Research On Optimization Design Of TBCC Bending Shock Wave Compression Adjustable Inlet

Because of high specific impulse,reliable and other advantages,TBCC engine has become one of the main development directions of hypersonic propulsion system.Inlet that used as the intake capture system for the TBCC engine is the primary compression component of engine,which can decelerate the air flow and increase the pressure.The overall performance of the inlet directly restricts the stability of the engine in a large mach number range.2D TBCC inlet develops rapidly,the traditional ramp compression method can not meet the future demand,it is of great significance to explore a new compression method for the TBCC inlet.In this paper,the ramjet channel and the turbine channel are designed on the basis of the curved shock compression,the excellent external compression surface is found by multi-objective optimization,by this basis,a variety of double channel over-under schemes are proposed for simulation and analysis,to investigate the influence of different layout on the performance of the inlet.(1)Based on the Inverse design method of wall pressure distribution,made a multi-objective optimization of Curved shock external compression surface through Isight software,combined with the optimization results,a series of definite geometry hypersonic inlet was designed,the Optimal inlet was compared to the three-ramp compression inlet in the same constraint condition.The results shows that:when Ma? Changes from 3 to 5,the mass flow capture of curved shock inlet was increased by 5.7%,8.6%and 10.6%,its total pressure recovery was increased by 3.6%,1.8%,5.5%and 7.4%when Ma? Changes from 2.5 to 5.(2)Select two kind of inlet with better performance to simulate and analysis three-dimensional flow field,the characteristics of the optimized inlet are studied when the starting position of the sidewall is different.The optimal scheme is compared with the three-dimensional performance of three-ramp compression inlet under the same constraint conditions,the mass-flow-ratio and total pressure of throat are higher under the off-design point,and its performance advantage is obvious.(3)Kinds of 2D curved shock compression TBCC inlet over-under case are put forward innovatively,simulate each case under the condition of that double channel is completely open at Ma2.5,the advantages and disadvantages of the over-under case are compared,and the length of the curve that impacts on the double channel performance is especially studied.(4)On the basis of 2D double channel aerodynamic model,turbo channel take a shape that square change to a circular,two kinds of 3D aerodynamic model of TBCC inlet are designed to analyze the flow field,the aerodynamic performance of the turbine channel of each case is especially compared.