Buckling is the most common failure mode for thin shell type structures. The buckling strength of such structures can be improved by increasing the thickness but with the penalty of increased weight. This phenomenon is not desirable for aero engine applications where the weight of the air borne structure plays a vital role in the performance of the engine. There have always been efforts to increase the buckling strength with disproportionate weight penalty. The aero gas turbine engines with After Burner capability meant for thrust augmentation posses Jet pipe liner. The weight of aero gas turbine engine must be kept low for better aero performance resulting in maximum pay load capacity. This can be achieved by increasing the Thrust to Weight ratio. In order to increase the aero-engine thrust to weight ratio, weight of each module of the engine must be kept low. The weight of a conventional Jetpipe liner of aero-engine for similar buckling strength can be reduced by the introduction of corrugation in the liner. The basic geometric parameters of the liner i.e. diameter and length are fixed based on aerodynamics and performance requirements. Considering these constraints, a baseline configuration of the corrugated liner from structural aspect is developed. This baseline configuration is further improved using finite element analysis by iterating the crucial parameters of the corrugation. Based on this study, a feasible corrugated liner configuration for high thrust class of aero-engine is arrived at meeting buckling requirement for flame out condition. Also, the results of a comparative study of conventional and corrugated liner from buckling strength point of view are presented.
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