CN107636279B - Multi-stag exhaust-driven turbo-charger exhaust-gas turbo charger and internal combustion engine - Google Patents
Multi-stag exhaust-driven turbo-charger exhaust-gas turbo charger and internal combustion engine Download PDFInfo
- Publication number
- CN107636279B CN107636279B CN201680028699.XA CN201680028699A CN107636279B CN 107636279 B CN107636279 B CN 107636279B CN 201680028699 A CN201680028699 A CN 201680028699A CN 107636279 B CN107636279 B CN 107636279B
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- exhaust
- compressor
- coolant
- charger
- channel structure
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- 238000002485 combustion reaction Methods 0.000 title claims description 11
- 239000002826 coolant Substances 0.000 claims abstract description 89
- 238000011144 upstream manufacturing Methods 0.000 claims abstract description 7
- 230000006835 compression Effects 0.000 claims description 10
- 238000007906 compression Methods 0.000 claims description 10
- 230000002093 peripheral effect Effects 0.000 claims description 7
- 238000013461 design Methods 0.000 claims description 4
- 239000007789 gas Substances 0.000 description 23
- 238000001816 cooling Methods 0.000 description 14
- 239000007788 liquid Substances 0.000 description 3
- 239000000463 material Substances 0.000 description 3
- 238000012546 transfer Methods 0.000 description 3
- 229910052799 carbon Inorganic materials 0.000 description 2
- 239000000567 combustion gas Substances 0.000 description 2
- 238000010438 heat treatment Methods 0.000 description 2
- 239000010721 machine oil Substances 0.000 description 2
- 238000000034 method Methods 0.000 description 2
- 239000003921 oil Substances 0.000 description 2
- OKTJSMMVPCPJKN-UHFFFAOYSA-N Carbon Chemical compound [C] OKTJSMMVPCPJKN-UHFFFAOYSA-N 0.000 description 1
- XAGFODPZIPBFFR-UHFFFAOYSA-N aluminium Chemical compound [Al] XAGFODPZIPBFFR-UHFFFAOYSA-N 0.000 description 1
- 229910052782 aluminium Inorganic materials 0.000 description 1
- 239000004411 aluminium Substances 0.000 description 1
- 239000003795 chemical substances by application Substances 0.000 description 1
- 230000004069 differentiation Effects 0.000 description 1
- 238000009826 distribution Methods 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 239000012530 fluid Substances 0.000 description 1
- 239000000446 fuel Substances 0.000 description 1
- 230000017525 heat dissipation Effects 0.000 description 1
- 238000004519 manufacturing process Methods 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 238000007634 remodeling Methods 0.000 description 1
- 238000007789 sealing Methods 0.000 description 1
- 238000003860 storage Methods 0.000 description 1
- XLYOFNOQVPJJNP-UHFFFAOYSA-N water Substances O XLYOFNOQVPJJNP-UHFFFAOYSA-N 0.000 description 1
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
- 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
- F01D25/08—Cooling; Heating; Heat-insulation
- F01D25/14—Casings modified therefor
-
- 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
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Physics & Mathematics (AREA)
- Thermal Sciences (AREA)
- Combustion & Propulsion (AREA)
- Supercharger (AREA)
- Chemical Kinetics & Catalysis (AREA)
- General Chemical & Material Sciences (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
Abstract
The present invention relates to a kind of multi-stag exhaust-driven turbo-charger exhaust-gas turbo chargers comprising exhaust turbine and compressor at least one turbine rotor.Turbine rotor and the second compressor drum section and the first compressor drum section are arranged on the common axis that rotation axis rotatably supports.First compressor stage in the upstream of the first compressor drum section there is the axial compressor for being connected to fresh air conduit to enter pipe fitting, and there are at least two first helical channel structures in the downstream of the first compressor drum section, the first helical channel structure is transitioned at least two second helical channel structures that the upstream in the second compressor drum section of the second compressor stage extends.To reduce thermic load, equipped with the first coolant channel structure at least extended between the first helical channel structure and/or the second coolant channel structure extended between the second helical channel structure.
