CN112257204B - Method for calculating S2 flow surface parameters of multistage compressor - Google Patents

Method for calculating S2 flow surface parameters of multistage compressor Download PDF

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CN112257204B
CN112257204B CN202011494951.0A CN202011494951A CN112257204B CN 112257204 B CN112257204 B CN 112257204B CN 202011494951 A CN202011494951 A CN 202011494951A CN 112257204 B CN112257204 B CN 112257204B
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翟志龙
曹传军
姜逸轩
李游
吴帆
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AECC Commercial Aircraft Engine Co Ltd
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Abstract

The invention provides a method for calculating S2 flow surface parameters of a multistage compressor, which comprises the following steps: step S1Starting calculation; step S2Acquiring full flow field parameters of the multistage compressor based on a quasi-three-dimensional S2 calculation method, wherein the full flow field parameters comprise flow field parameters of a main flow area and an end wall area of each stage of blade; based on a three-dimensional CFD calculation method, acquiring full flow field parameters of the multistage compressor, including flow field parameters of a main flow area and an end wall area of each stage of blade; step S3And merging the mainstream region parameters obtained by the quasi-three-dimensional S2 calculation method and the end wall region parameters corrected by the three-dimensional CFD calculation method to obtain new multistage compressor S2 flow surface parameters as final calculation results. The method combines the advantages of the quasi-three-dimensional S2 calculation method and the three-dimensional CFD calculation method, and overcomes the defects of severe flow field parameter change of the front edge and the tail edge of the blade calculated by the quasi-three-dimensional S2 and inaccurate flow field parameter average value of the blade channel calculated by the three-dimensional CFD.

Description

Method for calculating S2 flow surface parameters of multistage compressor
Technical Field
The invention relates to the field of pneumatic design of compressors, in particular to a method for calculating S2 flow surface parameters of a multistage compressor.
Background
In the prior art, a high-pressure compressor of an aircraft engine usually adopts a multi-stage series connection mode, the geometric profile of each row of blades is complex, and a blade body usually has complex geometric characteristics such as bending, sweeping and twisting. The blades of each stage have independent aerodynamic characteristics, the parameter difference between stages is very large, the blades and the end wall are mutually interfered and influenced, and the parameter difference between a main flow area and an end wall area is very large. It is very difficult to obtain relatively accurate results for the complete flow field in the vane channel.
The quasi-three-dimensional S2 calculation method is generally used for calculating the flow field by solving a radial balance equation, and the flow field calculation of the mainstream region is more accurate. However, in the calculation process, due to neglecting the influence of viscosity, only the flow field near the end wall is simply corrected by introducing an empirical model, so that the solution of the flow field near the end wall is obtained, the difference between the flow field parameters of the blade root and blade tip areas in the blade channel and the actual situation is large, and finally the flow field result obtained by the solution cannot truly reflect the design result.
The three-dimensional CFD calculation method is used for calculating a flow field by solving a viscosity N-S equation, and solving the flow field near the near-end wall by adopting a boundary layer equation. It is generally considered that such solution is more practical, but when the parameter of the main flow region is solved, some empirical models such as one-dimensional non-reflection and the like are adopted due to the transmission of the parameter of the interface between the blade row and the blade row.
The difference between the mainstream parameters of each stage and the actual situation is large, and particularly when the mainstream parameters of a multi-stage compressor (such as more than ten stages) are calculated and solved by using three-dimensional CFD, the calculation errors among the stages are gradually accumulated, so that the difference between the calculation result and the actual situation is gradually accumulated and amplified. The parameters of the main flow area are seriously distorted, and the error of the flow field result obtained by final solution is larger.
The quasi-three-dimensional S2 calculation method and the three-dimensional CFD calculation method have the following problems:
firstly, the difference between the parameters of the multistage compressor flow field obtained by adopting the quasi-three-dimensional S2 calculation method in the blade root and blade tip areas and the actual situation is larger, so that the deviation between the calculation result and the actual result is larger.
Secondly, the difference between the flow field of the multistage compressor obtained by adopting the three-dimensional CFD calculation method and the actual situation is larger in the mainstream region, so that the deviation between the calculation result and the actual result is larger.
In view of the above, in order to overcome the defects of the two design methods, the invention provides a method for generating a compressor flow field parameter closer to a real situation by combining the respective advantages of the quasi-three-dimensional S2 calculation method and the three-dimensional CFD calculation method.
