A method for optimizing aerodynamic matching between full three-dimensional stages of an axial flow compressor

Abstract

A method for optimizing aerodynamic matching between full three-dimensional stages of an axial flow compressor is provided. For a given axial compressor blade geometry, the RANS method is adopted, a 3-D viscous internal flow field is numerically simulated, and according to the numerical simulation results, the design target loads of each design section of the stator blade are constructed. For therotor, the target load distribution of the design section of the rotor blade is calculated, and the outlet flow boundary condition is given to ensure that the flow rate remains unchanged before and after optimization, that is to say, the purpose of completing the whole stage matching modification design of the compressor is achieved. The method can simultaneously complete quantitative design for swirl angle distribution and rotor pressure ratio distribution of an axial flow compressor stator outlet under a full three-dimensional environment. As a result, the axial compressor rotor and stator can be modified at the same time, the limitation that the traditional axial compressor aerodynamic matching modification technology can not simultaneously modify the rotor and stator blades is broken through, and an ideal aerodynamic matching effect is obtained.

Description

technical field [0001] The invention relates to the field of compressors, in particular to an aerodynamic optimization method of an axial flow compressor. Background technique [0002] Literature "Liu Zhaowei, Wu Hu, Liang Yan, Hou Chaoshan. Design method of multi-stage axial flow compressor inverse problem inter-stage aerodynamic matching[J]. Propulsion Technology, 2017,38(09):1987-1994." and literature "van Rooij M P C, Dang T Q, Larosiliere L M, Improving Aerodynamic Matching of Axial Compressor Blading Using a Three-Dimensional Multistage Inverse Design Method[J].Journal of Turbomachinery,2007,129(1):108–118.” is the closest to applying for a patent existing technology. [0003] Among them, "Multi-stage Axial Compressor Inverse Problem Interstage Aerodynamic Matching Design Method" provides a method of using full three-dimensional inverse method to complete the interstage aerodynamic matching method by setting the outlet swirl angle of the stator blades. This document ...

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Problems solved by technology

This document believes that the aerodynamic matching design needs to be in a multi-stage environment to obtain satisfactory results, but this document only studies the full three-dimensional inverse method modification design of the axial flow compressor rotor blades, and does not consider the impact of the stator blades on the compressor aerodynamics. At the same time, this document does not provide a quantitative method for the design parameters of the compressor blade during aerodynamic matching, so its aerodynamic matching scheme is more dependent on the experience of the designer, and lacks a clearer quantitative modification method

[0005] It can be seen from the existing technology that at present, the field of aerodynamic matching of compressors mostly stops at discussing the direct optimization in multi-level environment, and does not comprehensively consider the influence of internal dynamics and stationary vanes in multi-level environments on compressor aerodynamic matching; at the same time, for aerodynamic The quantitative design method of the matching problem lacks relevant conclusions, so there is no quantitative method and means to complete the aerodynamic matching between the axial flow compressor motor and the stator row

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