CN104481597B - Turbocharger rotor is to Barebone - Google Patents
Turbocharger rotor is to Barebone Download PDFInfo
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- CN104481597B CN104481597B CN201410535119.9A CN201410535119A CN104481597B CN 104481597 B CN104481597 B CN 104481597B CN 201410535119 A CN201410535119 A CN 201410535119A CN 104481597 B CN104481597 B CN 104481597B
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- Prior art keywords
- turbocharger
- armature spindle
- inside race
- association
- turbine
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Abstract
The present invention relates to a kind of turbocharger rotor to Barebone.Wherein, the externally threaded fore-end of band that the female thread boss extended back of the atresia wheel hub compressor drum of turbocharger is corresponding with the associated rotor axle of turbocharger engages, wherein the inner surface of inside race of the relevant rolling element bearing of turbocharger engages with both outer surfaces of the outer surface of armature spindle and the described female thread boss of described atresia wheel hub compressor drum, and wherein said armature spindle extends through the inside race of described rolling element bearing.
Description
Divisional application
The application is the Application No. 201080011742.4 of submission on January 20th, 2010, sends out
The division of the Chinese patent application of bright entitled " there is the turbocharger of turbine nozzle cartridge "
Application.
Cross-Reference to Related Applications
This application claims on January 20th, 2009 submit in first U.S. Provisional Application sequence number
The priority of 61/145,791, it is integrally incorporated by reference in this.
Technical field
The present invention relates to a kind of turbocharger rotor to Barebone.
Summary of the invention
The invention provides a kind of turbocharger rotor to Barebone, including:
A. armature spindle；
B. at least one inside race of rolling element bearing, wherein said armature spindle extends through institute
State at least one inside race described of rolling element bearing；
C. atresia wheel hub compressor drum, described atresia wheel hub compressor drum is combined with and prolongs backward
The female thread boss stretched, the band external screw thread that described female thread boss is corresponding with described armature spindle
Fore-end engage, at least one inside race described of wherein said rolling element bearing interior
The outer surface of surface and described armature spindle and the described female thread of described atresia wheel hub compressor drum
Both outer surfaces of boss engage.
At least one inside race described includes front inside race and rear inside race.
Preferably, multiple rolling elements of described rolling element bearing are around described front inside race and institute
State the axially centered layout in the junction surface between rear inside race.
The externally threaded leading section of described band of described armature spindle is acted on by described female thread boss
On Fen, at least one inside race described is held in shoulder and the described atresia wheel of described armature spindle
Between the rear surface of hub compressor drum.
The diameter of the described outer surface of described female thread boss substantially with described in described armature spindle
The diameter of outer surface is identical.
Accompanying drawing explanation
In the accompanying drawings:
Fig. 1 diagram include a pair cylinder head and with the pair of cylinder head all-in-one-piece corresponding
Isometric view to the first aspect of the internal combustion engine of turbocharger core；
Fig. 2 illustrates cylinder head and the turbocharging of the first aspect from the internal combustion engine shown in Fig. 1
The isometric view of device core；
Fig. 3 illustrates by the cylinder head shown in Fig. 2 and the first cross-sectional view of turbocharger core；
The isogonism of Fig. 4 diagram turbocharger core as used in the embodiment shown in Fig. 1～3
View；
Fig. 5 diagram is from the isometric view of the nozzle barrel assembly of the turbocharger core shown in Fig. 2；
Fig. 6 illustrates by the cylinder head shown in Fig. 2 and the second cross-sectional view of turbocharger core；
Fig. 7 illustrates the horizontal of the turbomachine injection nozzle part by the turbocharger core shown in Fig. 4
Cross-sectional view；
Fig. 8 diagram horizontal horizontal stroke by the bear box part of the turbocharger core shown in Fig. 4
Sectional view；
Fig. 9 illustrates by the cylinder head shown in Fig. 2 and the 3rd cross-sectional view of turbocharger core；
Figure 10 illustrates by the cylinder head shown in Fig. 9 and the 3rd cross-sectional view of turbocharger core
The enlarged drawing of a part；
Figure 11 illustrates has the cavity being suitable for receiving turbocharger core in comfortable cylinder head
The signal of the first alternate embodiment of the interface of multiple grate flow channels of each in multiple cylinders
Figure；
Figure 12 illustrates has the cavity being suitable for receiving turbocharger core in comfortable cylinder head
The signal of the second alternate embodiment of the interface of multiple grate flow channels of each in multiple cylinders
Figure；
Figure 13 diagram combines the turbocharger being connected to associate exhaust manifold to operably
The isometric view of a part for the second aspect of the internal combustion engine of the first embodiment of assembly；
The turbocharging that the second aspect of Figure 14 diagram and the internal combustion engine shown in Figure 13 is used together
The each several part of the first embodiment of device assembly and the exploded view associating housing；
The turbocharging that the second aspect of Figure 15 diagram and the internal combustion engine shown in Figure 13 is used together
The first embodiment of device assembly and the longitudinal cross-section decomposition view associating housing；
Figure 16 diagram is according to the second embodiment of the turbocharger assembly of the second aspect of internal combustion engine
Imperfect longitudinal sectional view；
Figure 17 illustrates the transverse cross-section of the second embodiment of the turbocharger assembly shown in Figure 16
Face figure；And
Figure 18 diagram has association radial-flow turbine according to the combining of second aspect of internal combustion engine
The 3rd embodiment of turbocharger assembly of second aspect of association turbocharger core.
