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Adaptation des méthodes et outils aéroacoustiques pour les jets en interaction dans le cadre des lanceurs spatiaux.

Abstract : During a space launch, the noise from hot supersonic jets, generated by rocket engines at liftoff and interacting with the launch pad, is harmful to the launcher and in particular its payload. Consequently, space actors are seeking to strengthen their understanding and control of this acoustic environment through numerical methods and tools, among the others. However, they do not dispose of a comprehensive numerical strategy that can simultaneously take into account accurate noise generation, nonlinear acoustic propagation, complex installation effects and realistic geometries, which are inherent to space applications. For this purpose, the present study consists in setting up and validating a numerical simulation methodology using a Navier-Stokes − Euler two-way coupling approach, then applying it to realistic cases of supersonic jet noise in order to improve prediction capabilities and contribute to the understanding of the noise generation mechanisms in such jets. The Navier-Stokes solver is based on an LES method on unstructured mesh and the acoustic solver on a high-order discontinuous Galerkin method on unstructured mesh. The methodology is first assessed on academic cases to validate the use of the two-way coupling. After preliminary computations, the methodology is applied to the simulation of the noise from a supersonic free jet at Mach 3.1. A geometric turbulence tripping method is implemented via a step at the nozzle wall. The computation leads to noise predictions very close to the experimental measurements performed at the MARTEL test bench and highlights significant nonlinear effects as well as a quite particular Mach waves radiation mechanism. Targeting even more realistic cases, the entire numerical approach is finally successfully adapted to the simulation of the noise from a supersonic jet configuration including a flame trench. In the future, it may be extended to configurations with clustered reactive jets, water injection devices or even at full scale.
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Submitted on : Wednesday, June 26, 2019 - 4:35:14 PM
Last modification on : Tuesday, March 16, 2021 - 3:18:03 PM


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  • HAL Id : tel-02166285, version 1


Adrien Langenais. Adaptation des méthodes et outils aéroacoustiques pour les jets en interaction dans le cadre des lanceurs spatiaux.. Autre. Thèse de doctorant de l'Université de Lyon présentée devant l'Ecole Centrale de Lyon, 2019. Français. ⟨NNT : 2019LYSEC003⟩. ⟨tel-02166285⟩



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