Rtx Corporation

United Technologies Corporation

Raytheon Technologies Corporation

Rohr, Inc.

Marc J Muldoon

Joseph Brent Staubach

Michael E McCune

Russell B Witlicki

Jesse M Chandler

Neil J Terwilliger

Gabriel L Suciu

Charles E Lents

Gregory E Reinhardt

Matthew R Feulner

James F Wiedenhoefer

Meggan Harris

John P Virtue

Stephen G Pixton

Jonathan Rheaume

John R Farris

Robert E Malecki

Hung Duong

David Allen Stachowiak

William G Sheridan

Michael G McCaffrey

Thomas E Clark

William K Ackermann

Jon E Sobanski

Francis Parnin

James B Coffin

Lance L Smith

Michael D Greenberg

Ulf J Jonsson

Om Parkash Sharma

Robert H Dold

Joseph H Polly

Brian M Holley

Robert T Brooks

Tor W Sherwood

Alessio Pescosolido

Nicholas D Leque

Eric Charles Mundell

Jason B Solomonides

Bradley C Schafer

Nathan D Korn

Murat Yazici

Brian V Winebrenner

Keith B Allyn

Xinwen Xiao

Andrew J Murphy

Nancy Poisson

Arnab Roy

Andrew Hahn

Gary L Grogg

Andreas Sadil

Martin Richard Amari

Stephen H Taylor

David Lei Ma

Daniel Benjamin

Todd M LaPierre

Gregory M Savela

Masayoshi Sonokawa

Grace E Szymanski

Daniel R Kapszukiewicz

Brian C Lund

Brian A Sherman

Christopher J Larson

Robert C Stutz

Carroll V Sidwell

Stephanie M Baker

Bessem Jlidi

William J Beeson

Michael E Mccune

Stephen J Lyle

Lyubov Y Belko

Meggan H Harris-Miller

Melissa B Chapin

Eric C Mundell

Meggan H Harris

A cryogenic fueled aircraft propulsion maintenance system includes a fuel system of an aircraft, the fuel system includes a cryogenic fuel tank that is configured to maintain the fuel in a liquid phase during aircraft operating conditions, a gas collection system where boil off gas from the fuel system is collected, and a fuel reliquification system that is configured to receive boil off gas from the gas collection system and transform the boil off gas into a liquid phase as liquid fuel.

Collection of boil off gas at airport gate

An assembly is provided for an aircraft propulsion system. This aircraft propulsion system assembly includes an electric machine, a rotating structure, a geartrain, a propulsion system component and a lubrication system. The electric machine includes a machine volume and a machine rotor. The rotating structure includes a bladed rotor. The geartrain couples the machine rotor to the rotating structure. The geartrain includes a geartrain volume. The propulsion system component is arranged with the rotating structure. The propulsion system component includes a component volume. The lubrication system includes a lubricant circuit and a lubricant source configured to direct lubricant through the lubricant circuit. The lubricant circuit includes the machine volume, the geartrain volume and the component volume.

Lubrication system for aircraft propulsion system with electric machine

A system includes a substrate and an electrical component mounted to the substrate. The system also includes a structural enclosure positioned around lateral edges of the electrical component and mounted to the substrate. The structural enclosure includes raised walls extending away from the substrate and surrounding the electrical component. The raised walls are configured to block foreign object debris from the electrical component. The system further includes a lid connected to the substrate, where the lid covers the electrical component and the structural enclosure. The system also includes a seal positioned between the structural enclosure and the lid, where the seal is configured to be compressed when the lid is connected to the substrate. In addition, the system includes a thermal interface material positioned between and contacting the electrical component and the lid.

Multi-stage partial admission axial turbine

A gas turbine engine and engine mount structure includes a core engine including a compressor section, a combustor section and a turbine section mounted within a core engine housing. The fan, the compressor section and the turbine section rotate about an axis of rotation. An outer nacelle surrounds the fan, and is spaced from the core engine housing to define a bypass duct. The fan delivers air into the bypass duct and into the core engine housing. The nacelle is formed with camber so as to be curved in a first plane away from the axis of rotation in a first lateral direction. An engine mount structure extends from the nacelle at an angle that is non-parallel and non-perpendicular to the first plane, and has a component in a lateral direction that is opposed to the first lateral direction. An aircraft is also disclosed.

Gas turbine engine mounted above wing and with camber

A propulsion system for an aircraft includes a gas generating core engine generates an exhaust gas flow that is expanded through a turbine section, a power turbine driven by the exhaust gas flow, a propulsor coupled to the power turbine, a hydrogen fuel system configured to supply hydrogen fuel to the combustor through a fuel flow path, a condenser arranged along the core flow path and configured to extract water from the exhaust gas flow, and an evaporator arranged along the core flow path receiving a portion of the water extracted by the condenser to generate a steam flow that is injected into the core flow path upstream of the turbine section.

Reverse flow hydrogen steam injected turbine engine

Examples described herein provide a computer-implemented method for managing battery usage for a hybrid electric engine of an aircraft. The method includes receiving a flight plan comprising flight plan data for a flight of an aircraft. The method further includes receiving battery data about a battery system of the aircraft. The method further includes determining waypoints for when to apply electric power from the battery system based at least in part on the flight plan data and the battery data. The method further includes controlling, based at least in part on the waypoints, an electric motor while the flight plan is executed. The method further includes updating, while the flight plan is executed, the waypoints based at least in part on data received during the flight.