Description
Technical field
The present invention relates to a kind of multi-stag exhaust-driven turbo-charger exhaust-gas turbo charger, particularly high pressure turbocharger for internal combustion engine,
The turbocharger includes exhaust turbine and compressor at least one turbine rotor, which includes band
There are the first compressor stage of the first compressor drum section and the second compressor stage with the second compressor drum section,
In, turbine rotor and the second and first compressor drum section be arranged in rotatably supported around rotation axis it is common
Axis on, wherein the first compressor stage the upstream of the first compressor drum section have for being connected to fresh air conduit
Axial compressor enter pipe fitting, and there are at least two first helical ducts in the downstream of the first compressor drum section
Structure, what the upstream in the second compressor drum section that these first helical channel structures are transitioned into the second compressor stage extended
At least two second helical channel structures.The present invention is additionally related to the internal combustion at least one this exhaust-driven turbo-charger exhaust-gas turbo charger
Machine.
Background technique
In order to provide higher fuel economy, higher rated power and improved discharge efficiency, needed in internal combustion engine
The turbocharger that there is high compression ratio.
In order to realize high compression ratio, the rotation speed of the active wheel of exhaust-driven turbo-charger exhaust-gas turbo charger can be increased.However, can make herein
At the load of the load-bearing capacity beyond material therefor.
2012/107481 A1 of WO describes a kind of single stage type exhaust-driven turbo-charger exhaust-gas turbo charger, which has
Turbine casing and the bearing case being connect with turbine casing.Coolant supply is carried out via turbine casing.In addition, DE
10 2,013 203 376A1 describe for internal combustion engine can the cooling single stage type radial turbine of liquid, wherein coolant is logical
Road is integrated into the turbine casing.
The known multi-stage compression for implementing pressurized air with two or more exhaust-driven turbo-charger exhaust-gas turbo chargers, these exhaust gas turbines
Booster works together with the compressor of series connection, and wherein intercooler is arranged between each compressor.Substantially from US
This scheme known to 2014/0358404 A1.Although a disadvantage is that these schemes are extremely complex and expend structure space.Class
It is by the multi-stag compressor drum on common axis for realizing each compressor stage, including combination axial compressor like method
Grade and radial compressor grade.However, herein also especially because the increase length of exhaust-driven turbo-charger exhaust-gas turbo charger and in Package size side
Face and be unfavorable also in terms of rotor dynamics and storage problem.
In this regard, 699 14 199 T2 of DE shows the pressure turbine slowly operated with two-stage type compressor, wherein
Turbine rotor and compressor drum are connected to each other via common axis.Compressor drum has at the front close to air intake
There is the first rotor blade and there is the second rotor blade on the back side.Compressed air is via diffuser from front and the back side
And it is transmitted to gas handling system therefrom.1 825 149 B1 of EP shows similar scheme.But by 6,834,501 B1 of US,
A kind of exhaust-driven turbo-charger exhaust-gas turbo charger known to 6,920,754 B2 of US 6,792,755 B2 or US, wherein in two-stage type compressor
Front and back between be configured with annular gap.
Although thus can realize higher compression ratio, larger load can be caused to material due to higher temperature: to the greatest extent
Air at pipe air intake has about 25 DEG C of temperature, but until the temperature of the second impeller of rotor is in the compression more than 4 bars
Apparent increase is more than 200 DEG C than in the case where.Here, impeller of rotor and turbocharger shell and bearing are by higher warm
Load.In addition, will lead to the oil component transported together in air from about 180 DEG C of temperature, such as combustion gas containing machine oil is blocked.
1 957 802 B1 of EP is suggested in this respect using the material of tolerable temperature or in bearing and shaft design
It is related to the precautionary measures of this respect.
The shortcomings that all known schemes, is, is on the one hand the high-temperature of compressed air stream, is on the other hand whirlpool
Take turns booster shell and the resulting thermic load of each component used.
Summary of the invention
The task of the present invention is the thermic loads for reducing multi-stag exhaust-driven turbo-charger exhaust-gas turbo charger.
According to the present invention, such as get off to solve the task by starting the multi-stag exhaust-driven turbo-charger exhaust-gas turbo charger referred to, that is, be equipped with
The first coolant channel structure at least extending between the first helical channel structure and/or between the second helical channel structure
The the second coolant channel structure extended.
