CN102562265A - Two-stage turbocharging system - Google Patents
Two-stage turbocharging system Download PDFInfo
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- CN102562265A CN102562265A CN2012100077748A CN201210007774A CN102562265A CN 102562265 A CN102562265 A CN 102562265A CN 2012100077748 A CN2012100077748 A CN 2012100077748A CN 201210007774 A CN201210007774 A CN 201210007774A CN 102562265 A CN102562265 A CN 102562265A
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- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
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Abstract
The invention discloses a two-stage turbocharging system, which comprises a high-pressure stage turbomachine, a low-pressure stage turbomachine, a high-pressure stage air compressor and a low-pressure stage air compressor. The high-pressure stage turbomachine comprises a first volute casing and a first turbine, wherein the first turbine is arranged in the first volute casing and provided with a plurality of first blades having first bending directions. The low-pressure stage turbomachine comprises a second volute casing and a second turbine, wherein the second turbine is arranged in the second volute casing and provided with a plurality of second blades in directions opposite to the first bending directions. The high-pressure stage air compressor comprises a first casing and a first impeller, wherein the first impeller is arranged in the first casing and driven by the first turbine. The low-pressure stage air compressor comprises a second casing and a second impeller, wherein the second impeller is arranged in the second casing and driven by the second turbine. In the two-stage turbocharging system, the high-pressure stage turbomachine and the low-pressure stage turbomachine are in counter rotating arrangement, so that the efficiency of the low-pressure stage turbomachine is increased and the integral efficiency of the two-stage turbocharging system is increased obviously.
Description
Technical field
The present invention relates to the supercharging equipment field, especially relate to a kind of two stage turbocharging system.
Background technique
In traditional two stage turbocharging system; High-pressure turbine stage outlet port waste gas eddy flow flows to the waste exhaust gases of low pressure stage turbine interior and has negative effect; Increased the loss that low pressure stage turbine wheel internal waste gas flows; It is low and blade tip is high that its reason is that low pressure stage turbine bucket import radial velocity presents root of blade; Cause secondary flow enhancing in the low pressure stage turbine wheel, cause the loss of exhaust energy to strengthen, thereby make the whole efficiency that the low pressure stage turbine efficiency reduces influences two stage turbocharging system.
Summary of the invention
The present invention is intended to solve at least one of technical problem that exists in the existing technology.For this reason, one object of the present invention is to propose a kind of two stage turbocharging system, and said two stage turbocharging system improves the utilization ratio of the exhaust energy of motor greatly.
Two stage turbocharging system according to the embodiment of the invention; Said two stage turbocharging system is suitable for being connected with gas exhaust manifold with the intake manifold of motor; Said two stage turbocharging system comprises: high-pressure turbine stage; Said high-pressure turbine stage comprises: first spiral case and first turbine that is located in said first spiral case; Turn up the soil at interval on the periphery of wherein said first turbine and be provided with a plurality of first blades, each in said a plurality of first blades all has first bending direction, and said first spiral case has first suction port and first air outlet and said first suction port and is suitable for being communicated with said gas exhaust manifold; The low pressure stage turbo machine; Said low pressure stage turbo machine comprises: second spiral case and second turbine that is located in said second spiral case; Turn up the soil at interval on the periphery of wherein said second turbine and be provided with a plurality of second blades; The bending direction of each in said a plurality of second blade is opposite with said first bending direction, and said second spiral case has second suction port and second air outlet and said second suction port and is communicated with said first air outlet; The high pressure stage gas compressor; Said high pressure stage gas compressor comprises: first pressure shell and first impeller that is located in said first pressure shell; Wherein said first impeller is by said first turbine drives, and said first pressure shell has the 3rd suction port and the 3rd air outlet and said the 3rd air outlet and is suitable for being communicated with said intake manifold; With the low pressure stage gas compressor; Said low pressure stage gas compressor comprises: second pressure shell and second impeller that is located in said second pressure shell; Wherein said second impeller is by said second turbine drives, and said second pressure shell has the 4th suction port and the 4th air outlet and said the 4th air outlet and is communicated with said the 3rd suction port.
