CN113139236A

CN113139236A - Modeling method for turbulence ribs of inner-cooling turbine blade based on sweep curve

Info

Publication number: CN113139236A
Application number: CN202110454600.5A
Authority: CN
Inventors: 王成恩; 袁辉
Original assignee: Shanghai Shengsheng Digital Technology Co ltd
Current assignee: Shanghai Shengsheng Digital Technology Co ltd
Priority date: 2021-04-26
Filing date: 2021-04-26
Publication date: 2021-07-20

Abstract

The invention discloses a modeling method of a turbulence rib of an internal cooling turbine blade based on a swept path, which comprises the following steps: creating at least one sweep path on the side of a flow channel blade back and/or a blade basin, wherein the direction of each sweep path in the at least one sweep path is consistent with the direction of the corresponding flow rib to be created; correspondingly creating a sweep cross section on the at least one sweep path respectively; generating a spoiler rib entity by sweeping the corresponding swept cross-section along the at least one swept path. The method can create curved surface turbulence ribs, the cross sections and the lengths of different turbulence ribs can be changed, the rib cross sections can be randomly arranged according to the situation, and modeling can be carried out under the condition that the inner flow channel is an integral curved surface.

Description

Modeling method for turbulence ribs of inner-cooling turbine blade based on sweep curve

Technical Field

The invention belongs to the technical field of modeling of turbine blades, and particularly relates to a modeling method for turbulence ribs of an internally-cooled twisted turbine blade.

Background

Increasing turbine inlet temperature is an important measure to increase the thrust-weight ratio of an engine, but is limited by the temperature tolerance of the turbine material. The turbine inlet temperature of the advanced military engine at present exceeds 1990K and far exceeds the working temperature of 1300-1400K of high-temperature resistant alloy. In order to ensure the reliable operation of the engine, the turbine blade generally adopts a composite cooling mode of air film and internal flow. The corresponding cooling structure comprises air film holes, turbulence ribs, turbulence columns, impact holes and the like. The flow disturbing ribs are important components and are arranged in the inner walls of a plurality of cooling channels formed by separating the blade inner cavity by the partition ribs, and the flow disturbing ribs comprise parallel ribs, discontinuous parallel ribs, V-shaped flow disturbing ribs and discontinuous V-shaped flow disturbing ribs, the schematic diagrams of the flow disturbing ribs and the V-shaped flow disturbing ribs are respectively shown as a, b, c and d in fig. 1, and the examples of the parallel ribs and the V-shaped flow disturbing ribs are respectively shown as a and b in fig. 2. The heat dissipation device has the functions of increasing the heat dissipation area and enhancing the air flow disturbance so as to enhance heat exchange and reduce the temperature of the inner wall of the blade.

Aiming at the characteristics of the turbulence ribs in the crankling cooling channel, the most advanced turbulence rib modeling at present is mainly a 'equidistant curved surface-based' turbulence rib modeling method, and rib bodies are obtained by cutting a flat plate tool body by using an equidistant surface of a rib partition surface and a blade basin or a blade back, so that the turbulence rib modeling is completed on the basis of the rib partition surface and the blade basin or the blade back. The existing modeling method can ensure that the thickness of the turbulence rib is uniform and consistent, well adapts to the condition of a twisted blade, avoids the problem that part of blade inner type entities are cut off by mistake in the modeling process, and realizes the arrangement of various types of turbulence ribs through fewer parameters such as the angle of a cutting body, the offset distance of each curved surface and the like.

However, the existing turbulent flow rib modeling method based on equidistant curved surface modeling has the following problems:

1. the basic entity of the turbulence rib is a cuboid, so that the geometric surface of the position A (including the corresponding geometric surface below) in the figure 3 can only be a plane, and the establishment of the entity of the curved turbulence rib can not be realized by adopting the existing method;

2. under certain scenes, turbulence ribs with different lengths or variable cross sections are needed, for example, the cross section at the root of a staggered rib is larger than the cross section at the tip of the staggered rib, and the modeling of the turbulence ribs with the variable cross sections cannot be realized by the conventional method;

3. the basic entity of the turbulence rib characteristic is a cuboid, so that the rib section is a rectangle or a part based on the rectangle, and the turbulence ribs with other shapes of sections cannot be created by applying the method;

4. the rib foundation body is cut through the four curved surfaces, and modeling cannot be carried out under the condition that the inner flow channel is a whole curved surface.

