Development of a 3D CFD aerodynamic optimization tool and application to engine air intake design

Millot, Grégory; Scholz, Olivier; Ouhamou, Saïd; Becquet, Mathieu; Magnabal, Sébastien

doi:10.1108/hff-06-2018-0276

Cited by 3 publications

(3 citation statements)

References 13 publications

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“…The inadequate length of the wind tunnel, road conditions and environmental factors can affect the test results. Numerical simulation methods compensate for the HFF 34,1 limitations of experimental conditions (Millot et al, 2020;Zhao and Guan, 2022). The combination of computer simulation and optimization methods can substantially improve research efficiency.…”

Section: Introductionmentioning

confidence: 99%

Aerodynamic optimization of mixed platoon Ahmed body vehicles based on response surface method

Luo,

Tie,

et al. 2023

HFF

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Purpose The purpose of this paper is to investigate the optimal average drag coefficient of the Ahmed body for mixed platoon driving under crosswind and no crosswind conditions using the response surface optimization method. This study has extraordinary implications for the planning of future intelligent transportation. Design/methodology/approach First, the single vehicle and vehicle platoon models are validated. Second, the configuration with the lowest average drag coefficient under the two conditions is obtained by response surface optimization. At the same time, the aerodynamic characteristics of the mixed platoon driving under different conditions are also analyzed. Findings The configuration with the lowest average drag coefficient under no crosswind conditions is 0.3 L for longitudinal spacing and 0.8 W for lateral spacing, with an average drag coefficient of 0.1931. The configuration with the lowest average drag coefficient under crosswind conditions is 10° for yaw angle, 0.25 L for longitudinal spacing, and 0.8 W for lateral spacing, with an average drag coefficient of 0.2251. Compared to the single vehicle, the average drag coefficients for the two conditions are reduced by 25.1% and 41.3%, respectively. Originality/value This paper investigates the lowest average drag coefficient for mixed platoon driving under no crosswind and crosswind conditions using a response surface optimization method. The computational fluid dynamics (CFD) results of single vehicle and vehicle platoon are compared and verified with the experimental results to ensure the reliability of this study. The research results provide theoretical reference and guidance for the planning of intelligent transportation.

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Section: Introductionmentioning

confidence: 99%

Aerodynamic optimization of mixed platoon Ahmed body vehicles based on response surface method

Luo,

Tie,

et al. 2023

HFF

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“…The expected trend is that intakes will have a reduced non-dimensional highlight radius ( r hi / r fan ) and length ( L int / r fan ), and it is likely that the fancowl length ( L nac / r hi ) and trailing edge radius ( r te / r hi ) will also be reduced (Figure 1). Although non-compact intakes with large r hi / r fan values can meet the aerodynamic requirements for the intake range of operability, they can result in an increase in nacelle drag (Peters et al , 2015; Millot et al , 2020). On the other hand, short fancowls with low L nac / r hi might lead to unfeasible intake configurations.…”

Section: Introductionmentioning

confidence: 99%

Towards the design and optimisation of future compact aero-engines: intake/fancowl trade-off investigation

Tejero

MacManus

García

et al. 2022

HFF

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Purpose Relative to in-service aero-engines, the bypass ratio of future civil architectures may increase further. If traditional design rules are applied to these new configurations and the housing components are scaled, then it is expected that the overall weight, nacelle drag and the effects of aircraft integration will increase. For this reason, the next generation of civil turbofan engines may use compact nacelles to maximise the benefits from the new engine cycles. The purpose of this paper is to present a multi-level design and optimisation process for future civil aero-engines. Design/methodology/approach An initial set of multi-point, multi-objective optimisations for axisymmetric configurations are carried out to identify the trade-off between intake and fancowl bulk parameters of highlight radius and nacelle length on nacelle drag. Having identified the likely optimal part of the design space, a set of computationally expensive optimisations for three-dimensional non-axisymmetric configurations is performed. The process includes cruise- and windmilling-type operating conditions to ensure aerodynamic robustness of the downselected configurations. Findings Relative to a conventional aero-engine nacelle, the developed process yielded a compact aero-engine configuration with mid-cruise drag reduction of approximately 1.6% of the nominal standard net thrust. Originality/value The multi-point, multi-objective optimisation is carried out with a mixture of regression and classification functions to ensure aerodynamic robustness of the downselected configurations. The developed computational approach enables the optimisation of future civil aero-engine nacelles that target a reduction of the overall fuel consumption.

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“…In the reduced design space, a range of RANS CFD calculations are performed and a multifidelity co-Kriging approach is used. Whilst the proposed method is used for aero-engine nacelle design applications, it can be applied for the optimisation of other complex aerodynamic problems (Millot et al , 2020; Embuena et al , 2018).…”

Section: Introductionmentioning

confidence: 99%

Aerodynamic optimisation of civil aero-engine nacelles by dimensionality reduction and multi-fidelity techniques

Tejero

MacManus

Hueso-Rebassa

et al. 2022

HFF

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Purpose Aerodynamic shape optimisation is complex because of the high dimensionality of the problem, the associated non-linearity and its large computational cost. These three aspects have an impact on the overall time of the design process. To overcome these challenges, this paper aims to develop a method for transonic aerodynamic design with dimensionality reduction and multifidelity techniques. Design/methodology/approach The developed methodology is used for the optimisation of an installed civil ultra-high bypass ratio aero-engine nacelle. As such, the effects of airframe-engine integration are considered during the optimisation routine. The active subspace method is applied to reduce the dimensionality of the problem from 32 to 2 design variables with a database compiled with Euler computational fluid dynamics (CFD) calculations. In the reduced dimensional space, a co-Kriging model is built to combine Euler lower-fidelity and Reynolds-averaged Navier stokes higher-fidelity CFD evaluations. Findings Relative to a baseline aero-engine nacelle derived from an isolated optimisation process, the proposed method yielded a non-axisymmetric nacelle configuration with an increment in net vehicle force of 0.65% of the nominal standard net thrust. Originality/value This work investigates the viability of CFD optimisation through a combination of dimensionality reduction and multifidelity method and demonstrates that the developed methodology enables the optimisation of complex aerodynamic problems.

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Development of a 3D CFD aerodynamic optimization tool and application to engine air intake design

Cited by 3 publications

References 13 publications

Aerodynamic optimization of mixed platoon Ahmed body vehicles based on response surface method

Aerodynamic optimization of mixed platoon Ahmed body vehicles based on response surface method

Towards the design and optimisation of future compact aero-engines: intake/fancowl trade-off investigation

Aerodynamic optimisation of civil aero-engine nacelles by dimensionality reduction and multi-fidelity techniques

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