CN112746876A - Improve exhaust gas turbocharger turbine case of engine exhaust pulse pressure - Google Patents
Improve exhaust gas turbocharger turbine case of engine exhaust pulse pressure Download PDFInfo
- Publication number
- CN112746876A CN112746876A CN202011621920.7A CN202011621920A CN112746876A CN 112746876 A CN112746876 A CN 112746876A CN 202011621920 A CN202011621920 A CN 202011621920A CN 112746876 A CN112746876 A CN 112746876A
- Authority
- CN
- China
- Prior art keywords
- air inlet
- channel
- inlet channel
- turbine
- double
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Pending
Links
Images
Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
- F01D25/24—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
-
- 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
-
- 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
-
- 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
Abstract
The invention discloses an exhaust gas turbocharger turbine box for improving exhaust pulse pressure of an engine, which comprises a turbine box main box body; 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 double-air-inlet-channel box body part is internally provided with two hollow first air inlet sub-channels; the rear end opening of the second air inlet channel is communicated with the lower end openings of the two first air inlet sub-channels; the inner end of the first air inlet sub-channel is connected with the hollow turbine runner through a bladeless 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 an 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 airflow from the double-row cylinders with different firing sequences in the external engine and improve the utilization rate of the pulse airflow energy.
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 adopted method is as follows: the combustion waste gas of the internal combustion engine is recovered, the energy of the waste gas exhausted by the internal combustion engine is utilized to drive the turbine in the turbine box of the supercharger to do work, and then the turbine drives the coaxial centrifugal compressor to pre-compress the air entering the cylinder, so that the air density is improved, more fuel is combusted, and the internal combustion engine generates higher power.
Through the exhaust gas turbocharger, the energy of exhaust gas can be effectively recycled, the air quantity in the lower cylinder with the same displacement is increased, the combustion process is optimized, and the working efficiency of the internal combustion engine is improved.
However, the conventional exhaust turbocharger turbine box is not scientific in structural design, and when exhaust gas discharged from an external engine is used, the pressure of the pulse gas flow cannot be effectively balanced for the exhaust pulse gas flow with high pressure discharged from the double-row cylinders with different firing orders in the external engine, and the utilization rate of the energy of the pulse gas flow is low, so that the working efficiency is affected. In addition, the exhaust gas pulse flow is also liable to cause damage to the turbine case of the supercharger.
Disclosure of Invention
The invention aims to provide an exhaust gas turbocharger turbine box for improving the exhaust pulse pressure of an engine aiming at the technical defects in the prior art.
Therefore, the invention provides an exhaust gas turbocharger turbine box for improving the exhaust pulse pressure of an engine, which comprises a turbine box main box body;
the main box body of the turbine box comprises a hollow single air inlet channel box body part and a hollow 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 single air inlet channel box body part is internally provided with a second air inlet channel;
the double-air-inlet-channel box body part is internally provided with two hollow first air inlet sub-channels;
the rear end opening of a second air inlet channel in the single air inlet channel box body part is communicated with the lower end openings of two first air inlet sub-channels in the double air inlet channel box body part;
the inner side ends of the two first air inlet sub-channels which are distributed in a surrounding way are overlapped together, a circle of opening is formed in the overlapping position of the two first air inlet sub-channels in a surrounding way, and a hollow annular vaneless nozzle ring is arranged at the opening in a surrounding way;
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 provided with a circle of open shelves in a surrounding way;
the bladeless nozzle ring is communicated with the inlet end of the hollow turbine runner through an opening;
the outlet end of the turbine runner is communicated with one end of an exhaust pipe through a turbine rear flange;
the turbine runner is positioned in the double-air inlet channel box body part;
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 a double-row cylinder with different ignition sequences in an external engine;
the first air inlet sub-channel and the second air inlet channel are necking channels.
Preferably, an inlet flange is provided at a front end of the intake passage case portion.
Preferably, a partition rib is provided between the two first intake sub-passages inside the intake passage box portion to partition the two first intake sub-passages.
