Research On The Design Method Of TBCC Adjustable Hypersonic Internal Rotation Inlet

With the rapid development of the global aerospace industry,hypersonic vehicles have become a research hotspot in the world.The key technology of hypersonic vehicles is the propulsion technology,hypersonic vehicles need to work in a wide range of Maher Numbers,however,the single dynamic propulsion system can not meet this requirement,the combined cycle propulsion system as the dynamic system of hypersonic vehicles,which integrates several single dynamic propulsion system,so it enables hypersonic vehicles to fly in a wide range of speeds,In recent years,Turbine-Based Combined Cycle(TBCC)dynamic system has become the main development direction of the combinatorial power technology.In the present paper,a TBCC inward turning variable geometry inlet was designed and investigated numerically,including the design of high-speed duct which can work in a wide range of speeds,the design of dual-duct,the design of three-duct and the design of the method of over-under.Firstly,the innovative basic flowfield with the pressure rise law of arc-tangent function and controlled centre body was established,then by adjusting the design parameters of the basic flowfield with excellent performance,a inward turning inlet with excellent performance and wide range flying capabilities was designed and optimized.In this paper,a over-under TBCC inward turning variable geometry inlet for hypersonic vehicle with Mach 2 to Mach 6 was designed and investigated numerically.Using CFD Tools,the three-dimensional flowfield characteristic of the inlet was shown at different operations over Mach 2 to 6,the change law of the overall performance parameters of inlet was analyzed during the mode transition and the effects of transition Mach number on inlet mode transition were investigated.A three-channel over-under adjustable inward turning inlet was designed and investigated numerically.Using the method of three-dimensional numerical simulation,the ramjet mode and transition mode were studied and analyzed.During the mode transition,when the low-speed channels of inlet closed symmetrically and closed asymmetrically,the change law of the key performance parameters of the three channels with the closure low-speed channel was investigated.In this paper,the effects of the back pressure of the turbine channel exit or the ramjet channel exit on the interference characteristics among channels of a three-channel over-under adjustable inward turning inlet were investigated.The result of the investigation indicates that using the isolator back pressure or the turbine channel back pressure can internally redistribute mass flow and adjust the turbine distortion.