the expansion ratio of the inlet and the outlet of a certain blade basin side channel is equal to the radius of an inscribed circle of a blade basin side outlet than the radius of an upper inscribed circle:

adjacent channel expansion ratio AR:

the AR value can influence the actual working attack angle of the blade, if the AR value is larger than 1, the actual working attack angle of the blade is more positive, and if the AR value is smaller than 1, the actual working attack angle of the blade is more negative, so that the value of the AR value is preferably in the range of 0.85-1.15.

Step S₅And carrying out expansion ratio analysis inside the channel.

Preferably, the step S₅The method also comprises the following steps: judging whether the blade load distribution is reasonable or not, and if so, entering the step S₆(ii) a If not, the expansion ratio of the internal passage of the blade needs to be optimized, and then the internal passage is returnedSaid step S₁。

And as the internal expansion ratio of the blade passage is represented to be changed in the figure 5, the larger the change slope of the expansion ratio is, the larger the load is represented, and the blade modeling scheme is adjusted to enable the expansion ratio of the internal passage of the blade to be changed uniformly.

Step S₆And carrying out full-circle three-dimensional calculation.

By carrying out full-circle three-dimensional calculation, flow field details such as isentropic Mach number distribution of all blade profile surfaces can be obtained.

Step S₇And optimizing the attack angle of each blade inlet by combining the three-dimensional calculation result and the expansion ratio change of the inlet and the outlet of each blade channel (as shown in figure 7).

Step S₈And optimizing the isentropic Mach number distribution of each blade profile surface by combining the three-dimensional calculation result and the expansion ratio change (shown in figure 5) in each blade channel.

Preferably, the step S₈The method also comprises the following steps: judging whether the optimization is completed or not, and if so, ending the optimization; if not, returning to step S₁。

According to the description, the wall-dividing support plate guide vane fusion design method provides a dimension reduction analysis means, can reduce full-ring three-dimensional numerical simulation calculation, and accelerates design convergence.

The wall-dividing support plate guide vane fusion design method provided by the invention utilizes the modeling result of the full-ring three-dimensional blade as input, carries out angle-preserving transformation on the typical height-expanding section of the full-ring three-dimensional blade profile, and expands the blade profile into the full-ring plane blade profile (as shown in figure 3). Before three-dimensional calculation is carried out, the internal expansion ratio of each blade channel of the typical overall plane blade profile height is analyzed, and the internal expansion ratio, the channel load and the attack angle of the blade modeling result are optimized, so that the three-dimensional calculation times are reduced, and the design is rapidly iterated and converged.

The blade surface loads were initially optimized by analyzing the blade channel internal expansion ratio changes, as shown in fig. 4 and 5, and in particular the profile channels (TD6 channel and TD7 channel) composed of the conventional OGV blade and the fencing vane fusion profile in fig. 6.

Wherein, R in FIG. 4_ICharacterizing the inlet passageway area for the radius of the inlet inscribed circle, R_OCharacterizing the outlet passage area for the radius of the outlet inscribed circle, R_MThe internal channel area is characterized for the internal inscribed circle radius.

In FIG. 5, the ordinate is

The channel internal expansion ratio is shown, and the abscissa is the central streamline coordinate. FIG. 5 represents the blade channel expansion ratio variation.

According to the wall dividing support plate guide vane fusion design method, the circumferential blade channels must be in uniform transition, if the transition is not uniform, the attack angle of adjacent blades is over-positive or over-negative, and the improvement of the culvert efficiency and the stability margin is not facilitated. As shown in fig. 6 and 7, the blade passage expansion ratio variation analysis is performed on the modeling result, and the expansion ratio distribution of the modeling result can be preliminarily optimized by using fig. 7.

In fig. 6, 14 channel numbers TD1 to TD14 are shown.

Wherein, FIG. 7 shows the expansion ratio distribution of each passage, and the abscissa is the expansion ratio of the inlet/outlet of the passage

The ordinate indicates the channel number.

Aiming at the difficult problem of the optimization design, the wall-dividing support plate guide vane fusion design method provides a dimension reduction design analysis method, which is used for rapidly analyzing the modeling result of the full-channel three-dimensional blade, reducing the three-dimensional analysis calculation amount, improving the optimization design efficiency and enabling the design to be rapidly iterated and converged.

In addition, the terms used in the present application are specifically explained as follows:

the support plate has the functions of transferring loads such as thrust and the like, transferring medium rigidity and the like after the traditional aircraft engine outer culvert fan blade and outer culvert guide vane.

