Rolls-royce North American Technologies Inc.

Rolls-royce Corporation

Rolls-royce High Temperature Composites Inc.

Allison Advanced Development Company

Other

Rolls-royce American Technologies, Inc.

Douglas David Dierksmeier

Daniel Kent Vetters

Edward Claude Rice

David John Thomas

Jun Shi

Ryan Charles Humes

Todd Engel

Ted Joseph Freeman

Michael Karam

Tab Michael Heffernan

Matthew T Kush

Timothy Fuesting

Michael D Wood

Donald Klemen

Douglas J Snyder

Jeffrey F Rhodes

Joseph P Lamusga

James Christopher Muskat

Patrick C Sweeney

William Barry Bryan

Graham Burkholder

David C Farnum

Bradley Eugene Auker

Douglas Boyd

Steven Wesley Tomlinson

Rick Uskert

Matt Brandt

Ben Moloney

Okey Kwon

Steven Lester Grant

Jeffrey A Ruppel

Shi Jun

Todd Z Engel

A radial turbine rotor incorporating ceramic matrix composite turbine blades is disclosed. The radial turbine rotor can include a dovetail shape retention features for coupling the ceramic matrix composite turbine blades to a central hub.

Radial turbine assembly with ceramic matrix composite airfoils having dovetail retention

A multi-piece radial turbine rotor includes a hub, turbine blades, and an intermediate ring that couples the turbine blades to the hub. Joints between the components of the rotor are adapted for inspection during manufacture to identify potential defects in the joints.

Radial turbine assembly with intermediate blade bonding ring

A multi-piece radial turbine rotor includes a hub, turbine blades, and a flowpath ring that couples the turbine blades to the hub. Joints between the components of the rotor are adapted for inspection during manufacture to identify potential defects in the joints.

Multi-piece radial turbine rotor

A turbine wheel for a gas turbine engine including a compressor impeller and a radial inflow turbine integral to or attached to the compressor impeller is provided. A compressor turbine wheel including features to increase surface area of a surface of the compressor impeller and/or the radial inflow turbine and/or a passage to flow air between the compressor impeller and the radial inflow turbine is further provided. Methods for cooling radial inflow turbines integral to compressor impellers are further provided.

Compressor turbine wheel

A gas turbine engine includes a centrifugal compressor, a combustor, a radial turbine, and a cooling air metering system. The centrifugal compressor is configured to rotate about an axis to produce compressed air. The combustor is fluidly connected downstream of the centrifugal compressor to receive the compressed air from the centrifugal compressor. The radial turbine is fluidly connected with the combustor and is axially spaced apart from the centrifugal compressor. The cooling air metering system is configured to selectively block or allow a portion of the compressed air flowing radially between the centrifugal compressor and the radial turbine, bypassing the combustor, and through a heat exchanger for cooling the radial turbine and other components.

Gas turbine engine with radial turbine having modulated fuel cooled cooling air

A propulsor includes an electric motor, a fan unit, and a thrust system positioned downstream of and coupled to the fan unit. The electric motor converts electrical power to mechanical rotation to rotationally drive the fan unit and create an air stream directed towards the thrust control system.

Aircraft with electric propulsor

A system includes a housing for a gas turbine engine, and a fan disposed in the housing to rotate coaxially with a gas turbine included in the housing. The system also includes an inlet guide vane disposed in the housing in axial alignment with the fan and configured to have an open position where a first flow of air is received by the fan through the inlet guide vane, and a closed position where airflow through the inlet guide vane is obstructed. The system further includes a heat exchanger disposed in a supply passage in fluid communication with a second flow of air received by the fan. The second flow of air is received by the fan via the supply passage with the inlet guide vane in the open position or in the closed position.

