General Electric Company

Ge Avio S.r.l.

General Electric Company Polska Sp. Z O.o.

Ge Aviation Systems Limited

General Electric Deutschland Holding Gmbh

Arthur William Sibbach

Brandon Wayne Miller

Nicholas Joseph Kray

Jeffrey Douglas Rambo

Daniel Alan Niergarth

Bugra Han Ertas

Scott Alan Schimmels

Robert R Rachedi

Andrea Piazza

Tsuguji Nakano

Elzbieta Kryj-Kos

Brian Lewis Devendorf

Gary Willard Bryant, Jr

Sean Christopher Binion

Andrew Hudecki

Michael Anthony Benjamin

Jeffrey Donald Clements

Ethan Patrick O'Connor

Erich Alois Krammer

Xiaohua Zhang

James Ryan Reepmeyer

Paul Burchell Glaser

Miriam Manzoni

Adam Tomasz Pazinski

Flavia Turi

Benjamin Thomas Van Oflen

Ryan T Roehm

John C Schilling

Vincenzo Martina

Ravindra Shankar Ganiger

Ian Francis Prentice

Wendy Wenling Lin

Aaron Michael Dziech

Scott Hunter

Christopher James Kroger

John Carl Glessner

Frank Worthoff

Gregory Carl Gemeinhardt

Michael John Franks

Timothy Richard DePuy

Egbert Geertsema

Michael Macrorie

Douglas Downey Turner

Lawrence William Nurre

Allan George Van De Wall

Jorge De Luis

Keith W Wilkinson

Hao Huang

Mohamed Osama

Randy M Vondrell

Kirk Douglas Gallier

Bhaskar Nanda Mondal

Joseph Alfred Iannotti

Constantinos Minas

Daniel Edward Mollmann

Patrick Michael Marrinan

Richard Alan Wesling

Brian Gene Brzek

Rajesh Kumar

Stefan Joseph Cafaro

Eric Richard Westervelt

David Marion Ostdiek

William Joseph Solomon

Andrew J Martin

Donald Scott Yeager

Vishnu Vardhan Venkata Tatiparthi

Kevin Edward Hinderliter

Tomasz Iglewski

Aaron Todd Sellinger

Douglas Lorrimer Armstrong

Nagashiresha G

Douglas Scott Jacobs

Koji Asari

Kedar S Vaidya

Vaibhav M Deshmukh

Sushilkumar Shevakari

Ahmet Dindar

Prateek Mathur

Avinash Natarajan

Rakshit Tirumala

Brent Michael Push

Robert Eugene Dyson

Michał Tomasz Kuropatwa

An engine component for a turbine engine. The engine component has a composite structure and a cover structure. The composite structure has a composite structure outer wall and a composite structure edge. The cover structure encases at least a portion of the composite structure outer wall. The cover structure has a main body. The main body extends along the at least a portion of the composite structure outer wall.

Engine component

A turbine engine with an engine core defining an engine centerline and comprising a rotor and a stator. The turbine engine including a set of composite airfoils circumferentially arranged about the engine centerline and defining at least a portion of the rotor. An airfoil in the set of composite airfoils including a composite portion extending chordwise between a composite leading edge and a trailing edge and a leading edge protector coupled to the composite portion.

Turbine engine with composite airfoils

A gas turbine engine is provided having a turbomachine comprising a compressor section, a combustion section, and a turbine section arranged in serial flow order, the compressor section having a high pressure compressor defining a high pressure compressor exit area (A) in square inches and the turbine section having a drive turbine defining a drive turbine exit area (A) in square inches, the turbomachine further comprising a drive turbine shaft coupled to the drive turbine; wherein the gas turbine engine defines a maximum exhaust gas temperature (EGT) in degrees Celsius, a maximum drive turbine shaft torque (T) in Newton meters, and a corrected specific power (CSP) in Newtons squared times degrees Celsius over meters squared, wherein the corrected specific power is determined as follows: wherein CSP is greater than 0.0001194×EGT−0.103×EGT+22.14 and less than 0.0003294×EGT−0.306×EGT+77.91; and wherein EGT is greater than 525 degrees Celsius and less than 1250 degrees Celsius.

Gas turbine engine

A turbofan engine defining an axial direction and a longitudinal centerline along the axial direction is provided. The turbofan engine includes: a fan section having a fan, the fan comprising a plurality of fan blades; a turbomachine drivingly coupled to the fan, the turbomachine comprising a compressor section with a low pressure compressor, a turbine section with a low pressure turbine, a reduction gearbox, and an outer casing, the low pressure turbine drivingly coupled to the low pressure compressor across the reduction gearbox; an outer nacelle surrounding the fan and at least a portion of the turbomachine; an outlet guide vane extending between the turbomachine and the outer nacelle at a location downstream of the plurality of fan blades, the outlet guide vane defining a base and a tip and being forward swept from the base to the tip.

