CN112746876B - Exhaust gas turbocharger turbine box for improving engine exhaust pulse pressure - Google Patents
Exhaust gas turbocharger turbine box for improving engine exhaust pulse pressure Download PDFInfo
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- CN112746876B CN112746876B CN202011621920.7A CN202011621920A CN112746876B CN 112746876 B CN112746876 B CN 112746876B CN 202011621920 A CN202011621920 A CN 202011621920A CN 112746876 B CN112746876 B CN 112746876B
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- air inlet
- inlet channel
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- 230000035485 pulse pressure Effects 0.000 title claims abstract description 19
- 230000007423 decrease Effects 0.000 claims description 5
- 230000000149 penetrating effect Effects 0.000 claims description 3
- 239000007789 gas Substances 0.000 abstract description 32
- 239000002912 waste gas Substances 0.000 abstract description 7
- 238000010304 firing Methods 0.000 abstract description 5
- 230000007704 transition Effects 0.000 description 8
- 238000002485 combustion reaction Methods 0.000 description 7
- 238000000926 separation method Methods 0.000 description 7
- 238000006243 chemical reaction Methods 0.000 description 4
- 230000035939 shock Effects 0.000 description 4
- 230000001133 acceleration Effects 0.000 description 3
- 230000008901 benefit Effects 0.000 description 3
- 230000009977 dual effect Effects 0.000 description 3
- 238000004519 manufacturing process Methods 0.000 description 3
- 230000009286 beneficial effect Effects 0.000 description 2
- 230000008859 change Effects 0.000 description 2
- 230000007547 defect Effects 0.000 description 2
- 238000006073 displacement reaction Methods 0.000 description 2
- 238000009826 distribution Methods 0.000 description 2
- 238000009434 installation Methods 0.000 description 2
- 238000000034 method Methods 0.000 description 2
- 230000003014 reinforcing effect Effects 0.000 description 2
- 230000003068 static effect Effects 0.000 description 2
- 230000006978 adaptation Effects 0.000 description 1
- 230000002730 additional effect Effects 0.000 description 1
- 238000005266 casting Methods 0.000 description 1
- 230000003247 decreasing effect Effects 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 238000007599 discharging Methods 0.000 description 1
- 230000005284 excitation Effects 0.000 description 1
- 238000002474 experimental method Methods 0.000 description 1
- 239000000446 fuel Substances 0.000 description 1
- 230000020169 heat generation Effects 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 238000005192 partition Methods 0.000 description 1
- 238000003825 pressing Methods 0.000 description 1
- 230000008569 process Effects 0.000 description 1
- 230000002035 prolonged effect Effects 0.000 description 1
- 230000004044 response Effects 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
- F01D25/24—Casings; Casing parts, e.g. diaphragms, casing fastenings
-
- 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
- F01D25/24—Casings; Casing parts, e.g. diaphragms, casing fastenings
- F01D25/243—Flange connections; Bolting arrangements
-
- 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
- F01D9/00—Stators
- F01D9/02—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles
- F01D9/04—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector
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- 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
- F02B37/00—Engines characterised by provision of pumps driven at least for part of the time by exhaust
- F02B37/02—Gas passages between engine outlet and pump drive, e.g. reservoirs
-
- 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
- F02B37/00—Engines characterised by provision of pumps driven at least for part of the time by exhaust
- F02B37/02—Gas passages between engine outlet and pump drive, e.g. reservoirs
- F02B37/025—Multiple scrolls or multiple gas passages guiding the gas to the pump drive
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2220/00—Application
- F05D2220/40—Application in turbochargers
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- 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
- Y02T10/00—Road transport of goods or passengers
- Y02T10/10—Internal combustion engine [ICE] based vehicles
- Y02T10/12—Improving ICE efficiencies
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Supercharger (AREA)
Abstract
The invention discloses an exhaust gas turbocharger turbine box for improving the exhaust pulse pressure of an engine, which comprises a main box body of the turbine box; the main box body of the turbine box comprises a single air inlet channel box body part and a double air inlet channel box body part; the single air inlet channel box body part is internally provided with a second air inlet channel; the inside of the box body part of the double air inlet channel is provided with two hollow first air inlet sub-channels; the rear end openings of the second air inlet channels are communicated with the lower end openings of the two first air inlet sub-channels; the inner side end of the first air inlet sub-channel is connected with a hollow turbine runner through a vaneless nozzle ring; the air inlet at the front end of the second air inlet channel is communicated with one end of an exhaust manifold on a double-row cylinder of the external engine; the first air inlet sub-channel and the second air inlet channel are necking channels. The invention can effectively balance the pressure of the waste gas pulse air flow from the double-row cylinders with different firing sequences in the external engine, and improves the utilization ratio of the energy of the pulse air flow.