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 circular arc section part which are connected with each other;
the second air inlet channel penetrates through the single air inlet channel section and the inner part of the first circular arc section;
the central angle of the first arc section part is alpha, and the corresponding circle center position is positioned on the axis A at the lowest position in the inner wall of the vaneless nozzle ring;
the second air inlet channel positioned in the first circular arc section part is only a single air inlet channel or comprises two mutually separated and independent second air inlet sub-channels;
wherein the second air intake passage located inside the single air intake passage section is only a single air intake passage.
Preferably, the double-inlet-channel box body part is a second arc section part, the second arc section part has a central angle of beta, and the corresponding position of the center of the circle is located 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;
and the two hollow first air inlet sub-channels penetrate through the inside of the second circular arc section part.
Preferably, the value range of the central angle alpha of the first arc section part is 0-45 degrees;
the central angle β of the second circular arc segment portion is 360 °.
Preferably, the second inlet passage inside the single inlet passage box portion is a constricted passage having a total opening area gradually decreasing from the inlet port.
Preferably, each first air inlet sub-passage inside the double air inlet passage box body part is a necking passage with an opening area gradually reduced from the air inlet.
Compared with the prior art, the technical scheme provided by the invention has the advantages that the turbine box of the exhaust gas turbocharger for improving the exhaust pulse pressure of the engine is scientific in structural design, the pressure of the exhaust gas pulse airflow discharged by the double-row cylinders with different firing sequences in the external engine can be effectively balanced, the utilization rate of the energy of the pulse airflow is improved, the overall efficiency of the turbine is improved, and the turbine box has great production practice significance.
In addition, the application of the invention can effectively improve the damage of the exhaust gas pulse airflow from an external engine to the turbine box of the supercharger.
Drawings
FIG. 1 is a schematic diagram of a front side structure of a turbine box of an exhaust gas turbocharger for improving the exhaust pulse pressure of an engine, provided by the invention;
FIG. 2 is a schematic longitudinal sectional view of a turbocharger turbine housing for improving engine exhaust pulse pressure according to the present invention;
FIG. 3 is a cross-sectional view of a single intake passage section in the single intake passage box portion, taken along line D-D of FIG. 2;
FIG. 4 is a cross-sectional view of a first circular arc segment portion of the single inlet channel case portion taken along the line C-C of FIG. 2 in a first embodiment;
FIG. 5 is a cross-sectional view of a first circular arc segment portion of the single inlet channel case portion taken along the line C-C of FIG. 2 in a second embodiment;
FIG. 6a is a front view of an internal chamber flow path in an exhaust gas turbocharger turbine housing of the present invention for improving engine exhaust pulse pressure;
FIG. 6b is a side view of an exhaust gas turbocharger turbine housing having internal chamber flow passages for improved engine exhaust pulse pressure provided by the present invention;
FIG. 6c is an isometric view of an exhaust gas turbocharger turbine housing having an internal chamber flow passage for improving engine exhaust pulse pressure in accordance with the present invention;
FIG. 7a is a front view of the turbine case of an exhaust gas turbocharger of the present invention for improving the pressure of the exhaust pulse of the engine;
FIG. 7b is a left side view of an exhaust gas turbocharger turbine case of the present invention providing improved engine exhaust pulse pressure;
FIG. 8 is a perspective view of the turbine case of the exhaust gas turbocharger of the present invention for improving the pressure of the exhaust pulse of the engine;
1. a single inlet channel section; 2. a turbine box main box body; 4. a dual inlet passage box portion; 5. a vortex rear flange;
7. a bearing body mating end surface; 8. opening a gear; 9. an inlet flange; 12. separating ribs; 13. a first arc segment portion; 14. a single inlet channel box portion; 15. a tongue portion;
Detailed Description
In order to make the technical means for realizing the invention easier to understand, the following detailed description of the present application is made in conjunction with the accompanying drawings and embodiments. It is to be understood that the specific embodiments described herein are merely illustrative of the relevant application and are not limiting of the application. It should be noted that, for convenience of description, only the portions related to the present application are shown in the drawings.
It should be noted that the embodiments and features of the embodiments in the present application may be combined with each other without conflict. The present application will be described in detail below with reference to the embodiments with reference to the attached drawings.
