Rolls-royce North American Technologies Inc.

Rolls-royce Corporation

Rolls-royce Cornoration

Todd S Taylor

Jack Dwane Petty, Sr

Bruce Edward Varney

Kenneth M Pesyna

Bryan H Lerg

James Carl Loebig

David Levi Sutterfield

Timothy Roesler

Kenneth William Froemming

Andrew Sanderson

Nicholas Metzger

Eric Sean Donovan

James Christopher Muskat

Jack D Petty, Sr

Randall E Yount

Donald E Pinnick

Mike Nesteroff

Sujit Nanda

Brad Farris

Marcus Timothy Holcomb

Vickie Rae Smiley

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

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

Variable area nozzle exhaust system with integrated thrust reverser

Systems and methods for suppressing infrared radiation generated by a turbine engine. A system comprises a primary assembly having a center body, a plurality of vanes extending from the center body, an outer radial duct with the plurality of vanes extending therethrough, a structural baffle, and a mixer. The primary assembly is disposed in the exhaust flow path of a turbine engine and encased in ducting and/or an airfoil. An air flow path defined between the center body and outer radial duct is axially spit by an interface rim and flow segregator. The flow segregator segregates engine core flow from ambient air flow.

Flow segregator for infrared exhaust suppressor

A combustor for use in a gas turbine engine includes a chute and a combustion liner defining a combustion chamber and a chute-receiving aperture that extends through the combustion liner. The chute extends through the chute-receiving aperture of the combustion liner and defines a passageway sized to convey air from an environment outside the combustion chamber through the combustion liner into the combustion chamber.

Combustor assembly with chutes

A gas turbine engine variable porosity combustor liner has a laminated alloy structure. The laminated alloy structure has combustion chamber facing holes on one side and cooling plenum facing holes on a radially opposite side. The combustion chamber facing holes are in fluid communication with the cooling plenum facing holes via axially and circumferentially extending flow passages sandwiched between metal alloy sheets of the laminated alloy structure. Porous zones having respective different cooling flow amounts are formed in the laminated allow structure based on at least one of an arrangement of the combustion chamber facing holes, an arrangement of the cooling plenum facing holes, and an arrangement of the flow passages.

Gas turbine engine with improved combustion liner

A gas turbine engine is disclosed having a compressor, combustor, and turbine and a flow path therethrough. A flow path member is disposed between an inner surface of the flow path and a rotating shaft that couples the compressor and turbine. The flow path member directs a cooling fluid along a path to cool a portion of the gas turbine engine between the inner surface and the rotating shaft. The flow path member is retained to permit radially free motion and can also be retained to permit axially free motion. The flow path member can have feed holes that permit the cooling fluid to pass.

Gas turbine engine flow path member

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

The invention is a combination that includes a gas turbine engine extending along an axis. The gas turbine engine includes an annular combustor with a combustor liner. The combination of the invention also includes a plurality of projections extending from the combustor liner and spaced from one another circumferentially about the axis. The combination of the invention also includes a free-standing ring disposed about the combustor liner and positioned adjacent to the plurality of projections along the axis. The plurality of projections engage a corresponding circumferentially-facing portion of the free-standing ring and circumferentially support the combustor liner while allowing relative radial displacement between the combustor liner and the free-standing ring. The combination of the invention also includes a rolling assembly operably disposed between the free-standing ring and the plurality of projections to reduce binding during the relative radial displacement.

Combustor liner support and seal assembly

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Bargersville, IN, United States of America

Todd S Taylor