Disclosure of Invention

The invention aims to solve the problems that curved surface turbulence ribs cannot be created, the cross section and the length of the turbulence ribs cannot be changed, the cross section of the ribs is single in shape, and modeling cannot be performed under the condition that an inner flow channel is an integral curved surface in the prior art, and provides a modeling method for the turbulence ribs of an inner cooling turbine blade based on a sweep curve.

In order to achieve the purpose, the invention adopts the following technical scheme:

the invention provides a modeling method for turbulence ribs of an internal cooling turbine blade based on a sweep curve, which specifically comprises the following steps:

creating at least one sweep path on the side of a flow channel blade back and/or a blade basin, wherein the direction of each sweep path in the at least one sweep path is consistent with the direction of the corresponding flow rib to be created;

correspondingly creating a sweep cross section on the at least one sweep path respectively;

generating a spoiler rib entity by sweeping the corresponding swept cross-section along the at least one swept path.

According to the scheme, the turbulence ribs of the blade are generated on the basis of the swept path, the swept path is created along the blade back or the blade basin side of the runner, and the direction of the swept path is consistent with the direction of the turbulence ribs to be created, namely the turbulence ribs with the curved surfaces on the outer surfaces can be generated on the basis of adapting to the bending and twisting change of the blade runner by adopting the method; the whole method does not need to cut the turbulence ribs by a plurality of curved surfaces, and modeling can be carried out under the condition that the inner runner is a whole curved surface. With this approach, the swept cross-section can be a variety of shapes, such as rectangular, trapezoidal, rectangular + semicircular, diamond, irregular, or other shapes, enabling modeling of spoiler ribs of a variety of cross-sectional shapes. By adopting the method, the sweep path determines the length of the turbulence rib, the sweep section determines the section size of the turbulence rib, and when different turbulence ribs are constructed, the sweep paths with different lengths and the sweep sections with different areas are generated, so that the turbulence ribs with different lengths and different section sizes are constructed, the requirements of certain scenes are met, and the modeling of the turbulence ribs with the section at the blade root larger than the section at the blade tip of the staggered rib is met.

In one possible design, the swept path includes an intermediate segment that is a curved segment that lies on the flowpath blade back or blade bowl curve.

In one possible design, the method for generating the middle segment includes:

creating at least one auxiliary surface attached to the flow channel, wherein the auxiliary surface is positioned on the blade back or the blade basin side of the flow channel;

and creating a plane correspondingly intersected with the auxiliary surface at least one height of the auxiliary surface, wherein the inclination angle of the plane is equal to that of the corresponding to-be-created turbulence rib, and the intersection line of the plane and the corresponding auxiliary surface is the middle section of the sweeping path of the to-be-created turbulence rib.

In a possible design, two auxiliary surfaces have an intersection line when the number of auxiliary surfaces is two.

The auxiliary surfaces are used for assisting in generating the middle section of the swept path, and in the V-shaped turbulence rib modeling process, the modeling speed of the turbulence rib is improved by simultaneously constructing the two auxiliary surfaces and the planes matched with the two auxiliary surfaces in number.

In one possible design, the swept path further includes an extension section extending in a tangential direction of at least one end of the intermediate section.

The turbulence ribs and the partition ribs are intersected, only the middle section is arranged to serve as a sweeping path, the sweeping path is too short, the constructed turbulence ribs and the partition ribs cannot be completely intersected sometimes, the two ends of the middle section are respectively extended with an extension section, the length of the turbulence ribs is ensured, and the effective connection of the turbulence ribs and the partition ribs is ensured.

