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依据某型涡扇发动机波瓣强迫混合排气系统结构,保持波瓣数以及波瓣几何参数不变,改变波瓣尾缘的凹扇修形程度,从而获得一组除凹扇修形程度不同其余几何参数均相同的波瓣几何模型。对该涡扇发动机波瓣强迫混合排气系统采用三维CFD模拟的方法,得到了凹扇修形对涡扇发动机波瓣强迫混合排气系统气动热力性能的影响规律。研究结果表明:在波瓣尾缘以及混合排气系统出口,随着凹扇修形程度的变大,热混合效率均呈现出上升的趋势;而总压恢复系数则均逐渐地减小。在混合排气系统出口,推力混合效率随凹扇修形程度的变大而上升,与没有凹扇修形的模型相比,研究的凹扇修形模型的推力混合效率最大增加了39.33%。此外,随着流向涡沿轴向发展,波瓣凹扇修形对热混合效率的影响逐渐减弱。
According to the structure of forced exhaust system of a turbofan engine, the number of lobes and the geometrical parameters of the lobes are kept constant, the degree of concave fan modification on the trailing edge of the lobe is changed, The remaining geometrical parameters are the same lobe geometry model. The three-dimensional CFD simulation method was adopted for the forced mixed exhaust system of the lobe engine lobe to obtain the influence law of concave fan modification on the aerodynamic performance of forced-mixed exhaust system of turbofan engine. The results show that at the exit of the lobe and at the exit of the hybrid exhaust system, the thermal mixing efficiency increases with the increase of the concave fan, while the total pressure recovery coefficient decreases gradually. At the outlet of the hybrid exhaust system, the thrust mixing efficiency increases with the increase of the concave fan. Compared with the model without the concave fan, the thrust mixing efficiency of the concave fan modified model increases by 39.33%. In addition, as the flow vortex develops in the axial direction, the influence of lobed concave fan modification on the heat mixing efficiency gradually diminishes.