Two stage turbocharging system according to the embodiment of the invention; First blade and second blade that have opposite directions of curvature through setting make the sense of rotation of first turbine and second turbine opposite; Promptly realized arranging of high-pressure turbine stage and low pressure stage turbo machine, thereby improved the high-pressure turbine stage first outlet port waste gas eddy flow, reduced the low pressure stage turbo machine second turbine internal waste gas flow losses the mobile influence of the waste exhaust gases of low pressure stage turbine interior to changeing; Thereby improved the efficient of low pressure stage turbo machine; The exhaust energy utilization ratio of two stage turbocharging system is obviously improved, effectively promote the power per liter of motor, improved engine power performance.
In addition, the two stage turbocharging system according to the embodiment of the invention also has following additional technical feature:
In one embodiment of the invention, said a plurality of first blade and said a plurality of second blade extending radially outwardly along said first turbine and said second turbine respectively.
In one embodiment of the invention, the external diameter of said second turbine is greater than the external diameter of the external diameter of said first turbine and said second impeller external diameter greater than said first impeller.
In one embodiment of the invention, said first turbine and said first impeller are rigidly connected through first rotating shaft and said second turbine and said second impeller are rigidly connected through second rotating shaft.Thus, make first turbine can drive first impeller rotation synchronously and second turbine can drive the rotation of second impeller synchronously, thereby realize that the high and low pressure stage turbine drives the purpose of the high and low gas compressor of arbitrarily downgrading respectively.
In one embodiment of the invention, said first turbine and said first blade are integral and said second turbine and said second blade are integral.Thus, make things convenient for production and processing, simultaneously intensity is high, can steady in a long-termly use not fragilely, has reduced user cost.
In one embodiment of the invention; Also comprise exhaust gas by-pass valve; One end of said exhaust gas by-pass valve is communicated with said gas exhaust manifold and the other end is communicated with said low pressure stage turbo machine, and said high-pressure turbine stage has the air pressure threshold limit value, when the waste gas air pressure that wherein said motor is discharged surpasses said threshold limit value; Said exhaust gas by-pass valve is opened, and said exhaust gas by-pass valve is closed when the waste gas air pressure of said motor discharge is lower than said threshold limit value.Thus; External diameter through the exhaust gas by-pass valve and second turbine are set is greater than the external diameter of said first turbine, the energy that waste gas had that the high-pressure turbine stage that makes two stage turbocharging system and low pressure stage turbo machine can utilize motor under different operating modes, to discharge better, thus improved the utilization ratio of exhaust energy; The efficient of two stage turbocharging system is improved; Guarantee that simultaneously suction pressure is unlikely to too high, avoided because too high first turbine hypervelocity that causes of suction pressure is beneficial to the two stage turbocharging system stable operation; Not fragile, reduced the working service cost.
In one embodiment of the invention, also comprise first intercooler, said first intercooler is located between said high pressure stage gas compressor and the said low pressure stage gas compressor.Thus,, the temperature of this part air is reduced, get into the air density in the high pressure stage gas compressor thereby improved through being provided for cooling off first intercooler of the air after the compression of low pressure stage gas compressor.
In one embodiment of the invention, also comprise second intercooler, said second intercooler is located between said high pressure stage gas compressor and the said intake manifold.Thus; Through being provided for cooling off second intercooler of the air after the compression of high pressure stage gas compressor, the temperature of this part air is reduced, get into the air density in the engine cylinder thereby improved; Cooperate the extra fuel injection of injection system, the power per liter of motor is obviously promoted.
Tradition is non-to changeing in the two stage turbocharging system; Because high-pressure turbine stage exit gas eddy flow, it is low and blade tip is high to cause low pressure stage turbine bucket inlet air flow radial velocity to present root of blade, and this can cause air-flow secondary flow enhancing in the low pressure stage turbine wheel; Cause the loss of exhaust energy to strengthen; Thereby make the low whole efficiency that influences two stage turbocharging system of low pressure stage turbine efficiency, according to the two stage turbocharging system of the embodiment of the invention, through high-pressure turbine stage and low pressure stage turbo machine are arranged changeing; The inlet air flow radial velocity that makes second blade of second turbine in the low pressure stage turbo machine presents the root height and the tip is low; Thereby effectively suppressed air-flow secondary flow in second turbine, the entropy increase and decrease is little, and the efficient and the exhaust energy utilization ratio that have improved the low pressure stage turbo machine are high; The whole efficiency of two stage turbocharging system is obviously promoted, improved engine power performance greatly.Additional aspect of the present invention and advantage part in the following description provide, and part will become obviously from the following description, or recognize through practice of the present invention.
