Exhaust mixer with offset lobes

摘要

An exhaust mixer (32) for a gas turbine engine where each outer lobe (44) has at the downstream end a circumferential offset in a direction corresponding to that of the swirl component of the flow entering the mixer (32). The mixer (32) has a crest line (45) having at least a downstream portion curved with respect with respect to a circumferential direction of the mixer (32) and/or a center line at the downstream end tilted with respect to a radial line extending to the tip of the outer lobe (44) to define the circumferential offset.