CN115977746A - Circumferential asymmetric nozzle ring, design method, volute and turbocharger - Google Patents
Circumferential asymmetric nozzle ring, design method, volute and turbocharger Download PDFInfo
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Abstract
The invention discloses a circumferentially asymmetric nozzle ring, a design method, a volute and a turbocharger, wherein the circumferentially asymmetric nozzle ring comprises: the nozzle ring body is used for being mounted on the volute body and is of a circular ring structure; vanes distributed along a circumference of the nozzle ring body, the vanes including first, second and third vanes, the first and second vanes each engaging an outer edge of the nozzle ring body, and the first and second vanes each engaging a volute tongue of the volute body; the third blades are distributed between the first blades and the second blades; and the inclination angles of the third blades are different. The inclination angles of the third blades are set to be different, and the inclination angles of the third blades are adjusted according to the angle of the airflow flowing out of the actual volute, so that the loss of the nozzle ring is lower, and the efficiency of the turbocharger is improved.
Description
Technical Field
The invention relates to the technical field of engines, in particular to a circumferentially asymmetric nozzle ring, a design method, a volute and a turbocharger.
Background
The turbocharger mainly comprises a gas compressor and a turbine, wherein the gas compressor mainly comprises a gas compressor impeller, a diffuser and a gas compressor volute; the turbine part mainly comprises a volute, a volute nozzle and a turbine wheel; and the nozzle ring of the volute nozzle comprises a nozzle ring main body and nozzle ring blades arranged on the nozzle ring main body.
A turbocharger: the air compressor is characterized in that the turbine is pushed to rotate by the inertia impulse force of waste gas discharged by an engine, and the turbine drives the coaxial impeller to rotate so as to compress air to increase the air input.
In the working process of an engine, exhausted waste gas firstly passes through the turbine shell, most of the existing turbine shells are circular or elliptical and are influenced by the shape of the turbine shell, and after fluid passes through the turbine shell, the speed and the direction of the fluid are not uniformly distributed in the circumferential direction.
The nozzle ring blade of present nozzle ring is at circumference ascending symmetric distribution, no matter how nozzle ring blade optimal design, must exist several nozzle ring blades and the fluid direction of flowing out the turbine shell and mismatch, must produce the loss in these several blades department, cause energy loss, influence turbo charger's efficiency.
Specifically, referring to fig. 1, the vanes are symmetrically distributed around the circumference of the nozzle ring vanes, which causes the vortex (the position circled by the circle in fig. 1) at the inlet of the nozzle ring, and the vortex causes energy loss.
Therefore, how to reduce the energy loss to improve the efficiency of the turbocharger is a technical problem to be solved urgently by those skilled in the art.
Disclosure of Invention
In view of this, the present invention provides a circumferentially asymmetric nozzle ring, which reduces energy loss to improve the efficiency of a turbocharger. In addition, the invention also provides a volute and a turbocharger with the circumferentially asymmetric nozzle ring. In addition, the invention also provides a design method of the circumferentially asymmetric nozzle ring.
In order to achieve the purpose, the invention provides the following technical scheme:
a circumferentially asymmetric nozzle ring, comprising:
the nozzle ring body is used for being mounted on the volute body and is of a circular ring structure;
the vanes are distributed along the circumference of the nozzle ring body and comprise a first vane, a second vane and a third vane which are obliquely arranged along the same oblique direction, the first vane and the second vane are attached to the outer edge of the nozzle ring body, and the first vane and the second vane are respectively attached to one volute tongue of the volute body;
the third blades are distributed between the first blades and the second blades;
and the included angles of all the third blades and the tangent line of the inner edge of the nozzle ring main body are different.
Preferably, in the circumferentially asymmetric nozzle ring, the third vanes have a gap with an outer edge of the nozzle ring body, and a length of the third vanes is smaller than a length of the first vanes and smaller than a length of the second vanes.
Preferably, in the nozzle ring with asymmetric circumferential direction, the first vanes and the second vanes are inclined at the same angle with respect to the inner edge of the nozzle ring body, and the first vanes and the second vanes are arranged in central symmetry.
Preferably, in the circumferentially asymmetric nozzle ring, the third vanes are distributed on both sides of a connecting line between the first vane and the second vane.