Hybrid electric engine power distribution

A propulsion system of an aircraft includes a hybrid electric gas turbine engine, and a nacelle at least partially enclosing the hybrid electric gas turbine engine. The nacelle includes a first nacelle half and a second nacelle half. Each of the first nacelle half and the second nacelle half include an outer nacelle sleeve, an inner nacelle sleeve radially offset from the outer nacelle sleeve such that a flowpath is defined between the outer nacelle sleeve and the inner nacelle sleeve, and an upper bifurcation connecting the outer nacelle sleeve to the inner nacelle sleeve at an upper end of the nacelle. The flowpath is circumferentially continuous between the upper bifurcation of the first nacelle half and the upper bifurcation of the second nacelle half.

Hybrid electric engine and nacelle system

A propulsion system is provided for an aircraft. This aircraft propulsion system includes an engine housing, an open propulsor rotor, an engine core and a thrust diversion system. The open propulsor rotor is outside of the engine housing. The engine core is within the engine housing and motively coupled to the open propulsor rotor. The thrust diversion system is configured with the engine housing. The thrust diversion system includes a door configured to move radially from a stowed position to a deployed position.

Thrust diverter for an open rotor aircraft propulsion system

An assembly for a gas turbine engine includes at least one rotational assembly, an engine static structure, a compressor, one or more compressed air loads, and a particulate separator assembly. The at least one rotational assembly includes a shaft, a bladed compressor rotor, and a bladed turbine rotor. The engine static structure includes an engine case assembly. The engine case assembly surrounds the at least one rotational assembly. The compressor includes the bladed compressor rotor. The compressor is configured to form a compressed air flow. The one or more compressed air loads are disposed within the engine case assembly. The particulate separator assembly includes a plurality of particulate separators. The plurality of particulate separators are disposed outside of the engine case assembly. The plurality of particulate separators are configured to separate particulate from the compressed air flow and direct the compressed air flow to the one or more compressed air loads.

Particulate separator assembly for a gas turbine engine

A bowed rotor prevention system includes a gas turbine engine, and electric motor, and a core turning controller. The gas turbine engine includes a rotor that is rotatably coupled to a drive shaft. The electric motor is rotatably coupled to a motor shaft, which is mechanically coupled to the drive shaft so as to rotate therewith. The core turning controller in signal communication with the electric motor. The core turning controller determines whether a rotor bow is present in the rotor based on an operating time of the gas turbine engine, determines a motoring time based on the operating time, and invokes an anti-rotor bowing mode configured to control the electric motor to rotate the rotor according to the motor time.

Core turning system

A hybrid-electric aircraft system is provided and includes first and second hybrid-electric engines, first and second ducting systems fluidly communicative with each other and with the first and second hybrid-electric engines, respectively, and a control system. The control system is operably coupled to each of the first and second hybrid-electric engines and to each of the first and second ducting systems. The control system is configured to run the first hybrid-electric engine normally, to run the second hybrid-electric engine in a lower power mode and to control each of the first and second ducting systems to direct bleed air from the first hybrid-electric engine to the second hybrid-electric engine.

Hybrid-electric single engine descent failure management

A fan drive gear system for a turbine engine includes a carrier that supports rotation of the plurality of intermediate gears and is configured for rotation about the axis. A rotating oil inlet and rotating gutter are attached to the carrier. A transfer bearing is fixed to a static engine structure and engaged to communicate oil to the rotating oil inlet. A static baffle that is disposed radially outward of the transfer bearing and configured to direct oil that is expelled from the transfer bearing into the rotating gutter.

Rotating carrier oil manifold

A gas turbine engine is provided that includes fan, compressor, combustor, and turbine sections, an outer casing, an outside core annular region, and a fan air circulation system. The outer casing is disposed radially outside of the compressor, combustor, and turbine sections. The engine has a core gas path and a fan bypass air duct. The core gas path extends through the compressor, combustor, and turbine sections, and is disposed radially inside of the outer casing. The fan bypass air duct is defined by inner and outer radial flow path boundaries. The outside core annular region is disposed radially between the outer casing and the inner radial boundary flow path boundary. The fan air circulation system is configured to receive fan bypass air from the fan bypass air duct and selectively pass the received fan bypass air into the outside core annular region.

Ducted firewall with upper bifi bleed for modulated core ventilation

An assembly is provided for a turbine engine. This turbine engine assembly includes a rotating structure, a stationary structure and an electric machine. The rotating structure is configured to rotate about a rotational axis. The stationary structure circumscribes the rotating structure. The electric machine includes a rotor and a stator. The rotor circumscribes the rotating structure and is coupled to the rotating structure through a spline connection. The stator is connected to the stationary structure.

Electric machine within a turbine engine

A gas turbine engine includes a fan shaft rotatable about an axis, a fan connected to the fan shaft, and an outer housing surrounding the fan to define a bypass passage. A compressor section has both a low pressure compressor that is fixed to rotate with the fan shaft and a high pressure compressor. A turbine section has a low pressure turbine driving a low speed spool and a high pressure turbine driving the high pressure compressor. The low pressure turbine includes rotating blades and a static structure aft of the rotating blades. A fan drivetrain includes a geared architecture connecting the low speed spool to the fan shaft such that the fan and low pressure compressor rotate at a lower speed than the low pressure turbine. A thrust bearing is axially aft of the geared architecture and axially forward of the high pressure compressor. A tower shaft is rotatably driven by the low speed spool.

Geared turbofan with over-speed protection

Growing community of inventors

Marlborough, CT, United States of America

Marc J Muldoon