each divided into two liner segments 62 the division occurs adjacent fuel nozzle opening 20 upstream extending lips 71 75 and 77 abut the bulkhead 14 cooling air passes through cooling flow openings in the bulkhead with all the flow continuing toward the shell 38 40 edges of the liner segments application_number US 35659994 A description fig1 shows an annular gas turbine combustor 10 and the centerline 12 of the gas turbine engine the conical bulkhead 14 is supported from support structures 16 and 18 sixteen gas turbine nozzle openings 20 are located around the circumference of the bulkhead a plurality of fuel nozzles 22 are locatable within these openings these nozzles are preferably of the low no x type with premixing of fuel and air for low temperature combustion at each opening there is a fuel nozzle guide 24 which is axially restrained with fuel nozzle guide retainer 26 the key washer 28 prevents rotation of the fuel nozzle guide retainer 26 after installation the fuel nozzle guide 24 and the retainer 26 are secured to contain between them the key washer 28 the bulkhead 14 and the bulkhead liner 30 good contact 32 is maintained between the guide and the liner segments to avoid any significant amount of air passing.