Preferably, in the nozzle ring with asymmetric circumferential direction, an included angle between a connecting line of a cross point of the length direction of the vane and the width direction of the vane and a midpoint of a trailing edge of the vane and a vertical symmetric axis of the nozzle ring body is a vane angle a i And along the first direction of the nozzle ring main body, the blade angles of the blades are sequentially as follows:
A i =A i-1 +360/N+b i ，i=1，2，3……7……N；
b i = b i-1 -1，
wherein N is the number of the blades, i is the serial number of the blades arranged in the first direction, b i For the relative angle of rotation of two adjacent said blades, b i The value range of (A) is 4-6 degrees.
Preferably, in the nozzle ring with asymmetric circumferential direction, an included angle between a connecting line of a cross point of the length direction of the vane and the width direction of the vane and a midpoint of a trailing edge of the vane and a vertical symmetric axis of the nozzle ring body is a vane angle a i When the vanes are uniformly distributed along the circumference of the nozzle ring main body, the vane angles of the vanes sequentially are as follows:
A i =A i-1 +360/N i=1，2，3……7……N，
wherein N is the number of the blades, and i is the serial number of the blades arranged in the first direction.
Preferably, in the nozzle ring with asymmetric circumferential direction, the included angle of the second vane is the initial vane angle a along the first direction of the nozzle ring main body 1 。
A volute comprising a volute body and a nozzle ring, the nozzle ring being the circumferentially asymmetric nozzle ring of any preceding claim.
Preferably, in the above scroll casing, the scroll casing main body has a first scroll tongue and a second scroll tongue, the first vane is connected to the first scroll tongue in an abutting manner, and the second vane is connected to the second scroll tongue in an abutting manner;
the first vane and the second vane divide an inner flow passage of the volute main body into a first flow passage and a second flow passage, the first flow passage is located on one side of a connecting line of the first vane and the second vane, and the second flow passage is located on the other side of the connecting line of the first vane and the second vane.
A turbocharger comprising a volute, wherein the volute is any one of the volutes described above.
A method of designing a circumferentially asymmetric nozzle ring for designing a circumferentially asymmetric nozzle ring of any of the above, comprising:
setting the blade angle A according to the item input i Inputting the three-dimensional model into design software to obtain an original version of the three-dimensional model of the nozzle ring;
CFD carries out flow field simulation analysis on the original nozzle ring model to determine whether the circumferential flow field distribution of the three-dimensional model of the original nozzle ring is uniform;
if the flow field is not uniformly distributed, setting and inputting b into the design software i The design software adjusts the blade angle of the nozzle ring blade according to the formula (1) to obtain b i Three-dimensional model of nozzle ring with corresponding values, from CFD to b i Performing flow field simulation analysis on the three-dimensional model of the nozzle ring corresponding to the value until the CFD flow field simulation determines that the circumferential flow field of the three-dimensional model of the nozzle ring is uniformly distributed, and outputting the three-dimensional model of the nozzle ring by the design software;
formula (1): a. The i =A i-1 +360/N+b i ，i=1，2，3……7……N；
Wherein, b i = b i-1 1,N is the number of blades, i is the number of blades arranged in the first direction, b i For the relative angle of rotation of two adjacent said blades, b i The value range of (A) is 4-6 degrees; a. The i The intersection of the length direction of the blade and the width direction of the bladeThe included angle between the connecting line of the fork point and the midpoint of the tail edge of the blade and the vertical symmetrical shaft of the nozzle ring main body is the blade angle.
The invention provides a circumferentially asymmetric nozzle ring, wherein the third blades are arranged in such a way that the included angles of the third blades and the tangent line of the inner edge of the nozzle ring main body are different, and the inclination angles of the third blades are adjusted according to the angle of the airflow flowing out of an actual volute, so that the loss of the nozzle ring is lower, and the efficiency of a turbocharger is improved.
Drawings
In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings used in the description of the embodiments or the prior art will be briefly described below, it is obvious that the drawings in the following description are only some embodiments of the present invention, and for those skilled in the art, other drawings can be obtained according to the drawings without creative efforts.
