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针对目前航空发动机喷出的高速气流的流量测量问题,本文利用槽道流量计,对高速可压管流,尤其是马赫数大于0.3的管流流量计量进行初步研究。首先通过在槽道流量计入口处设置一个拉瓦尔喷管,构建一个产生高速可压缩气流的平台,其次,采用数值模拟的方法探究出影响流量计量的四个因素:拉瓦尔喷管喉道的半径大小,喉道距槽道流量计入口的距离,喷管扩张段的扩张角大小以及第二喉道的宽度。并通过数值模拟给出各因素对其测量性能的影响。
In order to solve the problem of the flow measurement of the high-speed airflow emitted by aeroengine, a channel flowmeter is used to study the flow measurement of the high-speed tube flow, especially the Mach number greater than 0.3. Firstly, a Laval nozzle is set up at the inlet of the channel flow meter to build a platform that generates high-speed compressible airflow. Secondly, four factors influencing the flow measurement are explored by numerical simulation: Laval nozzle throat The radius, the distance of the throat from the inlet of the channel flowmeter, the expansion angle of the divergent section of the nozzle, and the width of the second throat. The influence of each factor on its measurement performance is given by numerical simulation.