Patent ID: 8549859

Claim:
A combustion apparatus in a gas turbine engine comprising: a combustor shell for receiving compressed air; a first fuel injection system associated with said combustor shell for delivering fuel to a main combustion zone; a first fuel supply structure in fluid communication with a source of fuel for delivering fuel from the source of fuel to said first fuel injection system; a second fuel injection system associated with said combustor shell for delivering fuel to a location that is downstream from the main combustion zone; a second fuel supply structure in fluid communication with the source of fuel for delivering fuel from the source of fuel to said second fuel injection system, said second fuel supply structure comprising a fuel supply tube including a first section extending axially from a cover plate at a forward end of the combustion apparatus to a second section, said second section being downstream from said first section relative to the fuel flow and extending circumferentially from said first section; and a shield structure associated with at least a portion of said second section of said fuel supply tube to substantially shield said second section portion of said fuel supply tube from compressed air.