Evaluation of novel-objective functions in the design optimization of a transonic rotor by using deep learning

Design optimization of transonic airfoils for rotary blades is a challenging subject that remarkably affects the stage and overall performance of axial-flow compressors. This paper describes a surrogate-based multi-objective optimization process over a transonic rotary blade. This blade works in the...

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Veröffentlicht in:Engineering applications of computational fluid mechanics Jg. 15; H. 1; S. 561 - 583
Hauptverfasser: Zeinalzadeh, A., Pakatchian, M.R.
Format: Journal Article
Sprache:Englisch
Veröffentlicht: Hong Kong Taylor & Francis 01.01.2021
Taylor & Francis Ltd
Taylor & Francis Group
Schlagworte:
Airfoil design optimization
axial compressor
Boundary layers
Deep learning
Design factors
Design optimization
Flat roofs
MISES
Multilayer perceptrons
Multilayers
Multiple objective analysis
Pressure distribution
Rotor blades
Rotor blades (turbomachinery)
Suction
Supercritical airfoils
supercritical pressure distribution
Supercritical pressures
transonic rotor
Turbocompressors
ISSN:1994-2060, 1997-003X
Online-Zugang:Volltext
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Zusammenfassung:Design optimization of transonic airfoils for rotary blades is a challenging subject that remarkably affects the stage and overall performance of axial-flow compressors. This paper describes a surrogate-based multi-objective optimization process over a transonic rotary blade. This blade works in the first high-pressure stage of a pre-designed industrial axial compressor. It experiences a massive separation behind an impinging shock wave over its suction side, resulting in very low efficiency of the whole stage. The key components of the current approach involve the application of novel-objective functions over the pressure distribution of airfoils, called the location of the shock wave and a flat-roof-top factor, to design supercritical airfoils. Moreover, to ensure the advantages of having an attached boundary layer and a high efficient blade, the area of separated boundary layer is also defined alongside other well-known objective functions related to the polar loss diagram. Notably, a sequential feed-forward multi-layer perceptron is designed to construct a mapping between airfoil geometrical variables and the objective functions. A numerical simulation of the whole compressor has shown an efficiency improvement of about 10% and 0.17% for the first stage and the whole compressor, respectively, and an attached boundary layer with a supercritical pressure distribution when employing the optimized rotor blade at the design stage.
Bibliographie:ObjectType-Article-1
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ISSN:1994-2060
1997-003X
DOI:10.1080/19942060.2021.1895889