Description
Technical Field
The invention relates to the technical field of exhaust gas driven turbochargers, in particular to an exhaust gas turbocharger turbine box for improving the exhaust pulse pressure of an engine.
Background
At present, in order to boost the power of an internal combustion engine under the same displacement, the following modes are adopted: the method comprises the steps of recovering combustion waste gas of the internal combustion engine, driving a turbine in a turbine box of the supercharger to do work by utilizing waste gas energy discharged by the internal combustion engine, driving a coaxial centrifugal compressor by the turbine, and pre-compressing air entering a cylinder, so that the air density is improved, more fuel is combusted, and the internal combustion engine emits more power.
The energy of the exhaust gas can be effectively recycled through the exhaust gas turbocharger, the air quantity in the cylinder under the same displacement is increased, the combustion process is optimized, and the working efficiency of the internal combustion engine is improved.
However, the conventional turbocharger turbine box is not scientific in structural design, and when exhaust gas discharged from an external engine is utilized, pulse gas flows with high pressure discharged from double-row cylinders with different firing sequences in the external engine cannot be effectively balanced, and the pulse gas flow energy utilization rate is low, so that the working efficiency is affected. In addition, the exhaust gas pulse flow is also prone to damage to the turbine box of the supercharger.
Disclosure of Invention
The invention aims at overcoming the technical defects in the prior art and provides an exhaust gas turbocharger turbine box for improving the exhaust pulse pressure of an engine.
Therefore, the invention provides an exhaust gas turbocharger turbine box for improving the exhaust pulse pressure of an engine, which comprises a main box body of the turbine box;
The main box body of the turbine box comprises a hollow single air inlet channel box body part and a double air inlet channel box body part;
the double air inlet channel box body part is positioned at the top of the single air inlet channel box body part;
Wherein, the inside of the single air inlet channel box body part is provided with a second air inlet channel;
the inside of the box body part with the double air inlet channels is provided with two hollow first air inlet sub-channels;
the rear end opening of the second air inlet channel in the single air inlet channel box body part is communicated with the lower end openings of the two first air inlet sub-channels in the double air inlet channel box body part;
wherein, the inner side ends of the two first air inlet sub-channels distributed in a surrounding way are overlapped together, a circle of opening is formed in the overlapping part of the two first air inlet sub-channels in a surrounding way, and a vaneless nozzle ring with a hollow inside and a circular ring shape is arranged in the surrounding way at the opening;
the outer side end of the bladeless nozzle ring is circumferentially provided with an air inlet communicated with the first air inlet sub-channel;
the inner side end of the bladeless nozzle ring is circumferentially provided with a circle of opening stop;
the vaneless nozzle ring is communicated with the inlet end of the hollow turbine runner through an opening stop;
the outlet end of the turbine runner is communicated with one end of an exhaust pipe through a vortex rear flange;
The turbine runner is positioned in the box body part of the double air inlet channels;
The vortex rear flange is arranged on the right side of the double-air-inlet-channel box body part;
The air inlet at the front end of the second air inlet channel is communicated with one end of an exhaust manifold on the double-row cylinder with different ignition sequences in the external engine;
The first air inlet sub-channel and the second air inlet channel are necking channels.
Preferably, the front end of the inlet channel box portion is provided with an inlet flange.
Preferably, a separation rib is provided between the two first air intake sub-passages inside the air intake passage case portion to separate the two.
Preferably, the two first air inlet sub-channels are channels distributed in a circular arc shape.
Preferably, the single air inlet channel box body part comprises a single air inlet channel section and a first arc section part which are mutually connected;
the second air inlet passage penetrates through the single air inlet passage section and the inner part of the first arc section;
The central angle of the first arc section part is alpha, and the corresponding central position is positioned on the axis A at the lowest position in the inner wall of the bladeless nozzle ring;
The second air inlet channel is positioned in the first arc section part and is only a single air inlet channel, or comprises two mutually separated and independent second air inlet sub-channels;
Wherein the second intake passage, which is located inside the single intake passage section, is only a single intake passage.
Preferably, the double air inlet channel box body part is a second arc section part, the central angle of the second arc section part is beta, and the corresponding central position is positioned on the central axis of the bladeless nozzle ring;
The rear end of the first arc section part is connected with the inner wall of the lower end of the second arc section part;
two hollow first air inlet sub-channels penetrate through the inner part of the second arc section part.
Preferably, the central angle alpha of the first arc section is in a value range of 0-45 degrees;
The central angle beta of the second arc segment part is 360 degrees.
