1 to 4, characterized in that the rear wall (13) of the turbine wheel (12) has, in its upper end region, a corner (E2) which has a first spacing (b) to the corner (E1) of the exhaust-gas flow separation edge (35) in a radial direction (R).
- Exhaust-gas turbocharger according to one of the preceding claims, characterized in that the rear wall (13) of the turbine wheel (12) has a third spacing (a) to the second sub-portion (TA2).
- Exhaust-gas turbocharger according to Claim 6, characterized in that the ratio of the third spacing (a) to the diameter (DTR) of the rear wall (13) of the turbine wheel (12) lies in the range between 0.005 and 0.025.
- Exhaust-gas turbocharger according to one of Claims 5 to 7, characterized in that the ratio of the second spacing (b) to the diameter (DTR) of the rear wall (13) of the turbine wheel (12) lies in the range between 0.005 and 0.025.
- Exhaust-gas turbocharger according to one of the preceding claims, characterized in that the bearing housing (20) has a water core (36) which is arranged adjacent to the exhaust-gas flow separation edge (35).
- Exhaust-gas turbocharger according to one of Claims 1-9, characterized in that that side wall of the bearing housing (20) which faces toward the turbine housing (10) is provided with a protective layer in the region of the first sub-portion (TA1), of the second sub-portion (TA2) and of the flank (F).
- Exhaust-gas turbocharger according to Claim 10, characterized in that the protective layer is composed of a material which is resistant to high temperatures, to oxidation and to corrosion.
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
DE102013210990.3A DE102013210990A1 (en) | 2013-06-13 | 2013-06-13 | Exhaust gas turbocharger with a radial-axial turbine wheel |
PCT/EP2014/058753 WO2014198453A1 (en) | 2013-06-13 | 2014-04-29 | Turbocharger with a radial/axial turbine wheel |
Publications (2)
Publication Number | Publication Date |
---|---|
EP3008292A1 EP3008292A1 (en) | 2016-04-20 |
EP3008292B1 true EP3008292B1 (en) | 2018-08-01 |
Family
ID=50588726
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
EP14719804.8A Active EP3008292B1 (en) | 2013-06-13 | 2014-04-29 | Turbocharger with a radial/axial turbine wheel |
Country Status (7)
Country | Link |
---|---|
US (1) | US10190415B2 (en) |
EP (1) | EP3008292B1 (en) |
KR (1) | KR101823744B1 (en) |
CN (1) | CN105264177B (en) |
BR (1) | BR112015029901B8 (en) |
DE (1) | DE102013210990A1 (en) |
WO (1) | WO2014198453A1 (en) |
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DE102021211009A1 (en) | 2021-09-30 | 2023-03-30 | Vitesco Technologies GmbH | Bearing housing of an exhaust gas turbocharger with heat shield, exhaust gas turbine assembly and exhaust gas turbocharger |
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2013
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-
2014
- 2014-04-29 KR KR1020157037276A patent/KR101823744B1/en active IP Right Grant
- 2014-04-29 WO PCT/EP2014/058753 patent/WO2014198453A1/en active Application Filing
- 2014-04-29 US US14/897,753 patent/US10190415B2/en active Active
- 2014-04-29 CN CN201480033583.6A patent/CN105264177B/en active Active
- 2014-04-29 BR BR112015029901A patent/BR112015029901B8/en not_active IP Right Cessation
- 2014-04-29 EP EP14719804.8A patent/EP3008292B1/en active Active
Also Published As
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CN105264177A (en) | 2016-01-20 |
WO2014198453A1 (en) | 2014-12-18 |
BR112015029901A2 (en) | 2017-07-25 |
BR112015029901B8 (en) | 2023-04-18 |
BR112015029901B1 (en) | 2022-01-11 |
DE102013210990A1 (en) | 2014-12-18 |
US10190415B2 (en) | 2019-01-29 |
KR101823744B1 (en) | 2018-01-30 |
US20160186568A1 (en) | 2016-06-30 |
EP3008292A1 (en) | 2016-04-20 |
CN105264177B (en) | 2017-12-15 |
KR20160016970A (en) | 2016-02-15 |
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