CN117218285A - Three-dimensional geometric modeling method for vortex flow channel in turbine shell - Google Patents

Abstract

The application relates to a three-dimensional geometric modeling method of a vortex runner in a turbine shell. The method comprises the steps of firstly creating a first initial ring surface and a second initial ring surface which encircle a turbine hole, then using a scanning modeling function of generating three-dimensional geometry by guiding a single variable-shape section to move in space by an arc track line, creating a volute surface which is in contact with the first initial ring surface and the second initial ring surface, finally removing redundant parts outside a contact line between the first initial ring surface and the second initial ring surface and the volute surface, and then obtaining the first ring surface and the second ring surface after the redundant parts are removed, and then forming a three-dimensional geometric model of a vortex runner together with the volute surface. The modeling type form of the method disclosed by the application has the advantages of smooth and untwisted shape, accurate and controlled shape, simplicity and rapidness in modification, stability and difficulty in failure. The application can also be used for modeling of volute runners or shaped surfaces of compressor shell runners, other fluid machinery such as water pumps, water turbines, fans, compressors and the like, and volute runners or shaped surfaces of general machinery, equipment, tool clamping molds and the like.

Description

Three-dimensional geometric modeling method for vortex flow channel in turbine shell

Technical Field

The application belongs to the technical field of centrifugal impeller machinery and fluid machinery, in particular to a three-dimensional geometric modeling method of a vortex runner in a turbine shell of a turbocharger, and is not limited to the method, in particular to a modeling method for creating a three-dimensional geometric model of the vortex runner by using a rotation modeling function and a scanning modeling function of computer software. The application can also be used for three-dimensional geometric modeling of scroll-shaped flow passages or shaped surfaces of compressor shell flow passages of turbochargers, volute flow passages of other fluid machinery such as water pumps, water turbines, fans, compressors and the like, and general machinery, equipment, work clamps, molds and the like.

Background

As is well known, a vortex flow passage in a turbine shell (or turbine box) of the turbocharger is responsible for guiding and distributing high-temperature waste gas to blow a turbine, driving a compressor impeller to rotate at a high speed, sucking and compressing fresh air, and greatly improving the pressure, density and quality of intake air, so that the power and torque of an internal combustion engine are improved, the fuel consumption and the emission of harmful pollutants are reduced, and the shape of the vortex flow passage has a great influence on the performance and reliability of the turbocharger; the spiral case of the water pump, the water turbine, the fan and the compressor needs to guide the flow of liquid or gas, and the performance indexes such as flow resistance, working efficiency and the like can be influenced. Along with development and application of three-dimensional CAD technology, a turbine shell, a volute and a vortex runner thereof are generally designed and modeled by using computer three-dimensional modeling software so as to truly and vividly express the space shape of complex bending, and currently, commonly used three-dimensional software comprises Creo, pro/E, UG, catia, solidWorks, MDT and the like, and Pro/E is an early software version of Creo.

Chinese patent CN 109711045B discloses a method for shaping the volute of centrifugal pump in a fairing, which comprises drawing two-dimensional sketches of multiple sections of the volute in UG software, and connecting the sections to generate three-dimensional curved surfaces of spiral parts of the volute by using a grid curved surface tool passing through a curve grid. The tool is the modeling function of software, which is also called modeling characteristic, and the spiral part is also called vortex runner part.

Chinese patent CN 102034014B discloses a method for establishing a three-dimensional model of a hydropower station mixed-flow hydraulic turbine volute by full parameters, wherein all volute sections are obtained first, and then the surfaces of the volute are obtained by stretching each volute section and a control guide line thereof. Stretching is understood herein to mean mixed forming.

In the text of "three-dimensional model design of centrifugal Pump volute based on CATIA" by "Huangmycin et al, a method for modeling a volute by adopting a layering function of Catia software is proposed, wherein the layering function needs to specify a plurality of section outlines, the layering function is called a multi-section curved surface in a software interface, and the section is called a section in the software.

Yue Jian, et al, in the study of Pro/E-based centrifugal Pump impeller and volute entity modeling, propose a method for volute modeling using a scanning mixing tool of Pro/E software, where the scanning mixing entails drawing multiple section profiles, the sections being referred to as sections in the software.

Zhao Qingsong et al, in the description of three-dimensional model design of centrifugal volute based on Pro/E, propose a method for modeling volute by adopting the characteristics of hybrid scanning and boundary scanning of Pro/E software, wherein the hybrid scanning needs to draw a plurality of section graphs, and a plurality of sections of circular arcs are designated as the tracks of the hybrid scanning. The hybrid scan referred to herein shall refer to a scan blend of software, the boundary scan shall refer to a boundary blend, the feature shall refer to a feature, and the boundary blend also requires specification of a plurality of boundary lines corresponding to cross sections.

Ma et al, in the text of the study of the influence of three-dimensional solid modeling method on CFD calculation, propose a method for modeling a volute using hybrid scanning and boundary hybrid features of Pro/E software, where the hybrid scanning requires at least two or more cross-sectional patterns, and specifies a base circle of the volute as a track of the hybrid scanning. The term hybrid scan herein shall refer to a scan blend of software.

