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The turbine based combined cycle propulsion system, a hopeful air-breathing propulsion system for high speed aircrafts, needs to work in a wide Mach number range. To meet the requirement, the variable-geometry internal waverider inlet based on improved Internal Conical of Flowfield C+ is proposed in this paper. Firstly, the axisymmetric basic flowfield is improved to an Internal Conical of Flowfield C+ with a higher external compression ratio, which befit to relieving the mass flow choke under low Mach number conditions. Secondly, a variable-geometry design method is proposed for the internal waverider and turbine based combined cycle inlet. In order to ensure sealing of variable geometry inlet, a new arrangement of the inlet osculating planes is proposed. And when the inlet geometry varies to expand the throat, the shape of cross-sections always keeps smooth. Such design contributes to a waverider shock structure without corner flows and high efficiency in wide speed range. Finally, CFD results indicate that the internal waverider and turbine based combined cycle inlet exhibits excellent aerodynamic performance characteristics, with high mass flow coefficient and low total pressure loss, thus enabling a great improvement for the turbine based combined cycle system.

A New Design of Variable-Geometry TBCC Inlet Based on an Internal Waverider Concept