Rolls-royce North American Technologies Inc.

Rolls-royce Corporation

Rolls-royce Cornoration

Bryan H Lerg

Douglas J Snyder

Michael James Armstrong

Mark Jon Blackwelder

David Levi Sutterfield

Kenneth M Pesyna

Andrew Sanderson

Jack Dwane Petty, Sr

Victor Oechsle

Michael Karam

Todd S Taylor

Crawford F Smith, Iii

Andrew M Simonich

Stephen A Bergeron

Curtlan C Betchley

Steven T Berenyi

Kenneth William Froemming

Emil R Dejulio

Anthony F Pierluissi

Michael Moser

Christopher J Bies

Michael C Monzella

Justin N Moore

Nilesh Shah

Zachary A Rauch

Benjamin R Harding

Crawford Smith Iii

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

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

A variable exhaust nozzle for use with a gas turbine engine includes an outer shroud and an inner plug that can move relative to the outer shroud. The relative movement of the inner plug and the outer shroud changes the shape of the variable exhaust nozzle from one that converges in area to one that converges and then diverges in area.

Single movement convergent and convergent-divergent nozzle

A propulsion unit includes a gas turbine engine arranged along an axis and an exhaust system coupled to the gas turbine engine. The gas turbine engine includes an engine core configured to discharge a core flow and a fan configured to be driven by the engine core to discharge a bypass flow. The exhaust system receives the mixed bypass and core flows from the gas turbine engine.

Reconfigurable exhaust nozzle for a gas turbine engine

An exhaust nozzle for use with a gas turbine engine includes an outer shroud, an inner plug spaced radially apart from the outer shroud, and at least one support vane that is coupled to the outer shroud. The outer shroud and the inner plug cooperate to provide an exhaust nozzle flow path therebetween. The at least one support vane interconnects the outer shroud and the inner plug to support the inner plug in the exhaust nozzle flow path.

Exhaust nozzle having a compliant shell for a gas turbine engine

Exhaust nozzle with centerbody support structure for a gas turbine engine

Variable area nozzle exhaust system with integrated thrust reverser

An exhaust nozzle for use with a gas turbine engine includes an outer shroud and a nozzle-plug assembly coupled to the outer shroud. The nozzle-plug assembly includes an inner plug and at least one support vane that is coupled to the outer shroud to support the inner plug in an exhaust nozzle flow path.

Exhaust nozzle with vane support structure for a gas turbine engine

A variable exhaust nozzle for a gas turbine engine includes an outer shroud and an inner plug. The outer shroud is arranged circumferentially about an axis. The inner plug extends along the axis and is at least partially located within the outer shroud. At least one of the outer shroud and the inner plug are movable selectively to cause a variable area region of the variable exhaust nozzle to change.

Methodology for minimizing aerodynamic buzz in an exhaust nozzle

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

A particle separator adapted for use with a gas turbine engine includes an inner wall, an outer wall, and a splitter. The splitter cooperates with the inner wall 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-curvature 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

A gas turbine engine system is disclosed herein. The gas turbine engine system includes an engine core configured to discharge air through an exhaust nozzle along a central axis and a thrust director arranged near the exhaust nozzle and configured to redirect the discharge air by applying flow to the discharge air near the exhaust nozzle.

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Carmel, IN, United States of America

Bryan H Lerg