Rolls-royce Corporation

Rolls-royce North American Technologies Inc.

Rolls-royce Deutschland Ltd & Co. Kg

Rolls-royce Corporalion

Jonathan M Rivers

Robert W Heeter

Daniel E Molnar, Jr

Roy David Fulayter

Dennes Kyle Burney

Eric William Engebretsen

Matthew J Kappes

Bronwyn Power

Benedict N Hodgson

Matthew Jordan

Trevor John Totten

Edward Claude Rice

Timothy Unton

Jonathan Acker

Robert F Proctor

Michael Stephen Krautheim

Matthew A Scott

Nathan J Cooper

Mark A Fleckenstein

Mark E Bartolomeo

Daniel Molnar

Philip Michael Bastnagel

Jeff Higbie

Maxwell Layman

Christopher I Hamilton

Bronwyn Powers

Christopher J Schubert

Eric Handa

Aaron Martin

Eric Engebretsen

A vane assembly adapted for a gas turbine engine includes a first vane segment that extends circumferentially about an axis and a second vane segment. The second vane segment includes a band that extends circumferentially about the axis and a plurality of vanes coupled to the band and extending radially from the band.

Vane assemblies with overlapping band couplings in gas turbine engines

A gas turbine engine includes a fan and a fan case assembly. The fan includes a fan rotor configured to rotate about an axis of the gas turbine engine and a plurality of fan blades coupled to the fan rotor for rotation therewith. The fan case assembly extends circumferentially around the plurality of fan blades radially outward of the plurality of the fan blades.

Adjustable fan track liner with groove array active fan tip treatment for distortion tolerance

A fan case assembly adapted for use with a gas turbine engine includes a fan casing and a bleed air flow control system. The fan casing includes an annular case and a fan track liner coupled with the annular case. The bleed air flow control system is configured to bleed selectively a portion of air flowing through a gas path of the fan case assembly for use as a cooling source in the fan case assembly.

Turbine engine fan case with bleed air for tip injection and heat exchanger cooling

Adjustable fan track liner with slotted array active fan tip treatment for distortion tolerance

Adjustable fan track liner with dual grooved array active fan tip treatment for distortion tolerance

Active fan tip treatment using rotating drum array with axial channels in fan track liner for distortion tolerance

Adjustable fan track liner with dual slotted array active fan tip treatment for distortion tolerance

Active fan tip treatment using rotating drum array in fan track liner with axial and circumferential channels for distortion tolerance

A fan case assembly adapted for use with a gas turbine engine includes a case at extends circumferentially at least partway about an axis of the gas turbine engine and a plurality of vanes. The case is formed to define a plenum that that extends circumferentially at least partway about the axis. The plurality of vanes are arranged in the plenum and spaced apart circumferentially about the axis to define a plurality of inlet openings in fluid communication with the plenum.

Adjustable air flow plenum with movable closure for a fan of a gas turbine engine

A fan case assembly adapted for use with a gas turbine engine includes a case at extends circumferentially at least partway about an axis of the gas turbine engine and a plurality of vanes. The case is formed to define a plenum that that extends circumferentially at least partway about the axis. The plurality of vanes are arranged in the plenum and spaced apart circumferentially about the axis.

Adjustable air flow plenum with sliding doors for a fan of a gas turbine engine

Adjustable air flow plenum with pivoting vanes for a fan of a gas turbine engine

A fan case assembly adapted for use with a gas turbine engine includes a case at extends circumferentially at least partway about an axis of the gas turbine engine and a plurality of vanes. The case is formed to define a plenum that extends circumferentially at least partway about the axis. The plurality of vanes are arranged in the plenum and spaced apart circumferentially about the axis to define a plurality of inlet openings in fluid communication with the plenum.

Adjustable air flow plenum with circumferential movable closure for a fan of a gas turbine engine

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 and an outer surface, a front acoustic panel having an outer surface, and attachment means attaching the front acoustic panel outer surface to the fan case inner surface. The attachment means comprise a sliding arrangement allowing the front acoustic panel to be slid axially into the fan case. The sliding arrangement comprises a first longitudinal member and a second longitudinal member, one of the members being attached to the fan case inner surface and the other member being attached to the front acoustic panel outer surface. The attachment means further comprise removable fastening means fixing the first longitudinal member and the second longitudinal member in the axial direction.

Fan case assembly for a gas turbine engine

Composite liners (such as acoustic panels, fan track liners, and/or ice impact panels or boxes for turbofan engines) and techniques for forming composite liners. In some examples, the composite liner includes at least one region comprising a reinforcement architecture comprising a matrix material, a plurality of relatively tough polymer-based reinforcement elements, and a plurality of second reinforcement elements. The plurality of relatively tough polymer-based reinforcement elements and the plurality of second reinforcement elements are embedded in the matrix material.

Composite liners for turbofan engines

A composite aerofoil may include an aerofoil body defining a leading edge and a trailing edge, wherein the body comprises a composite material including a plurality of relatively higher-modulus reinforcement elements, a plurality of relatively tougher polymer-based reinforcement elements, and a matrix material substantially encapsulating the plurality of relatively higher-modulus reinforcement elements and the plurality of relatively tougher polymer-based reinforcement elements. The plurality of relatively higher-modulus reinforcement elements are different from the plurality of relatively tougher polymer-based reinforcement elements. The disclosure also describes techniques for forming composite aerofoils.

Composite aerofoils

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Danville, IN, United States of America

Jonathan M Rivers