Detailed description of the invention
With reference to Fig. 1, make the internal combustion engine 14 of a pair turbocharger core 10 and V-structure, 14.1,
Such as V-6 internal combustion engine 14, corresponding a pair cylinder-head assembly 12 of first aspect of 14.1' become one
Body.Such as, according to any one in multiple thermodynamic cycle, described multiple thermodynamic cycle
Include but not limited to such as Otto (Otto) circulation, diesel (Diesel) circulation, Aunar gold
Gloomy (Atkinson) circulation, Miller (Miller) circulation or two-stroke cycle, internal combustion engine 14,
14.1 can be by appointing in the multiple design of one or more operations in polytype fuel
What one, described fuel includes but not limited to gasoline, diesel oil, biodiesel, natural gas, bag
Include liquefied natural gas (LNG) and compressed natural gas (CNG), include liquefied petroleum (LP)
The propane of gas, ethanol or methanol.Referring also to Fig. 2～10, each turbocharger core 10 includes
The compressor 16 driven by Exhaust Pressure turbine 18, wherein, when turbocharger core 10 example
During as being attached to internal combustion engine 14,14.1 by intercooler, each association turbine 18 is inserted
Enter the cavity 20 in respective cylinder head assembly 12, such as cylindrical cavity 20' or volute cavity 20 "
In and cooperate with described cavity 20, described cylinder-head assembly 12 is suitable for via association exhaust stream
Road 24 receives aerofluxus 21 from the cylinder 22 that associates being associated with described cylinder-head assembly 12.Such as,
Turbocharger core 10 combines axial flow turbo-machine 18', axial flow turbo-machine 18' and can construct
Have a relatively low association rotary inertia, thus provide for internal combustion engine 14,14.1 operation associated
The relatively quick dynamic response of condition change.In the first aspect of internal combustion engine 14,14.1,
Off-axis at the central axis 28 relative to cavity 20 from the grate flow channel 24 of each cylinder 22
Position connect with the public first row QI KOU 26 in the side of cavity 20, to cause stream
Enter aerofluxus 21 therein to circulate.
Turbocharger core 10 includes the turbine rotor 30 of turbocharger rotor assembly, turbine
The turbine rotor 30 of supercharger rotor assembly is connected to be supported group by armature spindle to operably
The rear end 32.1 of the armature spindle 32 of the turbocharger rotor assembly that part is rotatably supported,
Described rotor shaft supporting component includes being positioned at association bear box 38 and being spaced from each other along it
Rear shaft neck bearing 34 and front rolling element bearing 36.Combine and import in bear box 38
42 cooling jackets 40 being in fluid communication with outlet 44, described import 42 and outlet 44 are suitable for
Cooling current are received for cooling rear shaft neck axle from the water cooling system 46 of internal combustion engine 14,14.1
Holding 34 and front rolling element bearing 36, wherein, one group of import 42 and outlet 44 are used for internal combustion
The side of machine 14,14.1, and another group import 42' and outlet 44' be used for internal combustion engine 14,
The opposite side of 14.1, import 42', 42 and outlet 44', being not used by 44 of either side
One group blocked.Oil-in 48 is suitable for receiving a certain amount of from the oil pump of internal combustion engine 14,14.1
Pressurization machine oil and via association oil distribution passage 50 this oil is assigned to rear shaft neck bearing 34
With front rolling element bearing 36.Discharge from rear shaft neck bearing 34 and front rolling element bearing 36
Oil is collected in the oil return cavity 52 in the base of bear box 38 by gravity, and via at axle
The base position holding housing 38 is connected to associate the association oil return circuit 54 of oil return opening 54' (at Figure 13
Middle diagram) return to internal combustion engine 14,14.1.
It should be understood that rotor shaft supporting component is not limited to rear shaft neck bearing 34 and front rolling element
The combination of bearing 36, but rotor shaft supporting component can alternatively include axle journal and rolling element
Any combination of bearing or it is contemplated that the single extending length bearing of journals.
The compressor 16 of turbocharger core 10 includes being connected to armature spindle 32 to operably
Front end 32.2 and be suitable for therewith around turbocharger core 10 central axis 28' revolve
The compressor drum 56 of the turbocharger rotor assembly turned, wherein, central axis 28' is substantially
It is directed at the central axis 28 of cavity 20.Such as, in one embodiment, compressor drum
56 combine the front end being threadedly coupled to armature spindle 32 according to alleged atresia wheel hub
The female thread boss (boss) 58 that extends back on 32.2, and turbine rotor 30 is along whirlpool
The periphery of the cavity 60 between front end and the rear end 32.1 of armature spindle 32 of turbine wheel 30 is welded
Receiving the rear end 32.1 of armature spindle 32, it is for reducing from turbine rotor 30 to armature spindle 32
Heat transfer.Front rolling element bearing 36 is included between compressor drum 56 and shoulder 32.3
The outer race 62 being positioned on armature spindle 32 and front inside race 64 and rear inside race 66, outer race
62 and front inside race 64 and rear inside race 66 for armature spindle 32 is positioned bear box 38
In.Bear box 38 combines front sealing member 70 and rear sealing member 72, described front sealing member 70
The pressure leaking into turbocharger core 10 from bear box 38 for preventing oil with rear sealing member 72
In contracting machine 16 or turbine 18.
