EP3781799A1

EP3781799A1 - Multistage turbocharger device

Info

Publication number: EP3781799A1
Application number: EP19718632.3A
Authority: EP
Inventors: Elmar Groeschel; Frank Hummel; Bent Aamand PHILLIPSEN
Original assignee: ABB Schweiz AG
Current assignee: Turbo Systems Switzerland Ltd
Priority date: 2018-04-17
Filing date: 2019-04-11
Publication date: 2021-02-24
Also published as: WO2019201739A1; CN112334640A

Abstract

The invention relates to a multistage turbocharger device (1), which has a high-pressure turbine (2), a low-pressure turbine (3), a low-pressure compressor (4), a high-pressure compressor (5), a first shaft (6) and a second shaft (7), wherein one of the turbines and one of the compressors are arranged on the first shaft and the other turbine and the other compressor are arranged on the second shaft, the two shafts have the same axis of rotation, the two shafts are arranged one behind the other in the axial direction and the two shafts rotate in opposite directions.

Description

Multi-stage turbocharger device

Technical field of the invention

The invention relates to a multi-stage Turboladervorrich device.

State of the art

Multi-stage turbocharger devices are already known. By means of such multi-stage turbocharger devices can be achieved in comparison to single-stage turbocharger devices, a He increase in output power and a reduction of the fuel consumption of the motor in each case charged internal combustion engine. To keep the manufacturing and operating costs ei ner multi-stage turbocharger device low, the multi-stage turbocharger should be compact builds up.

From DE 10 2014 202 399 Al a multi-rotor turbola is known, which has a compressor and a turbine. The compressor contains several opposing compaction terrotors. The turbine contains several counter-rotating turbine rotors. A first of these compressor rotors is connected via a first shaft to a first of the turbine rotors. A first compressor rotor adjacent second Verdich terrotor is connected via a second shaft with a second turbine nenrotor. The two shafts are arranged coaxially with each other and rotate about a common axis of rotation.

Summary of the invention

The object of the invention is to provide a space-saving and easily realizable multi-stage turbocharger device whose efficiency is improved. This object is achieved by a multi-stage Turboladervorrich device having the features specified in claim 1. Such a multi-stage turbocharger apparatus comprises a high pressure turbine, a low pressure turbine, a Niederdruckver denser, a high pressure compressor, a first shaft and a second shaft, wherein one of the turbines and one of the United denser on the first shaft and the other turbine and the other compressor on the second shaft are arranged, the two shafts have the same axis of rotation, the two shafts are arranged one behind the other in the axial direction and in the waves have an opposite direction of rotation.

According to one embodiment of the invention, the low-pressure turbine to the output of the high-pressure turbine is ruled out.

According to one embodiment of the invention, the high pressure turbine and the high pressure compressor are arranged on the first shaft and the low pressure turbine and the low pressure compressor on the second shaft.

According to one embodiment of the invention, the high pressure turbine and the low pressure compressor are arranged on the first shaft and the low pressure turbine and the high pressure compressor on the second shaft.

According to one embodiment of the invention, the high-pressure turbine and the low-pressure turbine are arranged in a common turbine housing Tur.

According to one embodiment of the invention, the high-pressure turbine in a gas inlet housing and the Niederdrucktur bine arranged in a gas outlet housing, wherein the Ga is housing housing connected to the gas outlet housing.

According to one embodiment of the invention, the high-pressure turbine Leitschaufein. According to one embodiment of the invention, a inter mediate cooler is arranged between the low pressure compressor and the high pressure compressor.

According to one embodiment of the invention, a charge air cooler is connected to the outlet of the high-pressure compressor.

Brief description of the drawings

The invention will be described with reference to Ausführungsbeispie sources, which are explained with reference to drawings. This shows

FIG. 1 shows a sketch of a multi-stage turbocharger device according to a first exemplary embodiment of the invention,

FIG. 2 shows a sketch of a multistage turbocharger device according to a second exemplary embodiment of the invention,

Figure 3 is a first sketch to illustrate the central arrangement of the turbine stages in a multi-stage turbola dervorrichtung and

Figure 4 is a second sketch to illustrate the central arrangement of the turbine stages in another multi-stage turbocharger device.

