Aerodynamic Design Of Turbo For Solid Rocket Turbo Ramjet Engine

Hypersonic aircraft is the orientation of strategic development in the military and civil use in the future. There are three different types of propulsion system in hypersonic aircraft, such as rocket engine, ramjet engine and combination engine. The two different engines constitute the combination engine, usually taking rocket ramjet engine, solid rocket turbo ramjet engine and rocket turbo engine for example. Air turbo ramjet engine has some advantages of simple mechanism, strong thrust, high speed as well as low cost. This type of hypersonic aircraft has excellent performance of propulsion under different flight conditions. Focused on the part of the air turbo ramjet engine in this paper, the aerodynamic design of one-stage turbine is researched.In this article, the method and common process of the aerodynamic design of turbine is discussed firstly. Following with the transonic and supersonic flow model and governing equations established, the method of numerical solution in the flow field is introduced. The one dimensional aerothermodynamic computation in the average radius of the turbine following the meridional flow path is achieved, the results of which can determine size of meridional flow channel in the turbine, gas parameters in the space of two adjacent blades and velocity triangle. Based on the aerodynamic computation results as well as the parametric design method, the 2D profile of stator and rotor blades can be designed with the help of the commercial software and also Bezier curve is made use of to adjust the 2D blades profile. Then the trailing edge and centroid stack type along the radius direction will be used to construct the 3D stator and rotor blades separately. The designed geometric data of blades are put into the AutoCAD software to get the full-scale mock-up. The numerical analytical platform is established to simulate the internal flow field. The pressure distribution along profile, contour of Mach number, limit streamline and the distribution aerodynamic parameter along blade height at inlet and outlet in the S1 stream face of stator and rotor blades are analysed.