It should be noted that in the description of the present application, the terms of direction or positional relationship indicated by the terms "center", "upper", "lower", "left", "right", "vertical", "horizontal", "inner", "outer", etc. are 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 device or element 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 otherwise explicitly specified and limited, the term "mounted" and the like should be interpreted broadly, and may be, for example, either fixedly mounted or detachably mounted.
The specific meaning of the above terms in the present application can be understood by those skilled in the art as the case may be.
Referring to fig. 1 to 8, the present invention provides an exhaust turbocharger turbine case for improving engine exhaust pulse pressure, comprising a turbine case main body 2;
the turbine case main body 3 includes a hollow single intake passage case portion 14 (i.e., a D-region portion in fig. 2) and a double intake passage case portion 4 (i.e., a volute-shaped S-region portion in fig. 2);
the double inlet channel box section 4 is located on top of the single inlet channel box section 14;
wherein the single intake passage case portion 14 has a second intake passage 140 therein;
the interior of the double inlet channel box part 4 is provided with two hollow first inlet sub-channels 40;
the rear end opening of the second air intake channel 140 inside the single air intake channel box part 14 is communicated with the lower end openings of the two first air intake sub-channels 40 inside the double air intake channel box part 4;
wherein, the inner ends of the two first air inlet sub-channels 40 which are distributed in a surrounding way are overlapped together, and the overlapped part of the two first air inlet sub-channels is provided with a circle of opening (namely, the opening is provided with the same inner opening and is used as an air outlet) in a surrounding way, and the opening is provided with a ring-shaped vaneless nozzle ring 20 with a hollow inner part in a surrounding way (the radial section of the vaneless nozzle ring 20 is rectangular);
the outer end of the vaneless nozzle ring 20 is circumferentially provided with an air inlet communicated with the first air inlet sub-channel 40;
a circle of open shelves 8 (namely as air outlets) are circumferentially arranged at the inner side end of the bladeless nozzle ring 20;
the vaneless nozzle ring 20 is communicated with the inlet end of the hollow turbine runner 6 through the opening 8;
the outlet end of the turbine runner 6 is communicated with one end of an exhaust pipe through a turbine rear flange 5;
a turbine runner 6 located inside the double intake passage case portion 4 (specifically inside the right end of the double intake passage case portion 4);
a vortex rear flange 5 provided on the right side of the double intake passage case portion 4;
that is, the vaneless nozzle ring 20 serves as two first inlet sub-passages 40 (i.e., dual inlet passages) within the dual inlet passage housing portion 4, communicating with the middle of the inlet end of the turbine runner 6, the transition portion.
It should be noted that, inside the turbine runner 6, for installing a turbine, the high-speed airflow flowing out from the two first inlet sub-channels 40 inside the double inlet channel box part 4 enters into the turbine runner 6 through the open gear 8, and can drive the turbine to rotate. It should be noted that the installation manner of the turbine is the conventional installation manner, and is not described herein again.
Wherein, the air inlet at the front end of the second air inlet channel 140 is communicated with one end of the double-row cylinder upper exhaust manifold in different firing sequence in the external engine.
It should be noted that the exhaust manifold is used to exhaust the exhaust gas pulse flow.
In the invention, in the concrete implementation, 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 exhaust gases.
In the present invention, in a concrete implementation, a partition rib 12 for partitioning the two first intake sub-passages 40 inside the dual intake passage box portion 4 is provided between the two first intake sub-passages 40, that is, the two first intake sub-passages 40 inside the dual intake passage box portion 4 are two sub-passages obtained by partitioning one intake passage through the partition rib 12.
In the present invention, in a specific implementation, the two first sub-air inlet channels 40 are channels distributed in a circular arc shape.
It should be noted that the other end of the exhaust pipe connected to the vortex rear flange 5 is directly communicated with the outside atmosphere or is communicated with the outside atmosphere through a post-treatment device.
In the invention, in the concrete implementation, 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 a bearing body (namely a supercharger bearing body, also called a supercharger intermediate body) positioned outside through a clamping band or a screw pressing plate.
