Rolls-royce North American Technologies Inc.

Rolls-royce Corporation

Kenneth M Pesyna

Bryan H Lerg

Andrew M Simonich

Douglas J Snyder

Anthony F Pierluissi

Victor Oechsle

Nicholas Metzger

James Carl Loebig

Michael Karam

Timothy Roesler

Jack D Petty, Sr

Todd S Taylor

Steven T Berenyi

Curtlan C Betchley

Colin Faucett

Robert Anthony Ress, Jr

Rigoberto Jorge Rodriguez

Patrick C Sweeney

Von David Baker

Steven Gagne

Tab Michael Heffernan

Jeffrey P Henkle

William J Lewis

Crawford F Smith, Iii

Kenneth William Froemming

Daniel G Edwards

Joseph Clegg

Behram Kapadia

Philip Burkholder

Craig English

Michael Moser

Jason Lee Swindle

Michael C Monzella

Christopher Vincent

Zachary A Rauch

Nilesh Shah

Jason Wayne Rector

Justin N Moore

Crawford Smith Iii

Jr Robert A Ress

Tab M Heffernan

A propulsion unit includes a gas turbine engine and an exhaust nozzle coupled to an aft end of the gas turbine engine. The exhaust nozzle is configured to interact with exhaust gases exiting the gas turbine engine in an aft direction. The exhaust nozzle includes an outer nozzle case and an inner plug that cooperate to define an exhaust flow path therebetween. The exhaust nozzle is configured to manipulate the exhaust gases to provide different thrust capabilities for the gas turbine engine. The exhaust nozzle includes a thrust reverser configured to be retained by the inner plug.

Plug nozzle and thrust reverser for high mach gas turbine engines

An infrared suppressor adapted for use with a gas turbine engine includes a first ring arranged circumferentially around a axis, a second ring arranged circumferentially around the axis, and a strut that extends radially between and interconnects the first ring and the second ring. A portion of the second ring extends radially toward the first ring such that the portion of the second ring cooperates with the first ring to block line-of-sight into the infrared suppressor.

Compact infrared suppressors with ring vanes for gas turbine engines

A propulsion unit includes a gas turbine engine and an exhaust nozzle coupled to an aft end of the gas turbine engine. The exhaust nozzle is configured to interact with exhaust gases exiting the gas turbine engine in an aft direction. The exhaust nozzle includes an outer nozzle case and an inner plug that cooperate to define an exhaust flow path therebetween. The exhaust nozzle is configured to manipulate the exhaust gases to provide different thrust capabilities for the gas turbine engine.

An infrared suppressor adapted for use with a gas turbine engine includes a first ring arranged circumferentially around a central axis, a second ring arranged circumferentially around the central axis, and a strut that extends radially between and interconnects the first ring and the second ring. A portion of the second ring extends radially toward the first ring such that the portion of the second ring cooperates with the first ring to block line-of-sight into the infrared suppressor.

A gas turbine engine includes a bypass duct and a rotating detonation augmentor. The bypass duct is configured to conduct air through a flow path arranged around an engine core of the gas turbine engine to provide thrust for propelling the gas turbine engine. The rotating detonation augmentor is located in the bypass duct and configured to be selectively operated to detonate fuel and a portion of the air to increase the thrust for propelling the gas turbine engine.

Rotating detonation augmentors with adjustable throats for gas turbine engines

Plug nozzle for high mach gas turbine engines

Method of manufacture of plug nozzle with thrust reverser

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

Devices, systems, and methods of a casing for a heat suppression system of a gas turbine engine exhaust include a heat shield and an insulation layer for arrangement between the heat shield and an outer skin.

Heat shield for signature suppression system

A particle separator adapted for use with a gas turbine engine includes an adaptive-area hub, an outer wall, and a splitter. The splitter cooperates with the adaptive-area hub and the outer wall to separate particles suspended in an inlet flow moving through the particle separator to provide a clean flow of air to the gas turbine engine.

Adaptive-area inertial particle separators

An integrated aircraft cooling system comprising a turbine engine and a plurality of secondary cooling streams, wherein the turbine engine core exhaust stream drives the plurality of secondary cooling streams. A core exhaust stream outlet has a periphery and a composite secondary outlet positioned around the periphery of the core exhaust stream outlet, and the composite secondary outlet is segregated between the plurality of secondary streams. Each of the secondary flows are in fluid isolation from each other upstream of the composite secondary outlet.

Integrated aircraft cooling system

According to one aspect, a system for alignment of vanes to suppress infrared detection in a gas turbine engine is provided. The system includes a first vane disposed on a first component, and a second vane disposed on a second component. The second vane is configured to engage the first vane such that the second component is capable of being positioned proximal to the first component.

Infrared suppression system in a gas turbine engine

A propulsion system including a gas turbine engine is disclosed herein. The propulsion system further includes a heat exchanger arranged outside the gas turbine engine and adapted to cool fluid from the gas turbine engine.

Heat exchanger for a gas turbine engine propulsion system

According to one aspect, an infrared suppression system that utilizes a primary airflow and a secondary air flow for a gas turbine engine is provided. The infrared suppression system includes an exit flap configured to control a flow of exhaust air out of the gas turbine engine and a secondary flow door that is configured to selectively control the secondary air flow into the gas turbine engine. The mixture of the secondary air flow and the primary air flow from the gas turbine engine suppresses an infrared signature produced by the gas turbine engine.

Variable infrared suppression system in a gas turbine engine

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Carmel, IN, United States of America

Kenneth M Pesyna