• 专利附录
  • 专利说明
  • 权利要求
  • 类似技术
  • 同族专利
  • 引用文献
  • 法律状态
  • 优先权
    • 专利摘要:
    The invention relates to a multistage exhaust gas turbocharger (2), in particular a high-pressure turbocharger, for an internal combustion engine, with an exhaust gas turbine (1b) having at least one turbine impeller and a compressor (1a) having at least one first compressor stage (3) and a second compressor stage (4) in a compressor housing part (7) of the exhaust gas turbocharger housing (8) arranged compressor impeller (9), said turbine impeller and compressor impeller (9) on a in the exhaust gas turbocharger housing (8) about a rotation axis (10a) rotatably mounted common shaft (10) are arranged, wherein the compressor housing part (7) has an axial compressor inlet (11) for connection to a fresh air line. In order to reduce the thermal load on a multi-stage exhaust-gas turbocharger (2), it is provided that an intermediate cooler (15) is arranged between the first compressor stage (3) and the second compressor stage (4), the intercooler (15) issuing with at least one compressor stage (13) from the first compressor stage (3) and with at least one compressor stage inlet (14) in the second compressor stage (4) is fluidly connected
    公开号:AT516986A1
    申请号:T50244/2015
    申请日:2015-03-26
    公开日:2016-10-15
    发明作者:Thomas Ing Obenaus
    申请人:Avl List Gmbh；
    IPC主号:
    专利说明:

    The invention relates to a multi-stage exhaust gas turbocharger, in particular high-pressure turbocharger, for an internal combustion engine, with an at least one turbine impeller having exhaust gas turbine and a first compressor stage and a second compressor stage having compressor with at least one arranged in a compressor housing part of the turbocharger housing compressor impeller, wherein turbine impeller and compressor impeller on a in Exhaust gas turbocharger housing are arranged about a rotation axis rotatably mounted common shaft, wherein the compressor housing part has an axial compressor inlet for connection to a fresh air line.
    Turbochargers with high pressure ratios are needed to provide high fuel economy, high horsepower, and improved emissions performance in internal combustion engines.
    In order to achieve high pressure conditions, the rotational speeds of the rotors of exhaust gas turbochargers can be increased. However, this can lead to loads that exceed the capacity of the materials used.
    It is known to carry out a multi-stage compression of the charge air with two or more exhaust gas turbochargers, which operate with compressors connected in series, intercoolers being arranged between the compressors. Such solutions are known, for example, from the publications DE 10 2011 087 259 A1 or US 2014/0358404 A1. The disadvantage, however, is that these solutions are very complex and space-consuming. A similar approach involves the use of multiple compressor impellers on a common axis to achieve multiple compressor stages, whereby axial and radial compressor stages can be combined. However, here, too, disadvantages in the package size, but also in the rotor dynamics and bearing issues, result, in particular, from the increased length of the exhaust gas turbocharger.
    DE 699 14 199 T2 shows a slow-running high-pressure turbocharger with a two-stage compressor, the turbine runner and the compressor wheel being connected to one another via a common shaft. The compressor impeller has first impeller blades on a front side near an air inlet and second impeller blades on a rear side. The compressed air is over one
    Diffuser from the front to the back and forwarded from there into the inlet system. A similar solution is shown in EP 1 825 149 B1. On the other hand, exhaust gas turbochargers are known from US Pat. No. 6,834,501 Bl, US Pat. No. 6,792,755B2 or US Pat. No. 6,920,754 B2, in which annular gaps are formed between the front and rear sides of the two-stage compressor. While high compression ratios can be achieved as a result, the material is subjected to high stresses due to the high temperatures. While the air at the air inlet is approximately 25 ° C, the temperature increases to over 200 ° C up to the second impeller blades. Both the impeller blades and the turbocharger housing and the shaft bearings are exposed to high thermal loads. It also comes from temperatures of about 180 ° C for coking of airborne in the air oil fractions, for example, blow-by gases.
    EP 1 957 802 Bl proposes in this respect to use temperature-resistant materials or to make provision in this respect bearing and wave design.
    A disadvantage of all known solutions, on the one hand, the high temperature of the compressed air streams, on the other hand, the resulting thermal stresses of the turbocharger housing and the components used.
    The object of the invention is to reduce the thermal load of a multi-stage exhaust gas turbocharger.
