초록 ▼

A fuel injection assembly for a gas turbine engine combustor, including at least one fuel stem, a plurality of concentrically disposed tubes positioned within each fuel stem, wherein a cooling supply flow passage, a cooling return flow passage, and a tip fuel flow passage are defined thereby, and at

A fuel injection assembly for a gas turbine engine combustor, including at least one fuel stem, a plurality of concentrically disposed tubes positioned within each fuel stem, wherein a cooling supply flow passage, a cooling return flow passage, and a tip fuel flow passage are defined thereby, and at least one fuel tip assembly connected to each fuel stem so as to be in flow communication with the flow passages, wherein an active cooling circuit for each fuel stem and fuel tip assembly is maintained by providing all active fuel through the cooling supply flow passage and the cooling return flow passage during each stage of combustor operation. The fuel flowing through the active cooling circuit is then collected so that a predetermined portion thereof is provided to the tip fuel flow passage for injection by the fuel tip assembly.

대표청구항 ▼

1. A fuel injection assembly for a gas turbine engine combustor, comprising:(a) a pair of fuel stems positioned in spaced adjacent manner; (b) a plurality of fuel tip assemblies connected to each said fuel stem; (c) a bundle of concentrically disposed tubes positioned in each said fuel stem to defin

1. A fuel injection assembly for a gas turbine engine combustor, comprising:(a) a pair of fuel stems positioned in spaced adjacent manner; (b) a plurality of fuel tip assemblies connected to each said fuel stem; (c) a bundle of concentrically disposed tubes positioned in each said fuel stem to define an independent cooling supply flow passage, cooling return flow passage, and tip fuel flow passage in flow communication with each said fuel tip assembly; and (d) at least one cross brace member coupling said fuel stems.