Kriging-Based Framework Applied to a Multi-Point, Multi-Objective Engine Air-Intake Duct Aerodynamic Optimization Problem

The forecasted growth in dynamic global air fleet size in the coming decades, together with the need to introduce disruptive technologies supporting net-zero emission air transport, demands more efficient design and optimization workflows. This research focuses on developing an aerodynamic optimizat...

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Vydáno v:Aerospace Ročník 10; číslo 3; s. 266
Hlavní autoři: Drężek, Przemysław S., Kubacki, Sławomir, Żółtak, Jerzy
Médium: Journal Article
Jazyk:angličtina
Vydáno: Basel MDPI AG 01.03.2023
Témata:
Aerodynamics
Air transportation
Aircraft
Aircraft engines
Algorithms
Approximation
Aviation
Chebyshev approximation
Design optimization
Engine inlets
Flight conditions
Flow distortion
Forecasts and trends
Geometry
Global optimization
Industrial efficiency
Intake systems
Kriging
Light aircraft
Mathematical functions
metamodel
Morphing
multi-objective
multi-point
Net zero
optimization
Optimization techniques
Pressure loss
Radial basis function
surrogate
Turboprop engines
Workflow
United Kingdom
ISSN:2226-4310, 2226-4310
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Shrnutí:The forecasted growth in dynamic global air fleet size in the coming decades, together with the need to introduce disruptive technologies supporting net-zero emission air transport, demands more efficient design and optimization workflows. This research focuses on developing an aerodynamic optimization framework suited for multi-objective studies of small aircraft engine air-intake ducts in multiple flight conditions. In addition to the refinement of the duct’s performance criteria, the work aims to improve the economic efficiency of the process. The optimization scheme combines the advantages of Kriging-based Efficient Global Optimization (EGO) with the Radial Basis Functions (RBF)-based mesh morphing technique and the Chebyshev-type Achievement Scalarizing Function (ASF) for handling multiple objectives and design points. The proposed framework is applied to an aerodynamic optimization study of an I-31T aircraft turboprop engine intake system. The workflow successfully reduces the air-duct pressure losses and mitigates the flow distortion at the engine compressor’s front face in three considered flight phases. The results prove the framework’s potential for solving complex multi-point air-intake duct problems and the capacity of the ASF-based formulation to guide optimization toward the designer’s preferred objective targets.
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ISSN:2226-4310
2226-4310
DOI:10.3390/aerospace10030266