Disclosed is a linkage assembly for a gas turbine engine having a link having a first end, a second end, and a rod extending therebetween, the first end having a first sliding bearing disposed within a first sliding bearing housing, a fastener comprising a first flange and a second flange, a pin extending between the first flange and the second flange, wherein the first sliding bearing is pivotally connected to the pin; and a biasing member secured between the first flange and the sliding bearing housing, the biasing member contacting the sliding bearing housing and biasing the link against rotation about a center axis for the rod of the link.

A turbofan engine that includes a first flowpath, a second flowpath, a third flowpath, and a third flowpath exhaust nozzle is provided. The first flowpath is radially inboard of the second flowpath at a location upstream of a core section of the turbofan engine. The third flowpath is radially outboard of the second flowpath at the location upstream of the core section. The third flowpath exhaust nozzle defines a plurality of third flowpath exhaust exit ports through which gas traveling along the third flowpath may be discharged. An area or a geometry of each of the plurality of third flowpath exhaust exit ports is independently and selectively adjustable. A method for operating the turbofan engine includes independently and selectively adjusting an area or a geometry of at least one of the plurality of third flowpath exhaust exit ports to achieve a desired engine operation.

The present disclosure provides a turbojet engine nacelle having a downstream section including a cowl which is ended with a hinged flap constituting a nozzle. In particular, the hinged flap is hingedly and translatably hinged to the cowl.

A gas turbine engine includes a core engine defined about an axis, a gear system driven by the core engine, and a pylon variable area flow system. A fan is driven by the gear system. The variable area flow system operates to effect the bypass flow.

A propulsor system comprising a propulsor and an exhaust area control mechanism are described. The exhaust area control mechanism is connected to an outlet of the propulsor and is configured to vary the area through which air exits the propulsor system.

Methods and apparatus for sealing variable area fan nozzles of jet engines are disclosed. An apparatus in accordance with the teachings of this disclosure includes a frame and a seal to be coupled to the frame. The seal to enclose petals of a variable area fan nozzle to substantially prevent airflow between the petals.

A thrust reverse variable area nozzle system for a nacelle of an aircraft engine system may include a reverse thrust opening disposed in the nacelle, and a thrust reverser door pivotally movable relative to the nacelle for selectively covering the reverse thrust opening, wherein the thrust reverser door is pivotally movable between a first position for completely covering the reverse thrust opening, a second position for partially uncovering a forward portion of the reverse thrust opening and discharging a bypass airflow through the forward portion of the reverse thrust opening in a forward direction, and a third position for partially uncovering an aft portion of the reverse thrust opening and discharging the bypass airflow through the aft portion of the reverse thrust opening in an aft direction.

Methods and apparatus for sealing variable area fan nozzles of jet engines are disclosed. An apparatus in accordance with the teachings of this disclosure includes a frame and a seal to be coupled to the frame. The seal to enclose petals of a variable area fan nozzle to substantially prevent airflow between the petals.

A variable geometry exhaust nozzle arrangement includes a plurality of hingable exhaust petals defining a perimeter of an exhaust duct and an annular ring slidably engagable against a radially outer surface of each petal. The annular ring is coupled to a plurality of circumferentially spaced actuator arrangements, each including first and second circumferentially spaced parallel actuator arms pivotably coupled to the annular ring at a first end and to a slide arrangement at a second end. Each slide arrangement is mounted for linear sliding movement relative to the annular ring, such that sliding movement of each slide arrangement causes pivoting of the first and second actuator arms to thereby translate the annular ring in one or both of a longitudinal direction and a lateral direction.

Provided are methods and systems for measuring and controlling nozzle areas of variable area fan nozzles. A control system attached to a nozzle may include a cable having one end connected to a linear displacement measuring device, such as a string potentiometer. The other end of the cable may be connected to a petal. A reference portion of the cable extends across multiple petals of the nozzle and, in some embodiments, substantially parallel to the nozzle circumference. The linear displacement measuring device measures any changes in the length of this reference portion as the petals actuate outwardly or inwardly during operation of the nozzle. The output of the linear displacement measuring device may be used to control actuators that move the petals. In some embodiments, potentiometer's output may be combined with one or more outputs from other sensors, such as a linear variable differential transducer and/or thermocouple.