Rolls-royce North American Technologies Inc.

Rolls-royce Corporation

Rolls-royce High Temperature Composites Inc.

Andrew J Eifert

Ryan Charles Humes

Aaron D Sippel

David John Thomas

Daniel Kent Vetters

Peter Broadhead

Paulo Bazan

Jun Shi

Simon James Jones

Steven Hillier

Timothy Unton

Robert T Duge

Craig E Heathco

Paul Antony Davis

Jeffrey Allen Walston

Bruce Edward Varney

Robert Wayne Cedoz

Daniel G Edwards

Brian Thomas Spangler

Paul K Johnson

Michael Moser

Adrian Carl Sitler

Alexander Michalik

Richard Joseph Skertic

Roderick M Townes

Mark Jon Blackwelder

Richard Peace

Michael Karam

Eric E Wilson

Richard Andrew Young

Jack D Petty, Sr

Joseph Gordon Doyle

Russell E White

Michael Jacquinto

Wesley Thibault

Justin P Gilman

Kirk C Lefort

Oran Watts

David Thomas

Michael Abraham Karam

A vane assembly includes a casing, vanes, and an actuator assembly. The vanes are arranged within the casing and are rotatably coupled to the casing for rotation relative thereto and configured to rotate about their pitch axes. The actuator assembly is arranged radially outward of the casing and includes an annular ring surrounding the casing and coupled to the vanes, a magnet arranged on the ring, and a stator spaced apart from the magnet. The ring is configured to rotate the vanes about their pitch axes in response to rotation of the ring about the central axis and the stator is configured to selectively rotate the magnet and ring about the central axis. The stator is configured to create a magnetic field which causes annular movement of the ring via interaction with the magnet.

Variable stator vane assembly with magnetic actuation rotor for gas turbine engines

A vane assembly includes vanes, an actuator assembly, and a controller. The vanes are configured to rotate about their pitch axes. The actuator assembly includes an annular ring arranged radially outward of the vanes and coupled to the vanes, a magnet arranged on the annular ring, and a stator arranged adjacent the magnet. The ring is configured to rotate the vanes about the pitch axes in response to rotation of the ring about the central axis and the stator is configured to selectively rotate the magnet and annular ring about the central axis. The controller controls movement of the ring via the stator and magnets in response to at least one of (i) at least one operating condition of the gas turbine engine, or (ii) at least one operating parameter of the at least one first vane.

Stator vane control system with magnetic actuation rotor for gas turbine engines

A vane adjustment assembly includes a plurality of vanes, an annular ring coupled to the vanes, and a ring adjustment plate. The adjustment plate includes a main plate portion arranged on the ring and including a first adjustment region defined between two walls and a first elongated opening formed through the first adjustment region, and an adjustment fastener removably arranged in the first adjustment region between the first and second walls and including an adjustment head and a fastening pin eccentrically coupled to the adjustment head and removably coupled to the annular ring. The adjustment fastener can be selectively arranged at rotational positions within the first adjustment region so as to selectively arrange the fastening pin at distinct circumferential positions relative to the first and second walls such that the main plate portion can be positioned at distinct circumferential positions.

Systems and methods for multi-dimensional variable vane stage rigging utilizing adjustable bracket plates

A vane adjustment assembly includes a plurality of vanes, an annular ring coupled to the vanes, and a ring adjustment assembly. The ring adjustment assembly includes a base plate coupled to the ring and having a recess, a first collar removably arranged within the recess and having a cavity formed therein, a second collar removably arranged within the cavity, and a roller pin fixedly coupled to the second collar. The cavity is offset relative to the first collar and roller pin is offset relative to the second collar. The first collar can be selectively arranged at rotational positions within the recess and the second collar can be selectively arranged at rotational positions within the cavity such that the roller pin can be positioned at distinct positions each corresponding to a rotational position of the first collar and a rotational position of the second collar.

Systems and methods for multi-dimensional variable vane stage rigging

A vane adjustment assembly includes vanes, an annular ring coupled to the vanes, and a ring adjustment assembly. The adjustment assembly includes a base frame mounted on the ring and including a support body having a first cavity, a first collar removably arranged within the first cavity and having a second cavity formed therein, a second collar removably arranged within the second cavity, and a roller pin coupled to the second collar. The second cavity is offset relative to the first collar and the roller pin is offset relative to the second collar. The first and second collars can be selectively arranged at rotational positions within the first and second cavities such that the roller pin can be positioned at distinct roller pin positions each corresponding to a rotational position of the first collar and a rotational position of the second collar.