By in the first compressor stage, the second compressor stage or the two compressor stages through precompressed air into
Row cooling, present invention permission cool down air in exhaust-driven turbo-charger exhaust-gas turbo charger.Here, also generating smaller driven compressor
Power and turbine output power and reduced exhaust back-pressure.Since highest thermic load appears in the spiral shell of the second compressor stage
In spin line, the air transfer from exhaust-driven turbo-charger exhaust-gas turbo charger is into subsequent charge-air pipe here, thus in any feelings
Higher thermic load can be reduced under condition.Although air enters the first compressor stage with about 25 DEG C, in its exit, air has several
200 DEG C, occurs the high heating not allowed in the second compressor stage, this high heating can cause height to component of turbo-charger
Load.Pressurized air can be cooled to about 60 DEG C by coolant structure.Air is maintained in a temperature range as a result,
The oil component transported together in air, the carbon distribution of such as combustion gas containing machine oil are avoided in the temperature range.
By coolant channel structure, the cooling pressurized air of one side, this leads to the cooling heat dissipation capacity of less pressurized air
And the efficiency thus improved, on the other hand also cool down compressor case and remaining exhaust-driven turbo-charger exhaust-gas turbo charger.Coolant liquid physical efficiency
It is subsequently used for the bearing of cooling exhaust-driven turbo-charger exhaust-gas turbo charger, this makes it possible to save connector and conduit.In addition, the structure allows
Particularly compact structure type, so that other components can be disposed with for example before suction port of compressor, for example intersect booster
(Cross-Charger)。
In order to realize particularly effective cooling, it is advantageous to which the first coolant channel structure extends at least partly into
In the first profile region of one compressor drum section and/or the second coolant channel structure extends at least partly into second
In second contour area of compressor drum section.Here, by the entrance of compressor drum section and compressor drum section
Conduit wall section between outlet is known as contour area.Because in the region due to the compression to air can generate it is extra high
Temperature gradient, so effective cooling is particularly advantageous herein.
In a kind of modification of the invention, the first coolant structure is extended to from the region between the first helical channel structure
In the peripheral region of at least one or multiple first helical channel structures and/or the second coolant structure is from the second spiral
Region between channel design extends in the peripheral region of at least one or multiple second helical channel structures.By
This, it can be advantageous to cooling effect is improved, because film-cooled heat increases, helical channel structure is at a distance from rotation axis
Increase and increase its inner surface, which provides especially more heat transfer contact surfaces and being surrounded by coolant structure.
In order to realize advantageous flox condition, the first coolant channel structure has the first coolant collecting device and from first
The the first coolant passage portion and/or the second coolant channel structure that coolant collecting device is drawn have the second coolant collecting
Device and the second coolant passage portion drawn from the second coolant collecting device.Cooling is provided via coolant collecting device as a result,
Agent, and region to be cooled is directed coolant onto via passage portion.Here, coolant collecting device and passage portion are all
Extend including helical channel structure or between helical channel structure.
When the second coolant structure and the first coolant structure (advantageously the first coolant passage portion and the second cooling
Agent passage portion) when being connected to each other, it can be achieved that particularly effective cooling.Simple cooling structure is furthermore generated as a result, because can
Save intake line and output pipe.
According to the difference of thermic load, equipped with for the second coolant channel structure at least one coolant intake line and
At least one coolant output pipe of first coolant structure, or in turn (the second coolant channel knot to be used for that is, being equipped with
At least one coolant output pipe of structure and at least one coolant intake line of the first coolant structure).This by pair
The connector answered ensures.As a result, according to desired difference, fresh coolant is first directed to the second compressor stage or first draws
It leads to the first compressor stage.
In order to enable the manufacture of exhaust-driven turbo-charger exhaust-gas turbo charger according to the present invention becomes easy and advantageously, compressor has
Compressor case, the compressor case is at least one first compressor case part and at least one second compressor case
Part.Each section can individually cast, and then be connected to each other.
Furthermore task of the invention is solved by the internal combustion engine at least one this exhaust-driven turbo-charger exhaust-gas turbo charger.