Li Zaiyong, creo-based centrifugal pump volute flow passage curved surface modeling method, discloses a method for performing volute modeling by adopting Creo software for scanning mixing and boundary mixing, wherein the scanning mixing is required to draw a plurality of section outlines, and the boundary mixing is required to specify a plurality of boundary lines.

Li Shenjian et al, solid design and research of centrifugal pump based on UG, propose a method for modeling a volute by using the sweep function of UG software, and the sweep uses a plurality of section profiles, and the section is called a section in the software. It should be noted that the modeling functions of the UG software that use only a single section to move along a trajectory are: constant cross-section sweep along a guide line, and variable cross-section sweep; the sweep shaping function generally uses multiple sections, and can also specify only a single section, which sweeps essentially the same section at both ends of the guide wire, so the section shape along the guide wire remains constant.

Gu Ningning et al, in the text, "parametric design method for rotory pumps", propose a method for volute modeling using the lofting features of the SolidWorks software, where lofting entails drawing multiple section sketches.

Liu Jianguo, et al, in the description of three-dimensional modeling study and implementation of centrifugal pump volute based on MDT, propose a method for modeling a volute by using the lofting feature of MDT software, and the lofting must draw a plurality of section profiles.

The software modeling function used by the modeling method is different in name, but the core idea is that a plurality of fixed runner forming sections are established along the circumferential direction of a turbine hole of a turbine shell, and then are connected one by one to be formed in a mixed mode, each forming section is required to draw a primitive chain which surrounds one circle of the section, namely, drawing elements of the same section correspond to a first ring surface, a second ring surface and a volute surface of a vortex runner respectively. Generally, at least 9 sections are arranged along the circumference of the turbine hole, and adjacent sections are arranged at intervals of about 45 degrees, even 15-30 degrees.

For different flow channel forming sections with larger angles along the circumference of the turbine hole, the shape distortion is often generated even though the whole vortex flow channel is barely created because the cross section shape and the form of the cross section primitive chain, such as primitive number, primitive type and the like, can be changed, so that the complete vortex flow channel surface cannot be generally created by using one mixed forming characteristic; and the complete runner is formed by connecting a plurality of mixing forming characteristics, so that the number of curved surfaces formed by the runners is increased, and the connection between the runner surfaces of each section is difficult to smooth.

For the mixed forming method, although the shape of each runner forming section is accurate, the runner shape between each runner forming section is not directly controlled and is not accurate enough; the interval angle between adjacent forming sections is reduced, the number of forming sections is increased, and the fluctuation and the distortion of the surface are easily caused.

If the formed cross-section is not properly sized, even if only one cross-section is wrong, the mixed formed channel surface can generate curvature fluctuation, shape distortion and no smoothness, and even cause three-dimensional software reproduction failure.

If the shape of the runner is adjusted to adapt to different performance indexes, the profile of each formed section needs to be modified so as to ensure the overall consistency and the smoothness of the runner surface, and the operation is troublesome.

The modeling quality of the vortex flow channel surface can also influence the successful development of the subsequent CAE/CAM work, so that the finite element grid is abnormal or numerical control program codes cannot be generated.

Disclosure of Invention

The application aims to provide a three-dimensional geometric modeling method of a vortex runner in a turbine shell, which is suitable for centrifugal impeller machinery or fluid machinery, in particular to a turbine shell vortex runner of a turbocharger, and can solve the problems that the number of component curved surfaces is too large, the shape is unsmooth due to curvature fluctuation and easy distortion, the shape is not precisely controlled, the creation and modification process is troublesome and time-consuming, the adjustment is inconvenient, the model is easy to regenerate and fails and the like in a vortex runner model built by the existing modeling method.

According to the technical scheme provided by the application: a three-dimensional geometric modeling method of a vortex flow channel in a turbine shell is characterized in that a turbine hole is arranged in the middle of the turbine shell, a cavity of the vortex flow channel surrounds the turbine hole in the turbine shell and is communicated with the turbine hole, the wall surface of a single vortex flow channel comprises a first annular surface and a second annular surface which face each other along the axial direction of the turbine hole and are connected with the wall surface of the turbine hole, and a volute surface which is connected with the first annular surface and the second annular surface from the outer side of the first annular surface and gradually contracts from the outer side to the inner side along the circumferential direction of the turbine hole, a three-dimensional geometric model of the vortex flow channel is created in computer software, the three-dimensional geometric model comprises an arc line with a plane vertical to the axis of the turbine hole, the circle center of the arc line is positioned on the axis of the turbine hole, the arc angle of the arc line corresponds to the circumferential range occupied by the volute surface, A first initial ring surface and a second initial ring surface which encircle a turbine hole are firstly created, then a single forming section is guided by a designated track line to move in space by using a scanning modeling function of computer software to generate three-dimensional geometry, a volute surface which is contacted with the first initial ring surface and the second initial ring surface is created, the circular arc line is designated as the track line of the scanning modeling by the scanning modeling function, a cross-section primitive drawn in the forming section of the scanning modeling function correspondingly generates the volute surface, the forming section is set to be variable in drawing shape of the forming section when the scanning modeling is carried out along the track line, and the first ring surface, the second ring surface, the first ring surface, the second ring surface and the volute surface form a three-dimensional geometric model of a vortex runner together after the part outside the contact line between the first initial ring surface and the second initial ring surface and the volute surface is cut off.