With reference to Fig. 4,5,6 and 8～10, turbocharger core 10 also includes to operably
It is connected to the turbomachine injection nozzle cartridge module 74 of the rear side 38.1 of bear box 38.Turbomachine injection nozzle
Cartridge module 74 include front nozzle wall 76, the rear nozzle wall 78 separated backward with front nozzle wall 76,
Multiple blades 80 of being arranged between front nozzle wall 76 and rear nozzle wall 78, from rear nozzle wall 78
The turbine rotor cover portion 82 extended back and the nozzle row extended back from throat 82
Gas part 84.Although nozzle exhaust part 84 is illustrated as having the diameter of expansion relatively for extremely
Partially diffusion association aerofluxus, but nozzle exhaust part 84 is not necessarily required in diametrically phase
Association turbine rotor cover portion 82 is expanded relatively.
Such as, in one embodiment, front nozzle wall 76 is formed the first sheet metal element,
And rear nozzle wall 78 and turbine rotor cover portion 82 and the combination of nozzle exhaust part 84
Be formed the second sheet metal element the most each by punching press or spin formed；And
And blade 80 is each is formed such as by punching press and be inserted into and subsequently by sheet metal
Be welded or brazed onto in each in front nozzle wall 76 and rear nozzle wall 78 multiple accordingly
Slit 86.In another embodiment, rear nozzle wall 78, turbine rotor cover portion 82 and
Nozzle exhaust part 84 is each by the most such as passing through welding, brazing and/or being connect by press-fit
Two or more sheet metal piece separated being combined are formed.Alternately, can be to whirlpool
Turbine nozzle barrel assembly 74 casts or sinters, the most laser sintered.Turbine nozzle cartridge group
Part 74 is by that provide high temperature oxidation resistance and intensity, to be resistant to high-temperature exhaust air 21 material structure
Becoming, such as nickel alloy, such as, have the rustless steel of relatively high nickel content, such as 310 is stainless
Steel.The remainder of turbocharger core 10 be water or oil cooled can be by not that
Special and more cost effective material is constituted, such as aluminum or cast iron.Such as, except water-cooled footstep
Outside housing 38, can repair with the water cooling passageway with its exhaust casing part 88 thermal communication
Change cylinder-head assembly 12, thus allow the material (such as aluminum) of relatively low cost for its structure
Make.Therefore, turbocharger core 10 separate turbomachine injection nozzle cartridge module 74 and possible its
Comparing of its mode allows the most more economical use of exotic material to be such as confined to whirlpool
Turbine nozzle barrel assembly 74, and also allow turbocharger core 10 is integrated into cylinder head
In assembly 12.Such as, turbomachine injection nozzle cartridge module 74 is manufactured relative with cylinder-head assembly 12
The combined amount of the original material needed for simpler association exhaust casing part 88 will be less than manufacture etc.
The amount of the same material needed for conventional turbochargers exhaust casing.
In another embodiment, utilize permission in the case of the fault of its association turbo blade 92
The turbine of turbomachine injection nozzle cartridge module 74 reinforced by the sleeve 90 that accommodates accommodating turbine rotor 30
Machine rotor cover portion 82.
Turbomachine injection nozzle cartridge module 74 extend through the cavity 20 in cylinder-head assembly 12,20',
20″.In operation, the aerofluxus 21 from cylinder 22 is led to by association grate flow channel 24 inflow
Cavity 20,20', 20 " first row QI KOU 26, i.e. in cavity import air vent 26, wherein,
First row QI KOU 26 relative to cavity 20,20', 20 " off-axis position cause cavity 20,20',
20 " whirlpool of the aerofluxus 21 of flowing in.Aerofluxus 21 is then along turbomachine injection nozzle cartridge module 74
Blade 80 and abut against the turbo blade 92 of turbine rotor 30 and flow into turbine spray with whirlpool
In the peripheral inlet 93 of mouth cartridge module 74, thus drive turbine rotor 30, turbine rotor
30 make again armature spindle 32 and are attached to the compressor drum 56 of armature spindle 32 and rotate.Aerofluxus 21
Then be discharged to and pass through from cavity 20,20', 20 " rear end 20.1 counterbore 96 open
Begin to flow through turbine nozzle cartridge before the second exhaust port 94 of extension, i.e. cavity outlet air vent 94
The nozzle exhaust part 84 of assembly 74, wherein, second exhaust port 94 is connected to engine exhaust
System 98, engine exhaust system 98 such as can include one or more exhaust gas treatment device
100, the most one or more catalytic converters or acoustic filter.Cylinder-head assembly 12 can be in conjunction with
There is the exhaust gas valve 99 of operation between grate flow channel 24 and second exhaust port 94, thus allow to make
Aerofluxus 21 do not first flow through turbomachine injection nozzle cartridge module 74 with associate turbine rotor 30 feelings
Directly bypass to engine exhaust system 98 under condition.Therefore, before turbomachine injection nozzle cartridge module 74
Nozzle wall 76 makes circumference become the aerofluxus 21 of whirlpool at turbine nozzle cartridge with rear nozzle wall 78
Cavity 20 outside assembly 74,20', 20 " in flowing radially inward and the most backward
Alter course and accelerate, and then the whirlpool aerofluxus 21 flowed axially backward obtained impinges upon turbine
On the turbo blade 92 of machine rotor 30, thus drive turbine rotor 30, wherein, at one
In embodiment, the association blade 80 cooperated with front nozzle wall 76 and rear nozzle wall 78 is suitable for permitting
Permitted the aerofluxus 21 suitable vector orientation relative to turbine rotor 30 of collision, so that whirlpool
The efficiency of turbine 18 maximizes.
