Rolls-royce North American Technologies Inc.

Rolls-royce Corporation

Nicholas Metzger

Kenneth M Pesyna

Timothy Roesler

Todd S Taylor

Daniel G Edwards

Behram Kapadia

Joseph Clegg

Craig English

Jason Lee Swindle

Jason Wayne Rector

Christopher Vincent

A dual flow path exhaust assembly for use with a combined turbofan and ramjet engine includes a turbofan engine exhaust duct, a ramjet engine exhaust duct, a combined outlet, and door configured to move between an open position and a closed position to selectively isolate the turbofan engine exhaust duct from the combined outlet.

Dual flowpath exhaust for fuel cooling in a hypersonic propulsion system

Pressure equalization in a dual flow path exhaust of a hypersonic propulsion system

A hybrid propulsion system and methods for cooling the same are provided. The system may comprise a gas turbine and a secondary engine. The gas turbine engine may have a core passage and an engine compartment. The secondary engine may be a supersonic and/or hypersonic engine. The system may comprise a thermal barrier, an inlet and an exhaust. The thermal barrier may longitudinally envelope the gas turbine engine. The thermal barrier may comprise an inner envelope, an outer envelope, an upstream opening, and a downstream opening. The inlet may be in fluid communication with the ambient environment and the gas turbine engine via the upstream opening. The exhaust may be in fluid communication with the ambient environment and the gas turbine engine via the downstream opening. The engine compartment may be located between a boundary of the core passage and the inner envelope.

Isolated turbine engine cooling

A cooling system for a gas turbine is provided that may include a drive shaft, a shield of a combustor of the gas turbine engine, and a conduit. The drive shaft may be configured to mechanically couple a compressor of the gas turbine engine to a turbine of the gas turbine engine. The shield may be positioned between the compressor and the turbine. The combustor may be configured to drive the turbine. The conduit may be configured to supply a cooling fluid to a gap between an outer surface of the drive shaft and the shield of the combustor.

Turbine engine advanced cooling system

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Fishers, IN, United States of America

Nicholas Metzger