Detailed description of the invention
Next, further illustrating the present invention according to non-limitative drawings.It is shown in the accompanying drawings:
Fig. 1 illustrates exhaust-driven turbo-charger exhaust-gas turbo charger according to the present invention with vertical profile；
Fig. 2 shows the top half of the compressor side of the exhaust-driven turbo-charger exhaust-gas turbo charger of Fig. 1 with detail drawing；And
Fig. 3 is shown ... in a side view the compressor side of the exhaust-driven turbo-charger exhaust-gas turbo charger in Fig. 1 according to Fig. 1 middle line III-III.
The identical component of function is equipped with identical appended drawing reference in embodiments.
Specific embodiment
Fig. 1 schematically illustrates the exhaust-driven turbo-charger exhaust-gas turbo charger 1 of multi-stage compression, which includes 2 He of compressor
Exhaust turbine 3, the exhaust turbine 3 have turbine rotor not shown further.Compressor 2 has first pressure in outside
Second compressor stage 5 of contracting machine grade 4 and inside.The name in outside and inside is about the fresh air for flowing through compressor 2 herein
Flow direction for.Differentiation between first compressor stage 4 and the second compressor stage 5 is indicated by dotted line in fig 1 and 2.
Compressor drum 6 is via axis that is rotatably supporting around rotation axis 1a and not showing further and gives up
The turbine rotor of the exhaust turbine 3 of air turbine booster 1 non-rotatably connects.Compressor drum 6, which has, belongs to first
First compressor drum section 6a of compressor stage 4 and the second compressor drum section 6b for belonging to the second compressor stage 5.Compression
Machine rotor section 6a, 6b is arranged in the shown embodiment on the side relative to each other of common compressor drum 6.
Compressor 2 is arranged in compressor case, which has the first compressor case part 7a and second
Compressor case part 7b, the two casing parts are connected to each other and seal.It is disposed in the first compressor case part 7a
First compressor stage 4, and the second compressor stage 5 is then located in the second compressor case part 7b.Joint face is by Fig. 1 and 2
Above mentioned dotted line indicates.Embodiment equipped with multiple casing parts is also possible.
First compressor case part 7a has in the upstream of the first compressor drum section 6a for being connected to for inhaling
The axial compressor for entering the fresh air line not shown further of fresh air enters connector 8.Equally also it is not shown
The compressor for pressurized air at second compressor case part 7b of the charge-air pipe for being connected to internal combustion engine
Outlet.
Enter (outside) first profile area that connector 8 directs air into the first compressor drum section 6a from compressor
Domain 9.Contour area refers to the channel between the entrance of compressor drum section and the outlet of compressor drum section herein
Wall segment, especially air duct are expanded to the section of larger diameter from minor diameter.
In the upstream of the first compressor drum section 6a, multiple first helical duct knots are directed into through precompressed air
In structure 10a, 10b, 10c, 10d, 10e or helix.First helical channel structure 10a, 10b, 10c, 10d, 10e is herein with surrounding
Rotation axis 1a is extended with the radius circular increased.Meanwhile first helical channel structure 10a, 10b, 10c, 10d, 10e diameter
Also streamwise increases.
First helical channel structure 10a, 10b, 10c, 10d, 10e of first compressor stage 4 is transitioned into the second compressor stage 5
Same number of second helical channel structure 11,11'(two the second helical channel structures 11,11' are only shown in the accompanying drawings,
Or next further discuss the second helical channel structure 11 of only one) in.As in fig. 3 as it can be seen that in illustrated embodiment
In, first helical channel structure 10a, 10b, 10c, 10d, 10e is lain substantially on a circle, and the center of the circle is located at rotary shaft
On line 1a (being orthogonal to plan in Fig. 3 to extend and be not drawn into).
Second helical channel structure 11,11' equally also around rotation axis 1a circle extend, but with the first helical duct knot
There is the radius reduced with flow direction unlike structure, equally also there is reduced diameter.Second helical channel structure 11
It is passed through near rotation axis 1a in (inside) second contour area 12 of the second compressor drum section 6b or its entrance.From
Compressed air is continued to be directed to unshowned charge-air pipe in the outlet of second compressor drum section 6b.
