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

A technology of axial flow compressor and optimization method, which is applied in the field of compressor, can solve the problems of not comprehensively considering the impact, not giving compressor motor blades, and lacking quantitative modification methods, etc., to achieve the effect of improving adiabatic efficiency

Active Publication Date: 2019-01-08
NORTHWESTERN POLYTECHNICAL UNIV
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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 mo

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

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[0028] The present invention will be further described below in conjunction with the accompanying drawings and embodiments.

[0029] Step 1: Knowing the spatial geometry coordinates of the blades of the full three-dimensional axial flow compressor, which is called the initial blade geometry, given the total inlet temperature T0, the total inlet pressure P0, the inlet airflow angle α and the outlet back pressure p, for the given For a given axial compressor blade geometry, the Reynolds time-averaged Navier-Stokes equation (RANS) method is used to numerically solve the method. The spatial discretization adopts the JST format based on the center of the mesh body, and the time advancement adopts the hybrid display Rugge-Kutta time advancement scheme, and the turbulence model Using the B-L algebraic turbulence model, the full three-dimensional viscous internal flow field numerical simulation is carried out, and the numerical simulation results of the initial blade geometric flow fie...

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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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Application Information

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IPC IPC(8): G06F17/50
CPCG06F30/17
Inventor 侯朝山杨晨吴虎梁言刘昭威
Owner NORTHWESTERN POLYTECHNICAL UNIV
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