公开(公告)号：US20240417100A1

公开(公告)日：2024-12-19

申请号：US18703042

申请日：2022-10-13

Applicant: SAFRAN

Inventor： Pierre-Alain Marie Cyrille LAMBERT ,  Hugo Pierre Mohamed JOUAN

IPC: B64D37/34 ,  B64D37/30 ,  F02C6/10 ,  F02C7/224

Abstract: A fuel conditioning system configured to supply a turbomachine with fuel from a cryogenic tank, the conditioning system comprising a fuel circuit connected at the inlet to the cryogenic tank and at the outlet to the turbomachine, a pump, a fuel cell configured to provide electricity to an electrical network of the aircraft, at least a first heat exchanger belonging to the fuel circuit and configured to transmit calories from the fuel cell to the fuel flow in order to heat it, and at least one second heat mounted downstream of the first heat exchanger in the fuel circuit and configured to transmit calories from the turbomachine to the fuel flow in order to heat it.

公开(公告)号：US20240359816A1

公开(公告)日：2024-10-31

申请号：US18768636

申请日：2024-07-10

Applicant: General Electric Company

Inventor： Arthur W. Sibbach ,  Michael A. Benjamin ,  Paul Burchell Glaser

IPC: B64D37/32 ,  B64D27/10 ,  B64D37/04 ,  B64D37/30 ,  B64D37/34 ,  C06B23/00 ,  C06B43/00

CPC classification number: B64D37/32 ,  B64D27/10 ,  B64D37/04 ,  B64D37/30 ,  B64D37/34 ,  C06B23/008 ,  C06B43/00

Abstract: A hydrogen fuel including a safety marker and a method and apparatus for adding the safety marker to the hydrogen fuel. The hydrogen fuel may be stored in a tank in a liquid phase and then heated to at least one of a gaseous phase and a supercritical phase. The safety marker may be added to the hydrogen fuel when the hydrogen fuel is in the at least one of the gaseous phase and the supercritical phase after heating the hydrogen fuel. The hydrogen fuel may be delivered in the at least one of the gaseous phase and the supercritical phase to a power generator, such as a gas turbine engine. The safety marker may be a visual safety marker, such as a noble gas, or an odorant.

公开(公告)号：US12129045B2

公开(公告)日：2024-10-29

申请号：US17609937

申请日：2020-06-22

Applicant: PARKER-HANNIFIN CORPORATION

Inventor： Bryan D. Jensen ,  Daniel C. Massie ,  Daniel J. Henninger ,  Scott P. Auld-Hill

IPC: B64D37/32 ,  A62C3/06 ,  A62C3/08 ,  A62C99/00 ,  B64D37/34

CPC classification number: B64D37/32 ,  A62C3/065 ,  A62C3/08 ,  A62C99/0018 ,  B64D37/34

Abstract: A sparging evaporator for an inerting system including an outer vessel, an inner vessel within the outer vessel, and a plenum formed between the inner and outer vessels. The outer vessel includes a gas inlet for receiving inlet gas into the plenum, and a liquid inlet for receiving liquid fuel into the plenum. The inlet gas in the plenum generates a gas pressure that is exerted against a free surface of the liquid fuel in the plenum thereby forcing the liquid fuel and the inlet gas through an inlet of the inner vessel. The inner vessel contains a structure that promotes liberation of fuel vapor from the liquid fuel and enables the inlet gas in the liquid fuel to sparge the fuel vapor in the liquid fuel, thereby forming a fuel-enriched gas mixture that can be fed to a reactor of the inerting system.

公开(公告)号：US12071235B2

公开(公告)日：2024-08-27

申请号：US17383757

申请日：2021-07-23

Applicant: The Boeing Company

Inventor： Matthew W. Orr ,  Philip A. Van Seeters ,  Christopher B. Pastega

IPC: B64C3/34 ,  B64D37/04 ,  B64D37/34

CPC classification number: B64C3/34 ,  B64D37/04 ,  B64D37/34

Abstract: An access panel to be received in an access aperture in a lower skin of a wing on an aircraft incorporates a body surrounded by a sealing flange. The body is configured to be received in the access aperture and the sealing flange is configured to be received on a sealing land surrounding the access aperture. An integral heat exchanger extends from a top surface of the body into a fuel tank in the wing to conduct heat from the fuel to an external surface of the access panel.

公开(公告)号：US20240174376A1

公开(公告)日：2024-05-30

申请号：US18059515

申请日：2022-11-29

Applicant: General Electric Company

Inventor： Michael Joseph Murray ,  Victor Moreno Patan

IPC: B64D37/34 ,  B64D37/32

CPC classification number: B64D37/34 ,  B64D37/32

Abstract: An aircraft fuel system includes a first fuel storage tank arranged to store a first fuel, a fuel oxygen reduction unit arranged to generate a deoxygenated fuel from the first fuel, and a second fuel storage tank arranged to store the deoxygenated fuel generated by the fuel oxygen reduction unit, and being arranged to supply the deoxygenated fuel to an engine.