The rear end 84.1 of the nozzle exhaust part 84 of turbomachine injection nozzle cartridge module 74 combines outside
Sealing surfaces 102, outer seal surface 102 with in the interior grooves 106 being positioned in counterbore 96
Sealing ring such as piston ring seal ring 104' cooperation, thus allow by turbine spray
The outlet side 108 of mouth cartridge module 74 is sealed to the exhaust casing part 88 of cylinder-head assembly 12,
So that essentially all aerofluxus 21 is discharged to from turbomachine injection nozzle cartridge module 74 and is passed through second
Outlet 94 also enters in association engine exhaust system 98, thus substantially makes at turbine
The cavity 20 of nozzle barrel assembly 74 upstream, 20', 20 " in aerofluxus 21 with from turbine nozzle cartridge
The aerofluxus 21 that assembly 74 is discharged is isolated.The sealing ring 104 cooperated with outer seal surface 102
Allow for turbomachine injection nozzle cartridge module 74 outlet side 108 can in response to its thermic expand or
It is contracted in expansion or shrinkage sliding in the axial direction in the radial direction, is simultaneously held in turbine
Air-proof condition at the outlet side 108 of machine nozzle cartridge module 74, and there is no turbine nozzle cartridge group
The significantly association thermic of part 74 loads.
The front end 76.2 of front nozzle wall 76 include coordinate from the rear side 38.1 of bear box 38 to
Tubular antelabium 110 on the corresponding tubular step 112 of rear extension.Turbomachine injection nozzle cartridge module 74
By the respective radial holes 116 extended through in tubular antelabium 110 and enter in tubular step 112
Multiple radial peg 114 of corresponding blind radial hole 118 be maintained on bear box 38.Radially
Pin 114 is symmetrically located at tubular antelabium 110 and tubular step 112 with associating radial hole 116,118
Circumference.Internal diameter and the external diameter of tubular step 112 of tubular antelabium 110 can be adjusted,
Make at ambient temperature, tubular antelabium 110 and tubular step 112 interference engagement.But,
Under the operating temperature improved, front nozzle wall 76 and the tubular antelabium 110 associated respectively responsive to
The difference of front nozzle wall 76 and the temperature of bear box 38 or thermal expansion rates is releasably fastened to cylinder
Shape step 112 carries out thermal expansion, in this case, radial peg 114 the tubular lip carried out
The joint of edge 110 allows turbomachine injection nozzle cartridge module 74 is remained to bear box 38, and closes
Connection radial peg 114 is arranged symmetrically with for keeping turbomachine injection nozzle with associate radial hole 116,118
Cartridge module 74 in the range of its thermal technology makees substantially with the central axis 28' of turbocharger core 10
With one heart.Such as, in the normal operation period, turbomachine injection nozzle cartridge module 74 and bear box 38
Compare and will relatively faster heat and reach the most higher temperature as a result, tubular antelabium 110
Internal diameter typical case will expand, thus more than the external diameter of tubular step 112, thus from ambient temperature
Under may interfere transit to improve at a temperature of substantially loose fit, in this case, footpath
To be used for tubular antelabium 110 is symmetrically and concentrically maintained at tubular step 112 to pin 114
On, thus keep the relative alignment of turbomachine injection nozzle cartridge module 74 and association turbine rotor 30.
Alternately, the front end 76.2 of front nozzle wall 76 can centered by bear box 38,
Wherein, multiple axial pin is extended back or bolt extends through from the rear side 38.1 of bear box 38
Corresponding radial slot in the front end 76.2 of front nozzle wall 76, and be bolted or by before cavity 20
Step in end is maintained on bear box 38.
When turbomachine injection nozzle cartridge module 74 is assembled into bear box 38, turbine rotor 30
Turbo blade 92 be positioned at the turbine rotor cover portion 82 of turbomachine injection nozzle cartridge module 74,
This turbine rotor cover portion 82 accordingly acts as turbine blade tip shroud 82', wherein, turbo blade
The internal diameter of integral shroud 82' is adapted to provide for about 0.01 inch of the tip 120 of turbo blade 92
Clearance, the tolerance limit offer of this relative close otherwise may make changing of the turbine 18 that clearance is bigger
Kind efficiency.Therefore, utilize turbine blade tip shroud 82', be maintained on bear box 38 and in chamber
Body 20,20', 20 " in counterbore 96 in the most floating turbomachine injection nozzle cartridge module 74 one
The exhaust casing part 88 of part, i.e. turbine blade tip shroud 82' not subject cylinder head assembly 12, example
As wherein or come from its thermic stress or the impact of its external mechanical load, its otherwise its
The tip 120 with turbo blade 92 may be caused to interfere, enabling use and produce hardware and journey
It is relative that sequence is easily achieved between turbine blade tip shroud 82' and the tip 120 of turbo blade 92
Little clearance.