Description of drawings
Above-mentioned and/or additional aspect of the present invention and advantage obviously with are easily understood becoming embodiment's the description from combining figs, wherein:
Fig. 1 is the schematic representation according to the two stage turbocharging system of the embodiment of the invention;
Fig. 2 is that the master of high-pressure turbine stage and high pressure stage gas compressor looks schematic representation;
Fig. 3 is that the master of low pressure stage turbo machine and low pressure stage gas compressor looks schematic representation;
Fig. 4 is the plan view of high-pressure turbine stage; With
Fig. 5 is the plan view of low pressure stage turbo machine.
Embodiment
Describe embodiments of the invention below in detail, said embodiment's example is shown in the drawings, and wherein identical from start to finish or similar label is represented identical or similar elements or the element with identical or similar functions.Be exemplary through the embodiment who is described with reference to the drawings below, only be used to explain the present invention, and can not be interpreted as limitation of the present invention.
In description of the invention; It will be appreciated that; The orientation of indications such as term " " center ", " vertically ", " laterally ", " on ", D score, " preceding ", " back ", " left side ", " right side ", " vertically ", " level ", " top ", " end " " interior ", " outward " or position relation are for based on orientation shown in the drawings or position relation; only be to describe with simplifying for the ease of describing the present invention; rather than the device or the element of indication or hint indication must have specific orientation, with specific azimuth configuration and operation, therefore can not be interpreted as limitation of the present invention.In addition, term " first ", " second " only are used to describe purpose, and can not be interpreted as indication or hint relative importance.
In description of the invention, need to prove that only if clear and definite regulation and qualification are arranged in addition, term " installation ", " linking to each other ", " connection " should be done broad understanding, for example, can be to be fixedly connected, also can be to removably connect, or connect integratedly; Can be mechanical connection, also can be to be electrically connected; Can be directly to link to each other, also can link to each other indirectly through intermediary, can be the connection of two element internals.For those of ordinary skill in the art, can concrete condition understand above-mentioned term concrete implication in the present invention.In addition, in description of the invention, except as otherwise noted, the implication of " a plurality of " is two or more.
Following with reference to the two stage turbocharging system 100 of figure 1-Fig. 5 description according to the embodiment of the invention; Said two stage turbocharging system 100 is connected with gas exhaust manifold with the intake manifold of motor 200, and is suitable for being used in large truck, heavy truck, light-duty boats and ships etc. and requires on the machinery of the high-power high pressure-charging of motor.
Two stage turbocharging system 100 according to the embodiment of the invention; Comprise high-pressure turbine stage 1, low pressure stage turbo machine 2, high pressure stage gas compressor 3 and low pressure stage gas compressor 4; Wherein high-pressure turbine stage 1 comprises first spiral case 11 and first turbine 12 that is located in first spiral case 11; Wherein turn up the soil at interval on the periphery of first turbine 12 and be provided with a plurality of first blades 121; In a plurality of first blades 121 each all has first bending direction, and first spiral case 11 has first suction port and first air outlet and first suction port and is suitable for being communicated with gas exhaust manifold.Here, bending direction refers to the bending direction of first blade, 121 lamellar bodies, all is known for the one of ordinary skilled in the art about the shape of first blade 121 and bending direction etc., no longer specifies here.Alternatively, high-pressure turbine stage 1 is the single shaft radial-flow turbine.Certainly, the present invention is not limited to this, and in another embodiment of the present invention, high-pressure turbine stage 1 is the single shaft combined flow turbine.