Preferably, the second intake passage inside the single intake passage box portion is a constricted passage in which the total area of the openings gradually decreases from the intake port.
Preferably, each of the first intake sub-passages inside the double intake passage box portion is a constricted passage having an opening area which gradually decreases from the intake port.
Compared with the prior art, the technical scheme provided by the invention has the advantages that the structure design is scientific, the pressure of the exhaust gas pulse air flow discharged by the double-row air cylinders with different firing sequences in the external engine can be effectively balanced, the utilization rate of the pulse air flow energy is improved, the overall efficiency of the turbine is improved, and the turbine has great production practice significance.
In addition, the application of the invention can effectively improve the damage of the exhaust pulse airflow from the external engine to the turbine box of the supercharger.
Drawings
FIG. 1 is a schematic diagram of the front side of an exhaust gas turbocharger turbine housing for improving engine exhaust pulse pressure in accordance with the present invention;
FIG. 2 is a schematic view of a longitudinal cross-sectional structure of a turbocharger turbine housing for improving engine exhaust pulse pressure in accordance with the present invention;
FIG. 3 is a cross-sectional view of a single intake passage segment in a single intake passage housing portion, taken along line D-D of FIG. 2;
FIG. 4 is a cross-sectional view of a first arcuate segment portion of the single inlet channel housing portion taken along line C-C of FIG. 2 in a first embodiment;
FIG. 5 is a cross-sectional view of a first arcuate segment portion of the single inlet channel housing portion taken along line C-C of FIG. 2 in a second embodiment;
FIG. 6a is a front view of an internal chamber airflow passage in an exhaust gas turbocharger turbine housing for improving engine exhaust pulse pressure in accordance with the present invention;
FIG. 6b is a side view of an internal cavity airflow passage in an exhaust gas turbocharger turbine housing for improving engine exhaust pulse pressure in accordance with the present invention;
FIG. 6c is a schematic axial view of an inner chamber airflow passage in an exhaust gas turbocharger turbine housing for improving engine exhaust pulse pressure in accordance with the present invention;
FIG. 7a is a front elevational view of an exhaust gas turbocharger turbine housing for improving engine exhaust pulse pressure in accordance with the present invention;
FIG. 7b is a left side view of an exhaust gas turbocharger turbine housing for improving engine exhaust pulse pressure in accordance with the present invention;
FIG. 8 is a perspective view of the shaft side of an exhaust gas turbocharger turbine housing for improving engine exhaust pulse pressure in accordance with the present invention;
1. A single intake passage section; 2. a main body of the turbine box; 4. a double inlet channel box portion; 5. a vortex rear flange;
7. The bearing body is matched with the end face; 8. a gear is opened; 9. an inlet flange; 12. a separation rib; 13. a first arc segment portion; 14. a single intake passage box portion; 15. tongue portion;
Detailed Description
In order that the manner in which the application is carried out will become more readily apparent, a more particular description of the application will be rendered by reference to specific embodiments thereof which are illustrated in the appended drawings. It is to be understood that the specific embodiments described herein are merely illustrative of the application and not limiting of the application. It should be further noted that, for convenience of description, only the portions related to the present application are shown in the drawings.
It should be noted that, without conflict, the embodiments of the present application and features of the embodiments may be combined with each other. The application will be described in detail below with reference to the drawings in connection with embodiments.
It should be noted that, in the description of the present application, terms such as "center," "upper," "lower," "left," "right," "vertical," "horizontal," "inner," "outer," and the like indicate directions or positional relationships based on the directions or positional relationships shown in the drawings, which are merely for convenience of description, and do not indicate or imply that the apparatus or elements must have a specific orientation, be constructed and operated in a specific orientation, and thus should not be construed as limiting the present application.
In addition, it should be noted that, in the description of the present application, unless explicitly specified and limited otherwise, the term "mounted" and the like should be construed broadly, and may be fixed or removable, for example.
The specific meaning of the above terms in the present application can be understood by those skilled in the art according to the specific circumstances.