In the present invention, in a specific implementation, the single intake passage box portion 14 (i.e., the portion indicated by the D region in fig. 2) includes the single intake passage section 1 and the first circular arc section portion 13 (which may be integrally formed) connected to each other;
a second air intake passage 140 penetrating through the single air intake passage section 1 and the inside of the first circular arc section portion 13;
wherein, the central angle of the first arc segment part 13 is α, and the corresponding position of the center of the circle is located on the axis a of the lowest position in the inner wall of the vaneless nozzle ring 20;
the second air inlet channel 140 located inside the first circular arc segment portion 13 is only a single air inlet channel, or comprises two separate independent second air inlet sub-channels 1401; that is, according to the present invention, the interior of the first arc segment portion 13 of the single intake passage casing portion 14 may be a single passage or a double passage.
Wherein, the second air intake passage 140 located inside the single air intake passage section 1 is only a single air intake passage;
in concrete implementation, the opening area of the portion of the second air intake passage 140 located inside the single air intake passage section 1 is larger than the opening area of the portion of the second air intake passage 140 located inside the first circular arc section portion 13 (no matter the opening area of a single passage or the sum of the opening areas of the two second air intake subchannels 1401).
It should be noted that the center position of the first arc segment portion 13 corresponding to the central angle α is located on the axis a of the lowest position of the inner wall of the vaneless nozzle ring 20 inside the double inlet passage casing portion 4.
In the present invention, in a specific implementation, the dual inlet channel housing portion 4 (i.e., the portion of the S area in fig. 2) is a second arc segment portion (i.e., the portion of the housing area covered by the central angle β shown in fig. 2), the second arc segment portion has a central angle β, and the corresponding center position is located on the central axis of the vaneless nozzle ring 20;
the rear end (i.e., the end point) of the first arc segment portion 13 is connected with the inner wall (i.e., the start point) of the lower end of the second arc segment portion (the joint is a smooth arc transition portion);
that is, the end point of the first arc segment portion 13 at the angle α and the start point of the second arc segment portion at the angle β are uniformly transitionally connected and communicated.
It should be noted that two hollow first sub-air inlet passages 40 penetrate through the inside of the second circular arc segment portion.
It is noted that the single intake passage section 1 is located on one side of the double intake passage case portion 4 while serving as a side wall of the first intake sub-passage 40 in the double intake passage case portion 4.
In a concrete implementation, the value range of the central angle α of the first arc section part 13 is 0-45 °, and is not limited to be changed within the range of 0-45 °;
the central angle β of the second circular arc segment portion is 360 °.
In particular, the first arc section 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 an obliquely distributed tongue part 15 for separating the airflow of the single air inlet channel section 1 and preventing the airflow 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 the rear to the front.
In a specific implementation, the rear end opening of the second air intake channel 140 inside the single air intake channel housing portion 14 is located behind and below the tongue portion 16.
In the present invention, the second inlet duct 140 inside the single inlet duct housing portion 14 is a constricted duct having an opening whose total area gradually decreases from the inlet.
In the present invention, in a concrete implementation, each first air inlet sub-channel 40 in the double air inlet channel box part 4 is a necking channel with an opening area gradually reduced from an air inlet (i.e. the diameter gradually reduces from the air inlet)
In the present invention, in a concrete implementation, with respect to 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;
while the sectional shape of the second intake air passage 140 inside the single intake air passage section 1, which is located at the rear end of the single intake air passage case portion 14, is as shown in fig. 5 when the second intake air passage 140 inside the single intake air passage section 1 is only a single intake air passage, and is as shown in fig. 4 when the second intake air passage 140 inside the single intake air passage section 1 includes two separate independent second intake air subchannels 1401; that is, the second air intake passage 140 inside the single air intake passage section 1 may have two shapes, i.e., a single-passage or a double-passage structure, and thus has two different passage cross-sectional shapes.
In the present invention, the cross-sectional shape of the first intake sub-passage 40 inside the double intake passage case portion 4 is shown in fig. 1.
In the present invention, in a specific implementation, two first air inlet sub-channels 40 inside the double air inlet channel box part 4 are communicated with the turbine runner 6 through a hollow open gear 8;
meanwhile, the rear end opening of the first air intake passage 140 located inside the first arc segment portion 13 of the angle α is also communicated with the turbine runner 6 through the hollow open step 8.
