CN214660392U - 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
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- CN214660392U CN214660392U CN202023299820.5U CN202023299820U CN214660392U CN 214660392 U CN214660392 U CN 214660392U CN 202023299820 U CN202023299820 U CN 202023299820U CN 214660392 U CN214660392 U CN 214660392U
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Abstract
The utility model discloses 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 single air inlet channel box body and a double air inlet channel box body; the single air inlet channel box body is internally provided with a second air inlet channel; two hollow first air inlet sub-channels are arranged in the double air inlet channel box body; 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 utility model discloses can effectively balance the waste gas pulse air current's that comes from the different biserial cylinders of firing order in the external engine pressure promotes the utilization ratio to the pulse air current energy.
Description
Technical Field
The utility model relates to an exhaust-gas drive turbo charger technical field especially relates to an improve exhaust-gas turbo charger turbine case of engine exhaust pulse pressure.
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.
SUMMERY OF THE UTILITY MODEL
The utility model aims at providing an improve exhaust gas turbine booster turbine case of engine exhaust pulse pressure to the technical defect that prior art exists.
Therefore, the utility model 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 and a hollow double air inlet channel box body;
the double-air-inlet-channel box body is positioned at the top of the single-air-inlet-channel box body;
the single air inlet channel box body is internally provided with a second air inlet channel;
the double-air-inlet-channel box body 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 is communicated with the lower end openings of two first air inlet sub-channels in the double air inlet channel box body;
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;
the vortex rear flange is arranged on the right side of the double-air-inlet-channel box body;
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, the front end of the single air inlet channel box body is provided with an inlet flange.
Preferably, a partition rib is arranged between the two first air inlet sub-channels in the double-air inlet channel box body and separates the two first air inlet sub-channels.
Preferably, the two first air inlet sub-channels are channels distributed in a circular arc shape.
Preferably, the single air inlet channel box body 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 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 air inlet channel inside the single air inlet channel box body is a necking channel with the total opening area gradually reduced from the air inlet.
Preferably, each first air inlet sub-channel in the double air inlet channel box body is a necking channel with an opening area gradually reduced from the air inlet.
By above the technical scheme provided by the utility model it is visible, compare with prior art, the utility model provides an improve exhaust gas turbine booster turbine case of engine exhaust pulse pressure, its structural design science, its pressure that can effective balance come from the biserial cylinder exhaust gas pulse air current of the different order of firing in the external engine promotes the utilization ratio to pulse air current energy, and then is favorable to promoting the whole efficiency of turbine, has the meaning of great production practice.
Furthermore, the utility model discloses an use, can also effectively improve the harm that the exhaust gas pulse air current that comes from outside engine caused the turbine case of booster.
Drawings
Fig. 1 is a schematic front side structural view of a turbine box of an exhaust gas turbocharger for improving exhaust pulse pressure of an engine according to the present invention;
fig. 2 is a schematic longitudinal sectional structure view of a turbine box of an exhaust gas turbocharger for improving exhaust pulse pressure of an engine according to the present invention;
FIG. 3 is a cross-sectional view of a single inlet passage section of the single inlet passage housing 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 housing taken along 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 housing taken along line C-C of FIG. 2 in a second embodiment;
fig. 6a is a front view of an inner chamber airflow channel in an exhaust gas turbocharger turbine box for improving the exhaust pulse pressure of an engine provided by the present invention;
FIG. 6b is a side view of an exhaust gas turbocharger turbine housing having an internal chamber airflow path for improving engine exhaust pulse pressure in accordance with the present invention;
fig. 6c is a perspective view of the internal airflow channel of the exhaust gas turbocharger turbine box for improving the exhaust pulse pressure of the engine according to the present invention;
fig. 7a is a front view of the turbine box of the exhaust gas turbocharger for improving the exhaust pulse pressure of the engine provided by the present invention;
fig. 7b is a left side view of an exhaust gas turbocharger turbine case for improving engine exhaust pulse pressure according to the present invention;
fig. 8 is a perspective view of the exhaust gas turbocharger turbine box for improving the exhaust pulse pressure of the engine according to the present invention;
1. a single inlet channel section; 2. a turbine box main box body; 4. a double inlet channel box body; 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; 15. a tongue portion;
Detailed Description
In order to make the technical means of the present invention easier to understand, the present application will be further described in detail with reference to the accompanying drawings and examples. 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 gas turbocharger turbine box for improving exhaust pulse pressure of an engine, comprising a turbine box main body 2;
the turbine case main body 2 includes a hollow single intake passage body 14 (i.e., a D-region portion in fig. 2) and a double intake passage body 4 (i.e., a volute-shaped S-region portion in fig. 2);
the double-air-inlet-channel box body 4 is positioned at the top of the single-air-inlet-channel box body 14;
wherein, the single air inlet channel box body 14 is internally provided with a second air inlet channel 140;
the double air inlet channel box body 4 is internally 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 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 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;
the turbine runner 6 is positioned inside the double air inlet channel box body 4 (specifically, inside the right end of the double air inlet channel box body 4);
the vortex rear flange 5 is arranged on the right side of the double-air-inlet-channel box body 4;
that is, the vaneless nozzle ring 20 serves as two first inlet sub-passages 40 (i.e., dual inlet passages) inside the dual inlet passage housing 4, and communicates with and transitions between the inlet ends of the turbine runner 6.