Referring to fig. 1 to 8, the present invention provides an exhaust gas turbocharger turbine housing for improving engine exhaust pulse pressure, comprising a main housing 2 of the turbine housing;
the main turbine housing 3 includes a hollow single-intake-channel housing portion 14 (i.e., a section D in fig. 2) and a double-intake-channel housing portion 4 (i.e., a section S in fig. 2 in a vortex shape);
the double intake channel housing portion 4 is located on top of the single intake channel housing portion 14;
wherein the single intake passage box portion 14 has a second intake passage 140 therein;
The inside of the double air inlet channel box body part 4 is provided with two hollow first air inlet sub-channels 40;
The rear end opening of the second air intake passage 140 inside the single air intake passage box portion 14 communicates with the lower end openings of the two first air intake sub-passages 40 inside the double air intake passage box portion 4;
Wherein, the inner ends of the two first air inlet sub-channels 40 distributed in a surrounding manner are overlapped together, and a circle of openings (namely the same inner openings are used as air outlets) are formed in the overlapping position of the two first air inlet sub-channels in a surrounding manner, and the openings are circumferentially provided with an inner hollow annular bladeless nozzle ring 20 (the radial cross section shape of the bladeless nozzle ring 20 is rectangular);
the outer end of the vaneless nozzle ring 20 is circumferentially vented with an air inlet communicating with the first air inlet sub-passage 40;
the inner side end of the bladeless nozzle ring 20 is circumferentially provided with a circle of opening 8 (namely, used as an air outlet);
the vaneless nozzle ring 20 is communicated with the inlet end of the hollow turbine runner 6 through an opening 8;
the outlet end of the turbine runner 6 is communicated with one end of an exhaust pipe through a vortex rear flange 5;
A turbine runner 6 located inside the double intake passage housing portion 4 (specifically inside the right end of the double intake passage housing portion 4);
The vortex rear flange 5 is arranged on the right side of the double-air-inlet-channel box body part 4;
That is, the vaneless nozzle ring 20 serves as two first air intake sub-passages 40 (i.e., dual air intake passages) inside the dual air intake passage housing portion 4, communicating with the middle of the inlet end of the turbine runner 6, the transition portion.
The turbine runner 6 is used for installing a turbine, and high-speed air flows flowing out from the two first air inlet sub-channels 40 in the double air inlet channel box body part 4 enter the turbine runner 6 through the opening 8 and can drive the turbine to rotate. It should be noted that, the installation mode of the turbine is the existing conventional installation mode, and will not be described herein.
Wherein, the air inlet at the front end of the second air inlet channel 140 is communicated with one end of the exhaust manifold on the double-row cylinder with different ignition sequences in the external engine.
The exhaust manifold is used for discharging the exhaust pulse airflow.
In the invention, in particular, the front end of the single air inlet channel box body part 14 is provided with an inlet flange 9;
an inlet flange 9 for connection to an exhaust manifold on an external engine for exhausting exhaust gases.
In the present invention, in particular, a separation rib 12 is provided between the two first air intake sub-passages 40 in the double air intake passage housing part 4 to separate the two first air intake sub-passages, that is, the two first air intake sub-passages 40 in the double air intake passage housing part 4 are two sub-passages obtained by separating one air intake passage by the separation rib 12.
In the present embodiment, the two first air intake sub-channels 40 are channels distributed in a circular arc shape.
The other end of the exhaust pipe to which the post-vortex flange 5 is connected is directly connected to the outside atmosphere or is connected to the post-treatment device.
In the invention, the left side of the upper part of the main box body 2 of the turbine box is provided with a bearing body matching end surface 7, and the bearing body matching end surface 7 is assembled and connected with an external bearing body (namely a supercharger bearing body, also called a supercharger intermediate body) through a clamping band or a screw pressing plate.
In the present invention, in particular, the single intake passage box portion 14 (i.e., the D-zone portion in fig. 2) includes the single intake passage segment 1 and the first circular arc segment portion 13 (may be integrally formed) that are connected to each other;
a second intake passage 140 penetrating through the inside of the single intake passage segment 1 and the first circular arc segment portion 13;
wherein, the central angle of the first arc segment part 13 is alpha, and the corresponding central position is positioned on the axis A at the lowest position in the inner wall of the bladeless nozzle ring 20;
The second air intake passage 140 located inside the first circular arc segment portion 13 is only a single air intake passage, or includes two separate second air intake sub-passages 1401 that are separated from each other; that is, for the present invention, the inside of the first circular arc segment portion 13 of the single intake passage box portion 14 may be a single passage or a double passage.
Wherein the second intake passage 140, which is located inside the single intake passage section 1, is only a single intake passage;
in particular, the opening area of the second intake passage 140 portion located inside the single intake passage segment 1 is larger than the opening area of the second intake passage 140 portion located inside the first circular arc segment 13 (whether this is the opening area of the single passage or the sum of the opening areas of the two second intake sub-passages 1401).
The center position corresponding to the center angle α of the first circular arc segment 13 is located on the axis a at the lowest position in the inner wall of the vaneless nozzle ring 20 inside the double intake passage box portion 4.
