Raytheon Technologies Corporation

Sean Danby

Daniel Bernard Kupratis

Christopher J Hanlon

Walter A Ledwith

William F Schneider

Robert H Bush

Benjamin Bellows

A gas turbine engine includes a core flowpath for flowing a core stream, a second flowpath located radially outward from the core flowpath for flowing a second stream, and an auxiliary flowpath located radially outward from the second flowpath for flowing an auxiliary stream. A heat exchanging device is constructed and arranged to divert a portion of the second stream into the auxiliary flowpath. A turbine exhaust case is constructed and arranged to flow the auxiliary stream into the core flowpath for mixing with the core stream.

Gas turbine engine and an airflow control system

A gas turbine engine includes a turbine section that is configured to drive a fan through a fan shaft. The fan includes a plurality of fan blades rotatable about an axis of rotation of the gas turbine engine. A fan nacelle includes a first electrical machine component. The fan is located within the fan nacelle. A plurality of fan inlet guide vanes includes a second electrical machine component. The plurality of fan inlet guide vanes are rotatable about the axis.

Turbofan with motorized rotating inlet guide vane

Growing community of inventors

East Hampton, CT, United States of America

Sean Danby