General Electric Company

Intermagnetics General Corporation

Mti Microfuel Cells Inc.

Martin Marietta Corporation

Constantinos Minas

William Morton

Evangelos Trifon Laskaris

Harry Kirk Mathews, Jr

Mark Gilbert Benz

Gregory Alan Steinlage

Thomas Robert Raber

Charles Gitahi Mukira

Gregory Reznikov

Wayne Charles Hasz

Ernst Wolfgang Stautner

Charles Michael Carlstrom, Jr

Lana Maria Osusky

Gregory Alexander Natsui

Melvin Robert Jackson

Arthur William Sibbach

Russel Hugh Marvin

Kenneth Gordon Herd

Paul A Siemers

Ann Melinda Ritter

Brian Magann Rush

Nesim Abuaf

Robert Adolph Ackermann

Stefan Joseph Cafaro

Douglas J Snyder

Eric Richard Westervelt

Adrian M Beltran

Eyitayo James Owoeye

James Ryan Reepmeyer

David Robert Schumacher

Robert S Hirsch

Keith Garrette Brown

Sanjay M Correa

Sean Christopher Binion

David H Leach

Robert Patrick Campbell

Ahmed K Kalafala

John Eric Meschter

Mitchell R Cohen

Dan Arthur Gross

John Breunissen

F Scott Murray

Robert J Miller

Mark C Mendrick

Megan A Fannon

James Michael Gent

Richard W Lindberg

James K Prueitt

Michael L Chen

Russ Marvin

Yuri Lvovsky

Ernst Stautner Wolfgang

Michael J Rysz

Lisa Tang

Jeffrey Alan Graves

Ross Anthony McLean

Lance Gordon Peterson

Myron Clyde Muth

Ping Huang

Sampath Venkataswamy

Amit Chaugule

A fuel tank heat rejection system for an aircraft. The fuel tank heat rejection system includes a fuel tank compartment in the aircraft and a fuel tank having an exterior surface and storing fuel therein. The fuel tank is located in the fuel tank compartment. The fuel tank heat rejection system includes one or more air valves that provide fluid communication to the fuel tank compartment. The one or more air valves opening to operably direct cooling air into the fuel tank compartment through the one or more air valves, the cooling air contacting the exterior surface of the fuel tank such that heat from the fuel is rejected from the fuel tank.

Fuel tank heat rejection system

A superconducting motor including a rotor, a heat sink, and a bearing. The rotor includes a superconducting winding formed from a superconducting material. The heat sink is positioned within the superconducting motor to absorb heat produced by the superconducting motor. The bearing includes an inner race, an outer race, and a rolling element. The bearing rotatably supports the rotor and is thermally connected to each of the rotor and the heat sink to transfer heat from the rotor to the heat sink. The rolling element is formed from a material having, at 25 K, a thermal conductivity of 20 W/mK or more and an ultimate tensile strength of 650 MPa or more. The rolling element may be formed from a copper alloy.

High heat transfer cryogenic bearing

Methods, apparatus, systems, and articles of manufacture are disclosed herein that include a cryogenic pump system comprising: a cryogenic liquid tank; a cryogenic pump including a suction adapter, the suction adapter connected to the cryogenic liquid tank via a liquid supply line and a gaseous return line; and a phase separator connected downstream of the cryogenic liquid tank and upstream of the cryogenic pump, the phase separator including a filtration structure integrated into the liquid supply line to separate vapor from cryogenic liquid, the phase separator connected to the gaseous return line to direct the vapor to the cryogenic liquid tank.

Apparatus and systems for separating phases in liquid hydrogen pumps

Example systems, methods, and apparats for refueling hydrogen aircraft are disclosed herein. An example multiphase hydrogen refueling system includes a liquid hydrogen (LH2) tank coupled to at least one of a cryo-compressed hydrogen (CcH2) tank and a gaseous hydrogen (GH2) tank; a liquid nitrogen (LN2) tank; and a hydrant coupled to the LH2 tank, the CcH2 tank, the GH2 tank, and the LN2 tank, the hydrant including: a transfer line to refuel an aircraft with at least LH2, CcH2, or GH2; a purge valve to purge the transfer line using at least one of nitrogen (N2) from the LN2 tank or GH2 from the GH2 tank; and a GH2 return line to transmit evaporated GH2 back to the GH2 tank.

Systems, methods, and apparatus for refueling hydrogen aircraft

A sub-cooler for a sub-cooling cryogenic refueling system is disclosed herein. The sub-cooler includes a first valve to separate flowing cryogenic fuel into a primary flowline and an auxiliary flowline, a second valve to reduce the saturated pressure and temperature of the cryogenic fuel in the auxiliary flowline, a cryogenic heat exchanger to transfer heat from the primary flowline to the auxiliary flowline, a temperature sensor to measure the temperature of the sub-cooled cryogenic fuel in the primary flowline, and a sub-cooler controller to control the effective areas of the primary flowline inlet and the auxiliary flowline inlet at the first valve.

Sub-coolers for refueling onboard cryogenic fuel tanks and methods for operating the same

An engine control system may be configured to perform a method of controlling thermal bias in a turbomachine. An exemplary method may include determining a thermal bias-value for the turbomachine, and performing a cooling treatment based at least in part on the thermal bias-value. The thermal bias-value may include a difference between an upward temperature-value corresponding to a first one or more temperature measurements of an upward portion of the turbomachine and a downward temperature-value corresponding to a second one or more temperature measurements of a downward portion of the turbomachine. The cooling treatment may include at least one of: circulating air through at least a portion of the turbomachine, and rotating a shaft of the turbomachine with a motoring system.

