简介:An ongoing research ramjet program initiated at ONERA under support of DGA
(French ministry of Defence) aims to improve methodology for ramjet combustion chamber
design and tuning by using validated CFD codes. A transp简介:An ongoing research ramjet program initiated at ONERA under support of DGA
(French ministry of Defence) aims to improve methodology for ramjet combustion chamber
design and tuning by using validated CFD codes. A transparent model rig was used for
aerodynamic tests with air flows at atmospheric pressure and room temperature. In the case of
the simulation of a Solid Ducted Rocket (SDR) combustor, two fuel holes were located at the
head end of the combustor in order to simulate the fuel supply from the auxiliary gas generator
in the case of a real combustor.
Among the various mechanisms that are controlling the development of the combustion
processes inside the combustor, the mixing is certainly one of the most crucial as far as stability
or efficiency are concerned. The work presented in this paper is addressing the
characterization, in absence of combustion, of the turbulent flow velocity and scalar fields
associated to the mixing between fuel (simulated by CO2) and air. Particle image velocimetry
(PIV) and gas sampling analysis are the two techniques that were used to serve that purpose.
Results presented in this paper are very useful to assess the ability of numerical computations,
based either on Reynolds-Averaged Navier-Stokes (RANS) or Large-Eddy Simulations (LES)
approaches, to reliably predict velocity and fuel concentration fields inside this research
combustor.详细>