▎ 摘　　要

NOVELTY - The method involves calculating a temperature field of a blade without heat radiation protection measures. An initial blade temperature field is obtained as a contrast basis. A protection position is determined. A gas film hole is optimized. An air film covering effect is evaluated. A thermal barrier coating is designed. A graphene coating layer is designed. The blade temperature fields are calculated after adopting protective measures. USE - Method for designing high temperature heat radiation protection of high pressure turbine guide vane of gas turbine used in civil power generation, natural gas pipeline pressurizing, ship and offshore platform field. ADVANTAGE - The method reduces the temperature difference of the high and low temperature area, so as to reduce the blade temperature gradient, reduce the heat stress of the blade, which is good for improving the service life of blade and structure reliability. DESCRIPTION OF DRAWING(S) - The drawing shows a flow chart of a high temperature heat radiation protection design method of high pressure turbine guide vane of gas turbine. (Drawing includes non-English language text).