The invention belongs to the field of aero-engine blades, and particularly relates to a cooling structure design method for a high-pressure
turbine guide cooling blade margin plate. The cooling structure design method for the high-pressure
turbine guide cooling blade margin plate comprises the steps that firstly, the margin plate is partitioned into a
cold air introduction area and a non-
cold air introduction area according to the air introduction position of the margin plate and the position of a vertical plate; secondly, an
impact and air film combined cooling structure is designed in the
cold air introduction area of the margin plate; thirdly, a turbulent flow column and air film combined cooling structure is designed in the non-cold air introduction area of the margin plate; fourthly, gas film cooling structures are designed on the
fuel gas side surface of the margin plate and a blade body close to the margin plate; and fifthly, variable-
radius fillets are arranged on the connecting sections of the margin plate and the blade body along a blade profile. According to the cooling structure design method for the high-pressure
turbine guide cooling blade margin plate, a combined cooling mode is adopted for cooling the wall face of the high-pressure turbine guide blade margin plate, the hot-spot temperature of the margin plate can be reduced, the
cooling effect of the blade margin plate can be improved, and the service life of blades can be prolonged.