Rolls-royce Corporation

Rolls-royce North American Technologies Inc.

Rolls-royce Deutschland Ltd & Co. Kg

Eric William Engebretsen

Matthew J Kappes

Jonathan M Rivers

Jonathan Acker

Aaron Weishaar

Robert W Heeter

Daniel E Molnar, Jr

Patrick E Bailey

Brett Hartnagel

Samuel J Lacombe

Rodney D Conrad

Trevor John Totten

Christopher D Hall

Timothy Unton

Ewan Fergus Thompson

Benedict N Hodgson

Matthew A Scott

Matthew Jordan

Daniel Molnar

Erin M Romanowski

Russel MacFarlane

Michael Buckley

Benedict M Hodgson

Erick Meyer

Eric Thurston

Jonathan Michael Rivers

Matthew Joseph Kappes

John Trevor Totten

A gas turbine engine includes: an inlet guide vane; an inlet channel extending from a location downstream of the inlet guide vane to a stem manifold; and an outlet channel extending to an outlet port, the outlet port configured to dump anti-ice air overboard, wherein the inlet guide vane includes an anti-ice cavity in fluid communication with the inlet channel and the outlet channel such that anti-ice air, flowing from a downstream location within a core flow of the gas turbine, flows from the inlet channel, through the inlet guide vane, and to the outlet channel.

Anti-ice system for gas turbine engine and inlet guide vane

A gas turbine engine includes: a manifold arrangement; a plurality of inlet guide vanes located radially inward of the manifold arrangement, wherein each inlet guide vane of the plurality of guide vanes includes an anti-ice cavity for directing a flow of an anti-ice air; and a plurality of crossover ducts located radially inside the manifold arrangement, wherein each crossover duct of the plurality of crossover ducts provides fluid communication between two adjacent inlet guide vanes.

Manifold assembly and anti-ice system for gas turbine engine

A rotor assembly includes a first component, a second component, and a splined balance weight. The first component is arranged circumferentially around a central axis. The second component is arranged circumferentially around the central axis. The splined balance weight is located radially between the first component and the second component.

Splined balance weight for rotating components in gas turbine engines

A compressor assembly for a gas turbine engine includes an outer band, a plurality of variable pitch vanes, and an inner band. The plurality of variable pitch vanes extend radially between the outer band and the inner band. The inner band extends circumferentially partway about an axis and includes a first ring segment and a second ring segment that cooperate to receive the plurality of variable pitch vanes.

Sectioned compressor inner band for variable pitch vane assemblies in gas turbine engines

Aspects of the disclosure regard a fan case assembly for a gas turbine engine, the fan case assembly comprising a fan case having an inner surface, a fan case liner having an outer surface, and a reclosable fastening system attaching the fan case liner to the fan case, the reclosable fastening system comprising two components, a first component being attached to the fan case inner surface and a second component being attached to the fan case liner outer surface.

Fan case assembly for a gas turbine engine

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

A fan case for use in a gas turbine engine of an aircraft includes an outer shroud and a liner extending along the outer shroud. The fan case provides a protective band that blocks fan blades from being thrown out of the fan case in case of a blade-off event in which a fan blade is released during operation of the gas turbine engine.

Fan case assemblies

The present disclosure provides a liner system for a turbine engine. The liner system includes a fan track liner panel that is positionable axially within a casing that is arranged around a rotatable fan and that forms a blade containment zone. The fan track liner panel is further positionable radially outward of the rotatable fan. The fan track liner panel includes a body that extends a length of the fan track liner panel from a fore portion of the fan track liner panel to an aft portion of the fan track liner panel. The fan track liner panel is configured to be directly secured to the casing by a fastener that extends through only part of the body and entirely through the casing within the blade containment zone such that the aft portion of the fan track liner panel abuts an interior surface of the casing.

Liner system

A spinner for use in a gas turbine engine includes a body and an aft ring coupled to the body. The body is symmetrically formed by filament winding around a central axis. The aft ring includes a band coupled to the body and a plurality of fairings that extend outward in a radial direction from the band away from the central axis.

Spinner for a gas turbine engine

A method of replacing a fan case liner panel in an engine fan case is provided. In one illustrative form, the method may include applying heat to an engine fan case to debond an adhesive layer, removing the first fan case liner panel, and bonding a second fan case liner panel.

Fan case liner removal with external heat mat

A containment system for a gas turbine engine includes a fan track assembly for use with a containment case. The fan track assembly includes a body of collapsible material that is positioned within a cavity of the fan case, and voids are provided for providing space in the event of a catastrophic blade failure. Various configurations of the fan track liner assembly are provided along with various mounting methodologies for securing the track liner assembly to the fan case of a gas turbine engine.

Fan track liner designed to yield next to fan case hook

An aerodynamic fan nosecone for a gas turbine engine is provided and includes a fan nosecone that may be made of composite material. To improve airflow transition to the blade members, aerodynamic fairings are provided and are secured to an exterior surface of the nosecone which enhances fuel economy. The fairings may be secured to the nosecone by various methods, including providing for the fairings to be changed out and replaced with other fairings on the same nosecone assembly.

Aerodynamic fairings secondarily attached to nosecone

An aggregate vane assembly includes a core vane assembly encircling a central longitudinal axis and having a plurality of core vanes each extending radially between an inner hub and an outer band. The aggregate vane assembly also includes a bypass vane assembly disposed on a radially opposite side of the outer band relative to the plurality of core vanes. The aggregate vane assembly also includes a splitter ring positioned proximate to the first forward end. The aggregate vane assembly also includes at least one retention plate overlapping a forward end of the at least one bypass vane along the central longitudinal axis and also overlapping at least a portion of the splitter ring along the central longitudinal axis.

Aggregate vane assembly

A balance weight adapted to be assembled to a nose cone assembly of a turbine engine for improving a balance of the nose cone assembly is disclosed herein. The balance weight is one-piece and formed from a plurality of different materials including at least first and second materials. The first and second materials are arranged substantially heterogeneously relative to one another such that said first and second materials are separate from one another and fixed together.

Growing community of inventors

Zionsville, IN, United States of America

Eric William Engebretsen