CN107636279A - Multi-stag exhaust-driven turbo-charger exhaust-gas turbo charger - Google Patents
Multi-stag exhaust-driven turbo-charger exhaust-gas turbo charger Download PDFInfo
- Publication number
- CN107636279A CN107636279A CN201680028699.XA CN201680028699A CN107636279A CN 107636279 A CN107636279 A CN 107636279A CN 201680028699 A CN201680028699 A CN 201680028699A CN 107636279 A CN107636279 A CN 107636279A
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- Prior art keywords
- compressor
- exhaust
- charger
- cooling agent
- channel structure
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- 239000002826 coolant Substances 0.000 claims abstract description 88
- 238000011144 upstream manufacturing Methods 0.000 claims abstract description 8
- 238000002485 combustion reaction Methods 0.000 claims description 8
- 230000002093 peripheral effect Effects 0.000 claims description 7
- 239000004744 fabric Substances 0.000 claims 1
- 239000007789 gas Substances 0.000 description 25
- 238000001816 cooling Methods 0.000 description 12
- 230000006835 compression Effects 0.000 description 9
- 238000007906 compression Methods 0.000 description 9
- 239000000463 material Substances 0.000 description 3
- 238000012546 transfer Methods 0.000 description 3
- 238000005266 casting Methods 0.000 description 2
- 239000000567 combustion gas Substances 0.000 description 2
- 238000013461 design Methods 0.000 description 2
- 238000010438 heat treatment Methods 0.000 description 2
- 239000007788 liquid Substances 0.000 description 2
- 239000010721 machine oil Substances 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
- 229910052799 carbon Inorganic materials 0.000 description 1
- 239000003795 chemical substances by application Substances 0.000 description 1
- 239000000110 cooling liquid 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
- 230000002349 favourable effect 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
- 238000000034 method 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
- 238000003860 storage Methods 0.000 description 1
- XLYOFNOQVPJJNP-UHFFFAOYSA-N water Substances O XLYOFNOQVPJJNP-UHFFFAOYSA-N 0.000 description 1
Classifications
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- 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
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02B—INTERNAL-COMBUSTION PISTON ENGINES; COMBUSTION ENGINES IN GENERAL
- F02B29/00—Engines characterised by provision for charging or scavenging not provided for in groups F02B25/00, F02B27/00 or F02B33/00 - F02B39/00; Details thereof
- F02B29/04—Cooling of air intake supply
- F02B29/0406—Layout of the intake air cooling or coolant circuit
- F02B29/0437—Liquid cooled heat exchangers
- F02B29/0443—Layout of the coolant or refrigerant circuit
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
- F02C6/00—Plural gas-turbine plants; Combinations of gas-turbine plants with other apparatus; Adaptations of gas- turbine plants for special use
- F02C6/04—Gas-turbine plants providing heated or pressurised working fluid for other apparatus, e.g. without mechanical power output
- F02C6/10—Gas-turbine plants providing heated or pressurised working fluid for other apparatus, e.g. without mechanical power output supplying working fluid to a user, e.g. a chemical process, which returns working fluid to a turbine of the plant
- F02C6/12—Turbochargers, i.e. plants for augmenting mechanical power output of internal-combustion piston engines by increase of charge pressure
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
- F04D—NON-POSITIVE-DISPLACEMENT PUMPS
- F04D29/00—Details, component parts, or accessories
- F04D29/58—Cooling; Heating; Diminishing heat transfer
-
- 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
Abstract
The present invention relates to a kind of multi-stag exhaust-driven turbo-charger exhaust-gas turbo charger (1), the turbocharger includes exhaust turbine (3) and compressor (2) with least one turbine rotor, and the compressor (2) includes the first compressor stage (4) with the first compressor drum section (6a) and the second compressor stage (5) with the second compressor drum section (6b).Turbine rotor and the second compressor drum section (6b) and the first compressor drum section (6a) are arranged on the common axle rotatably supported around rotation axis (1a).First compressor stage (4) in the upstream of the first compressor drum section (6a) there is the axial compressor for being used to be connected to fresh air conduit to enter pipe joint (8), and there are at least two first helical channel structure (10a in the downstream of the first compressor drum section (6a), 10b, 10c, 10d, 10e), first helical channel structure is transitioned at least two second helical channel structures (11,11') extended in the upstream of the second compressor drum section (6b) of the second compressor stage (5).In order to reduce thermic load, provided with least in the first helical channel structure (10a, 10b, 10c, 10d, the the first coolant channel structure (13) extended between 10e) and/or the second coolant channel structure (14) extended between the second helical channel structure (11,11').