Creating a swept cross section at the end point of the swept path, sweeping along the path, and generating at least one turbulence rib entity;

deleting a temporary geometry comprising the swept path, swept cross-section;

and combining the turbulence rib entity and the blade body to obtain a blade model with turbulence ribs.

In one possible design, the rounding operation is performed on the edges of the spoiler ribs in the blade model.

In the process of generating the turbulence ribs, sharp angles exist at junctions of the turbulence ribs and the blade bodies, the edge of each turbulence rib is rounded, and the structural performance of the model is improved.

In one possible design, the combination of the spoiler rib entity and the blade body is realized by using a Boolean summation method.

Compared with the prior art, the invention at least has the following advantages and beneficial effects:

1. the scheme of the invention is based on the sweep path to generate the turbulence ribs of the blade, the sweep path is established along the blade back or the blade basin side of the runner, and the direction of the sweep path is consistent with the direction of the turbulence ribs to be established, namely, the method can generate the turbulence ribs with the curved surface on the outer surface on the basis of adapting to the bending and twisting change of the blade runner; in the whole method, the rib entity is not required to be cut by a plurality of curves, and modeling can be carried out under the condition that the inner runner is an integral curved surface.

2. According to the scheme of the invention, the turbulence rib is obtained by sweeping the constructed swept section along the swept path, the shape of the swept section is not limited, the turbulence rib can be constructed at will, for example, the turbulence rib can be rectangular, trapezoidal or in other shapes, and modeling of turbulence ribs with various cross-sectional shapes can be realized.

3. According to the scheme, the length of the turbulence rib is determined by the sweep path, the size of the cross section of the turbulence rib is determined by the sweep cross section, when different turbulence ribs are constructed, the sweep paths with different lengths and the sweep cross sections with different areas are generated, so that the turbulence ribs with different lengths and different cross section sizes are constructed, the requirements of certain scenes are met, and the modeling of the turbulence rib, such as the cross section at the root of the staggered rib is larger than the cross section at the tip of the blade, is met.

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 view of a turbulator rib;

FIG. 2 is an exemplary view of a turbulator rib;

FIG. 3 is a schematic diagram of a structure of a spoiler rib generated in an original modeling direction;

FIG. 4 is a flow chart of a spoiler rib modeling method of the present invention;

FIG. 5 is a view showing an example of an interrupted V-shaped spoiler rib;

FIG. 6 is a graph of parameter values for a curve segment;

FIG. 7 is a process of creating an auxiliary curved surface in an embodiment when modeling the interrupted V-shaped spoiler rib;

FIG. 8 is a diagram illustrating the determination of the starting point of the sweep path in an embodiment when modeling the interrupted V-shaped spoiler rib;

FIG. 9 is a diagram illustrating a process of forming a sweep path in an embodiment when modeling the interrupted V-shaped spoiler rib;

FIG. 10 is a diagram illustrating a process of forming a swept cross-section to a spoiler rib entity in an embodiment when modeling a discontinuous V-shaped spoiler rib;

FIG. 11 is a solid diagram of a blade body merged with a spoiler rib in an embodiment when modeling an interrupted V-shaped spoiler rib;

FIG. 12 is a graph illustrating a result of chamfering the spoiler rib of FIG. 12;

FIG. 13 is a solid partial view of a blade having a solid side rib;

FIG. 14 is a perspective view of a turbine blade having interrupted V-shaped turbulator ribs;

FIG. 15 is a diagram of auxiliary surface creation in an embodiment when modeling V-shaped turbulating ribs;

FIG. 16 is a diagram illustrating a sweep path formation process in an embodiment when modeling V-shaped turbulator ribs;

FIG. 17 is a plot of swept cross-sections in an embodiment when modeling V-shaped turbulator ribs;

FIG. 18 is a perspective view of a turbine blade having V-shaped turbulator ribs;

FIG. 19 is a diagram of auxiliary camber creation in an embodiment when parallel turbulator ribs are created on a twisted blade body;

FIG. 20 is a plot of swept path generation in an embodiment when parallel turbulator ribs are created on a twisted blade body;

FIG. 21 is a plot of swept cross-sections generated in an embodiment when parallel turbulator ribs are created on a twisted blade body;

FIG. 22 is a diagram illustrating the physical generation of a turbulator rib in one embodiment when parallel turbulator ribs are created on a twisted blade body;

FIG. 23 is a diagram of a multi-turbulator rib entity generation in one embodiment when parallel turbulator ribs are created on a twisted blade body;

FIG. 24 is a solid view of a twisted blade body with parallel turbulator ribs.

