Design method for micro-rib double-wall guide vane of aero-engine turbine

The invention belongs to the technical field of aero-engine turbine micro-rib double-wall guide vane design, and relates to an aero-engine turbine micro-rib double-wall guide vane design method which comprises the following steps: analyzing the airflow flowing characteristics of cooling air in a guide vane; extracting a resistance element and a heat exchange element which are close to real flow; an air supply cavity, an impact hole, a laminate cavity, a micro rib and an air film hole in the guide vane are connected in series and fitted through a resistance element and a heat exchange element, and a one-dimensional flow heat exchange calculation network is obtained; based on a one-dimensional flow heat exchange calculation network, considering the on-way temperature rise of the cooling gas, performing internal flow heat exchange calculation to obtain the cooling gas consumption and heat exchange parameters of the guide vane, and adjusting the structural parameters of the guide vane to enable the cooling gas co