Turbocharger core 10 utilizes multiple bolt 122 to be assembled into cylinder-head assembly 12, described many
Association flange 125 that is that individual bolt 122 passes through bear box 38 or that extend from bear box 38
Or corresponding multiple holes 124 in flange group 126', by adapter bush 128 and enter cavity 20,
20', 20 " around the periphery of the forward part 132 of exhaust casing part 88 of cylinder-head assembly 12
In respective screw hole 130 in so that when being installed to cylinder-head assembly 12, turbocharging
The bear box 38 of device core 10 is for closing the front end of cavity 20, and it is bear box 38 He
The joint of adapter bush 128 and cavity 20,20', 20 " around the periphery of cylinder-head assembly
Sealed at the forward part 132 of the exhaust casing part 88 of 12 and the junction surface of adapter bush 128,
Such as by coordinating flat surfaces as directed or by coordinating conical surface.Connect
The internal diameter of head lining 128 is substantially greater than the front nozzle wall 76 of turbomachine injection nozzle cartridge module 74
The external diameter of tubular antelabium 110, thus in tubular antelabium 110 gap 134 in-between
Unrestricted thermic expand, thus prevent turbomachine injection nozzle cartridge module 74 thermic machinery should
Power, described thermic mechanical stress otherwise expands at the outward radial of tubular antelabium 110 and is otherwise subject to
To occur in the case of the restriction of adapter bush 128.Adapter bush 128 is additionally operable to radial peg
114 captures are in its radial hole 118 in tubular step 112.The rear table of adapter bush 128
Face 136 be positioned and be contoured for from cavity 20', 20 " inner surface 138 to front nozzle wall
The relative smooth transition of 76, thus promote that aerofluxus 21 is from cavity 20', 20 " to turbine nozzle cartridge
Flowing in assembly 74.Such as, in one embodiment, the rear surface 136 of adapter bush 128
Including a part of concavity ring surface 136', it provides inner surface 138 and front spray in terms of cross section
The fillet of 1/4 circle between mouth wall 76.Alternately, can be by by adapter bush 128
Material is bonded directly in the exhaust casing part 88 of cylinder-head assembly 12 substitute adapter bush
128.Additionally, alternately, it is possible to use V-arrangement folder rather than bolt 122 are by turbocharger
Core 10 is installed to the forward part 132 of the exhaust casing part 88 of cylinder-head assembly 12.
In the operation of turbocharger core 10, from first row QI KOU 26 aerofluxus 21 first
It is collected in by the exhaust casing in the cylinder-head assembly 12 outside turbomachine injection nozzle cartridge module 74
The cavity 20 of part 88,20', 20 " the annulus 140 that limited of part in, and so
The turbo blade of turbine rotor 30 is accelerated to afterwards therefrom by turbomachine injection nozzle cartridge module 74
In 92.Turbomachine injection nozzle cartridge module 74 is for guiding exhaust stream and accelerating to turbine rotor
In the turbo blade 92 of 30, and control the association mass flow of these aerofluxuss 21.Accordingly, it is capable to
Enough structure turbomachine injection nozzle cartridge module 74 is independent of the association exhaust casing of cylinder-head assembly 12
Part 88 or cavity 20,20', 20 " design, such as pass through turbine nozzle cartridge by adjustment
Area/the radius ratio (A/R) of the passage 140 of assembly 74 thus be suitable for given internal combustion engine
14, the specific turbocharging requirement of 14.1, it allows to simplify and is tuned to by turbocharger core 10
The process of internal combustion engine 14,14.1, this is because be whirlpool by the unique parts of change in this process
Turbine nozzle barrel assembly 74.Such as, in one group of embodiment, front nozzle wall 76 and rear nozzle wall
78 include corresponding front sweeping surface 76' and rear sweeping surface 78', can make front sweeping surface 76'
Be suitable for the shape of rear sweeping surface 78' with associate blade 80 cooperate for tuning turbine increase
Depressor core 10.
In response to collision aerofluxus 21 thereon, the whirlpool of the turbine 18 of turbocharger core 10
Turbine wheel 30 drives armature spindle 32, the armature spindle 32 rear shaft neck bearing in bear box 38
34 and front rolling element bearing 36 in rotate, and again drive compressor drum 56, compressor
Rotor 56 rotates in the association compressor housing 142 of association compressor 16, and being used for will be from
The air of central inlet 144 is compressed in compressor housing 142, and by turning around compressor
Compressed air discharged by the volute diffuser 146 of son 56.Compressed air is discharged from compressor 16
To being connected to import high-tension room 150, being such as connected to or around being connected to internal combustion engine 14,14.1
The pipeline 148 of throttle body 152 of inlet manifold 154.
