Low-Noise Blade Design Optimization for a Transonic Fan Using Adjoint-Based MDO Approach

Abstract This paper proposes a new duty-based Smith Chart as part of an improved method of selecting the geometric topology of compressors (axial, mixed or radial) in the earliest stage of design. The method has a number of advantages over previous methods: it is based on the non-dimensional flow and the non-dimensional work, which aligns with the aerodynamic function of the compressor and is therefore more intuitive than specific speed and specific diameter. It is based on a large number of consistently designed compressor rotors which have been computationally predicted using RANS CFD. Most importantly, it provides the designer not only with a choice of topology but also with the complete meridional geometry of the compressor, its blade design and the number of blades. This fidelity of geometry at the very early stage of design allows the designer to undertake a true systems design optimization (noise, manufacturing, packaging constraints and cost). This has the major advantage of significantly reducing early stage design times and costs and allows the designer to explore completely new products more quickly.

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Comments on "CMOS low-noise amplifier design optimization techniques"

IEEE Transactions on Microwave Theory and Techniques ◽

10.1109/tmtt.2006.877051 ◽

2006 ◽

Vol 54 (7) ◽

pp. 3155 ◽

Cited By ~ 11

Author(s):

Jingxue Lu ◽

Fengyi Huang

Keyword(s):

Design Optimization ◽

Low Noise ◽

Optimization Techniques ◽

Low Noise Amplifier ◽

Amplifier Design ◽

Noise Amplifier

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1305 Aerodynamic Design Optimization of Low Noise High-Lift Airfoil for Civil Aircraft

The Proceedings of Design & Systems Conference ◽

10.1299/jsmedsd.2013.23._1305-1_ ◽

2013 ◽

Vol 2013.23 (0) ◽

pp. _1305-1_-_1305-10_

Author(s):

Ryu SHINOMIYA ◽

Masahiro KANAZAKI ◽

Mitsuhiro MURAYAMA ◽

Kazuomi YAMAMOTO

Keyword(s):

Design Optimization ◽

Low Noise ◽

Aerodynamic Design ◽

High Lift ◽

Aerodynamic Design Optimization ◽

Civil Aircraft

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Further Improvements in the SNUF Blade Design by Numerical Design Optimization Framework

Journal of Aerospace Engineering ◽

10.1061/(asce)as.1943-5525.0000794 ◽

2018 ◽

Vol 31 (1) ◽

pp. 04017081

Author(s):

WonJong Eun ◽

JiSoo Sim ◽

SangWoo Lee ◽

SangJoon Shin

Keyword(s):

Design Optimization ◽

Blade Design ◽

Optimization Framework ◽

Numerical Design

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A Novel Transonic Fan Swept Outlet Guide Vane Using 3D Design Optimization

Volume 2A: Turbomachinery ◽

10.1115/gt2014-25857 ◽

2014 ◽

Cited By ~ 1

Author(s):

Toyotaka Sonoda ◽

Giles Endicott ◽

Toshiyuki Arima ◽

Markus Olhofer

Keyword(s):

Design Optimization ◽

Guide Vane ◽

Suction Side ◽

Optimization Method ◽

Optimized Design ◽

Loss Reduction ◽

3D Design ◽

Blade Thickness ◽

Transonic Fan ◽

Blade Geometry

In our previous work on a transonic fan swept outlet guide vane (OGV) for a small turbofan engine (GT2011-46363), we showed a novel oscillatory casing profile that leads to approximately 20% loss reduction, using a numerical design optimization method. In this paper we analyze the resulting geometry of an optimization based on a blade representation which is able to realize significantly larger surface modifications. The final optimized design displays a novel blade geometry that has its maximum blade thickness at around 80% blade chord (located between the blade’s mid-chord and trailing edge) especially in the mid-span region. The flow physics explaining why this blade geometry without the oscillatory casing profile has the same loss reduction level of more than 20% at the peak efficiency point are discussed, focusing on the secondary flow and span-wise static pressure gradient on the blade suction side.

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Radial Variation in Distortion Transfer and Generation in a Highly Loaded Fan Stage From Near-Stall to Choke

Volume 2A: Turbomachinery ◽

10.1115/gt2019-91753 ◽

2019 ◽

Cited By ~ 1

Author(s):

Daniel R. Soderquist ◽

Andrew D. Orme ◽

Steven E. Gorrell ◽

Michael G. List

Keyword(s):

Performance Prediction ◽

Total Pressure ◽

Blade Design ◽

Local Power ◽

Inlet Distortion ◽

Total Temperature ◽

And Performance ◽

Transonic Fan ◽

The Relationship ◽

Operating Points

Abstract Understanding distortion transfer and generation through fan and compressor blade rows is able to assist in blade design and performance prediction. Using full annulus URANS simulations, the effects of distortion as it passes through the rotor of a transonic fan at five radial locations (10%, 30%, 50%, 70%, and 90% span) are analyzed. The inlet distortion profile is a 90-degree sector with a 15% total pressure deficit. Fourier distortion descriptors are used in this study to quantitatively describe distortion transfer and generation. Results are presented and compared for three operating points (near-stall, design, and choke). These results are used to explain the relationship between inlet total pressure distortion, pressure-induced swirl, total pressure distortion transfer, total temperature distortion generation, and circumferential rotor power variation. It is shown that very large changes in pressure-induced swirl and distortion transfer and generation occur between near-stall and design, but only small changes are seen between design and choke. The greatest changes are shown to be near the tip. Local power variations are shown to correlate with total pressure distortion transfer and total temperature distortion generation.

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Multidisciplinary Design Optimization of a Low-Noise and Efficient Next-Generation Aero-Engine Fan

Volume 2D: Turbomachinery ◽

10.1115/gt2020-14580 ◽

2020 ◽

Author(s):

Robert Jaron ◽

Antoine Moreau ◽

Sébastien Guérin ◽

Lars Enghardt ◽

Timea Lengyel-Kampmann ◽

...

Keyword(s):

Design Optimization ◽

Multidisciplinary Design Optimization ◽

Hybrid Approach ◽

Low Noise ◽

Multidisciplinary Design ◽

Noise Prediction ◽

Noise Sources ◽

Aerodynamic Efficiency ◽

Aero Engine ◽

Rans Simulations

Abstract Due to the increasing bypass ratios of modern engines, the fan stage is increasingly becoming the dominant source of engine noise. Accordingly, it is becoming more and more important to develop not only efficient but also quiet fan stages. In this paper the noise emission of a fan for an aero-engine with a bypass ratio of 19 is reduced within a multidisciplinary design optimization (MDO) by means of an hybrid noise prediction method while at the same time optimizing the aerodynamic efficiency. The aerodynamic performance of each configuration in the optimization is evaluated by stationary Reynolds-Averaged Navier-Stokes (RANS) simulations. These stationary flow simulations are also used to extract the aerodynamic excitation sources for the analytical fan noise prediction. The resulting large database of the optimization provides new insights into which extent an MDO can contribute to the design of both quiet and efficient fan stages. In addition to that the hybrid approach of numerical flow solutions and analytical description of the noise sources enables to understand the noise reduction mechanisms. In particular, the influence of rotor blade loading on the aerodynamic efficiency and the noise sources as well as the potential of configurations with a comparatively low number of outlet guide vanes (OGV) is explored. The acoustic results of selected configurations are confirmed by unsteady RANS simulations.

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