| 基于声学CT重建航空发动机燃烧室出口温度场的仿真研究 |
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| 引用本文： | 王交峰,田丰,田金光.基于声学CT重建航空发动机燃烧室出口温度场的仿真研究[J].沈阳航空工业学院学报,2009,26(2). |
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| 作者姓名： | 王交峰 田丰 田金光 |
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| 作者单位： | 1. 沈阳航空工业学院计算机学院,辽宁,沈阳,110136
2. 中航一集团沈阳黎明航空发动机(集团)有限责任公司技术中心测试室,辽宁沈阳,110034 |
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| 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.
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| 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 |
Temperature field simulation at aeroengine combustor exit on acoustic computer tomography |
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| WANG Jiao-feng,TIAN Feng,TIAN Jin-guang.Temperature field simulation at aeroengine combustor exit on acoustic computer tomography[J].Journal of Shenyang Institute of Aeronautical Engineering,2009,26(2). |
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| Authors: | WANG Jiao-feng TIAN Feng TIAN Jin-guang |
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| Institution: | 1.College of Computer Science;Shenyang Institute of Aeronautical Engineering;Liaoning Shenyang 110136;2.Testing Chamber of Technology Center;Shenyang Liming Aviation Engine Company Ltd.;Liaoning Shenyang 110034 |
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| Abstract: | 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-sults 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... |
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| Keywords: | aeronautics and space propulsion systems acoustic pyrometry aeroengine combustor exit temperature field |
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