Disclosure of Invention
The invention provides a method for calculating S2 flow surface parameters of a multistage compressor, aiming at overcoming the defect that the difference between the actual situation and the multistage gas flow field parameters obtained by a quasi-three-dimensional S2 calculation method and a three-dimensional CFD calculation method in the prior art is large.
The invention solves the technical problems through the following technical scheme:
a method for calculating S2 flow surface parameters of a multistage compressor is characterized in that the method for calculating S2 flow surface parameters of the multistage compressor comprises the following steps:
step S1Starting calculation;
step S2Acquiring full flow field parameters of the multistage compressor based on a quasi-three-dimensional S2 calculation method, wherein the full flow field parameters comprise flow field parameters of a main flow area and an end wall area of each stage of blade; based on a three-dimensional CFD calculation method, acquiring full flow field parameters of the multistage compressor, including flow field parameters of a main flow area and an end wall area of each stage of blade;
step S3And merging the mainstream region parameters obtained by the quasi-three-dimensional S2 calculation method and the end wall region parameters corrected by the three-dimensional CFD calculation method to obtain new multistage compressor S2 flow surface parameters as final calculation results.
According to an embodiment of the invention, said step S2The method specifically comprises the following steps:
step S21Performing flow field solving according to a quasi-three-dimensional S2 calculation method to obtain flow field parameter distribution of each stage of blades of the multistage compressor, including flow field parameters of a main flow region and an end wall region;
step S22And judging whether a full flow field is obtainedA parameter; if yes, go to step S3(ii) a If not, returning to the step S21And restarting the quasi-three-dimensional S2 calculation method to solve the flow field.
According to an embodiment of the invention, said step S2The method specifically comprises the following steps:
step S21’Performing flow field solution according to a three-dimensional CFD calculation method to obtain flow field parameter distribution of each stage of blades of the multistage gas compressor, wherein the flow field parameter distribution comprises flow field parameters of a main flow area and an end wall area;
step S22’Judging whether the parameters of the full flow field are obtained or not; if yes, go to step S3(ii) a If not, returning to the step S21’And restarting the three-dimensional CFD calculation method to solve the flow field.
According to an embodiment of the invention, said step S3The method specifically comprises the following steps:
step S31Summarizing the step S21And step S21’Obtaining flow field parameters;
step S32Merging data to obtain new flow field parameters;
step S33And finishing all calculations.
According to one embodiment of the invention, the multistage compressor comprises n stages of blades, wherein n is a natural number and n is more than or equal to 5, and the step S32Comprises the following steps:
step S321Aiming at the leading edge parameter or the trailing edge parameter of the first-stage blade, directly adopting a calculation result of a quasi-three-dimensional S2 calculation method in an area of which the span (x) is more than or equal to 0.1 and less than or equal to 0.9 of the new flow field parameter;
step S322For span (x)>0.9 field flow parameters, and span (x)<And (3) correcting the flow field parameters of the 0.1 area according to the calculation result of the three-dimensional CFD calculation method.
According to an embodiment of the invention, said step S322The method also comprises the following steps:
dividing the flow field parameters of the span (x) >0.9 area obtained by the three-dimensional CFD calculation method by the flow field parameters at the span (x) =0.9 position respectively to obtain a group of coefficients, and multiplying the coefficients by the flow field parameters of the span (x) =0.9 position obtained by the quasi-three-dimensional S2 calculation method to obtain new flow field parameters of the span (x) >0.9 area;
dividing the flow field parameters of the span (x) <0.1 region obtained by the three-dimensional CFD calculation method by the flow field parameters at the span (x) =0.1 position respectively to obtain a group of coefficients, and multiplying the coefficients by the flow field parameters of the span (x) =0.1 position obtained by the quasi-three-dimensional S2 calculation method to obtain the flow field parameters of a new span (x) <0.1 region;
and combining the flow field parameters of the areas of new span (x) <0.1, span (x) <0.1 ≤ and (x) < 0.9, and span (x) >0.9 according to the leading edge parameters or the trailing edge parameters of the first-stage blade to obtain the new flow field parameters with complete corresponding section positions.