The wall separation (hanging) refers to that the outer culvert of the traditional aero-engine is provided with the wall separation (hanging) for connecting the airplane and the engine and installing accessories such as a precooler and the like.

The guide vane is fused by the wall dividing support plate, namely the guide vane is fused into a structure which integrates three structures of a wall dividing structure, a support plate structure and an outer culvert guide vane, and the guide vane has the functions of flow guiding, diffusion, load transmission and structural connection.

The attack angle refers to the included angle between the flow angle of the incoming flow of the blade and the metal angle of the blade profile inlet.

In summary, the wall dividing support plate guide vane fusion design method has the following advantages:

the invention provides a dimension reduction analysis means aiming at the complex design of the guide vane of the fusion wall-dividing support plate, which is beneficial to the reduction of complexity and simplification of designers and the rapid summary of design experience.

The three-dimensional modeling result is used as input, and before full-circle three-dimensional calculation is carried out, the load and attack angle optimization of the full-circle blade can be carried out, so that the three-dimensional full-circle numerical simulation calculation in the optimization design process is greatly reduced, the design efficiency is obviously improved, and the design rapid convergence is facilitated.

While specific embodiments of the invention have been described above, it will be appreciated by those skilled in the art that these are by way of example only, and that the scope of the invention is defined by the appended claims. Various changes and modifications to these embodiments may be made by those skilled in the art without departing from the spirit and scope of the invention, and these changes and modifications are within the scope of the invention.

Claims

1. A fusion design method for a wall-dividing support plate guide vane is characterized by comprising the following steps:

S₃to, forSolving the radius of an inscribed circle and a central flow line of each adjacent blade channel of the unfolded planar blade profile to obtain the channel expansion ratio change on the central flow line of each blade channel and the channel expansion ratio change of an inlet and an outlet of the adjacent channel;

S₄developing expansion ratio circumferential distribution analysis;

S₅carrying out expansion ratio analysis inside the channel;

S₆carrying out full-circle three-dimensional calculation;

2. The wall-dividing strut vane fusion design method as claimed in claim 1, wherein step S₂The method specifically comprises the following steps: the typical spanwise cross-section includes a three-dimensional profile of 0% spanwise, 20% spanwise, 50% spanwise, 80% spanwise, and 100% spanwise cross-section.

3. The wall-dividing strut vane fusion design method as claimed in claim 1, wherein step S₄The method also comprises the following steps: judging whether the distribution of the attack angles of the blade profiles is reasonable or not according to the circumferential distribution of the expansion ratio, and if so, entering the step S₅(ii) a If not, optimizing the distribution of the inlet attack angle and the expansion ratio, and returning to the step S₁。

4. The wall-dividing strut vane fusion design method as claimed in claim 3, wherein step S₄If the ratio AR of the expansion ratios of the adjacent channels of the blade is greater than 1, the actual working attack angle of the blade is deflected to be positive; and if the ratio AR of the expansion ratios of the adjacent channels of the blade is less than 1, the actual working attack angle of the blade is negative.

5. The wall-dividing strut guide vane fusion design method as claimed in claim 4, wherein the ratio AR of the expansion ratio of the adjacent channels of the blade ranges from 0.85 to 1.15.

6. The wall dividing plate guide vane fusion design method as claimed in claim 1, wherein the step S₅The method also comprises the following steps: judging whether the blade load distribution is reasonable or not, and if so, entering the step S₆(ii) a If not, the expansion ratio of the internal passage of the blade needs to be optimized, and the step S is returned to₁。

7. The wall dividing strut guide vane fusion design method as claimed in claim 6, wherein the larger the change slope of the channel internal expansion ratio, the larger the characteristic load, and the blade modeling scheme needs to be adjusted to make the expansion ratio of the blade internal channel change uniformly.

8. The wall dividing plate guide vane fusion design method as claimed in claim 1, wherein the step S₆And carrying out full-circle three-dimensional calculation to obtain the isentropic Mach number distribution of all the blade profile surfaces.

9. The wall dividing plate guide vane fusion design method as claimed in claim 1, wherein the step S₈The method also comprises the following steps: judging whether the optimization is completed or not, and if so, ending the optimization; if not, returning to step S₁。

10. The wall-dividing strut vane fusion design method of claim 1, wherein the fusion blades comprise at least one wall-dividing strut vane fusion blade and a plurality of strut vane fusion blades; the culvert guide vane comprises a plurality of culvert guide vanes of a plurality of blade types.