A 3D Parameterization for Transonic Fan Blade Multidisciplinary Design

Trépanier, Jean‐Yves

doi:10.15406/aaoaj.2017.01.00004

Cited by 4 publications

(2 citation statements)

References 14 publications

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“…For aerodynamic optimization of multistage axial flow compressors, the aim is to find a parametric method to reduce the design variables and achieve dimensionality reduction while retaining as much of the optimal solution from the original design space as possible. The traditional parametric method has remarkably high-dimensional characteristics because each section of the blade is modeled separately and independently of each other [24]. An effective method to constrain the control parameters of each section is the surface parametric method, which was first applied in outflow aerodynamic optimization and is an effective dimensionality reduction method [25][26][27][28].…”

Section: Introductionmentioning

confidence: 99%

Design Optimization of a Multistage Axial Flow Compressor Based on Full-Blade Surface Parameterization and Phased Strategy

Cheng

Zhao

Dong

et al. 2021

International Journal of Aerospace Engineering

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A new design optimization method is proposed for the problem of high-precision aerodynamic design of multistage axial compressors. The method mainly contains three aspects: full-blade surface parametrization can significantly reduce the number of control variables per blade row and increase the degrees of freedom of the leading edge blade angle compared with the traditional semiblade parametric method; secondly, the artificial bee colony algorithm improved initialization and food source exploration and exploitation mechanism to enhance the global optimization ability and convergence speed, and a distributed optimization system is built on the supercomputing platform based on this method; finally, a phased optimization strategy based on the “synchronous change in multirow blades” is proposed, and expert experience is introduced to achieve a better balance between exploration and exploitation. The optimization method is applied to the AL-31F four-stage low-pressure compressor. As a result, the adiabatic efficiency is improved by 0.67% and the surge margin is improved by 3.1% under the premise that the total pressure ratio and mass flow rate satisfy the constraints, which verifies the effectiveness and engineering practicality of the proposed optimization method in the field of multistage axial flow compressor aerodynamic optimization.

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Section: Introductionmentioning

confidence: 99%

Design Optimization of a Multistage Axial Flow Compressor Based on Full-Blade Surface Parameterization and Phased Strategy

Cheng

Zhao

Dong

et al. 2021

International Journal of Aerospace Engineering

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“…Applying the "man-in-the-loop" concept from the perspective of the parameterization method is an important way to reduce the design space and the optimization time. Trepanier et al [40] used a parameterization method that combined global scope and local scope to optimize compressor blades and introduced the design experience in the process, which achieved their optimization goal. Guangwen et al [41] used the recursive algorithm of the Bezier curve to optimize the compressor blade profile by a multilevel parameterization method, which accelerated the convergence process.…”

Section: Introductionmentioning

confidence: 99%

Research on Aerodynamic Optimization Method of Multistage Axial Compressor under Multiple Working Conditions Based on Phased Parameterization Strategy

Cheng

Dong

Zhao

et al. 2021

Mathematical Problems in Engineering

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Multistage axial compressor is the key component of aeroengine and gas turbine to realize energy conversion. In order to avoid the “curse of dimensionality” problem in the global optimization process of AL-31F four-stage low-pressure compressor under multiple working conditions, an optimization method based on phased parameterization strategy is proposed. The method uses the idea of “exploration before exploitation” for reference and divides the optimization process into two phases. In the first phase, the traditional parametric modification method based on stacking line is adopted; in the second phase, the full-blade surface parametric modification method with significant low-dimensional characteristics is adopted. Based on the improved artificial bee colony algorithm, a multitask concurrent optimization system is built on the supercomputing platform, and the engineering optimization solution is obtained within 91 hours. The optimization results are as follows: under the condition of meeting the constraints, the adiabatic efficiency is increased by 0.3% and the surge margin is 4.0% at the design speed; the adiabatic efficiency is increased by 0.8% and the surge margin is 2.3% at the off-design speed. These results verify the usefulness and reliability of the optimization method in the field of aerodynamic optimization of a multistage axial flow compressor.

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A relative adequacy framework for multimodel management in multidisciplinary design optimization

Bayoumy

Kokkolaras

2020

Struct Multidisc Optim

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A 3D Parameterization for Transonic Fan Blade Multidisciplinary Design

Cited by 4 publications

References 14 publications

Design Optimization of a Multistage Axial Flow Compressor Based on Full-Blade Surface Parameterization and Phased Strategy

Design Optimization of a Multistage Axial Flow Compressor Based on Full-Blade Surface Parameterization and Phased Strategy

Research on Aerodynamic Optimization Method of Multistage Axial Compressor under Multiple Working Conditions Based on Phased Parameterization Strategy

A relative adequacy framework for multimodel management in multidisciplinary design optimization

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