According to one embodiment of the invention, the multistage compressor comprises n stages of blades, wherein n is a natural number and n is more than or equal to 5, and the step S32Comprises the following steps:
step S321’Aiming at the leading edge parameter or the trailing edge parameter of the nth-stage blade, directly adopting a calculation result of a quasi-three-dimensional S2 calculation method in an area where span (x) is more than or equal to 0.2 and less than or equal to 0.8 of the new flow field parameter;
step S322’For span (x)>0.8 area of flow field parameters, and span (x)<And (3) correcting the flow field parameters of the 0.2 area according to the calculation result of the three-dimensional CFD calculation method.
According to an embodiment of the invention, said step S322’The method also comprises the following steps:
dividing the flow field parameters of the span (x) >0.8 area obtained by the three-dimensional CFD calculation method by the flow field parameters at the span (x) =0.8 position respectively to obtain a group of coefficients, and multiplying the coefficients by the flow field parameters of the span (x) =0.8 position obtained by the quasi-three-dimensional S2 calculation method to obtain new flow field parameters of the span (x) >0.8 area;
dividing the flow field parameters of the span (x) <0.2 area calculated by the three-dimensional CFD calculation method by the flow field parameters at the span (x) =0.2 position respectively to obtain a group of coefficients, and multiplying the coefficients by the flow field parameters of the span (x) =0.2 position obtained by the quasi-three-dimensional S2 calculation method to obtain the flow field parameters of a new span (x) <0.2 area;
and aiming at the leading edge parameter or the trailing edge parameter of the nth-stage blade, merging the flow field parameters of the areas of new span (x) <0.2, span (x) <0.2 and span (x) < 0.8, and span (x) >0.8 to obtain the flow field parameter with complete corresponding section position.
According to one embodiment of the invention, the multistage compressor comprises n stages of blades, wherein n is a natural number and n is more than or equal to 5, and the step S32Comprises the following steps:
step S321’’Aiming at the leading edge parameter or the trailing edge parameter of the blade of the (n/2) th or (n +1)/2 th stage, directly adopting the calculation result of the quasi-three-dimensional S2 calculation method in the area of 0.15-span (x) -0.85 of the new flow field parameter;
when n is an odd number, taking the (n + 1)/2-stage blade; when n is an even number, taking the n/2-stage blade;
step S322’’For span (x)>Flow field parameters of region 0.85, and span (x)<And (5) correcting the flow field parameters of the 0.15 area according to the calculation result of the three-dimensional CFD calculation method.
According to an embodiment of the invention, said step S322’’The method also comprises the following steps:
dividing the flow field parameters of the span (x) >0.85 area calculated by the three-dimensional CFD calculation method by the flow field parameters of the span (x) =0.85 area respectively to obtain a group of coefficients, and multiplying the coefficients by the flow field parameters of the span (x) =0.85 area calculated by the quasi-three-dimensional S2 calculation method to obtain new flow field parameters of the span (x) >0.85 area;
dividing the flow field parameters of the span (x) <0.15 area calculated by the three-dimensional CFD calculation method by the flow field parameters of the span (x) =0.15 area respectively to obtain a group of coefficients, and multiplying the coefficients by the flow field parameters of the span (x) =0.15 area calculated by the quasi-three-dimensional S2 calculation method to obtain new flow field parameters of the span (x) <0.15 area;
aiming at the leading edge parameter or the trailing edge parameter of the (n/2) th or (n +1)/2 th stage blade, combining the flow field parameters of the new area of span (x) <0.15, span (x) < 0.85 and span (x) >0.85 to obtain the flow field parameter with complete corresponding section position.
The positive progress effects of the invention are as follows:
the method for calculating the flow surface parameters of the multistage compressor S2 combines the advantages of the quasi-three-dimensional S2 calculation method and the three-dimensional CFD calculation method, and overcomes the defects of severe flow field parameter changes of the front edge and the tail edge of the blade calculated by the quasi-three-dimensional S2 and inaccurate flow field parameter average values of the blade channel calculated by the three-dimensional CFD on the basis of the method for calculating the flow field by the quasi-three-dimensional S2 and the method for calculating the flow field by the three-dimensional CFD.
The method for calculating the flow surface parameters of the multi-stage compressor S2 provides a new flow field parameter generation method, can quickly obtain a flow field result, provides targeted suggestions for blade flow field analysis and blade profile optimization design, and improves design accuracy.
