Rolls-royce Corporation

Rolls-royce North American Technologies Inc.

Michael G Meyer

Daniel E Molnar, Jr

Robert W Heeter

Kathryn A Sontag

Roy David Fulayter

Michael George Glavicic

Matthew Jordan

A gas turbine engine comprises a primary fan and an engine core. The primary fan is mounted for rotation about an axis of the gas turbine engine to provide thrust. The engine core is coupled to the primary fan and configured to drive the primary fan about the axis to cause the fan to push air to provide thrust for the gas turbine engine.

Distributed electric and hybrid fans for distortion tolerance of turbofan engines

An aircraft includes a duct system configured to receive a flow of air therethrough and a gas turbine engine. The duct system includes a main duct and inlet ducts arranged fluidly upstream of the main duct so as to conduct the flow of air from the inlet ducts into the main duct. The gas turbine engine in downstream fluid communication with the main duct.

Multiple intake distortion adaptive fan for gas turbine engine

Distributed electric tip fans for distortion tolerance of turbofan engines

Methods for forming a blade for a gas turbine engine include altering the crystallographic texture of the blade in a discrete region relative to the surrounding locations of the blade to minimize flutter and/or mistune the blade by changing the natural frequency response of at least one mode of the blade.

Tailored material property tuning for turbine engine fan blades

A gas turbine engine comprises an engine core and an electric fan array. The engine core includes a compressor, a combustor, and a turbine. The compressor compresses and delivers air to the combustor. The combustor mixes fuel with the compressed air received from the compressor and ignites the fuel. The hot, high-pressure products of the combustion reaction in the combustor are directed into the turbine to cause the turbine to rotate about an axis and drive the compressor. The electric fan array may include at least two non-concentric fans having parallel shafts.

Electric fan array for distortion tolerance of turbofan engines

A gas turbine engine assembly includes a static component and a rotatable component configured to rotate about a central axis of the gas turbine engine assembly relative to the static component. The gas turbine engine assembly further includes a vibration-dampening system configured to dampen vibration of the gas turbine engine assembly.

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Indianapolis, IN, United States of America

Michael G Meyer