Gas turbine engine with forward swept outlet guide vanes

A turbine engine for an aircraft. The turbine engine includes a core turbine engine and a steam system. The steam system extracts water from combustion gases, vaporizes the water to generate steam, and injects the steam into a core air flow path of the core engine to add mass flow to core air. A core hot gas path component may be fluidly connected to a hot gas path that routes combustion gasses from the combustor. The core turbine engine may also include a turbine fluidly connected to the hot gas path to receive the combustion gases. The turbine may include a turbine airfoil. Each of the core hot gas path component and the turbine airfoil includes a combustion-gas-facing surface facing the hot gas path. A hydrophobic coating is formed on the combustion-gas-facing surface, reducing wetting of water vapor within the combustion gases on the core hot gas path component.

Turbine engine including a gas path component having a hydrophobic coating

A hybrid electric propulsion system includes a gearbox, an electric motor operably coupled to the gearbox, a battery operably coupled to the electric motor to power the electric motor, and an engine lubrication system. The engine lubrication system includes a tank that holds an engine lubrication fluid. The engine lubrication system includes a pump that is configured to pump the lubrication fluid from the tank toward one or both of the battery and the electric motor through a supply line to maintain one or both of the battery and the electric motor above a threshold temperature.

Component heating in hybrid electric propulsion systems

The disclosure herein relates to an automated fiber placement assembly for forming a component by the successive layering of strips of fiber tows with a pressure roller. The pressure roller has a rotational axis about which the pressure roller rotates to apply the strip of fiber tows to the component. The pressure roller can be shaped complementary to a non-uniform surface of the component for even application of the strip of fiber tows to the component.

Automated fiber placement assembly with pressure roller

An aircraft engine assembly includes a gas turbine engine having an intake channel configured to receive an incoming flow of air and form an intake flow of air, the intake channel configured to turn the received incoming flow of air from an incoming flow direction to a first axial direction of the gas turbine engine, the incoming flow direction reverse of the first axial direction, and an electric machine coupled with the low pressure shaft and located at the aft end of the gas turbine engine proximate the intake channel, the electric machine in heat exchange communication with the intake flow of air such that the electric machine transfers heat to the incoming flow of air within the intake channel when the electric machine is operated.

Reverse flow gas turbine engine having electric machine

A hybrid electric turboprop includes a propeller, a thermal engine, an electric motor, a gearbox, and an air inlet. The propeller is configured to rotate about a propeller axis and includes a plurality of blades extending radially outwardly from the propeller axis such that, as the propeller is rotated about the propeller axis, the plurality of blades define a substantially circular blade path area centered about the propeller axis and having a radius. The gearbox couples both the thermal engine and the electric motor to the propeller to enable each of the thermal engine and the electric motor to drive rotation of the propeller about the propeller axis. The air inlet defines an opening. A radial distance is defined from the propeller axis to a location within the opening. The radial distance is equal to or less than 60% of the radius.

Air inlet configurations for hybrid aircraft

A gearbox assembly includes a gearbox and a gutter for collecting a gearbox lubricant scavenge flow from the gearbox. The gutter is characterized by a lubricant extraction volume ratio between 0.01 and 0.3, and given by Vis a gutter volume of the gutter and Vis a gearbox volume. A gas turbine engine includes a combustion section and the gearbox assembly. A fuel delivery system includes a fuel supply line for delivering fuel to the combustion section. A lubrication system includes a lubricant supply line for delivering lubricant to the gearbox assembly. A thermal management system includes a fuel-lubricant heat exchanger for cooling the lubricant with the fuel. The thermal management system selectively directs the fuel through fuel bypass lines or the lubricant through lubricant bypass lines to bypass the fuel-lubricant heat exchanger based on a fuel temperature or a lubricant temperature.

Gearbox assembly with lubricant extraction volume ratio

A turbine engine for an aircraft. The turbine engine includes a combustor fluidly coupled to a fuel delivery assembly to receive fuel from the fuel delivery assembly. The fuel is injected into the combustor and combusted in the combustor to generate combustion gases. A condenser is located downstream of a turbine to receive the combustion gases and to condense water. The fuel heat exchanger is thermally coupled to the condenser to receive heat from the water condensed by the condenser. The fuel heat exchanger is located in the fuel delivery assembly to receive the fuel and to transfer the heat received from the water to the fuel. The boiler is located downstream of the fuel heat exchanger. The boiler receives the water and is fluidly connected to the combustor to receive the combustion gases and to boil the water to generate steam.

Turbine engine including a steam system

Growing community of inventors

Boxford, MA, United States of America

Arthur William Sibbach