CN104392027B - A kind of parametric modeling method of turbo blade turbulence columns - Google Patents

Abstract

The present invention proposes a parametric modeling method for turbine blade turbulence columns. The meridian is obtained by connecting the center of the trailing edge of the inner shape of the airfoil, and the middle arc and the middle arc surface of the inner shape of the airfoil are generated by a double-pipeline method, and the disturbance is determined on the middle arc surface. The starting point of the stream column, through the starting point, make a datum plane perpendicular to the Z axis, find the intersection point of the datum plane and the meridian, and then move the intersection point a given number of times along the meridian at a given distance to obtain a list of points along the meridian, and do the points respectively The datum plane perpendicular to the Z-axis obtains the set of intersection lines between the datum plane and the mid-arc surface, and moves all the above-mentioned intersection points along each intersection line with an arc length L to obtain the center of the first row of spoiler columns. The center of the flow column moves N times along each intersection line with the arc length L', and a set of center of the spoiler column on the arc surface of the distribution is obtained. In this method, the centers of each group of spoiler columns are distributed on the mid-arc surface with equal arc lengths and equal intervals, so that the position distribution on the airfoil surface is more uniform, and the turbulence and heat dissipation inside the airfoil are better strengthened. .

Description

A Parametric Modeling Method of Turbine Blade Spoiler Column

technical field

The invention relates to the field of parametric modeling design of a spoiler column of a turbine blade.

Background technique

Aeroengine blades are the key components of aeroengines, which have the characteristics of complex structure, many varieties, large quantities, great influence on engine performance, and long design and manufacturing cycle. Blade design and manufacturing technology level play an important role in improving the performance of aero-engines, shortening the development cycle and reducing costs.

Relevant domestic personnel have carried out extensive and in-depth research on the modeling method of aero-engine blades, and initially realized the parametric design method of turbine blades. However, the existing blade modeling system mainly focuses on providing the modeling function of the blade airfoil profile and the design function of the blade airfoil section line. There are not many researches on ribs and other modeling technologies, which can no longer meet the needs of today's increasingly complex blade designs.

The inside of the airfoil has a complex cavity to help heat dissipation and cooling. The inner cavity includes spoiler columns, longitudinal ribs, transverse ribs and other structures. The complex structure of the inner cavity of the blade body is reflected in the inner shape of the blade body in the opposite way of concave and convex, so the structure of the inner shape part is very complicated. It is the result of the Boolean subtraction of the inner surface and the spoiler column, transverse rib and longitudinal rib. The design and modeling of spoiler columns, transverse ribs and longitudinal rib structures is a very cumbersome process. Extracting their parametric information will greatly improve their design efficiency and shorten the design cycle. The existing high-end CAD modeling software has become the Design the heart of your production process. In the existing blade parametric modeling system, the establishment of the spoiler column feature model is to encapsulate the basic feature cylinder and array features, etc. By establishing the spoiler column design rules, the design parameters such as cylinder diameter and geometric parameters such as array mode are extracted. and achieved.

There are three ways to distribute traditional spoiler columns on the inner shape as follows:

The coordinates of the center of the spoiler column are given by the data file;

The distribution of the center coordinates of the spoiler column is a rectangular array;

The distribution of the center coordinates of the spoiler column is a complex array;

The above-mentioned spoiler columns are all generated in a certain array on the reference plane parallel to the plane near the mid-arc surface of the blade body. When the center of the spoiler column on the reference plane is projected onto the blade body profile, it will cause the The distribution of the center of the spoiler column on the body surface is very uneven, which is not conducive to the spoiler heat dissipation of the blades.

Contents of the invention

The purpose of the present invention is to solve the problem of inaccurate position generation of spoiler column center coordinates in the prior art, and to propose a new method for parametric modeling of blade spoiler column by using CAD modeling software as a platform. The meridian is obtained by connecting the center of the inner trailing edge of the blade body, and the middle arc of the inner shape of the blade body is generated by the double pipeline method, and then the middle arc surface is obtained. Datum plane, find the intersection point of the datum plane and the meridian, and then move the intersection point for a given number of times along the meridian at a given distance to obtain a list of points along the meridian, and make a datum plane perpendicular to the Z-axis through the points respectively to obtain the datum plane and the middle arc For the intersection line set of the surface, move all the above-mentioned intersection points once along each intersection line with an arc length L to obtain the center of the first row of spoiler columns, and move the center of the first row of spoiler columns along each intersection line with an arc length L' to move N times, a group of spoiler column centers on the arc surface of the distribution is obtained. In this new method of parametric modeling of blade spoiler columns, the centers of each group of spoiler columns are distributed on the mid-arc surface with equal arc lengths and equal intervals, so that the position distribution on the airfoil surface is more uniform and more accurate. The turbulence and heat dissipation inside the blade body are well strengthened.

