Rolls-Royce North American Technologies Inc.

Rolls-Royce Corporation

Randall E Yount

Robert Anthony Ress, Jr

David Levi Sutterfield

Charles B Graves

Charles Bryce Graves

Todd S Taylor

Victor Oechsle

Kaare Erickson

Stephen A Bergeron

Thomas D Destefano

Afework Woubshet

Jitendra R Patel

Mindi D Moore

Marcus Timothy Holcomb

Robert A Ress

An improved system, apparatus and method may comprise an inner liner and an outer liner extending circumferentially around an engine centerline axis thereby forming a combustion chamber therebetween. The system, apparatus, and method may include a front end extending between the inner and outer liners and having a plurality of fuel nozzle ports configured to each receive a fuel nozzle. First and second outer plunged inlet holes may be formed in the outer liner and extending in a first radial direction toward the engine centerline axis and into at least a portion of the combustion chamber. First and second inner plunged inlet holes may be formed in the inner liner and extending in a second radial direction away from the engine centerline axis and into at least a portion of the combustion chamber.

Counter-swirl doublet combustor with plunged holes

A nozzle support system for a nozzle of a gas turbine includes an outer ring, an inner ring disposed within the outer ring, and a plurality of links pivotally attaching the outer ring to the inner ring. Each one of the links may have an outer end that is pivotally attached to the outer ring, and each one of the links may have an inner end that is pivotally attached to the inner ring, such that the inner ring moves along a longitudinal axis of the outer ring.

Nozzle support system

A system for removing oxygen from a fuel is provided including a pressurized gas lumen and a liquid transport lumen having a fuel separation device. The liquid transport lumen is positioned partially within the pressurized gas lumen and includes a plurality of openings formed along its length within said pressurized gas lumen. A shearing feature is formed within the liquid transport lumen and is positioned downstream of the openings and upstream of the fuel separation device. The gas enters the liquid transport lumens through the openings to form a plurality of bubbles removing oxygen from the fuel. The shearing feature collapses the bubbles into larger bubbles prior to flow into the fuel separation device.

Liquid flow with gas mixing

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

One embodiment of the present invention is a gas turbine engine with a bypass mixer. Other embodiments include apparatuses, systems, devices, hardware, methods, and combinations for gas turbine engines and bypass mixers. Further embodiments, forms, features, aspects, benefits, and advantages of the present application will become apparent from the description and figures provided herewith.

Gas turbine engine with bypass mixer

A combustor liner for a turbine engine is disclosed herein. The combustor liner includes an inner liner surface operable to define at least part of a combustion chamber in a turbine engine. The inner liner surface extends along a portion of a chordal arc on a first side of the chordal arc. The combustor liner also includes a bearing surface operable to support a floating dome panel. At least part of the bearing surface is spaced from the chordal arc on a second side of the chordal arc opposite the first side.

Combustor liner

One embodiment of the present invention is an integrated aero-engine flowpath structure. Another embodiment is a method of manufacturing integrated aero-engine flowpath structure. Other embodiments include apparatuses, systems, devices, hardware, methods, and combinations for aero-engine flowpath structures. Further embodiments, forms, features, aspects, benefits, and advantages of the present application shall become apparent from the description and figures provided herewith.

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Indianapolis, IN, United States of America

Randall E Yount