In the present invention, in a specific implementation, the double air intake channel box portion 4 (i.e., the S-zone portion in fig. 2) is a second arc segment portion (i.e., the box region portion covered by the central angle β shown in fig. 2), where the second arc segment portion has a central angle β, and the corresponding central position is located on the central axis of the vaneless nozzle ring 20;
The rear end (namely, the end point) of the first arc segment part 13 is connected with the inner wall (namely, the starting point) of the lower end of the second arc segment part (the connecting part is a smooth arc transition part);
That is, the end point of the first arc segment portion 13 of the angle α is uniformly transitionally connected to the start point of the second arc segment portion of the angle β.
Two hollow first air inlet sub-passages 40 penetrate through the inside of the second circular arc segment portion.
It should be noted that the single intake passage section 1 is located on one side of the double intake passage housing portion 4 while being a side wall of the first intake sub-passage 40 in the double intake passage housing portion 4.
In the concrete implementation, the value range of the central angle alpha of the first arc section part 13 is 0-45 degrees, and the change is not limited to the range of 0-45 degrees;
The central angle beta of the second arc segment part is 360 degrees.
In particular implementation, the first arc segment part 13 is positioned at one side of one first air inlet sub-channel 40 of the double air inlet channel box body part 4, and is provided with a tongue part 15 which is obliquely distributed and used for separating the air flow of the single air inlet channel segment 1 and preventing the air flow from directly entering the turbine runner 6 without fully passing through the annular opening 8;
the height of the tongue portion 15 increases gradually from back to front.
In particular, the rear end opening of the second air intake passage 140 within the single air intake passage housing portion 14 is located rearwardly and downwardly of the tongue portion 16.
In the present invention, the second air intake passage 140 inside the single air intake passage box portion 14 is a constricted passage in which the total area of the openings is gradually reduced from the air intake.
In the present invention, in particular, each of the first intake sub-passages 40 in the inside of the double intake passage box portion 4 is a constricted passage having an opening area which gradually decreases from the intake port (i.e., has a gradually decreasing caliber from the intake port)
In the present invention, in particular, for the single intake passage case portion 14, the sectional shape of the second intake passage 140 at the front end is as shown in fig. 3;
and the second intake passage 140 inside the single intake passage section 1 at the rear end of the single intake passage box portion 14 has a sectional shape as shown in fig. 5 when the second intake passage 140 inside the single intake passage section 1 is only a single intake passage, and has a sectional shape as shown in fig. 4 when the second intake passage 140 inside the single intake passage section 1 includes two separate, independent second intake sub-passages 1401; that is, the second intake passage 140 inside the single intake passage section 1 may be selected to have two different passage cross-sectional shapes by selecting a single-passage or double-passage two-shape structure.
In the present embodiment, the first intake sub-passage 40 inside the double intake passage box portion 4 has a sectional shape as shown in fig. 1.
In the invention, in particular implementation, two first air inlet sub-channels 40 in the double air inlet channel box body part 4 are communicated with the turbine runner 6 through a hollow opening 8;
Meanwhile, the rear end opening of the first air intake passage 140 located inside the first circular arc segment portion 13 of the angle α is also communicated with the turbine runner 6 through the hollow opening 8.
It should be noted that, for the present invention, the single intake passage section 1 in the single intake passage box portion 14 is an independent area, communicates with the first circular arc section portion 13 of the angle α, communicates with the outside (for example, an exhaust manifold for exhausting exhaust gas on an external engine) through the inlet flange 9, or may be provided with a bypass hole to communicate with the outside.
In particular, exhaust gas discharged from two rows of cylinders with different engine firing sequences flows in through the second air inlet channel 140 at the single air inlet channel section 1 in the single air inlet channel box body part 14 (namely, the section D in fig. 2), and forms a confluence, flows through the double air inlet channel box body part 4, enters the turbine runner 6, and is discharged through an exhaust pipe connected with the vortex rear flange 5.
In addition, the structure can effectively lighten the weight of the turbine box, does not have the separation rib at the air inlet of the turbine box, can reduce the contact area of air flow and channel walls, reduces the friction loss of the air flow and fully mixes the waste gas.
According to the invention, the single-double mixing channel is adopted, so that the arrangement of the reinforcing ribs can be reduced in process, casting defects at the thin wall of the reinforcing ribs are prevented, and the overall weight of the turbine box is reduced.
In the present invention, the ranges of the α angle of the first circular arc segment 13 in the double intake passage box portion 4 and the single intake passage box portion 14, and the single intake passage box portion 14 may be adjusted as needed.
