should be further understood that the disclosed cooling flow paths are but an illustrated embodiment and should not be limited only thereto each wall 60 62 generally includes a respective support shell 68 70 that supports one or more respective liners 72 74 mounted to a hot side of the respective support shell 68 70 the liners 72 74 define a liner array that may be generally annular in shape each of the liners 72 74 may be generally rectilinear and manufactured of for example a nickel based super alloy or ceramic material the combustor 56 further includes a forward assembly 80 immediately downstream of the compressor section 24 to receive compressed airflow therefrom the forward assembly 80 generally includes an annular hood 82 a bulkhead subassembly 84 a multiple of fuel nozzles 86 one shown and a multiple of swirlers 90 one shown that defines a central opening 92 the annular hood 82 extends radially between and is secured to the forwardmost ends of the walls 60 62 the annular hood 82 includes a multiple of circumferentially distributed hood ports 94 that accommodate the respective fuel nozzle 86 and introduce air into the forward end of the chamber 66 the centerline of the fuel nozzle 86 is concurrent with the centerline f of the respective swirler 90 each fuel nozzle 86 may be secured to the diffuser case 64 to project through one of the hood ports 94 and through the central opening 92 within the respective swirler 90 each swirler 90 is circumferentially aligned with one of the hood ports 94 to project through the bulkhead subassembly 84 each bulkhead subassembly 84 includes a bulkhead support shell.