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From 11 May 2020 to 13 May 2020

High-fidelity simulations of Turbomachinery Flows

nasri |  

Deadline for registration: 15 days before the starting date of each training
Duration : 3 days / (21 hours)


In May 2019, 100% of participants were satisfied or very satisfied


This training course aims at providing advanced training and formation in the field of turbomachinery flows. To do so, participants will reinforce their theoretical background in fluid dynamics as understood in the context of turbomachinery applications. These specificities will then be particularly developed in the specific context of Large Eddy Simulations whenever devised for the prediction of these flows. In this case, introduction and use of the in-house CERFACS LES code, named Turbo AVBP, will be specifically detailed. To do so, Hands-on sessions are organized to put the theoretical courses into practice.


Objective of the training session

The objective of this training course is to become familiar with LES of turbomachinery flows and more specifically the use of the proposed tool Turbo AVBP.

Learning outcomes

On completion of this course, you will be able to:

  • Explain the concept of turbulent scale separation and LES
  • Use and constructed test cases around turbomachinery applications with Turbo AVBP,
  • Define a-priori parameters for a Turbo AVBP LES computation (mesh genration, CPU cost…)
  • Become familiar numeric and modeling of LES for such flows
  • Analyze the predictions

Target participants

This training session is for students, engineers, physicists and computer scientists who wish to reinforce or extend their theoretical background to the precise use and analysis of LES simulations. Specific use of Turbo AVBP will also be enforced.


In order to follow this course, you need to:

  • Knowledge of Unix commands.
  • Basic knowledge of Python.
  • Knowledge of numerical flow simulations.

In order to verify that the prerequisites are satisfied, the following questionnaires must be completed. You need to get at least 75% of correct answers in order to be authorized to follow this training session. If you don’t succeed it, your subscription will not be validated. You only have two chances to complete them.

Questionnaire 1 : https://docs.google.com/forms/d/10CmaWgYni68tFjNwdW2QCIylPsQf81Fa_du_1dOrecY/edit

Questionnaire 2 : https://goo.gl/forms/dmBNAmZq1aJLknXD2

Questionnaire 3 : https://goo.gl/forms/mbH6Ye8k0GbyYNHt2

Scientific contact: Laurent Gicquel


  • Trainees/PhDs/PostDocs : 210 €
  • CERFACS shareholders/CNRS/INRIA : 600 €
  • Public : 1200 €


From 9h to 17h00
Jour 1

  • Physics of turbomachinery flows, aerodynamics of compressor/turbines, losses, flow stability/instabilities
  • Unsteady phenomena, rotor / stator interactions, multi-stages

Jour 2

  • CFD modeling of turbomachinery flows: RANS, URANS, LES state-of-the-art
  • Numeric and modeling in LES of turbomachinery flows: Turbo AVBP context

Jour 3

  • Complex turbomachinery LES: Turbo AVBP setup and case construction
  • Complex turbomachinery LES: Turbo AVBP advanced post-processing

Final examination

A final exam will be conducted during the training.



First 360-degrees Large-Eddy Simulation of a full engine

Jérôme DOMBARD |  17 June 2020

Within the PRACE project FULLEST (First fUlL engine computation with Large Eddy SimulaTion), a joint collaboration between CERFACS, SAFRAN and AKIRA technologies, Dr. C. Pérez Arroyo (post doctoral fellow at CERFACS) has carried out under the supervision of Dr. J. Dombard the first high-fidelity simulation of a part of the real engine DGEN380 (for now, from the fan to the combustion chamber). This 360-degrees integrated large-eddy simulation contains around two billion cells on the three instances, carried out with the AVBP code of CERFACS.  The CPU cost is obviously large but still within reach, performing around one turn of fan during 5 days over 14400 skylake cores. Post-treatments are in progress and already show, among other complex phenomena, a strong interaction between the high pressure compressor and the combustion chamber (see forthcoming paper GT2020-16288 C. Pérez Arroyo et al). Below a video showing: in the fan an isosurface at mid-height of the vein colored by the Mach number, in the high pressure compressor a gradient of density, in the bypass of the combustion chamber the static pressure and in the flame tube a temperature field. One of the goals of the project is to create a high-fidelity unsteady database to study interactions between modules and may help other teams to develop new lower order models and/or validate existing ones. Beyond the feasibility and the maturity of the AVBP code, this kind of calculation is an important milestone for the aeronautical industry and would allow to apprehend earlier in the design the effect of integration and installation and thus, to reduce the cycle and therefore the cost of the future aircraft engines. We acknowledge PRACE for awarding us access to Joliot-Curie (Genci) hosted at CEA/TGCC, FRANCE, Safran Tech and DGAC fundings within the project ATOM, along with the invaluable technical support at...Read more

B. Cuenot distinguished as Program Chair of international Symposium on Combustion

superadmin |  29 May 2020

B. Cuenot has been distinguished as Program Chair for the 39th International Symposium on Combustion, to be held in Vancouver (Canada) in 2022. The International Symposium on Combustion is a major event for the combustion community, where the current best research is presented.Read more