    According to the invention, this is achieved by arranging an intermediate cooler between the first compressor stage and the second compressor stage, wherein the intermediate cooler is flow-connected with at least one compressor stage outlet from the first compressor stage and with at least one compressor stage inlet into the second compressor stage.
    The invention allows cooling of the precompressed air after the first compressor stage. While the air enters the first compressor stage at about 25 ° C, it has almost 200 ° C at its outlet - in the second compressor stage an inadmissibly high temperature increase would occur which causes high loads on turbocharger components. By means of the intercooler, the charge air can be cooled to about 60 ° C. This results in addition to the higher efficiency of the compressor, especially the second compressor stage, and an increase in efficiency of the supplied with the compressed charge air engine.
    By cooling the coolant, on the one hand, a cooling of the charge air, on the other hand, but also a cooling of the compressor housing, as well as the remaining exhaust gas turbocharger, whereby a higher mechanical durability is given. The cooling liquid can be used subsequently for cooling the shaft bearings of the exhaust gas turbocharger, which allows a saving of connections and lines.
    Preferably, the intercooler has a radiator housing connected to the compressor housing part, the intercooler being connected directly to the at least one compressor stage outlet and the at least one compressor stage inlet. The intercooler thus establishes a flow connection between at least one compressor stage outlet from the first compressor stage and at least one compressor stage inlet into the second compressor stage.
    The radiator housing attached to the compressor housing part of the exhaust gas turbocharger has the advantage that space, lines and fasteners can be saved in comparison to a separate from the exhaust gas turbocharger external intercooler.
    It is particularly advantageous if the cooler housing essentially has the shape of a torus [donut or bagel form], preferably a trapezoidal or rectangular torus, wherein the cooler housing is arranged concentrically to the axis of rotation and preferably surrounds the axial compressor inlet. As a result, only a little additional space is occupied by the intercooler and at the same time ensures good cooling.
    A compact arrangement results if at least one compressor stage outlet from the first compressor stage and at least one compressor stage inlet in the second compressor stage are arranged in the region of a preferably annular first end side of the compressor housing part, with the first end side particularly preferably facing away from the exhaust gas turbine side of the compressor
    Compressor housing part is arranged. The annular first end surrounds the axial compressor inlet, which passes through the center thereof.
    In an advantageous embodiment variant of the invention, it is provided that at least one compressor stage outlet and / or at least one compressor stage inlet are designed to run coaxially to the axis of rotation of the exhaust gas turbocharger shaft, wherein preferably at least one compressor stage outlet and / or at least one compressor stage inlet in the compressor housing component is annular or spirally about the axis of rotation of the compressor Shaft of the exhaust gas turbocharger are arranged to extend. The hot compressed air of the first compressor stage thus exits from the annular or spiral formed about the axis of rotation compressor stage outlet and passes through the open first cooler front side directly into the cooling space of the intercooler, where heat is released into the cooling medium. Thereafter, the air leaves the intercooler and flows again via the open first end face into the compressor stage inlet of the second compressor stage. After compression in the second compressor stage, the compressed air leaves the compressor and is routed in the usual way via at least one charge air line to the intake manifold of the internal combustion engine.
    Alternatively to annular or spiral around the axis of rotation of the shaft arranged Verdichterstufenaustritten and compressor stage entries may also each example, circular cross section having Verdichterstufenein- or exits or more distributed on the annular face circumferentially arranged compressor stage entries and Verdichterstufenaustritte-related to the axis of rotation - in different angular ranges be arranged.
    In other words, a plurality of compressor stage inlets and outlets are provided on the annular end face in the circumferential direction, which preferably have a circular cross section. In a variant of the invention, one compressor stage inlet and one compressor stage outlet are alternately provided in the circumferential direction. In a further variant of the invention, the annular end face is divided into a plurality of ring segments which extend over the same or different angular ranges, and each ring segment is associated with at least one pair of compressor stage inlet and outlet.
    In order to achieve effective cooling, it is advantageous if the intercooler is designed as an air / water heat exchanger or as an air / oil heat exchanger. In a variant of the invention, a cooling liquid leading, preferably annular and / or spirally wound around the axis of rotation, cooling line is arranged in the radiator housing. The cooling line can be guided over only a part of the torus shape and thus cover only a ring segment, but also have complete ring or spiral shape with several orbits around the axis of rotation.