Drawings
The above and other features, properties and advantages of the present invention will become more apparent from the following description of the embodiments with reference to the accompanying drawings in which like reference numerals denote like features throughout the several views, wherein:
fig. 1 is a schematic view of the aerodynamic layout of the multi-stage compressor in the calculation method of the flow surface parameters of the S2 of the multi-stage compressor.
Fig. 2 is a flowchart of a method for calculating the flow surface parameters of the multistage compressor S2 according to the present invention.
Fig. 3 is a schematic diagram of a calculation method of S2 flow surface parameters of the multistage compressor, a quasi-three-dimensional S2 calculation method, a three-dimensional CFD calculation method and temperature distribution obtained by test results.
Detailed Description
In order to make the aforementioned objects, features and advantages of the present invention comprehensible, embodiments accompanied with figures are described in detail below.
Embodiments of the present invention will now be described in detail with reference to the accompanying drawings. Reference will now be made in detail to the preferred embodiments of the present invention, examples of which are illustrated in the accompanying drawings. Wherever possible, the same reference numbers will be used throughout the drawings to refer to the same or like parts.
Further, although the terms used in the present invention are selected from publicly known and used terms, some of the terms mentioned in the description of the present invention may be selected by the applicant at his or her discretion, the detailed meanings of which are described in relevant parts of the description herein.
Furthermore, it is required that the present invention is understood, not simply by the actual terms used but by the meaning of each term lying within.
Fig. 1 is a schematic view of the aerodynamic layout of the multi-stage compressor in the calculation method of the flow surface parameters of the S2 of the multi-stage compressor.
As shown in fig. 1, in a typical multi-stage compressor aerodynamic layout, the inner and flow channels are both rotors, and the middle is a vane at each stage, where IGV is a guide vane, R1 is a first-stage rotor vane, and S1 is a first-stage stator vane. By parity of reasoning, the airflow is discharged out of the compressor after being pressurized by each stage of blades.
S2 flow surface parameter calculation is to calculate the distribution form of pressure, temperature and other parameters along the height of the blade after the airflow flows through each stage of blade.
The inner and outer absolute radii of each row of stators are respectively marked as Rhi and Rti, for example, the inner diameter of the first stage stator blade is Rh1, the outer diameter is Rt1, the inner diameter of the tenth stage stator blade is Rh10, and the outer diameter is Rt 10. Taking the first stage as an example, the radius of the middle area between the inner diameter and the outer diameter is denoted as Rx, and is normalized by span (x) = (Rx-Rh1)/(Rt1-Rh1) along the radial direction, where x is the height of an arbitrary cross-sectional position.
Fig. 2 is a flowchart of a method for calculating the flow surface parameters of the multistage compressor S2 according to the present invention. Fig. 3 is a schematic diagram of a calculation method of S2 flow surface parameters of the multistage compressor, a quasi-three-dimensional S2 calculation method, a three-dimensional CFD calculation method and temperature distribution obtained by test results.
As shown in fig. 2 and fig. 3, the invention discloses a method for calculating a flow surface parameter of a multistage compressor S2, which comprises the following steps:
step S1And starting the calculation.
Step S2Obtaining full flow field parameters of the multistage compressor based on a quasi-three-dimensional S2 calculation method, wherein the full flow field parameters comprise flow field parameters of a main flow area and an end wall area of each stage of bladeCounting; based on a three-dimensional CFD calculation method, the full flow field parameters of the multistage compressor are obtained, including the flow field parameters of the main flow area and the end wall area of each stage of blade.
Preferably, the step S2 specifically includes:
step S21And performing flow field solving according to a quasi-three-dimensional S2 calculation method to obtain the flow field parameter distribution of each stage of blade of the multistage compressor, including the flow field parameters of a main flow region and an end wall region.
For example, taking the temperature calculation result as an example, and taking the ten-stage stator blades as an example, as shown in fig. 3, the curve 11 is the distribution of the leading edge temperature of the first-stage stator blade along the blade height obtained by the quasi-three-dimensional S2 calculation method, and the curve 21 is the distribution of the leading edge temperature of the tenth-stage stator blade along the blade height obtained by the quasi-three-dimensional S2 calculation method.
Step S22Judging whether the parameters of the full flow field are obtained or not; if yes, go to step S3(ii) a If not, returning to the step S21And restarting the quasi-three-dimensional S2 calculation method to solve the flow field.
