A vane arm connection system for a gas turbine engine includes a vane stem having a head with flat contact surfaces; a vane arm having a claw, the claw having opposed arms having inwardly facing surfaces engaging the flat contact surfaces of the head; and a torque transfer member having a body defining an opening for engaging the flat contact surfaces of the head of the vane stem, and at least one arm extending from the body to contact the claw, whereby load from torque is transferred away from the inwardly facing surfaces.

A turbocharger actuator arrangement for a turbocharger includes a movable actuator operating lever, a control rod, and a wave spring. More specifically, the control rod is couplable to a setting element of the turbocharger and is connected to the actuator operating lever by means of a bolt such that the control rod is arranged to be rotatable relative to the actuator operating lever. The bolt extends from the actuator operating lever through an opening in an end region of the control rod and through the wave spring. As such, the control rod and the wave spring are arranged between the actuator operating lever and a bolt securing means, which is arranged at an end region of the bolt that is averted from the actuator operating lever.

A hook body for a latch mechanism includes a plurality of longitudinal members, each of the plurality of longitudinal members extending in a longitudinal direction with respect to the hook body; and a load slot at a proximal end of the hook body, the load slot having a loading portion and a receiving portion, the receiving portion configured to receive a transverse rod of a T-bolt and the loading portion configured to apply a load to the transverse rod upon translation of the hook body away from the transverse rod..

A system for controlling the clearance distance between an impeller blade tip of a centrifugal compressor and a radially inner surface of an impeller shroud in a turbine engine. The system comprises a high pressure air source, an air piston mounted between an engine casing and the shroud and adapted to receive high pressure air from the high pressure air source, a mounting arm coupling the shroud and air piston, and a slidable coupling adapted to allow axial movement of the shroud and joining the shroud to an axial member.

A system for controlling the clearance distance between an impeller blade tip of a centrifugal compressor and a radially inner surface of an impeller shroud in a turbine engine. The system comprises a two-piece integral impeller shroud with a fixed inner member and a variable outer member. An actuator is coupled to an aft end of the variable outer member and imparts axially forward and aft motion on the aft end, causing deflection of the outer member.

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.

Methods of manufacturing toothed components for gas turbine engines are provided. The methods include forming a first tooth in the component with a top land, a bottom land, a side wall extending therebetween, and a fillet radius transitioning between the side wall and the bottom land, forming a second tooth in the component adjacent the first tooth, the second tooth having a top land, a bottom land, a side wall extending therebetween and facing the first tooth, and a fillet radius transitioning between the side wall and the bottom land, the bottom land of the second tooth extending toward the bottom land of the first tooth, wherein the bottom lands define a gable area of the component, and forming a stress relief feature in the gable area such that the stress relief feature reduces a stress concentration near the gable area during operation of the toothed component.

A system for deploying a blocker door of a nacelle includes a master link configured to be coupled to a fixed structure of the nacelle and a master crank pivotally attached to the master link. The system further includes a first door crank and a first door link pivotally coupled to the first door crank. The system further includes a first blocker door coupled to the first door link and a first driveshaft coupled to the master crank and to the first door crank and configured to transfer motion from the master crank to the first door crank such that aft translation of a translating sleeve of the nacelle drives the master crank via the master link, which drives the first door link via the first driveshaft and the first door crank to move the first blocker door into a bypass air duct defined by the nacelle.

Steering rod for connecting an actuator to a turbocharger drive member, comprising an elongated main body (2), which extends between a first end (5) equipped with a first through-hole (7), and a second end (6) equipped with a second through-hole (8), and two bushings (3), (4) immovably mounted in the through-holes (7), (8), wherein the bushings (3), (4) are made of a material which has a greater resistance to mechanical wear than the material delimiting the through-holes (7), (8), and wherein each bushing (3) (4) has an outer surface that is in contact with an inner part of the through-hole (7), (8) and has a radial recess (9), the second material tightening the bushing (3), (4) preventing it from rotating and filling the recess (9) preventing the bushing (3), (4) from being extracted from the second through-hole (7), (8).

A compressed air conduit can have a cross-sectional area, and a valve, the valve having at least one arm being deployable laterally into the cross-sectional area of the conduit to restrict flow within the conduit.