    The cooling line may be formed as a cooling coil and, for example, have a circular cross-section. The heat input into the cooling liquid can be improved by increasing the wetted surface, if the cooling line is designed as a flat pipe, for example, with a rectangular cross-section.
    In a variant of the invention, the intercooler and / or the radiator housing in the region of the compressor housing part facing the first radiator end face are formed substantially open. This makes it possible to achieve even better heat dissipation from the compressor area.
    The intercooler has at least one coolant inlet and at least one coolant outlet, wherein the coolant inlet and / or the coolant outlet can be arranged in the region of at least one radiator front side of the intercooler, preferably on a second radiator front side facing away from the first end side of the compressor housing part.
    In the context of the invention it is further provided that within the intercooler at least one preferably metallic cooling and / or guide wall is arranged for the air to be cooled.
    According to a variant of the invention, the cooling and / or guide wall is in thermal communication with the adjacent cooling and / or guide walls and either directly or indirectly with the cooling line. Direct connection here means that a cooling and / or baffle disposed adjacent to the cooling line and is in thermal communication with this. Indirect connection here means that the cooling and / or guide wall is not arranged directly next to the cooling line, but one or more cooling and / or baffles are arranged therebetween and the cooling and / or baffle via thermal
    Contact with the cooling and / or baffles is in thermal communication with the cooling line.
    A particularly preferred embodiment of the invention provides that at least one first cooling and / or guide wall - preferably a plurality of first cooling and / or baffles - radially with respect to the axis of rotation extending - particularly preferably evenly distributed around the circumference - is arranged or are. Radially running here means that the cooling and / or baffles are made substantially flat and describe extending through the axis of rotation radial planes. The cooling and / or guide walls preferably have at least one recess for the cooling line. This recess can be designed as a slot or as the cross section of the cooling pipe corresponding opening - the slot allows, for example, a simple installation, since the cooling and / or baffle can be easily inserted in the axial direction on the cooling line and soldered to it. In the case of openings, a particularly good heat can also be achieved by soldering the cooling and / or guide wall to the cooling line.
    In this case, at least two first cooling and / or baffles and the cooler housing can span a substantially torus sector-shaped partial cooling space, wherein preferably at least one torus sector-shaped partial cooling space extends over an angular range of at least approximately 10 °. In principle, however, smaller or larger partial cooling rooms are possible.
    The partial cooling chambers represent flow connections between the first and second compressor stage, the flow connection forcibly causing a circulation of the cooling pipe located in the partial cooling chambers. The thermal connection of the cooling line with the cooling and / or guide walls allows an enlargement of the thermally active surface of the intercooler and particularly good heat dissipation from the pre-compressed air. The usually poor heat transfer between air and metal is favored by the good heat transfer metal coolant to the cooling line allows rapid removal of heat energy.
    In a first embodiment variant of the invention, at least one compressor stage outlet from the first compressor stage and at least one compressor stage inlet into the second compressor stage have different radial distances to the rotation axis within a partial cooling space, preferably at least one compressor stage outlet in the radial direction between the compressor stage inlet and rotation axis or at least one Compressor inlet is arranged in the radial direction between the compressor stage outlet and axis of rotation. The different radial distances of the compressor stage outlets and inlets from the axis of rotation apply a roller-like flow substantially in the radial direction within the respective partial cooling space, with the cooling lines flowing around in the transverse direction. In order to avoid a deviation of the flow in the tangential direction, it is advantageous if the angular range of a torus sector-shaped partial cooling space is at most about 90 °, preferably at most about 60 °, for example about 18 °. In principle, however, the angular ranges of the partial cooling chambers can also be selected to be smaller.
    However, short-circuit currents of the air flowing in the partial cooling space between the compressor stage outlet and the compressor stage inlet could adversely affect the cooling effect. In order to avoid such short-circuit flows, it is advantageous if at least one flow-guiding element is arranged between at least one compressor-stage outlet and an adjacent compressor-stage inlet of the same partial cooling chamber. The flow guide may be formed by the compressor housing part or by the radiator housing. In an exemplary embodiment, the flow guiding element is designed as a circular annular bead which extends from the compressor housing part in the direction away from the exhaust gas turbine.
    According to a second embodiment variant of the invention, at least one compressor stage outlet from the first compressor stage and at least one compressor stage inlet from the first compressor stage are circumferentially spaced from one another within at least one partial cooling space, wherein preferably within the partial cooling chamber the compressor stage outlet and the compressor stage inlet are substantially equidistant from the axis of rotation are arranged.
