A5067136579- Combustion and Detonation Processes
- Energetic Materials and Combustion
- Computational Fluid Dynamics and Aerodynamics
- Rocket and propulsion systems research
- Combustion and flame dynamics
- Gas Dynamics and Kinetic Theory
- Advanced Combustion Engine Technologies
- Fluid Dynamics and Turbulent Flows
- Fire dynamics and safety research
- Risk and Safety Analysis
- Spectroscopy and Laser Applications
- Atmospheric chemistry and aerosols
- Atmospheric Ozone and Climate
- Numerical methods for differential equations
- Particle Dynamics in Fluid Flows
- Aerodynamics and Acoustics in Jet Flows
- Thermal and Kinetic Analysis
- Coagulation and Flocculation Studies
- Industrial Automation and Control Systems
- Fluid Dynamics and Heat Transfer
- Fluid Dynamics and Mixing
- Nuclear Engineering Thermal-Hydraulics
- Cardiac Arrest and Resuscitation
- Advanced ceramic materials synthesis
- nanoparticles nucleation surface interactions
Université Paris-Saclay
2019-2024
Office National d'Études et de Recherches Aérospatiales
2015-2020
Centre National de la Recherche Scientifique
2003-2015
Institut de Combustion Aérothermique Réactivité et Environnement
2006-2015
Centre de Biophysique Moléculaire
2009-2011
National Council for Scientific Research
2011
Centre National pour la Recherche Scientifique et Technique (CNRST)
2009
Institut Icare
2008
International Center for Agribusiness Research and Education
2008
Laboratoire des Systèmes Perceptifs
2005
This paper presents numerical results on the operation of combustion chamber a Continuous Detonation Wave Rocket Engine (CDWRE). The propagation transversal detonation wave in layer continuously injected gaseous mixture H2-O2 has been simulated by reactive high-resolution Euler code 2D approach with periodicity boundary conditions. A parametric study conducted to investigate effect injection parameters (injector relative area and pressure), length, spacing between successive fronts integral...
The paper presents the computational method and results of 2D 3D numerical simulations flowfield in Continuous Detonation Wave Engine (CDWE) chambers different geometries. Numerical have been performed using a detailed thermochemical model H2-O2 mixture high-resolution Euler code with Adaptive Mesh Refinement (AMR) method. flowfields are described their comparative analysis is conducted order to demonstrate effects. It has found that flow specific features due detonation reflection from...
A systematic computational study has been conducted on the supersonic combustion of a hydrogen jet in LAERTE chamber, which was experimentally tested at ONERA. The fuel is injected Mach 2 along chamber axis into hot flow vitiated air. conditions air are: number 2, total temperature about 1850 K. By assuming two-dimensional axisymmetric (2DA) configuration broad parametric performed following important factors: boundary conditions, mesh adaptation, turbulence and chemical kinetic models,...
This paper is devoted to a review of some recent studies conducted at ONERA within the framework solid rocket propulsion for missiles, as well space launchers. The viewpoint adopted present physical phenomena studied using modeling, simulations and experimentations. Three major scientific topics will be investigated in this article: combustion propellants; motor interiorballistics with focus on two-phase flows, turbulence radiative effects; exhaust plumes, including vicinity aft body.
Covers advancements in spacecraft and tactical strategic missile systems, including subsystem design application, mission analysis, materials structures, developments space sciences, processing manufacturing, operations, applications of technologies to other fields.
The paper presents the scope of theoretical and numerical studies conducted at ICARECNRS on Continuous Detonation Wave Engine (CDWE). last part is devoted to a comparative performance analysis two ideal engines fed with gaseous H2 O2: conventional rocket engine (CRE) continuous detonation wave (CDWRE). Flow parameters in main cross sections are evaluated using global 0D approach detailed thermochemical model equilibrium combustion products. Performance results obtained wide rages mixture...
Propulsion systems based on the constant-pressure combustion process have reached maturity in terms of performance, which is close to its theoretical limit. Technological breakthroughs are needed develop more efficient transportation that meet today’s demands for reduced environmental impact and increased performance. The Rotating Detonation Engine (RDE), a specific implementation detonation process, appears today as promising candidate due high thermal efficiency, wide operating Mach range,...
Continuous Detonation Wave Rocket Engine (CDWRE) for space application is considered in the framework of French R&D and scientific research. A CDWRE demonstrator a dedicated test bench are designed by MBDA France. At ICARE-CNRS, theoretical experimental studies on internal processes under progress. Twodimensional (2D) Euler simulations combustion chamber have been performed to investigate effect geometrical injection parameters process performance. An study prepared liquid oxygen breakup...
The efficiency gain of rotating detonation depends on several loss factors related to the chamber geometry, injection principle, propellants and their mass flow rates, equivalence ratio. Numerical simulation can help quantify these losses, this work presents a Large Eddy Simulation (LES) in an annular its validation against experiments. captured mixing processes, overall dynamics detonation, deflagration, burnt gas expansion. device was numerically designed ensure partial premixing before...
An experimental study has been conducted to determine flame propagation velocities in micro- (6 µm) and nanosized (250 nm) aluminum particle clouds for various concentrations air. The results show faster nanoparticle cloud with respect the microparticle flame. Maximum temperature measured using a high-resolution spectrometer operating visible range. Analysis of combustion residual shows that is realized via gaseous phase. A laminar model proposed based on this observation. Model parameters...
Ignition characteristics of methane can be significantly improved by adding some hydrogen. The aim the present work is to obtain a suitable kinetic mechanism for -hydrogen fuel and integrate it into MSD code. Several comprehensive, skeletal, reduced mechanisms have been tested using simple reactor models (shock-tube perfectly stirred reactor) identify an appropriate able describe combustion parameters -hydrogen-air reacting system such as temperature profile, ignition delay, extinction...
§The problem of application the k-e turbulence model to numerical simulation compressible round jets is analyzed by comparing experimental and results. A limiting Pope correction proposed account for vortex stretching preserve computational stability. The limited validated in case an incompressible jet a slow coflow. Two variants Sarkar compressibility are plane mixing layers with different convective Mach numbers. corrections then tested several still air supersonic simulations have...
Covers advancements in spacecraft and tactical strategic missile systems, including subsystem design application, mission analysis, materials structures, developments space sciences, processing manufacturing, operations, applications of technologies to other fields.