Gas turbine stationary blade insert installation method and application

The invention relates to the technical field of gas turbine hollow blade cooling, and particularly discloses a gas turbine stationary blade insert installation method which is applied to installationof heavy-duty gas turbine hollow blade inserts or aviation turbine engine hollow blade inserts. The method specifically comprises the following steps of calculating a relation between the insert assembling clearance and cooling gas leakage to obtain the insert assembling clearance, wherein the insert assembling clearance is 0-1.0 mm; reserving inner cavity grooves in inner cavities of stationary blades; correcting the shape of inserts; performing repairing and polishing; performing assembling; and completing assembling. According to the method, the leakage of cooling gas is effectively controlled within a reasonable range, and the service life of the blades is prolonged. 本发明涉及燃气轮机空心叶片冷却技术领域，具体公开了一种燃机透平静叶插件安装方法，应用于重型燃气轮机空心叶片插件或航空涡轮发动机空心叶片插件的安装，具体包括以下步骤:计算插件装配间隙与冷却气体泄漏关系，获得插件装配间隙；所述插件装配间隙为0-1.0mm；在静叶内腔中预留内腔凹槽；插件矫形；修