Abstract: A fuel nozzle assembly 32 for a gas turbine engine 10 is disclosed. Various construction details relating to a heat shield 92 are developed. In one embodiment, the heat shield is attached to only a radial surface 96 on the assembly and is free to grow axially from the radial surface of attachment.
Abstract: A stator assembly 16 for a gas turbine is disclosed. Various construction details which increase the effectiveness of the use of cooling fluid are developed enabling the use of stator vanes which do not have blockable holes for cooling air. In one embodiment, a segmented seal ring extends circumferentially between an array of coolable stator vanes 34 and a casing 22 to block the vane cooling air from convectively transfering heat to the casing.