Thermal bias control in turbomachines

A system for detecting hydrogen leaks within a vehicle includes a hydrogen sensor for generating data indicative of a level of hydrogen present within a compartment of the vehicle and a computing system. The computing system determines at least one of the level of hydrogen present within the compartment or a rate of change of the level of hydrogen present within the compartment and compares the determined at least one of the level of hydrogen present within the compartment or the rate of change of the level of hydrogen present within the compartment to a threshold value. When the determined at least one of the level of hydrogen present within the compartment or the rate of change of the level of hydrogen present within the compartment exceeds the threshold value, the computing system initiates a control action for reducing the level of hydrogen present within the compartment.

Hydrogen fuel leak detection system for a vehicle

A gas turbine engine is provided having: a turbomachine; a fan section having a fan rotatable by the turbomachine; a nacelle enclosing the fan; and an engine controller positioned within the nacelle. The nacelle defines an inner surface radius (r) along the radial direction inward of the engine controller, wherein the engine controller defines a radial height (Δr) along the radial direction, a total volume (V), and a normalized radius (r'). The normalized radius (r′) is a ratio of the inner surface radius (r) to the total volume (V) to cube root, and wherein these parameters are related by the following equation:0.1(′)(′),wherein the normalized radius (r′) is between 1.25 and 8 and K is equal to 40%, or the normalized radius (r′) is between 2.75 and 4.5 and K is equal to 65%.

Engine controller for a gas turbine engine

A gas turbine engine is provided defining an axial direction, a radial direction, and a circumferential direction. The gas turbine engine includes a turbomachine having a compressor section, a combustion section, and a turbine section in serial flow order; a fan section including a fan rotatable by the turbomachine; a nacelle enclosing the fan; and an oil tank positioned within the nacelle, wherein the oil tank defines an effective length (L) along the axial direction, a circumference span (CS) along the circumferential direction, and a radial height (Δr) along the radial direction, and wherein these parameters are related by a tank sizing factor (TSF) equal to the effective length (L) times the circumference span (CS) divided by the radial height (Δr) squared L×CS/Δr), wherein the tank sizing factor (TSF) is between 20 and 2200.

Conformal structure for a gas turbine engine

A method of operating a fuel system for a vehicle having an engine, the fuel system comprising a fuel delivery system, the fuel delivery system including a liquid hydrogen delivery assembly and a regulator assembly, the regulator assembly having a buffer tank, the method including: providing a first flow of hydrogen fuel from a liquid hydrogen fuel tank through the liquid hydrogen delivery assembly to the regulator assembly, wherein providing the first flow of hydrogen fuel includes pumping the first flow of hydrogen fuel through the liquid hydrogen delivery assembly using a pump at a first fuel flowrate; receiving data indicative of a commanded fuel flowrate to the engine, wherein the commanded fuel flowrate is higher than the first fuel flowrate; and providing stored hydrogen fuel from a gaseous fuel storage to the engine.

Hydrogen fuel system

Methods and apparatus are disclosed for a hydrogen aircraft with cryo-compressed storage. An example fuel distribution system includes a vacuum vessel, a cryogenic vessel positioned within the vacuum vessel, the cryogenic vessel part of a cryo-compressed hydrogen delivery assembly, and at least one of a heater or a thermosiphoning loop to maintain a pressure of the cryogenic vessel.

Hydrogen aircraft with cryo-compressed storage

An aircraft including a fuselage, a power generator configured to provide power to the aircraft, and at least one fuel tank for holding fuel for the power generator, and a fuel delivery assembly. The fuel tank is positioned in the fuselage and is configured to hold hydrogen fuel in a liquid phase. The fuel tank has a chamber for holding the hydrogen fuel and a fuel extraction line fluidly coupled to the chamber. The fuel extraction line extends from the fuel tank in a forward direction of the fuselage and at a downward angle relative to a centerline of the fuselage. The fuel delivery assembly is fluidly coupled to the fuel extraction line and fluidly connects the fuel tank to the power generator. The fuel delivery assembly is configured to provide the hydrogen fuel from the fuel tank to the power generator.

Onboard liquid hydrogen storage for a hydrogen aircraft

A heat exchanger for a hydrogen fuel delivery system includes a tube bank including an inner-tube where a first portion of the inner-tube extends through an inlet region of the tube bank, a second portion of the inner-tube extends through a mid-region of the tube bank, and a third portion of the inner-tube extends through an outlet region of the tube bank. A thermal buffer at least partially surrounds the inner-tube. A first portion of the thermal buffer extends along the first portion of the inner-tube, a second portion of the thermal buffer extends along the second portion of the inner-tube, and a third portion of the thermal buffer extends along the third portion of the inner-tube. A plurality of fins is disposed along the inner-tube and extends radially outwardly from an outer surface of the thermal buffer.

Heat exchanger for a hydrogen fuel delivery system

Systems and methods are disclosed for estimating or determining a rate or an amount of fuel coke formation in a fuel system, such as of a gas turbine engine. The system is operable to control a rate of fuel coke formation. The system may include a sensor that measures an operating parameter associated with fuel coke formation in the fuel system. A controller is in communication with the sensor to receive the signal therefrom for determining an amount or a rate of fuel coking in the fuel system. Based on this determination the controller may adjust the rate of fuel coke formation by adjusting the operation of the turbine engine, a thermal management system of the turbine engine, or the fuel system.

Systems and methods for controlling fuel coke formation

A minimum creep life location (MCLL) on a blade for a turbine blade design is received. A temperature at the MCLL on the blade is monitored. When the temperature at the MCLL exceeds a predetermined threshold, a cooling air supply is adjusted to lower the temperature below the threshold during engine operation.

Method and apparatus for cooling turbine blades

Growing community of inventors

Slingerlands, NY, United States of America

Constantinos Minas