Analysis Of Combustion And Structural Characteristics Of Combustor Liner

The combustor liner is an important component of the combustion of the aero-engine combustion chamber and the release of combustion energy.The design of each part of the combustion chamber has a critical impact on the performance of the aeroengine.At the same time,the flame tube requires a very harsh working environment,and during the combustion the high temperature thermal load generated process will cause great damage to the combustor liner.Therefore,the performance of the combustor liner determines the overall performance of the aeroengine,which determines the key to the efficient,stable and longevity of the aero engine.In this thesis,a new type of combustor liner structure is designed.The overall design parameters of the combustor liner are designed and calculated,and the flow distribution of the combustor liner and the design of the cooling hole are determined.The head of the flame tube adopts a three-stage radial swirler,and its optimal structure is established on the basis of previous research.This study adopts experimental design conditions,which are intended to prepare for the later research and optimization of the flame tube design.The design conditions are different when the pilot stage is working separately and the pilot stage and the primary stage are working at the same time.In the case of quantity,the simulation method combined with the fluid-thermal-solid coupling method is used to analyze the combustion performance and structural performance of the combustor liner.The results show that the design of the design of the combustor liner and the swirler is more reasonable and can meet the basic work requirements of the aeroengine.In terms of the combustion performance of the combustor liner,the combustor liner basically meets the flow field characteristics required for combustion,and can form a negative velocity low pressure region at the main combustion zone of the combustor liner,which has better reflow characteristics;the mixing holes and the cooling holes jet is reasonable,and the airflow distribution is reasonable;With the increase of fuel quantity,the combustion performance of the combustor liner has a tendency to deteriorate when the pilot stage works alone.When the pilot stage and the primary stage work at the same time,the overall combustion performance is better,the combustion is stable,and the stable combustion is satisfied;The combustor liner pollution has the characteristics of low pollution;The outlet temperature has a good distribution,and when the pilot stage and the primary stage work at the same time,the trend that the combustor liner outlet characteristics becomes better is very obvious as fuel quantity increases.The overall wall temperature characteristics of the combustor liner are better.As the fuel quantity increases,the hot-spot area is more evenly distributed,the temperature gradient distribution is better,and the high temperature extreme value appears at the exit of the combustor liner;The thermal stress and the thermal strain of the flame tube has a high consistency with the high temperature thermal load,indicating that the design of the combustor liner is reasonable.The concentration of thermal stress and strain appears at the end of the combustor liner,which needs to be treated in the process of later design and optimization.