We present a new aerodynamic design method based on the lattice Boltzmann method （LBM） and the adjoint approach. The flow field and the adjoint equation are numerically simulated by the GILBM （generalized form of i...We present a new aerodynamic design method based on the lattice Boltzmann method （LBM） and the adjoint approach. The flow field and the adjoint equation are numerically simulated by the GILBM （generalized form of interpolation supplemented LBM） on non-uniform meshes. The first-order approximation for the equilibrium dis- tribution function on the boundary is proposed to diminish the singularity of boundary conditions. Further, a new treatment of the solid boundary in the LBM is described par- ticularly for the airfoil optimization design problem. For a given objective function, the adjoint equation and its boundary conditions are derived analytically. The feasibility and accuracy of the new approach have been perfectly validated by the design optimization of NACA0012 airfoil.展开更多
Abstract A first study on the continuous adjoint formulation for aerodynamic optimization design of high pressure turbines based on S2 surface governed by the Euler equations with source terms is presented. The object...Abstract A first study on the continuous adjoint formulation for aerodynamic optimization design of high pressure turbines based on S2 surface governed by the Euler equations with source terms is presented. The objective function is defined as an integral function along the boundaries, and the adjoint equations and the boundary conditions are derived by introducing the adjoint variable vec- tors. The gradient expression of the objective function then includes only the terms related to phys- ical shape variations. The numerical solution of the adjoint equation is conducted by a finite- difference method with the Jameson spatial scheme employing the first and the third order dissipa- tive fluxes. A gradient-based aerodynamic optimization system is established by integrating the blade stagger angles, the stacking lines and the passage perturbation parameterization with the quasi-Newton method of Broyden Fletcher Goldfarb-Shanno （BFGS）. The application of the continuous adjoint method is validated through a single stage high pressure turbine optimization case. The adiabatic efficiency increases from 0.8875 to 0.8931, whilst the mass flow rate and the pressure ratio remain almost unchanged. The optimization design is shown to reduce the passage vortex loss as well as the mixing loss due to the cooling air injection.展开更多
为解决当前汽车气动减阻设计中基于工程师经验的试凑法所带来的盲目性与低效性,以及车身曲面难于参数化的问题,作者将离散伴随法和试验设计(Design of Experiment,DOE)引入汽车减阻优化流程,以阶梯背式MIRA模型为研究对象,通过对外流场...为解决当前汽车气动减阻设计中基于工程师经验的试凑法所带来的盲目性与低效性,以及车身曲面难于参数化的问题,作者将离散伴随法和试验设计(Design of Experiment,DOE)引入汽车减阻优化流程,以阶梯背式MIRA模型为研究对象,通过对外流场进行数值计算,根据外流场特性和车辆表面灵敏度分析,确定优化变量;通过DOE创建样本空间,并采用网格变形技术对各优化变量进行参数化;通过CFD仿真获取各样本点的风阻系数;采用Kriging空间插值法来建立近似模型;使用自适应模拟退火算法对模型优化。优化后模型风阻系数较原模型共计降低16 counts,减阻5.4%,表明该方法在汽车气动减阻优化中有较好的减阻效果和可行性。展开更多
将连续伴随方程法与自由变形技术(Free Form Deform-FFD)相结合开展了跨声速机翼气动外形优化设计方法研究。采用Bernstein基函数建立了空间FFD参数化方法,并应用基于控制理论的连续伴随方程方法建立了目标函数对于待优化几何外形的梯...将连续伴随方程法与自由变形技术(Free Form Deform-FFD)相结合开展了跨声速机翼气动外形优化设计方法研究。采用Bernstein基函数建立了空间FFD参数化方法,并应用基于控制理论的连续伴随方程方法建立了目标函数对于待优化几何外形的梯度求解模式,将几何外形参数化方法、连续伴随方法以及CFD数值模拟技术相结合,研究、构建了适合跨声速机翼的气动外形优化设计系统。利用该系统对ONERA M6机翼及某型民用客机机翼进行了气动减阻设计,算例验证表明该方法应用于跨声速机翼气动减阻设计效果明显,并且能较好的保持几何表面连续性和光滑性。展开更多
基金Project supported by the National Basic Research Program of China(No.2014CB744100)the National Natural Science Foundation of China(Nos.61403245 and 91648119)the Shanghai Municipal Science and Technology Commision(No.14500500400)
文摘We present a new aerodynamic design method based on the lattice Boltzmann method （LBM） and the adjoint approach. The flow field and the adjoint equation are numerically simulated by the GILBM （generalized form of interpolation supplemented LBM） on non-uniform meshes. The first-order approximation for the equilibrium dis- tribution function on the boundary is proposed to diminish the singularity of boundary conditions. Further, a new treatment of the solid boundary in the LBM is described par- ticularly for the airfoil optimization design problem. For a given objective function, the adjoint equation and its boundary conditions are derived analytically. The feasibility and accuracy of the new approach have been perfectly validated by the design optimization of NACA0012 airfoil.
基金funded by the Aeronautical Science Foundation of China–China(No.2010ZB51023)
文摘Abstract A first study on the continuous adjoint formulation for aerodynamic optimization design of high pressure turbines based on S2 surface governed by the Euler equations with source terms is presented. The objective function is defined as an integral function along the boundaries, and the adjoint equations and the boundary conditions are derived by introducing the adjoint variable vec- tors. The gradient expression of the objective function then includes only the terms related to phys- ical shape variations. The numerical solution of the adjoint equation is conducted by a finite- difference method with the Jameson spatial scheme employing the first and the third order dissipa- tive fluxes. A gradient-based aerodynamic optimization system is established by integrating the blade stagger angles, the stacking lines and the passage perturbation parameterization with the quasi-Newton method of Broyden Fletcher Goldfarb-Shanno （BFGS）. The application of the continuous adjoint method is validated through a single stage high pressure turbine optimization case. The adiabatic efficiency increases from 0.8875 to 0.8931, whilst the mass flow rate and the pressure ratio remain almost unchanged. The optimization design is shown to reduce the passage vortex loss as well as the mixing loss due to the cooling air injection.
文摘为解决当前汽车气动减阻设计中基于工程师经验的试凑法所带来的盲目性与低效性,以及车身曲面难于参数化的问题,作者将离散伴随法和试验设计(Design of Experiment,DOE)引入汽车减阻优化流程,以阶梯背式MIRA模型为研究对象,通过对外流场进行数值计算,根据外流场特性和车辆表面灵敏度分析,确定优化变量;通过DOE创建样本空间,并采用网格变形技术对各优化变量进行参数化;通过CFD仿真获取各样本点的风阻系数;采用Kriging空间插值法来建立近似模型;使用自适应模拟退火算法对模型优化。优化后模型风阻系数较原模型共计降低16 counts,减阻5.4%,表明该方法在汽车气动减阻优化中有较好的减阻效果和可行性。
文摘将连续伴随方程法与自由变形技术(Free Form Deform-FFD)相结合开展了跨声速机翼气动外形优化设计方法研究。采用Bernstein基函数建立了空间FFD参数化方法,并应用基于控制理论的连续伴随方程方法建立了目标函数对于待优化几何外形的梯度求解模式,将几何外形参数化方法、连续伴随方法以及CFD数值模拟技术相结合,研究、构建了适合跨声速机翼的气动外形优化设计系统。利用该系统对ONERA M6机翼及某型民用客机机翼进行了气动减阻设计,算例验证表明该方法应用于跨声速机翼气动减阻设计效果明显,并且能较好的保持几何表面连续性和光滑性。