FIG. 1 is a schematic structural view of a circumferentially symmetrical nozzle ring with vortices as disclosed in an embodiment of the present invention;
FIG. 2 is a schematic structural view of a circumferentially asymmetric nozzle ring of the volute disclosed in the embodiments of the present invention;
FIG. 3 is a schematic view of the volute disclosed in the embodiment of the present invention;
FIG. 4 is a comparison of a circumferentially asymmetric nozzle ring and a circumferentially symmetric nozzle ring of the volute disclosed in the embodiments of the present invention;
FIG. 5 is a flow chart of a blade angle optimization process disclosed in an embodiment of the present invention;
wherein, 1 is a volute main body, and 2 is a nozzle ring main body;
31 is a first blade, 32 is a second blade, 33 is a third blade;
Detailed Description
The invention discloses a circumferentially asymmetric nozzle ring, which reduces energy loss so as to improve the efficiency of a turbocharger. In addition, the invention also discloses a volute and a turbocharger with the circumferentially asymmetric nozzle ring. In addition, the invention also provides a design method of the circumferentially asymmetric nozzle ring.
The technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the drawings in the embodiments of the present invention, and it is obvious that the described embodiments are only a part of the embodiments of the present invention, and not all of the embodiments. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present invention.
In the description of the present invention, it should be noted that the terms "center", "upper", "lower", "left", "right", "vertical", "horizontal", "inner", "outer", etc., indicate orientations or positional relationships based on the orientations or positional relationships shown in the drawings, and are only for convenience of description and simplicity of description, but do not indicate or imply that the device or element being referred to must have a particular orientation, be constructed and operated in a particular orientation, and thus, should not be construed as limiting the present invention. Furthermore, the terms "first," "second," and "third" are used for descriptive purposes only and are not to be construed as indicating or implying relative importance.
In the description of the present invention, it should be noted that, unless otherwise explicitly specified or limited, the terms "mounted," "connected," and "connected" are to be construed broadly, e.g., as meaning either a fixed connection, a removable connection, or an integral connection; can be mechanically or electrically connected; they may be connected directly or indirectly through intervening media, or they may be interconnected between two elements. The specific meanings of the above terms in the present invention can be understood in a specific case to those of ordinary skill in the art.
At present, the nozzle ring blades of the nozzle ring are symmetrically distributed in the circumferential direction, and no matter how the nozzle ring blades are optimally designed, the fluid directions of a plurality of nozzle ring blades and the fluid flowing out of a turbine shell are not matched with each other, and the loss is generated at the positions of the plurality of blades, so that the energy loss is caused, and the efficiency of the turbocharger is influenced.
Specifically, referring to fig. 1, the vanes are symmetrically distributed around the circumference of the nozzle ring vanes, which causes the vortex (the position circled by the circle in fig. 1) at the inlet of the nozzle ring, and the vortex causes energy loss.
In view of the above, the present application discloses a circumferentially asymmetric nozzle ring, which has blades asymmetrically distributed along the circumference of the nozzle ring main body to reduce the swirl and reduce the energy loss.
As shown in fig. 2, a circumferentially asymmetric nozzle ring is disclosed herein, comprising a nozzle ring body 2 and vanes.
The nozzle ring main body 2 is used for being mounted on the volute main body 1 in fig. 3, the nozzle ring main body 2 is of a circular ring structure, an inner ring of the circular ring structure is an inner edge, and an outer ring of the circular ring structure is an outer edge. The dimensions and materials for the nozzle ring body 2 may be set according to different needs.
The blades include a first blade 31, a second blade 32, and a third blade 33 (shown in fig. 3). The vanes are along a circumferential portion of the nozzle ring body 2, and first and second vanes 31, 32 each engage the outer edge of the nozzle ring body 2, the first and second vanes 31, 32 each being long vanes.
The third vanes 33 are located between the first vanes 31 and the second vanes 32, and since the nozzle ring body 2 is of a circular ring structure, the third vanes 33 are provided on both sides of the line connecting the first vanes 31 and the second vanes 32.
The third vanes 33 have a clearance from the outer edge of the nozzle ring body 2, and the length of the third vanes 33 is less than the length of the first and second vanes 31, 32.
In some embodiments, the first blade 31 and the second blade 32 are the same length.
It should be noted that the third vanes 33 in this application are plural, and the included angle of the third vanes 33 with respect to the tangent to the inner edge of the nozzle ring body 2 is different.
When asymmetric nozzle cascade of circumference and spiral case main part 1 assembled in this application, first blade 31 and second blade 32 laminate with a volute tongue of spiral case main part 1 respectively to utilize first blade 31 and second blade 32 and volute tongue, divide into first runner and second runner with the inside runner of spiral case main part 1, the third blade 33 of first blade 31 and second blade 32 line both sides corresponds a runner respectively, can make the air current independent flow in two runners, effectively avoid the collision loss of air current in two runners.
