航空发动机燃烧室出口温度的高低及出口温度场的均匀程度，直接影响到发动机的工作寿命和输出功率的大小。
The aero-engine combustion outlet temperature makes a strong impact on the life of engine and the power of the engine output.
在二元试验燃烧室上，研究了四种掺混孔设计方案对燃烧室出口径向温度分布影响。
The exit radial temperature profiles formed by four configurations of dilution hole design have been studied experimentally on a two-dimensional experimental combustor.
分析和比较了两种计算方法，这些方法已应用到燃烧室出口高温燃气温度测量中。
These methods have already been used for the gas temperature measurement at the exit of the high temperature rise combustor.
分析和比较了两种计算方法，这些方法已应用到燃烧室出口高温燃气温度测量中。
These methods have already been used for the gas temperature measurement at the exit of the high temperature rise combustor.
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