Detailed Description

The invention is further described with reference to the following figures and specific embodiments. It should be noted that the description of the embodiments is provided to help understanding of the present invention, but the present invention is not limited thereto. Specific structural and functional details disclosed herein are merely illustrative of example embodiments of the invention. This invention may, however, be embodied in many alternate forms and should not be construed as limited to the embodiments set forth herein.

It will be understood that, although the terms first, second, etc. may be used herein to describe various elements, these elements should not be limited by these terms. These terms are only used to distinguish one element from another. For example, a first element could be termed a second element, and, similarly, a second element could be termed a first element, without departing from the scope of example embodiments of the present invention.

It should be understood that, for the term "and/or" as may appear herein, it is merely an associative relationship that describes an associated object, meaning that three relationships may exist, e.g., a and/or B may mean: a exists alone, B exists alone, and A and B exist at the same time; in addition, for the character "/" that may appear herein, it generally means that the former and latter associated objects are in an "or" relationship.

It should be understood that specific details are provided in the following description to facilitate a thorough understanding of example embodiments. However, it will be understood by those of ordinary skill in the art that the example embodiments may be practiced without these specific details. For example, systems may be shown in block diagrams in order not to obscure the examples in unnecessary detail. In other instances, well-known processes, structures and techniques may be shown without unnecessary detail in order to avoid obscuring example embodiments.

As shown in fig. 4, the present embodiment provides a modeling method for turbine blade turbulator ribs, which may be, but is not limited to, performed by a modeling apparatus, which may be software, or a combination of software and hardware, and which may be integrated in an intelligent device such as a smart mobile terminal, a tablet, a computer, etc. Specifically, as shown in fig. 4, the modeling method for the turbine blade spoiler rib includes the following steps S101 to S107.

S101, at least one sweeping path is created on the side of a flow channel blade back and/or a blade basin, and the direction of each sweeping path in the at least one sweeping path is consistent with the direction of the corresponding flow rib to be created. The swept path may be a straight line or a curved line depending on the flow rib structure to be created. In this step, according to the modeling requirement of the turbulence rib, the modeling method can be only established on the back side of the runner blade, or only established on the blade basin side of the runner, or established on the blade back and the blade basin side of the runner at the same time, and the number and the direction of the sweeping paths are matched with the modeling requirement of the turbulence rib.

Specifically, at least one auxiliary surface attached to the flow channel is created, and the auxiliary surface is located on the blade back side or the blade basin side of the flow channel according to modeling requirements of the turbulence rib; the auxiliary surface may be an auxiliary curved surface or an auxiliary flat surface depending on the flow channel structure. Depending on the type of construction of the turbulator ribs, only one auxiliary surface may be created, or two auxiliary surfaces may be constructed simultaneously. When two auxiliary surfaces are provided, the two auxiliary surfaces have an intersection line, and the method can be used for modeling V-shaped ribs or discontinuous V-shaped ribs.