In one embodiment of the application, the first initial annulus and the second initial annulus are created using a rotational modeling function of computer software, the rotational centerline of the rotational modeling function coinciding with the turbine bore axis.

In one embodiment of the application, in a primitive chain formed by connecting the primitive cross sections drawn by the forming section of the computer software modeling function for creating the first initial torus and the second initial torus, the primitive cross sections which can always contact the volute surface around the turbine hole are only one smooth first independent primitive and the other smooth second independent primitive respectively,

in one embodiment of the application, in the forming section of the scroll surface scanning modeling function, two end points of the drawn section primitive chain are respectively restrained on the first initial ring surface and the second initial ring surface, the outermost point position of the drawn section primitive chain marks the size of the vortex diameter with the axis of the turbine hole, the size of the vortex diameter is controlled by a function formula, and the value of the vortex diameter is gradually changed during the orbital line scanning modeling.

In one embodiment of the present application, the first initial torus and the second initial torus are created using a scan modeling function, the scan modeling function designates the circular arc line as a trajectory line of the scan modeling, a plane of a shaped section of the scan modeling function along the trajectory line where the section is located is perpendicular to the circular arc line, and the shaped section is set to be constant in shape of the section when the scan modeling is performed.

In one embodiment of the application, in a chain of cross-sectional primitives drawn by a shaped cross-section of a computer software modeling function that creates a first initial torus and a second initial torus, a plurality of connected primitives are converted into individual sample strip primitives, and the cross-sectional primitives that are always in contact with the scroll face around the turbine bore are only the sample strip primitives.

In one embodiment of the application, in a forming section of a scanning modeling function for creating a scroll surface, a drawing section primitive chain comprises a primitive number ranging from one to a plurality, a radius value of a circular arc primitive in the drawing section primitive chain is controlled by a function formula, and the radius value gradually changes when the modeling is scanned along an orbit line.

In one embodiment of the application, a turbine housing has first and second scroll runners therein, each including respective first, second and scroll faces.

In one embodiment of the application, the function of creating the scan pattern of the scroll face also designates a curve gradually shrinking inwards along the circumferential direction of the turbine hole as another track line of the scan pattern, the shaped section of the scan pattern function is perpendicular to the arc line along the track line when the section plane is in the scan pattern, and the position of the outermost point of the drawn section primitive chain is aligned with the intersection point of the curve and the section plane along the axial direction of the turbine hole.

The application has the positive progress effects that:

in the three-dimensional geometric model of the vortex flow channel built by the modeling method, the modeling forming sections of the first annular surface and the second annular surface are only drawn to be used for contacting the vortex surface, so that the first annular surface and the second annular surface only comprise a single curved surface to be connected with the vortex surface, and the vortex surface is created by a single scanning modeling function, and the vortex surface is also the same curved surface along the circumferential direction, so that the total number of the component curved surfaces of the vortex flow channel is less, and the fairing is easier to realize; the curvature distribution of the scroll surface along the circumferential direction only depends on a scroll diameter size function formula or a corresponding scanning modeling track curve, and obviously, compared with the multiple shaping sections of the existing mixed modeling method, one track curve is easier to adjust the fairing; the forming principle of rotary modeling and scanning modeling determines that the cross section shape of any flow passage of the vortex flow passage along the circumferential direction of the turbine hole is accurately and directly controlled, and the shape of each part is not distorted and is smoother; the shape of the runner can be modified by editing the modeling forming sections of the first initial ring surface, the second initial ring surface and the volute surface which are only equivalent to a single mixing forming section and a vortex diameter formula or a corresponding track curve, so that the change rule of the circumferential sectional area and the surface diameter ratio of the required runner is realized, the adjustment operation is more accurate, simple, convenient and quick, and the model regeneration failure is not easy to cause.

The vortex runner model created by the modeling method has the advantages of small quantity of curved surfaces, small curvature fluctuation, no distortion and smooth morphology; the cross-sectional shape of any flow passage along the circumference of the turbine hole is accurately controlled; the modification and adjustment are convenient and quick, and the model is not easy to fail in regeneration. The application can also be used in the shaping of scroll-shaped flow passages or profiles of compressor housing flow passages of turbochargers, scroll-shaped flow passages of other fluid machinery such as water pumps, water turbines, fans, compressors, and general machinery, equipment, jigs, molds, etc.

Drawings

FIG. 1 is a schematic illustration of the shape of a turbine shell and extracted vortex flow path of the present application.

FIG. 2 is a schematic illustration of the shape of the turbine shell of the present application taken along the axis of the turbine bore.

Fig. 3 is an isometric and axial view of the vortex flow channel of the present application.

Fig. 4 is a cross-sectional view of a scroll flow passage of the present application.

FIG. 5 is a schematic cross-sectional view of the formation of the rotational and scanning contouring function of the present application to create a scroll runner contoured surface.

FIG. 6 is a schematic representation of a multi-primitive transition single-sample-bar primitive and double-vortex flow path in a shaped cross-section in accordance with the present application.

