公开(公告)号：US20240359816A1

公开(公告)日：2024-10-31

申请号：US18768636

申请日：2024-07-10

申请人： General Electric Company

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

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

CPC分类号： B64D37/32 ,  B64D27/10 ,  B64D37/04 ,  B64D37/30 ,  B64D37/34 ,  C06B23/008 ,  C06B43/00

摘要： 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：US12129797B2

公开(公告)日：2024-10-29

申请号：US18463641

申请日：2023-09-08

申请人： Rolls-Royce plc

发明人： Mark P. Reid

IPC分类号： F02C7/14 ,  B64D27/10 ,  F02C7/06 ,  F02C7/224

CPC分类号： F02C7/14 ,  B64D27/10 ,  F02C7/06 ,  F02C7/224

摘要： A heat management system includes a fuel tank storing a fuel; a first heat exchanger thermally coupled to the fuel tank; a hydraulic pump for circulating a hydraulic fluid; a hydraulic circuit including first and second hydraulic lines fluidly coupled to the first heat exchanger and the hydraulic pump, such that the first heat exchanger brings the hydraulic fluid and the fuel into a heat exchange relationship; an oil circuit; and a second heat exchanger thermally coupled to the oil circuit and at least one of the first and second hydraulic lines, such that the second heat exchanger brings the hydraulic fluid and the oil into a heat exchange relationship, thereby allowing heat transfer between the fuel and the oil via the hydraulic fluid.

公开(公告)号：US12103695B2

公开(公告)日：2024-10-01

申请号：US17948870

申请日：2022-09-20

申请人： Pratt & Whitney Canada Corp.

发明人： Michel Labrecque ,  Kevin Nguyen

IPC分类号： B64D33/04 ,  B64D27/10 ,  B64D29/00 ,  F02K1/06 ,  F02K1/08 ,  F02K1/09 ,  F02K1/36

CPC分类号： B64D33/04 ,  B64D27/10 ,  B64D29/00 ,  F02K1/06 ,  F02K1/08 ,  F02K1/09 ,  F02K1/36

摘要： An exhaust nozzle assembly for a propulsion system include a primary nozzle, an outer shroud, an ejector nozzle, and an actuator. The primary nozzle extends along an exhaust centerline. The primary nozzle includes a downstream axial end. The outer shroud surrounds the primary nozzle. The ejector nozzle extends axially between a first axial end and a second axial end. The second axial end forms a nozzle exit plane for the exhaust nozzle assembly. The ejector nozzle converges in a direction from the first axial end to the second axial end. The ejector nozzle forms a mixing cross-sectional area between the primary nozzle and the ejector nozzle at the downstream axial end. The actuator is mounted on the ejector nozzle. The actuator is configured to move the ejector nozzle between a first position and a second position, relative to the outer shroud, to control an area of the mixing cross-sectional area.

公开(公告)号：US12095405B2

公开(公告)日：2024-09-17

申请号：US17651156

申请日：2022-02-15

申请人： Rolls-Royce Corporation ,  Rolls-Royce Electrical Norway AS ,  Rolls-Royce Singapore Pte. Ltd.

发明人： David Loder ,  David Russell Trawick ,  Eirik Mathias Husum ,  Erlend Engevik ,  Roar Furuhaug ,  Chandana Jayampathi Gajanayake

IPC分类号： H02P9/00 ,  B64D27/10 ,  B64D27/24 ,  B64D27/02 ,  H02P101/25 ,  H02P101/30

CPC分类号： H02P9/006 ,  B64D27/10 ,  B64D27/24 ,  B64D27/026 ,  B64D2221/00 ,  H02P2101/25 ,  H02P2101/30

摘要： A turbo-generator system for generating propulsive electrical power for an aircraft includes an electric machine comprising: a rotor configured to be rotated by a gas-turbine of the turbo-generator system; a stator comprising: a first active section comprising first windings surrounding a first portion of the rotor, and a second active section comprising second windings surrounding a second portion of the rotor.