At the same time, the step S2The method specifically comprises the following steps:
step S21’And solving the flow field according to a three-dimensional CFD calculation method to obtain the flow field parameter distribution of each stage of blade of the multistage compressor, including the flow field parameters of the main flow area and the end wall area.
For example, taking the temperature calculation result as an example and each stage of blades is ten stages of stator blades as an example, as shown in fig. 3, a curve 14 is the distribution of the leading edge temperature of the first stage stator blade along the blade height obtained by the three-dimensional CFD calculation method, and a curve 24 is the distribution of the leading edge temperature of the first stage stator blade along the blade height obtained by the three-dimensional CFD calculation method.
Step S22’Judging whether the parameters of the full flow field are obtained or not; if yes, go to step S3(ii) a If not, returning to the step S21’And restarting the three-dimensional CFD calculation method to solve the flow field.
Step S3The mainstream region parameters obtained by the quasi-three-dimensional S2 calculation method and the corrected mainstream region parameters based on the three-dimensional CFD calculation methodThe end wall area parameters are combined to obtain new flow surface parameters of the multistage compressor S2 as final calculation results.
Preferably, the step S3The method specifically comprises the following steps:
step S31Summarizing the step S21And step S21’And obtaining the flow field parameters.
Step S32And merging data to obtain new flow field parameters.
Assuming that the multistage compressor comprises n stages of blades, wherein n is a natural number and is more than or equal to 5, the step S32Specifically, data merging is performed according to the following rules:
step S321And aiming at the leading edge parameter or the trailing edge parameter of the first-stage blade, directly adopting the calculation result of the quasi-three-dimensional S2 calculation method in the area of the new flow field parameter, wherein the span (x) is more than or equal to 0.1 and less than or equal to 0.9.
Step S322For span (x)>0.9 field flow parameters, and span (x)<And (3) correcting the flow field parameters of the 0.1 area according to the calculation result of the three-dimensional CFD calculation method.
Further, step S322The specific calculation method comprises the following steps: span (x) obtained by calculating a three-dimensional CFD calculation method>Dividing the flow field parameter of the 0.9 area by the flow field parameter at the span (x) =0.9 position respectively to obtain a group of coefficients, multiplying the coefficients by the flow field parameter at the span (x) =0.9 position obtained by the quasi-three-dimensional S2 calculation method to obtain a new span (x)>Flow field parameters of region 0.9.
Dividing the flow field parameters of the span (x) <0.1 region obtained by the three-dimensional CFD calculation method by the flow field parameters at the span (x) =0.1 position respectively to obtain a group of coefficients, and multiplying the coefficients by the flow field parameters of the span (x) =0.1 position obtained by the quasi-three-dimensional S2 calculation method to obtain the flow field parameters of the new span (x) <0.1 region.
And combining the flow field parameters of the areas of new span (x) <0.1, span (x) <0.1 ≤ and (x) < 0.9, and span (x) >0.9 according to the leading edge parameters or the trailing edge parameters of the first-stage blade to obtain the new flow field parameters with complete corresponding section positions.
Similarly, assuming that the multistage compressor comprises n stages of blades, wherein n is a natural number and is more than or equal to 5, the step S32Specifically, data merging is also performed according to the following rules:
step S321’And aiming at the leading edge parameter or the trailing edge parameter of the nth-stage blade, directly adopting the calculation result of the quasi-three-dimensional S2 calculation method in the area of 0.2-span (x) -0.8 of the new flow field parameter.
Step S322’For span (x)>0.8 area of flow field parameters, and span (x)<And (3) correcting the flow field parameters of the 0.2 area according to the calculation result of the three-dimensional CFD calculation method.
Further, step S322’The specific calculation method comprises the following steps: span (x) obtained by calculating a three-dimensional CFD calculation method>Dividing the flow field parameter of the 0.8 area by the flow field parameter at the span (x) =0.8 position respectively to obtain a group of coefficients, multiplying the coefficients by the flow field parameter at the span (x) =0.8 position obtained by the quasi-three-dimensional S2 calculation method to obtain a new span (x)>Flow field parameters of region 0.8.
Dividing the flow field parameters of the span (x) <0.2 region calculated by the three-dimensional CFD calculation method by the flow field parameters at the span (x) =0.2 position respectively to obtain a set of coefficients, and multiplying the coefficients by the flow field parameters of the span (x) =0.2 position obtained by the quasi-three-dimensional S2 calculation method to obtain the flow field parameters of the new span (x) <0.2 region.