And creating a plane correspondingly intersected with the auxiliary surface at least one height of the auxiliary surface, wherein the inclination angle of the plane is equal to that of the corresponding to-be-created turbulence rib, and the intersection line of the plane and the corresponding auxiliary surface is the middle section of the sweeping path of the to-be-created turbulence rib. According to the modeling quantity requirement of the turbulence ribs, planes can be created at different heights of the auxiliary surface, one plane corresponds to one turbulence rib, and the intersection line of one plane and the corresponding auxiliary surface is the middle section of the sweeping path of the turbulence rib to be created, which corresponds to the plane. It should be noted here that, if there are a plurality of auxiliary surfaces, a plane may intersect with the plurality of auxiliary surfaces, but the intersection line of the plane and all the auxiliary surfaces is not the middle section of the sweep path, the middle section of the sweep path is only the intersection line of the plane and the corresponding auxiliary surface that is adopted as the middle section of the sweep path corresponding to the spoiler rib to be created, and the remaining intersection lines are invalid line segments, that is, it can be understood that a plane corresponds to only a spoiler rib to be created, and an auxiliary surface may intersect with a plurality of planes. It should be noted that the height herein refers to the height along the axial direction of the flow passage.

The middle section can be directly used as a sweep path, but the determination of the middle section cannot guarantee that the created turbulence ribs are long enough and cannot guarantee complete intersection with the partition ribs.

And S102, correspondingly creating a swept cross section on the at least one swept path, wherein the swept cross section can be in a square, diamond, trapezoid, circle or any other structure according to the modeling requirement of the turbulence rib.

S103, sweeping the corresponding swept cross section along the at least one swept path to generate a turbulence rib entity. In this step, the sweep may adopt a sweep function of CAD software or a PK _ BODY _ make _ sweep _ BODY () function in Parasolid.

The method is adopted to realize modeling of the turbulence rib, the sweep path can be a curve or a straight line, the turbulence rib obtained by sweeping the sweep section along the sweep path can be a straight line or a curved line, and the method can generate the turbulence rib with the curved surface on the outer surface on the basis of adapting to the bending and twisting change of the blade flow channel. The shape of the cross section of the swept cross section is not limited, and can be a rectangle, a trapezoid, a rectangle + a semicircle, a diamond, an irregular shape or other shapes, the turbulent flow rib obtained by sweeping the swept cross section along the swept path has the same cross section as the swept cross section, and modeling of the turbulent flow rib with various cross section shapes can be realized. The length of the turbulence rib is determined by the sweep path, the section size of the turbulence rib is determined by the sweep section, when different turbulence ribs are constructed, the sweep paths with different lengths and the sweep sections with different areas are generated, so that the turbulence ribs with different lengths and different section sizes are constructed, the requirements of certain scenes are met, and the modeling of the turbulence ribs with the sections larger than the sections at the blade tips at the blade roots of the staggered ribs is met.

S104, constructing at least one turbulence rib entity, wherein the number and the position of the turbulence rib entities are consistent with the modeling requirements according to the turbulence ribs.

S105, deleting a temporary geometry, wherein the temporary geometry comprises the sweep path and the sweep section.

S106, combining the turbulence rib entity and the blade body to obtain a blade model with turbulence ribs. In this step, the combination of the spoiler rib entity and the blade BODY may adopt a boolean operation function of CAD software or a PK _ BODY _ coolean _2() function in Parasolid.

And S107, rounding the edges of the turbulence ribs in the blade model. And the sharp angle at the edge of the turbulence rib, namely the joint of the turbulence rib and the blade body, is removed by rounding operation.

The interrupted V-shaped turbulence ribs are rib features that a plurality of turbulence ribs are arranged on the inner wall of one flow channel in a V shape along the stacking direction, but the rib features that the middle is not connected, and two edges of the V shape are staggered with each other along the stacking direction of the blades, a schematic diagram is shown as d in fig. 1, and an example is shown as fig. 5. The description is given in detail by taking the model of the interrupted V-shaped turbulence rib and the turbine blade with the interrupted V-shaped turbulence rib as an example, specifically, by taking the example of creating the interrupted V-shaped turbulence rib on the blade body model of the closed Nurbs curve with the flow channel stacking cross-sectional profile as the second-order eight control points, of course, the basis for creating the interrupted V-shaped turbulence rib is not limited to the blade body model of the closed Nurbs curve with the flow channel stacking cross-sectional profile as the second-order eight control points, but may also be the blade body of other structures. The modeling process includes the following steps S201 to S207.

