Abstract: A support structure for a low NO.sub.x industrial gas turbine engine fuel nozzle includes a pressure vessel which forms an interior cavity such that the exterior of the pressure vessel is exposed to the high pressure and temperature of the compressor outlet while the interior cavity of the pressure vessel is exposed to ambient conditions. The fuel lines to the nozzle run through the interior cavity of the pressure vessel, isolated from the high temperatures and pressures at the compressor outlet. The pressure vessel housing and the ambient air within the housing act as natural insulators which prevent the fuel lines from becoming too hot and coking. The support structure also facilitates maintenance of the combustor section of the engine since the low NO.sub.x fuel nozzle and the annular combustor assembly of the engine are easily accessible for maintenance.

Abstract: Truncated pie shaped bulkhead liner sections 60 are 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.