The liner of a combustor (100) for a gas turbine engine is provided with a projection region (111) provided with a plurality of projections (110) each projecting toward the compressed air chamber (56) from the liner outer surface and having a vertical wall portion (114) extending substantially orthogonally to a flow direction of compressed air flowing in the compressed air chamber, and a plurality of cooling holes (118) passed through the liner from the liner outer surface to the liner inner surface such that an end of each cooling hole on a side of the compressed air chamber is more downstream than an end of the cooling hole on a side of the combustion chamber (52) with respect to the flow direction of the compressed air in the compressed air chamber, at least a part of the cooling holes being formed in the projection region.