Inlet guide vane draw heat exchanger system

A gas turbine engine system includes a gas turbine engine having a fan bypass duct, a heat exchanger system, and a flow transfer unit configured to selectively allow or preclude flow between the fan bypass duct and the heat exchanger system. A controller is coupled to and configured to vary the state of one or more of a fan exit nozzle, a heat exchanger exit nozzle, and a flow control valve controlling flow between the fan bypass duct and the heat exchanger system.

Gas turbine engine with reversible heat exchanger

A door panel is included in a nacelle assembly for use with a gas turbine engine to block and allow access selectively to the gas turbine engine. The nacelle assembly includes a nacelle wall, a sleeve, and the door panel. The nacelle wall is arranged at least partway around the gas turbine engine and formed to define an opening that extends through the nacelle wall. The door panel is located in the opening and movable relative to the nacelle wall. The sleeve is coupled with one of the nacelle wall and the door panel and configured to move relative to the nacelle wall or the door panel toward and away from the other of the nacelle wall and door panel to adjust a size of a gap between the door panel and the nacelle wall.

Adjustable door seal

A gas turbine engine includes an engine core, a propulsion unit, and a particle separator. The engine core is configured to combust fuel and air to drive rotation of the propulsion unit. The propulsion unit is driven to rotate by the engine core to provide thrust for the gas turbine engine. The particle separator is configured to separate unwanted particles from air being directed toward the engine core.

Inlet particle separator

A gas turbine engine includes an engine unit and an inlet. The engine unit includes an engine core that includes a compressor, a combustor, and a turbine and a nacelle arranged circumferentially around at least a portion of the engine core. The inlet is removably coupled with the nacelle and configured to conduct fluid into the engine unit. The inlet includes a nose and an intake lip arranged circumferentially around the nose to define an intake passage that extends through the inlet.

Gas turbine engine with mount for interchangeable inlets

An air seal for a jet turbine engine with an upper stator, lower stator and finned turbine disk. The thermal expansion of the stators may be regulated by a control ring, which has a lower rate of thermal expansion that the stators, to prevent rubbing between the stator and fins.

Reduced leakage air seal

An assembly is disclosed for adjusting the radial position of one or more blade tracks radially encasing the blades of a turbine stage in a gas turbine engine. The assembly comprises a static turbine casing, a plurality of blade track carriers, an annular control ring, an actuator, and a plurality of blade tracks. The blade tracks have a radially inner surface that defines a flowpath boundary of the turbine stage. The blade tracks are carried by the blade track carriers, which are engaged with the annular control ring. Actuation of the actuator moves the control ring in an axial dimension and this movement is translated into an adjustment of the radial position of the blade track.

Blade tip clearance assembly

A shroud for radially encasing a turbine in a gas turbine engine is provided. The shroud comprises a carrier which defines a pin-receiving carrier bore, and a ceramic matrix composite (CMC) seal segment comprising an arcuate flange with a surface facing the turbine and a part that defines a pin-receiving seal segment bore. The seal segment bore is radially spaced from the arcuate flange by a spacing flange which extends radially outward from the arcuate flange to effect receipt within the seal segment bore of an elongated pin. The elongated pin extends through the carrier bore and the seal segment bore, and the elongated pin has a lateral cross-sectional dimension of at least three-eighths of an inch.

Shroud cartridge having a ceramic matrix composite seal segment

An assembly is disclosed for adjusting the radial position of a blade track relative to a blade of a turbine stage in a gas turbine engine. The assembly comprises a static turbine casing, a blade track carrier, a blade track support assembly, an actuator, and a blade track. The blade track carrier comprises a pair of radially extending flanges each defining at least one bore in radial and axial alignment with each other forming a pair of bores. The blade track support assembly comprises a portion extending through each bore in a pair of bores, and one or more cam-shaped portions rotatable about an axis of rotation. The blade track has an arcuate flange and a support flange, the support flange being carried by the cam-shaped portion of the blade track support assembly such that rotation of the cam-shaped portion effects radial movement of the blade track.

Growing community of inventors

Franklin, IN, United States of America

Douglas David Dierksmeier