Optimum design method for fan/gas compressor end wall profile and optimization platform

An optimized design, compressor technology, applied in the direction of calculation, genetic model, special data processing application, etc., can solve the problems of complex counter-pressure flow environment in the through-flow part, sharp inherent contradictions in stall margin, etc., to improve the overall aerodynamic performance, Streamlined optimization steps and a wide range of effects

Inactive Publication Date: 2018-01-09
HARBIN INST OF TECH
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  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0004] However, with the increasing aerodynamic load level of the fan / compressor stage, the reverse pressure flow environment of the flow part is becoming more and more complicated. The inherent contradiction among the four aerodynamic parameters of the machine, including pressure ratio, flow rate, efficiency and stall margin, is becoming more and more acute

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  • Optimum design method for fan/gas compressor end wall profile and optimization platform
  • Optimum design method for fan/gas compressor end wall profile and optimization platform
  • Optimum design method for fan/gas compressor end wall profile and optimization platform

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Embodiment 1

[0064] An optimal design method for the end wall profile of a fan / compressor, establishing an optimal design method for the end wall profile of a fan / compressor based on a quasi-three-dimensional system, and integrating it into a corresponding optimal design platform. The quasi-three-dimensional optimal design method includes The following steps:

[0065] Step 1: First, parameterize the original design of the axial fan hub and casing;

[0066] Step 2: extract the data information of the control point parameters, and use the cubic spline function for correlation; the correlation is to use the cubic spline function to express the original design of the axial fan hub and the shape of the casing, so as to optimize the design in the next step;

[0067] Step 3: Execute the shell script program;

[0068] Step 4: Generate new control parameters and end wall profile scheme samples;

[0069] Step 5: Use the new control parameters and end wall profile scheme samples as quasi-three-dime...

Embodiment 2

[0075] The optimization platform of the optimal design method of a fan / compressor end wall profile described in Embodiment 1, the optimal design platform of its end wall comprises the following steps:

[0076] Step 1: the user defines the optimization parameter variable name and its position in the file in the template file;

[0077] Step 2: Selection of optimization algorithm and parameter setting, setting of optimization variable range, objective function and optimization constraints;

[0078] Step 3: Carry out Step 1 and execute the DPrePro program, and input different variable values ​​to the template file;

[0079] Step 4: Input the Prcontrol.dat file, the sample parameter file;

[0080] Step 5: Execute the cubic spline function program, and calculate the end wall curve according to the control points and the cubic spline function;

[0081] Step 6: Quasi-3D S 2 Input files, geometric and aerodynamic parameter files related to fan / compressor blade design: *.tstk, *.bgp;...

Embodiment 3

[0087] The optimal design method of a kind of fan / compressor end wall molding line described in embodiment 1 first separately optimizes the design of the wheel hub molding line, and then optimizes the design of the casing molding line on this basis, and the specific steps are as follows:

[0088] Step S101: Parametric analysis and processing of the profile data of the prototype fan / compressor hub. That is, based on the original design data of the fan / compressor hub, the corresponding control point data information is extracted, and the geometric characteristics of the hub profile are expressed through the information of the control points and the cubic spline function;

[0089] Step S102: establishing a mathematical model for the optimal design of the hub shape;

[0090] The adiabatic efficiency of the fan / compressor stage is used as the objective function, and the coordinate information of the control points is used as the optimization variable to establish a mathematical mod...

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Abstract

The invention discloses an optimum design method for a fan / gas compressor end wall profile and an optimization platform. First, original design of an axial fan hub and a case is subjected to parameterization; data information of control point parameters is extracted, and correlation is performed by the adoption of a cubic spline function; a shell script program is executed; a new control parameterand end wall profile scheme sample is generated; the new control parameter and end wall profile scheme sample serves as input data needed for an exact three-dimensional S2 stream surface calculationprogram, and exact three-dimensional S2 stream surface calculation of a fan / gas compressor is performed; all target function values of the new end wall profile sample are obtained and subjected to global optimization to obtain the optimum end wall profile structure. The optimum design method for the fan / gas compressor end wall profile and the optimization platform are used for end wall profile optimum design theory research and product research of fans / gas compressors of aero-engines and other impeller machines (such as axial flow / radial flow turbines, axial flow / radial flow pumps / gas compressors and axial flow / radial flow fans).

Description

Technical field: [0001] The invention relates to an optimization design method and an optimization platform for the end wall profile of a fan / compressor. Background technique: [0002] As one of the high-tech products with high technical content and high energy density in the modern industrial field, aero-engines. Therefore, it is known as the "Pearl in the Crown" of modern industry. It is not only the heart of the aircraft and the strategic equipment of the country, but also an important symbol to measure a country's industrial foundation, technological and industrial strength, military equipment level and comprehensive national strength. The improvement of its performance has been an important research topic in this technical field. For this reason, it has never been absent in the major scientific and technological research plans of major developed countries, and has been listed as a key development goal. For example, the Integrated High Performance Turbine Engine Techno...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): G06F17/50G06N3/12
Inventor 刘洋陈焕龙李杰灵王军里
Owner HARBIN INST OF TECH
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