FIG. 7 is a schematic diagram showing the comparison of the model appearance of the scan modeling method of the present application and the prior art hybrid modeling method.

FIG. 8 is a graph showing the comparison of model curvatures of the scan modeling method of the present application and the conventional hybrid modeling method.

Fig. 9 is an external detail view of a swirl flow channel model of a conventional mixing modeling method.

FIG. 10 is a schematic illustration of the shape of the opposing double vortex flow channels created by the scan modeling method of the present application.

Detailed Description

It should be noted that, without conflict, the embodiments of the present application and features of the embodiments may be combined with each other. The application will be described in detail below with reference to the drawings in connection with embodiments.

In order that those skilled in the art will better understand the present application, a technical solution in the embodiments of the present application will be clearly and completely described below with reference to the accompanying drawings in the embodiments of the present application, and it is apparent that the described embodiments are only some embodiments of the present application, not all embodiments. All other embodiments, which can be made by those skilled in the art based on the embodiments of the present application without making any inventive effort, shall fall within the scope of the present application.

It should be noted that the terms "first," "second," and the like in the description and the claims of the present application and the above figures are used for distinguishing between similar objects and not necessarily for describing a particular sequential or chronological order. It is to be understood that the data so used may be interchanged where appropriate in order to describe the embodiments of the application herein. Furthermore, the terms "include" and "have," and the like, mean that other content not already listed may be "included" and "provided" in addition to those already listed in "include" and "provided; for example, a process, method, system, article, or apparatus that comprises a list of steps or elements is not necessarily limited to those steps or elements not expressly listed but may include other steps or elements not expressly listed or inherent to such process, method, article, or apparatus.

As shown in fig. 1 to 4, a turbine hole 3 is provided in the middle of the turbine housing 1, a cavity of the scroll flow passage 2 surrounds the turbine hole 3 inside the turbine housing 1 and is connected with the turbine hole 3, a wall surface of the single scroll flow passage 2 comprises a first annular surface 4 and a second annular surface 5 which are axially opposite along the turbine hole 3 and are connected with the wall surface of the turbine hole 3, and a scroll surface 6 which is connected with the first annular surface 4 and the second annular surface 5 from the outer side of the first annular surface 4 and the second annular surface 5 and gradually contracts from outside to inside along the circumferential direction of the turbine hole 3.

The application relates to a three-dimensional geometric modeling method of a vortex runner in a turbine shell, which is used for creating a three-dimensional geometric model for generating the vortex runner 2 in computer software.

Taking Creo software as an example:

the modeling function of the Creo software is called as a feature in the software, and firstly, necessary basic features are created, including some features such as a reference plane, a reference shaft and the like, wherein one reference shaft represents the axis of the turbine hole 3, one reference plane perpendicular to the axis of the turbine hole 3 represents the symmetrical plane of a runner between the first annular surface 4 and the second annular surface 5, and one reference plane passing through the axis of the turbine hole represents the vortex starting plane; the symmetrical plane of the flow channel is used as a sketch plane, a circular arc line 7 is created by using sketch characteristics, the circle center of the circular arc line 7 is positioned on the axis of the turbine hole 3, the circular arc angle corresponds to the circumferential range occupied by the scroll surface 6, and one end of the circular arc line 7 falls on the scroll initial plane; for clarity of illustration, the arc 7 shown in fig. 3 is spaced from the plane of symmetry of the flow channel.

As shown in fig. 4 and fig. 5, the reference plane of the vortex starting plane or other turbine passing hole axis is taken as a sketch plane, a rotation feature is used for creating the first initial annular surface 11 and the second initial annular surface 12, the rotation feature sketch, namely, the forming section of the rotation modeling function, the rotation center line of the rotation feature coincides with the axis of the turbine hole 3, the forming section of the first initial annular surface 11 and the forming section of the second initial annular surface 12 respectively comprises two and one graphic element, two surfaces and one surface are correspondingly generated, wherein the graphic element of the section to be contacted with the vortex surface 6 is respectively a smooth first individual graphic element 9 and another smooth second individual graphic element 10, the first individual graphic element 9 and the second individual graphic element 10 are illustrated as straight line segments, that is, the occupation range of the first individual graphic element 9 and the second individual graphic element 10 along the radial direction of the turbine hole 3 is beyond the occupation range of the connecting edges of the vortex surface 6 and the first annular surface 4 and the second annular surface 5; the graphic element chain is a branched line chain formed by drawing a plurality of graphic elements in a two-dimensional section sketch or section sketch in series end to end, and the number of the graphic elements contained in the graphic element chain can be from one to a plurality of graphic elements, and the graphic elements are abbreviated as graphic elements; the first initial torus 11 and the second initial torus 12 are created by the same rotation characteristics, or can be integrated after being created by different rotation characteristics; the first initial torus 11 and the second initial torus 12 are created as "face set" geometries, which are also known differently in each three-dimensional modeling software, and as solid geometries, which represent surfaces with shape, area, but without volume and mass.

