China Mechanical Engineering

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Study on Multi-disciplinary Design Optimization on Civil Turbofan Engines

LUO Ju;GUO Fushui   

  1. AECC Commercial Aircraft Engine CO,Ltd,Shanghai,200241
  • Online:2019-08-10 Published:2019-08-14

民用涡扇发动机总体多学科设计优化研究

罗钜;郭福水   

  1. 中国航发商用航空发动机有限责任公司,上海,200241
  • 基金资助:
    上海市科委基础研究领域资助项目(14DJ1400300)

Abstract: In order to take account of the couplings of various disciplines and balance the conflicts of different indicators, a multi-disciplinary design optimization platform was built based on collaborative optimization strategy for the civil high bypass ratio turbofan engines in the conceptual design phases, which included analysis and estimation modules of thermodynamic cycle, size/mass, fuel consumption, NOx emission, noise, component aerodynamics and structure strength. Based on NSGA-Ⅱ (non-dominated sorting genetic algorithm Ⅱ) algorithm, a multi-objective optimization study of engine scheme designs was conducted. Through the researches, the following conclusions are obtained: bypass ratio and turbine inlet temperature have greater effects on the fuel consumption and total weight. Besides, the distribution of the fuel consumption and total mass in Pareto solutions is similar to a conic.

Key words: turbofan engine, multi-disciplinary design optimization, collaborative optimization strategy;multi-objective optimization

摘要: 为了在概念设计阶段充分考虑各学科间的耦合和平衡各指标间的冲突,以某型民用大涵道比涡扇发动机为研究对象,基于协同优化策略构建了发动机总体多学科设计优化平台,该平台集成了热力循环分析、尺寸/质量估算、轮挡燃油估算、污染物排放估算、整机噪声估算以及部件气动和结构强度分析等多个模块。采用非支配排序遗传算法进行了发动机总体方案多目标优化研究。计算结果表明:涵道比和涡轮进口温度对轮挡燃油和整机质量的影响较大,后两者在Pareto解中呈近似二次曲线式的分布规律。

关键词: 涡扇发动机, 多学科设计优化, 协同优化策略, 多目标优化

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