It should be noted that, for the present invention, the single intake passage section 1 in the single intake passage housing portion 14 is an independent area, and communicates with the first arc section portion 13 at the angle α, and communicates with the outside (for example, an exhaust manifold for discharging exhaust gas of an external engine) through the inlet flange 9, or may be provided with a bypass hole to communicate with the outside.
In a specific implementation, exhaust gas discharged from two rows of cylinders with different engine firing sequences flows in from the second air inlet channel 140 at the single air inlet channel section 1 in the single air inlet channel box part 14 (i.e. the part D in fig. 2), and forms a confluence, flows through the double air inlet channel box part 4, enters the turbine runner 6, and is discharged through an exhaust pipe connected with the turbine rear flange 5.
It should be noted that, for the present invention, a single and double mixing channel is adopted, and in terms of manufacturability, the air inlet of the turbine box cancels the separating rib, and a single air inlet channel is adopted, so that the impact influence of the exhaust gas flow pulse discharged by the cylinder of the engine on the separating rib in the turbine box can be effectively reduced, and the pressure fluctuation of the tongue part can be reduced.
According to the invention, the single-double mixed channel is adopted, so that the arrangement of the reinforcing ribs can be reduced in the process, the casting defect at the thin wall of the reinforcing rib is prevented, and the overall weight of the turbine box is reduced.
It should be noted that, with the present invention, the range of the α angle of the double intake passage box portion 4 and the single intake passage box portion 14, and the range of the α angle of the first arc segment portion 13 in the single intake passage box portion 14, can be adjusted as needed.
It should be noted that, referring to fig. 3 to 5, for the present invention, compared with the second air intake channel 140 (i.e. single channel) of the single air intake channel segment 1 in the single air intake channel housing portion 14, the two first air intake sub-channels 40 in the dual air intake channel housing portion 4 have the partition rib 12 in between, when the pulse air is taken in from the second air intake channel 140 (i.e. single channel) as the transition section (i.e. exhaust air entering the external engine cylinder), the air flows can be mixed in the second air intake channel 140 (i.e. single channel), the influence of the air flow pulse on the turbine can be reduced, by reducing the opening area of the channel (i.e. using the necking channel), the tongue position can be designed to be strengthened, and the pressure fluctuation at the tongue position can be reduced, and such a structure can effectively shorten the length of the inlet section of the turbine box, and reduce the weight of the turbine box, the contact area of the inlet airflow and the channel wall is reduced, and the additional effects of reducing the cost of the turbine shell, reducing the friction loss of the airflow and improving the thermal shock resistance of the turbine box are achieved.
It should be noted that, for the present invention, the inlet flange 9 of the turbine box is connected to the single intake passage section 1 in the single intake passage box portion 14, and after passing through the single intake passage section 1 of the single intake passage box portion 14 and the second arc section 13 at the angle α, the turbine box gradually transitions to the double intake passage box portion 4 (i.e., the second arc section portion), and the double intake passage box portion 4 has two hollow first intake sub-passages 40, and the cross section of the first intake sub-passages is a double-passage cross section.
It should be noted that, with the present invention, the exhaust gas discharged from the engine flows in from the single intake channel section 1 in the single intake channel box portion 14, enters the two first intake sub-channels 40 in the double intake channel box portion 4 to form a split flow, and then flows through the turbine runner 6 and is discharged through the exhaust pipe connected to the turbine rear flange 5.
It can be seen from the above technical solutions that the gas flow passage inside the turbine box of the turbocharger is gradually changed from a single passage at the inlet of the single intake passage box portion 14 to a two-passage flow passage of 360 ° inside the double intake passage box portion 4 (i.e. two hollow first intake sub-passages 40), and the gas flow enters the turbine flow passage 6 through these passages to drive the turbine inside the turbine flow passage, so that the damage of the pulse gas flow from the engine double row exhaust to the turbocharger turbine can be improved.
For the present invention, a single-double mixing channel turbine box structure is adopted, the air flow is mixed in the single air inlet channel box body part 14, and the double channels (i.e. the two first air inlet sub-channels 40) in the double air inlet channel box body part 4 are used for converting the pressure energy and the kinetic energy.