It should be noted that, inside the turbine runner 6, a turbine is installed, and the high-speed airflow flowing out from the two first air inlet sub-channels 40 inside the double air inlet channel box 4 enters the turbine runner 6 through the open gear 8, so as to 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 utility model, in the concrete implementation, the front end of the single air inlet channel box body 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.
The utility model discloses in, on specifically realizing, between two inside first inlet sub-channels 40 of two inlet channel boxes 4, have the separation muscle 12 of coming with both spaced apart, that is to say, two inside first inlet sub-channels 40 of two inlet channel boxes 4 are two sub-channels that obtain after separating an inlet channel through separating muscle 12.
In the present invention, in the concrete implementation, the two first air inlet sub-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.
The utility model discloses in, on specifically realizing, the upper portion left side of turbine case owner box 2 is bearing body counterface 7, and this bearing body counterface 7 carries out the be assembled between/be connected between with the bearing body that is located the outside (supercharger bearing body, also called the booster midbody) through strap or screw clamp plate.
In the present invention, in particular, the single air inlet channel box 14 (i.e. the portion of the D region in fig. 2) includes a single air inlet channel section 1 and a first circular arc section 13 (which may be integrally formed) connected together;
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 to say, to the utility model discloses, inside the first circular arc section part 13 of single inlet channel box 14, can be the single channel, also can be the binary channels.
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 dual inlet passage housing 4.
In the present invention, in particular, the double inlet channel box 4 (i.e., the S-area portion in fig. 2) is a second arc section portion (i.e., the box area portion covered by the central angle β shown in fig. 2), the second arc section portion has a central angle β, and the corresponding center position is located on the central axis of the bladeless 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 should be noted that the single intake passage section 1 is located on one side of the dual intake passage housing 4, and serves as a side wall of the first intake sub-passage 40 in the dual intake passage housing 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 the concrete implementation, 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 4, and is provided with a tongue part 15 which is distributed obliquely and used 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 inlet channel 140 inside the single air inlet channel box 14 is located behind and below the tongue portion 16.
The utility model discloses in, in the concrete realization, the inside second inlet channel 140 of single inlet channel box 14 is the necking down passageway that the total area of opening begins to reduce gradually from the air inlet.
In the present invention, in the concrete implementation, each first air inlet sub-channel 40 inside the double air inlet channel box 4 is a necking channel whose opening area gradually decreases from the air inlet (i.e. from the air inlet, the caliber gradually decreases)
In the present invention, in particular, for the single intake passage box 14, the cross-sectional shape of the second intake passage 140 located at the front end is as shown in fig. 3;
the cross-sectional shape of the second intake air passage 140 located at the rear end of the single intake air passage housing 14 and inside the single intake air passage section 1 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 air inlet sub-channel 40 inside the double air inlet channel box 4 is shown in fig. 1.
In the utility model, in the concrete implementation, two first air inlet sub-channels 40 inside the double air inlet channel box body 4 are communicated with the turbine runner 6 through the 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 air inlet channel section 1 in the single air inlet channel box 14 is an independent area, and is communicated with the first arc section part 13 of the α angle, and is communicated with the outside (for example, an exhaust manifold for discharging 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 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 14 (i.e. the section D in fig. 2), and forms a confluence, and enters the turbine runner 6 after flowing through the double air inlet channel box 4, and is discharged through an exhaust pipe connected with the rear vortex flange 5.
It should be noted that, to the utility model discloses, adopt single two hybrid channel, with respect to the manufacturability, the air inlet cancellation of turbine case separates the muscle, adopt an independent inlet channel, can effectively reduce the impact influence of the cylinder exhaust waste gas air current pulse of engine to separating the muscle in the turbine case, alleviate the pressure oscillation at tongue position, and such structure, can effectively alleviate the weight of turbine case, the air inlet department of turbine case does not separate the muscle, also can reduce the area of contact of air current and passageway wall, reduce the air current friction loss, make waste gas carry out the intensive mixing.