Technical scheme of the present invention is:

The parametric modeling method of a turbine blade spoiler column is characterized in that it comprises the following steps:

Step 1: Obtain the meridian by connecting the center of the trailing edge of the inner shape of the blade body;

Step 2: Use the double pipeline method to generate the inner arc of the blade body, and obtain the inner arc of the blade body from the inner arc of the blade body;

Step 3: Select the starting point of the spoiler column on the mid-arc surface, so that the direction of the spoiler column is along the positive direction of the stacking axis;

Step 4: Determine the distribution position of the spoiler column center coordinates, and a set of spoiler column center coordinates are determined by the following steps:

Step 4.1: The starting point of the spoiler column obtained in step 3 is used as the datum plane perpendicular to the Z-axis of the blade coordinate system to obtain the intersection point P1 of the datum plane perpendicular to the Z-axis of the blade coordinate system and the meridian;

Step 4.2: Move the intersection point P1 along the meridian by a given distance D1 N1 times to obtain a list of point sets Gp1 along the meridian;

Step 4.3: Each point in the point set Gp1 obtained in step 4.2 is respectively set as a datum plane perpendicular to the stacking axis, and the intersection line between the datum plane perpendicular to the stacking axis and the mid-arc surface corresponding to each point is obtained;

Step 4.4: Move each point in the point set Gp1 once along the corresponding intersection line according to the given arc length L1, and obtain the center of the spoiler column of the first group and the first column distributed on the mid-arc surface;

Step 4.5: Move the center of the first group of spoiler columns distributed on the mid-arc surface several times along their respective intersection lines according to the given arc length L1' to obtain the first group distributed on the mid-arc surface Center of all spoiler columns;

Step 5: Move the center of each set of spoiler columns generated on the mid-arc surface to an equal distance along the centerline of the spoiler columns away from the blade body to obtain the center coordinates of the spoiler columns when they are generated; generated by the spoiler columns The coordinates of the center of the circle at the time and the diameter, direction, and stretched height of the spoiler columns are used to obtain each group of spoiler columns.

A further preferred solution, the parametric modeling method of the spoiler column of the turbine blade, is characterized in that: the process of determining the center coordinates of the kth set of spoiler column is:

Step a: Move the intersection point P(k-1) once along the meridian according to the set distance to obtain the intersection point P(k);

Step b: Move the intersection point P(k) along the meridian according to a given distance D(k) N(k) times to obtain a list of point sets Gp(k) along the meridian;

Step c: each point in the point set Gp(k) obtained by step b is respectively made as a datum plane perpendicular to the stacking axis, and the intersection line between the datum plane perpendicular to the stacking axis and the mid-arc surface corresponding to each point is obtained;

Step d: Move each point in the point set Gp(k) once along the corresponding intersection line according to the given arc length L(k), and obtain the first column of the kth group of spoilers distributed on the mid-arc surface center of circle

Step e: Move the center of the spoiler columns distributed on the mid-arc surface in the first column of the k-th group several times along the corresponding intersection lines according to the given arc length L(k)' to obtain the distribution on the mid-arc surface Center of all spoiler columns in group k.

Beneficial effect

The beneficial effect of the present invention is that in the new method of parametric modeling of the blade spoiler columns, the centers of each set of spoiler columns are distributed on the mid-arc surface in a manner of equal arc length and equal interval, so that they are on the airfoil profile surface. The position distribution of the method is more uniform, which meets the needs of the enterprise, overcomes the shortcomings of the existing technology, improves the design efficiency and quality, and has high flexibility, and this method has no restrictions on the platform of the 3D software. This method can be used in A variety of software platforms, with good versatility.