Description
The present invention relates to a kind of multi-stag exhaust-driven turbo-charger exhaust-gas turbo charger for internal combustion engine, particularly high pressure turbocharger,
The turbocharger includes exhaust turbine and compressor with least one turbine rotor, and the compressor 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, its
In, turbine rotor and the second and first compressor drum section be arranged in rotatably supported around rotation axis it is common
Axle on, wherein, the first compressor stage the upstream of the first compressor drum section have be used for be connected to fresh air conduit
Axial compressor enter pipe joint, and there are at least two first helical ducts in the downstream of the first compressor drum section
Structure, these first helical channel structures be transitioned into the second compressor stage the second compressor drum section upstream extend
At least two second helical channel structures.The present invention is additionally related to the internal combustion with least one this exhaust-driven turbo-charger exhaust-gas turbo charger
Machine.
In order to provide higher fuel economy, higher rated power and improved discharge efficiency, needed in internal combustion engine
There is the turbocharger of high compression ratio.
In order to realize high compression ratio, the rotary speed of the active wheel of exhaust-driven turbo-charger exhaust-gas turbo charger can be raised.However, it can make herein
Into the load of the load-bearing capacity beyond material therefor.
The A1 of WO 2012/107481 describe a kind of single stage type exhaust-driven turbo-charger exhaust-gas turbo charger, and the exhaust-driven turbo-charger exhaust-gas turbo charger has
Turbine casing and the bearing case being connected with turbine casing.Cooling agent supply is carried out via turbine casing.In addition, DE
10 2,013 203 376A1 describe for internal combustion engine can liquid cooling single stage type radial turbine, wherein cooling agent leads to
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 is worked together with the compressor being connected in series, 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 to be used to the multi-stag compressor drum on common axle realize each compressor stage, including combination axial compressor like method
Level and radial compressor level.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.
On the other hand, the T2 of DE 699 14 199 show the pressure turbine of the slow operating with two-stage type compressor, wherein,
Turbine rotor and compressor drum are connected to each other via common axle.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 above and the back side
And gas handling system is delivered to therefrom.The B1 of EP 1 825 149 show similar scheme.But by the B1 of US 6,834,501,
A kind of exhaust-driven turbo-charger exhaust-gas turbo charger known to US 6,792,755B2 or the B2 of US 6,920,754, wherein, in two-stage type compressor
Annular gap is configured between front and back.
Although higher compression ratio thus can be realized, 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
It is significantly raised more than 200 DEG C than in the case of.Here, impeller of rotor and turbocharger shell and bearing are by higher warm
Load.In addition, the oil component that can cause to transport together in atmosphere from about 180 DEG C of temperature, such as combustion gas containing machine oil are blocked.
The B1 of EP 1 957 802 suggested using the material of tolerable temperature or in bearing and shaft design in this respect
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 part used.
The task of the present invention is to reduce the thermic load of 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, i.e. be provided with
The first coolant channel structure at least extending between the first helical channel structure and/or between the second helical channel structure
Second coolant channel structure of extension.
By to entering through precompressed air in the first compressor stage, the second compressor stage or the two compressor stages
Row cooling, the present invention allow to cool down air in exhaust-driven turbo-charger exhaust-gas turbo charger.Here, also produce smaller driven compressor
Power and turbine output power and the exhaust back-pressure of reduction.Because 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 follow-up charge-air pipe here, thus in any feelings
Higher thermic load can be reduced under condition.Although air has several with about 25 DEG C of compressor stages of entrance first in its exit air
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 cooling agent structure.Thus, air is maintained in a temperature range,
The oil component transported together in atmosphere, the carbon distribution of such as combustion gas containing machine oil are avoided in the temperature range.