The turbine box with the single-double mixing channel has the advantages of scientific structure, good manufacturability, strong adaptability and the like. The turbine case of this structure can be equipped with the waste gas that different exhaust manifold come on the engine and get into booster turbine case, and the air current mixes in single cross-section passageway section, under the prerequisite that does not change original booster appearance interface position, through changing the structure pattern, rationally sets up the changeover portion, reduces carminative shock wave influence, promotes booster turbine case and to the utilization ratio of pulse air current energy, effectively promotes booster turbine efficiency.
For the invention, the flexible adjustment of the range of the variable channel transition region (namely the first arc section part 13 included by the single air inlet channel box body part 14) can strengthen the tongue position structure of the turbine box, effectively utilize the exhaust pulse, reduce the exhaust shock wave, realize the uniform pressure reduction and acceleration of the air flow, drive the turbine impeller to rotate by the high-speed waste gas with uniform static pressure distribution, effectively improve the utilization rate of the low-pressure waste gas and improve the efficiency of the turbine.
It should be noted that, for the present invention, the conversion rate from the air pressure energy to the kinetic energy can be improved by using two channels (i.e. two first air inlet sub-channels 40) with uniform necking, the impact on the turbine can be reduced by using a uniform non-pulse high-speed air flow, the tongue part 15 can be easily reinforced by the transition region (i.e. the first arc section part 13 included in the single air inlet channel box body part 14), and the pressure fluctuation of the tongue part 15 can be reduced.
It should be noted that, with the present invention, the turbine case as an exhaust gas turbocharger includes a double intake passage case portion and a single intake passage case portion, and the cross section of the internal passage of the turbine case also includes two types of a double passage cross section and a single passage cross section. The second air intake channel 140 in the single air intake channel box part is located at the inlet section, and the second air intake channel 140 located at the single air intake channel section 1 is of a single cross section and has no partition ribs. The two first air inlet sub-channels 140 are separated by a separation rib 12 in the middle; the air outlets of the two first air inlet sub-channels 140 are located in the ring turbine open gear area. The single-channel and double-channel area range can be flexibly arranged according to the requirement.
In order to more clearly understand the technical solution of the present invention, the following describes the working principle of the present invention.
The invention provides a turbine box of an exhaust gas turbocharger, which comprises an inlet flange, a double-air-inlet-channel box body part, a single-air-inlet-channel box body part, a gear opening, a bearing body matching surface and the like, wherein exhaust gas discharged by an engine enters an air passage through a single air inlet channel (namely a second air inlet channel 140) in a single air inlet channel section 1 in a single air inlet channel box body part 14 from an inlet of the turbine box, the single air inlet channel is a necking channel, the pressure energy of exhaust pulses is converted into kinetic energy, the exhaust gas at low speed and high pressure enters the single air inlet channel to be subjected to pressure reduction and acceleration mixing, the energy of high-speed and low-pressure pulse air flow is mutually exchanged during mixing and is alternately converted into pushing and pushed air flow, after the pressure stabilization balance of the air flow in the single air inlet channel (namely the second air inlet channel 140) is realized, the pressure reduction and acceleration are continuously carried out in the necking double channels (namely two first air inlet sub-, and then enters the turbine runner 6 through opening to drive the turbine inside the turbine runner 6 to rotate.
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 the following beneficial effects:
1. according to the turbine box, the air inlet channel of the turbine box is switched from a single channel to a double channel, so that the pulse impact of air flow can be reduced, and the production cost can be reduced. The length and the mixed cross-section position of transition passageway (the second inlet channel 140 in single inlet channel section 1 and the first circular arc section part 13 promptly) can set up according to the performance requirement is nimble, and the necking down passageway can be so that pulse air current can be kinetic energy with pressure energy conversion in the air flue, and the single channel inner wall is less than binary channels inner wall surface area, and high-speed air current can reduce by a wide margin with inner wall frictional heating in the passageway to reduce the loss of air current kinetic energy.
2. According to the turbine box, the air inlet channel of the turbine box is switched from a single channel to a double channel, so that the conversion efficiency of air inlet pressure energy to kinetic energy can be improved, the air flow pressure in the channel can be effectively balanced by the transition channel (such as the single air inlet channel section 1 and the second air inlet channel 140 in the first arc section part 13) of the single channel, and high airflow energy can be obtained by low exhaust pressure under the low-speed state of an engine, so that the static pressure distribution of the circumference of the turbine inlet is more uniform, the rotating speed of a driving rotor is uniformly increased, the supercharging pressure under the low-speed state is improved, and the low-speed response performance of a supercharger is improved.
