Rolls-royce Corporation

Rolls-royce North American Technologies Inc.

Samuel J Lacombe

Patrick E Bailey

Eric William Engebretsen

Matthew J Kappes

Rodney D Conrad

Patrick L Lunsford

Christopher D Hall

James Christopher Muskat

Rodney Conrad

Joseph Benjamin LaBelle

Matthew Kappes

Eric Engebretsen

Patrick Bailey

A fan assembly for use in a gas turbine engine of an aircraft includes a fan disk having a number of fan blades and a windage shield coupled to the fan disk to move therewith. The fan assembly supplies air for use in the engine. The windage shield rotates with the fan disk during operation of the gas turbine engine and directs air supplied by the fan blade.

Attachment of piloting feature

Method to pilot using flexible profile

An impeller includes a shell having a plurality of blades. The shell may also define a cavity. The impeller may further include a backplate that engages at least a portion of the shell. The backplate can include a post which can be coupled to the impeller through a fastener such as a threaded nut. The backplate can be thereafter clamped to the impeller shell. Seals can be provided in the impeller, such as in the backplate. The backplate and impeller shell can be piloted onto each other. In some forms splines can be used to secure the backplate to the impeller shell.

Multi-piece impeller

A gas turbine engine according to the present disclosure includes a first component, a second component coupled to the first component, and a pilot unit. The pilot unit provides means for maintaining a pilot-setting force between the first and second component to retain alignment of the first component with the second component.

A disk for a turbine engine is disclosed herein. The disk includes a rotatable body extending along a longitudinal axis between a forward side and an aft side. The disk also includes a plurality of slots disposed about a periphery of the body. Each of the slots extends between the forward and aft sides along a respective slot axis. The sides of each of the slots are asymmetrical relative to one another in a cross-section normal to the slot axis.

Disk for turbine engine

Growing community of inventors

Indianapolis, IN, United States of America

Samuel J Lacombe