摘要
结合声波传感器与计算机断层成像技术,提出一种航空发动机燃烧室环形出口温度场重建的方法。首先确定了航空发动机燃烧室出口处声波速度与温度的数学模型,然后用最小二乘方法对航空发动机燃烧室环形出口温度场进行了重建。仿真结果表明,温度场重建结果的相对平均误差在3%以内,相对最大误差在6%以内,该方法具有测温范围宽,可测得航空发动机燃烧室环形出口截面温度分布等优点。
Combined with acoustic sensors and computer tomography, a new temperature field reconstruction method of aeroengine combustor toroidal exit was proposed. Mathematical model between acoustic velocity and temperature was determined, and the temperature field at aeroengine combustor exit was reconstructed by the least square. Simulation re-suhs show that the relative average error is less than 3% and the relative maximum error is less than 6%, and it is of ad - vantages such as wide temperature measurement scope and ability to measure aeroengine combustor toroidal exit cross - section temperature distribution.
出处
《沈阳航空工业学院学报》
2009年第2期38-42,共5页
Journal of Shenyang Institute of Aeronautical Engineering
基金
航空科学基金(2007ZD54005)
关键词
航空、航天推进系统
声学测温
航空发动机燃烧室出口
温度场
aeronautics and space propulsion systems
acoustic pyrometry
aeroengine combustor exit
temperature field