Low pressure stage turbo machine 2 comprises second spiral case 21 and second turbine 22 that is located in second spiral case 21; Wherein turn up the soil at interval on the periphery of second turbine 22 and be provided with a plurality of second blades 221; The bending direction of each in a plurality of second blades 221 is opposite with first bending direction; The bending direction of bending direction and first blade, 121 lamellar bodies that is to say second blade, 221 lamellar bodies is opposite; Waste gas promotes a plurality of first blades 121 and a plurality of second blades 221 successively to drive first turbine 12 and 22 rotations of second turbine respectively like this, owing to the bending direction of first blade 121 and second blade 221 is opposite, thereby makes the sense of rotation of first turbine 12 and second turbine 22 opposite.The sense of rotation of for example supposing first turbine 12 is for turning clockwise; The sense of rotation of second turbine 22 is and is rotated counterclockwise so; Promptly the sense of rotation of first turbine 12 and second turbine 22 is opposite constantly; Effectively weakened of the negative effect of the waste gas eddy flow in high-pressure turbine stage 1 first outlet port thus, improved the efficient of low pressure stage turbo machine 2 low pressure stage turbo machine 2 internal waste gas flow fields.Wherein, second spiral case 21 has second air outlet and second suction port and second suction port and is communicated with first air outlet.Alternatively, low pressure stage turbo machine 2 is the single shaft radial-flow turbine.Certainly, the present invention is not limited to this, and in another embodiment of the present invention, low pressure stage turbo machine 2 is the single shaft combined flow turbine.
High pressure stage gas compressor 3 comprises first pressure shell and first impeller 31 that is located in first pressure shell, and wherein first impeller 31 is driven by first turbine 12, and first pressure shell has the 3rd suction port and the 3rd air outlet and the 3rd air outlet and is suitable for the intake manifold connection.
Low pressure stage gas compressor 4 comprises second pressure shell and second impeller 41 that is located in second pressure shell, and wherein second impeller 41 is driven by second turbine 22, and second pressure shell has the 4th suction port and the 4th air outlet and the 4th air outlet and is communicated with the 3rd suction port.
Two stage turbocharging system 100 according to the embodiment of the invention; First blade 121 and second blade 221 that have opposite directions of curvature through setting make the sense of rotation of first turbine 12 and second turbine 22 opposite; Promptly realized arranging of high-pressure turbine stage 1 and low pressure stage turbo machine 2 to changeing; Thereby improved the influence that high-pressure turbine stage 1 first outlet port waste gas eddy flow flows to low pressure stage turbo machine 2 inner waste exhaust gases; Reduce low pressure stage turbo machine 2 second spiral cases 21 and second turbine, 22 internal waste gas flow losses, thereby improved the efficient of low pressure stage turbo machine 2, the exhaust energy utilization ratio of two stage turbocharging system 100 is obviously improved; And then high pressure stage gas compressor 3 and low pressure stage gas compressor 4 can be got into the more air compression in the cylinder; Cooperate the extra fuel injection of injection system simultaneously, effectively promote the power per liter of motor 200, improved the power performance of motor 200.
In an example of the present invention, a plurality of first blades 121 and a plurality of second blades 221 are respectively along the extending radially outwardly of first turbine 12 and second turbine 22, as shown in Figures 2 and 3.
In one embodiment of the invention, the external diameter of second turbine 22 is greater than the external diameter of the external diameter of first turbine 12 and second impeller 41 external diameter greater than first impeller 31.
In one embodiment of the invention, first turbine 12 and first impeller 31 are rigidly connected through first rotating shaft 5 and second turbine 22 and second impeller 41 are rigidly connected through second rotating shaft 6.Thus, make first turbine 12 can drive the rotation of first impeller 31 synchronously and second turbine 22 can drive 41 rotations of second impeller synchronously, thereby realize that the high and low pressure stage turbine drives the purpose of the high and low gas compressor of arbitrarily downgrading respectively.
In one embodiment of the invention, first turbine 12 and first blade 121 are integral and second turbine 22 and second blade 221 are integral.Thus, make things convenient for production and processing, simultaneously intensity is high, can steady in a long-termly use not fragilely, has reduced user cost.
