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Technical Brief

Surrogate-Model-Based Liner Optimization for Aeroengines and Comparison with Finite Elements

[+] Author and Article Information
Hanbo Jiang

Department of Mechanical and Aerospace Engineering, The Hong Kong University of Science and Technology, Clear Water Bay, Kowloon, Hong Kong, China
hb.jiang@connect.ust.hk

Alex Siu Hong Lau

Department of Mechanical and Aerospace Engineering, The Hong Kong University of Science and Technology, Clear Water Bay, Kowloon, Hong Kong, China
alexshlau@ust.hk

Xun Huang

State Key Laboratory of Turbulence and Complex System, Department of Aeronautics and Astronautics, College of Engineering, Peking University, Beijing, 100871, China; Department of Mechanical and Aerospace Engineering, The Hong Kong University of Science and Technology, Clear Water Bay, Kowloon, Hong Kong, China
huangxun@pku.edu.cn
huangxun@ust.hk

1Corresponding author.

ASME doi:10.1115/1.4038680 History: Received June 09, 2017; Revised September 25, 2017

Abstract

Numerical optimizations are very useful in liner designs for low-noise aeroengines. Although modern computational tools are already very efficient for a single aeroengine noise propagation simulation run, the prohibitively high computational cost of a broadband liner optimization process which requires hundreds of thousands of runs renders these tools unsuitable for such task. To enable rapid optimization using a desktop computer, an efficient analytical solver based on the Wiener-Hopf method is proposed in the current study. Although a Wiener-Hopf-based solver can produce predictions very quickly (order of a second), it usually assumes an idealized straight duct configuration with a uniform background flow that makes it arguable for practical applications. In the current study, we employ the Wiener-Hopf method in our solver to produce an optimized liner design for a semi-infinite annular duct set-up, and compare its noise-reduction effect with an optimized liner designed by the direct application of a numerical finite element solver for a practical aeroengine intake configuration with an inhomogeneous background flow. The near-identical near- and far-field solutions by the Wiener-Hopf-based method and the finite element solvers clearly demonstrate the accuracy and high efficiency of the proposed optimization strategy. Therefore, the current Wiener-Hopf solver is highly effective for liner optimizations with practical set-ups, and is very useful to the preliminary design process of low-noise aeroengines.

Copyright (c) 2017 by ASME
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