Creating scanning characteristics in software, and drawing a single scanning section except for a specified scanning track line; as shown in fig. 3 and 5, after the first initial annulus 11 and the second initial annulus 12 are created, the scroll surface 6 in contact with the first initial annulus 11 and the second initial annulus 12 is created using scan modeling in which the cross-sectional shape is set to be variable scan characteristics; the scanning characteristic designates the arc line 7 as an origin trajectory line of scanning, and a sketch plane of a section is perpendicular to the origin trajectory line when the section is shaped along the trajectory line scanning; the drawing element chain of the section comprises an arc-shaped element, and two end points 13 and 14 of the element chain are respectively restrained on the first initial ring surface 11 and the second initial ring surface 12 and are tangent to the first initial ring surface 11 and the second initial ring surface 12, and the restraint is realized by adopting a proper mode to establish sketch reference elements corresponding to the first initial ring surface 11 and the second initial ring surface 12 in the scanning section; the position of the outermost point 15 of the primitive chain is marked with the vortex diameter size of the axis of the turbine hole 3, the vortex diameter size is controlled by a function formula input in a sketch relation dialog box, the vortex diameter size value gradually changes during the orbital trace scanning modeling, and the change rule of the circumferential sectional area or the surface diameter ratio of the vortex flow channel, namely the A/R, is reflected; the scroll face 6 is also created as a face group or entity, depending on the geometry created by the first initial annulus 11 and the second initial annulus 12.

Finally, by using the merging feature, after the respective redundant parts of the first initial annular surface 11, the second initial annular surface 12 and the scroll surface 6 are automatically cut off along the contact lines of the two initial annular surfaces, the two initial annular surfaces are combined into a single surface group geometry which represents the shape surface of the scroll runner 2, the first initial annular surface 11 becomes the first annular surface 4 after the redundant parts are cut off, and the second initial annular surface 12 becomes the second annular surface 5 after the redundant parts are cut off; when the first initial torus 11 and the second initial torus 12 are created as solid geometry, the scanning feature of creating the scroll face 6 is set to "scan as solid" and "remove material", thereby making the generated scroll face 6 directly belong to solid geometry; and after the shape surface of the inlet channel is established to connect the turbine shell inlet and the vortex flow channel, the three-dimensional geometric model of the vortex flow channel can be used for establishing a complete turbine shell three-dimensional geometric model and carrying out subsequent CAE simulation analysis and mould CAM numerical control programming.

FIG. 7 is a schematic diagram showing the comparison of the appearance of a scroll flow channel model using a scan molding method according to the present application and a conventional scroll flow channel model using a hybrid molding method, FIG. 8 is a schematic diagram showing the comparison of the curvature distribution of the outer peripheral profiles of the scroll flow channel model constructed by the two molding methods, the left part of FIG. 7 and FIG. 8 is a hybrid molding method using 18 molding sections, and the right part is a scan molding method according to the present application; fig. 9 is a detailed view i of the conventional mixed modeling swirl flow channel model in fig. 7, after the enlargement, it can be found that the intersection line 21 of the flow channel surface, which should be smooth in shape, has protrusions and folds, and it is obvious that there is serious local distortion of the flow channel surface, which can cause that the finite element mesh cannot be divided and the numerical control program cannot be generated. Compared with the prior art, the modeling method has the advantages that the number of the formed curved surfaces of the model built by the modeling method is smaller, the shape is smoother, no distortion exists, the section control is more accurate, and the adjustment is simpler, more convenient and faster.

In order to create a first or second initial torus of complex cross-sectional profile, as shown in fig. 6, for a number of connected primitives in the chain of cross-sectional primitives to be contacted by the scroll face, they are converted into individual sample bar primitives 17, the curvature profile inside the sample bar primitives 17 should seek to avoid excessive steps, oscillations and changes in direction to ensure successful scan shaping.

To create a volute surface with a complex cross-sectional profile, as shown in fig. 6, the cross-sectional primitive chain of the volute surface corresponding to the scan feature includes a plurality of connected primitives, wherein the radius value of the circular arc primitive 18 in contact with the first initial torus or the second initial torus is controlled by a functional formula, the radius value gradually changes when the model is scanned along the trajectory, and the plurality of connected primitives can also be converted into individual sample strip primitives.

In order to fully utilize the exhaust pulse energy of the engine, as shown in fig. 6, two scroll passages, namely a first scroll passage 19 and a second scroll passage 20, are provided in the turbine housing in parallel and facing each other in the axial direction of the turbine hole, and each of the two scroll passages includes a first annular surface, a second annular surface, and a scroll surface. As shown in fig. 10, the double scroll flow passage may be arranged opposite the turbine bore axis.

In order to create a volute with a circumferential extent of 360 deg., two end-to-end series scanning features are used, with the arc trajectories used for the two scanning features taking up an arc angle of 360 deg..

Instead of creating the rotation characteristics of the first initial torus 11 and the second initial torus 12, the first initial torus 11 and the second initial torus 12 are created by using the scan characteristics with the cross-sectional shape set to be constant during the scan modeling, the scan characteristics designate the circular arc line 7 as the origin trajectory line of the scan modeling, the sketch plane of the cross-section during the cross-sectional along trajectory scan modeling is perpendicular to the origin trajectory line, and in the drawing element chain, the elements to be contacted with the scroll surface 6 are respectively a smooth first single element and another smooth second single element, and the effects of the rotation characteristics and the scan characteristics for creating the first initial torus and the second initial torus are basically the same.