It should be noted that, referring to fig. 3 to 5, in the present invention, compared with the second air intake passage 140 (i.e., single passage) of the single air intake passage section 1 in the single air intake passage box portion 14, the two first air intake sub-passages 40 in the double air intake passage box portion 4 have a partition rib 12 therebetween, when the pulse air flow uses the second air intake passage 140 (i.e., single passage) as the transition air intake (i.e., exhaust entering the external engine cylinder), the air flow can be mixed in the second air intake passage 140 (i.e., single passage), the influence of the air flow pulse on the turbine can be reduced, the tongue position can be strengthened by reducing the opening area of the passage (i.e., adopting the necking passage), the pressure fluctuation of the tongue position can be reduced, and the structure can effectively shorten the length of the inlet section of the turbine box, reduce the weight of the turbine box, reduce the contact area of the air flow and the passage wall, and obtain the additional effects of reducing the turbine shell cost, reducing the air flow friction loss and improving the thermal shock resistance of the turbine box.
It should be noted that, for the present invention, the inlet flange 9 of the turbine case is connected to the single intake passage section 1 in the single intake passage case portion 14, and gradually transits to the double intake passage case portion 4 (i.e., the second circular arc section portion) after passing through the single intake passage section 1 and the second circular arc section 13 of the angle α of the single intake passage case portion 14, and the double intake passage case portion 4 has two hollow first intake sub-passages 40 whose cross sections are double-channel cross sections.
In the present invention, exhaust gas discharged from the engine flows into the single intake passage section 1 in the single intake passage housing portion 14, enters the two first intake sub-passages 40 in the double intake passage housing portion 4, is split, flows through the turbine runner 6, and is discharged through the exhaust pipe connected to the turbine rear flange 5.
It should be noted that, based on the above technical solutions, the air flow channel in the turbine box of the turbocharger is changed from a single channel transition at the inlet of the single air inlet channel box portion 14 into a 360 ° double channel flow channel (i.e., two hollow first air inlet sub-channels 40) in the double air inlet channel box portion 4, and the air flow reenters the turbine flow channel 6 through these channels to drive the turbine in the turbine flow channel, so as to improve the damage of the pulse air flow from the double-row exhaust of the engine to the turbine of the turbocharger.
For the present invention, a turbine box structure with a single and double mixing channels is adopted, the air flows are mixed in a single air inlet channel in the single air inlet channel box body part 14, and the double channels (namely, two first air inlet sub-channels 40) in the double air inlet channel box body part 4 are used for pressure energy and kinetic energy conversion.
As the turbine box with the single and double mixing channels, the invention has the advantages of scientific structure, good manufacturability, strong adaptability and the like. The turbine box of this structure can be furnished with the waste gas that different exhaust manifolds come on the engine and get into the booster turbine box, and the air current mixes at single cross-section passageway section, under the prerequisite that does not change original booster appearance interface position, through changing structural style, rationally set up the changeover portion, reduce exhaust shock wave influence, promote booster turbine box to the utilization ratio of pulse air flow energy, effectively promote booster turbine efficiency.
For the invention, the flexible adjustment of the range of the channel-changing transition zone (namely the first arc section part 13 included in the single air inlet channel box body part 14) can strengthen the tongue position structure of the turbine box, effectively utilize exhaust pulse, reduce exhaust shock wave, realize uniform depressurization and acceleration of air flow, and drive the turbine impeller to rotate with uniform static pressure distribution by high-speed waste gas, thereby effectively improving the utilization rate of low-pressure waste gas and turbine efficiency.
It should be noted that, for the present invention, by adopting the dual channels (i.e. the two first air intake sub-channels 40) with uniform necking, the conversion rate from the air flow pressure energy to the kinetic energy is improved, the uniform non-pulse high-speed air flow can reduce the impact on the turbine, the transition area (i.e. the first circular arc section part 13 included in the single air intake channel box body part 14) is easy to strengthen the tongue part 15, and the pressure fluctuation of the tongue part 15 is reduced, and the structure can effectively reduce the weight of the turbine box, the pulse air flow inlet of the turbine box has no separating rib, the pulse air flow can be uniformly mixed, and meanwhile, when the bypass hole is opened in the single air intake channel box body part 14, the exhaust is smoother, the influence of the non-uniform air flow on the turbine is reduced, and the exhaust noise is reduced.
In the present invention, the turbine housing as the exhaust gas turbocharger includes a double-intake passage housing portion and a single-intake passage housing portion, and the cross section of the internal passage of the turbine housing also includes two types of a double-passage cross section and a single-passage cross section. The second air inlet channel 140 in the single air inlet channel box body part is positioned at the inlet section, and the second air inlet channel 140 positioned at the single air inlet channel section 1 is of a single section and has no separation rib. The two first air inlet sub-channels 140 are separated by a separation rib 12; the air outlets in the two first air inlet sub-channels 140 are located in the ring turbine shift region. The single-double-channel area range can be flexibly arranged according to the needs.
In order to more clearly understand the technical scheme of the present invention, the working principle of the present invention is described below.