公开(公告)号：US12091183B1

公开(公告)日：2024-09-17

申请号：US18308766

申请日：2023-04-28

申请人： Raytheon Technologies Corporation

发明人： Jon Erik Sobanski

IPC分类号： B64D35/02 ,  B64D27/10

CPC分类号： B64D35/02 ,  B64D27/10

摘要： A propulsion system for an aircraft includes a propulsor section that includes a fan with a plurality of fan blades that are rotatable about a fan axis, a core engine that is configured to generate a gas flow, a power turbine where the gas flow from the core engine is expanded to generate shaft power, and a power turbine shaft that is coupled between the power turbine and the propulsor section. The power turbine shaft is of an axial length between a first end portion and a second end portion along the fan axis that is greater than half a distance between a leading edge of the fan blades and a mechanical coupling of the power turbine shaft to the power turbine, and includes an outer diameter that increases in a direction away from each of the first end portion and the second end portion.

公开(公告)号：US12091179B2

公开(公告)日：2024-09-17

申请号：US17965252

申请日：2022-10-13

申请人： General Electric Company

发明人： Vinod S. Kumar

IPC分类号： B64D27/02 ,  B64D27/10 ,  B64D27/24 ,  B64D31/00 ,  B64D35/00 ,  B64D47/00 ,  F02C6/00 ,  F02C7/36

CPC分类号： B64D27/10 ,  B64D27/24 ,  B64D31/00 ,  B64D35/00 ,  B64D47/00 ,  F02C6/00 ,  F02C7/36 ,  B64D27/026

摘要： An aircraft includes a gas turbine engine, an electric motor, and a propulsion device. The gas turbine engine and the electric motor are configured to provide a target cumulative output to the propulsion device. An electronic control unit is configured to set the gas turbine engine to a first engine mode to provide a first engine output to the propulsion device, set the electric motor to a first motor mode to provide a first motor output to the propulsion device, a sum of the first engine output and the first motor output being within a predetermined range of the target cumulative output, and in response to a speed of the aircraft reaching a target speed and the first engine output increasing to a second engine output, set the electric motor to a second motor mode.

公开(公告)号：US20240300662A1

公开(公告)日：2024-09-12

申请号：US18180381

申请日：2023-03-08

申请人： General Electric Company

发明人： Vinod Kumar ,  Kevin Richard Graziano

IPC分类号： B64D31/14 ,  B64D27/10 ,  B64D27/24 ,  B64D31/08 ,  B64D35/02

CPC分类号： B64D31/18 ,  B64D35/025 ,  H02P9/008 ,  B64C13/16

摘要： A hybrid gas turbine engine for use on an aircraft includes a motor/generator and gas turbine engine placed in parallel power communication with a rotating bladed component, such as an aircraft propeller, through a combining gear box. Power can be modulated with the propeller using the motor/generator. An aircraft having the aircraft propeller can also include several aircraft systems such as an air data computer, automatic flight control system (AFCS), a guidance and navigation system, a full authority digital engine controller/flight control computer (FADEC/FCC), and a fault detection and mitigation controller (FDMC). Data from each of these respective systems can be communicated over an aircraft data bus. In one form data from the AFCS and guidance and navigation system can be provided over the aircraft bus to the FDMC to modulate power to the propeller and in some forms act as a backup to the FADEC/FCC.

公开(公告)号：US12078112B2

公开(公告)日：2024-09-03

申请号：US18096858

申请日：2023-01-13

申请人： ROLLS-ROYCE PLC

发明人： Peter Swann ,  David M Beaven ,  Craig W Bemment ,  Alastair G Hobday ,  Benjamin J Keeler ,  Christopher P Madden ,  Martin K Yates

IPC分类号： G01N21/33 ,  B64D27/10 ,  B64D47/00 ,  F02C9/00 ,  G01N21/3577 ,  G01N21/64 ,  G01N33/28 ,  B64D37/00 ,  G01N21/35

CPC分类号： F02C9/00 ,  B64D27/10 ,  B64D47/00 ,  G01N21/33 ,  G01N21/3577 ,  G01N21/64 ,  G01N33/287 ,  B64D37/00 ,  G01N2021/3595