And aiming at the leading edge parameter or the trailing edge parameter of the nth-stage blade, merging the flow field parameters of the areas of new span (x) <0.2, span (x) <0.2 and span (x) < 0.8, and span (x) >0.8 to obtain the flow field parameter with complete corresponding section position.
Similarly, assuming that the multistage compressor comprises n stages of blades, wherein n is a natural number and is more than or equal to 5, the step S32Specifically, data merging is also performed according to the following rules:
step S321’’And aiming at the leading edge parameter or the trailing edge parameter of the blade of the (n/2) th or (n +1)/2 th stage, directly adopting the calculation result of the quasi-three-dimensional S2 calculation method in the area of 0.15 equal to or less than span (x) equal to or less than 0.85 of the new flow field parameter.
Here, when n is an odd number, the (n + 1)/2-stage blade is taken; and when n is an even number, taking the blade of the nth/2 stage.
Step S322’’For span (x)>Flow field parameters of region 0.85, and span (x)<And (5) correcting the flow field parameters of the 0.15 area according to the calculation result of the three-dimensional CFD calculation method.
Further, step S322’’The specific calculation method comprises the following steps: span (x) calculated by three-dimensional CFD calculation method>Dividing the flow field parameter of the 0.85 area by the flow field parameter of the span (x) =0.85 area to obtain a group of coefficients, multiplying the coefficients by the flow field parameter of the span (x) =0.85 area calculated by the quasi-three-dimensional S2 calculation method to obtain a new span (x)>Flow field parameters of the 0.85 region.
Dividing the flow field parameters of the span (x) <0.15 area calculated by the three-dimensional CFD calculation method by the flow field parameters of the span (x) =0.15 area respectively to obtain a group of coefficients, and multiplying the coefficients by the flow field parameters of the span (x) =0.15 area calculated by the quasi-three-dimensional S2 calculation method to obtain new flow field parameters of the span (x) <0.15 area.
Aiming at the leading edge parameter or the trailing edge parameter of the (n/2) th or (n +1)/2 th stage blade, combining the flow field parameters of the new area of span (x) <0.15, span (x) < 0.85 and span (x) >0.85 to obtain the flow field parameter with complete corresponding section position.
Here, the blades of the multistage compressor may be stator blades or rotor blades, and the number of the blades is only an example and is not limited thereto, and the analogy may be made according to the principle of the above steps.
For example, the multistage compressor adopts ten-stage blades, and is suitable for the step S for the leading edge parameter or the trailing edge parameter of the first-stage blade321And step S322(ii) a For the leading edge parameter or the trailing edge parameter of the tenth stage blade, the above step S is applied321’And step S322’(ii) a For the leading edge parameter or the trailing edge parameter of the fifth stage blade, the above step S is applied321’’And step S322’’。
In addition, for other levels of position parameters, calculation is carried out according to a similar method, and only the areas adopted by the flow field parameter combination are different, and linear interpolation calculation is carried out according to the proportion.
Finally, step S33And finishing all calculations.
Thus, the curve 13 and the curve 23 shown in fig. 3 are obtained, and the curves 12 and 22 are respectively test results, so that the calculation method of the flow surface parameter of the multistage compressor S2 is closer to the test results.
As shown in fig. 3, the flow field parameters take temperature as an example, the multistage compressor takes ten-stage stator blades as an example, and the curve 11 is the temperature distribution of the leading edge of the first-stage stator blade calculated in S2;
curve 12 is the first stage stator vane leading edge temperature distribution as measured experimentally;
the curve 13 is the temperature distribution of the leading edge of the first-stage stator blade obtained by the calculation method of the flow surface parameters of the multistage compressor S2;
curve 14 is the first stage stator vane leading edge temperature distribution obtained by the three-dimensional CFD calculation method;
the curve 21 is the temperature distribution of the leading edge of the tenth-stage stator blade obtained by the quasi-three-dimensional S2 calculation method;
curve 22 is the temperature distribution of the leading edge of the tenth-stage stator blade measured by the test;
the curve 23 is the temperature distribution of the leading edge of the tenth-stage stator blade calculated by the calculation method of the flow surface parameters of the multistage compressor S2;
curve 24 is the tenth stage stator blade leading edge temperature distribution calculated by the three-dimensional CFD.
