Optimization design and analysis of the exhaust system considering multi-component influences

The design of an aero-engine exhaust system that integrates superior aerodynamic performance with effective infrared radiation (IR) suppression is crucial for advancing military technology. This study addresses the complex interactions among various components of an aircraft engine by focusing on an exhaust system that incorporates the influences of both the turbine and afterburner. Utilizing commercial software for flow field calculations and the discrete transfer method for assessing infrared radiation intensity, the research employs a hierarchical optimization strategy. This strategy targets four structural design variables and five infrared coating variables, with a detailed analysis of their impacts on aerodynamic performance and infrared characteristics. Through the application of main effect relationships and the control variable method, the study delves into the aerodynamic and thermal radiation properties to elucidate the underlying physical mechanisms. The outcome is the development of a high-performance exhaust system that, compared to the baseline model, demonstrates a 1.31 % improvement in flow coefficient, a 3.19 % increase in thrust coefficient, a 46.88 % reduction in 0° infrared intensity, and a 17.31 % decrease in average infrared intensity at angles of 30°, 60°, and 90°.