Rolls-royce Corporation

Rolls-royce North American Technologies Inc.

Michael Stephen Krautheim

Robert W Heeter

Daniel E Molnar, Jr

Jonathan F Carrotte

Alastair Duncan Walker

Anthony J Rae

Ian Mariah

Richard Northall

Daniel Kent Vetters

Jonathan M Rivers

Eric Sean Donovan

Michael Karam

Donald G Chouinard

Carlos Soto-Gonzalez

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 channel that that extends circumferentially at least partway about the axis. The plurality of vanes are arranged in the channel and spaced apart circumferentially about the axis.

Adjustable depth tip treatment with axial member with pockets 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 channel that extends circumferentially at least partway about the axis. The plurality of vanes are arranged in the channel and spaced apart circumferentially about the axis.

Adjustable depth tip treatment with rotatable ring with pockets for a fan of a gas turbine engine

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

An annular array of turning vanesis provided in a ductof a gas turbine engine. The annular array of turning vanescomprises aerodynamic vanesand strut-vanes. The strut-vaneshave greater chord length and extend further axially downstream than the aerodynamic vanes. The leading edge of the strut-vanesis upstream of the trailing edge of the aerodynamic vanes. The strut-vanes provide flow turning. The arrangement allows the ductto be axially short.

Gas turbine engine vanes

An annular array of turning vanesis provided in a ductof a gas turbine engine. The annular array of turning vanescomprises aerodynamic vanesand strut-vanes. The strut-vaneshave greater chord length and extend further axially downstream than the aerodynamic vanes. The leading edge of the strut-vanesis upstream of the trailing edge of the aerodynamic vanes. The strut-vanes provide flow turning. The space to chord ratio of the aerodynamic vanes that are closest to the suction surface of a strut-vane is higher than the space to chord ratio of aerodynamic vanes that are closest to a pressure surface of the strut-vane. The arrangement allows the ductto be axially short.

One embodiment of the present invention is a unique aircraft propulsion gas turbine engine. Another embodiment is a unique gas turbine engine. Another embodiment is a unique gas turbine engine. Other embodiments include apparatuses, systems, devices, hardware, methods, and combinations for gas turbine engines with heat exchange systems. Further embodiments, forms, features, aspects, benefits, and advantages of the present application will become apparent from the description and figures provided herewith.

Gas turbine engine with air/fuel heat exchanger

A gas turbine engine having a heat exchanger is disclosed. In one form the gas turbine engine includes a particle separator that can be used to separate particles or foreign objects and create a dirty flow and a clean flow. A blower can be used to discharge the particles or foreign objects from the separator. The heat exchanger includes a relatively warm flow path from a downstream region of a compressor and a relatively cool flow path from an upstream region of the compressor. The relatively cool flow path is merged with the dirty flow. In another embodiment, the gas turbine engine is a turbofan and the relatively cool flow path is merged with a bypass flow. In one embodiment of the engine the relatively warm flow path, after having exchanged heat with the relatively cool flow path is delivered to a working component without passing through a turbomachinery component.

Gas turbine engine heat exchanger

An axial flow compressor for a gas turbine engine is disclosed having a casing treatment that includes a shrouded rotor and an airflow member disposed in a passage between a casing and the shrouded rotor. In one form the airflow member is stationary with the casing and in another the airflow member is coupled to rotate with the shrouded rotor. The airflow member can have an airfoil shape in some embodiments. A passage inlet that extracts working fluid and provides it to the passage can be formed between a leading edge of the rotor and a trailing edge. A passage outlet can be formed upstream of the leading edge of the rotor.

Compressor casing treatment for gas turbine engine

A wheel is constructed from a disk disposed for rotation about an axis and a ring with a plurality of blades being connectable to the disk. The wheel is operable for pumping, compressing, or expanding fluid in a turbomachine. The disk is configured to receive at least a portion of the ring within the disk and be coupled using a protrusion or protrusions. The protrusion can be configured to prevent relative movement between the disk and the ring. In some forms a bracket can be extended between the ring and disk to prevent relative movement.

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Fountaintown, IN, United States of America

Michael Stephen Krautheim