Systems and methods for multi-dimensional variable vane stage rigging utilizing coupling mechanisms

A bleed air control system is configured to vary the air pressure at the inlet of a gas turbine engine. The bleed air control system includes a first gas turbine engine configured to provide bleed air, a second gas turbine engine acting as an auxiliary power unit, and a bleed air control system configured to selectively provide bleed air from the first gas turbine engine to the second gas turbine engine.

Gas turbine engine system with mixed flow auxiliary power unit

A vane adjustment assembly includes a plurality of vanes, an annular ring coupled to the vanes, and a ring adjustment assembly. The ring adjustment assembly includes a first inclined plate and a second inclined plate, the first inclined plate having an inclined surface facing a first inclined surface of the second inclined plate. A roller pin is coupled to a second inclined surface of the second inclined plate opposite the first inclined surface. The second inclined plate is adjustable in the circumferential direction such that the inclined surface of the first inclined plate and the first inclined surface of the second inclined plate slide against each other during adjustment of the second inclined plate so as to adjust an axial position and a circumferential position of the roller pin relative to the annular ring.

Systems and methods for multi-dimensional variable vane stage rigging utilizing adjustable inclined mechanisms

A power-generation system for a nuclear reactor includes a power unit, a reactor heat exchanger, and an auxiliary combustion system. The power unit produces compressed air that is heated by the reactor heat exchanger. The auxiliary combustion system includes an auxiliary combustor located external to the power unit and fluidly connected with the compressed air to increase the temperature of the compressed air.

Engine system with fuel-drive thermal support

A vane adjustment assembly includes a plurality of vanes, an annular ring coupled to the vanes, and a ring adjustment assembly. The ring adjustment assembly includes a shim plate having a first shim surface removably arranged on an axially facing surface of the annular ring, a carrier plate having a first carrier surface removably arranged on a second shim surface of the shim plate opposite the first shim surface, and a roller pin coupled to a second carrier surface of the carrier plate opposite the first carrier surface. The shim plate is sized so as to locate the roller pin at a predetermined distance from the annular ring so as to adjust a position of the plurality of variable vanes relative to the roller pin.

Systems and methods for multi-dimensional variable vane stage rigging utilizing adjustable alignment mechanisms

A propulsion system includes two gas turbine engines and an air-provisioning system. The air-provisioning system includes a first ejector, a second ejector, a plenum fluidically connected with the first ejector and the second ejector, and a first propulsor. The air-provisioning system is configured to bleed and mix air from each gas turbine engine in the ejectors so as to provide selectively a flow of plenum air from the plenum to the first propulsor at a desired pressure and a desired flow rate to power the first propulsor.

Air-provisioning system with ejectors

A power-generation system for a nuclear reactor includes a power unit, a heat exchanger, and a temperature control system. The power unit produces compressed air that is heated by the nuclear reactor via the heat exchanger. The temperature control system includes a heat transfer fluid and a heat exchanger fluidly connected with the compressed air to transfer heat between the compressed air and heat transfer fluid to control the power level of the power unit.

System for control of externally heated turbine engine

A compressor adapted for use in a gas turbine engine includes an impeller, a diffuser, and a deswirler. The impeller is arranged circumferentially about an axis and configured to rotate about the axis. The diffuser is arranged circumferentially around the impeller to receive the air from the impeller. The deswirler is configured to receive the air from the diffuser and to conduct the air into a combustion chamber.

Centrifical compressor assembly for a gas turbine engine

A power generation system for a nuclear reactor includes an externally-heated turbine engine, a reactor heat exchanger, and a heat recuperating system. The externally-heated turbine engine produces compressed air that is heated by the reactor heat exchanger. The heat recuperating system includes a heat exchanger thermally connected to the externally-heated turbine engine to transfer heat to the compressed air to supplement the reactor heat exchanger.

System for startup support of externally heated turbine engine

A blade track for a gas turbine engine includes a plurality of blade track segments. The blade track segments are arranged circumferentially around a central axis to form the blade track.

Keystoned blade track

A blade track for a gas turbine engine includes segments and joints that couple the segments together. Each segment extends part-way around a central axis of the engine and the joints couple together adjacent segments to form a full hoop.

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Indianapolis, IN, United States of America

Andrew J Eifert