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基于一种全新的轴流压气机叶片反问题设计边界条件,发展了一种全新的三维粘性反问题设计方法。该方法以叶片表面静压分布作为输入的气动性能参数,叶片吸、压力面型线为设计对象。全新的反问题边界条件采用壁面边界处黎曼不变量守恒建立起给定的气动参数分布与叶片几何变化量之间的关系。由于计算过程中叶片几何构型不断发生变化,采用动网格技术对计算网格进行更新。为了验证方法的有效性,采用NASA Rotor 37作为算例,进行叶片返回试验,对叶片表面静压分布进行合理修改,通过反问题设计计算,设计出新的叶片几何构型。计算结果显示,反问题设计很好地满足了给定的叶片表面静压分布,正确地反映了设计意图。改型后的叶片吸力面逆压梯度有所降低,气流分离得到抑制,压气机流量、总压比以及效率分别提高了0.7%,2.2%和1.0%,验证了方法的有效性和正确性。
Based on a new design of boundary conditions for the inverse problem of axial-flow compressor blades, a new design method of three-dimensional viscous inverse problem is developed. The method takes the static pressure distribution on the blade surface as the input aerodynamic performance parameter, and the blade suction and pressure surface shape lines are the design objects. The new inverse problem boundary condition establishes the relationship between the given aerodynamic parameter distribution and the geometric variation of blade using the Riemann constant conservation at the wall boundary. Due to the continuous change of the blade geometry during the calculation, the moving grid technique is used to update the calculation grid. In order to verify the effectiveness of the method, NASA Rotor 37 is used as an example to conduct the blade return test. The static pressure distribution on the blade surface is reasonably modified. A new blade geometry is designed by inverse problem design and calculation. The calculation results show that the inverse problem design can well meet the given static pressure distribution on the blade surface and correctly reflect the design intent. The pressure gradient on the suction side of the modified blade is reduced, the airflow separation is restrained, and the flow rate, total pressure ratio and efficiency of the compressor are increased by 0.7%, 2.2% and 1.0% respectively, which verifies the validity and correctness of the method.