Abstract: Floating panel heat shields 26 cover the walls of a combustor with a portion of the cooling air 32 passing upstream. The dome heat shield 36 has a lip 42 overlapping a portion of the wall hot shield 26. Dome 16 at location 44 deflects cooling flow 32 forcing it inwardly against lip 42 to improve cooling of lip 42.

Abstract: A combustor liner is supported from a surrounding diffuser case, and restricted from upstream movement by radial surfaces of complimentary radial lugs. A split seal ring seals against the downstream outside edge of the liner and the upstream facing surface of a downstream located blade platform. An outwardly extending flange cooperates with a waveform washer to bias the seat against the blade platform. The flange cooperates with the seal ring itself to restrict downstream movement of the liner.

Abstract: A refilmer for the combustion/dilution air hole of a floatwall panel of the combustor of a gas turbine engine carries a 180.degree. lip extending in, the hot gas stream of the combustor having a projection projecting in the combustion/dilution air hole to divert a portion of the air stream to form the film on the inner surface of the segmented panel. The refilmer is formed integrally with the segmented panel and carries a shoulder bearing against the inner surface of the shell defining a spacer. Forming the combustion/dilution air hole integrally with the segmented panel allows the air hole to be located in any efficacious location for effectuating optimum combustion.