大涵道比风扇叶片气动优化设计

张金环; 周正贵; 周旭

doi:10.13224/j.cnki.jasp.2017.01.032

大涵道比风扇叶片气动优化设计

doi: 10.13224/j.cnki.jasp.2017.01.032

南京航空航天大学能源与动力学院江苏省航空动力系统重点实验室,南京 210016

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出版历程
- 收稿日期: 2015-04-17
- 刊出日期: 2017-01-28

Aerodynamic optimization design of high bypass ratio fan blades

摘要

摘要: 应用自动优化方法进行大涵道比风扇叶片三维气动设计,数值最优化采用遗传算法，并利用网络通讯协议实现多CPU并行优化,大幅度缩短优化耗时.对风扇叶片型面、叶片积叠线、子午面流道、叶型安装角和叶型弦长采用基于修改量的参数化方法、结合遗传算法设计参数范围限制,以达到优化过程生成个体的可控制、合理性.采用Denton黏性体积力方法进行流场计算,较大程度减少流场计算耗时，进一步缩短优化时间.以提高设计点风扇效率、保持设计点总压比和流量不变为优化目标,并对非设计点性能进行全工况校核.通过两次不同设计参数设置的优化,最终优化风扇效率由09463提高到09560；稳定裕度由112%增加到219%.最终优化风扇叶尖处激波前马赫数略有下降，且激波向通道内倾斜,因此激波及激波造成的附面层损失下降，且稳定裕度增加.
- 航空发动机 /
- 燃烧室气动优化 /
- 大涵道比风扇 /
- 并行遗传算法 /
- 流场计算 /
- 参数化方法
Abstract: The automatic optimization method was applied to 3D aerodynamic design of a high bypass ratio fan blade. A genetic algorithm was used as numerical optimization method, and multiCPU parallel optimization was realized by using network communication protocol to greatly shorten the optimization time. The fan blade profiles, stack line, the flow passage in meridian plane, installation angle and chord length were set as design variables. The parameterization method based on modifications to these design variables was combined with the range limit of the design variables in the genetic algorithm, and it controlled and rationalized the individuals generated in optimization process.Dentons viscous volume force method was applied to flow field calculation of the fans,decreasing the calculation time and further reducing the optimization time. The optimization goal was set to improve the fan efficiency and keep total pressure ratio and mass flow rate unchanged at the design point, and the optimized fans performance at offdesign points was checked. The original fan was optimized in two steps, in which the design parameters were adjusted according to aerodynamic characteristics of the fan to be optimized. The final optimized fans efficiency increased from 09463 to 09560, and stability margin increased from 112% to 219%. Mach number of shock wave at blade tip section of the final optimized fan decreased slightly, and the shock wave leaned to the blade passages. Therefore, loss of the shock wave and its effect on boundary layer decreasd, and the stability margin increased.
- aeroengine /
- combustoraerodynamic optimization /
- high bypass ratio fan /
- parallel genetic algorithm /
- flow field calculation /
- parameterization method

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