公开(公告)号：US20240158095A1

公开(公告)日：2024-05-16

申请号：US18507556

申请日：2023-11-13

Applicant: Airbus Operations SAS

Inventor： Jérôme MILLIERE

IPC: B64D37/30 ,  B64D37/00 ,  B64D37/34

CPC classification number: B64D37/30 ,  B64D37/005 ,  B64D37/34

Abstract: An aircraft including a supply system including a hydrogen gas tank, a recipient device that consumes hydrogen gas, a feed line between the tank and the recipient device, a first enclosure in which are installed a heating system configured to heat the hydrogen gas, a second enclosure in which are installed a drive system configured to drive the hydrogen gas towards the recipient device, a safety tank for a pressurized inert fluid, and a purge line between a free section of the feed line and a distribution system. If a leak is detected, the pressurized inert fluid is pushed into the purge line to evacuate the hydrogen gas from the free section. With such a supply system, the hydrogen gas present in a free section is evacuated in case of leakage.

公开(公告)号：US20240102657A1

公开(公告)日：2024-03-28

申请号：US18372646

申请日：2023-09-25

Applicant: University of Central Florida Research Foundation, Inc.

Inventor： Jayanta Kapat ,  Richard Blair ,  Marcel Otto ,  Erik Fernandez

IPC: F23R3/36 ,  B63H21/16 ,  B64D27/12 ,  B64D37/04 ,  B64D37/34 ,  F23R3/00

CPC classification number: F23R3/36 ,  B63H21/16 ,  B64D27/12 ,  B64D37/04 ,  B64D37/34 ,  F23R3/002

Abstract: A power system for an engine that can be used in an aircraft, a marine vessel or a land vehicle has a storage tank containing ammonia. An engine supported on the vehicle is configured to operate using hydrogen gas as fuel. A cracking device in or adjacent the engine receives heat from operation of the engine, e.g., from a compressor or a combustion chamber, and also receives ammonia from the storage tank, and it uses the heat from the engine to dissociate the ammonia to produce hydrogen gas. The cracking device supplies the hydrogen gas to the engine, which has a combustor in which combustion of the hydrogen gas takes place. The energy from the combustion drives the engine so as to provide mechanical energy.

公开(公告)号：US11939078B1

公开(公告)日：2024-03-26

申请号：US16927754

申请日：2020-07-13

Applicant: Clarence Lui ,  Matthew Dooley

Inventor： Clarence Lui ,  Matthew Dooley

IPC: B64D37/34 ,  B64D13/06 ,  B64D13/08 ,  B64D37/02 ,  F02C7/224

CPC classification number: B64D37/34 ,  B64D13/08 ,  F02C7/224 ,  B64D2013/0614 ,  B64D2013/0696 ,  B64D37/02 ,  F05D2270/07

Abstract: Fuel used as a coolant in an aircraft can be thermally conditioned for active thermal management of the airframe and engine. The fuel can be thermally conditioned using the residual cooling capacity of a power and thermal module (PTM), providing flexibility of thermal system design, or via a compact engine-mounted turbo cooler, to maximize system efficiency. The fuel can be stored in a thermal reserve tank to provide a missionized heat sink capable serviceable for periodic high heat flux equipment. The cooling and provision of cooled fuel to aircraft components can be intelligently controlled to provide efficient cooling and effectively unlimited ground hold times.

公开(公告)号：US11834985B2

公开(公告)日：2023-12-05

申请号：US18081512

申请日：2022-12-14

Applicant: AMOGY INC.

Inventor： Young Suk Jo ,  Hyunho Kim ,  Scott Mandelbaum ,  Christopher Stanczak

IPC: F02C3/30 ,  F02C7/14 ,  F02C7/22 ,  B64D27/24 ,  B64D37/30 ,  B64D37/34 ,  C01B3/04 ,  B01J8/04 ,  B01J8/00

CPC classification number: F02C3/30 ,  B01J8/001 ,  B01J8/0496 ,  C01B3/047 ,  F02C7/14 ,  F02C7/22 ,  B01J2208/0053 ,  B01J2208/00415 ,  B01J2208/00504 ,  B01J2208/00539 ,  B01J2208/00548 ,  C01B2203/0277 ,  C01B2203/066 ,  C01B2203/0822 ,  F05D2220/323

Abstract: The present disclosure provides systems and methods for processing ammonia. The system may comprise one or more reactor modules configured to generate hydrogen from a source material comprising ammonia. The hydrogen generated by the one or more reactor modules may be used to provide additional heating of the reactor modules (e.g., via combustion of the hydrogen), or may be provided to one or more fuel cells for the generation of electrical energy.

公开(公告)号：US20230304439A1

公开(公告)日：2023-09-28

申请号：US17860756

申请日：2022-07-08

Applicant: Raytheon Technologies Corporation

Inventor： Brian M. Holley ,  Joseph B. Staubach ,  Marc J. Muldoon ,  Charles E. Lents

IPC: B64D37/34 ,  F02C7/22 ,  F02C7/224 ,  F02C7/228 ,  F02C7/232

CPC classification number: B64D37/34 ,  F02C7/222 ,  F02C7/224 ,  F02C7/228 ,  F02C7/232 ,  B64D2041/005

Abstract: Aircraft propulsion systems and aircraft are described. The aircraft propulsion systems include aircraft systems having at least one hydrogen tank and an aircraft-systems heat exchanger and engine systems having at least a main engine core, a high pressure pump, a hydrogen-air heat exchanger, and an expander, wherein the main engine core comprises a compressor section, a combustor section having a burner, and a turbine section. Hydrogen is supplied from the at least one hydrogen tank through a hydrogen flow path, passing through the aircraft-systems heat exchanger, the high pressure pump, the hydrogen-air heat exchanger, and the expander, prior to being injected into the burner for combustion.