A gas turbine engine turbine section has tie rod assemblies interconnecting an inner diameter structure and an outer casing. Each tie rod has: an inner diameter end; an outer diameter end; and an eyelet of an outer diameter spherical bearing formed at the outer diameter end. A first clevis carries a spherical ball of the bearing, a shank of said clevis extending to an outer diameter (OD) end. A tensioning bolt is mated to a threaded opening in said clevis OD end whereby tightening said bolt applies a tension to said rod. A radial span between a center of the outer diameter spherical bearing and an inner diameter surface of the outer casing is at least 50% greater than that between an outer diameter (OD) surface of the outer ring and the center.

A pod for a turbojet engine includes an outer cowl having a structure with at least one opening and a panel pivotably mounted about an axis between a closed position and an open position, and a system for actuating the panel designed to lock the panel in closed position and to move same between the closed position and the open position thereof. The actuation system includes a lateral connecting rod connected to the panel and to the structure, pivoting relative to the structure about a first pivoting axis and about a second pivoting axis, and a linear actuator attached to the lateral connecting rod. The actuator system is designed to move the lateral connecting rod during the extension of the actuator, and the lateral connecting rod exerts a force on the panel during the movement thereof, pivoting the panel about the axis thereof.

A gas turbine engine turbine section has tie rod assemblies interconnecting an inner diameter structure and an outer casing. Each tie rod has: an inner diameter end; an outer diameter end; and an eyelet of an outer diameter spherical bearing formed at the outer diameter end. A first clevis carries a spherical ball of the bearing, a shank of said clevis extending to an outer diameter (OD) end. A tensioning bolt is mated to a threaded opening in said clevis OD end whereby tightening said bolt applies a tension to said rod. A radial span between a center of the outer diameter spherical bearing and an inner diameter surface of the outer casing is at least 50% greater than that between an outer diameter (OD) surface of the outer ring and the center.

A thrust reverser for a gas turbine engine may comprise a frame, a first reverser door pivotally mounted to the frame at a first pivot point, a second reverser door pivotally mounted to the frame at a second pivot point, a first nacelle defining a first trailing edge of the gas turbine engine coupled between the frame and the first reverser door, and a second nacelle defining a second trailing edge of the gas turbine engine coupled between the frame and the second reverser door. The first nacelle and the second nacelle translate in an aft and radial outward direction relative to the gas turbine engine in response to the thrust reverser moving to a deployed position.

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 nacelle has a fixed cowl and a mobile cowl, which is movable along a translation path between closing and opening positions, a window delimited by the fixed cowl and the mobile cowl and open between an airflow and exterior of the nacelle, a reverser flap rotatably mounted to move between closed and open positions, and a drive mechanism configured to control passage of the reverser flap between the closed and open positions as the mobile cowl moves between the closed and open positions. From the closing/closed positions, the drive mechanism assures a translation of the mobile cowl and a rotation of the reverser flap toward their respective opening/open positions. From the open/opening positions, the drive mechanism assures a rotation of the reverser flap and a translation of the mobile cowl toward their respective closed/closing position. In some embodiments, the nacelle further includes an additional, or second, flap.

An assembly is provided for an aircraft propulsion system with an axial centerline. This assembly includes a nacelle structure and a thrust reverser system. The nacelle structure includes a fan cowl, where a forward cavity extends axially into the nacelle structure from an aft end of the fan cowl. The thrust reverser system includes a sleeve, a cascade structure, a blocker door and a linkage. The sleeve is configured to translate axially along the centerline and relative to the nacelle structure between a forward stowed position and an aft deployed position. The cascade structure, the blocker door and the linkage are at least partially within the forward cavity when the sleeve is in the forward stowed position. The cascade structure is fixedly attached to the sleeve. The linkage extends between and is pivotally attached to the cascade structure and the blocker door.

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 device for adjusting the pitch of at least one annular row of stator vanes for a turbine engine module. The device includes a first control ring mounted to rotate freely about an axis of the turbine engine. The device also includes connecting rods for connecting the first control ring to the vanes and a second control ring mounted to rotate freely about the axis. Each vane of the at least one row is simultaneously connected to the first and second control rings by a set of at least two connecting rods. The device is suitable for use as part of a module and is suitable for use in a turbine engine.

An oil tank mounting system for use on a structure of a turbine engine, includes three mounts with each mount configured to constrain the oil tank with a different number of degrees of freedom of movement. A first mount may have fix the oil tank in one degree of freedom, a second mount may fix the oil tank in two degrees of freedom, and a third mount may fix the oil tank in three degrees of freedom. This allows limited rotational and expansion movement while coupling the oil tank to the engine. The mount attachments may be embodied in rubber, with pins, or with spherical joints in a variety of configurations. Frangible pins may be used to absorb energy but still retain the oil tank in the event of a high energy event.