一种改进的冲压发动机一维流分析模型

An Improved One-Dimensional Analysis Model for Ramjet

关键词:  冲压发动机  燃烧室  一维流分析  跨声速求解  性能计算

Key words:  Ramjet  Combustor  One-dimensional flow analysis  Transonic solution  Performance calculation

摘要:

为了建立一种适用于冲压发动机的不依赖于实验数据的、可以实现多区域跨声速区稳定求解的一维流分析计算模型，通过对目前已有的各种冲压发动机一维流分析模型进行分类、总结和对比分析表明，依靠实验静压数据的一维模型难以满足实际性能计算的需要，去掉等压段假设并用摩擦项替代芯流经验公式是可行的，多区域跨声速区求解可以通过变量替换法实现。在此基础上，建立了一种改进的适用于冲压发动机的一维流快速计算模型，该算法不依赖于实验数据，可以实现多区域的跨声速区稳定求解。将算例结果与实验数据相比，总压误差在5.2%以内；与某模型的结果相比，总温相差1.3%，马赫数相差2.7%。新模型的结果在马赫数、静压、总压、总温等参数的计算上较准确，改进方法可方便快速地用于冲压发动机的性能计算。

Abstract:

In order to establish a kind of suitable ramjet model which does not depend on the experimental data and it can be used to solve the multiple regions of transonic，the existent one-dimensional flow analysis models for ramjet were classified，summarized and comparatively analyzed. The results show that one-dimension models relied on the experimental static pressure data were difficult to meet the computing needs of the actual performance calculation. The isotonic section assumption could be removed，the empirical formula of core flow could be replaced with friction term and the transonic region could be solved by defining a new variable. According to this，an improved one-dimensional flow model for ramjet was established，which could get rid of the needs of the experimental data and solve the multiple regions of transonic. The numerical results were compared with the experimental data，the total pressure error was within 5.2%. Compared with other model ’ s results，the maximum difference in total temperature was 1.3% and the maximum difference in Mach number was 2.7%. The results show good agreement in static pressure，Mach number，total pressure，total temperature etc. The consistent results demonstrate that this improved method can be used for ramjet performance calculation.