摘要
本文针对低雷诺数工作条件下的某风扇/增压级进行了通流设计、流道结构设计、各叶片排叶片几何设计及三维数值模拟。在完成气动设计循环、确定风扇/增压级流道结构形式和叶片叶型几何造型等根据设计需求进行的工作之后,使用商用软件NUMECA对该风扇/增压级12 km、0.6 Ma飞行条件100%和95%折合转速以及地面标准大气条件86.6%(简称87%)和80%折合转速的特性曲线进行了数值计算。前者用于考察巡航状态性能及流场特征,后者对应于地面起飞的最大状态。就目前设计方案的三维数值模拟结果表明,外函完全达到了设计需求指标的要求,内函除效率外,其它均达到设计要求。
According to the requirements of collective capability, a low-pressure compressor such as fan/compressor worked at low Reynolds Number was designed by the through flow program. The design including configuration of flow passage and the blade geometry of each blade row was finished. Then, the fan/compressor was calculated by three-dimension numerical simulation software named NUMECA （Numerical Mechanics Application）. Referring to aerodynamic design circulation, the configurations of flow passage and blade profile geometry of fan/compressor were confirmed; furthermore, based on the 12kin, 0.6Ma flight condition the aerodynamic parameters were calculated at 100%, 95% corrected speed in order to evaluate the cruise performance and the feature of flow field. On the other side, the characteristic curve of 86.6%, 80% corrected speed under the condition of the standard ground atmosphere was obtained by calculation. It could be used to review the fan/compressor performance operated in maximum region of its ground take-off. The three-dimension numerical simulation result indicates that the design requirements of bypass duct have been realized completely, and the design requirements of core duct were almost realized expects its efficiency.
出处
《燃气涡轮试验与研究》
2007年第3期18-22,共5页
Gas Turbine Experiment and Research
基金
国家自然基金资助项目(50136010)
关键词
低雷诺数
风扇/增压级
气动设计
low Reynolds Number
fan/compressor
aerodynamic design
