An assembly is provided for a turbofan engine. This turbofan engine assembly includes a cowling, a door and an actuation mechanism configured to actuate movement of the door in response to receiving a control signal. The cowling is configured to form a compartment at least partially around a case of the turbofan engine. The cowling includes an exhaust port that is fluidly coupled with the compartment. The door is configured to at least partially open and close the exhaust port. This variable exhaust port may be opened in case increased airflow is needed through the compartment, such as when increased cooling airflow is needed through an environmental air precooler that cools compressed air for the aircraft cabin and the precooler exhausts its cooling air into the compartment.

In various embodiments, a cowl actuation system may comprise a cowl, an actuator, a bell crank, and a guide arm. The cowl may be configured to modulate at least a portion of the exhaust flow of a gas turbine engine. The bell crank may have a first end and a second end. The first end may be operatively coupled to the actuator. The second end may be operatively coupled to the cowl. The bell crank may be configured to pivot about a first point located between the first end and the second end. The first point may also be located along a diameter. The guide arm may have a third end and a fourth end. The third end may be mounted to a second point. The fourth end may be operatively coupled to the cowl. The second point may be located along the diameter.

A shape memory alloy (SMA) actuated aerostructure operable to dynamically change shape according to flight conditions is disclosed. Deformable structures are actuated by SMA actuators that are coupled to face sheets of the deformable structures. Actuating the SMA actuators produces complex shape changes of the deformable structures by activating shape changes of the SMA actuators. The SMA actuators are actuated via an active or passive temperature change based on operating conditions. The SMA actuated aerostructure can be used for morphable nozzles such as a variable area fan nozzle and/or a variable geometry chevron of a jet engine to reduce engine noise during takeoff without degrading fuel burn during cruise.

A shape memory alloy (SMA) actuated aerostructure operable to dynamically change shape according to flight conditions is disclosed. Deformable structures are actuated by SMA actuators that are coupled to face sheets of the deformable structures. Actuating the SMA actuators produces complex shape changes of the deformable structures by activating shape changes of the SMA actuators. The SMA actuators are actuated via an active or passive temperature change based on operating conditions. The SMA actuated aerostructure can be used for morphable nozzles such as a variable area fan nozzle and/or a variable geometry chevron of a jet engine to reduce engine noise during takeoff without degrading fuel burn during cruise.

In one or more aspects of the present disclosure, an aerospace vehicle includes a frame, an actuable multifunctional cellular structure connected to the frame, the actuable multifunctional cellular structure including a first face member and a second face member, and a shape memory alloy core coupled to the first face member and the second face member, and wherein, at least one of the first face member and the second face member is a graded thermal structure configured so that heat transferred through the graded thermal structure in a predetermined thermal pattern to the shape memory alloy core effects a predetermined change in a shape of the shape memory alloy core and effects a change in shape of the actuable multifunctional cellular structure.

In one or more aspects of the present disclosure, an aerospace vehicle includes a frame, an actuable multifunctional cellular structure connected to the frame, the actuable multifunctional cellular structure including a first face member and a second face member, and a shape memory alloy core coupled to the first face member and the second face member, and wherein, at least one of the first face member and the second face member is a graded thermal structure configured so that heat transferred through the graded thermal structure in a predetermined thermal pattern to the shape memory alloy core effects a predetermined change in a shape of the shape memory alloy core and effects a change in shape of the actuable multifunctional cellular structure.

A flow control panel in an aircraft engine two-dimensional, convergent/divergent nozzle adjusts a throat area of the nozzle and is configured to be self-sealing, thereby requiring fewer parts and providing a more simplified construction of the throat area of the nozzle.

A flow control panel in an aircraft engine two-dimensional, convergent/divergent nozzle adjusts a throat area of the nozzle and is configured to be self-sealing, thereby requiring fewer parts and providing a more simplified construction of the throat area of the nozzle.

A nozzle including a frame having a plurality of deflecting elements arranged in an array, the array extending about a longitudinal axis, and a skin positioned over the frame.

A nozzle including a frame having a plurality of deflecting elements arranged in an array, the array extending about a longitudinal axis, and a skin positioned over the frame.