A deployment mechanism for inflatable surface-increasing features a gas turbine exhaust case comprising a plurality of inflatable surface-increasing features adapted to be circumferentially distributed within the gas turbine exhaust case at a trailing edge thereof. The inflatable surface-increasing features are inflatable from a stowed configuration in which the inflatable surface-increasing features are substantially concealed fore of the trailing edge, to a deployed configuration in which the inflatable surface-increasing features extend beyond the trailing edge. A pressurizing system in fluid communication with the plurality of chevrons inflates and deflates the inflatable surface-increasing features.

A thrust reverser for an aircraft propulsion unit, including a fixed structure equipped with a wall for radially internally delimiting a secondary flow duct, and a mobile structure including at least one reverser mobile cowl equipped with a reverser-cowl radially internal wall, the mobile structure being movable between a forward direct-thrust position and a retreated reverse-thrust position, the thrust reverser also including at least one obturator membrane designed to deflect at least some of the secondary flow towards the cascade vanes when the mobile structure is in the retreated reverse-thrust position. The reverser can include a mobile frame for deploying the obturator membrane, this frame being mounted with the ability to pivot on the mobile structure of the reverser between a retracted position and a position in which it is deployed in the secondary flow duct.

An aircraft gas turbine engine includes a fan that in operation moves air through both a core airflow path and a bypass airflow path of the gas turbine engine. The core airflow path and the bypass airflow path converge at a jet nozzle of the gas turbine engine. A method of controlling the gas turbine engine includes detecting, at a controller of the gas turbine engine, a cruise operating condition of the gas turbine engine, and in response to detecting the cruise operating condition, operating a mechanism of the gas turbine engine to decrease an effective area of the jet nozzle.

A gas turbine engine for an aircraft includes an outer bypass section wall, and a jet nozzle including at least one inflatable diaphragm. The at least one inflatable diaphragm is disposed along the outer bypass section wall. The gas turbine engine also includes a fluid pressure sensor configured to measure a fluid pressure within the at least one inflatable diaphragm, an inlet valve configured to control a pressurized flow of a fluid into the at least one inflatable diaphragm in response to a command from a controller, and a release valve configured to control a release of the fluid from within the at least one inflatable diaphragm in response to a command from the controller.