方案摘要
方案下载应用领域 | 其他 |
检测样本 | 其他 |
检测项目 | |
参考标准 | 暂无 |
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.
在一个双稳湍流涡旋火焰中,对间歇性动态的时间-频率定位
Particle-laden Taylor-Couette流:高阶转变和径向局部波浪涡旋的证据
7根杆束的流体-结构相互作用:用实验数据对比数值模拟
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