A variable vane assembly includes a variable vane; a trunnion arranged on one end of the variable vane; a bushing mated to the trunnion to define an interface between the trunnion and the bushing; and a surface modification on at least one of the trunnion and the bushing at the interface, whereby frictional heating at the interface during operation of the assembly is reduced.

A system and a method for configuring at least one variable geometry mechanism (VGM) of an aircraft engine are provided. Pass-off testing data for the aircraft engine is obtained, the pass-off testing data indicative of an actual value of at least one operating parameter of the aircraft engine. Based on the pass-off testing data, at least one trim value to be used to adjust a setting of the at least one VGM to bring the actual value of the at least one operating parameter towards a target value is determined, a running line of the aircraft engine being substantially constant when the actual value of the at least one operating parameter is at the target value. The setting of the at least one VGM is adjusted, during pass-off testing of the aircraft engine, using the at least one trim value.

A variable guide vane assembly is provided for a turbine defining a core air flowpath. The variable guide vane assembly includes an airfoil band defining a flowpath surface and a cavity. The variable guide vane assembly further includes an airfoil including a first end extending at least partially into the cavity of the airfoil band and an opposite second end, the airfoil extending generally along an axis between the first end and the second end and being moveable generally about the axis relative to the airfoil band. The variable guide vane assembly further includes a sealing element operable to form a seal between the first end of the airfoil and the airfoil band.

A casing treatment for a compressor includes one or more cavities in a casing disposed radially outwardly of tips of the compressor rotor blades. A liner is moveable relative to the casing between a first position and a second position. The liner is shaped to add a volume to the tip clearance gap when moving from the second position toward the first position. The liner is displaceable between the first and second positions in coordination with at least the rotation of inlet guide vanes (IGVs) between IGV positions.

A gas turbine engine includes: a fan rotating about an engine main axis; a core duct; an engine core; an Engine Section Stator (ESS) including a plurality of ESS vanes and arranged in the core duct downstream of the fan; and a plurality of variable inlet guide vanes (VIGV) adapted to rotate about a pivot axis and arranged in the core duct downstream of the ESS. The VIGV vanes are arranged angularly rotated with respect to the ESS vanes such that the VIGVs are shielded by the ESS, thereby protecting the VIGVs from icing and from ice shedding from the ESS vanes.

An illustrative example embodiment of a compressor includes an inlet defining an intake passage, a plurality of lateral inlet guide vanes in the intake passage, and a plurality of medial inlet guide vanes in the intake passage. The lateral guide vanes are selectively oriented to alter an amount of fluid flow through a first, lateral portion of the intake passage. The medial inlet guide vanes are selectively oriented to alter an amount of fluid flow through a second, medial portion of the intake passage.

A blower includes a first extension having a first discharge port formed in a first wall, a second extension having a second discharge port formed in a second wall facing and spaced apart from the first wall, a fan provided below the first and second extensions to guide air toward each of the first tower and the second tower, a first gate provided inside the first tower or protruding from the first wall, a second gate provided inside the second tower or protruding from the second wall, a first guide motor to change a position of the first gate, and a second guide motor to change a position of the second gate.

A fan assembly for use in a sidewall of an animal house. The fan assembly includes an impeller, a motive force configured to rotate the impeller about a fan assembly axis, and a butterfly shutter. A shutter operation mechanism moves the butterfly doors of the shutter between the closed position and the open position in synchrony with an operating speed of the impeller. The shutter operating mechanism includes pushrods connected to the butterfly doors, and a linkage between the impeller and the second pushrods. The linkage includes at least one weight configured to rotate with the impeller about the fan assembly axis, wherein rotation of the at least one weight causes the linkage to exert a force on the pushrods to push the butterfly doors toward the open position when the impeller is rotating.

A vane assembly for a turbomachine includes a variable vane (10-15), the vane having at least one first, in particular plane or curved, engagement surface (11; 11′) for clamping, in particular without play, an actuator (20) of the vane assembly for adjustment of the vane, this first engagement surface not being inclined toward a longitudinal axis (L) of the vane or being inclined toward it by no more than 15°, and/or the vane assembly including a clamp (30; 31) for clamping the actuator against the first engagement surface by at least partially elastically compressing the clamp transversely to the longitudinal axis of the vane and/or by advancing the clamp in a clamp direction (S) that forms an angle of at least 45° with the longitudinal axis of the vane.

A variable-pitch stator vane for a turbine engine compressor stator, extending in a longitudinal radial plane including a radially inner plate and a radially outer plate between which at least one blade extends, each plate including a transverse longitudinal wall facing the other plate, characterised in that the transverse longitudinal wall of at least one plate includes at least one fin protruding radially towards the other plate.