3. According to the turbine box, the airflow channel of the turbine box is subjected to single-conversion double-conversion, the pressure energy of pulse airflow can be effectively utilized, a series of tests show that the measure well balances the exhaust pulse pressure, the advantages of the bladeless turbine box with 360-degree full air inlet can be fully utilized in a double-channel occasion, the excitation influence of airflow shock waves on the long tongue head 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 a scientific structural design, can effectively balance the pressure of the exhaust gas pulse airflow discharged from the double-row cylinders with different firing sequences in the external engine, improves the utilization rate of the pulse airflow energy, is favorable for improving the overall efficiency of the turbine, and has great production practice significance.
In addition, the application of the invention can effectively improve the damage of the exhaust gas pulse airflow from an external engine to the turbine box of the supercharger.
The foregoing is only a preferred embodiment of the present invention, and it should be noted that, for those skilled in the art, various modifications and decorations can be made without departing from the principle of the present invention, and these modifications and decorations should also be regarded as the protection scope of the present invention.
Claims (9)
1. An exhaust gas turbocharger turbine box for improving the exhaust pulse pressure of an engine is characterized by comprising a turbine box main box body (2);
the turbine box main body (3) comprises a hollow single air inlet channel body part (14) and a double air inlet channel 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 intake passage box portion (14) has a second intake passage (140) therein;
the double-air-inlet-channel box body part (4) is internally provided with two hollow first air inlet sub-channels (40);
the rear end opening of a second air inlet channel (140) in the single air inlet channel box body part (14) is communicated with the lower end openings of two first air inlet sub-channels (40) in the double air inlet channel box body part (4);
wherein, the inner side ends of the two first air inlet sub-channels (40) which are distributed in a surrounding way are overlapped together, the overlapped part of the two first air inlet sub-channels is provided with a circle of opening in a surrounding way, and the opening is provided with a ring-shaped vaneless nozzle ring (20) which is hollow inside in a surrounding way;
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);
a circle of open shelves (8) are circumferentially arranged at the inner side end of the vaneless nozzle ring (20);
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 turbine rear flange (5);
the turbine runner (6) is positioned in the double-air-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);
wherein, the air inlet at the front end of the second air inlet channel (140) is communicated with one end of an exhaust manifold on two rows of cylinders with different firing sequences in an external engine;
the first air inlet sub-channel (40) and the second air inlet channel (140) are necking channels.
2. The exhaust turbocharger turbine housing for improving engine exhaust pulse pressure according to claim 1, characterized in that an inlet flange (9) is provided at a front end of the intake passage housing portion (14).
3. The exhaust turbocharger turbine housing for improving engine exhaust pulse pressure according to claim 1, wherein a partition rib (12) for partitioning the two first intake sub-passages (40) is provided between the two first intake sub-passages in the intake passage housing portion (4).
4. The exhaust-gas turbocharger turbine housing for improving the engine exhaust gas pulse pressure as claimed in claim 1, characterized in that the two first inlet sub-channels (40) are channels which are distributed in the shape of a circular arc.
5. The exhaust turbocharger turbine case for improving engine exhaust pulse pressure according to claim 1, wherein the single intake passage case portion (14) includes a single intake passage section (1) and a first circular arc section portion (13) connected to each other;
the second air inlet channel (140) penetrates through the single air inlet channel section (1) and the interior of the first circular arc section part (13);
wherein, the central angle of the first circular arc section part (13) is alpha, and the corresponding position of the center of the circle is positioned on the axis A of the lowest position in the inner wall of the vaneless nozzle ring (20);
the second air inlet channel (140) is positioned inside the first circular arc segment part (13) and is only a single air inlet channel, or comprises two separated independent second air inlet sub-channels (1401);
wherein the second air inlet channel (140) located inside the single air inlet channel section (1) is only a single air inlet channel.