In connection with fig. 4, the solid lines in fig. 4 are circumferentially asymmetrically arranged blades, while the dashed lines are circumferentially symmetrically arranged blades.
By setting the inclination angles of the third vanes 33 to be different, the inclination angles of the third vanes 33 are adjusted according to the angle of the air flow flowing out of the actual volute, so that the loss of the nozzle ring is lower, and the efficiency of the turbocharger is improved.
The inclination angles of the first blade 31 and the second blade 32 in the present application are the same, and the first blade 31 and the second blade 32 are arranged in a central symmetry manner, that is, the second blade 32 can be obtained by rotating the first blade 31 by 180 °. It can be understood that the first blade 31 and the second blade 32 have the same inclination direction, the same inclination angle, and the same size.
Because the nozzle ring main body 2 is of a circular ring structure, the third blades 33 are distributed on two sides of the connecting line of the first blades 31 and the second blades 32, and the number of the third blades 33 on each side can be set according to different requirements. In the application, the inclination angle of each third blade 33 and the included angle between the third blade 33 and the adjacent third blade 33 are analyzed by combining a simulation technology.
The number of the vanes of the nozzle ring is defined as N, and the included angle between the connecting line of the intersection point of the length direction of the vanes and the width direction of the vanes and the midpoint of the tail edge of the vanes and the vertical symmetrical axis of the nozzle ring body 2 is defined as a vane angle A i 。
Taking the counterclockwise direction in fig. 3 and 4 as an example, the counterclockwise direction is the first direction: along the anticlockwise of nozzle ring main part 2, the blade angle of blade does in proper order:
defining: a1 is a connecting line between a cross point of a length direction of a first vane of the nozzle ring and a width direction of an initial vane and a midpoint of a trailing edge of the vane, and an included angle with a vertical axis of symmetry of the nozzle ring body is an initial vane angle, it is understood that A1 may be the initial vane. The number of the blades of the nozzle ring is N, so that the angle occupied by each blade is 360/N. Then, under the condition that the blade angles of the nozzle ring are uniformly distributed in the circumferential direction, the blade angle of the second blade is A1+360/N, and on the basis, the relative rotation angle b2 between the second blade and the first blade is increased, so that the blade angle of the second blade is A1+360/N + b2 under the condition that the blade angles are non-uniformly distributed in the circumferential direction can be obtained, and the following formula can be obtained by analogy:
A i =A i-1 +360/N+b i ，i=1，2，3……7……N；
b i = b i-1 -1；
where i is the number of the blades arranged in the first direction, b i Is the relative rotation angle of two adjacent blades, b i When less than 0, b i The value is 0.
It should be noted that, except the angular difference (i.e. 360/N) produced by the 360-degree uniform distribution of two adjacent blades, the remaining angular difference is defined as the relative rotation angle b i 。
Empirically obtained from simulation results, b i The value range of (A) is 4-6 degrees.
In practice, the included angle of the second vane 32 in the counterclockwise direction of the nozzle ring body 2 is the initial vane angle A 1 In calculating the blade angle, the blade angle from the second blade 32 to the first blade 31 and the blade angle from the first blade 31 to the second blade 32 in the counterclockwise direction may be separately calculated.
The effect that the angles of all the blades are different can be achieved through calculation of the formula, so that the problem that the circumferential distribution of the turbine inlet angle is uneven due to pressure fluctuation at the volute tongue is solved. The existing known structure only adjusts the angle of the integral blade in a consistent manner and cannot adapt to the incoming airflow under different working conditions.
When the blade along nozzle ring main part 2's circumference evenly distributed, the blade angle of blade does in proper order:
A i =A i-1 +360/N i=1，2，3……7……N，
where N is the number of blades and i is the number of blades arranged in the first direction.
According to the arrangement, the problem that airflow flowing out of the volute body 1 is not uniform in circumferential distribution is solved, the vane angle of the nozzle ring is designed in a circumferential asymmetric mode according to actual flow field characteristics, so that the airflow flowing out of the volute body 1 passes through the circumferentially asymmetric nozzle ring, the speed and the flow direction of the airflow are more uniform in circumferential distribution, and the loss is lower when the airflow enters the turbine.
In addition, this application still discloses a circumference asymmetric nozzle ring, including spiral case main part and nozzle ring, wherein, the nozzle ring is the circumference asymmetric nozzle ring disclosed in above-mentioned embodiment.