Instead of marking the size of the vortex path between the position of the outermost point 15 of the primitive chain and the axis of the turbine hole 3 in the scanning characteristic section for creating the vortex surface, as shown in fig. 3, a curve 8 which gradually contracts towards the center in a vortex shape along the circumferential direction of the turbine hole 3 is drawn on the symmetrical plane of the flow passage by using a sketch characteristic or other curve creation characteristics, and the starting and stopping angle positions of the curve 8 and the circular arc line 7 along the circumferential direction of the turbine hole are kept the same; for clarity of presentation, curve 8 shown in fig. 3 is a distance from the plane of symmetry of the flow channel; creating the scan profile of the scroll face 6 also designates the curve 8 as a second trajectory line of the scan profile, as shown in fig. 5, where in the cross-section of the scan profile the outermost point 15 of the chain of primitives is positioned in axial alignment along the turbine bore 3 with the intersection point 16 of said second trajectory line and the sketched plane of the cross-section, this alignment being achieved by making the drawn circular-arc primitives tangential to the auxiliary line elements passing through the intersection point 16 and parallel to the axis of the turbine bore 3.

Instead of assigning the circular arc line 7 and the curve line 8 to the origin trajectory line and the second trajectory line in the scan feature for creating the scroll surface, respectively, assigning the curve line 8 as the origin trajectory line, assigning the circular arc line 7 as the second trajectory line, and the sketch plane of the cross section when the cross section is shaped along the trajectory line scan is perpendicular to the second trajectory line, and the outermost point position of the primitive chain is aligned with the intersection point of the origin trajectory line and the sketch plane of the cross section along the axial direction of the turbine hole 3.

Instead of creating a scan feature trajectory specification curve 8 for the scroll face, the trajectory specifies the outer edge of a scan feature-built face set geometry for a specially constructed trajectory; the scanning characteristic of the special construction trace line is that the cross section shape is variable when the trace line is set to be scanned and the circular arc line 7 is designated as the original trace line, the scanning cross section graphic element chain comprises a straight line segment graphic element, the outer end point of the straight line segment is marked with the vortex diameter size with the axis of the turbine hole 3, the vortex diameter size is controlled by a function formula, and the vortex diameter size value is gradually changed when the trace line is scanned and molded.

Instead of assigning circular arcs 7 to the trace of the scanning feature, the trace is assigned as a chain of multiple segments of concentric, equal-radius and end-to-end series arc lines; the trajectory line can also be designated as a spline line which has equal curvature along the circumference of the turbine hole or has small curvature fluctuation so as to be close to the equal curvature; the track line can also be designated as a linear chain formed by connecting multiple sections of curves in series, and the composition curve of the linear chain can be a spline or an arc, so long as the linear chain presents equal curvature or nearly equal curvature along the circumferential direction of the turbine hole.

Instead of assigning a circular arc 7 to the trajectory of the scanning feature, the trajectory is assigned as an arc edge belonging to the geometry of the other surface, the plane of the arc edge is perpendicular to the axis of the turbine hole 3, the center of the arc edge is located on the axis of the turbine hole 3, and the arc angle of the arc edge corresponds to the circumferential range occupied by the scroll surface 6.

Instead of constraining the two end points 13, 14 of the primitive chain on the first initial torus 11 and the second initial torus 12, respectively, in the scan feature cross section for creating the scroll face, the primitive chain is in contact with the first initial torus 11 and the second initial torus 12, respectively, but the end points of the primitive chain are disconnected, i.e. not constrained to the first initial torus 11 and the second initial torus 12, and when the merging of the first initial torus 11, the second initial torus 12 and the scroll face is performed, the software automatically tailors the redundant parts of the scroll face, the first initial torus 11 and the second initial torus 12 along the contact lines.

The vortex runner three-dimensional geometric modeling method can be applied to the historical version of Creo software as well: pro/E and Pro/E Wildfire, as well as other computer three-dimensional modeling software, three-dimensional tooling programming software, and modeling modules of three-dimensional mold design software, or historical versions thereof, including, but not limited to, UG NX, catia, solidWorks, MDT, inventor, solidEdge, I-DEAS, spaceClaim, thinkDesign, hope 3D, CAXA, powerShape, powerMill, visi, cimatron, mastercam, and the like, for example.

The designations of the same concept in different software may not be consistent, for example: the "sketch" in the Creo software is called "sketch" in UG, catia, solidWorks;