Description of drawings

Figure 1 is a schematic diagram of the inner shape and meridian of the blade body.

In the figure, 1-the inner shape of the blade body; 2-the meridian obtained by connecting the center of the trailing edge of the inner shape of the blade body.

Fig. 2 is a schematic diagram of the arc surface of the inner shape of the blade body.

In the figure, 3-medium arc; 4-medium arc.

Figure 3 is a schematic diagram of the starting point.

In the figure, 5-starting point.

Fig. 4 is a schematic diagram of the intersection line between the arc surface and the reference plane in the inner shape of the airfoil.

In the figure, 6- datum plane; 7- intersection line.

Fig. 5 is a schematic diagram of the distribution of the centers of two sets of spoiler columns on the arc surface.

In the figure, 8-the center of the first spoiler column in the first column of the first group; 9-the center of the first spoiler column in the first column of the second group.

Fig. 6 is a schematic diagram of the spoiler column generated at the position of the trailing edge of the blade airfoil.

Fig. 7 is a schematic diagram of the inner shape of the airfoil after Boolean difference with the spoiler column.

Fig. 8 is a schematic diagram of the result of the Boolean difference between the inner shape of the airfoil and the outer shape of the airfoil.

detailed description

Describe the present invention below in conjunction with specific embodiment:

This embodiment takes the parametric modeling design process of a spoiler column of a certain blade as an example, and the CAD software design environment is UGNX7.5 software.

After importing the inner shape of the blade body in UG NX7.5 software, take the following steps:

Step 1: Find the center of the section line of the inner profile trailing edge of the blade body, and obtain the meridian by connecting the center of the inner profile trailing edge of the blade body, as shown in Figure 1.

Step 2: Use the double pipeline method to generate the inner arc of the blade body, and obtain the inner arc of the blade body from the inner arc of the blade body, as shown in Figure 2.

Step 3: Select the starting point of the spoiler column on the mid-arc surface. The selection of the starting point must make the generation direction of the spoiler column positive along the stacking axis. The starting point determines the initial height of the spoiler column from the center plane of the engine. , as shown in Figure 3.

Step 4: After the spoiler column design parameters (direction and diameter of the spoiler column central axis) are determined, its geometric parameters will be determined, that is, the distribution positions of the spoiler column centers on the mid-arc surface (there are two groups in this embodiment) spoiler):

Step 4.1: The starting point of the spoiler column obtained in step 3 is used as the datum plane perpendicular to the Z-axis of the blade coordinate system to obtain the intersection point P1 of the datum plane perpendicular to the Z-axis of the blade coordinate system and the meridian;

Step 4.2: Move the intersection point P1 along the meridian by a given distance D1 N1 times to obtain a list of point sets Gp1 along the meridian; N1=8 in this example;

Step 4.3: For each point in the point set Gp1 obtained in step 4.2, make a datum plane perpendicular to the stacking axis, and obtain the intersection line between the datum plane perpendicular to the stacking axis and the mid-arc surface corresponding to each point, as shown in Figure 4 ;

Step 4.4: Move each point in the point set Gp1 once along the corresponding intersection line according to the given arc length L1, and obtain the center of the spoiler column of the first group and the first column distributed on the mid-arc surface;

Step 4.5: Move the center of the spoiler columns distributed on the mid-arc surface of the first group and the first column twice along the respective intersection lines according to the given arc length L1' to obtain the first group distributed on the mid-arc surface Center of all spoiler columns;

Step 4.6: Move the intersection point P1 once along the meridian according to the distance of D1/2 to obtain the intersection point P2;

Step 4.7: Move the intersection point P2 along the meridian by a given distance D2 N2 times to obtain another point set Gp2 along the meridian; D1=D2, N1=N2 in this embodiment;

Step 4.8: Each point in the point set Gp2 obtained in step 4.7 is respectively set as a datum plane perpendicular to the stacking axis, and the intersection line between the datum plane perpendicular to the stacking axis and the mid-arc surface corresponding to each point is obtained;

Step 4.9: Move each point in the point set Gp2 once along the corresponding intersection line according to the given arc length L2, and obtain the center of the spoiler column in the first column of the second group distributed on the middle arc surface; in this embodiment , L2=2*L1;

Step 4.10: Move the center of the spoiler columns distributed on the mid-arc surface in the first column of the second group twice along the respective intersection lines according to the given arc length L2' to obtain the second group distributed on the mid-arc surface Center of all spoiler columns; L2'=L1' in this embodiment.

