Rolls-royce Corporation

Rolls-royce North American Technologies Inc.

Gm Global Technolgoy Operations, Inc.

Allison Advanced Development Company

Rolls-royce Cornoration

Jack Dwane Petty, Sr

Daniel Kent Vetters

Bryan H Lerg

David Levi Sutterfield

Andrew Sanderson

Bruce Edward Varney

Todd S Taylor

Eugene Clemens

Ted Joseph Freeman

Aaron D Sippel

Kenneth William Froemming

Gregory W Zeaton

Edward Claude Rice

Michel Shawn Smallwood

Philip Michael Bastnagel

Vickie Rae Smiley

Mark A Herbertz

A combustor for a gas turbine engine includes a combustor shell, a burner seal, and a burner seal retainer. The combustor shell includes metallic materials and is formed to define an interior combustion space. The burner seal includes ceramic matrix composite materials and is configured to extend through apertures formed in the combustor shell and the heat shield. The burner seal retainer is configured to retain the burner seal to the combustor shell.

Combustor for a gas turbine engine with ceramic matrix composite sealing element

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 combustor adapted for use in a gas turbine engine includes a metallic combustor shell forming an interior space, a heat shield, and a liner arranged in the interior space of the metallic case. The liner defines a combustion chamber in which fuel is burned during operation of a gas turbine engine.

Combustor liner for a gas turbine engine with ceramic matrix composite components

A seal assembly can accommodate deflection between two components through a cartridge that is slidingly engaged with a slide plate.

Deflection seal system

A gas turbine engine includes a turbine having a plurality of vanes, a plurality of blades, a turbine shroud arranged around the vanes and blades, and a turbine case arranged around the turbine shroud. The turbine shroud is sized to block combustion products from passing over the blades without pushing the blades to rotate. The turbine shroud includes a runner arranged around the blades and a carrier arranged around the runner.

Gas turbine engine with health monitoring system

A turbine shroud for use in a gas turbine engine includes a carrier, a blade track segment, and a load-distribution system. The carrier is arranged around a central axis of the turbine shroud. The blade track segment is configured to be supported by the carrier. The load-distribution system is positioned between the carrier and the blade track segment to distribute loads transmitted between the carrier and the blade track segment.

Gas turbine engine with compliant layer for turbine shroud mounts

A turbine vane assembly for use in a gas turbine engine includes an endwall, a flow path component, and a load-distribution system. The endwall is arranged around a central axis of the turbine vane assembly. The flow path component is configured to direct fluid flow through the turbine vane assembly. The load-distribution system is positioned between the endwall and the flow path component to distribute loads transmitted between the endwall and the flow path component.

Gas turbine engine with compliant layer for turbine vane assemblies

Turbine shroud with mounted full hoop blade track

Full hoop blade track with interstage cooling air

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

The present invention relates to combustors, and provides a combustion liner that may at least partially contain a combustion process. The combustion liner may include a support structure that supports a plurality of panels. The panels may be in the form of thermal barrier panels, e.g., that are attached to the support structure and/or other parts of the machine.

Growing community of inventors

Indianapolis, IN, United States of America

Jack Dwane Petty, Sr