General Electric Company

Mustafa Dindar

Richard David Cedar

Scott Alan Schimmels

David William Crall

Keith Edward James Blodgett

Scott Andrew Burton

Joseph Donofrio

Vaughn Ray Kunze

Jan Christopher Schilling

Trevor Howard Wood

Kishore Ramakrishnan

Wendy Wen-Ling Lin

Scott Roger Finn

Bernard James Renggli

Jixian Yao

Jeffrey S Spruill

Keith Blodgett

Robert Paul Tyler

Daniel Robert Dwyer

Andrew J Hank

Keith E J Blodgett

Keith Edward Blodgett

A gas turbine engine includes: a turbomachine including a combustion section and an exhaust assembly arranged in serial flow order; and a fuel system. The fuel system includes: a hydrogen fuel tank for holding a hydrogen fuel in a liquid phase; and a hydrogen delivery assembly in thermal communication with the exhaust assembly. The hydrogen delivery assembly includes: a liquid hydrogen line in fluid communication with the hydrogen fuel tank; a gaseous hydrogen line in fluid communication with the combustion section of the gas turbine engine; and a heat exchanger tubing positioned within the exhaust assembly downstream of the liquid hydrogen line and upstream of the gaseous hydrogen line.

Hydrogen fuel system for a gas turbine engine

A fuel system for a gas turbine engine is provided. The gas turbine engine including an exhaust assembly. The exhaust assembly including a tail cone and defining a radial direction, a circumferential direction, an axial direction, a working gas flow path, and an outer bypass flow path, the fuel system including: a hydrogen fuel tank for holding a hydrogen fuel; a heat exchanger configured to be coupled to or integrated into the tail cone of the exhaust assembly, the heat exchanger including: a first axial flow path in flow communication with the hydrogen fuel tank; a second axial flow path in flow communication with a combustion section of the gas turbine engine; and a radial flow path.

A method of operating a fuel management unit for a fuel system. The method including: receiving data indicative of a state of an exhaust assembly using a sensor of the fuel system, the state of the exhaust assembly including a temperature of a working gas flow within the exhaust assembly; determining an amount of a hydrogen fuel in a liquid phase to provide to a hydrogen delivery assembly in response to receiving data indicative of the state of the exhaust assembly; and directing one or more components to provide the determined amount of the hydrogen fuel to the hydrogen delivery assembly.

A turbofan engine is provided. The turbofan engine includes a fan comprising a plurality of fan blades; and a nacelle that circumferentially surrounds the fan, the nacelle comprising an annular wall having an exterior surface and an interior surface, the exterior surface comprising a first exterior portion, and the interior surface comprising a first interior portion, wherein a first exterior portion is formed of a first structure defining an exterior surface porosity, and wherein a first interior portion is formed of a second structure defining an interior surface porosity.

Flow control mechanism for nacelle of turbofan engine

A variable area exhaust nozzle defining an actual area ratio for a gas turbine engine that includes a shroud assembly having a fixed shroud and an adjustable cowl, an adjustable plug, a nozzle adjustment assembly, and a controller configured to receive data indicative of an operating speed of the gas turbine engine; determine a target area ratio based at least in part on received data indicative of the operating speed of the gas turbine engine; and operate the nozzle adjustment assembly to selectively adjust at least one of the adjustable cowl or the adjustable plug such that the actual area ratio is substantially equivalent to the target area ratio.

Variable area exhaust nozzle system and method for control thereof

The disclosure is towards an inlet cowl for a turbine engine including a surface defining an inlet with a flow path and a method towards controlling the airflow in the flow path. The inlet cowl further includes an inlet lip and inner and outer barrels. The inlet lip confronts the inner barrel at a junction defining a gap.

Inlet cowl for a turbine engine

An engine nacelle is provided for an aircraft. The engine nacelle comprises: an inlet for receiving an air flow to generate a thrust force for the aircraft; a lip portion positioned at the inlet and surrounding the inlet; and at least one strake provided on a surface of the engine nacelle.

Engine nacelle for an aircraft

A propulsion system for an aircraft includes a propulsor; a turbomachine mechanically coupled to the propulsor for driving the propulsor during a combustion operating mode of the propulsion system and mechanically decoupled from the propulsor during an electric operating mode of the propulsion system; and an electrical power source. The propulsion system further includes an electric machine, the electric machine being electrically coupled to the electrical power source and mechanically coupled to the propulsor during the electric operating mode of the propulsion system such that the electric machine drives the propulsor during the electric operating mode of the propulsion system.

Hybrid electric propulsion system for an aircraft

A method of fabricating a mixer for a gas turbine engine is provided. The method includes forming a forward end and an aft end of the mixer, and forming an annularly undulating contour that defines a plurality of core immersion lobes and a plurality of bypass immersion lobes between the forward end and the aft end. The plurality of bypass immersion lobes includes a first bypass immersion lobe and a second bypass immersion lobe. The first bypass immersion lobe has a first crown contour line extending from the forward end to the aft end of the mixer, and the second bypass immersion lobe has a second crown contour line extending from the forward end to the aft end of the mixer. The first crown contour line is different than the second crown contour line.

Variable immersion lobe mixer for turbofan jet engine exhaust and method of fabricating the same

A turbofan exhaust nozzle includes: a conical inner shell disposed coaxially inside a surrounding outer shell to define an annular flow duct therebetween terminating in an outlet at a trailing edge of the outer shell and the inner shell terminates in a trailing edge aft of the outlet; and a pylon interrupting circumferentially the duct, wherein at least a portion of the trailing edge of the outer shell is vertically non-coplanar.

Exhaust nozzle with non-coplanar and/or non-axisymmetric shape

A turbine exhaust nozzle includes an inner shell disposed coaxially inside an outer shell to define a flow duct terminating in an outlet at a trailing edge of the outer shell. The inner shell is non-axisymmetric and varies in axial slope angle circumferentially around the duct.

Variable slope exhaust nozzle

A mixer for mixing flows in a turbofan engine is provided. The mixer includes a plurality of chevron lobes, each of the plurality of lobes comprising a crown, a keel, a first trailing edge, a second trailing edge, and a first transverse edge extending between first trailing edge and second trailing edge, said mixer configured to receive two separate incoming exhaust flows and mix the two flows into at least one rotational exhaust flow that is ejected out at least one of said first trailing edge and said second trailing edge.

Turbofan engine mixer assembly

A multi-component hybrid turbine blade comprises a shank portion and an airfoil portion. The airfoil portion comprises a composite section having a first density. The composite section comprises a recess and an insert section. The insert section has a second mass density, which is less than the first mass density. The insert section is disposed in the recess, and the insert section is bonded to the composite section. The composite section and the insert section together define an airfoil shape. A fabrication method comprising laying up composite material layers to form a portion of the composite section. The portion of the composite section comprises a recess. Disposing the insert section in the recess. Laying up additional composite material layers to achieve a final desired thickness of the composite section while covering the insert section.

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Cincinnati, OH, United States of America

Mustafa Dindar