Importance

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Abstract

A combustor for a gas turbine engine includes a liner receiving a fuel and air mixing body. The mixing body communicates with a source of fuel, and has an inner chamber centered on a central axis. Fuel passages communicate with the source of fuel and deliver fuel into the inner chamber. The inner chamber extends between a bottom wall and an end face leading into a combustion chamber within the liner. Inner air swirler passages are formed in the mixing body at an axially intermediate location between the bottom wall and the end wall and deliver air into the inner chamber to mix with fuel from the fuel passages. Outer air passages in the mixing body in a portion which is radially outward of the chamber. The outer air passages have a component extending radially inwardly toward the central axis of the chamber.

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First Claim