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Abstract
It becomes more difficult and expensive to design and test new combustors for large jet engines which require increasing mass flow rates and temperature and pressure levels. Therefore, it is important to study the scaling laws of combustor performance and to provide the modeling rules for practical use for the development and application of engines. This paper deals with the modeling theory of combustion chambers. Based on similarity principles and some typical combustion mechanisms, different rules for combustor modeling, are systematically suggested, particularly for the modeling of gas turbine combustors. These rules may be applied to the design and testing of combustion systems. Moreover as the theory has extensively correlated with the operating parameters of the combustor, it may also be used to predict the combustor performance.