Referring to fig. 1, the volute body 1 of the present application has a first volute tongue and a second volute tongue, and the position of the volute tongue has a large pressure fluctuation, so that the position of the outlet speed distribution of the volute body 1 is substantially located near the volute tongue, and in view of this, the first volute tongue is connected to the first vane 31 in an abutting manner, and the second volute tongue is connected to the second vane 32 in an abutting manner, and the inner flow channel of the volute body 1 can be divided into a first flow channel 41 and a second flow channel 42 by the arrangement of the first vane 31 and the second vane 32.
The first flow passage 41 and the second flow passage 42 are respectively located on two sides of a connecting line of the first blade 31 and the second blade 32. The first blade 31 abuts against the first volute tongue to form a sealed part, correspondingly, the second blade 32 abuts against the second volute tongue to form a sealed part, and the airflow entering the volute body 1 can flow in the first flow channel 41 and the second flow channel 42 respectively, so that collision loss of the airflow in the two flow channels can be effectively avoided.
In addition, the application also discloses a turbocharger with the volute, which comprises the volute, wherein the volute is disclosed in the embodiment, so that the turbocharger with the volute also has all the technical effects, and the details are not repeated herein.
Referring to FIG. 5, FIG. 5 is a flow chart of a blade angle optimization process. Specifically, the simulation process includes the following steps:
step S1: and inputting the items to obtain an original three-dimensional model of the nozzle ring.
Setting the blade angle A according to the item input i And inputting the three-dimensional model into design software to obtain an original version of the three-dimensional model of the nozzle ring.
The blades of the three-dimensional model of the original nozzle ring are uniformly arranged along the circumferential direction of the nozzle ring main body, and the included angle between the connecting line of the intersection point of the length direction of each blade and the width direction of each blade and the midpoint of the trailing edge of each blade and the vertical symmetrical axis of the nozzle ring main body is a blade angle A i Specifically, the blade angle of each blade is as follows: a. The i =A i-1 +360/N i =1,2,3 … … 7 … … N, where N is the number of blades and i is the serial number of blades arranged in the first direction.
It should be noted that the design software in this document may be a common three-dimensional software. The project input comprises the gas flow and gas pressure parameters and the like which are set into the three-dimensional model of the nozzle ring, and the part is the design scheme known in the prior art.
Step S2: and (5) CFD flow field simulation analysis.
And (3) carrying out flow field simulation analysis on the original nozzle ring model by CFD (Computational Fluid Dynamics, english abbreviation for Computational Fluid Dynamics) to determine whether the circumferential flow field distribution of the three-dimensional model of the original nozzle ring is uniform.
If the flow field distribution is not uniform, step S3 is executed.
And step S3: input b i The values optimize the vane angle of the nozzle ring.
Setting and inputting b into design software i Adjusting the blade angle of the nozzle ring blade according to the formula (1) by design software to obtain b i Three-dimensional model of nozzle ring with corresponding values, from CFD to b i And performing flow field simulation analysis on the three-dimensional model of the nozzle ring corresponding to the value, and performing iterative optimization according to the flow until the circumferential flow field of the three-dimensional model of the nozzle ring is uniformly distributed according to CFD flow field simulation.
Wherein, formula (1): a. The i =A i-1 +360/N+b i ，i=1，2，3……7……N；
Wherein, b i = b i-1 1,N is the number of blades, i is the number of blades arranged in the first direction, b i For the relative angle of rotation of two adjacent said blades, b i The value range of (A) is 4-6 degrees; a. The i And the included angle between the connecting line of the cross point of the length direction of the blade and the width direction of the blade and the midpoint of the tail edge of the blade and the vertical symmetrical axis of the nozzle ring main body is a blade angle.
And step S4: and the design software outputs a three-dimensional model of the nozzle ring.
And when the CFD flow field simulation determines that the circumferential flow field of the three-dimensional model of the nozzle ring is uniformly distributed, automatically storing and displaying the three-dimensional model of the nozzle ring and related data of the three-dimensional model of the nozzle ring by design software.
Can obtain required blade angle through above-mentioned optimization process in this application, guarantee that the blade that obtains can reduce the loss, reduce energy loss, guarantee turbocharger's efficiency.
