A combustor for a turbine engine, comprising: a first liner; a second liner forming a combustion chamber with the first liner, the combustion chamber configured to receive an air-fuel mixture for combustion therein, the first liner being a first double wall liner comprising a first wall forming a portion of the combustion chamber and a second wall extending around at least a portion of the first wall to form a liner cavity with the first wall, the first wall defining a first wall orifice and the second wall defining a second wall orifice, the first wall having a first side facing the combustion chamber and a second side facing the liner cavity; and an insert mounted on the second wall within the second wall orifice and extending through the first wall orifice, the insert configured to direct a first air jet through the second wall, through the first wall, and into the combustion chamber, the insert is formed by a tubular body portion that extends through the first wall orifice and the second wall orifice, the insert includes a shoulder extending around the body portion that abuts a first side of the second wall, the body portion is spaced apart from the first wall within the first wall orifice in a radial dimension to form an axial passage between the body portion and the first wall, characterized in that the insert further includes a flange circumscribing the body portion within the combustion chamber, wherein the flange is spaced apart from the first side of the first wall in an axial dimension to form a radial passage between the flange and the first wall, and wherein the insert is configured such that cooling air within the liner cavity flows through the axial passage and through the radial passage to provide a radiating flow of the cooling air around a circumference of the insert within the combustion chamber. a first liner; a second liner forming a combustion chamber with the first liner, the combustion chamber configured to receive an air-fuel mixture for combustion therein, the first liner being a first double wall liner comprising a first wall forming a portion of the combustion chamber and a second wall extending around at least a portion of the first wall to form a liner cavity with the first wall, the first wall defining a first wall orifice and the second wall defining a second wall orifice, the first wall having a first side facing the combustion chamber and a second side facing the liner cavity; and an insert mounted on the second wall within the second wall orifice and extending through the first wall orifice, the insert configured to direct a first air jet through the second wall, through the first wall, and into the combustion chamber, the insert is formed by a tubular body portion that extends through the first wall orifice and the second wall orifice, the insert includes a shoulder extending around the body portion that abuts a first side of the second wall, the body portion is spaced apart from the first wall within the first wall orifice in a radial dimension to form an axial passage between the body portion and the first wall, characterized in that the insert further includes a flange circumscribing the body portion within the combustion chamber, wherein the flange is spaced apart from the first side of the first wall in an axial dimension to form a radial passage between the flange and the first wall, and wherein the insert is configured such that cooling air within the liner cavity flows through the axial passage and through the radial passage to provide a radiating flow of the cooling air around a circumference of the insert within the combustion chamber.