By coolant channel structure, pressurized air is on the one hand cooled down, this causes less pressurized air to cool down heat dissipation capacity
And the efficiency thus improved, on the other hand also cool down compressor case and remaining exhaust-driven turbo-charger exhaust-gas turbo charger.Cooling liquid energy
It is subsequently used for cooling down the bearing of 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, make it 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 referred to as contour area.Because in the region due to the compression to air can produce it is extra high
Thermograde, so effective cooling is particularly advantageous herein.
In a kind of modification of the present invention, the first cooling agent structure extends 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 cooling agent structure is from the second spiral
Region between channel design is extended 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 with the distance with rotation axis
Increase and increase its inner surface, the inner surface provides especially more heat transfer contact surfaces by being surrounded by cooling agent structure.
In order to realize favourable flox condition, the first coolant channel structure has the first coolant collecting device and from first
The the first cooling agent passage portion and/or the second coolant channel structure that coolant collecting device is drawn have the second coolant collecting
Device and the second cooling agent passage portion drawn from the second coolant collecting device.Thus, cooling is provided via coolant collecting device
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 cooling agent structure and the first cooling agent structure (advantageously the first cooling agent passage portion and the second cooling
Agent passage portion) when being connected to each other, particularly effective cooling can be achieved.Thus, simple cooling structure is produced in addition, because can
Save intake line and output pipe.
According to the difference of thermic load, provided with least one cooling agent intake line for the second coolant channel structure and
At least one cooling agent output pipe of first cooling agent structure, or in turn (that is, provided with for the second coolant channel knot
At least one cooling agent output pipe of structure and at least one cooling agent intake line of the first cooling agent structure).It is right that this passes through
The connector answered ensures.Thus, difference as requested, fresh cooling agent are first directed to the second compressor stage or first drawn
Lead to the first compressor stage.
In order that according to the present invention exhaust-driven turbo-charger exhaust-gas turbo charger manufacture become it is easy and advantageously, compressor has
Compressor case, the compressor case carry at least one first compressor case part and at least one second compressor case
Part.Each several part can individually cast, and then be connected to each other.
In addition solves the task of the present invention by the internal combustion engine with least one this exhaust-driven turbo-charger exhaust-gas turbo charger.
Next, further explain the present invention according to non-limitative drawings.It is shown in the drawings：
Fig. 1 illustrates the 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 Fig. 1 exhaust-driven turbo-charger exhaust-gas turbo charger with detail drawing；And
Fig. 3 illustrates the compressor side of the exhaust-driven turbo-charger exhaust-gas turbo charger in Fig. 1 according to Fig. 1 center lines III-III with side view.
Function identical part is provided with identical reference in embodiments.
Fig. 1 schematically illustrates the exhaust-driven turbo-charger exhaust-gas turbo charger 1 of multi-stage compression, and the exhaust-driven turbo-charger exhaust-gas turbo charger includes the He of compressor 2
Exhaust turbine 3, the exhaust turbine 3 have turbine rotor not shown further.Compressor 2 has first pressure in outside
Contracting machine level 4 and the second compressor stage 5 of inner side.The name of outside and inner side is the fresh air on 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 axle that is being rotatably supported around rotation axis 1a and not showing further with giving 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 on the side relative to each other of common compressor drum 6 in the embodiment shown.
Compressor 2 is arranged in compressor case, and the compressor case has the first compressor case part 7a and second
Compressor case part 7b, the two casing parts are connected to each other and sealed.It is disposed with 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 provided with multiple casing parts is also possible.
First compressor case part 7a has in the first compressor drum section 6a upstream to be used to be connected to for inhaling
The axial compressor for entering the fresh air line not shown further of fresh air enters joint 8.Equally also it is not shown
For the compressor for pressurized air at the second compressor case part 7b of the charge-air pipe for being connected to internal combustion engine
Outlet.
The first compressor drum section 6a (outside) the first profile area is directed air into from compressor into joint 8
Domain 9.Contour area refers to the passage between the entrance of compressor drum section and the outlet of compressor drum section herein
Wall segment, particularly air duct are expanded to the section of larger diameter from minor diameter.
