Rolls-royce North American Technologies Inc.

Rolls-royce Corporation

Victor Oechsle

Kenneth M Pesyna

Bryan H Lerg

Andrew M Simonich

Curtlan C Betchley

Steven T Berenyi

Robert Anthony Ress, Jr

Philip Harold Snyder

Crawford F Smith, Iii

Randall E Yount

Michael Moser

Stephen A Bergeron

Michael C Monzella

Zachary A Rauch

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

An air-inlet duct includes an outer wall, an inner wall, and a splitter. The splitter cooperates with the outer wall and the inner wall to establish a particle separator which separates particles entrained in an inlet flow moving through the air-inlet duct to provide a clean flow of air to a compressor section of a gas turbine engine.

Particle separator

A gas turbine engine having a ramburner is disclosed. The ramburner is disposed downstream of a gas turbine engine combustor and receives an engine exhaust flow from the gas turbine engine combustor. The ramburner also accepts a bypass air. Fuel is injected into the ramburner and a combustion reaction is auto-initiated based upon local gas temperatures. No mechanical flame holders need be used. A slidable valve may be used to vary the amount of bypass air into the ramburner. A movable cowl and a plug nozzle form an exit flow path of the gas turbine engine. The movable cowl can be positioned to vary a throat area and exit area of the gas turbine engine based upon the operation of the ramburner, which may be influenced by the amount of bypass air entering the ramburner.

Combustor added to a gas turbine engine to increase thrust

The present invention provides in one embodiment a unique gas turbine engine. Another embodiment is a unique gas turbine engine combustion system. Still another embodiment is a unique gas turbine engine combustor. Other embodiments include apparatuses, systems, devices, hardware, methods, and combinations for gas turbine engines and gas turbine engine combustion systems and combustors.

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Avon, IN, United States of America

Victor Oechsle