With reference to Figure 11 and Figure 12, according to corresponding first alternate embodiment and the second alternate embodiment,
The cavity 20 of the exhaust casing part 88 of cylinder-head assembly 12,20', 20 " may be constructed such that from
Multiple first row QI KOU 26,26.1,26.2,26.3 receive aerofluxus 21, and each air vent is with can
Mode of operation is associated, often with one or more association grate flow channels 24,24.1,24.2,24.3
Individual grate flow channel 24 to operably with one or more cylinders 22 of internal combustion engine 14,14.1
It is associated, wherein, for each first row QI KOU 26,26.1,26.2,26.3, each
Corresponding association grate flow channel 24,24.1,24.2,24.3 is oriented substantially tangentially will row
Gas 21 be incorporated into cavity 20,20', 20 " in so that obtain from each association first exhaust
Mouthfuls 26,26.1,26.2,26.3 cavity 20,20', 20 " in aerofluxus 21 flow public
Whirlpool is formed on whirlpool direction 156.Such as, with reference to Figure 11, in the first alternate embodiment,
Cavity 20,20', 20 " it is connected to that there are three different grate flow channels 24,24.1,24.2,24.3
Three different cylinders in each, each in grate flow channel by separate corresponding the
One air vent 26,26.1,26.2,26.3 aerofluxus 21 is discharged to cavity 20,20', 20 " in,
Wherein, association grate flow channel 24,24.1,24.2,24.3 is oriented such that whole first rows
Aerofluxus 21 is tangentially arranged on public whirlpool direction 156 by QI KOU 26,26.1,26.2,26.3
Go out to cavity 20,20', 20 " in.Additionally, with reference to Figure 12, in the second alternate embodiment,
Cavity 20,20', 20 " it is connected to that there are three different grate flow channels 24,24.1,24.2,24.3
Three different cylinders in each, two grate flow channels in grate flow channel 24,24.1,
Aerofluxus 21 is discharged to cavity by the corresponding first row QI KOU 26,26.1,26.2 separated by 24.2
20,20', 20 " in, the 3rd grate flow channel 24,24.3 in grate flow channel is by aerofluxus 21 row
Going out in second exhaust runner 24,24.2, second exhaust runner 24,24.2 is further through described many
Aerofluxus 21 is discharged to cavity by second the first row QI KOU 26,26.2 in individual first row QI KOU
20,20', 20 " in, wherein, the grate flow channel 24,24.1,24.2 of association is oriented such that
Both first row QI KOU 24,24.1 and second exhaust port 24,24.2 are in public whirlpool direction 156
On aerofluxus 21 is tangentially discharged to cavity 20,20', 20 " in.
By combining turbocharger core 10 in association cylinder-head assembly 12, and it is used for will be around
The association cavity 20 of turbocharger core 10,20', 20 " the association aerofluxus of cylinder-head assembly 12
Housing parts 88 and bear box 38 water cooling, turbocharger core 10 is for the most corresponding
Comparable independent turbocharger assembly needed for the amount of exotic material to compare minimizing high temperature resistant
The amount of material, such as relative to the amount of alloy of high nickel content, this and independent turbocharger assembly
Compare permission and reduce cost.Additionally, combine turbocharger core in association cylinder-head assembly 12
10 for being more closely connected to turbocharger from the cylinder 22 of internal combustion engine 14,14.1
Core 10, this allowed with otherwise in the case of corresponding comparable independent turbocharger assembly
Possible efficiency compares the efficiency of improvement.
With reference to Figure 13～15, according to internal combustion engine second aspect with associate turbocharger assembly
First embodiment, association turbocharger core 10 and the turbocharger exhaust housing 158 separated
Cooperation, its import 160 is connected to the exhaust manifold 162 of internal combustion engine 14,14.2 to operably,
Such as, utilization enters by being positioned at the first flange 166 at the outlet 168 of exhaust manifold 162
It is positioned at multiple spiral shells of the second flange 170 at the import 160 of turbocharger exhaust housing 158
Bolt 164 carries out described connection.Import 160 is via first row QI KOU 26' and turbocharger exhaust
" fluid communication, first row QI KOU 26' is positioned as guiding association cavity 20 in housing 158
The center of aerofluxus 21 deviation, thus at cavity 20 " in cause the eddy current of aerofluxus 21.Turbine sprays
The bear box 38 of the turbocharger core 10 that mouth cartridge module 74 is attached as above
Utilize by bear box 38 and enter the turbocharger exhaust housing 158 around side face 172
On association threaded socket 176 in multiple bolts 174 be bolted to the whirlpool around cavity 20'
The side face 172 of wheel supercharger exhaust casing 158 so that the turbomachine injection nozzle cartridge module 74 of association
Extend through association second exhaust port 94' on the opposition side of cavity 20 " and entering at cavity 20 ".
Second exhaust port 94' combines the sealing ring 104 in interior grooves 106, sealing ring 104 with
Associated external on the rear end 84.1 of the nozzle exhaust part 84 of turbomachine injection nozzle cartridge module 74 is close
Envelope surface 102 cooperates, thus for the outlet side 108 of turbomachine injection nozzle cartridge module 74 is sealed
To turbocharger exhaust housing 158, so that essentially all aerofluxus 21 is by from turbomachine injection nozzle
Cartridge module 74 is discharged to second exhaust port 94 and passes through second exhaust port 94 and enter sending out of association
In motivation gas extraction system 98, thus substantially by the chamber in turbomachine injection nozzle cartridge module 74 upstream
Body 20 " in aerofluxus 21 isolate with the aerofluxus 21 discharged from turbomachine injection nozzle cartridge module 74.With
The sealing ring 104 of outer seal surface 102 cooperation is for making turbomachine injection nozzle cartridge module 74
Outlet side 108 can extend in radial directions in response to its thermic expansion or shrinkage or shrink also
Slide in the axial direction, be simultaneously held at the outlet side 108 of turbomachine injection nozzle cartridge module 74
Air-proof condition, and do not have the significantly association thermic of turbomachine injection nozzle cartridge module 74 to load.
In operation, the aerofluxus 21 from exhaust manifold 162 flows into turbocharger exhaust housing
The import 160 of 158 also subsequently enters association cavity 20 ".Aerofluxus 21 is at cavity 20 " in around whirlpool
The outside of turbine nozzle barrel assembly 74 forms whirlpool, and then along its blade 80 and against
The turbo blade 92 turbine rotor 30 flows into the week of turbine nozzle cartridge assembly 74 with whirlpool
In limit import 93, thus driving turbine rotor 30, turbine rotor 30 makes again armature spindle 32
Rotate with the compressor drum 56 being attached to armature spindle 32.Then aerofluxus 21 is being discharged to also
By flowing through turbomachine injection nozzle before second exhaust port 94' in turbocharger exhaust housing 158
The nozzle exhaust part 84 of cartridge module 74, and subsequently into engine exhaust system 98, send out
Motivation gas extraction system 98 such as can include one or more exhaust gas treatment device 100, such as one
Individual or multiple catalyst or acoustic filter.