    The distance in the circumferential direction between a compressor stage outlet and a compressor stage inlet within a partial cooling space causes a swirl flow substantially in the circumferential direction about the axis of rotation within the respective partial cooling space, wherein the Kühlleituhgeh are flowed around in the longitudinal direction. For the formation of a pronounced swirl flow, it is advantageous if the angular range of a partial toroidal cooling chamber is at least about 90 °, preferably at least about 120 °.
    Turbulence in the partial cooling space can be avoided if at least one second cooling and / or guide wall is arranged to extend substantially parallel to the cooling line, preferably the second cooling and / or guide wall being at a defined distance from at least one adjacent first cooling and / or guide wall having. Furthermore, to improve the cooling, it may be provided that at least two adjacent cooling and / or guide walls are fixedly connected to one another by at least one heat-conducting connection. The thermally conductive connection can be realized for example by local impressions or wave-like shaping of the second cooling and / or baffles and soldering to the respective adjacent cooling and / or baffle. In addition to preventing turbulence, this variant also allows an increase of the thermally effective area again, so that the pre-compressed air passing by finds more contact surface and the heat transfer is improved.
    The invention is explained in more detail below with reference to the non-limiting figures.
    Show it
    1 shows an exhaust gas turbocharger according to the invention in a longitudinal section in a first embodiment,
    2 shows the exhaust gas turbocharger in a section along the line II-II in Fig. 1st
    3 shows a cooler housing of an intermediate cooler in a sectional oblique view,
    Fig. 4 is a cooling line in an oblique view.
    5 shows an intercooler in a sectional oblique view,
    6 shows this intercooler in a further cut oblique view,
    7 shows the intercooler from FIG. 1 without cooling lines in an oblique view, FIG.
    8 shows a cooling and / or air guide wall in detail in an oblique view,
    9 shows the intercooler of FIG. 1 along with cooling lines in an oblique view,
    10 shows the intercooler of FIG. 9 in a sectional oblique view, FIG.
    11 shows the intercooler of FIG. 9 in a plan view of the first radiator front side, FIG.
    12 shows an exhaust gas turbocharger according to the invention in an oblique view in a second embodiment,
    13 this exhaust gas turbocharger in a further oblique view,
    14 shows the exhaust gas turbocharger from FIG. 12 without an intercooler in an oblique view, FIG.
    15 shows the exhaust gas turbocharger from FIG. 14 in a further oblique view, FIG.
    16 shows the exhaust gas turbocharger from FIG. 14 in an axial view, FIG.
    17 is a disassembled intercooler of the exhaust gas turbocharger shown in Fig. 14 in an oblique view,
    18 is a detail of this intercooler in an oblique view,
    19 and 20 show details of second cooling and guide walls in oblique views,
    Fig. 21, the intercooler of FIG. 14 without cooling and baffles in an oblique view and
    Fig. 22, the cooling line of the intermediate cooler shown in Fig. 21.
    Functionally identical parts are provided in the embodiments with the same reference numerals.
    1 shows a compressor la of an exhaust gas turbocharger 2, which has a first compressor stage 3 and a second compressor stage 4. A two-sided with
    Blades 5, 6 trained and arranged in the compressor housing part 7 of the exhaust gas turbocharger housing 8 compressor impeller 9 is rotatably mounted about a rotational axis 10a in the exhaust gas turbocharger housing 8 shaft 10 with a not further illustrated turbine wheel of the exhaust gas turbine of the exhaust gas turbocharger 2 in a rotationally fixed connection. The compressor housing part 7 has an axial compressor inlet 11 for connecting a fresh air line, not shown, for sucking in fresh air, and a compressor outlet, indicated by the reference numeral 12, for charge air for connection to a charge air line of an internal combustion engine. The flow of air is indicated by arrows S.
    In the flow path between a in the region of a substantially normal to the rotational axis 10a formed annular first end face 7a of the compressor housing part 7 arranged Verdichterstufenaustritt 13 from the first compressor stage 3 and also arranged in the region of the first end face 7a compressor stage inlet 14 in the second compressor stage 4 is an example arranged as an air / water heat exchanger or designed as an air / oil heat exchanger intercooler 15. The compressor stage outlet 13 is flow-connected to the pressure side 3a of the first compressor stage 3 and the compressor stage inlet 14 to the suction side 4a of the second compressor stage 4.