S201, creating a sweeping path on the blade back and/or the blade basin side of the flow channel.

First, a secondary curved surface of the leaf back or the leaf basin portion is created, the leaf back being taken as an example in this example. Referring to fig. 7, a curve (a Nurbs curve, referring to geometry) is taken as a stacking contour of the auxiliary curved surface along each stacking section contour line of the inner flow passage 11, and in the second-order eight-control-point closed Nurbs curve, a parameter value range of a curve section near the blade back can be determined according to fig. 6, where the curve section near the blade back is t 0-0.9375 and t 1-0.0625 (in fig. 6, t is a control point of the parameter curve in a defined domain P0-P7). Because of a closed periodic Nurbs curve, t is 0.0625 and t is 1.0625 can be regarded as the same parameter value. Fitting each section of curve at the blade back of the flow channel to form an auxiliary surface 1, wherein the auxiliary surface 1 is completely attached to the flow channel, as shown in c in fig. 7, the constructed auxiliary surface is an auxiliary curved surface, wherein a in fig. 7 is a contour line of the blade and the inner flow channel, and b is a contour line of the flow channel at the blade and the blade back. The auxiliary curved surface is used to assist in creating one side rib of the interrupted V-shaped spoiler rib, and in particular, the auxiliary curved surface is used to assist in creating the right side rib of the interrupted V-shaped spoiler rib, taking the view angle of fig. 7 as an example.

A three-dimensional coordinate system is constructed, and a spoiler rib near the blade root is taken as an example for explanation. As shown in fig. 8, a horizontal plane 2 is formed at a vertex of the spoiler rib in the Z-axis direction, where the Z-axis is the height direction or the flow channel direction, and a leftmost intersection point of the intersection line of the horizontal plane and the auxiliary surface is used as a starting point ptLocation of the sweep path, and at this time, the horizontal plane may be deleted.

And constructing an inclined plane, wherein the inclination angle of the inclined plane is the same as that of the interrupted V-shaped turbulence ribs, and the inclination angle of the inclined plane is the included angle between the inclined plane and the plane formed by the X, Y shaft, namely the included angle between the inclined plane and the horizontal plane. The inclined plane also needs to be large enough to intersect the auxiliary surface to form an intersection line, on which the starting point ptLocation is placed, as shown in fig. 9 a. The intersection line of the plane and the auxiliary surface 1 forms an intermediate section 31 of the sweep path, and at this time, the intermediate section extends to form an extended section 32, specifically, the intermediate section extends in the tangential direction at the non-starting point ptLocation end of the intersection line, as shown in b in fig. 9, and at this time, the sweep path includes the intermediate section 31 and the extended section 32.

S202, a swept cross section is created on the swept path, specifically, a swept cross section may be created at one end of the swept path, and the swept cross section may be a square, a diamond, a trapezoid, a circle, or any other structure according to modeling requirements of the spoiler rib, where as shown in a diagram a in fig. 10, a rectangular swept cross section 4 is created at a starting point ptLocation, specifically, a rectangular cross section is created with the starting point ptLocation as a center, a tangential direction of the point as a normal direction, and a main normal direction of the point as a reference direction, and a length and a width of a rectangular sheet body are used as input parameters of rib characteristics.

S203, sweeping the swept cross section along the swept path to generate the spoiler rib entity 5, and the generated result is shown as b in fig. 10. In this step, the sweep may adopt a sweep function of CAD software or a PK _ BODY _ make _ sweep _ BODY () function in Parasolid.

So far, a spoiler rib entity is created by adopting the steps S201 to S203. After modeling of a turbulence rib entity is completed, the turbulence rib entity needs to be combined with a blade body to form a turbine blade model with discontinuous V-shaped turbulence ribs, modeling of the turbulence ribs can be sequentially built one by one and can also be simultaneously built, and similarly, combination of the turbulence ribs and the blade body can be performed after modeling of one turbulence rib and can also be performed simultaneously after modeling of all the turbulence ribs is completed.