In the first compressor drum section 6a upstream, 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 herein with around
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 drawings,
Or the following helical channel structure 11 of only one second discussed further) in.As visible in fig. 3, in illustrated embodiment
In, first helical channel structure 10a, 10b, 10c, 10d, 10e is lain substantially on a circle, and the circle is centrally located at rotary shaft
On line 1a (being orthogonal to plan in figure 3 to extend and be not drawn into).
Second helical channel structure 11,11' equally extend also around rotation axis 1a is circular, but with the first helical duct knot
With the radius reduced with flow direction unlike structure, equally also there is the diameter reduced.Second helical channel structure 11
It is passed through near rotation axis 1a in (inner side) 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 second compressor drum section 6b outlet.
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, the first coolant channel structure 13, the first coolant channel structure are provided with the first compressor stage 4
13 the first cooling agent passage portion 16a drawn with the first coolant collecting device 15 and from the first coolant collecting device 15,
16b, 16c, 16d, 16e (shown in phantom in fig 1 and 2) and it is connected in the embodiment shown with cooling agent output pipe 17.
First coolant collecting device 15 is in the embodiment shown around the annular extension of the second contour area 9.
Second coolant channel structure 14 be arranged in the second compressor stage 5 and with the second coolant collecting device 18 with
And the second cooling agent passage portion 19, the 19'(drawn from the second coolant collecting device 18 is shown in phantom in fig 1 and 2).Second
Coolant channel structure 14 is connected with cooling agent intake line 20.Here, water or other liquid or fluid are used as cooling agent.
Coolant channel structure 13,14 or cooling agent passage portion 16a, 16b, 16c, 16d, 16e, 19 are herein corresponding
Helical channel structure 10a, 10b, 10c, 10d, 10e, 11, extend between 11'.So that in hot key area effectively
Radiate and the temperature of compressed air may remain in optimum range.As shown in Figure 2, coolant channel structure 13,14
In the contour area 9,12 of compressor drum section 6a, 6b corresponding to extending up to, it can be produced at these regions extra high
Thermic load and therefore especially need to radiate.
Fig. 3 shows the sectional view along Fig. 1 line III-III, in top half, the first coolant channel structure 13 or
First cooling agent passage portion 16a, 16b, 16c is between first helical channel structure 10a, 10b, 10c, 10d, 10e
Region, which extends to, to be surrounded in helical channel structure 10a, 10b, 10c, 10d, 10e peripheral region.Here, peripheral region refers to position
The region outside intermediate region between helical channel structure, i.e., around helical channel structure or in the area on its periphery
Domain, wherein, peripheral region is also represented by the region of compressed air impact in terms of heat.First coolant channel structure 13 also includes
Helical channel structure 10a, 10b, 10c, 10d, 10e for optimal heat conduction.Hereby it is achieved that the air duct of heat and cooling are tied
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 sufficiently cool compressor 2 and exhaust-driven turbo-charger exhaust-gas turbo charger 1 is also served as into high pressure turbocharger.Corresponding embodiment
It can set 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 cooling agent passage portion 16a, 16b, 16c, 16d, 16e and the second cooling agent passage portion 19
Carry out.Thus, it is possible to cooling agent intake line 20 is disposed with the region of the second compressor stage 5, then in the first compressor
Cooling agent output pipe 17 is disposed with level 4.It is of course also possible to cooling agent is guided in turn.
As described above, by air guide path and coolant channel form according to the present invention well-formed by tool
There are the first compressor case part 7a and the second compressor case part 7b compressor case to realize：They can simply be poured
Casting forms, such as is formed by the aluminium casting of heat conduction particularly well, and it is close by suitable seal to be assembled into compact medium
The compressor 2 of envelope.
The cooling that the described present invention adds by two-stage supercharging and for one stage of compression allows to be worth mentioning
Heat power advantage, while there is compact structure, the compact structure, 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 domain of main claim
Various remodeling are possible.
