Gas turbine combustion system cooling arrangement

Cooling is provided for a gas turbine combustion system (10) that includes a first member (13), such as a liner, having exterior (26) and interior (28) surfaces that define a wall (30) therebetween and a central area. A second member (40), such as a cap, is located adjacent that interior surface (28). A source of cooling gas is in fluid communication with the exterior surface (26) of the first member (13). An open space (60), in which is located a hula seal (50), is located between the interior surface (20) of the first member (13) and the second member (40). At least one opening (70) in the wall of the first member (13) provides a passageway (71) for the cooling gas from the exterior surface (26) of the first member (13) to the open space (60). The passageway (71) has a directional axis (82) along which the cooling gas flows and is discharged into the open space. The directional axis (82) is substantially oriented in a direction other than a direction towards the central area of the first member (13).