Research On TBCC Adjustable Binary Inlet Design Method

With the development of aerospace technology,hpersonic vehicle has become a hot research topic.The dynamic system of hypersonic vehicle is the key technology to restrict its development,and it needs to meet the requirements of the wide range of Maher number.TBCC(Turbine Based Combined Cycle)is a kind of superior hypersonic flight power technology program.Inlet is an important part of the TBCC,its role is to slow down the flow,and provide to the combustion chamber.In this paper,the TBCC inlet is designed,including the design of the ramjet channel,the design of the turbine channel,the design of the dual channel and the regulation of the design.(1)Choose Ma6 as the design point,design the ramjet which can also work at Ma2.5;Design the turbine channel,so that it can be combined with the ramjet channel.(2)Compare the characteristics and performance of different combinations.The performance of various schemes is studied,and the numerical simulation is carried out for the various positions of the modal transformation process.(3)Propose a new scheme,explore its regulation law.Change the length of the board and the pivot point position,finish the steady state analysis of the modal transformation.Study the influence of these factors on the performance of modal transformation,(4)Through the wind tunnel experiment of the adjustable inlet model,study the change of flow coefficient and total pressure recovery in the process of mode transformation.