United Technologies Corporation

John T Pickens

Phillip Alexander

Tuy Tran

Anthony R Bifulco

Allan R Penda

Kevin J Cummings

Roland R Barnes

Stanley J Szymanski

An exemplary gas turbine engine component assembly includes, among other things, a case having a generally cylindrical outer surface. At least one synchronizing ring is received at least partially about the outer surface of the case. A plurality shims situated between an inner surface on the at least one synchronizing ring and the outer surface of the case at a plurality of shim locations are circumferentially spaced about the case outer surface. Each shim location includes at least one of the shims. A radial thickness of the shims at a first one of the shim locations is different than the radial thickness of the shims at a second one of the shim locations.

Gas turbine engine components and method of assembly

A compressor disk for a turbine engine includes a plurality of blades mounted about the circumference. To assemble the blades onto the disk a lock assembly is inserted within a blade slot on the disk. A blade is assembled into the blade slot and slider seals are inserted between the blade and the disk to limit air from entering the blade slot. Additional blades are assembled until the end of the slider seals are reached. The process is repeated until all the blades have been assembled onto the disk. After the last blade has been assembled a spacer seal is placed at each lock assembly to take up the slack. Once all the blades and spacer seals are assembled the lock assemblies can be moved to a locked position.

Rotor disk and blade arrangement

A compressor for a turbine engine includes multiple compressor disks having rotor blades mounted about the circumference of each of the disks. A plurality of stator blades extend between the rotor blades of axially adjacent disks. A knife edge seal is supported and retained by retaining flanges extending from a rim on each disk, and contacts the stator blades to limit the recirculation of air within the compressor. A plurality of lock assemblies are spaced about the circumference of disk backbones formed in each disk, with a plurality of knife edge seals located between each lock assembly. When in the lock position the lock assemblies reduce the slack used for assembly of the final knife edge seal to prevent shifting and rotating during operation.

Interlocking knife edge seals

An array of blades for use in an engine includes a disk having a slot, a pair of rails adjacent the slot and extending above an upper surface of the slot, and a pair of shoulders located outside the rails. A plurality of radially loaded blades are inserted into the slot. A plurality of snaps overhang the rails and rest on the shoulders. Each of the blades is positioned between a pair of snap seals and overlaps a side edge of each one of the pair of snap seals.

Method for loading and locking tangential rotor blades and blade design

A method of reverse engineering a component of a gas turbine engine having a root attachment feature includes scanning the root attachment feature a plurality of times to obtain raw scan data, creating a best fit line relative to pressure faces of the root attachment feature as a function of the raw scan data, determining a pressure face angle as a function of the relationship between the best fit lines of the pressure faces, bisecting the pressure face angle to determine a symmetry plane for the root attachment feature, establishing a master attachment data set in relation to the local coordinate system by averaging the best fit lines and the raw scan data for each scan of the root attachment feature, and verifying symmetry of the master attachment data set.

Reverse engineering method for disk and blade attachments

A compressor for a turbine engine includes multiple compressor disks having rotor blades mounted about the circumference of each of the disks. A plurality of stator vanes extend between the rotor blades of axially adjacent disks. A knife edge seal segment is supported by each disk backbone extending from the disks and contacts the stator vanes to restrict leakage of compressed air from between the stator vane and the compressor rotor to limit the recirculation of air. Retaining flanges extend from each disk rim to retain the knife edge seal segments to the disk backbone and spacer bridges integral to the knife edge seal segments prevent axial movement of the knife edge seal segments. A plurality of lock assemblies are spaced about the circumference of the disk backbone to prevent circumferential shifting and rotating of the knife edge seal segments during operation.

Split knife edge seals

An attachment system for use with a variable incidence vane is disclosed. The attachment system includes a vane arm for joining a unison ring to a vane spindle. The vane arm has an arm portion and a bushing connected to the arm portion. The attachment system further has a pin for joining the vane arm to the unison ring. The pin fits within an interior bore in the bushing and is joined to the unison ring by a dual swage.

Variable vane arm/unison ring attachment system

The present invention relates to a bumper system for use with a compressor variable vane system. The bumper system broadly comprises a synchronizing ring, a bumper, a shim for defining a gap between a bumper pad and the bumper, a pin for preventing rotation of the bumper relative to the synchronizing ring, and a device for fully trapping the shim. In a first embodiment, the device for fully trapping the shim comprises a sleeve passing through the synchronizing ring. In a second embodiment, the device for fully trapping the shim comprises a pin which passes through the synchronizing body. In a third embodiment, the device for fully trapping the shim comprises a fastener with a shoulder.

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Middletown, CT, United States of America

John T Pickens