In the following description, identical reference _Z are used for calibrating the same and equivalent parts.

Detailed Bes the time s

1 shows a sketch of a multi-stage turbocharger device according to a first embodiment of the invention. In the device shown in Figure 1 is a two-stage turbocharger device, as it can be used in particular in connection with large engines, such as marine engines.

This two-stage turbocharger device 1 has a high-pressure turbine 2, a low-pressure turbine 3, a low-pressure compressor 4 and a high-pressure compressor 5. The high-pressure turbine 2 has a gas inlet housing 10 a. The low-pressure turbine 3 has a gas outlet housing 1 Ob. The low-pressure compressor 4 is arranged in a low pressure Verdich tergehäuse 4a. The high pressure compressor 5 is arranged in a high pressure compressor housing 5a.

The high-pressure turbine 2 has an input region 18, to which a hot exhaust gas stream is fed to a not shown internal combustion engine. This hot exhaust stream is fed via Leitschaufein 11 the blades 15 of the high-pressure turbine 2. These blades 15 are part of a high-pressure turbine 31, which is rotatably connected to a first shaft 6 or integrated part of this first shaft 6. The high-pressure turbine wheel 31 is driven by the supplied hot exhaust gas flow and sets the first shaft 6 in a rotational movement.

This rotational movement of the first shaft 6, which takes place in the direction of rotation 29 is transmitted to the Niederdruckverdichterrad 13 of the low-pressure compressor 4, which is also rotatably connected to the ers th shaft 6 or integrated part of the first shaft 6 is. The Niederdruckverdichterrad 13 has blades 17, of which pre-compressed air via Leitschaufein 4b in an output region 25 of the low-pressure compressor 4 is issued. About this Ausgangsbe range 25 of the low pressure compressor 4 is the Eingangsbe rich 26 of the high pressure compressor 5, the pre-compressed air for further compression supplied. Between the output region 25 of the low-pressure compressor 4 and the input region 26 of the high-pressure compressor 5, an intercooler can be actuated. orders be. About the input portion 24 is the low-pressure compressor 4, the air to be compressed supplied.

The high-pressure compressor 5, which is supplied via its input portion 26, the pre-compressed air, has a high-pressure compressor wheel 28 which is ausgestat tet with blades 16. Of these blades 16, the compressor in the high pressure further compressed air via Leitschaufein 5b in an output range 27 of the high-pressure compressor and output from there, not shown in the figure 1

Internal combustion engine supplied to the power increase.

In the other end portion of the second shaft 7, the low-pressure turbine 32 of the low-pressure turbine 3 is rotatably fixed or integrated part of the second shaft 7. The low-pressure turbine 32 has blades 14 on. The second shaft 7 rotates in a direction of rotation 30, which is opposite to the direction of rotation of the first shaft 6. In de waves 6 and 7 rotate about a common axis of rotation 8. The two shafts 6 and 7 are arranged in the axial direction 9 hinerei nander. The output region 19 of the high-pressure turbine 2 forms the input region 20 of the low-pressure turbine 3. Consequently, the low-pressure turbine 3 is provided with the exhaust gas flow output by the high-pressure turbine 2 as input exhaust gas flow. This Eingangsabgasström the low-pressure turbine drives the low-pressure turbine wheel 32 of the low-pressure turbine 3 and puts this in rotation. This rotational movement is transmitted to the fixedly connected to the low-pressure turbine 32 second shaft 7, which is thereby also rotated. The rotational movement of the second shaft 7 in turn drives the non-rotatably ver with the second shaft 7 connected high-pressure compressor 28, which - as already stated - the high-pressure compressor 5 supplied compressed further compressed air and outputs to the internal combustion engine to increase their performance. Asked by the high-pressure turbine 2 from gas flow can advantageously the blades 14 of the low-pressure turbine 3 directly, ie without the use of dazwi arranged Leitschaufein be supplied because of the high pressure turbine 2 made available from gas flow without previous diversion or , without the use of special guide elements for driving the blades 14 of the low-pressure turbine wheel 32 is suitable. The low-pressure turbine wheel 32 output exhaust stream is forwarded in the Ausgangsbe region 21 of the low-pressure turbine 3 and output from the sem in a conventional manner to an exhaust pipe.

