al11

Measuring Non-Volatile Particle Properties in the Exhaust of an Aircraft Engine

Auteurs: 

I. K. Ortega, D. Delhaye (ONERA)
F.-X. Ouf (Institut de Radioprotection et de Sûreté Nucléaire)
D. Ferry (Aix-Marseille Université, CNRS, CINaM UMR 7325)
C. Focsa, C. Irimiea, Y. Carpentier, B. Chazallon (Laboratoire de Physique des
Lasers, Atomes et Molécules UMR CNRS 8523, Université de Lille 1 Sciences et Technologies)
P. Parent, C. Laffon (Aix-Marseille Université, CNRS, CINaM UMR 7325)
O. Penanhoat, N. Harivel (SNECMA/SAFRAN Group)
D. Gaffié, X. Vancassel (ONERA)

The steady growth of air traffic and its foreseen expansion during future years have raised concerns about its potential impact on climate and ground-level air quality. So far, the smoke number has been used to evaluate the non-volatile particulate matter amount emitted by aircraft engines, but it is a poor proxy for modern engine emissions.

Methodology for the Numerical Prediction of Pollutant Formation in Gas Turbine Combustors and Associated Validation Experiments

Auteurs: 

F. Dupoirieux, N. Bertier, C. Guin, L.-H. Dorey (ONERA)
K.P. Geigle, C. Eberle, P. Gerlinger (DLR)

For aircraft engine manufacturers the formation of pollutants such as NOx or soot particles is an important issue because the regulations on pollutant emissions are becoming increasingly stringent. In order to comply with these regulations, new concepts of gas turbine combustors must be developed with the help of simulation tools. In this paper we present two different strategies, proposed by ONERA and DLR respectively, to simulate soot or NOx formation in combustors.

Advanced Simulation of Aeronautical Combustors

Auteurs: 

B. Cuenot (CERFACS)
R. Vicquelin (CNRS, UPR 288, EM2C, Centrale-Supélec, U. Paris-Saclay)
E. Riber (CERFACS)
V. Moureau, G. Lartigue (CORIA, CNRS UMR6614, Normandie Université, Université et INSA de Rouen)
A. Figuer, Y. Mery (SAFRAN AIRCRAFT ENGINES)
J. Lamouroux, S. Richard (SAFRAN HELICOPTER ENGINES)
L.Gicquel (CERFACS)
T. Schmitt, S. Candel (CNRS, UPR 288, EM2C, Centrale-Supélec, U. Paris-Saclay)

The development of new aeronautical combustor concepts relies on the best possible knowledge of combustion phenomena, such as ignition and extinction, flame structure, combustion instabilities or pollutant emissions. Numerical simulation, and in particular the Large Eddy Simulation approach, is a powerful tool to understand, predict and control the coupled physics involved in turbulent combustion in both academic and applied configurations.

Modeling Challenges in Computing Aeronautical Combustion Chambers

Auteurs: 

B. Fiorina, A. Vié, B. Franzelli, N. Darabiha (Laboratoire EM2C, CNRS, Centrale-Supélec, Université Paris-Saclay)
M. Massot (Laboratoire EM2C, CNRS, Centrale-Supélec, Université Paris-Saclay, ONERA)
G. Dayma, P. Dagaut (ICARE, CNRS, Université d'Orléans)
V. Moureau, L. Vervisch, A. Berlemont (CORIA-UMR 6614-Normandie
Université, CNRS-Université, INSA de Rouen)
V. Sabelnikov (ONERA)
E. Riber, B. Cuenot (CERFACS)

This article reviews the modeling challenges for performing Large Eddy Simulations of aero-nautical combustion chambers. Since the kerosene is injected in a liquid phase into the combustion chamber, the description of the atomization is of primary importance. The article first discusses the numerous numerical challenges encountered during this process, which leads to the formation of small droplets that constitute a spray.

Numerical Simulation of Reactive Flows in Ramjet Type Combustors and Associated Validation Experiments

Auteurs: 

T. Le Pichon, A. Laverdant

Twenty years ago, a review listed the main challenges to overcome to accurately predict the reactive flow fields in ramjet combustion chambers. These issues were grouped into five topics: flow organization, combustion phenomena, stability and performance, unsteady combustion and heat transfer. The aim of this paper is to give a brief overview of the numerical and experimental studies that have been carried out since this inventory in the specific program named “Research Ramjet” to improve CFD codes.

ONERA test Facilities for Combustion in Aero Gas Turbine Engines, and Associated Optical Diagnostics

Auteurs: 

A. Cochet, V. Bodoc, C. Brossard, O. Dessornes, C. Guin, R. Lecourt, M. Orain, A. Vincent-Randonnier (ONERA)

The aim of this paper is to provide an overview of the ONERA test facilities devoted to the study of combustion in gas turbine engines. The objectives of the experimental studies performed with these test rigs are very ambitious and extend from building databases for the validation of codes and models used in numerical simulation to applied research for evaluating the performance of advanced aero injection systems in mono-sector, multi-sector or full annular combustion chambers.

Research Activity to Tackle the Challenges in Combustion for Aerospace Propulsion

Auteurs: 

Francis Dupoirieux (ONERA)

The use of combustion for aerospace propulsion is inescapable for the long term. The improvement of the energetic efficiency, safety and reliability, and the compliance with increasingly stringent environmental rules require the enhancement of existing technologies and/or a breakthrough in propulsion devices. A vigorous research activity must be pursued in the field of combustion to meet these goals.