As shown in Figure 5, the distribution of the centers of the two sets of spoiler columns on the arc surface.

Step 5: Move the center of each set of spoiler columns generated on the mid-arc surface to an equal distance along the centerline of the spoiler columns away from the blade body to obtain the center coordinates of the spoiler columns when they are generated; generated by the spoiler columns The coordinates of the center of the circle at the time and the diameter, direction, and stretched height of the spoiler columns are used to obtain each group of spoiler columns. The generation of spoiler columns is carried out in groups, and the direction and diameter of each group of spoiler columns can be different. Figure 6 shows the spoiler column generated by the trailing edge of the inner shape of the blade; Figure 7 shows the inner shape of the blade body after Boolean difference with the spoiler cylinder; Figure 8 is the result of the Boolean difference between the outer shape of the blade body and the inner shape of the blade body.

Claims (2)

1. a kind of parametric modeling method of turbo blade turbulence columns, it is characterised in that：Comprise the following steps：

Step 1：Meridian is obtained by connecting the blade inner mold trailing edge center of circle；

Step 2：Blade inner mold mean camber line is generated using two-tube Dow process, cambered surface in blade inner mold is obtained by blade inner mold mean camber line；

Step 3：Turbulence columns starting point is chosen in middle cambered surface, makes the direction that turbulence columns are generated positive along long-pending folded axle；

Step 4：Determine turbulence columns central coordinate of circle distributing position：

Step 4.1：Cross the turbulence columns starting point that step 3 obtains and make reference plane perpendicular to blade coordinate system Z axis, obtain perpendicular to The reference plane of blade coordinate system Z axis and meridianal intersection point P1；

Step 4.2：Intersection point P1 is moved N1 times along meridian according to given apart from D1, obtained along meridianal row point set Gp1；

Step 4.3：The every bit crossed in the point set Gp1 that step 4.2 is obtained does the reference plane perpendicular to long-pending folded axle respectively, obtains each The intersection of the corresponding reference plane perpendicular to long-pending folded axle of point and middle cambered surface；

Step 4.4：Every bit in point set Gp1 is moved once along each self-corresponding intersection according to given arc length L1, obtained First group of first row is distributed in the turbulence columns center of circle in middle cambered surface；

Step 4.5：First group of first row is distributed in the turbulence columns center of circle in middle cambered surface along each self-corresponding intersection according to given Arc length L1 ' it is mobile several times, obtain first group of all turbulence columns center of circle being distributed in middle cambered surface；

Step 5：By the every group of turbulence columns center of circle generated in middle cambered surface along turbulence columns center line toward the direction mobile phase away from blade Deng distance, obtain flow-disturbing cylinder generation when central coordinate of circle；Central coordinate of circle and turbulence columns when being generated by flow-disturbing cylinder it is straight Footpath, direction, cylinder stretching height obtain every group of turbulence columns.

2. a kind of parametric modeling method of turbo blade turbulence columns according to claim 1, it is characterised in that：Kth group is disturbed Fluidization tower central coordinate of circle determination process is：

Step a：Intersection point P (k-1) is moved once along meridian according to setpoint distance, intersection point P (k) is obtained；

Step b：Intersection point P (k) is obtained along meridianal row point along meridian according to given secondary apart from the mobile N (k) of D (k) Collect Gp (k)；

Step c：The every bit crossed in the point set Gp (k) that step b is obtained does the reference plane perpendicular to long-pending folded axle respectively, obtains each point The intersection of the corresponding reference plane perpendicular to long-pending folded axle and middle cambered surface；

Step d：Every bit in point set Gp (k) is mobile once according to given arc length L (k) along each self-corresponding intersection, obtain The turbulence columns center of circle in middle cambered surface is distributed in kth group first row；

Step e：Kth group first row is distributed in the turbulence columns center of circle in middle cambered surface along each self-corresponding intersection according to given arc Long L (k) ' is mobile several times, obtains all turbulence columns centers of circle of kth group being distributed in middle cambered surface.