In the turbocharger apparatus described above, the low-pressure compressor 4 and the high-pressure compressor 5 each have Leitschaufein.

An alternative embodiment is to realize the low pressure compressor 4 and the high pressure compressor 5 without this Leitschaufein.

In the turbola dervorrichtung described above with reference to Figure 1, the high-pressure turbine 2 and the low-pressure turbine 3 are arranged in series with each other, wherein the high-pressure turbine 2 in a gas inlet housing 10a and the low-pressure turbine 3 in a gas outlet housing 1 is arranged is and wherein these two housing together verbun are the, for example, are bolted together. This division of the two turbine stages on different Ge housing is advantageous for assembly and service reasons.

Alternatively, the high-pressure turbine 2 and the low pressure turbine 3 may be arranged within a single turbine housing 10, as illustrated in Figure 2 and is interpreted in Figures 3 and 4 with dashed lines on. In this case, a separate housing for the low-pressure turbine is not necessary. As a result, the number of components required to realize the two-stage turbocharger device is kept small. Because in a housing always Even energy losses occur, the energy _V losses of the two-stage turbocharger device are redu ed by saving its own housing for the low-pressure turbine and thus increases their efficiency.

Furthermore, by saving a separate housing for the low-pressure turbine, the compactness of the two-stage turbocharger device is also increased.

Due to the above-mentioned saving a separate housing for the low-pressure turbine 3 connecting lines between different turbine housings are also saves, which further increases the compactness of the turbocharger device and further reduces the number of required for the realization of the turbo charger device components.

Since it also needs in the entry area of the low-pressure turbine 3 kei ner Leitschaufein, the compactness of the turbola dervorrichtung in both aforementioned cases is further increased and further reduces the number of components required to realize the turbocharger device.

Since the two shafts 6 and 7 in the axial direction 9 are arranged behind the other, have opposite directions of rotation and the output of the high-pressure turbine exhaust gas flow of the low-pressure turbine can be fed directly, the be described two-stage turbocharger device can also be produced in simp cher manner. It is, inter alia, of importance that there is no need for storage and stable guidance coaxial with each other extending waves. The storage of the shaft 6 can suc in a conventional manner in a bearing housing 22 conditions, the bearing of the shaft 7 in a corresponding manner in egg NEM bearing housing 23rd

As can be seen from the Ausfüh approximately exemplary embodiments described with reference to Figures 1 and 2, the two turbines of the two-stage turbocharger device are arranged on different Wel len. On the first wave 6, where the high Pressure turbine 31 of the high-pressure turbine 2 is rotatably angeord net is, as shown in Figure 1, further arranged the Niederdruckverdichterrad 13 of the low-pressure compressor 4. On the second shaft 7, on which the low-pressure turbine wheel 32 of the low-pressure turbine 3 is arranged rotationally fixed, as is also shown in Figure 1, further arranged the high-pressure compressor 28 of the high pressure Verdich age 5.

Alternatively, according to another exemplary embodiment, the high-pressure compressor wheel 28 of the high-pressure compressor 5 can furthermore be arranged on the first shaft 6, on which the high-pressure turbine wheel 31 of the high-pressure turbine 2 is arranged in a rotationally fixed manner. In this case, on the second shaft 7, on which the low-pressure turbine wheel 32 of the low-pressure turbine 3 is arranged rotationally fixed, further arranged the Niederdruckver dichterrad 13 of the low-pressure compressor 4.