The utility model discloses, adopt single two hybrid channel, can reduce arranging of strengthening rib in technology, prevent to appear the casting defect in strengthening rib thin wall department, alleviate the whole weight of turbine case.
It should be noted that, for the present invention, the area range of the α angle of the first arc segment part 13 in the double inlet channel box 4 and the single inlet channel box 14, and the single inlet channel box 14 can be adjusted as required.
It should be noted that, referring to fig. 3 to fig. 5, it can be known that, 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 box 14, there is a separating rib 12 in the middle of the two first air intake sub-channels 40, when the pulse air is taken in by taking the second air intake channel 140 (i.e. single channel) as the transition section (i.e. entering the exhaust of the external engine cylinder), the air flow can be mixed in the second air intake channel 140 (i.e. single channel), which can reduce the influence of the air flow pulse on the turbine, by reducing the opening area of the channel (i.e. adopting 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 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, to the utility model discloses, the single inlet channel section 1 in inlet flange 9 and the single inlet channel box 14 of turbine case links to each other, through the second circular arc section 13 of single inlet channel section 1 and alpha angle of single inlet channel box 14 after, gradually transition to two inlet channel boxes 4 (be the second circular arc section part), and two inlet channel boxes 4 have two hollow first air inlet sub-channel 40, and its cross-section is the binary channels cross-section.
It should be noted that, to the utility model discloses, engine exhaust's waste gas, after single inlet channel section 1 by single inlet channel box 14 flows into, enters into two first inlet sub-channel 40 in the two inlet channel boxes 4 after, forms the reposition of redundant personnel, then flows through turbine runner 6, through the blast pipe discharge of being connected with vortex rear flange 5.
It can be seen from the above technical solutions that the air flow passage inside the turbine box of the turbocharger is gradually changed from a single passage at the inlet of the single air inlet passage box 14 to a two-passage flow passage (i.e. two hollow first air inlet sub-passages 40) of 360 ° inside the double air inlet passage box 4, and the air 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 air flow from the engine double-row exhaust to the turbocharger turbine can be improved.
To the utility model discloses, be the turbine case structure who adopts single two hybrid channel, the single inlet channel of air current in single inlet channel box 14 mixes, and the inside binary channels of two inlet channel boxes 4 (be two first inlet sub-channel 40) carry out pressure energy and kinetic energy conversion.
To the utility model discloses, as the turbine case that has single two hybrid channel, have advantages such as structure science, manufacturability good, strong adaptability. 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.
The utility model discloses, the nimble adjustment of the transition district of changing the passageway (first circular arc section part 13 that single inlet channel box 14 includes promptly) scope can make the tongue position structure of turbine case strengthen, can effectively utilize the exhaust pulse, reduces the exhaust shock wave, realizes that the air current evenly steps down with higher speed, and high-speed waste gas can be rotatory with comparatively even static pressure distribution drive turbine wheel, effectively promotes the utilization ratio of low pressure waste gas, promotes turbine efficiency.
It should be noted that, to the utility model discloses, can be through the binary channels (being two first inlet sub-channel 40) that adopt even necking down, improve the air pressure and can arrive the conversion rate of kinetic energy, even non-pulse high velocity air current, can reduce the impact to the turbine, the transition zone (being the first circular arc section part 13 that single inlet channel box 14 includes) strengthens the processing to tongue position 15 easily, alleviate 15 pressure fluctuations at tongue position, and such structure, can effectively alleviate the weight of turbine case, the pulse air current import department of turbine case does not have the partition muscle, can make pulse air current homogeneous mixing, when seting up the bypass hole in single inlet channel box 14 department simultaneously, can let the exhaust more smooth and easy, reduce the inhomogeneous influence to the turbine of tolerance, reduce exhaust noise.
It should be noted that, to the utility model discloses, as exhaust gas turbocharger's turbine case, including two inlet channel boxes and single inlet channel box, this turbine incasement portion passageway's cross-section also includes two kinds of styles of binary channels cross-section and single channel cross-section. The second air inlet channel 140 in the single air inlet channel box body 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 separating rib. 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 understand the technical solution of the present invention more clearly, the working principle of the present invention is explained below.
