Abstract: An assembly for operating a device, such as a variable vane, has an arm, a stem to which the arm is connected, the stem having a slot, and a member having a tab which fits into the slot.

Abstract: An exemplary variable vane actuation system for a gas turbine engine includes a vane arm attachable to a vane stem and configured to rotate the vane stem about a radially extending axis. The vane arm includes a claw feature to be press-fit onto the vane stem.

Abstract: An exemplary variable vane actuation system includes, among other things, a vane arm with a vane stem contact surface and a radially outward facing surface. The vane stem contact surface is to contact a vane stem of a variable vane and thereby actuate the variable vane about a radially extending axis. The vane stem contact surface is angled relative to both the radially extending axis and the radially outward facing surface.

Abstract: An actuator system mounted to a gas turbine engine that communicates mechanical power for positioning variable guide vanes within the gas turbine engine. The actuator system includes a torque box having components for communicating mechanical power to the variable guide vanes for positioning the vanes and an actuator mechanically coupled to provide mechanical power to the components of the torque box used to communicate the provided mechanical power to the inlet guide vanes. The actuator is mounted to the torque box via an elongate fastener extending in one direction and another elongate fastener extending in another direction.

Abstract: An assembly for operating a device, such as a variable vane, has an arm, a stem to which the arm is connected, the stem having a slot, and a member having a tab which fits into the slot.

Abstract: An exemplary variable vane actuation system includes, among other things, a vane arm with a vane stem contact surface and a radially outward facing surface. The vane stem contact surface is to contact a vane stem of a variable vane and thereby actuate the variable vane about a radially extending axis. The vane stem contact surface is angled relative to both the radially extending axis and the radially outward facing surface.

Abstract: An actuator system mounted to a gas turbine engine that communicates mechanical power for positioning variable guide vanes within the gas turbine engine. The actuator system includes a torque box having components for communicating mechanical power to the variable guide vanes for positioning the vanes and an actuator mechanically coupled to provide mechanical power to the components of the torque box used to communicate the provided mechanical power to the inlet guide vanes. The actuator is mounted to the torque box via an elongate fastener extending in one direction and another elongate fastener extending in another direction.

Abstract: An actuator system mounted to a gas turbine engine that communicates mechanical power for positioning variable guide vanes within the gas turbine engine. The actuator system includes a torque box having components for communicating mechanical power to the variable guide vanes for positioning the vanes and an actuator mechanically coupled to provide mechanical power to the components of the torque box used to communicate the provided mechanical power to the inlet guide vanes. The actuator is mounted to the torque box via a plurality of bolts.

Abstract: A gas turbine engine includes a synchronizing ring. A cradle includes an integrally formed anti-rotation feature. The cradle is secured to the synchronizing ring and located relative thereto with the anti-rotation feature. A bumper is slidably supported within the cradle. In one example, a bushing is provided within a hole in the bumper. A fastener is inserted into the hole and a bushing to secure the bumper to the synchronizing ring.

Abstract: An exemplary variable vane actuation system for a gas turbine engine includes a vane arm attachable to a vane stem and configured to rotate the vane stem about a radially extending axis. The vane arm includes a claw feature to be press-fit onto the vane stem.

Abstract: A synchronizing assembly for a gas turbine engine includes a synchronizing ring. A composite bumper is secured to the synchronizing ring by a fastener. A structure is arranged between the bumper and the synchronizing ring. The fastener applies a first load through the structure to the synchronizing ring and a second load through the bumper. The second load is substantially less than the first load. In one example, the structure includes a bushing that extends through a hole in the bumper. The bushing is proud of the hole on the other side of the bumper and protrudes into the counterbore. The fastener is arranged in the bushing and applies a clamping load through the bushing to secure the bumper to the synchronizing ring.

Abstract: An assembly includes a torque box and a first bell crank. The torque box has a housing with an interior cavity. The first bell crank is pivotally supported from the housing and extends through the interior cavity. The first bell crank has three arms for transferring an actuating force to a plurality of variable guide vanes for positioning the guide vanes within a gas turbine engine.

Abstract: An actuator system mounted to a gas turbine engine that communicates mechanical power for positioning variable guide vanes within the gas turbine engine. The actuator system includes a torque box having components for communicating mechanical power to the variable guide vanes for positioning the vanes and an actuator mechanically coupled to provide mechanical power to the components of the torque box used to communication the provided mechanical power to the inlet guide vanes. The actuator is mounted to the torque box via a plurality of bolts.

Abstract: An adjustable clevis assembly includes a clevis, a first adjustment sleeve, a second adjustment sleeve, a tongue and a clevis pin. The clevis includes a first support flange with a first sleeve aperture and a second support flange with a second sleeve aperture. The first adjustment sleeve is seated in the first sleeve aperture, and includes a first pin aperture that is eccentric relative to the first sleeve aperture. The second adjustment sleeve is seated in the second sleeve aperture, and includes a second pin aperture that is eccentric relative to the second sleeve aperture. The tongue is arranged between the first support flange and the second support flange. The clevis pin extends through the first pin aperture, the second pin aperture and a third pin aperture in the tongue.

Abstract: A gas turbine engine includes a synchronizing ring. A cradle includes an integrally formed anti-rotation feature. The cradle is secured to the synchronizing ring and located relative thereto with the anti-rotation feature. A bumper is slidably supported within the cradle. In one example, a bushing is provided within a hole in the bumper. A fastener is inserted into the hole and a bushing to secure the bumper to the synchronizing ring.

Abstract: A synchronizing assembly for a gas turbine engine includes a synchronizing ring. A composite bumper is secured to the synchronizing ring by a fastener. A structure is arranged between the bumper and the synchronizing ring. The fastener applies a first load through the structure to the synchronizing ring and a second load through the bumper. The second load is substantially less than the first load. In one example, the structure includes a bushing that extends through a hole in the bumper. The bushing is proud of the hole on the other side of the bumper and protrudes into the counterbore. The fastener is arranged in the bushing and applies a clamping load through the bushing to secure the bumper to the synchronizing ring.