In one embodiment of the invention; Two stage turbocharging system 100 also comprises exhaust gas by-pass valve 7; One end of exhaust gas by-pass valve 7 is communicated with gas exhaust manifold and the other end is communicated with low pressure stage turbo machine 2, and wherein high-pressure turbine stage 1 has threshold limit value, when the waste gas air pressure of motor 200 discharges surpasses said threshold limit value; Exhaust gas by-pass valve 7 is opened, and exhaust gas by-pass valve 7 is closed when the waste gas air pressure of motor 200 discharges is lower than said threshold limit value.That is to say; Under the operating mode of motor 200 at high load, when the waste gas air pressure of promptly discharging when motor 200 surpassed the threshold limit value of high-pressure turbine stage 1, exhaust gas by-pass valve 7 was opened; This moment, the waste gas part of motor 200 discharges got into high-pressure turbine stage 1; And another part waste gas gets into low pressure stage turbo machine 2 through exhaust gas by-pass valve 7, under the operating mode of motor 200 at low-load, when the waste gas air pressure of promptly discharging when motor 200 is lower than the threshold limit value of high-pressure turbine stage 1; Exhaust gas by-pass valve 7 is closed, and this moment, the waste gas of motor 200 discharges all got into high-pressure turbine stage 1.
Thus; External diameter through the exhaust gas by-pass valve 7 and second turbine 22 are set is greater than the external diameter of first turbine 12, the energy that waste gas had that the high-pressure turbine stage 1 that makes two stage turbocharging system 100 and low pressure stage turbo machine 2 can utilize motor 200 under different operating modes, to discharge better, thus improved the utilization ratio of exhaust energy; The efficient of two stage turbocharging system 100 is improved; Guarantee that simultaneously suction pressure is unlikely to too high, avoided because too high high-pressure turbine stage 1 interior first turbine, 12 hypervelocities that cause of suction pressure are beneficial to the two stage turbocharging system stable operation; Not fragile, reduced the working service cost.
In one embodiment of the invention, two stage turbocharging system 100 also comprises first intercooler, and first intercooler is located between high pressure stage gas compressor 3 and the low pressure stage gas compressor 4.Thus,, the temperature of this part air is reduced, get into the air density in the high pressure stage gas compressor 3 thereby improved through being provided for cooling off first intercooler of the air after 4 compressions of low pressure stage gas compressor.
In one embodiment of the invention, two stage turbocharging system 100 also comprises second intercooler, and second intercooler is located between high pressure stage gas compressor 4 and the intake manifold.Thus; Through being provided for cooling off second intercooler of the air after 3 compressions of high pressure stage gas compressor; The temperature of this part air is reduced; Get into the air density in motor 200 cylinders thereby improved, cooperate the extra fuel injection of injection system, the power per liter of motor 200 is obviously promoted.
Following with reference to the two stage turbocharging system 100 of figure 1-Fig. 5 detailed description according to the embodiment of the invention.
At first the HTHP waste gas of the discharge of motor 200 enters in the high-pressure turbine stage 1 through the gas exhaust manifold and first suction port successively; This moment, waste gas promoted 121 rotations of a plurality of first blades to drive 12 rotations of first turbine; Waste gas is discharged high-pressure turbine stage 1 and is got into low pressure stage turbo machine 2 through second suction port through first air outlet then; This moment, waste gas promoted 221 rotations of a plurality of second blades to drive 22 rotations of second turbine, and last waste gas discharges low pressure stage turbo machine 2 through second relief opening and the process exhaust treatment system is finally discharged outside the car.Because high-pressure turbine stage 1 adopts with low pressure stage turbo machine 2 and arranges changeing; Thereby effectively weakened of the negative effect of high-pressure turbine stage 1 first outlet port waste gas eddy flow to low pressure stage turbo machine 2 internal waste gas flow fields; Improved the efficient of low pressure stage turbo machine 2; Thereby the whole efficiency of two stage turbocharging system 100 is improved, and the exhaust energy utilization ratio improves, and the power performance of motor 200 is further strengthened; And be beneficial to the raising fuel economy, reduce discharge of harmful gases simultaneously.