The calculation method of the flow surface parameters of the multi-stage compressor S2 can accurately obtain the average result of the flow field and accurately evaluate the design scheme.
In summary, the calculation method for the flow surface parameters of the multistage compressor S2 combines the respective advantages of the quasi-three-dimensional S2 calculation method and the three-dimensional CFD calculation method, and overcomes the defects of severe variation of the flow field parameters of the leading edge and the trailing edge of the blade calculated by the quasi-three-dimensional S2 and inaccurate average values of the flow field parameters of the blade channel calculated by the three-dimensional CFD based on the method for calculating the flow field by the quasi-three-dimensional S2 and the method for calculating the flow field by the three-dimensional CFD.
The method for calculating the flow surface parameters of the multi-stage compressor S2 provides a new flow field parameter generation method, can quickly obtain a flow field result, provides targeted suggestions for blade flow field analysis and blade profile optimization design, and improves design accuracy.
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 (7)

1. A method for calculating S2 flow surface parameters of a multistage compressor is characterized in that the method for calculating S2 flow surface parameters of the multistage compressor comprises the following steps:
step S1Starting calculation;
step S2Acquiring full flow field parameters of the multistage compressor based on a quasi-three-dimensional S2 calculation method, wherein the full flow field parameters comprise flow field parameters of a main flow area and an end wall area of each stage of blade; based on a three-dimensional CFD calculation method, acquiring full flow field parameters of the multistage compressor, including flow field parameters of a main flow area and an end wall area of each stage of blade;
step S3Merging the mainstream region parameters obtained by the quasi-three-dimensional S2 calculation method and the end wall region parameters corrected based on the three-dimensional CFD calculation method to obtain new multistage compressor S2 flow surface parameters serving as final calculation results;
said step S2The method specifically comprises the following steps:
step S21Performing flow field solving according to a quasi-three-dimensional S2 calculation method to obtain flow field parameter distribution of each stage of blades of the multistage compressor, including flow field parameters of a main flow region and an end wall region;
step S22Judging whether the parameters of the full flow field are obtained or not; if yes, go to step S3(ii) a If not, returning to the step S21Restarting the quasi-three-dimensional S2 calculation method to solve the flow field;
said step S2The method specifically comprises the following steps:
step S21’Performing flow field solution according to a three-dimensional CFD calculation method to obtain flow field parameter distribution of each stage of blades of the multistage gas compressor, wherein the flow field parameter distribution comprises flow field parameters of a main flow area and an end wall area;
step S22’Judging whether the parameters of the full flow field are obtained or not; if yes, go to step S3(ii) a If not, returning to the step S21’Restarting the three-dimensional CFD calculation method to solve the flow field;
said step S3The method specifically comprises the following steps:
step S31Summarizing the step S21And step S21’Obtaining flow field parameters;
step S32Merging data to obtain new flow field parameters;
step S33And finishing all calculations.
2. The method for calculating S2 flow surface parameters of multi-stage compressor of claim 1, wherein the multi-stage compressor comprises n stages of blades, where n is a natural number and n ≧ 5, and step S32Comprises the following steps:
step S321Aiming at the leading edge parameter or the trailing edge parameter of the first-stage blade, directly adopting a calculation result of a quasi-three-dimensional S2 calculation method in an area of which the span (x) is more than or equal to 0.1 and less than or equal to 0.9 of the new flow field parameter;
step S322For span (x)>0.9 field flow parameters, and span (x)<And (3) correcting the flow field parameters of the 0.1 area according to the calculation result of the three-dimensional CFD calculation method.
3. The method for calculating S2 flow surface parameters of multi-stage compressor according to claim 2, wherein the step S322The method also comprises the following steps:
dividing the flow field parameters of the span (x) >0.9 area obtained by the three-dimensional CFD calculation method by the flow field parameters at the span (x) =0.9 position respectively to obtain a group of coefficients, and multiplying the coefficients by the flow field parameters of the span (x) =0.9 position obtained by the quasi-three-dimensional S2 calculation method to obtain new flow field parameters of the span (x) >0.9 area;
dividing the flow field parameters of the span (x) <0.1 region obtained by the three-dimensional CFD calculation method by the flow field parameters at the span (x) =0.1 position respectively to obtain a group of coefficients, and multiplying the coefficients by the flow field parameters of the span (x) =0.1 position obtained by the quasi-three-dimensional S2 calculation method to obtain the flow field parameters of a new span (x) <0.1 region;
and combining the flow field parameters of the areas of new span (x) <0.1, span (x) <0.1 ≤ and (x) < 0.9, and span (x) >0.9 according to the leading edge parameters or the trailing edge parameters of the first-stage blade to obtain the new flow field parameters with complete corresponding section positions.