6. The exhaust turbocharger turbine housing for improving engine exhaust gas pulse pressure according to claim 5, wherein the double intake passage housing portion (4) is a second circular arc segment portion having a central angle β, the corresponding central position being located on the central axis of the vaneless 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;
and two hollow first air inlet sub-channels (40) penetrate through the inner part of the second circular arc section part.
7. The exhaust gas turbocharger turbine box for improving the engine exhaust gas pulse pressure according to claim 6, characterized in that the central angle α of the first circular arc segment portion (13) ranges from 0 ° to 45 °;
the central angle β of the second circular arc segment portion is 360 °.
8. The exhaust turbocharger turbine housing for improving engine exhaust pulse pressure according to claim 1, wherein the second intake passage (140) inside the single intake passage case portion (14) is a constricted passage having an opening total area gradually reduced from the intake port.
9. The exhaust gas turbocharger turbine casing for improving engine exhaust gas pulse pressure according to claim 1, wherein each of the first intake sub-passages (40) inside the double intake passage casing portion (4) is a constricted passage having an opening area gradually reduced from the intake port.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202011621920.7A CN112746876A (en) | 2020-12-30 | 2020-12-30 | Improve exhaust gas turbocharger turbine case of engine exhaust pulse pressure |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202011621920.7A CN112746876A (en) | 2020-12-30 | 2020-12-30 | Improve exhaust gas turbocharger turbine case of engine exhaust pulse pressure |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN112746876A true CN112746876A (en) | 2021-05-04 |
Family
ID=75650335
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202011621920.7A Pending CN112746876A (en) | 2020-12-30 | 2020-12-30 | Improve exhaust gas turbocharger turbine case of engine exhaust pulse pressure |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN112746876A (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114738063A (en) * | 2022-04-28 | 2022-07-12 | 一汽解放汽车有限公司 | Exhaust pipe with volute, engine and vehicle |
-
2020
- 2020-12-30 CN CN202011621920.7A patent/CN112746876A/en active Pending
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114738063A (en) * | 2022-04-28 | 2022-07-12 | 一汽解放汽车有限公司 | Exhaust pipe with volute, engine and vehicle |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN1214191C (en) | Dewwirler system for centrifugal compressor | |
| CN101929359B (en) | Asymmetric split-inlet turbine housing | |
| JP4317327B2 (en) | Low speed, high compression ratio turbocharger | |
| US4530640A (en) | Method and apparatus for wastegating turbocharged engine with divided exhaust system | |
| US9157396B2 (en) | Nozzled turbine | |
| US20040068981A1 (en) | Exhaust mixer and apparatus using same | |
| US20040234373A1 (en) | Turbine efficiency tailoring | |
| US20050005606A1 (en) | Turbocharger compressor with non-axisymmetric deswirl vanes | |
| WO2013099461A1 (en) | Twin-scroll turbocharger | |
| KR20140099206A (en) | Axial turbine with meridionally divided turbine housing | |
| KR20050000319A (en) | Turbocharger | |
| KR20170007340A (en) | Dual volute turbocharger to optimize pulse energy separation for fuel economy and egr utilization via asymmeric dual volutes | |
| US6398487B1 (en) | Methods and apparatus for supplying cooling airflow in turbine engines | |
| JP5184825B2 (en) | Composite diffusion device for reciprocating piston combustion engine and reciprocating piston combustion engine | |
| WO1990007087A1 (en) | Jet air cooled turbine shroud for improved swirl cooling and mixing | |
| KR101369601B1 (en) | Compressor impeller | |
| KR20150097576A (en) | Turbine housing with dividing vanes in volute | |
| CN112746876A (en) | Improve exhaust gas turbocharger turbine case of engine exhaust pulse pressure | |
| CN102536432A (en) | Counter-rotating turbine combination device and engine system with same | |
| US6582188B2 (en) | Turbocharger | |
| CN214660392U (en) | Improve exhaust gas turbocharger turbine case of engine exhaust pulse pressure | |
| US20080104956A1 (en) | Turbocharger having inclined volutes | |
| CN112682116A (en) | High-performance turbine box of exhaust gas turbocharger | |
| GB2367096A (en) | Turbocharger arrangement with exhaust gas diverter valve | |
| CN114738063A (en) | Exhaust pipe with volute, engine and vehicle |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination |