Laboratory for physical and numerical simulation of flows with combustion in the engines of perspective aircrafts
Grant Agreement No.: 14.G39.31.0001
Project name: Studies and development of physical models and numerical technologies for description of different combustion regimes in aircraft engines
Name of the institution of higher learning: Central Aerohydrodynamic Institute
Fields of scientific research: Mechanics and engineering
The goal of project is to study physical and numerical simulation of flows with combustion in the engines of perspective aircrafts. Models for different regimes of combustion in ramjets and special software for using in cycle of aerodynamic designing the engines of perspective aircrafts will be developed and validated.
To achieve these purposes, following problems have been solved:
1. Improvement of known physical models of combustion and development of new these, their adjustment the considered classes of problems and creation on their basis a universal method for describing complex high-speed gas flows with a range of different combustion regimes.
2. Theoretical analysis of physical structure of flow in high-speed combustion chambers and creation of turbulence models for adequate description of this class flow in the framework of RANS approach (Reynolds Averaged Navier-Stokes equations) and LES approach (Large Eddy Simulation - direct numerical simulation of large-scale turbulence).
3. Development of high-performance (on speed and RAM costs) algorithms and computer codes that realize fully developed models.
4. Validation of developed physical models and software on the basis of “fire” aerodynamic experiment specially performed in TsAGI.
5. Designing and manufacturing the experimental model of dual-mode combustion chamber (chamber with supersonic flow at the entrance, where subsonic or supersonic combustion regime takes place in dependence of inflow parameters) with/without thermochemical fuel conversion.
6. Testing the flow in given model of combustion chamber for regimes of subsonic and supersonic combustion of propane, with/without thermochemical fuel conversion.
7. Development and detailed investigation of engine model with resonator cavity, where fuel combustion takes place in rotating detonation wave.
Sabelnikov Vladimir Anatolievich
Date of Birth: 03.09.1946
Academic degree and title: Doctor in physics and mathematics
Job Title: ONERA – The French Aerospace Lab
Field of scientific interests: turbulent combustion, supersonic combustion, turbulence, plasma assisted combustion
1997-2002 Member of the editorial board of the journal «Aerothermodynamics at
since 1997 Member of the Academy of Space named after K.E.Tsiolkovsky
1994-2004 Chairman of the section «Propulsion at hypersonic velocities» of the annual conference organized by the Academy of Sciences of Russia
1989-2000 Member of the Scientific Board of TsAGI
1988 Zhukovsky 1-st Prize of Aviation Ministry of Russia for investigations in
aerodynamics for 1987