Aircraft powerplant exhaust section with flow diverter

A powerplant for an aircraft, comprising:

• a core of a gas turbine engine including a core flowpath, a compressor section, a combustor section and a turbine section, the core flowpath extending longitudinally through the compressor section, the combustor section and the turbine section;
• and
• an exhaust section including an exhaust flowpath, a first diverter section, a second diverter section and a flow diverter;
• the exhaust flowpath fluidly coupled to and downstream of the core flowpath, the exhaust flowpath including a diffuser section, a first nozzle section and a second nozzle section, wherein a cross-sectional flow area of the diffuser section increases in size as the diffuser section extends longitudinally away from the core flowpath, a cross-sectional flow area of the first nozzle section decreases in size as the first nozzle section extends longitudinally towards a first nozzle outlet from the exhaust section, and a cross-sectional flow area of the second nozzle section decreases in size as the second nozzle section extends longitudinally towards a second nozzle outlet from the exhaust section;
• the flow diverter comprising a diverter panel configured to pivot about a pivot axis between a first position and a second position, the flow diverter configured to fluidly couple the diffuser section to the first nozzle section and fluidly decouple the diffuser section from the second nozzle section when the diverter panel is in the first position, and the flow diverter configured to fluidly couple the diffuser section to the second nozzle section and fluidly decouple the diffuser section from the first nozzle section when the diverter panel is in the second position;
• the first diverter section extending longitudinally through the flow diverter from the diffuser section to the first nozzle section when the diverter panel is in the first position, a cross-sectional flow area of the first diverter section increasing in size as the first diverter section extends longitudinally along a first side of the diverter panel towards the first nozzle section;
• and
• the second diverter section extending longitudinally through the flow diverter from the diffuser section to the second nozzle section when the diverter panel is in the second position, a cross-sectional flow area of the second diverter section continuously decreasing in size as the second diverter section extends longitudinally along a second side of the diverter panel to the second nozzle section.