Turbine blade margin plate heat exchange boundary construction method

The invention provides a turbine blade margin plate heat exchange boundary construction method, and relates to the field of aero-engines. Comprising the following steps: S1, acquiring geometrical characteristic parameters of a single-blade margin plate surface, and constructing an outer ring side line and an inner ring side line; s2, obtaining a front edge endpoint coordinate and a rear edge endpoint coordinate of an inner ring side line, and dividing the inner ring side line into a blade basin curve and a blade back curve; obtaining the coordinates of a front edge line projection point and a rear edge line projection point through the projection of the front edge end point and the rear edge end point on the front edge line and the rear edge line; s3, physical parameters for constructing a single-blade marginal plate surface heat exchange boundary are obtained; s4, constructing a runner edge plate surface between two adjacent blades, and dividing the runner edge plate surface into orthogonal grids; s5, constr