A passive transpirational flow acoustic liner assembly (61; 161) for a gas turbine engine, the assembly comprising: a guide vane (64; 164) assembly comprising: an airfoil having a suction side and a pressure side; and a transpirational flow acoustic liner (100; 200) disposed in the airfoil, the liner (100; 200) comprising: a face sheet defining a portion of an outer surface of the airfoil and having a plurality of first apertures; a segmented member coupled to the face sheet, the segmented member comprising a plurality of chambers in fluid communication with the outer surface via the plurality of first apertures; a backing sheet coupled to the segmented member such that the segmented member is positioned between the face sheet and the backing sheet, the backing sheet having a plurality of second apertures; and a plenum coupled to the backing sheet opposite the segmented member; and a conduit (80; 180) fluidly connected to the plenum and configured to deliver airflow received from the plenum to one of: a plurality of exhaust outlets on an outer surface of a nacelle, the plurality of exhaust outlets disposed about a circumference of the nacelle on a top side of the nacelle; or a plurality of exhaust passages located to deliver airflow to components disposed in a cavity of the core housing and to an active clearance control system in a turbine section (28, 46, 54) of the gas turbine engine, the conduit connected to the active clearance control system, wherein the active clearance control system comprises a valve located in a fluid position aft of the plurality of exhaust passages and configured to regulate the airflow to the turbine section (28, 46, 54). an airfoil having a suction side and a pressure side; and a transpirational flow acoustic liner (100; 200) disposed in the airfoil, the liner (100; 200) comprising: a face sheet defining a portion of an outer surface of the airfoil and having a plurality of first apertures; a segmented member coupled to the face sheet, the segmented member comprising a plurality of chambers in fluid communication with the outer surface via the plurality of first apertures; a backing sheet coupled to the segmented member such that the segmented member is positioned between the face sheet and the backing sheet, the backing sheet having a plurality of second apertures; and a plenum coupled to the backing sheet opposite the segmented member; and a conduit (80; 180) fluidly connected to the plenum and configured to deliver airflow received from the plenum to one of: a plurality of exhaust outlets on an outer surface of a nacelle, the plurality of exhaust outlets disposed about a circumference of the nacelle on a top side of the nacelle; or a plurality of exhaust passages located to deliver airflow to components disposed in a cavity of the core housing and to an active clearance control system in a turbine section (28, 46, 54) of the gas turbine engine, the conduit connected to the active clearance control system, wherein the active clearance control system comprises a valve located in a fluid position aft of the plurality of exhaust passages and configured to regulate the airflow to the turbine section (28, 46, 54). a face sheet defining a portion of an outer surface of the airfoil and having a plurality of first apertures; a segmented member coupled to the face sheet, the segmented member comprising a plurality of chambers in fluid communication with the outer surface via the plurality of first apertures; a backing sheet coupled to the segmented member such that the segmented member is positioned between the face sheet and the backing sheet, the backing sheet having a plurality of second apertures; and a plenum coupled to the backing sheet opposite the segmented member; and a conduit (80; 180) fluidly connected to the plenum and configured to deliver airflow received from the plenum to one of: a plurality of exhaust outlets on an outer surface of a nacelle, the plurality of exhaust outlets disposed about a circumference of the nacelle on a top side of the nacelle; or a plurality of exhaust passages located to deliver airflow to components disposed in a cavity of the core housing and to an active clearance control system in a turbine section (28, 46, 54) of the gas turbine engine, the conduit connected to the active clearance control system, wherein the active clearance control system comprises a valve located in a fluid position aft of the plurality of exhaust passages and configured to regulate the airflow to the turbine section (28, 46, 54). a plurality of exhaust outlets on an outer surface of a nacelle, the plurality of exhaust outlets disposed about a circumference of the nacelle on a top side of the nacelle; or a plurality of exhaust passages located to deliver airflow to components disposed in a cavity of the core housing and to an active clearance control system in a turbine section (28, 46, 54) of the gas turbine engine, the conduit connected to the active clearance control system, wherein the active clearance control system comprises a valve located in a fluid position aft of the plurality of exhaust passages and configured to regulate the airflow to the turbine section (28, 46, 54).