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邱奥祥, 桑为民, 张桐, 安博, 李栋, 张彬乾. 翼身融合布局飞机分布式推进边界层吸入效应影响研究. 力学学报, 2024, 54(8): 1-20. DOI: 10.6052/0459-1879-23-552
引用本文: 邱奥祥, 桑为民, 张桐, 安博, 李栋, 张彬乾. 翼身融合布局飞机分布式推进边界层吸入效应影响研究. 力学学报, 2024, 54(8): 1-20. DOI: 10.6052/0459-1879-23-552
Qiu Aoxiang, Sang Weimin, Zhang Tong, An Bo, Li Dong, Zhang Binqian. Research on the effect of boundary layer ingestion of blended-wing-body aircraft with distributed propulsion. Chinese Journal of Theoretical and Applied Mechanics, 2024, 54(8): 1-20. DOI: 10.6052/0459-1879-23-552
Citation: Qiu Aoxiang, Sang Weimin, Zhang Tong, An Bo, Li Dong, Zhang Binqian. Research on the effect of boundary layer ingestion of blended-wing-body aircraft with distributed propulsion. Chinese Journal of Theoretical and Applied Mechanics, 2024, 54(8): 1-20. DOI: 10.6052/0459-1879-23-552

翼身融合布局飞机分布式推进边界层吸入效应影响研究

RESEARCH ON THE EFFECT OF BOUNDARY LAYER INGESTION OF BLENDED-WING-BODY AIRCRAFT WITH DISTRIBUTED PROPULSION

  • 摘要: 翼身融合布局是指机翼和机身高度融合的全升力面飞机外形, 在提升巡航效率和减排降噪等方面展现出明显的性能优势和发展潜力. 采用雷诺平均Navier-Stokes方法结合基于叶素理论的体积力模型, 针对翼身融合布局民机分布式推进边界层吸入(BLI)效应影响下的绕流流场进行了数值研究. 首先, 将翼身融合布局民机分布式BLI推进构型简化为涵道风扇-机翼段耦合构型, 计算涵道风扇质量流率小于1、等于1以及大于1的3个工况, 对比分析了滑移网格方法、冻结转子方法和基于叶素理论的体积力模型法的流场细节、计算精度以及计算效率. 其次, 建立分布式BLI推进-机翼耦合构型, 对此构型不同转速下的绕流流场进行对比分析, 探究并验证本文所建立的分布式BLI推进系统抑制分离的能力. 最后, 将分布式BLI推进安装于翼身融合布局飞机概念方案NPU-BWB-300机翼与机身的融合段, 探究其对NPU-BWB-300绕流流场的影响. 研究结果表明: 滑移网格方法、冻结转子方法和基于叶素理论的体积力模型方法均可以较好地刻画涵道风扇边界层吸入效应的流场细节; 本文所建立的分布式BLI推进系统具备抑制分离的能力, 将其应用于NPU-BWB-300也可以取得较为明显的改善分离流场的效果.

     

    Abstract: The blended-wing-body configuration refers to the full lift surface aircraft shape that greatly integrates the wing and fuselage, demonstrating significant performance advantages and development potential in improving cruise efficiency, reducing emissions, and reducing noise. Using Reynolds averaged Navier-Stokes method and body force model based on blade element momentum theory, the separation flow field under the effect of boundary layer ingestion caused by the distributed propulsion installed on the civil blended-wing-body aircraft was preliminarily investigated. Firstly, the distributed BLI propulsion configuration of the civil aircraft with a blended-wing-body layout was simplified to the duct fan-wing segment coupling configuration, and three working conditions of duct fan, indicating that the mass flow rate is less than 1, equal to 1, or greater than 1, were calculated respectively. The details of the flow field and calculation accuracy and efficiency of sliding mesh method, frozen rotor method, and body force model method based on blade element momentum theory were compared and analyzed. Secondly, the distributed BLI propulsion -wing coupling configuration was established. Comparative analysis of the flow field around the distributed BLI propulsion -wing coupling configuration at different rotational speeds is conducted to explore and verify the ability of the distributed BLI propulsion system established in this paper to suppress separation. Finally, the distributed BLI propulsion was installed on the wing-body fusion section of NPU-BWB-300, a conceptual civil BWB aircraft, to explore its influence on the aerodynamic characteristics and separation flow field of NPU-BWB-300. The results show that the sliding mesh method, the frozen rotor method and the body force model method based on the blade element theory can all describe the flow field details of the boundary layer ingestion of the duct fan. The distributed BLI propulsion established in this paper has the ability of restraining separation, and its application to NPU-BWB-300 can also achieve a relatively obvious effect of improving the separation flow field.

     

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