United Technologies Corporation

Raytheon Technologies Corporation

Rtx Corporation

Bernard W Pudvah

Eugene C Gasmen

Stanley Wiecko

Christopher St Mary

Jonathan D Little

Herbert L Walker

Mark Boyer

Christopher R Osborne

Nicholas G Morganti

Manjunath Subramanya

Matthew E Bintz

Daniel W Major

Anthony Valenti

Donald Dougan

Nicholas Morganti

An actuation structure changes the orientation of a vane airfoil. A spindle is fixed to the airfoil such that when the arm turns the spindle, the spindle turns the airfoil, the spindle extends through a bore in the housing. A mount is between the spindle and the housing at the bore, with a metal wear sleeve pressed into the housing at the bore, such that it is part of the housing. A bushing is secured to an outer periphery of the spindle such that a bearing surface during rotation of the spindle is provided by an outer periphery of the bushing and an inner periphery of the metal wear sleeve. A seal is radially outward of the bushing with the seal providing an air seal between the spindle and the bore. A gas turbine engine is also disclosed.

Compressor variable vane spindle mount with floating seal

A method of manufacturing a compressor. A member is cast having forward and aft annular portions. A cavity forward wall extends from the forward annular portion to a first inner end. A cavity aft wall extends from the aft annular portion to a second inner end. A cavity outer wall extends between the forward and aft annular portions and defines an outer aperture. A cavity inner wall is cast and welded between the cavity forward and aft walls such that the cavity inner wall is offset from the first and second inner ends of the cavity forward and aft walls to form a U-shaped end channel. The compressor case is capable of receiving a vane so that a trunnion bearing extends from a vane root to a trunnion bearing outer end, through the inner aperture in the cavity inner wall and the outer aperture in the cavity outer wall.

Compressor case with a cooling cavity

A link setting assembly according to an exemplary aspect of the present disclosure includes, among other things, a fixture including at least one platform mount and at least one linkage mount. The at least one linkage mount is spaced-apart from the platform mount by a distance corresponding to a predetermined link length.

Link setting assembly and method

A variable vane stabilizer is disclosed. One or more variable vane stabilizer may be interconnected between/among two or more vanes of a gas turbine engine in order to fix the angle of attack of the vanes.

Variable vane stabilizer

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.

Vane arm assembly

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.

Vane arm having a claw

A synchronizing ring assembly for a variable guide vane system is disclosed. The synchronizing ring assembly is disposed about an engine axis and includes a synchronizing ring having a radially outer surface with a clevis bracket mounted to the radially outer surface of the synchronizing ring and defining radially extending openings through the clevis bracket. A plurality of fasteners are configured and adapted to be received within the radially extending openings in the clevis bracket for securing the clevis bracket to the radially outer surface of the synchronizing ring.

Radial fastening of tubular synchronizing rings

A variable area vane arrangement includes a stator vane including a shaft having an axis. The vane arrangement also includes a vane lever arm that rotates the stator vane about the axis. The vane lever arm includes a base, a first tab and a second tab. The base is arranged laterally between the first tab and the second tab. The first tab laterally overlaps the base. The second tab includes an aperture and laterally overlaps the base and the first tab. The shaft extends through the aperture and is connected to the base.

Vane lever arm for a variable area vane arrangement

An example turbomachine bushing a bushing having a wear surface configured to interface directly with a variable vane assembly to limit radially inward movement of the variable vane assembly, wherein the variable vane assembly is moveable axially between a first position contacting the wear surface and a second position spaced from the wear surface.

Flanged bushing for variable vane

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.

Machined vane arm of a variable vane actuation system

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.

Actuator mounted to torque box

A fastener system that when assembled prevents the assembly from accidently falling out of the housing. The fastener system includes a reduced shank bolt, a bushing with internal threads and a snap ring relief, a snap ring, and a housing modified to receive the bushing and the snap ring. The flange may have a flange relief to seat the snap ring when the fully engaged.

Fastener system

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.

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.

Growing community of inventors

Portland, CT, United States of America

Bernard W Pudvah