S204, in this case, the above-constructed turbulence rib and blade body are combined as an example, and the entity of the turbulence rib and the blade body are subjected to boolean summation to obtain the entity result shown in fig. 11.

After the turbulence rib entity and the blade body are combined in the shape, the edge of the turbulence rib has a sharp angle, and the turbulence rib needs to be chamfered at the moment.

S205, in this embodiment, a spoiler rib and a blade body are combined and then taken as an example, and the edges of the spoiler rib in the blade model are rounded, and the result is shown in fig. 12.

S206, sequentially increasing the height of the horizontal plane 2 and repeating steps S201 to S205, a blade entity having one-side rib entities as shown in fig. 13 is generated.

S207, constructing the other side of the intermittent V-shaped turbulence rib according to the steps 201 to 206, and generating a blade entity with the intermittent V-shaped turbulence rib as shown in FIG. 14.

The V-shaped turbulence ribs are a row of turbulence ribs which are arranged on the inner wall of one flow channel in a V shape along the stacking direction and are connected in the middle. The V-shaped spoiler rib modeling is taken as an example for detailed description, specifically, the V-shaped spoiler rib is created on the blade body model of the closed Nurbs curve with the flow channel stacking cross-sectional profile as the second-order eight control points, and of course, the creation basis of the intermittent V-shaped spoiler rib is not limited to the blade body model of the closed Nurbs curve with the flow channel stacking cross-sectional profile as the second-order eight control points, but may be the blade body with other structures. The modeling process includes the following steps S301 to S306.

S301, two sweeping paths are created on the blade back side and/or the blade basin side of the flow channel.

Similarly, a secondary curved surface is first created at the leaf back or the leaf basin section, which is exemplified by the leaf back in this example. The auxiliary surfaces 1 are also curved surfaces, two auxiliary surfaces are provided and are respectively used as sweeping auxiliary curved surfaces on two sides of the V-shaped turbulence rib, the two auxiliary surfaces have an intersection line, the modeling steps of the auxiliary surfaces are the same as those of the interrupted V-shaped turbulence rib, and the created result is shown in FIG. 15.

Two inclined planes as shown in a figure of a in figure 16 are created at the position, at a height from the bottom end of the flow channel, of the intersection line of the two auxiliary surfaces, the height is the distance between the first turbulence rib close to the bottom end of the flow channel and the bottom end of the flow channel, the inclination angles of the two inclined planes are respectively consistent with the inclination angles of the ribs on two sides of the V-shaped turbulence rib, the two inclined planes are respectively intersected with the two auxiliary surfaces to obtain a middle section 31 as shown in a figure b in figure 16, and the tangent line positions of two ends of the middle section 31 are lengthened to obtain an extension section as shown in a figure c in figure 17.

S302, a sweep cross section is created on the sweep path, specifically, a sweep cross section is created at one end of the sweep path as shown in fig. 17, and similarly, the sweep cross section may be rectangular, trapezoidal, semicircular + rectangular, or other shapes according to the modeling requirement of the turbulence rib.

S303, sweeping the swept section along the swept path to generate a turbulence rib entity.

S304, performing Boolean summation on the turbulence rib entity and the blade body, and performing rounding operation on the turbulence rib edge.

S305, increasing the height of the inclined plane in the stacking direction in the S301, and repeating the steps S301 to S304 until all the turbulence ribs are generated.

S306, deleting a temporary geometry, wherein the temporary geometry comprises the sweeping path, the sweeping section and the auxiliary surface. The resulting V-shaped turbulator ribs are shown in fig. 18.

The parallel turbulence ribs are a plurality of turbulence ribs arranged in parallel on the inner wall of the flow channel. The modeling process of creating parallel spoiler ribs on a twisted blade body and a twisted turbine blade with the parallel spoiler ribs is described in detail herein, and includes the following steps S401 to S406.

S401, a sweeping path is created on the blade back side and/or the blade basin side of the flow channel.

