Abstract: The combustion section of the gas turbine is comprised of an engine casing receiving compressor discharge air and housing a plurality of combustion chamber assemblies having removable inner center liners. The combustion chamber assemblies are comprised of an outer liner having an end wall in which fuel injectors are mounted and the removable inner center liner extending within the outer liner from the end wall to define an annular combustion chamber space adjacent the end wall.

Abstract: Apparatus for diffusing the working medium gases which flow from the compression section of a gas turbine engine is disclosed. A controlled diffuser comprising an inner and an outer flow path shroud initially increases the static pressure and decreases the velocity of the medium gases flowing therebetween. The diffusion process is completed downstream of the flow path shrouds in a dump region of rapidly increasing flow area. The inner and outer shrouds of the controlled diffuser are concentrically supported at both the upstream and downstream ends. The inner and outer shrouds support the compressor exit vanes within the path of working medium gases flowing from the compressor and damp vane vibration during operation of the engine.