A turbofan having a nacelle delimiting a duct for a bypass flow and including a fixed structure including a guide vane support with guide vanes, a mobile cowl movable in translation between an advanced position and a retracted position, arms, each one being mobile in rotation on the guide vane support between a stowed position and a deployed position and comprising a distal end and a proximal end, for each pair of adjacent arms, a flexible screen extending angularly between the two arms, and of which an exterior edge is attached to the guide vane support, and wherein the distal end of each arm is fixed along the interior edge, a link rod mounted articulated between the distal ends, actuators to cause the mobile cowl to move, and an operating system which moves each arm. Such an arrangement allows a reduction in weight.

A vane lever (46) for a guide apparatus (28) of a turbocharger (10) may include a base (49). The base (49) may include a bore (48) disposed therethrough. An arm (50) may extend from the base (49) and may be receivable in an aperture (42) of an adjustment ring (40) of the guide apparatus (28). A protuberance (52) may extend from the base (49) and may be capable of limiting axial movement of the adjustment ring (40).

A linkage system includes a pivot bias assembly at each pivot which removes internal clearances and resultant vibratory wear. The pivot bias assembly includes a cavity which defines an axis transverse to the pivot axis. A spring biased piston is located therein to provide a radial load toward the rotation pivot to close radial clearances. The spring loaded piston reduces all the radial internal clearances to zero to reduce vibratory wear created by engine vibratory inputs. An assembly flat is positioned such that the component is assembled in a non-operating angular position such that the spring biased piston is under minimal or no load then the component is rotated into operating position so as to preload the spring biased piston.

A centrifugal compressor includes a volute base block, a volute cover plate, an impeller, a diffuser-adjusting assembly, a radial constraint assembly, an axial constraint assembly and a driving assembly. A diffuser and a connected volute are formed between the cover plate and the base block. The impeller discharges gas to the centrifugal compressor through the diffuser and the volute. The diffuser adjustment assembly includes a driving ring, a driving rod, a pin and a diffuser ring. The radial constraint assembly is disposed on an inner circumference surface of the driving ring. The axial constraint assembly on an outer circumference surface of the driving ring is located between the top and bottom portions. The drive assembly is to rotate the driving ring. When the driving ring rotates, the pin slides along the pin track, and the driving rod displaces the diffuser ring to adjust a flow-path width of the diffuser.

An apparatus for controlling turbine blade tip clearance is provided. The apparatus for controlling turbine blade tip clearance includes a turbine casing configured to guide a flow of combustion gas, an actuator ring rotatably mounted outside the turbine casing, a plurality of turbine blades rotatably mounted inside the turbine casing, a plurality of ring segments surrounding tips of the turbine blades and installed to form a predetermined gap with each tip, a plurality of rotary shafts each configured to have one end connected to several of the plurality of ring segments and the other end extending radially from the turbine casing, a link member configured to rotate an associated one of the rotary shafts according to circumferential rotational motion of the actuator ring, and a pusher member provided at an inner end of the rotary shaft to move the ring segments radially inward by rotation of the rotary shaft, wherein the actuator ring rotates back and forth in a predetermined angular range by an actuator installed outside the turbine casing.

An insertion tool is provided for an engine defining an access opening and including a component defining at least in part a cavity. The insertion tool includes: an insertion tool arm having a plurality of segments, the insertion tool arm configured for insertion through the access opening into the cavity and the plurality of segments configured to be in a fixed position relative to one another within the cavity; and a base coupled to the insertion tool arm and configured to be positioned outside the cavity and to move the insertion tool arm along at least two degrees of freedom.

A variable guide vane (VGV) assembly for a gas turbine engine has: vanes distributed about a central axis and having airfoils between stems at respective ends of the airfoils; a unison ring; sliders protruding from the unison ring; and vane arms engaged to first stems and defining respective slots, each of the slots extending in a direction having a radial component relative to a respective one of the spanwise axes, the sliders received within respective ones of the slots, a slot extending from a proximal end to a distal end along a slot axis, the vane arm defining the slot having an end wall at the distal end, the end wall extending in a direction having a component transverse to the slot axis such that a slider abuts against the end wall when the slider is at the distal end to prevent the sliders from moving out of the slots.

A damping link assembly for a bleed valve of a gas turbine engine. The damping link assembly having: a bleed valve ring having a link aperture; a mechanical fastener disposed in the link aperture; and a damping guide link operatively coupled to the mechanical fastener at one end for rotation about a first axis of the mechanical fastener and the damping guide link being operatively coupled to an idler bracket at an opposite end for rotation about a second axis, the damping guide link being capable of twisting about a third axis different from the first axis and the second axis when the bleed valve ring is rotated from a first position to a second position.

A variable guide vane (VGV) assembly for a gas turbine engine, has: variable guide vanes circumferentially distributed about a central axis, the variable guide vanes rotatable about respective spanwise axes; and a unison member rollingly engageable to a casing of the gas turbine engine for rotation about the central axis, the unison member operatively connected to the variable guide vanes for rotating the variable guide vanes about the respective spanwise axes, the unison member having: a first ring extending around the central axis, a second ring spaced apart from the first ring and extending around the central axis, and connecting members connecting the first ring to the second ring.

A variable nozzle device includes: a nozzle mount; a plurality of nozzle vanes; a drive ring being having a plurality of receiving portions disposed at different positions along a circumferential direction; and a plurality of lever plates each having a fixed portion to be fixed to corresponding one of the plurality of nozzle vanes and an engaging portion to be engaged with corresponding one of the plurality of receiving portions of the drive ring. The receiving portions include a first-side guide surface and a second-side guide surface. The engaging portions each include a first-side roll surface which is to be in contact with the first-side guide surface and a second-side roll surface which is to be in contact with the second-side guide surface. The first-side roll surface includes a lever-plate-side linear portion extending linearly in at least a part of a range which is to be in contact with the first-side guide surface. The first-side guide surface includes a drive-ring-side protruding curved surface portion extending in a protruding curve shape in at least a part of a range which is to be in contact with the first-side roll surface.