First, an auxiliary surface of the leaf back or the leaf basin section is created, the leaf back being taken as an example in this example. Referring to fig. 6, a curve with t0 being 0.0 and t1 being 0.125 is taken on the blade flow path bottom surface basin curve, and if an auxiliary surface is created on the blade back side, a curve with t0 being 0.5 and t1 being 0.625 is taken on the blade flow path bottom surface basin curve. The curve is subjected to stretching sweep according to the zooming and twisting mode of the blade to form a curved surface, namely the auxiliary surface 1, as shown in fig. 19. And for the stacked blades, a curve surface can be generated by adopting a fitting mode of curve segments of all the sections. And (5) calculating the coordinate of the point, namely 0, and moving the point upwards by the height H of the first spoiler rib from the bottom edge to the starting point ptLocation.

Taking the starting point ptLocation as a reference point, a horizontal plane 2 is created, which has 2 intersection points with the auxiliary plane, and similarly, taking the three-dimensional coordinates in fig. 20 as an example, in this case, a point with a smaller X value among the 2 intersection points is taken as a reference point, and an inclined plane is created, which has an inclination angle identical to that of the spoiler rib. The intersection of this inclined plane and the auxiliary surface constitutes the middle section 31 of the swept path. If a turbulence rib is created on the blade back side at this time, a point with a larger X value in the 2 intersection points is used as a reference point, and an inclined plane is created. And extending the intersection line along the tangential directions of the two end points to obtain a sweeping path with an extension section.

S402, creating a swept cross section on the swept path, specifically, creating a swept cross section 4 at one end of the swept path, where the swept cross section may be a rectangle, a trapezoid, a semicircle plus a rectangle or other shapes according to the modeling requirements of the spoiler rib, and the creation result is shown in fig. 21. The normal direction of the swept cross section is consistent with the tangential direction of the endpoint of the swept path.

S403, sweeping the swept cross section along the swept path to generate the turbulence rib entity 5, and the generated result is shown in fig. 22.

And S404, performing Boolean summation on the turbulence rib entity and the blade body.

S405, rounding the edges of the turbulence ribs in the blade model,

s406, increasing the height of the starting point ptLocation, and repeating the steps S401 to S405 to generate a parallel turbulence rib entity as shown in FIG. 23, wherein the parallel turbulence ribs gradually become smaller from bottom to top, that is, the cross section of the blade is reduced from 100% to 50%; the turbine blade entity obtained by the Boolean summation of all the parallel spoiler ribs and the blade body is shown in FIG. 24.

Finally, it should be noted that: the above description is only a preferred embodiment of the present invention, and is not intended to limit the scope of the present invention. Any modification, equivalent replacement, or improvement made within the spirit and principle of the present invention should be included in the protection scope of the present invention.

Claims

1. A modeling method for turbulence ribs of an inner-cooling turbine blade based on a sweep curve is characterized by comprising the following steps:

2. The method of claim 1, wherein the swept path comprises an intermediate segment that is a curved segment on a flowpath blade back or a bucket curved surface.

3. The method of claim 2, wherein the method of generating the intermediate section comprises:

4. The modeling method for turbulence ribs of an internal cooling turbine blade based on a swept curve of claim 3, wherein when the number of the auxiliary surfaces is two, the two auxiliary surfaces have an intersection line.

5. The method of claim 2, wherein the swept path further comprises an extension extending in a tangential direction of at least one end of the intermediate segment.

6. The modeling method for the turbulence ribs of the internal cooling turbine blade based on the sweep curve as recited in claim 1, wherein a sweep cross section is created at an end point of a sweep path, the sweep cross section is swept along the sweep path to generate turbulence rib entities, and the turbulence rib entities and the blade body are combined to obtain a blade model with the turbulence ribs.

7. The method of claim 1, further comprising rounding edges of turbulator ribs in the blade model.

8. The modeling method for the turbulence rib of the internal cooling turbine blade based on the sweep curve as recited in claim 1, wherein the combination of the turbulence rib entity and the blade body is realized by a Boolean summation method.