    7b, one of the exhaust gas turbine of the exhaust gas turbocharger 2 facing the second end face of the compressor housing part is designated.
    The intercooler 15 has a substantially toroidal radiator housing 16 with a likewise substantially toroidal cooling space 17. The radiator housing 16 is in the embodiments on the compressor housing part 7 facing the first radiator end 18 open and on the compressor housing part 7 facing away from the second radiator front side 19 substantially closed, wherein in the embodiments for the supply and discharge of cooling liquid to or from the in the refrigerator 17 the radiator housing arranged annular, spiral, or helical cooling line 22, a coolant inlet 20 and a coolant outlet 21 are arranged on the second radiator end face 19. Fig. 4 shows, for example, a cooling line 22 with a circular cross-section, which consists of several concentric helical gears. In contrast, in Fig. 22 formed as a flat pipe between the coolant inlet 20 and the coolant outlet 21 annular cooling line 22 is shown. FIG. 18 shows the connection of the coolant inlet 20 and the coolant outlet 21 to the cooling line 22 formed by a flat tube.
    In the first embodiment shown in FIGS. 1 to 11, the compressor stage outlet 13 from the first compressor stage 3 and the compressor stage inlet 14 are formed in the second compressor stage 4 respectively by annular and concentric about the axis of rotation 10a openings formed on the first end face 7a of the compressor housing part 7 , as shown in Fig. 2.
    FIG. 3 shows the radiator housing 16 of an intercooler 15 which is open in the region of its first radiator end face 18 and closed in the region of its second radiator end face 19. The cooling space 17 extends between an inner housing shell 16a and an outer housing shell 16b. The inner housing shell 16a surrounds the axial compressor inlet 11th
    FIGS. 5 and 6 show a cooler housing 16 with cooling line 22 arranged in the cooling space 17.
    As shown in FIGS. 7 to 11, the cooling space 17 can be subdivided into individual torus sector-shaped partial cooling spaces 23 by metallic first cooling and / or guide walls 24, wherein the first cooling and guide walls 24 are uniform in the radial direction in the cooling space 17 arranged distributed over the circumference.
    The first cooling and / or guide walls 24 each extend from an inner housing jacket 16a to an outer housing jacket 16b of the cooling housing 16. In this case, two first cooling and / or guide walls 24 and the cooler housing 16 each span a substantially torus sector-shaped partial cooling space 23 in which, in the first embodiment, the torus sector-shaped partial cooling space 23 extends through an angular range β of approximately 18 °. Each cooling and / or guide wall 24 has slot-shaped recesses 25 for receiving the cooling line 22 (FIG. 8). The recesses 25 may also be designed as openings, preferably with the same shape as the cross-sectional area of the cooling line 22. This allows a simplified installation. On the one hand, a flow line of the precompressed air through the intercooler 15 takes place via the cooling and / or guide walls 24. On the other hand, the cooling and / or guide walls 24 increase the thermal effect or contact area to the air. Cooling line 22 and cooling and / or guide walls 24 are in thermal
    Contact, especially by the cooling and / or baffles 24 are soldered to the cooling line 22. Thus, heat released from the air to the cooling and / or baffles 24 is transferred to the cooling line 22 and dissipated by the coolant flowing therein.
    The compressor stage outlet 13 and the compressor stage inlet 14 are located for each partial cooling space 23 in a relatively narrow angle section, wherein in the embodiment of the compressor stage outlet 13 between the compressor stage inlet 14 and the axis of rotation 10 a are arranged. As a result, in each partial cooling space 23, a roller flow oriented essentially in the radial direction with respect to the axis of rotation 10a arises between the compressor stage outlet 13 and the compressor stage inlet 14, the cooling conduit 22 being substantially circulated in the transverse direction.
    In order to avoid a short-circuit flow between the compressor stage outlet 13 and the compressor stage inlet 14 in the partial cooling space 23, at least one flow guide element 31 is arranged between the compressor stage outlet 13 and the adjacent compressor stage inlet 14 of the same partial cooling space 23, which can be formed, for example, by the compressor housing part 7. But it is also possible to form the flow guide 31 through the radiator housing 16 or a separate additional part. By way of example, the flow-guiding element 31 can be designed as an annular bead element, as can be seen in cross-section in FIG.