In order to cool down compressor 2, coolant channel structure 13,14 is implemented in compressor case portion now according to the present invention
Divide in 7a, 7b.Here, being equipped with the first coolant channel structure 13, the first coolant channel structure in the first compressor stage 4
13 with the first coolant collecting device 15 and from the first coolant collecting device 15 draw the first coolant passage portion 16a,
It 16b, 16c, 16d, 16e (dotted line is shown in fig 1 and 2) and is connect in the shown embodiment with coolant output pipe 17.
First coolant collecting device 15 extends around 12 annular of the second contour area in the shown embodiment.
Second coolant channel structure 14 be arranged in the second compressor stage 5 and have the second coolant collecting device 18 with
And from the second coolant collecting device 18 draw the second coolant passage portion 19, dotted line is shown 19'(in fig 1 and 2).Second
Coolant channel structure 14 is connect with coolant intake line 20.Here, water or other liquid or fluid are used as coolant.
Coolant channel structure 13,14 or coolant passage portion 16a, 16b, 16c, 16d, 16e, 19 are herein in correspondence
Helical channel structure 10a, 10b, 10c, 10d, 10e, 11, extend between 11'.So that in hot key area effectively
It radiates and the temperature through compressed air may remain in optimum range.As shown in Figure 2, coolant channel structure 13,14
It extends up in the contour area 9,12 of corresponding compressor drum section 6a, 6b, can be generated at these regions extra high
It thermic load and therefore especially needs to radiate.
Fig. 3 shows the cross-sectional view of the line III-III along Fig. 1, in top half, the first coolant channel structure 13 or
First coolant passage portion 16a, 16b, 16c is between first helical channel structure 10a, 10b, 10c, 10d, 10e
Region extends in the peripheral region for surrounding helical channel structure 10a, 10b, 10c, 10d, 10e.Here, peripheral region refers to position
The region except intermediate region between helical channel structure, i.e., around helical channel structure or its periphery area
Domain, wherein peripheral region is also represented by the region of compressed air impact in terms of heat.First coolant channel structure 13 further includes
For best thermally conductive helical channel structure 10a, 10b, 10c, 10d, 10e.Hereby it is achieved that the air duct of heat and cooling knot
The increase of heat-transfer surface between structure.The combination of flow path sufficiently large film-cooled heat and cooling and to be cooled
Allow to be fully cooled compressor 2 and exhaust-driven turbo-charger exhaust-gas turbo charger 1 is also served as into high pressure turbocharger.Corresponding embodiment
It can be arranged for the second compressor stage 5, but not showed that for open-and-shut purpose.
First coolant channel structure 13 and the second coolant channel structure 14 flow connection each other, wherein in shown reality
Flowing in example is applied to connect via first coolant passage portion 16a, 16b, 16c, 16d, 16e and the second coolant passage portion 19
It carries out.Thus, it is possible to coolant intake line 20 is disposed in the region of the second compressor stage 5, then in the first compressor
Coolant output pipe 17 is disposed at grade 4.It is of course also possible to guide coolant in turn.
As described above, the well-formed according to the present invention being made of air guide path and coolant channel by tool
Have the compressor case of the first compressor case part 7a and the second compressor case part 7b to realize: they can simply be poured
It casts, such as is cast by aluminium thermally conductive particularly well, and it is close by suitable sealing element to be assembled into compact medium
The compressor 2 of envelope.
By two-stage supercharging and for one stage of compression, additional cooling allows to be worth mentioning the described present invention
Heat power advantage, while there is compact structure, which, which has accommodated, increasingly increased reduces asking for structure space
Topic.
It is evident that the present invention is not only restricted to described embodiment, but in the protection scope of main claim
Various remodeling are possible.