4. The method for calculating S2 flow surface parameters of multi-stage compressor of claim 1, wherein the multi-stage compressor comprises n stages of blades, where n is a natural number and n ≧ 5, and step S32Comprises the following steps:
step S321’Aiming at the leading edge parameter or the trailing edge parameter of the nth-stage blade, directly adopting a calculation result of a quasi-three-dimensional S2 calculation method in an area where span (x) is more than or equal to 0.2 and less than or equal to 0.8 of the new flow field parameter;
step S322’For span (x)>0.8 area of flow field parameters, and span (x)<And (3) correcting the flow field parameters of the 0.2 area according to the calculation result of the three-dimensional CFD calculation method.
5. The method for calculating S2 flow surface parameters of multi-stage compressor according to claim 4, wherein the step S322’The method also comprises the following steps:
dividing the flow field parameters of the span (x) >0.8 area obtained by the three-dimensional CFD calculation method by the flow field parameters at the span (x) =0.8 position respectively to obtain a group of coefficients, and multiplying the coefficients by the flow field parameters of the span (x) =0.8 position obtained by the quasi-three-dimensional S2 calculation method to obtain new flow field parameters of the span (x) >0.8 area;
dividing the flow field parameters of the span (x) <0.2 area calculated by the three-dimensional CFD calculation method by the flow field parameters at the span (x) =0.2 position respectively to obtain a group of coefficients, and multiplying the coefficients by the flow field parameters of the span (x) =0.2 position obtained by the quasi-three-dimensional S2 calculation method to obtain the flow field parameters of a new span (x) <0.2 area;
and aiming at the leading edge parameter or the trailing edge parameter of the nth-stage blade, merging the flow field parameters of the areas of new span (x) <0.2, span (x) <0.2 and span (x) < 0.8, and span (x) >0.8 to obtain the flow field parameter with complete corresponding section position.
6. The method for calculating S2 flow surface parameters of multi-stage compressor of claim 1, wherein the multi-stage compressor comprises n stages of blades, where n is a natural number and n ≧ 5, and step S32Comprises the following steps:
step S321’’Aiming at the leading edge parameter or the trailing edge parameter of the blade of the (n/2) th or (n +1)/2 th stage, directly adopting the calculation result of the quasi-three-dimensional S2 calculation method in the area of 0.15-span (x) -0.85 of the new flow field parameter;
when n is an odd number, taking the (n + 1)/2-stage blade; when n is an even number, taking the n/2-stage blade;
step S322’’For span (x)>Flow field parameters of region 0.85, and span (x)<And (5) correcting the flow field parameters of the 0.15 area according to the calculation result of the three-dimensional CFD calculation method.
7. The method for calculating S2 flow surface parameters of multi-stage compressor of claim 6, wherein the step S322’’The method also comprises the following steps:
dividing the flow field parameters of the span (x) >0.85 area calculated by the three-dimensional CFD calculation method by the flow field parameters of the span (x) =0.85 area respectively to obtain a group of coefficients, and multiplying the coefficients by the flow field parameters of the span (x) =0.85 area calculated by the quasi-three-dimensional S2 calculation method to obtain new flow field parameters of the span (x) >0.85 area;
dividing the flow field parameters of the span (x) <0.15 area calculated by the three-dimensional CFD calculation method by the flow field parameters of the span (x) =0.15 area respectively to obtain a group of coefficients, and multiplying the coefficients by the flow field parameters of the span (x) =0.15 area calculated by the quasi-three-dimensional S2 calculation method to obtain new flow field parameters of the span (x) <0.15 area;
aiming at the leading edge parameter or the trailing edge parameter of the (n/2) th or (n +1)/2 th stage blade, merging the flow field parameters of the new regions of span (x) <0.15, span (x) < 0.85 and span (x) >0.85 to obtain the flow field parameter with complete corresponding section position.
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