Wherein, Exhaust gas by-pass valve 7 is at motor 200 to close under the operating mode of low-load does not work; Be in when motor 200 under the operating mode of high load, exhaust gas by-pass valve 7 is opened, and the waste gas part of motor 200 discharges this moment directly gets into through exhaust gas by-pass valve 7 and promotes 22 work of second turbine in the low pressure stage turbo machine 2; And another part waste gas gets into high-pressure turbine stage 1, the description of the working procedure above of the waste gas of this part entering high-pressure turbine stage.Thus; Prevent high-pressure turbine stage 1 because the too high damage of components that causes of waste gas air pressure; The energy that waste gas had that makes two stage turbocharging system 100 can utilize motor 200 to discharge better simultaneously; The exhaust gas utilization rate is improved greatly, thereby the whole efficiency of two stage turbocharging system 100 is improved.
Tradition is non-to changeing in the two stage turbocharging system; Because high-pressure turbine stage exit gas eddy flow, it is low and blade tip is high to cause low pressure stage turbine bucket inlet air flow radial velocity to present root of blade, and this can cause air-flow secondary flow enhancing in the low pressure stage turbine wheel; Cause the loss of exhaust energy to strengthen; Thereby make the whole efficiency that the low pressure stage turbine efficiency reduces influences two stage turbocharging system,, arrange through 2 pairs in high-pressure turbine stage 1 and low pressure stage turbo machine are changeed according to the two stage turbocharging system 100 of the embodiment of the invention; The inlet air flow radial velocity that makes second blade 221 of second turbine 22 in the low pressure stage turbo machine 2 presents the root height and the tip is low; Thereby effectively suppressed air-flow secondary flow in second turbine 22, the entropy increase and decrease is little, and the efficient and the exhaust energy utilization ratio that have improved low pressure stage turbo machine 2 are high; The whole efficiency of two stage turbocharging system 100 is obviously promoted, improved the power performance of motor 200 greatly.
In the description of this specification, the description of reference term " embodiment ", " some embodiments ", " illustrative examples ", " example ", " concrete example " or " some examples " etc. means the concrete characteristic, structure, material or the characteristics that combine this embodiment or example to describe and is contained at least one embodiment of the present invention or the example.In this manual, the schematic statement to above-mentioned term not necessarily refers to identical embodiment or example.And concrete characteristic, structure, material or the characteristics of description can combine with suitable manner in any one or more embodiments or example.
Although illustrated and described embodiments of the invention; Those having ordinary skill in the art will appreciate that: under the situation that does not break away from principle of the present invention and aim, can carry out multiple variation, modification, replacement and modification to these embodiments, scope of the present invention is limited claim and equivalent thereof.
Claims (8)
1. two stage turbocharging system, said two stage turbocharging system is suitable for being connected with gas exhaust manifold with the intake manifold of motor, it is characterized in that, comprising:
High-pressure turbine stage; Said high-pressure turbine stage comprises: first spiral case and first turbine that is located in said first spiral case; Turn up the soil at interval on the periphery of wherein said first turbine and be provided with a plurality of first blades; In said a plurality of first blade each all has first bending direction, and said first spiral case has first suction port and first air outlet and said first suction port and is suitable for being communicated with said gas exhaust manifold;
The low pressure stage turbo machine; Said low pressure stage turbo machine comprises: second spiral case and second turbine that is located in said second spiral case; Turn up the soil at interval on the periphery of wherein said second turbine and be provided with a plurality of second blades; The bending direction of each in said a plurality of second blade is opposite with said first bending direction, and said second spiral case has second suction port and second air outlet and said second suction port and is communicated with said first air outlet;
The high pressure stage gas compressor; Said high pressure stage gas compressor comprises: first pressure shell and first impeller that is located in said first pressure shell; Wherein said first impeller is by said first turbine drives, and said first pressure shell has the 3rd suction port and the 3rd air outlet and said the 3rd air outlet and is suitable for being communicated with said intake manifold; With
The low pressure stage gas compressor; Said low pressure stage gas compressor comprises: second pressure shell and second impeller that is located in said second pressure shell; Wherein said second impeller is by said second turbine drives, and said second pressure shell has the 4th suction port and the 4th air outlet and said the 4th air outlet and is communicated with said the 3rd suction port.
