Variable area nozzle exhaust system with integrated thrust reverser

An exhaust system for use with a gas turbine engine, the exhaust system comprising

• a static exhaust system structure that defines a primary exhaust system flow path of the exhaust system, the static exhaust system structure including a jet pipe arranged around an axis to provide an outer boundary surface of the primary exhaust system flow path and an inner plug that defines an inner boundary surface of the primary exhaust system flow path,
• a noise management structure including a moveable exhaust outlet that is mounted for movement along the axis and provides a portion of the outer boundary surface of the primary exhaust system flow path, wherein the noise management structure is configured to axially translate relative to the static exhaust system structure between a slid-aft take-off position, a slid-aft thrust-reverse position, and a slid-forward cruise position to provide a reconfigurable exhaust nozzle that adjusts a variable nozzle throat area of the exhaust system to vary noise produced by the gas turbine engine during operation of the gas turbine engine, and
• a thrust reverser unit including a plurality of blocker doors configured to pivot relative to the jet pipe about a pivot axis between a closed position in which the plurality of blocker doors are located within an aperture formed in the moveable exhaust outlet to close the aperture formed in the moveable exhaust outlet and an open position in which each blocker door extends into the primary exhaust system flow path and blocks at least some flow along the primary exhaust system flow path so as to direct at least some flow out of the primary exhaust system flow path through the aperture formed in the moveable exhaust outlet and create reverse thrust,
• wherein the slid-aft take-off position of the moveable exhaust outlet provides a convergent nozzle shape between the outer boundary surface of the jet pipe and the inner boundary surface of the inner plug to reduce noise produced by the gas turbine engine during operation of the gas turbine engine at one of take-off or landing,
• wherein the slid-forward cruise position of the moveable exhaust outlet provides a convergent-divergent nozzle shape between the outer boundary surface of the jet pipe and the inner boundary surface of the inner plug to increase acceleration of the flow, and
• wherein the slid-forward cruise position is axially forward of the slid-aft take-off position.

A method comprising:

• providing an exhaust system for use with a gas turbine engine, the exhaust system comprising a static exhaust system structure that defines a primary exhaust system flow path of the exhaust system, the static exhaust system structure including a jet pipe arranged around an axis to provide an outer boundary surface of the primary exhaust system flow path and an inner plug that defines an inner boundary surface of the primary exhaust system flow path, a noise management structure including a moveable exhaust outlet that is mounted for movement along the axis and provides a portion of the outer boundary surface of the primary exhaust system flow path, wherein the noise management structure is configured to axially translate relative to the static exhaust system structure between a slid-aft take-off position, a slid-aft thrust-reverse position, and a slid-forward cruise position to provide a reconfigurable exhaust nozzle that adjusts a variable nozzle throat area of the exhaust system to vary noise produced by the gas turbine engine during operation of the gas turbine engine, and a thrust reverser unit including a plurality of blocker doors configured to pivot relative to the jet pipe about a pivot axis between a closed position in which the plurality of blocker doors are located within an aperture formed in the moveable exhaust outlet to close the aperture formed in the moveable exhaust outlet and an open position in which each blocker door extends into the primary exhaust system flow path and blocks at least some flow along the primary exhaust system flow path so as to direct at least some flow out of the primary exhaust system flow path through the aperture formed in the moveable exhaust outlet and create reverser thrust, wherein the slid-aft take-off position of the moveable exhaust outlet provides a convergent nozzle shape between the outer boundary surface of the jet pipe and the inner boundary surface of the inner plug to reduce noise produced by the gas turbine engine during operation of the gas turbine engine at one of take-off or landing, wherein the slid-forward cruise position of the moveable exhaust outlet provides a convergent-divergent nozzle shape between the outer boundary surface of the jet pipe and the inner boundary surface of the inner plug to increase acceleration of the flow, and wherein the slid-forward cruise position is axially forward of the slid-aft take-off position, directing the moveable exhaust outlet to translate axially along the axis relative to the static exhaust system structure to the slid-aft take-off position to provide the convergent nozzle shape with a maximum nozzle throat area of the reconfigurable exhaust nozzle, directing the moveable exhaust outlet to translate axially along the axis relative to the static exhaust system structure to the slid-forward cruise position to provide a convergent-divergent nozzle shape with a minimum nozzle throat area of the reconfigurable exhaust nozzle, directing the moveable exhaust outlet to translate axially along the axis relative to the static exhaust system structure to the slid-aft thrust-reverse position, and directing the plurality of blocker doors of the thrust reverser unit to move from a stored arrangement in which the plurality of blocker doors are located within the aperture and a thrust-reversing arrangement in which each blocker door blocks the at least some flow along the primary exhaust system flow path and creates reverse thrust.