The invention belongs to the technical field of aviation engine thermal barrier coatings and particularly relates to a preparation method for an IC10 alloy low-pressure-turbine guide vane thermal barrier coating. A matrix material is an IC10 directional solidified high temperature alloy, and the preparation process procedure comprises the steps of supplied part checking, preparing before spraying,spraying process parameter confirming, cleaning, protecting before grit blasting, grit blasting, protecting before spraying, a NiCrAlYSi metal bonding bottom layer supersonic spraying, a nano zirconium oxide coating atmospheric plasma spraying, clearing, final checking and respraying and repairing. According to the preparation method for the IC10 alloy low-pressure-turbine guide vane thermal barrier coating, the NiCrAlYSi metal bonding bottom layer supersonic spraying and the nano zirconium oxide coating atmospheric plasma spraying are adopted, so that the high temperature oxidation resistance and heat insulation capacities of the coating are improved, the preparation of low-pressure-turbine guide vane surface thermal barrier coating of an aviation engine of some type is realized, and bymeans of the preparation of coating, the service life of hot end components can be effectively prolonged.