    The illustrated in FIGS. 12 to 22 second embodiment of an exhaust gas turbocharger 2 with compressor la and exhaust gas Ib differs from the first embodiment in that several - here three-Verstichterstufeaustritte 13 from the first compressor stage 3 and several - here three - compressor stage entries 14 in the second compressor stage 4 are provided in the region of the first end face 7a of the compressor housing part 7, wherein the compressor stage outlets 13 and compressor stage inlets 14 have, for example, circular solid cross sections.
    The compressor stage outlets 13 are fluidly connected to the pressure side of the first compressor stage 3 via outlet channels 26 integrated in the compressor housing part 7. Likewise, the compressor stage inlets 14 are connected via inlet channels 27 to the suction side of the second compressor stage 4. The
    Outlet passages 26 can be spirally guided around the axis of rotation 10a in the region of the pressure side of the first step 3. The compressor stage outlets 13 and the compressor stage inlets 14 are arranged in the region of the first end face 7a such that the compressor stage outlets 13 and the compressor stage inlets 14 have substantially the same distance in the radial direction from the axis of rotation 10a. A substantially equal distance of the compressor stage outlets 13 and the compressor stage inlets 14 from the rotation axis 10a is present here when the compressor stage outlets 13 and the compressor stage inlets 14 at least partially overlap in a fictitious rotation about the axis of rotation 10a, as clearly seen in FIG , The flow of air between the compressor stage outlets 13 and the compressor stage inlets 14 is indicated by arrows S in FIG.
    Here, too, the intercooler 15 has first guide and cooling walls 24, which extend radially between the inner housing shell 16a and the outer housing shell 16b and divide the cooling space 17 into torus sector-shaped partial cooling spaces 23, as best shown in FIGS. 17 and 21.
    In the illustrated second embodiment, the partial cooling spaces 23 extend by an angle range β of approximately 120 °. In each partial cooling chamber 23, a plurality of second cooling and / or guide walls 28 can further be arranged, which are arranged substantially parallel to the cooling channel 22, that is to say concentrically to the axis of rotation 10a. The second cooling and guide walls 28 and the cooling channel 22 form torus-segment-shaped flow channels 32 about the axis of rotation 10a for the air to be cooled, wherein the cooling channel 22 is flowed around in the longitudinal direction of the air to be cooled substantially.
    The ends of the second cooling and / or baffles 28 are spaced from the first cooling and / or guide walls 24 normal thereto in order to allow a flow passage between the flow channels 32. With reference to a partial cooling space 23, the respective compressor stage outlet 13 from the first compressor stage 3 and at least one compressor stage inlet 14 are spaced as far as possible from each other in the circumferential direction in the second compressor stage 4, whereby a pronounced flow in the longitudinal direction of the cooling channel 22 and a good heat emission of the precompressed air to the Cooling and / or guide walls 24, 28 and the cooling line 22 is achieved. To illustrate this are in Fig. 17 the
    Positions of the compressor stage exits 13 and compressor stage entries 14 are displayed.
    The cooling effect can be further improved if at least two adjacent second cooling and / or guide walls 28 are thermally connected to one another via a heat-conducting connection 29. The thermally conductive connection between adjacent second cooling and / or guide walls 28 may be formed, for example, by a local impression 30 of a second cooling and / or guide wall 28, which is connected via a solder connection to the adjacent cooling and / or guide wall 28, as in FIG Fig. 19 and 20 is shown. As a result, on the one hand a thermal connection is obtained, on the other hand, the flow control is reduced to a minimum.
    For reasons of clarity, the particularly preferred variant is that all cooling and / or guide walls 24, 28 are thermally connected to each other and directly or indirectly to the cooling line 22, for example in the manner described above.
    Through each of the embodiments, an effective intermediate cooling of the compressed air between the first and the second compressor stage 3, 4 can be achieved in a very compact manner and thus the thermal load of the exhaust gas turbocharger 2 can be substantially reduced. This gives a higher mechanical durability. Furthermore, the cooling of the air increases the efficiency of both the second compressor stage 4 and the downstream engine.
