为了研究超声速燃烧室尺度放大后，保持火焰稳定边界相对于基准燃烧室不变，凹腔火焰稳定器几何参数应遵循何种放大准则的问题，基于已有的Driscoll凹腔稳焰数学模型，采用典型的单凹腔矩形截面燃烧室作为基准燃烧室，分别计算基准燃烧室在贫燃和富燃状态时的火焰稳定准则数Da_NP，再按照燃烧室尺度放大定义写出尺度放大燃烧室的稳焰准则数表达式DaNP'，将稳焰边界不变作为约束条件，构建尺度放大准则方程式Da_NP=DaNP'，求解准则方程式获得凹腔几何参数放大准则表达式，绘制准则特性曲线，分析归纳近似准则，并通过数值计算方法初步验证准则的有效性。采用Driscoll凹腔稳焰模型的尺度效应分析结果表明，燃烧室放大一定倍数n后，无法通过调整凹腔长度和深度放大倍数k₁和k₂使得贫燃熄火边界保持不变；但是，可以通过调整参数k₁和k₂使得富燃熄火边界保持不变，此时凹腔几何参数遵循的放大准则近似为k1≈k2≈n1/4。

In order to investigate the magnifying rule of cavity flameholder， theoretic and numerical studies were conducted on the scaled supersonic combustor under the condition of the constant flame blowout limits. First， based on the Driscoll cavity blowout limits model including lean and rich blowout limits embranchment model， a typical rectangular section combustor with single-cavity was employed as the benchmark combustor to calculate flame stabilization Damkohler number Da_NP. Secondly， according to the definition of scaling effect of combustor， flame stabilization Damkohler number DaNP' expression of the scaled combustor was derived. Thirdly， by keeping the flame blowout limits constant， the equation Da_NP=DaNP' was deduced. By solving the above equation， the magnifying rule expression of cavity flameholder was acquired， and the characteristic curves of scaling effect were drawn. The approximate magnifying rule was obtained by means of analyzing the curves. Finally， the availability of the rule was demonstrated elementarily by numerical simulation. The research results show that the flame lean blowout limit could not be kept constant through adjusting scaling coefficient k₁ and k₂ of cavity length and cavity depth when a combustor is scaled to be n of the benchmark combustor， however， the flame rich blowout limit could keep constant through adjusting scaling coefficient k₁ and k₂ of cavity length and cavity depth when a combustor is scaled to be n of the benchmark combustor， the approximate magnifying rule is k1≈k2≈n1/4.

V231.2