Claims (10)
1. a kind of multi-stag exhaust-driven turbo-charger exhaust-gas turbo charger (1) for internal combustion engine, the turbocharger includes having at least one
The exhaust turbine (3) and compressor (2) of turbine rotor, the compressor (2) include having the first compressor drum section
First compressor stage (4) of (6a) and the second compressor stage (5) for having the second compressor drum section (6b), wherein turbine
Machine rotor and the second compressor drum section (6b) and the first compressor drum section (6a) are arranged in around rotation axis
On the common axis that (1a) is rotatably supported, wherein first compressor stage (4) is in the first compressor drum section
There is the axial compressor for being connected to fresh air conduit to enter connector (8) for the upstream of (6a), and described first
The downstream of compressor drum section (6a) has at least two first helical channel structures (10a, 10b, 10c, 10d, 10e), institute
State the first helical channel structure be transitioned into second compressor stage (5) in the upper of the second compressor drum section (6b)
Swim at least two second helical channel structures (11,11') extended, which is characterized in that be equipped at least logical in first spiral
The first coolant channel structure (13) for extending between road structure (10a, 10b, 10c, 10d, 10e) and/or in second spiral shell
The the second coolant channel structure (14) extended between rotation channel design (11,11').
2. exhaust-driven turbo-charger exhaust-gas turbo charger (1) as described in claim 1, which is characterized in that the first coolant channel structure
(13) it extends at least partly into the first profile region (9) of the first compressor drum section (6a) and/or described
Two coolant channel structures (14) extend at least partly into the second contour area of the second compressor drum section (6b)
(12) in.
3. exhaust-driven turbo-charger exhaust-gas turbo charger (1) as claimed in claim 1 or 2, which is characterized in that the first coolant channel structure
(13) from the region between first helical channel structure (10a, 10b, 10c, 10d, 10e) extend to around at least one
In the peripheral region of one helical channel structure (10a, 10b, 10c, 10d, 10e) and/or the second coolant channel structure
(14) it extends to from the region between second helical channel structure (11) around at least one the second helical channel structure
(11) in peripheral region.
4. exhaust-driven turbo-charger exhaust-gas turbo charger (1) as claimed in claim 1 or 2, which is characterized in that the first coolant channel structure
(13) with the first coolant collecting device (15) and from the first coolant collecting device (15) draw the first coolant part
Channel (16a, 16b, 16c, 16d, 16e) and/or the second coolant channel structure (14) have the second coolant collecting device
(18) and from the second coolant collecting device (18) the second coolant passage portion (19,19') drawn.
5. exhaust-driven turbo-charger exhaust-gas turbo charger (1) as claimed in claim 1 or 2, which is characterized in that the second coolant channel structure
(14) and the first coolant channel structure (13) flows connection each other.
6. exhaust-driven turbo-charger exhaust-gas turbo charger (1) as claimed in claim 4, which is characterized in that the first coolant passage portion
The flowing of (16a, 16b, 16c, 16d, 16e) and the second coolant passage portion connects.
7. exhaust-driven turbo-charger exhaust-gas turbo charger (1) as claimed in claim 1 or 2, which is characterized in that be equipped with and be used for second coolant
At least one coolant intake line (20) of channel design (14) and be equipped be used for the first coolant channel structure
(13) at least one coolant output pipe (17), or in turn.
8. exhaust-driven turbo-charger exhaust-gas turbo charger (1) as claimed in claim 1 or 2, which is characterized in that the compressor (2) has compression
Machine shell, the compressor case have outside at least one the first compressor case part (7a) and at least one second compressor
Shell parts (7b).
9. exhaust-driven turbo-charger exhaust-gas turbo charger (1) as claimed in claim 1 or 2, which is characterized in that the turbocharger is high pressure whirlpool
Take turns booster.
10. a kind of internal combustion engine, the internal combustion engine has at least one according to claim 1 to exhaust gas whirlpool described in any one of 9
It takes turns booster (1).