2. two stage turbocharging system according to claim 1 is characterized in that, said a plurality of first blades and said a plurality of second blade be extending radially outwardly along said first turbine and said second turbine respectively.
3. two stage turbocharging system according to claim 1 is characterized in that, the external diameter of said second turbine is greater than the external diameter of the external diameter of said first turbine and said second impeller external diameter greater than said first impeller.
4. two stage turbocharging system according to claim 1 is characterized in that, said first turbine and said first impeller are rigidly connected through first rotating shaft and said second turbine and said second impeller are rigidly connected through second rotating shaft.
5. two stage turbocharging system according to claim 4 is characterized in that, said first turbine and said first blade are integral and said second turbine and said second blade are integral.
6. two stage turbocharging system according to claim 1; It is characterized in that, also comprise exhaust gas by-pass valve, an end of said exhaust gas by-pass valve is communicated with said gas exhaust manifold and the other end is communicated with said low pressure stage turbo machine; Said high-pressure turbine stage has the air pressure threshold limit value; When the waste gas air pressure that wherein said motor is discharged surpassed said threshold limit value, said exhaust gas by-pass valve was opened, and said exhaust gas by-pass valve was closed when the waste gas air pressure of discharging when said motor was lower than said threshold limit value.
7. two stage turbocharging system according to claim 1 is characterized in that, also comprises first intercooler, and said first intercooler is located between said high pressure stage gas compressor and the said low pressure stage gas compressor.
8. two stage turbocharging system according to claim 7 is characterized in that, also comprises second intercooler, and said second intercooler is located between said high pressure stage gas compressor and the said intake manifold.
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| CN2012100077748A CN102562265A (en) | 2012-01-11 | 2012-01-11 | Two-stage turbocharging system |
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| CN2012100077748A CN102562265A (en) | 2012-01-11 | 2012-01-11 | Two-stage turbocharging system |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104806343A (en) * | 2015-05-07 | 2015-07-29 | 长春富奥石川岛增压器有限公司 | Two-stage pressurizer |
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| US20040134193A1 (en) * | 2002-06-26 | 2004-07-15 | Dieter Klingel | Motor brake device for a turbocharged internal combustion engine |
| US20070169479A1 (en) * | 2006-01-20 | 2007-07-26 | Nicolle Frederic F | Two-stage turbocharger system with integrated exhaust manifold and bypass assembly |
| CN101341320A (en) * | 2006-08-10 | 2009-01-07 | 三菱重工业株式会社 | Multi-stage exhaust turbosupercharger |
| US20100061843A1 (en) * | 2008-09-10 | 2010-03-11 | Borgwarner Inc. | Coupling turbochargers for passive pre-swirl counter-rotation |
| WO2011036083A1 (en) * | 2009-09-22 | 2011-03-31 | Abb Turbo Systems Ag | Turbocompound system and components |
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| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20040134193A1 (en) * | 2002-06-26 | 2004-07-15 | Dieter Klingel | Motor brake device for a turbocharged internal combustion engine |
| US20070169479A1 (en) * | 2006-01-20 | 2007-07-26 | Nicolle Frederic F | Two-stage turbocharger system with integrated exhaust manifold and bypass assembly |
| CN101341320A (en) * | 2006-08-10 | 2009-01-07 | 三菱重工业株式会社 | Multi-stage exhaust turbosupercharger |
| US20100061843A1 (en) * | 2008-09-10 | 2010-03-11 | Borgwarner Inc. | Coupling turbochargers for passive pre-swirl counter-rotation |
| WO2011036083A1 (en) * | 2009-09-22 | 2011-03-31 | Abb Turbo Systems Ag | Turbocompound system and components |
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| Publication number | Priority date | Publication date | Assignee | Title |
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| CN104806343A (en) * | 2015-05-07 | 2015-07-29 | 长春富奥石川岛增压器有限公司 | Two-stage pressurizer |
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Application publication date: 20120711 |