Rolls-royce North American Technologies Inc.

Rolls-royce Corporation

Other

Rolls-royce Cornoration

David Levi Sutterfield

Bryan H Lerg

Andrew Sanderson

Jack Dwane Petty, Sr

Todd S Taylor

Gregory W Zeaton

Mark O'Leary

Von David Baker

Randall E Yount

Anthony F Pierluissi

Aric Acius

Jagdish Singh Sokhey

Christopher J Bies

William J Dionne

Gregory Wp Zeaton

Gregory W P Zeaton

Sean F Sullivan

A vane assembly includes an outer case, a plurality of vanes, and an inner body assembly. The outer case defines an outer boundary of a flow path of the vane assembly. The plurality of vanes extend radially inward from the outer case relative to a central axis. The inner body assembly is configured to secure the plurality of vanes radially relative to the central axis. The inner body assembly includes an inner case arranged circumferentially about the central axis, a band coupled with the inner case, and a retainer ring that extends into the band and into each of the plurality of vanes.

Retainer rings for vane assemblies used in 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

Various embodiments of the present disclosure provide an aircraft anti-icing system that includes an aircraft engine inlet component, a pressurized air source, and a heat source operable to: (1) heat the leading edge of the aircraft engine inlet component via the heat source to prevent ice formation on the outer surface of the leading edge; and (2) direct pressurized air from the pressurized air source so that it forces water off of the outer surface of the inlet components (and into the external air flow) as the water travels downstream from the leading edge outer surface downstream toward the trailing edge, which prevents runback ice formation.

Aircraft anti-icing 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.

Coanda device for a round exhaust nozzle

A sealing assembly may include a support, an engine component, and a seal. The engine component may be mounted relative to the support to define a gap between the engine component and the support. The seal may be arranged between the support and the engine component to block gasses from passing through the gap. The seal may be adapted to compress and expand to fill the gap during expansion and contraction of the adjacent components that occurs during operation of a gas turbine engine including the sealing assembly.

Seals for a gas turbine engine

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

An exemplary fuel spray bar system can include a conduit, which is pivotally attached to an engine frame and configured to deliver fuel from a fuel line to an engine flow path. The system further includes a drive mechanism, which is configured to move the conduit between a stowed position and a deployed position.

Growing community of inventors

Greenwood, IN, United States of America

David Levi Sutterfield