Applications Claiming Priority (3)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| ATA50242/2015A AT516978B1 (en) | 2015-03-26 | 2015-03-26 | MULTI-STAGE ABGASTURBOLADER |
| ATA50242/2015 | 2015-03-26 | ||
| PCT/AT2016/050077 WO2016149728A1 (en) | 2015-03-26 | 2016-03-24 | Multi-stage turbocharger |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN107636279A CN107636279A (en) | 2018-01-26 |
| CN107636279B true CN107636279B (en) | 2019-06-04 |
Family
ID=55858728
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201680028699.XA Expired - Fee Related CN107636279B (en) | 2015-03-26 | 2016-03-24 | Multi-stag exhaust-driven turbo-charger exhaust-gas turbo charger and internal combustion engine |
Country Status (4)
| Country | Link |
|---|---|
| CN (1) | CN107636279B (en) |
| AT (1) | AT516978B1 (en) |
| DE (1) | DE112016001401A5 (en) |
| WO (1) | WO2016149728A1 (en) |
Families Citing this family (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US10190596B2 (en) * | 2016-11-03 | 2019-01-29 | Garrett Transportation I Inc. | Two-stage compressor with asymmetric second-stage inlet duct |
| DE102017114232A1 (en) | 2017-06-27 | 2018-12-27 | Ebm-Papst Mulfingen Gmbh & Co. Kg | Return geometry of a turbocompressor |
| DE102021126261B3 (en) | 2021-10-11 | 2023-03-30 | Audi Aktiengesellschaft | Method for operating a drive device and corresponding drive device |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US7014418B1 (en) * | 2004-12-03 | 2006-03-21 | Honeywell International, Inc. | Multi-stage compressor and housing therefor |
| DE102007023142A1 (en) * | 2007-05-16 | 2008-11-20 | Audi Ag | Exhaust gas compressor for automotive exhaust gas turbocharger has spiral wall incorporating cooling duct |
| DE102009001321A1 (en) * | 2009-03-04 | 2010-09-16 | Ford Global Technologies, LLC, Dearborn | Supercharged internal combustion engine has intake line for supplying internal combustion engine with combustion air and compressor arranged in intake line |
| WO2012107481A1 (en) * | 2011-02-10 | 2012-08-16 | Continental Automotive Gmbh | Turbocharger with cooled turbine housing, cooled bearing housing, and a common coolant supply |
| DE102013203376A1 (en) * | 2013-02-28 | 2014-08-28 | Ford Global Technologies, Llc | Liquid-cooled radial-flow turbine for exhaust gas turbocharger of motor car, has bearing housing comprising coolant cladding integrated in bearing housing and arranged adjacent and spaced apart to assembly flange surface in flange |
-
2015
- 2015-03-26 AT ATA50242/2015A patent/AT516978B1/en not_active IP Right Cessation
-
2016
- 2016-03-24 CN CN201680028699.XA patent/CN107636279B/en not_active Expired - Fee Related
- 2016-03-24 WO PCT/AT2016/050077 patent/WO2016149728A1/en active Application Filing
- 2016-03-24 DE DE112016001401.5T patent/DE112016001401A5/en not_active Withdrawn
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| US7014418B1 (en) * | 2004-12-03 | 2006-03-21 | Honeywell International, Inc. | Multi-stage compressor and housing therefor |
| DE102007023142A1 (en) * | 2007-05-16 | 2008-11-20 | Audi Ag | Exhaust gas compressor for automotive exhaust gas turbocharger has spiral wall incorporating cooling duct |
| DE102009001321A1 (en) * | 2009-03-04 | 2010-09-16 | Ford Global Technologies, LLC, Dearborn | Supercharged internal combustion engine has intake line for supplying internal combustion engine with combustion air and compressor arranged in intake line |
| WO2012107481A1 (en) * | 2011-02-10 | 2012-08-16 | Continental Automotive Gmbh | Turbocharger with cooled turbine housing, cooled bearing housing, and a common coolant supply |
| DE102013203376A1 (en) * | 2013-02-28 | 2014-08-28 | Ford Global Technologies, Llc | Liquid-cooled radial-flow turbine for exhaust gas turbocharger of motor car, has bearing housing comprising coolant cladding integrated in bearing housing and arranged adjacent and spaced apart to assembly flange surface in flange |
Also Published As
| Publication number | Publication date |
|---|---|
| CN107636279A (en) | 2018-01-26 |
| WO2016149728A1 (en) | 2016-09-29 |
| AT516978A1 (en) | 2016-10-15 |
| AT516978B1 (en) | 2018-04-15 |
| DE112016001401A5 (en) | 2017-12-07 |
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