Abstract

Aiming at the multi-objective optimization design problem of propeller aerodynamics and noise, the three-dimensional geometric deformation of the whole blade is carried out by the free-form surface deformation method based on non-uniform rational B-spline. In order to save the calculation cost of optimization, the RANS method and the Hanson model are combined to predict pure tone noise, and the prediction accuracy is comparable to the accuracy of the FW-H equation coupled with URANS method. Kriging surrogate model and non-dominated sorting genetic algorithm are used to search for optimal value, and a multi-objective optimization design framework for propeller aerodynamics and noise is established. This method is used to optimize the blade shape of a passenger airliner propeller, and the airfoil torsion angle and chord length of different positions are optimized as design variables. Compared with the basic blade, the noise value of the axial monitoring point near the cruise configuration under the wind tunnel experiment condition is reduced by about 0.25 dB at the same time as the power is reduced. In the case of a slight increase in power, the noise is reduced by about 1 dB.

Highlights

  • Aiming at the multi⁃objective optimization design problem of propeller aerodynamics and noise, the three⁃dimensional geometric deformation of the whole blade is carried out by the free⁃form surface deformation meth⁃ od based on non⁃uniform rational B⁃spline

  • In order to save the calculation cost of optimization, the RANS method and the Hanson model are combined to predict pure tone noise, and the prediction accuracy is comparable to the accuracy of the FW⁃H equation coupled with URANS method

  • Kriging surrogate model and non⁃dominated sorting genetic algorithm are used to search for optimal value, and a multi⁃objective optimization design framework for pro⁃ peller aerodynamics and noise is established

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Summary

Introduction

关 键 词:自由曲面变形方法( FFD) ;多重参考坐标系( MRF) ;Hanson 噪声模型;非支配关系排 序算法( NSGAII) 控制点数;Bil( s) ,Bjm( u) 和 Bkn( t) 为 Bernstein 多项 式,表示为 [ 1] PAGANO A, FREDERICO L, BARBARINO M, et al Multi⁃Objective Aeroacoustic Optimization of an Aircraft Propeller[ C] ∥ 12th AIAA / ISSMO Multidisciplinary Analysis and Optimization Conference, 2008 [2] MARINUS B G, ROGER M, VAN DEN BRAEMBUSSCHE R A, et al Multidisciplinary Optimization of Propeller Blades: Focus on the Aeroacoustic Results[ C] ∥17th AIAA / CEAS Aeroacoustics Conference, 2011

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