Abstract: The present invention relates to the field of metal additive manufacturing, and disclosed thereby is a method for printing a structure of a combustion chamber liner by using GRCop-84 spherical powder. The method mainly comprises the following steps: (1) establishing a model; (2) configuring printing parameters; (3) performing laser printing; (4) performing annealing treatment; and (5) performing surface sandblasting. The present invention uses GRCop-84 spherical powder as the material of a combustion chamber liner model, and said material has excellent electrical conductivity, thermal expansion, strength, creep resistance, ductility, fatigue and like properties, and the comprehensive performance thereof is excellent, which significantly improves the performance of a rocket engine. In the GRCop-84 spherical powder material of the present invention, Cr and Nb form a Cr2Nb phase, and the volume fraction of a second phase is about 14%, same being evenly distributed in a copper matrix.