摘要： A fuel characteristic determination system and method for determining one or more fuel characteristics of an aviation fuel for powering a gas turbine engine of an aircraft. The system includes a sensor component that is formed from a nitrile seal material and includes a surface that can be exposed to the fuel; a sensor for measuring a swell parameter of the seal material; and a fuel characteristics determination module for determining one or more fuel characteristics of the fuel based on the swell parameter. The method includes: exposing one or more seals of a fuel system of an aircraft to fuel within the fuel system; exposing a sensor component, made from the same material as the one or more seals, to the fuel; and measuring a swell parameter of the seal material.

公开(公告)号：US20240246690A1

公开(公告)日：2024-07-25

申请号：US18159506

申请日：2023-01-25

申请人： Rolls-Royce Corporation

发明人： David Russell Trawick

IPC分类号： B64D27/10 ,  B64C11/30 ,  B64D27/24 ,  B64D35/00 ,  B64D41/00 ,  F02C6/00 ,  F02C7/36 ,  H02K7/102 ,  H02K7/116 ,  H02K7/18 ,  H02K11/00

CPC分类号： B64D27/10 ,  B64C11/30 ,  B64D27/24 ,  B64D35/00 ,  B64D41/00 ,  F02C6/00 ,  F02C7/36 ,  H02K7/102 ,  H02K7/116 ,  H02K7/1823 ,  H02K11/0094 ,  B64D2027/026

摘要： An example aircraft includes a parallel propulsion unit, the parallel propulsion unit comprising: a propulsor configured to provide forward propulsion of the aircraft; a gas turbine engine configured to drive the propulsor; an electrical machine configured to generate, for output via one or more electrical busses, electrical energy using mechanical energy derived from the gas turbine engine; and a power sharing module configured to control a ratio of the mechanical energy used to drive the propulsor and used to generate electrical energy; and a plurality of series propulsion units, each series propulsion unit comprising a respective propulsor of a plurality of propulsors that are configured to provide vertical propulsion of the aircraft and a respective electrical machine of a plurality of electrical machines, each respective electrical machine configured to drive a respective propulsor of the plurality of propulsors using electrical energy received from one or more electrical busses.

公开(公告)号：US20240246689A1

公开(公告)日：2024-07-25

申请号：US18243049

申请日：2023-09-06

申请人： JETOPTERA, INC.

发明人： Andrei Evulet

IPC分类号： B64D33/04 ,  B64C9/38 ,  B64C15/00 ,  B64C15/14 ,  B64C21/00 ,  B64C21/04 ,  B64C23/00 ,  B64C39/02 ,  B64D27/10 ,  B64D27/18 ,  B64D29/02 ,  B64D33/02 ,  B64U30/00 ,  B64U30/10 ,  F02C3/04 ,  F02C6/04 ,  F02K1/00 ,  F02K1/36

CPC分类号： B64D33/04 ,  B64C9/38 ,  B64C15/00 ,  B64C15/14 ,  B64C21/00 ,  B64C21/04 ,  B64C23/00 ,  B64C23/005 ,  B64C39/024 ,  B64D27/10 ,  B64D27/18 ,  B64D29/02 ,  B64D33/02 ,  F02C3/04 ,  F02C6/04 ,  F02K1/002 ,  F02K1/36 ,  B64C2230/04 ,  B64C2230/06 ,  B64C2230/16 ,  B64D2033/0273 ,  B64U30/00 ,  B64U30/10 ,  F05D2220/90 ,  Y02T50/10 ,  Y02T50/30 ,  Y02T50/40

摘要： A propulsion system coupled to a vehicle. The system includes a convex surface, a diffusing structure coupled to the convex surface, and at least one conduit coupled to the convex surface. The conduit is configured to introduce to the convex surface a primary fluid produced by the vehicle. The system further includes an intake structure coupled to the convex surface and configured to introduce to the diffusing structure a secondary fluid accessible to the vehicle. The diffusing structure comprises a terminal end configured to provide egress from the system for the introduced primary fluid and secondary fluid.