In all of the aforementioned cases, a space-saving and easily realizable multi-stage turbocharger device with high efficiency is made available.

Furthermore, in all the above cases, the turbine stages are arranged centrally in the turbocharger device, currency end the two compressor stages are positioned at the outer ends of the turbocharger device. This will be explained in more detail hereinafter with reference to FIGS. 3 and 4, which show sketches of multi-stage turbocharger devices, in which the turbine stages are arranged centrally.

FIG. 3 shows a first sketch to illustrate the central arrangement of the turbine stages in a multistage turbocharger device.

The turbocharger apparatus 1 shown in FIG. 3 has a high-pressure turbine 2, a low-pressure turbine 3, a low-pressure compressor 4 and a high-pressure compressor 5. The high-pressure turbine 2, the hot exhaust gas of an internal combustion engine 34 is supplied. This hot exhaust drives the high pressure turbine wheel of the high pressure turbine 2. The high-pressure turbine wheel is firmly connected to a first shaft 6, on which further the high-pressure compressor wheel of the high pressure compressor 5 is arranged rotationally fixed. The first shaft 6 has a direction of rotation 29. The high-pressure turbine wheel driven by the hot exhaust gas displaces the first shaft 6 into a rotational movement which is transmitted to the high-pressure wheel via the first shaft 6 so that it is also rotated. By this rotation of the Hochdruckver dichterrades the high-pressure compressor 5 supplied compressed air before, which is provided by the low-pressure compressor 4 via an intercooler 12, further compressed. The present at the output of the high-pressure compressor 5 compressed air is supplied via an intercooler 33 of the internal combustion engine 34 to increase their performance.

The exhaust gas discharged from the high-pressure turbine 2 is directly supplied to the low-pressure turbine 3 whose low-pressure turbine wheel is driven by the exhaust gas discharged from the high-pressure turbine 2. The low-pressure turbine wheel is rotatably mounted on a second shaft 7 and transmits its rotational movement to the second shaft 7. The second shaft 7, which rotates in the direction of rotation 30 in opposite directions to the first shaft 6, is further connected to the low-pressure compressor of the low pressure compressor 4 rotatably connected , Consequently, the rotational movement of the second shaft 7 is transmitted to the Niederdruckverdich terrad, so that this is also set in rotation ver. By this rotational movement of the Niederdruckverdich terrades fresh air provided by a fresh air source 35 fresh air in the low-pressure compressor 4 is pre-compressed. This precompressed air is supplied to the high-pressure compressor 5 via the intercooler 12.

The intercooler 12 is preferably a heat exchanger which is operated with water, which is the precompressed air flow from the low pressure compressor 4 cools down.

In this case, the pre-compressed air in the low pressure compressor 4 is supplied to the intercooler 12 via a piping system. The cooled in the intercooler 12 precompressed air is also forwarded via a piping system to the Hochdruckver dense 5.

In the turbocharger shown in Figure 3 han it is after all a two-stage TurboladerSys system, which has two axially arranged in succession te, has counter-rotating shafts, and which has centrally disposed turbine stages, wherein the output from egg ner high-pressure turbine exhaust gas Turbine wheel of the low-pressure turbine drives.

FIG. 4 shows a second sketch to illustrate the central arrangement of the turbine stages in another multi-stage turbocharger device.

The turbocharger apparatus 1 shown in FIG. 4 has a high-pressure turbine 2, a low-pressure turbine 3, a low-pressure compressor 4 and a high-pressure compressor 5.