The invention provides an exhaust gas turbocharger turbine box, which comprises an inlet flange, a double-inlet-channel box body part, a single-inlet-channel box body part, a gear opening and bearing body matching surface and the like, wherein exhaust gas discharged by an engine enters an air passage from a single inlet channel (namely a second inlet channel 140) in a single inlet-channel section 1 in the single inlet-channel box body part 14 through an inlet of the turbine box, the single inlet channel is a necking channel, pressure energy of exhaust pulse is converted into kinetic energy, exhaust gas at low speed and high pressure enters the single inlet channel, depressurization and acceleration mixing can be carried out, energy of pulse air at high speed and low pressure is exchanged during mixing, the pulse air flow at high speed and the pulse air flow at low pressure alternately become pushed and pushed air flow, after stable pressure balance is realized on the air flow in the single inlet channel (namely the second inlet channel 140), depressurization and acceleration are continuously carried out in the double channels (namely two first inlet sub-channels 40 in the double inlet-channel box body part 4) of the necking, and then enter a turbine runner 6 through the gear opening, and turbine in the turbine runner 6 is driven to rotate.
Compared with the prior art, the exhaust gas turbocharger turbine box for improving the exhaust pulse pressure of the engine has the following beneficial effects:
1. According to the turbine box, the air inlet channel of the turbine box is changed from single channel to double channels, so that the air flow pulse impact can be reduced, and the production cost can be reduced. The length and the mixing section position of the transition channel (i.e. the single air inlet channel section 1 and the second air inlet channel 140 in the first arc section part 13) can be flexibly set according to performance requirements, the necking channel can enable the pulse air flow to convert pressure energy into kinetic energy in the air channel, the single channel inner wall is smaller than the double channel inner wall in surface area, and friction heat generation between the high-speed air flow and the inner wall in the channel can be greatly reduced, so that the air flow kinetic energy loss is reduced.
2. According to the turbine box disclosed by the invention, the air inlet channel of the turbine box is changed from single channel to double channels, so that the conversion efficiency of air inlet pressure energy to kinetic energy can be improved, the air flow pressure in the channels can be effectively balanced by the single channel transition channel (such as the single air inlet channel section 1 and the second air inlet channel 140 in the first circular arc section part 13), the high air flow kinetic energy is obtained by the low exhaust pressure of the engine in a low-speed state, the circumferential static pressure distribution of the turbine inlet is more uniform, the rotating speed of the driving rotor is uniformly improved, the supercharging pressure in the low-speed state is improved, and the low-speed response performance of the supercharger is improved.
3. According to the turbine box, the airflow channel of the turbine box is subjected to single-change double conversion, so that the pressure energy of pulse airflow can be effectively utilized, a series of experiments show that the measure can well balance the exhaust pulse pressure, and in a double-channel occasion, the advantage of the vaneless turbine box with 360-degree full air inlet can be fully utilized, the excitation influence of airflow shock waves on the long tongue structure of the turbine box is weakened, the low-speed performance of an engine is improved, and the service life of the turbine box is prolonged.
In summary, compared with the prior art, the exhaust gas turbocharger turbine box for improving the exhaust pulse pressure of the engine provided by the invention has scientific structural design, can effectively balance the pressure of exhaust gas pulse airflows discharged by double-row cylinders with different firing sequences in an external engine, improves the utilization ratio of pulse airflows energy, is further beneficial to improving the overall efficiency of a turbine, and has great production practice significance.
In addition, the application of the invention can effectively improve the damage of the exhaust pulse airflow from the external engine to the turbine box of the supercharger.
The foregoing is merely a preferred embodiment of the present invention and it should be noted that modifications and adaptations to those skilled in the art may be made without departing from the principles of the present invention, which are intended to be comprehended within the scope of the present invention.
