The invention relates to a split face laser seal coating process in a gas turbine cylinder. The process is characterized in that detection and preparation are carried out before laser cladding of a gas turbine cylinder body; laser cladding is carried out, wherein a all-solid-state 1KW laser is employed during laser cladding, laser cladding is carried out on split face in the gas turbine cylinder, three mutually-parallel seal lines are co-cladded, width of each seal line is 2+/-0.2 mm, and the height is 1+/-0.2 mm, multistage parallel soft metal sealing strips are formed, an air bag-type sealing chamber is formed after a laser cladding layer is subjected to compressional deformation after installation, gradual sealing effect is realized; the sealing strip is sealed after laser cladding and detected and recorded; the sealing strip is treated through pliers, height size and contact area of each point of each strip are ensured; flaw detection is carried out, dye penetrant inspection detection is carried out, no defect is generated on surface and inner part. The process employs laser sealing, and split leakage problem in the cylinder can be effectively solved under matrix performance is not damaged.