"face groups" are referred to as "sheets" in UG, as "curved surfaces" in Catia, and as "curved surface entities" in SolidWorks;

the "rotation" feature is referred to in UG as a "revolution" feature, in Catia as a "rotator" feature that creates an entity, a "rotation slot" feature that creates an entity ablation, a "rotation" feature that creates a set of facets, in SolidWorks as a "rotation" feature that creates an entity, a "ablation-rotation" feature that creates an entity ablation, a "curved-rotation" feature that creates a set of facets;

the variable cross-section "scan" feature is called a "change sweep" feature in UG, a "sweep" feature and an "adaptive sweep" feature in Catia, a "scan" feature that creates a solid, a "cut-scan" feature that creates a solid cut, a "curved-scan" feature that creates a set of facets, and the variable cross-section "scan" feature can of course also be a geometric shape with constant cross-section;

the constant cross-section "scan" feature is referred to in UG as "sweep along guide line" feature, in Catia as "rib" feature to create entity, "slot" feature to create entity ablation, in SolidWorks as "scan" feature to create entity, "ablation-scan" feature to create entity ablation, and "surface-scan" feature to create surface set;

the cross-section of a "scan" feature is referred to as a "cross-section" in UG, a "contour" or "sketch" in Catia, and a "contour" in SolidWorks;

the scan-mix feature is called a "sweep" feature in UG, a "multi-section entity" feature that creates an entity, a "removed multi-section entity" feature that creates an entity-cut, a "multi-section curved surface" feature that creates a set of faces, and requires a specified ridge line, a "loft" feature that creates an entity, a "cut-loft" feature that creates an entity-cut, a "curved surface-loft" feature that creates a set of faces in SolidWorks;

the cross-section of the "scan-mixed" feature is called "cross-section" in UG, "cross-section" in Catia, and "profile" in SolidWorks;

the trajectory of a "scan" or "scan mix" feature is referred to as a "path," "guide line," or "ridge line" in UG, a "center curve," "guide line," or "ridge line" in Catia, and a "path," "center line," or "guide line" in SolidWorks;

the boundary mixing feature is called as a grid curved surface feature in UG, is subdivided into a curve group, a curve grid and other features, is called as a multi-section curved surface feature in Catia, is called as a boundary feature for creating an entity, a boundary-cutting feature for creating entity cutting, and a boundary-curved surface feature for creating a surface group in SolidWorks;

the "merge" feature is referred to as a "stitch" feature in UG, a "join" feature in Catia, and a "stitch curved" feature in SolidWorks;

some software integrates multi-section mixed shaping and single-section scanning shaping into a large geometric modeling function, such as the sweep feature of the ICEM module of Catia software, which has both multi-section and single-section modeling sub-functions, and of course, the two sub-functions can only be selected and cannot be implemented simultaneously.

The three-dimensional geometric modeling method of the vortex runner can also be applied to Matlab and other mathematical software, and the three-dimensional geometric model of the vortex runner is created by programming in the mathematical software.

As an expanding application of the modeling method of the application, the modeling method of the application can be applied to three-dimensional geometric modeling of a compressor shell runner of a turbocharger, a volute runner of other fluid machinery such as a water pump, a water turbine, a fan, a compressor, a turbine pump and the like, and a scroll-shaped flow passage or a shape surface of general machinery, equipment, a fixture, a mold and the like, so as to obtain a smoother runner curved surface, better model quality and simplify a modeling process.

It will be appreciated by those skilled in the art that embodiments of the present application may be provided as a method, system, or computer program product. Accordingly, the present application may take the form of an entirely hardware embodiment, an entirely software embodiment or an embodiment combining software and hardware aspects. Furthermore, the present application may take the form of a computer program product embodied on one or more computer-usable storage media (including, but not limited to, disk storage, CD-ROM, optical storage, and the like) having computer-usable program code embodied therein.

The present application is described with reference to flowchart illustrations and/or block diagrams of methods, apparatus (systems) and computer program products according to embodiments of the application. It will be understood that each flow and/or block of the flowchart illustrations and/or block diagrams, and combinations of flows and/or blocks in the flowchart illustrations and/or block diagrams, can be implemented by computer program instructions. These computer program instructions may be provided to a processor of a general purpose computer, special purpose computer, embedded processor, or other programmable data processing apparatus to produce a machine, such that the instructions, which execute via the processor of the computer or other programmable data processing apparatus, create means for implementing the functions specified in the flowchart flow or flows and/or block diagram block or blocks.

These computer program instructions may also be stored in a computer-readable memory that can direct a computer or other programmable data processing apparatus to function in a particular manner, such that the instructions stored in the computer-readable memory produce an article of manufacture including instruction means which implement the function specified in the flowchart flow or flows and/or block diagram block or blocks.

These computer program instructions may also be loaded onto a computer or other programmable data processing apparatus to cause a series of operational steps to be performed on the computer or other programmable apparatus to produce a computer implemented process such that the instructions which execute on the computer or other programmable apparatus provide steps for implementing the functions specified in the flowchart flow or flows and/or block diagram block or blocks.

It is apparent that the above examples are given by way of illustration only and are not limiting of the embodiments. Other variations and modifications of the present application will be apparent to those of ordinary skill in the art in light of the foregoing description. It is not necessary here nor is it exhaustive of all embodiments. And obvious variations or modifications thereof are contemplated as falling within the scope of the present application.

Finally, it should be noted that the above-mentioned embodiments are only for illustrating the technical solution of the present application, and not for limiting the same, and although the present application has been described in detail with reference to examples, it should be understood by those skilled in the art that modifications and equivalents may be made to the technical solution of the present application without departing from the spirit and scope of the technical solution of the present application, and all such modifications and equivalents are intended to be encompassed in the scope of the claims of the present application.