Claims (5)
1. An exhaust gas turbocharger turbine housing for improving the pulse pressure of engine exhaust gas, characterized by comprising a main housing (2) of the turbine housing;
The main box body (2) of the turbine box comprises a hollow single air inlet channel box body part (14) and a double air inlet channel box body part (4);
The double air inlet channel box body part (4) is positioned at the top of the single air inlet channel box body part (14);
Wherein the single air inlet channel box body part (14) is internally provided with a second air inlet channel (140);
The inside of the double air inlet channel box body part (4) is provided with two hollow first air inlet sub-channels (40);
The rear end opening of the second air inlet channel (140) in the single air inlet channel box body part (14) is communicated with the lower end openings of the two first air inlet sub-channels (40) in the double air inlet channel box body part (4);
wherein, the inner side ends of two first air inlet sub-channels (40) distributed in a surrounding way are overlapped together, a circle of opening is formed in the overlapping part of the two first air inlet sub-channels in a surrounding way, and an inner hollow circular ring-shaped bladeless nozzle ring (20) is arranged in the surrounding way at the opening;
the outer side end of the bladeless nozzle ring (20) is circumferentially provided with an air inlet communicated with the first air inlet sub-channel (40);
the inner side end of the bladeless nozzle ring (20) is circumferentially provided with a circle of opening stop (8);
The vaneless nozzle ring (20) is communicated with the inlet end of the hollow turbine runner (6) through an opening (8);
the outlet end of the turbine runner (6) is communicated with one end of an exhaust pipe through a vortex rear flange (5);
A turbine runner (6) positioned in the double-inlet-channel box body part (4);
the vortex rear flange (5) is arranged on the right side of the double-air-inlet-channel box body part (4);
the air inlet at the front end of the second air inlet channel (140) is communicated with one end of an exhaust manifold on the double-row cylinder with different ignition sequences in the external engine;
the first air inlet sub-channel (40) and the second air inlet channel (140) are necking channels;
The two first air inlet sub-channels (40) are channels distributed in an arc shape;
A single intake passage box portion (14) including a single intake passage section (1) and a first circular arc section portion (13) connected to each other;
a second air intake passage (140) penetrating through the inside of the single air intake passage section (1) and the first circular arc section portion (13);
wherein, the central angle of the first arc section part (13) is alpha, and the corresponding central position is positioned on the axis A at the lowest position in the inner wall of the bladeless nozzle ring (20);
the second air inlet channel (140) is positioned in the first arc section part (13) and is only a single air inlet channel, or comprises two mutually separated and independent second air inlet sub-channels (1401);
Wherein the second air inlet channel (140) is positioned inside the single air inlet channel section (1) and is only a single air inlet channel;
The double air inlet channel box body part (4) is a second arc section part, the central angle of the second arc section part is beta, and the corresponding central position is positioned on the central axis of the bladeless nozzle ring (20);
The rear end of the first arc section part (13) is connected with the inner wall of the lower end of the second arc section part;
two hollow first air inlet sub-channels (40) penetrating through the inside of the second arc segment part;
The value range of the central angle alpha of the first arc section part (13) is 0-45 degrees;
The central angle beta of the second arc segment part is 360 degrees.
2. An exhaust-gas turbocharger turbine housing for improving the pressure of engine exhaust pulses as claimed in claim 1, characterized in that the front end of the single-inlet channel housing part (14) is provided with an inlet flange (9).
3. An exhaust-gas turbocharger turbine housing for improving the pressure of engine exhaust pulses as claimed in claim 1, characterized in that between the two first intake sub-channels (40) inside the double intake channel housing part (4) there are separating ribs (12) separating the two.
4. The exhaust gas turbocharger turbine housing for improving the pressure of engine exhaust pulses according to claim 1, wherein the second intake passage (140) inside the single intake passage housing portion (14) is a constricted passage having an opening total area which gradually decreases from the intake port.
5. An exhaust gas turbocharger turbine housing improving the pressure of the engine exhaust gas pulse as claimed in claim 1, characterized in that each first intake sub-passage (40) inside the double intake passage housing portion (4) is a constricted passage having an opening area which gradually decreases from the intake port.
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| CN102661180A (en) * | 2012-05-07 | 2012-09-12 | 康跃科技股份有限公司 | Dual-zone turbine for turbocharging |
| CN202707159U (en) * | 2012-05-24 | 2013-01-30 | 湖南天雁机械有限责任公司 | Turbocharger water cooling turbine case with exhaust gas by-passing valve |
| US9347367B2 (en) * | 2013-07-10 | 2016-05-24 | Electro-Motive Diesel, Inc. | System having dual-volute axial turbine turbocharger |
| CN203476409U (en) * | 2013-09-11 | 2014-03-12 | 宁波威孚天力增压技术有限公司 | Turbocharger turbine box with airflow injection function |
| CN103726928A (en) * | 2014-01-09 | 2014-04-16 | 孙敏超 | Exhaust by-pass valve for turbocharging system |
| CN107524482A (en) * | 2017-07-14 | 2017-12-29 | 同济大学 | A kind of double scroll turbine shrouds of combined type |
| DE102017119144A1 (en) * | 2017-08-22 | 2017-10-05 | FEV Europe GmbH | Double-flow turbocharger |
| US11085311B2 (en) * | 2019-03-12 | 2021-08-10 | Garrett Transportation I Inc. | Turbocharger with twin-scroll turbine housing and twin vaned nozzle ring for directing exhaust gases from each scroll onto turbine wheel in interleaved fashion |
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