Additively manufactured liner on a turbofan or geared turbofan fan stage

A gas turbine engine with acoustic treatment proximate a fan stage comprising:

• a fan located within a fan duct;
• and
• an array of fan exit guide vanes supported within the fan duct downstream from the fan, the array of fan exit guide vanes spans across the fan duct attached to a radially inner surface of the fan duct and a radially outer surface of the fan duct;
• and
• the acoustic treatment disposed in at least one location along surfaces exposed to a fan discharge airflow proximate the array;
• wherein at least one acoustic zone formed downstream of the fan is configured for acoustic dampening features manufactured directly into a parent material along the surfaces;
• and wherein a location and a shape of the at least one acoustic zone is responsive to the design of the fan stage, acoustic and attachment structural requirements;
• wherein the acoustic treatment is proximate an intra-stage panel and targeted for tones;
• the acoustic treatment is proximate an aft inner panel and targeted for broadband noise;
• and wherein the acoustic treatment is proximate an outside diameter platform and an inside diameter platform and targeted for both tones and broadband noise.