The high-pressure turbine 2, the hot exhaust gas of an internal combustion engine 34 is supplied. This hot exhaust drives the high pressure turbine wheel of the high pressure turbine 2. The high-pressure turbine wheel is firmly connected to a first shaft 6, on which further the low pressure compressor wheel of the low pressure compressor 4 is arranged rotationally fixed. The first shaft 6 has a direction of rotation 29. The high-pressure turbine wheel driven by the hot exhaust gas displaces the first shaft 6 into a rotational movement which is transmitted to the low-pressure compressor via the first shaft 6 so that it is also rotated. Due to this rotation of the low-pressure compressor wheel, the fresh air supplied from a fresh-air source 35 is precompressed in the low-pressure compressor 4. The precompressed air is fed via an intercooler 12 to the high pressure compressor 5 and sealed by this further ver. The present at the output of the high pressure compressor 5 de compressed air is supplied via a charge air cooler 33 of the engine 34 to increase their performance.

The exhaust gas discharged from the high-pressure turbine 2 is directly supplied to the low-pressure turbine 3 whose low-pressure turbine wheel is driven by the exhaust gas discharged from the high-pressure turbine 2. The low-pressure turbine wheel is rotatably mounted on a second shaft 7 and transmits its rotational movement to the second shaft 7. The second shaft 7, which rotates in the direction of rotation 30 in opposite directions to the first shaft 6, is further rotatably connected to the high-pressure compressor wheel of the high-pressure compressor 5 , Consequently, the rotational movement of the second shaft 7 is transmitted to the high-pressure compressor wheel, so that this is also rotated. As a result of this rotational movement of the high-pressure compressor wheel, the air pre-compressed by the low-pressure compressor 4 is compressed. This further compressed air is supplied via a charge air cooler 33 of the internal combustion engine 34 to their performance increase.

In the intercooler 12 is preferably egg nen heat exchanger, which is operated with water, which cools the pre-compressed air flow from the low-pressure compressor 4 from.

The turbocharger device shown in FIG. 4 is also a two-stage turbocharger system, which has two shafts, which are arranged one behind the other in the axial direction and rotate in opposite directions, and which are arranged centrally. Nete turbine stages, wherein the output from a high-pressure turbine exhaust turbine drives the turbine Niederdrucktur bine.

Hereinafter, some aspects of the invention will be described. These aspects can be combined with any other aspects and embodiments.

According to one aspect of the invention, a multi-stage turbo 1ade _V is provided orrichtung having a high pressure turbine, a low pressure turbine, a low pressure compressor, a high pressure compressor, a first shaft and a second shaft. In this case, one of the turbines and one of the compaction ter on the first shaft and the other turbine and the other compressor is arranged on the second shaft. The two shafts are arranged one behind the other in the axial direction and have the same axis of rotation. The two waves do not run into each other or. are axially spaced from each other. The two waves have an opposite direction of rotation.

According to one aspect, the output area of the high-pressure turbine forms the input area of the low-pressure turbine, so that the low-pressure turbine of the exhaust gas stream emitted by the high-pressure turbine is made available as input flow. In this case, the exhaust gas flow provided by the high-pressure turbine can advantageously be fed directly to the rotor blades of the low-pressure turbine, ie H . without use of since between arranged special guide elements, are supplied.

According to one aspect, the turbocharger device to a multi-stage compressor device, wherein the compressor from the low-pressure pre-compressed air flow, optionally via an inter mediate cooler, the high-pressure compressor is supplied.

According to one aspect, the two turbine stages are arranged axially centrally in the turbocharger device, while the two compressor stages are positioned at the axial outer ends of the tur boladervorrichtung. In one aspect, give the two compressor stages, the two turbine stages axially from both opposite sides.

The two turbines of the turbocharger device are preferably axial turbines, i. H . Turbines, the impeller is in each case flows in the axial direction. According to one aspect, the respective blades of the two turbines cover at least 50%, preferably at least 80% overlapping, radial area, the radial area being related to the radial distance, measured in cross-section, of the entrance area of the blades.

The storage of the two shafts of the turbocharger device can be carried out in a conventional manner. There are no special requirements regarding this storage.

Regarding the arrangement of the compressor stages Flexibi lity to the effect that the low-pressure compressor can be arranged either on the same shaft as the high-pressure turbine or on the same shaft as the low-pressure turbine. The high-pressure compressor is in each case arranged on the other shaft than the low-pressure compressor.