    权利要求:
    Claims (20)
    [1]
    1. Multi-stage exhaust gas turbocharger (2), in particular high-pressure turbocharger, for an internal combustion engine, having an at least one turbine wheel exhaust turbine (Ib) and a first compressor stage (3) and a second compressor stage (4) having compressor (la) with at least one in one Compressor housing part (7) of the exhaust gas turbocharger housing (8) arranged compressor impeller (9), wherein turbine impeller and compressor impeller (9) on a in the exhaust gas turbocharger housing (8) about a rotation axis (10a) rotatably mounted common shaft (10) are arranged, wherein the compressor housing part (7 ) has an axial compressor inlet (11) for connection to a fresh air line, characterized in that between the first compressor stage (3) and the second compressor stage (4) an intercooler (15) is arranged, the intercooler (15) having at least one Compressor stage outlet (13) from the first compressor stage (3) and with at least ei A compressor stage inlet (14) in the second compressor stage (4) is fluidly connected.
    [2]
    2. Exhaust gas turbocharger (2) according to claim 1, characterized in that the intercooler (15) with the compressor housing part (7) connected to the radiator housing (16) and the intercooler (15) directly to the at least one Verdichterstufenaustritt (13) and the at least a compressor stage inlet (14) is connected.
    [3]
    3. Exhaust gas turbocharger (2) according to claim 1 or 2, characterized in that the radiator housing (16) has substantially the shape of a torus [donut or bagel shape], preferably a trapezoidal or Rechtecktorus, wherein the radiator housing (16) concentrically is arranged to the rotation axis (10 a) and preferably surrounds the axial compressor inlet (11).
    [4]
    4. Exhaust gas turbocharger (2) according to one of claims 1 to 3, characterized in that at least one compressor stage outlet (13) from the first compressor stage (3) and at least one compressor stage inlet (14) in the second compressor stage (4) in the region of a preferably annular first end face (7a) of the compressor housing part (7) are arranged, wherein particularly preferably the first end face (7a) on the exhaust gas turbine (Ib) facing away from the compressor housing part (7) is arranged.
    [5]
    5. Exhaust gas turbocharger (2) according to one of claims 1 to 4, characterized in that at least one compressor stage outlet (13) and / or at least one compressor stage inlet (14) coaxial with the axis of rotation (10a) of the shaft (10) of the exhaust gas turbocharger (2) running are formed.
    [6]
    6. Exhaust gas turbocharger (2) according to one of claims 1 to 5, characterized in that at least one compressor stage outlet (13) and / or at least one compressor stage inlet (14) in the compressor housing part (7) annularly or spirally about the axis of rotation (10a) of the shaft (10a). 10) of the exhaust gas turbocharger (2) are arranged to extend.
    [7]
    7. Exhaust gas turbocharger (2) according to one of claims 1 to 4, characterized in that at least one compressor stage outlet (13) and / or at least one compressor stage inlet (14) - with respect to the axis of rotation (10a) - are arranged in different angular ranges.
    [8]
    8. Exhaust gas turbocharger (2) according to one of claims 1 to 7, characterized in that in the cooler housing (16) leading a cooling liquid, preferably annular and / or spirally around the axis of rotation (10 a) wound, cooling line (22) is arranged.
    [9]
    9. Exhaust gas turbocharger (2) according to one of claims 1 to 8, characterized in that the intercooler (15) and / or the radiator housing (16) in the region of the compressor housing part (7) facing the first radiator end face (18) is substantially open ,
    [10]
    10. Exhaust gas turbocharger (2) according to one of claims 1 to 9, characterized in that within the intercooler (15) at least one preferably metallic cooling and / or baffle (24, 28) is arranged for the air to be cooled.
    [11]
    11. Exhaust gas turbocharger (2) according to claim 10, characterized in that at least one first cooling and / or baffle (24) - preferably a plurality of first cooling and / or baffles (24) - radially with respect to the axis of rotation (10a) extending - Is particularly preferably uniformly distributed around the circumference - is or are.
    [12]
    12. Exhaust gas turbocharger (2) according to claim 10 or 11, characterized in that at least one cooling and / or guide wall (24, 28) has at least one recess (25) for the cooling line (22).
    [13]
    13. Exhaust gas turbocharger (2) according to claim 11 or 12, characterized in that at least two first cooling and / or baffles (24) and the cooler housing (16) span a substantially torus sector-shaped partial cooling space (23), preferably at least one torussektorförmiger Partial cooling space (23) by an angular range (ß) of at least about 10 ° extends.
    [14]
    14. Exhaust gas turbocharger (2) according to claim 13, characterized in that within at least one partial cooling space (23) at least one compressor stage outlet (13) from the first compressor stage (3) and at least one compressor stage inlet (14) in the second compressor stage (4) different radial Have distances to the axis of rotation (10a), wherein preferably at least one compressor stage outlet (13) in the radial direction between the compressor stage inlet (14) and rotation axis (10a) or at least one compressor stage inlet (14) in the radial direction between the compressor stage outlet (13) and rotation axis (10a) is.
