某型无人机进气道扩压器设计与优化  

Design and Optimization of Inlet Diffuser for UAV

作　　者：唐宜文 钟易成[1] 万齐仁 TANG Yiwen;ZHONG Yicheng;WAN Qiren(College of Energy and Power Engineering,Nanjing University of Aeronautics and Astronautics,Nanjing 210016,China)

机构地区：[1]南京航空航天大学能源与动力学院,江苏南京210016

出　　处：《机械制造与自动化》2023年第4期44-47,共4页Machine Building & Automation

摘　　要：依据喷气发动机喉道扩压段设计方法,通过给定的设计参数,初步设计扩压段方案,采用CFD方法对扩压段性能进行仿真分析。通过调整喉道位置和面积、出口面积等参数;优化扩压段结构参数。研究调整扩压比、改变喉道位置对进气道性能的影响规律,通过仿真分析验证该方法设计的扩压段的有效性。According to the design method of the nozzle diffuser section of jet engine,the preliminary diffuser section scheme was designed with the given design parameters,and the performance of the diffuser section was simulated and analyzed by CFD method.By adjusting the parameters of the throat position and the area of the outlet area,the structural parameters of the diffuser section were optimized.The effect regularity of the adjusted diffuser ratio and changed position of the throat on the performance of the inlet was analyzed and simulated,which verifies the vadility of the designed scheme of the difussion section.

关 键 词：扩压段 仿真设计优化 性能评估 

分 类 号：V231.3[航空宇航科学与技术—航空宇航推进理论与工程]