Turbocharger exhaust housing 158 can be made up of the material of same type such as cast iron,
Or alternatively, utilize the alloy casting that nickel content is relatively high, as can be to exhaust manifold 162
Use.About the first aspect of internal combustion engine, can be by amendment turbomachine injection nozzle cartridge module 74
It is tuned to be suitable for specific electromotor by turbocharger core 10, with turbocharger exhaust shell
Body 158 with associate cavity 20 " design unrelated.
With reference to Figure 16 and Figure 17, according to being suitable for and the second aspect one of internal combustion engine 14,14.2
Act the second embodiment of the association turbocharger assembly used, the turbocharger exhaust of association
Housing 158 combines internal heat shield piece 178, and internal heat shield piece 178 is such as by being resistant to
The sheet material of high-temperature exhaust air 21 is constituted, and such as nickel alloy such as has relatively high nickel and contains
The rustless steel of amount, such as, 310 rustless steels, it provides high temperature oxidation resistance and intensity.Turbine increases
Aerofluxus 21 in depressor exhaust casing 158 is substantially contained within the interior of internal heat shield piece 178
In surface 178.1, the latter therein combines the indenture 180 that multiple outside is prominent, the plurality of
Outside prominent indenture 180 is for associate the space 182 appearance by internal heat shield piece 178
Face 178.2 separates with the inner surface 158.1 of turbocharger exhaust housing 158, associates space 182
Pass for reducing the conduction heat from internal heat shield piece 178 to turbocharger exhaust housing 158
Pass.Therefore, internal heat shield piece 178 provides radiant heat shielding and conduction heat shielding.
Although illustrating internal heat shielding under the background of the second aspect of internal combustion engine 14,14.2
Shield 178, i.e. in the outside of association cylinder-head assembly 12, but at the of internal combustion engine 14,14.2
On the one hand under background internal heat shield piece 178 be probably it is particularly advantageous that i.e. with associate cylinder
Head assembly 12 is integrated, thus is used for substantially reducing and is transferred to cylinder-head assembly 12 from aerofluxus 21
Heat, otherwise its by need removed by the association water cooling system 46 of internal combustion engine 14,14.2.
Such as, there is 6mm wall thickness and be lined with and associate turbocharger core 10 having to combine
The association aluminum cylinder-head assembly of the cavity 20 of the inside heat shield piece 178 that the 1.5mm of cooperation is thick
In one simulation embodiment of the first aspect of the internal combustion engine 14,14.1 of 12, for 1050
For aerofluxus 21 under degree Celsius, the heat transfer of association is reduced to 1.80 thousand from 8.20 kilowatts
Watt, and the heat transfer coefficient associated is decreased to about every Kelvin temperature from about every Kelvin 9 watts
Spending 2 watts, internal heat shield piece 178 operates under about 904 degrees Celsius.
Have been illustrated for being configured with the turbocharger core 10 of axial flow turbo-machine 18' above,
Wherein, the aerofluxus 21 discharged from the nozzle segment 74.1 of turbomachine injection nozzle cartridge module 74 by along
Substantial axial backward directions 184 are directed to backward and abut against and are positioned at after front nozzle wall 76
The turbo blade 92 of associated shaft flow turbine 18', blade 80 and turbine nozzle cartridge group
The nozzle segment 74.1 of part 74.
Alternately, with reference to Figure 18, in conjunction with having association radial-flow turbine 18 " and corresponding
The second aspect diagram of the association turbocharger core 10' of association turbomachine injection nozzle cartridge module 74' depends on
According to the 3rd embodiment of the turbocharger assembly that the second aspect of internal combustion engine is revised, it is used for
Generally radially in inward direction 186 by association aerofluxus 21 from turbomachine injection nozzle cartridge module 74
Nozzle segment 74.1' be discharged to and abut against the association footpath of the radially inner side being positioned at front nozzle wall 76
The turbo blade 92' of flow turbine 18', blade 80 and turbomachine injection nozzle cartridge module 74'
Nozzle segment 74.1'.
Additionally, alternately, it is possible to use combined flow turbine, the radial-flow type i.e. combined and axle
Flow turbine revises turbocharger core 10, and association turbomachine injection nozzle cartridge module 74 is suitable for
Cooperate, but generally constructed as described above ground, the combined flow turbine machine rotor of association
It is positioned at the nozzle segment 74.1 of front nozzle wall 76, blade 80 and turbomachine injection nozzle cartridge module 74
Rear portion and radially inner side, and between it, there is the taper border of association.
Furthermore, it is to be understood that the first aspect of association internal combustion engine mentioned above or second party
Face may adapt to allow exhaust gas valve 99 to allow around turbocharger core 10 as from internal combustion
The aerofluxus 21 of machine 14,14.1,14.2 sets bypass, i.e. so that some or all aerofluxus 21
Can flow to from grate flow channel 24 and exhaust manifold 162 in the case of without flow through turbine 18
Engine exhaust system 98.