    [15]
    15. Exhaust gas turbocharger (2) according to claim 14, characterized in that the angular range (ß) of a Torussektorförmigen partial cooling space (23) a maximum of about 90 °, preferably at most 60 °, more preferably about 18 °.
    [16]
    16. Exhaust gas turbocharger (2) according to claim 14 or 15, characterized in that between at least one compressor stage outlet (13) and an adjacent compressor stage inlet (14) of the same partial cooling space (23) at least one flow guide (31) is arranged.
    [17]
    17. Exhaust gas turbocharger (2) according to claim 13, characterized in that within at least one partial cooling space (23) at least one compressor stage outlet (13) from the first compressor stage (3) and at least one compressor stage inlet (14) in the second compressor stage (4) in the circumferential direction are spaced apart, wherein preferably within the sub-cooling space (23) of the compressor stage outlet (13) and the compressor stage inlet (14) are arranged substantially equidistant from the axis of rotation (10a).
    [18]
    18. Exhaust gas turbocharger (2) according to claim 17, characterized in that the angular range (ß) of a torus sector partial cooling chamber (23) is at least about 90 °, preferably at least about 120 °.
    [19]
    19. Exhaust gas turbocharger (2) according to claim 17 or 18, characterized in that at least one second cooling and / or baffle (28) is arranged to extend substantially parallel to the cooling line (22), wherein preferably the second cooling and / or baffle (28) has a distance from at least one adjacent first cooling and / or guide wall (24).
    [20]
    20. Exhaust gas turbocharger (2) according to claim 19, characterized in that at least two adjacent second cooling and / or baffles (28) by at least one heat-conducting connection (29) are fixedly connected to each other.
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    同族专利:
    公开号 | 公开日
    WO2016149727A1|2016-09-29|
    AT516986B1|2018-09-15|
    DE112016001412A5|2018-01-25|
    CN107667226B|2020-08-21|
    CN107667226A|2018-02-06|
    引用文献:
    公开号 | 申请日 | 公开日 | 申请人 | 专利标题
    CH215474A|1938-07-21|1941-06-30|Sulzer Ag|Multi-stage, axially working turbo machine.|
    US2612310A|1948-10-01|1952-09-30|Oerlikon Maschf|Intermediate cooler for multistage rotary compressors|
    US3134536A|1961-06-27|1964-05-26|Ass Elect Ind|Intercoolers for gas compressors|
    DE2233970C2|1972-07-11|1975-03-13|Maschinenfabrik Augsburg-Nuernberg Ag, 8900 Augsburg|TWO-STAGE CHARGED PISTON COMBUSTION MACHINES|
    US7278472B2|2002-09-20|2007-10-09|Modine Manufacturing Company|Internally mounted radial flow intercooler for a combustion air changer|
    US6929056B2|2002-12-06|2005-08-16|Modine Manufacturing Company|Tank manifold for internally mounted radial flow intercooler for a combustion air charger|JP2020084924A|2018-11-29|2020-06-04|トヨタ自動車株式会社|Turbo charger|
    JP6639728B1|2018-11-29|2020-02-05|トヨタ自動車株式会社|Turbocharger|
    EP3699436A1|2019-02-20|2020-08-26|ABB Schweiz AG|Compressor housing of a radial flow compressor and method for feeding charged air to a combustion engine|
    US10746099B1|2019-04-03|2020-08-18|GM Global Technology Operations LLC|Multi-step bore turbocharger|
    法律状态:
    优先权:
    申请号 | 申请日 | 专利标题
    ATA50244/2015A|AT516986B1|2015-03-26|2015-03-26|MULTI-STAGE ABGASTURBOLADER|ATA50244/2015A| AT516986B1|2015-03-26|2015-03-26|MULTI-STAGE ABGASTURBOLADER|
    PCT/AT2016/050076| WO2016149727A1|2015-03-26|2016-03-23|Multi-stage turbocharger|
    CN201680028644.9A| CN107667226B|2015-03-26|2016-03-23|Multi-stage exhaust gas turbocharger|
    DE112016001412.0T| DE112016001412A5|2015-03-26|2016-03-23|Multi-stage turbocharger|
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