This application is different through the contained angle that sets up the third blade as the tangent line of third blade and the inner edge of nozzle cascade main part, and the inclination of the air current angle adjustment third blade that flows according to actual spiral case makes the nozzle cascade loss lower, is favorable to improving turbo charger's efficiency.
As used in this disclosure and in the claims, the terms "a," "an," "the," and/or "the" are not intended to be inclusive in the singular, but rather are inclusive in the plural, unless the context clearly dictates otherwise. In general, the terms "comprises" and "comprising" merely indicate that steps and elements are included which are explicitly identified, that the steps and elements do not form an exclusive list, and that a method or apparatus may include other steps or elements. An element defined by the phrase "comprising a … …" does not exclude the presence of additional like elements in a process, method, article, or apparatus that comprises the element.
The embodiments in the present description are described in a progressive manner, each embodiment focuses on differences from other embodiments, and the same and similar parts among the embodiments are referred to each other.
The previous description of the disclosed embodiments is provided to enable any person skilled in the art to make or use the present invention. Various modifications to these embodiments will be readily apparent to those skilled in the art, and the generic principles defined herein may be applied to other embodiments without departing from the spirit or scope of the invention. Thus, the present invention is not intended to be limited to the embodiments shown herein but is to be accorded the widest scope consistent with the principles and novel features disclosed herein.
Claims (11)
1. A circumferentially asymmetric nozzle ring, comprising:
the nozzle ring body is used for being mounted on the volute body and is of a circular ring structure;
the vanes are distributed along the circumference of the nozzle ring body and comprise a first vane, a second vane and a third vane which are obliquely arranged along the same oblique direction, the first vane and the second vane are attached to the outer edge of the nozzle ring body, and the first vane and the second vane are respectively attached to one volute tongue of the volute body;
the third blades are distributed between the first blades and the second blades;
and included angles of all the third vanes and tangents of the inner edges of the nozzle ring main bodies are different.
2. The circumferentially asymmetric nozzle ring of claim 1, wherein the third vanes have a gap from an outer edge of the nozzle ring body, and the third vanes have a length that is less than the first vane length and less than the second vane length.
3. The circumferentially asymmetric nozzle ring of claim 1, wherein the first and second vanes are inclined at the same angle relative to the inner edge of the nozzle ring body, and the first and second vanes are arranged in central symmetry.
4. A circumferentially asymmetric nozzle ring as claimed in claim 1, wherein said third vanes are distributed on both sides of a line connecting said first vanes and said second vanes.
5. A circumferentially asymmetric nozzle ring as claimed in claim 4, wherein the angle between the line joining the intersection of the lengthwise direction of the vanes and the widthwise direction of the vanes and the midpoint of the trailing edge of the vanes and the axis of vertical symmetry of the nozzle ring body is vane angle A i And along the first direction of the nozzle ring main body, the blade angles of the blades are sequentially as follows:
A i =A i-1 +360/N+b i ，i=1，2，3……7……N；
b i = b i-1 -1，
wherein N is the number of the blades, i is the serial number of the blades arranged in the first direction, b i For the relative angle of rotation of two adjacent said blades, b i The value range of (A) is 4-6 degrees.
6. A circumferentially asymmetric nozzle ring as claimed in claim 4, wherein the angle between the line joining the intersection of the vane length and width and the midpoint of the vane trailing edge to the vertical axis of symmetry of the nozzle ring body is the vane angle A i When the vanes are uniformly distributed along the circumference of the nozzle ring main body, the vane angles of the vanes sequentially are as follows:
A i =A i-1 +360/N i=1，2，3……7……N，
wherein N is the number of the blades, and i is the serial number of the blades arranged in the first direction.
7. A circumferentially asymmetric nozzle ring as claimed in claim 5 or 6, wherein the included angle of the second vanes is an initial vane angle A in the first direction of the nozzle ring body 1 。
8. A volute comprising a volute body and a nozzle ring, wherein the nozzle ring is a circumferentially asymmetric nozzle ring as claimed in any one of claims 1 to 7.
9. The volute of claim 8, wherein the volute body has a first volute tongue against which the first vane is connected and a second volute tongue against which the second vane is connected;
the first vane and the second vane divide an inner flow passage of the volute main body into a first flow passage and a second flow passage, the first flow passage is located on one side of a connecting line of the first vane and the second vane, and the second flow passage is located on the other side of the connecting line of the first vane and the second vane.
