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为了使现有轻型航空发动机在海拔高度为10 km的高空保持原有动力性不变,需要采用二级涡轮增压,保持发动机在不同海拔高度时稳压腔内的进气密度与海平面的一致.对原发动机在一级涡轮增压的基础上进行二级涡轮增压匹配.这里采用AVL-Boost软件建模,根据实验校验一级涡轮增压模型,然后建立二级涡轮增压模型.考虑小型离心式压气机高海拔工作特性受雷诺数影响,确定了压气机匹配工作点.计算表明,匹配方案可行,原发动机满足飞行设计要求.
In order to maintain the original dynamic performance of the existing light aeroengine at a altitude of 10 km above sea level, a two-stage turbocharger needs to be adopted to keep the intake air density and the sea level of the pressure regulating chamber at different altitudes The first engine is based on the first stage turbocharging based on the second stage turbocharger matching.Using AVL-Boost software modeling, according to the experimental verification of a turbocharged model, and then the establishment of two turbocharged model Considering the high altitude working characteristics of small centrifugal compressor, the match point of compressor is determined by the Reynolds number.The calculation shows that the matching scheme is feasible and the original engine meets the requirements of flight design.