In one aspect, the high pressure turbine is connected to the low pressure compressor via the first shaft. In one aspect, the low pressure turbine is connected to the high pressure compressor via the first shaft.

LIST OF REFERENCE NUMBERS

1 Multi-stage turbocharger device

2 high-pressure turbine

3 low-pressure turbine

4 low-pressure compressor

4a low pressure compressor housing

4b guide vane

5 high pressure compressor

5a high pressure compressor housing

5b vane

6 First wave

7 second wave

8 axis of rotation

9 axial direction

10 Common turbine housing

10a gas inlet housing of the high-pressure turbine

1 Whether gas outlet casing of the low-pressure turbine

11 vane

12 intercoolers

13 low-pressure compressor wheel

14 Blade of the low-pressure turbine

15 Laufschaufei the high-pressure turbine

16 Laufschaufei the high-pressure compressor

17 Blade of the low-pressure compressor

18 Entrance area of the high-pressure turbine

19 Output range of the high-pressure turbine

20 Entrance area of the low-pressure turbine

21 Output range of the low-pressure turbine

22 bearing housing

23 bearing housing

24 Entrance area of the low-pressure compressor

25 outlet area of the low-pressure compressor

26 Entrance area of the high pressure compressor

27 output range of the high pressure compressor

28 high pressure compressor wheel

29 Direction of rotation of the first shaft 6

30 direction of rotation of the second shaft 7 31 high pressure turbine wheel

32 low-pressure turbine wheel

33 intercooler

34 internal combustion engine 35 fresh air source

Claims

claims

1. Multi-stage turbocharger device (1), which has a high-pressure turbine (2), a low-pressure turbine (3), a low-pressure compressor (4), a high-pressure compressor (5), a ers th shaft (6) and a second shaft (7) where one of the turbines and one of the compressors on the first shaft

(6) and the other turbine and the other compressor on the second shaft (7) are arranged, the two shafts (6, 7) have the same axis of rotation (8), the two shafts (6, 7) in the axial direction (9) in a row are arranged and at the shafts (6, 7) an opposite direction of rotation (29, 30) ha ha.

2. Multi-stage turbocharger apparatus according to claim 1, wherein the low-pressure turbine (3) to the output of the high-pressure turbine (2) is connected.

A multistage turbocharger apparatus according to claim 2, wherein said high-pressure turbine (2) and high-pressure compressor (5) are disposed on said first shaft (6) and said low-pressure turbine (3) and low-pressure compressor (4) are disposed on said second shaft (7).

4. Multi-stage turbocharger apparatus according to claim 2, wherein the high pressure turbine (2) and the Niederdruckverdich ter (4) on the first shaft (6) and the low pressure turbine (3) and the high pressure compressor (5) on the second shaft (7) are arranged ,

5. Multi-stage turbocharger apparatus according to one of vorherge existing claims, wherein the high-pressure turbine (2) and the low-pressure turbine (3) housing in a common Turbinenge (10) are arranged.

6. Multi-stage turbocharger device according to one of vorherge existing claims, wherein the high-pressure turbine (2) in egg nem gas inlet housing (10 a) and the low-pressure turbine (3) is arranged in a gas outlet housing (10b) and the gas inlet housing (10a) with the gas outlet housing (10b) is connected.

7. Multi-stage turbocharger apparatus according to one of vorherge existing claims, wherein the high-pressure turbine (2) guide vanes (11).

8. A multi-stage turbocharger apparatus according to any one of the preceding claims, wherein said low-pressure turbine (3) has no guide vane.

9. Multi-stage turbocharger device according to one of vorherge existing claims, in which between the Niederdruck- compressor (4) and the high pressure compressor (5) a Zwischenküh ler (12) is arranged.

10. Multi-stage turbocharger apparatus according to any one of the preceding claims, in which the output of the high pressure _V erdichters (5) a charge air cooler (33) connected.