| As an important military strategic resource,hypersonic aircraft has huge military value and potential economic value.As one of the core equipment for the development of hyperaircraft,the adjustable nozzle of the directly connected test bench is responsible for the important task of adjusting the outlet airflow field.Because the front end of the nozzle is connected to the combustion chamber and the wall of the nozzle is impacted by the high temperature and high pressure supersonic airflow,it is necessary to design the panel of the adjustable nozzle to meet the working requirements under extreme conditions,and comprehensively consider the design parameters when designing The effect on the efficiency of the heat recovery cycle and the stiffness of the bushing.This paper analyzes the operating state of the adjustable nozzle for 10 s at a total temperature of 1000 K,a total pressure of 2MPa,and a Mach of 2.5,and studies the effects of different cooling jacket structure parameters on the overall structural rigidity and heat recovery capacity.The indicators are coordinated to optimize the panel.This article mainly includes the following contents:First,the sealing structure and transmission structure of the adjustable nozzle of the direct connection test bench are designed.The sealing structure includes the static seal between the boxes and the dynamic seal between the boxes and the panel.In view of the compact internal space of the nozzle,an external rotating shaft is used to control the rotation of the panel.Secondly,the aerodynamic analysis of the rotatable panel is carried out to study the change of the physical quantity inside the nozzle when the Mach number is the highest.Taking the corresponding physical quantities as boundary conditions,a numerical calculation model for the flow and heat transfer of a single-channel cooling jacket is established,and the temperature change of the throat section under working conditions is analyzed.Analyze the influence of convective heat transfer characteristics under different parameters by changing the parameters.Then,the model panel is simplified to Euler beam,and the nozzle flow field information is used as the input load of the model panel,and the force and moment based on the change of the rotation center are obtained by fitting.At the same time,the deformation equation of the shaped panel is constructed based on the thermoelastic theory,and the deflection and maximum deformation of the shaped panel and the lining layer are obtained by analytical methods.Use ANSYS to perform thermal-fluid-solid simulation analysis to obtain the maximum deformation,and compare with analytical calculations.Finally,the test method is used to establish the sensitivity model of the nozzle panel based on the heat transfer coefficient and the stiffness of the lining,analyze the contribution of each parameter to the heat transfer coefficient and the structural stiffness,and screen out the key variables.The polynomial response surface model is used to construct an approximate model,the multi-objective genetic algorithm is used to generate the optimal solution set,and the structural parameters are obtained and then simulated and verified.The results show that the optimization method adopted in this paper can effectively improve the ability of the nozzle-type panel to recover waste heat,and at the same time improve the overall rigidity of the panel.The nozzles with optimized parameters are processed and tested,and the results show that the nozzle panel meets the design requirements. |