Claims (9)
1. a kind of increase for the multi-stag exhaust-driven turbo-charger exhaust-gas turbo charger (1) of internal combustion engine, particularly high pressure turbocharger, the turbine
Depressor includes exhaust turbine (3) and compressor (2) with least one turbine rotor, and the compressor (2) includes band
There are the first compressor stage (4) of the first compressor drum section (6a) and the second pressure with the second compressor drum section (6b)
Contracting machine level (5), wherein, turbine rotor and the second compressor drum section (6b) and first compressor drum section (6a) cloth
Put on the common axle rotatably supported around rotation axis (1a), wherein, first compressor stage (4) is described
There is the axial compressor for being used to be connected to fresh air conduit to enter pipe joint for the upstream of one compressor drum section (6a)
(8), and the downstream of the first compressor drum section (6a) have at least two first helical channel structures (10a,
10b, 10c, 10d, 10e), first helical channel structure is transitioned into being pressed described second for second compressor stage (5)
At least two second helical channel structures (11,11') of the upstream extension of contracting machine rotor section (6b), it is characterised in that be provided with
The the first coolant channel structure at least extended between first helical channel structure (10a, 10b, 10c, 10d, 10e)
(13) the second coolant channel structure (14) and/or between second helical channel structure (11,11') extended.
2. exhaust-driven turbo-charger exhaust-gas turbo charger (1) as claimed in claim 1, it is characterised in that the first coolant channel structure
(13) in the first profile region (9) for extending at least partly into 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, it is characterised in that the first cooling agent structure (13)
Extended to from the region between first helical channel structure (10a, 10b, 10c, 10d, 10e) around at least one or more
In the peripheral region of individual first helical channel structure (10a, 10b, 10c, 10d, 10e) and/or the second cooling agent structure
(14) extend to from the region between second helical channel structure (11) and lead to around at least one or multiple second spirals
In the peripheral region of road structure (11).
4. the exhaust-driven turbo-charger exhaust-gas turbo charger (1) as any one of preceding claims, it is characterised in that first cooling agent
Structure (13) has the first coolant collecting device (15) and the first cooling agent drawn from the first coolant collecting device (15)
Passage portion (16a, 16b, 16c, 16d, 16e) and/or the second cooling agent structure (14) have the second coolant collecting device
(18) the second cooling agent passage portion (19,19') and from the second coolant collecting device (18) drawn.
5. the exhaust-driven turbo-charger exhaust-gas turbo charger (1) as any one of preceding claims, it is characterised in that second cooling agent
Structure (14) and the first cooling agent structure (13) flow connection each other.
6. the exhaust-driven turbo-charger exhaust-gas turbo charger (1) as described in claim 4 or 5, it is characterised in that the first cooling agent passage portion
(16a, 16b, 16c, 16d, 16e) connects with the second cooling agent passage portion (19) flowing.
7. the exhaust-driven turbo-charger exhaust-gas turbo charger (1) as any one of preceding claims, it is characterised in that provided with for described
At least one cooling agent intake line (20) of two cooling agent structures (14) and provided with the first cooling agent structure (13)
At least one cooling agent output pipe (19), or in turn.
8. the exhaust-driven turbo-charger exhaust-gas turbo charger (1) as any one of preceding claims, it is characterised in that the compressor (2)
With compressor case, the compressor case carries at least one first compressor case part (7a) and at least one second
Compressor case part (7b).
A kind of 9. internal combustion with least one exhaust-driven turbo-charger exhaust-gas turbo charger (1) according to any one of claim 1 to 8
Machine.
Applications Claiming Priority (3)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| ATA50242/2015 | 2015-03-26 | ||
| ATA50242/2015A AT516978B1 (en) | 2015-03-26 | 2015-03-26 | MULTI-STAGE ABGASTURBOLADER |
| PCT/AT2016/050077 WO2016149728A1 (en) | 2015-03-26 | 2016-03-24 | Multi-stage turbocharger |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN107636279A true CN107636279A (en) | 2018-01-26 |
| CN107636279B 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
Patent 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 |
Also Published As
| Publication number | Publication date |
|---|---|
| DE112016001401A5 (en) | 2017-12-07 |
| AT516978B1 (en) | 2018-04-15 |
| AT516978A1 (en) | 2016-10-15 |
| CN107636279B (en) | 2019-06-04 |
| WO2016149728A1 (en) | 2016-09-29 |
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