Abstract: A segmented heat shield (36) is provided for an annular combustor bulkhead (20). The shield segments (38) define a backside cooling volume (44) which receives a flow of cooling air (66) for protecting the shield segment (38) from the high temperature combustion reaction (34). A region of extended heat transfer surface (68) on the shield backside (42) increases heat transfer effectiveness, while backside raised ridges (60, 62, 64) direct the cooling air (66) for achieving a more even distribution before being exhausted (50) adjacent the combustor liners (12, 14).

Abstract: A seal assembly secured to the downstream end of a gas turbine engine combustor liner forms a gas path seal at the upstream facing platforms of turbine inlet guide vanes and also cools the vane platforms. The seal assembly includes an annular coolant compartment which feeds cooling air to a plurality of circumferentially spaced apart, axially extending open-ended channels formed between a conical portion of the downstream-most combustor liner and an annular baffle member disposed on the non-gas path side of the conical liner. The seal assembly is supported and axially located on a cylindrical surface which permits locating the seal assembly such that the downstream end of the conical liner is closely spaced from the turbine inlet guide vane platforms to reduce leakage from the gas path.

Abstract: A burner construction in which staging of combustion is obtained by a primary pressure-atomizing nozzle having a low spray angle to maintain combustion within a central core of the combustor, and a secondary fuel aerating nozzle delivering fuel in a hollow cone configuration surrounding the primary fuel spray for combustion in an annulus between the central core and the wall of the combustor. Although most of the air for primary combustion is supplied with the fuel nozzle, additional air may be introduced at the upstream end of the combustor by high penetration jets that enter the central core and additional air for secondary combustion is introduced by one or more rows of holes in the combustor wall near the upstream end.