The utility model provides a turbine box of exhaust gas turbocharger, including the import flange, two inlet channel boxes, single inlet channel box, open shelves and bearing body fitting surface etc, engine exhaust waste gas is by the import of turbine box, through single inlet channel (namely second inlet channel 140) entering the air flue in single inlet channel section 1 in single inlet channel box 14, single inlet channel is the necking down passageway, the pressure energy of exhaust pulse turns into kinetic energy, waste gas under low speed and high pressure gets into this single inlet channel, can step down and accelerate mixing, the energy of high-speed low pressure pulse air current exchanges each other during mixing, become the air current that promotes and is promoted in turn, after the air current in single inlet channel (namely second inlet channel 140) realizes steady voltage balance, continue to step down and accelerate in the binary channels of necking down (namely two inside first inlet sub-channels 40 of two inlet channel boxes 4), 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 utility model provides an improve exhaust gas turbine booster turbine case of engine exhaust pulse pressure has following beneficial effect:
1. the utility model discloses a turbine case, turbine case's inlet channel is switched by the single channel and is become the binary channels, and reducible air current pulse strikes and reduction in production cost. 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. The utility model discloses a turbine case, turbine case's inlet channel is switched by the single channel and is become the binary channels, can improve the inlet pressure and can be to kinetic energy conversion efficiency, the transition passageway of single channel (for example the second inlet channel 140 in single inlet channel section 1 and the first circular arc section part 13) can effectively balance the interior airflow pressure of passageway, low exhaust pressure obtains higher air current ability under the engine low-speed state, make turbine import circumference static pressure distribution more even, the rotational speed of drive rotor evenly promotes, thereby improve boost pressure under the low-speed state, promote the low-speed response performance of booster.
3. The utility model discloses a turbine case, turbine case's airflow channel carries out single change double conversion, can effectively utilize pulse airflow's pressure energy, shows through a series of tests, and the fine balanced exhaust pulse pressure of this kind of measure, in the binary channels occasion, can 360 full air admission's of make full use of bladeless turbine case advantage, has weakened the excitation influence of air current shock wave to turbine case long tongue head structure, has improved engine low-speed performance, extension turbine case life-span.
To sum up, compare with prior art, the utility model provides a pair of improve exhaust gas turbine booster turbine case of engine exhaust pulse pressure, its structural design science, its pressure that can effectively balance the exhaust waste gas pulse air current of the different biserial cylinder of order of firing in coming from the external engine promotes the utilization ratio to pulse air current energy, and then is favorable to promoting the whole efficiency of turbine, has the production practice meaning of great importance.
Furthermore, the utility model discloses an use, can also effectively improve the harm that the exhaust gas pulse air current that comes from outside engine caused the turbine case of booster.
The foregoing is only a preferred embodiment of the present invention, and it should be noted that, for those skilled in the art, a plurality of 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 box body (2) comprises a hollow single air inlet channel box body (14) and a double air inlet channel box body (4);
the double-air-inlet-channel box body (4) is positioned at the top of the single-air-inlet-channel box body (14);
wherein, the single air inlet channel box body (14) is internally provided with a second air inlet channel (140);
the double-air-inlet-channel box body (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 (14) is communicated with the lower end openings of two first air inlet sub-channels (40) in the double air inlet channel box body (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 (4);
the vortex rear flange (5) is arranged on the right side of the double-air-inlet-channel box body (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 gas turbocharger turbine housing for improving engine exhaust pulse pressure according to claim 1, characterized in that an inlet flange (9) is provided at the front end of the single intake passage housing (14).
3. The exhaust gas 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 double intake passage housing (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 housing for improving engine exhaust pulse pressure according to claim 1, characterized by a single intake passage housing (14) comprising 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 (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 gas turbocharger turbine housing for improving engine exhaust pulse pressure according to claim 1, wherein the second intake passage (140) inside the single intake passage housing (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 pulse pressure according to claim 1, wherein each of the first intake sub-passages (40) inside the double intake passage casing (4) is a constricted passage having an opening area gradually reduced from the intake port.
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| Application Number | Priority Date | Filing Date | Title |
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| CN202023299820.5U CN214660392U (en) | 2020-12-30 | 2020-12-30 | Improve exhaust gas turbocharger turbine case of engine exhaust pulse pressure |
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| CN202023299820.5U CN214660392U (en) | 2020-12-30 | 2020-12-30 | Improve exhaust gas turbocharger turbine case of engine exhaust pulse pressure |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112746876A (en) * | 2020-12-30 | 2021-05-04 | 天津北方天力增压技术有限公司 | Improve exhaust gas turbocharger turbine case of engine exhaust pulse pressure |
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Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112746876A (en) * | 2020-12-30 | 2021-05-04 | 天津北方天力增压技术有限公司 | Improve exhaust gas turbocharger turbine case of engine exhaust pulse pressure |
| CN112746876B (en) * | 2020-12-30 | 2024-08-16 | 天津北方天力增压技术有限公司 | Exhaust gas turbocharger turbine box for improving engine exhaust pulse pressure |
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