Claims (9)

1. A three-dimensional geometry method of a scroll runner inside a turbine shell, a turbine hole (3) is arranged in the middle of the turbine shell (1), a cavity of the scroll runner (2) surrounds the turbine hole (3) inside the turbine shell (1) and is communicated with the turbine hole (3), a wall surface of a single scroll runner (2) comprises a first annular surface (4) and a second annular surface (5) which face each other along the axial direction of the turbine hole (3) and are connected with the wall surface of the turbine hole (3), a scroll surface (6) which is connected with the first annular surface (4) and the second annular surface (5) from the outer side of the first annular surface (4) and gradually contracts from outside to inside along the circumferential direction of the turbine hole (3), a three-dimensional geometry model of the scroll runner (2) is created in computer software, the three-dimensional geometry model comprises an arc line (7) which is positioned on a plane and perpendicular to the axis of the turbine hole (3), the circle center of the arc line (7) is positioned on the axis of the turbine hole (3), and the arc angle of the line (7) corresponds to the circumferential range occupied by the scroll surface (6), and the three-dimensional geometry method is characterized in that: the method comprises the following steps:

in the modeling process of computer software, a first initial annular surface (11) and a second initial annular surface (12) which encircle a turbine hole (3) are firstly created, then a scanning modeling function of the computer software is used, wherein a single shaping section is guided by a designated track line to move in space to generate three-dimensional geometry, a volute surface (6) which is contacted with the first initial annular surface (11) and the second initial annular surface (12) is created, the circular arc line (7) is designated as the track line of the scanning modeling by the scanning modeling function, a scroll surface (6) is correspondingly generated by a section graphic element drawn in the shaping section of the scanning modeling function, the drawing shape of the shaping section is variable when the shaping section is set along the track line scanning modeling, and the three-dimensional geometry model of the vortex runner (2) is obtained by respectively cutting out the parts, outside the contact lines, on the first initial annular surface (11), the second initial annular surface (12), the second annular surface (5) and the volute surface (6).

2. A method of three-dimensional geometric modeling of a swirl flow passage inside a turbine casing according to claim 1, characterized in that the first initial annulus (11) and the second initial annulus (12) are created using a rotational modeling function of computer software, the rotational centre line of which coincides with the turbine bore (3) axis.

3. A method of three-dimensional geometrical shaping of a swirl flow channel inside a turbine casing according to claim 1, characterized in that the cross-sectional elements drawn by the shaped cross-section of the computer software shaping function creating the first initial torus (11) and the second initial torus (12) are connected into a chain of elements, the cross-sectional elements surrounding the turbine aperture (3) that can always be in contact with the swirl face (6) being only one smooth first individual element (9) and another smooth second individual element (10), respectively.

4. A method of three-dimensional geometry modeling of a swirl flow passage inside a turbine housing according to claim 1, characterized in that in the forming section of the scanning modeling function of creating the scroll face (6), both end points (13), (14) of the plotted section primitive chain are respectively constrained to the first initial torus (11) and the second initial torus (12), the outermost point (15) of the plotted section primitive chain is marked with the scroll size of the axis of the turbine hole (3), the scroll size is controlled by a functional formula, and the scroll size value is gradually changed during the orbital scanning modeling.

5. A method of three-dimensional geometrical shaping of a swirl flow channel inside a turbine casing according to claim 1, characterized in that the first initial annulus (11) and the second initial annulus (12) are created using a scanning shaping function, which designates the circular arc line (7) as a trajectory for the scanning shaping, the shaped cross section of which is arranged to be constant in shape along a plane in which the cross section is arranged to be perpendicular to the circular arc line (7) when the trajectory is scanned.

6. A method of three-dimensional geometrical shaping of a swirl flow channel inside a turbine casing according to claim 1, characterized in that in the chain of cross-sectional elements drawn by the shaped cross-section of the computer software shaping function creating the first initial torus (11) and the second initial torus (12), a plurality of connected elements are converted into individual sample strip elements (17), and the only cross-sectional elements surrounding the turbine hole that are always in contact with the volute surface are said sample strip elements (17).

7. A method of three-dimensional geometric modeling of a scroll flow path within a turbine housing as defined in claim 1 wherein in a shaped cross section of a scan modeling function that creates a scroll face, the chain of plotted cross-section primitives includes a number of primitives ranging from one to a plurality, the radius of the circular arc primitives (18) in the chain of plotted cross-section primitives is controlled by a functional formula, and the radius varies gradually as the scroll is scan modeled.

8. A method of three-dimensional geometric shaping of a scroll flow passage within a turbine housing according to claim 1, wherein the turbine housing has a first scroll flow passage (19) and a second scroll flow passage (20) therein, the two including respective first and second annular surfaces and scroll surfaces.

9. A method of three-dimensional geometrical shaping of a swirl flow channel inside a turbine casing according to claim 1, characterized in that the scanning shaping function creating the scroll face (6) also designates a curve (8) tapering gradually inwards along the circumference of the turbine bore (3) as another trajectory for the scanning shaping, the shaped cross section of the scanning shaping function being such that the plane of the cross section is perpendicular to said circular arc (7) as the trajectory is scanned, the outermost point (15) of the drawn chain of cross-section graphical elements being positioned in alignment with the intersection point (16) of said curve (8) and the plane of the cross section along the axial direction of the turbine bore (3).