航空活塞发动机高空模拟试验台温度系统研究  

Study of Temperature System on ASTF for Reciprocating Aeroengine

作　　者：袁领双[1] 刘猛[1] 王浚[1] 

机构地区：[1]北京航空航天大学航空科学与工程学院,北京100083

出　　处：《中国工程科学》2007年第12期53-56,共4页Strategic Study of CAE

摘　　要：在航空活塞发动机高空模拟试验中,模拟温度低、温度范围跨度大,高空模拟试验台(简称高空台)上应用了空气制冷和电加热两种调温措施,控制难度较大。将模拟温度划分为高温、常温、低温三个温度段,分别应用三种不同的调节方式进行温度控制;在系统数学建模和温度变化动态特性分析基础上,对高空台温度系统的调节过程进行了仿真研究,结果表明该方法能够满足温度的调节速度和控制精度要求。为了满足带涡轮增压器的航空活塞发动机对进气温度的要求,建立了涡轮增压器与中冷器之间的数学换热关系,以稳态时的发动机进气温度为例进行了仿真计算,结果与实际情况相符。Air cooling unit and electrical heater are used to simulate temperature with wide range on Altitude Simulation Test Facility （ASTF） for reciprocating aeroengine, it is difficult to achieve controlling accurately. In this paper simulated temperature is divided into three segments of low, normal and high temperature and distinct strategies are applied to regulate temperature respectively. Based on the dynamical analysis and modeling of temper- ature change, research is performed on the regulating process for ASTF temperature system, and simulation results show that these strategies could satisfy the demand for speed and precision of temperature controlling. For the inlet temperature of airflow into reciprocating aeroengine through turbocharger, the mathematic relationship for heat transfer between turbocharger and intercooler is built. Simulating calculation on an example for engine in steady state at different altitude is carried out. The results present that calculation trend is consistent with the fact.

关 键 词：航空活塞发动机 高空模拟试验台 温度 仿真 

分 类 号：V234[航空宇航科学与技术—航空宇航推进理论与工程] V263.4