Academic Journal
Loss assessment of the NASA SDT configuration using LES with phase-lagged assumption ; Analyse des pertes de la configuration NASA SDT par simulation LES avec hypothèse chorochronique
| العنوان: | Loss assessment of the NASA SDT configuration using LES with phase-lagged assumption ; Analyse des pertes de la configuration NASA SDT par simulation LES avec hypothèse chorochronique |
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| المؤلفون: | Fiore, Maxime, Daroukh, Majd, Montagnac, Marc |
| المساهمون: | Institut Supérieur de l'Aéronautique et de l'Espace (ISAE-SUPAERO), DAAA, ONERA, Université Paris-Saclay Châtillon, ONERA-Université Paris-Saclay, Centre Européen de Recherche et de Formation Avancée en Calcul Scientifique (CERFACS) |
| المصدر: | ISSN: 0045-7930. |
| بيانات النشر: | HAL CCSD Elsevier |
| سنة النشر: | 2021 |
| مصطلحات موضوعية: | NASA SDT, Large-eddy simulation (LES), Phase-lagged assumption, Proper orthogonal decomposition (POD), Loss assessment, NASA STD, SIMULATIONS AUX GRANDES ECHELLES, HYPOTHESE CHOROCRHONIQUE, DECOMPOSITION ORTHOGONALE AUX VALEURS PROPRES, ANALYSE DES PERTES, [SPI]Engineering Sciences [physics], [PHYS]Physics [physics] |
| الوصف: | International audience ; This paper presents the numerical study of the Source Diagnostic Test fan rig of the NASA Glenn (NASA SDT). Large-Eddy Simulations (LES) based on a finite volume approach are performed for the three different Outlet Guide Vane (OGV) geometries (baseline, low-count and low-noise) and three rotational speeds corresponding to approach, cutback and sideline operating conditions respectively. The full stage and nacelle geometries are considered in the numerical simulations, and results are compared to available measurements. The NASA SDT configuration is equipped respectively with 22 fan blades and either 26 of 54 vanes depending on the OGV geometry. The simulation domain could only be reduced to half of the full annulus and would still be a significant cost for the LES. In order to reduce computational cost, an LES with phase-lagged assumption approach is used. This method allows to perform unsteady simulations of multistage turbomachinery configurations including multiple frequency flows with a reduced computational domain composed of one single blade passage for each row. The large data storage required by the phase-lagged approach is handled by a compression method based on a Proper Orthogonal Decomposition replacing the traditional Fourier series decomposition. This compression method improves the signal spectral content especially at high frequency. Based on the numerical simulations, the flow field is described and used to assess the losses generated in the turbofan configuration based on an entropy approach. The results show different flow topologies for the fan depending on the rotational speed with a leading edge shock at high rotational speed. The fan boundary layer contributes strongly to losses with the majority of the losses being generated close to the leading edge for the dissipation due to mean strains and close to the recirculation zone occurring on the suction side for the turbulent kinetic energy production. ; Ce papier présente une étude numérique sur le banc SDT (Source ... |
| نوع الوثيقة: | article in journal/newspaper |
| اللغة: | English |
| DOI: | 10.1016/j.compfluid.2021.105256 |
| الاتاحة: | https://hal.science/hal-03531474 https://hal.science/hal-03531474v1/document https://hal.science/hal-03531474v1/file/DAAA21186.1642171051_postprint.pdf https://doi.org/10.1016/j.compfluid.2021.105256 |
| Rights: | info:eu-repo/semantics/OpenAccess |
| رقم الانضمام: | edsbas.6172D773 |
| قاعدة البيانات: | BASE |
| DOI: | 10.1016/j.compfluid.2021.105256 |
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