10. A turbocharger comprising a volute, wherein the volute is as claimed in claim 8 or 9.
11. A method of designing a circumferentially asymmetric nozzle ring as defined in any one of claims 1 to 7, comprising:
setting the blade angle A according to the item input i Inputting the three-dimensional model into design software to obtain an original version of the three-dimensional model of the nozzle ring;
CFD carries out flow field simulation analysis on the original nozzle ring model to determine whether the circumferential flow field distribution of the three-dimensional model of the original nozzle ring is uniform;
if the flow field is not uniformly distributed, setting and inputting b into the design software i Adjusting the blade angle of the nozzle ring blade according to the formula (1) by the design software to obtain b i Three-dimensional model of nozzle ring with corresponding values, from CFD to b i Carrying out flow field simulation analysis on the three-dimensional model of the nozzle ring with the corresponding value until the circumferential flow field of the three-dimensional model of the nozzle ring is uniformly distributed according to CFD flow field simulation, and outputting the nozzle ring by the design softwareA three-dimensional model;
formula (1): a. The i =A i-1 +360/N+b i ，i=1，2，3……7……N；
Wherein, b i = b i-1 1,N is the number of blades, i is the number of blades arranged in the first direction, b i For the relative angle of rotation of two adjacent said blades, b i The value range of (A) is 4-6 degrees; a. The i The included angle between the connecting line of the intersection point of the length direction of the blade and the width direction of the blade and the midpoint of the trailing edge of the blade and the vertical symmetrical axis of the nozzle ring main body is a blade angle.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
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| DE4242494C1 (en) * | 1992-12-16 | 1993-09-09 | Mercedes-Benz Aktiengesellschaft, 70327 Stuttgart, De | Adjustable flow-guide for engine exhaust turbocharger - has axially-adjustable annular insert in sectors forming different kinds of guide grilles supplied simultaneously by spiral passages |
| JP2000045784A (en) * | 1998-07-29 | 2000-02-15 | Hitachi Ltd | Variable capacity type turbo supercharger |
| US20080104956A1 (en) * | 2006-10-31 | 2008-05-08 | Caterpillar Inc. | Turbocharger having inclined volutes |
| CN101915130A (en) * | 2010-06-25 | 2010-12-15 | 北京理工大学 | Three-dimensional nozzle ring vane of variable geometry turbocharger and design method thereof |
| CN102900479A (en) * | 2012-10-30 | 2013-01-30 | 北京理工大学 | Variable nozzle turbocharger regulating mechanism integrated on turbine shell |
| CN107061321A (en) * | 2017-03-15 | 2017-08-18 | 清华大学 | The compressor of variable asymmetric vaned diffuser is coupled using established angle and denseness |
| CN215292600U (en) * | 2019-11-13 | 2021-12-24 | 博格华纳公司 | Inlet channel system and blade ring |
| CN114341466A (en) * | 2019-07-09 | 2022-04-12 | 康明斯有限公司 | Turbine assembly for turbocharger |
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| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| DE4242494C1 (en) * | 1992-12-16 | 1993-09-09 | Mercedes-Benz Aktiengesellschaft, 70327 Stuttgart, De | Adjustable flow-guide for engine exhaust turbocharger - has axially-adjustable annular insert in sectors forming different kinds of guide grilles supplied simultaneously by spiral passages |
| JP2000045784A (en) * | 1998-07-29 | 2000-02-15 | Hitachi Ltd | Variable capacity type turbo supercharger |
| US20080104956A1 (en) * | 2006-10-31 | 2008-05-08 | Caterpillar Inc. | Turbocharger having inclined volutes |
| CN101915130A (en) * | 2010-06-25 | 2010-12-15 | 北京理工大学 | Three-dimensional nozzle ring vane of variable geometry turbocharger and design method thereof |
| CN102900479A (en) * | 2012-10-30 | 2013-01-30 | 北京理工大学 | Variable nozzle turbocharger regulating mechanism integrated on turbine shell |
| CN107061321A (en) * | 2017-03-15 | 2017-08-18 | 清华大学 | The compressor of variable asymmetric vaned diffuser is coupled using established angle and denseness |
| CN114341466A (en) * | 2019-07-09 | 2022-04-12 | 康明斯有限公司 | Turbine assembly for turbocharger |
| CN215292600U (en) * | 2019-11-13 | 2021-12-24 | 博格华纳公司 | Inlet channel system and blade ring |
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