Abstract: A fuel injector for a gas turbine engine includes a support member having a fuel discharge nozzle proximal an end thereof, a first tubular heat shield disposed about a length of the support member to form a thermal insulating space therebetween, and a second tubular heat shield disposed about the first heat shield to form an annular air flow passage between the first heat shield and the second heat shield. The second heat shield has one or more upstream inlet openings for entry of pressurized air for flow through the air flow passage to a downstream discharge opening disposed about the fuel discharge nozzle to permit fuel to be discharged therefrom to a combustor of the gas turbine engine while pressurized air is discharged from the discharge opening. The Mach number of the air flowing through the air flow passage is controlled by the spacing between the first and second heat shields to improve cooling of the heat shields, fuel atomization and combustor fuel/air mixing.