Abstract: In order to develop a type of fan/booster suitable for high-altitude and low Reynolds number flow to solve the problem of HALE UAV power demand， the aerodynamic design of fan/booster working under the condition of high altitude and low Reynolds number is performed. The design process includes 1D thermodynamic calculation， S2 through flow design， blade profiling design and 3D numerical calculation. After the design iteration is carried out for several times， the optimum blade profile suitable for high altitude and low Reynolds condition is acquired. The results of 3D numerical calculation indicate that the core and bypass performances of fan /booster accord with the requirements of design targets， and have a high stability margin at high altitude and low Reynolds number. Compared with the performance of current engine fan component， the newly designed fan/booster has better ability for operation at high altitude and can satisfy the performance requirements addressed by overall engine.

Key words: Low Reynolds number;Fan;Compressor;Aerodynamic design;Blade profiling;Numerical simulation

摘要： 为发展一型适用于高空低雷诺数流动的风扇/增压级部件，解决高空长航时无人机动力对部件的技术需求，针对高空低雷诺数下的风扇/增压级进行了气动设计，设计过程包含了一维热力计算、S2通流设计、叶片造型设计和三维数值计算分析。经过多轮设计迭代后，得到了适用于高空低雷诺数条件下的最优叶型。三维数值计算结果表明：风扇/增压级的内、外涵性能都达到了设计指标的要求，且在高空低雷诺数下有较高的稳定裕度。与现有发动机风扇部件性能进行对比得出：新设计的风扇/增压级具有较好的高空工作能力，可以满足总体对风扇/增压级的性能需求。

关键词: 低雷诺数;风扇;压气机;气动设计;叶片造型;数值模拟