A gas turbine engine including an exhaust diffuser, the exhaust diffuser comprising: an inner boundary and an outer boundary forming an annular gas path; a plurality of strut structures extending radially between the inner boundary and the outer boundary and located within the gas path downstream of a last row of rotating blades; each of the strut structures including pressure and suction side walls (78a, 78b) extending in a downstream axial direction from a leading edge toward a downstream trailing edge of the strut structure; a plurality of radially spaced flow injectors (80a, 80b, 80c) formed in at least one of the pressure and suction side walls (78a, 78b), the flow injectors (80a, 80b, 80c) injecting a fluid flow (F c) into the gas path adjacent to the strut structure; and at least two fluid supply conduits (84a, 84b, 84c) connected to provide a fluid flow to respective radially spaced flow injectors (80a, 80b, 80c), and a flow control device associated with each of the conduits (84a, 84b, 84c) to independently control a fluid flow from a fluid source to each of the radially spaced flow injectors (80a, 80b, 80c), characterized in that each of the flow injectors (80a, 80b, 80c) discharge a flow of gas (F c) downstream substantially parallel to an outer surface of the at least one of the pressure and suction side walls (78a, 78b) to direct a portion (F A) of an exhaust flow passing over the strut structure toward a radial section of the strut structure associated with each of the flow injectors (80a, 80b, 80c), the flow of gas (F C) from the flow injectors (80a, 80b, 80c) each producing a Coanda effect to entrain and accelerate a portion (F A) of the exhaust flow to result in substantially attached flow (F A) along the at least one of the pressure and suction side walls (78a, 78b), each of the at least two fluid supply conduits (84a, 84b, 84c) including a plenum (90a, 90b, 90c), wherein the plenums (90a, 90b, 90c) are separated from each other to define individually controlled pressurized fluid sources at the radial location of each of their respective flow injectors (80a, 80b, 80c). an inner boundary and an outer boundary forming an annular gas path; a plurality of strut structures extending radially between the inner boundary and the outer boundary and located within the gas path downstream of a last row of rotating blades; each of the strut structures including pressure and suction side walls (78a, 78b) extending in a downstream axial direction from a leading edge toward a downstream trailing edge of the strut structure; a plurality of radially spaced flow injectors (80a, 80b, 80c) formed in at least one of the pressure and suction side walls (78a, 78b), the flow injectors (80a, 80b, 80c) injecting a fluid flow (F c) into the gas path adjacent to the strut structure; and at least two fluid supply conduits (84a, 84b, 84c) connected to provide a fluid flow to respective radially spaced flow injectors (80a, 80b, 80c), and a flow control device associated with each of the conduits (84a, 84b, 84c) to independently control a fluid flow from a fluid source to each of the radially spaced flow injectors (80a, 80b, 80c), characterized in that each of the flow injectors (80a, 80b, 80c) discharge a flow of gas (F c) downstream substantially parallel to an outer surface of the at least one of the pressure and suction side walls (78a, 78b) to direct a portion (F A) of an exhaust flow passing over the strut structure toward a radial section of the strut structure associated with each of the flow injectors (80a, 80b, 80c), the flow of gas (F C) from the flow injectors (80a, 80b, 80c) each producing a Coanda effect to entrain and accelerate a portion (F A) of the exhaust flow to result in substantially attached flow (F A) along the at least one of the pressure and suction side walls (78a, 78b), each of the at least two fluid supply conduits (84a, 84b, 84c) including a plenum (90a, 90b, 90c), wherein the plenums (90a, 90b, 90c) are separated from each other to define individually controlled pressurized fluid sources at the radial location of each of their respective flow injectors (80a, 80b, 80c).