Turbomachine injection nozzle cartridge module 74 is used for easily being mated by turbocharger core 10 or tuning
To specific engine 14,14.1,14.2, this is because typical case will need not repair during this process
Change the association aerofluxus of other parts particularly cylinder-head assembly 12 of turbocharger core 10
Housing parts 88 or association turbocharger exhaust housing 158.Additionally, at turbine nozzle cartridge
Assembly 74 is arranged from association exhaust casing part 88 or the association turbocharger of cylinder-head assembly 12
Gas housing 158 separate and relative to cylinder-head assembly 12 association exhaust casing part 88 or close
In the case of connection turbocharger exhaust housing 158 is the most floating, turbocharger core 10
The mode of production can be suitable for use with the tip 120 of turbine blade tip shroud 82' and turbo blade 92
Between relatively small clearance be operated, and within its life-span, there is no turbocharger core 10
Operation during its between the danger of interference.
Although describing and illustrate in the accompanying drawings specific enforcement in aforementioned detailed description in detail
Example, but those skilled in the art is it will be recognized that can make according to the general teachings content of the disclosure
Go out the various amendments to those details and replacement.It it should be understood that in this article to term "or"
Any with reference to meaning " hold concurrently or " or be also referred to as " logic or ", wherein, if A
Or B is true, if or A and B be very, then expression formula " A or B " is true.
Therefore, disclosed specific arrangements is merely intended to illustrative, and about the model of the present invention
Enclose is not restrictive, and the scope of the present invention is by given appended claims and any
Complete width with all equivalents.
Claims (5)
1. turbocharger rotor is to a Barebone, including:
A. armature spindle；
B. at least one inside race of rolling element bearing, the leading section of wherein said armature spindle is prolonged
Extend through at least one inside race described of described rolling element bearing；
C. atresia wheel hub compressor drum, described atresia wheel hub compressor drum is combined with and prolongs backward
The female thread boss stretched, described female thread boss is relative with the described leading section of described armature spindle
The externally threaded fore-end of band answered engages, described at least the one of wherein said rolling element bearing
The outer surface of the described leading section of the inner surface of individual inside race and described armature spindle and described atresia wheel
Both outer surfaces of the described female thread boss of hub compressor drum engage.
Turbocharger rotor the most according to claim 1 is to Barebone, wherein, described
At least one inside race includes front inside race and rear inside race.
Turbocharger rotor the most according to claim 2 is to Barebone, wherein, described
Multiple rolling elements of rolling element bearing are around between described front inside race and described rear inside race
The axially centered layout in junction surface.
Turbocharger rotor the most according to claim 1 is to Barebone, wherein, passes through
Before the described band of the described leading section that described female thread boss acts on described armature spindle is externally threaded
In end portion, at least one inside race described is held in the described leading section of described armature spindle
Between the rear surface of shoulder and described atresia wheel hub compressor drum.
Turbocharger rotor the most according to claim 1 is to Barebone, wherein, described
The diameter of the described outer surface of female thread boss and the described leading section of described armature spindle described outside
The diameter on surface is identical.
Applications Claiming Priority (2)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| US14579109P | 2009-01-20 | 2009-01-20 | |
| US61/145,791 | 2009-01-20 |
Related Parent Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201080011742.4A Division CN102348868B (en) | 2009-01-20 | 2010-01-20 | Turbocharger core and turbine nozzle cartridge assembly |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN104481597A CN104481597A (en) | 2015-04-01 |
| CN104481597B true CN104481597B (en) | 2017-01-04 |
Family
ID=
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| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN1050591A (en) * | 1989-09-08 | 1991-04-10 | 株式会社东芝 | Fluid compression engine |
| US5536144A (en) * | 1994-10-13 | 1996-07-16 | General Motors Corporation | Turbocharger turbine wheel and shaft assembly |
| CN1245863A (en) * | 1998-07-29 | 2000-03-01 | 亚瑞亚·勃朗勃威力有限公司 | Radial bearing |
| CN1273622A (en) * | 1997-08-06 | 2000-11-15 | 联合讯号公司 | Turbocharger integrated bearing system |
| US6920754B2 (en) * | 2003-05-05 | 2005-07-26 | Honeywell International, Inc. | High-pressure ratio turbocharger |
| CN1846067A (en) * | 2003-08-28 | 2006-10-11 | 通用电气公司 | Turbocharger compressor wheel having a counterbore treated for enhanced endurance to stress-induced fatigue and configurable to provide a compact axial length |
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN1050591A (en) * | 1989-09-08 | 1991-04-10 | 株式会社东芝 | Fluid compression engine |
| US5536144A (en) * | 1994-10-13 | 1996-07-16 | General Motors Corporation | Turbocharger turbine wheel and shaft assembly |
| CN1273622A (en) * | 1997-08-06 | 2000-11-15 | 联合讯号公司 | Turbocharger integrated bearing system |
| CN1245863A (en) * | 1998-07-29 | 2000-03-01 | 亚瑞亚·勃朗勃威力有限公司 | Radial bearing |
| US6920754B2 (en) * | 2003-05-05 | 2005-07-26 | Honeywell International, Inc. | High-pressure ratio turbocharger |
| CN1846067A (en) * | 2003-08-28 | 2006-10-11 | 通用电气公司 | Turbocharger compressor wheel having a counterbore treated for enhanced endurance to stress-induced fatigue and configurable to provide a compact axial length |
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Granted publication date: 20170104 Termination date: 20220120 |