公开(公告)号：US12234022B2

公开(公告)日：2025-02-25

申请号：US17819509

申请日：2022-08-12

Applicant: Rolls-Royce North American Technologies, Inc. ,  Rolls-Royce plc

Inventor： Peter Schenk ,  Mark Angelo Tanner

IPC: B64D31/00 ,  B60L50/52 ,  B64D27/10 ,  B64D27/24 ,  H02J7/00 ,  H02K7/00 ,  H02K7/18 ,  H02K11/33 ,  B64D27/02

Abstract: An example system includes an electrical machine electrically configured to generate electrical energy used by one or more components of a gas-turbine engine; an energy storage system; and a controller electrically connected to the energy storage system and configured to receive electrical energy from the energy storage system, wherein, in response to the gas-turbine engine being shut off, the controller is configured to cause the electrical machine to rotate a rotor of the gas-turbine engine using the energy received from the energy storage system.

公开(公告)号：US20250059922A1

公开(公告)日：2025-02-20

申请号：US18936481

申请日：2024-11-04

Applicant: ROLLS-ROYCE PLC

Inventor： Peter SWANN ,  Craig W. BEMMENT ,  Christopher P. MADDEN

IPC: F02C9/26 ,  B64D27/10 ,  B64D37/30 ,  F02C7/22 ,  F23R3/36

Abstract: A gas turbine engine for an aircraft includes a staged combustion system having pilot fuel injectors and main fuel injectors. The gas turbine engine further includes a fuel delivery regulator arranged to control delivery of fuel to the pilot and main fuel injectors, and a fuel characteristic determination module configured to determine one or more fuel characteristics of the fuel being supplied to the staged combustion system. A controller is configured to determine a staging point defining the point at which the staged combustion system is switched between pilot-only operation and pilot-and-main operation, the staging point being determined based on the determined one or more fuel characteristics, the controller being configured to control the staged combustion system according to the determined staging point.

公开(公告)号：US20250051018A1

公开(公告)日：2025-02-13

申请号：US18778405

申请日：2024-07-19

Applicant: Tennessee Technological University

Inventor： Rory Roberts

IPC: B64D27/33 ,  B64D27/10 ,  B64D27/355 ,  F01D15/10 ,  F02C7/22

Abstract: A propulsion system for an aircraft as disclosed herein may include a nacelle, a shaft positioned centrally within a cylindrical passageway of the nacelle, a fan coupled to one end of the shaft, a turbine coupled to an opposite end of the shaft, an electric motor coupled to the shaft, a compressor positioned within the cylindrical passageway, and a solid oxide fuel cell positioned with a hollow ring-shaped interior of the nacelle. The hollow ring-shaped interior may surround and be isolated from the cylindrical passageway. The turbine may be configured to provide primary torque to the shaft while the electric motor may be configured to provide additional torque to the shaft. The electric motor may be powered an electric output of the solid oxide fuel cell while the turbine may be powered at least in part by output gases from the solid oxide fuel cell.

公开(公告)号：US12221927B2

公开(公告)日：2025-02-11

申请号：US18304575

申请日：2023-04-21

Applicant: PRATT & WHITNEY CANADA CORP.

Inventor： Sylvain Lamarre ,  Kashif Mohammed ,  John Sgouromitis

IPC: F02C7/25 ,  B64D27/10 ,  F01D25/18 ,  F02C7/14 ,  F02C7/18 ,  F02C7/22 ,  F02C7/232 ,  F02C7/36 ,  F02C9/26

Abstract: An aircraft engine reservoir system includes a reservoir inner chamber containing a flammable fluid. A chamber inlet is fluidly connectable to a flammable fluid source pressurizing the fluid. The chamber includes an outlet. An air source operates at a pressure that is lower that a flammable fluid pressure during an engine operational condition. A valve selectively fluidly connecting the chamber to the air source is movable between a closed position, in which the chamber flammable fluid pressure acting on the valve exceeds the air source pressure acting on the valve such that the valve blocks the air from entering the chamber, and an open position, in which the chamber flammable fluid pressure acting on the valve is lower than the air source pressure acting on the valve such that the valve allows the air to flow into the chamber and evacuate the flammable fluid from the chamber through the outlet.

公开(公告)号：US20250019081A1

公开(公告)日：2025-01-16

申请号：US18714334

申请日：2022-12-02

Applicant: SAFRAN NACELLES

Inventor： Tony MIOSSEC ,  Fabien BRAVIN ,  Vincent DEVANLAY ,  Marc VERSAEVEL ,  Valentin SIMEON

IPC: B64D27/10

Abstract: An assembly for an ejection cone of an aircraft turbomachine, including a first annular wall and a plurality of first partitions and of second partitions extending substantially perpendicularly from the first wall, the first partitions additionally extending wholly in the axial direction and the second partitions extending wholly in a circumferential direction between the adjacent pairs of first partitions and being curved partitions including at least one arcuate portion in the axial direction upstream or downstream, the first wall, the first partitions and the second partitions additionally defining between them a plurality of acoustic boxes distributed around the first wall.

公开(公告)号：US20250003370A1

公开(公告)日：2025-01-02

申请号：US18884969

申请日：2024-09-13

Applicant: ROLLS-ROYCE PLC

Inventor： Christopher P. MADDEN ,  Craig W. Bemment ,  Andrew T Smith ,  Peter Swann

IPC: F02C7/264 ,  B64D27/10 ,  F23R3/28

Abstract: A gas turbine engine has a combustor with a combustion chamber and a plurality of fuel spray nozzles including a first subset of nozzles and a second subset of nozzles. The first subset of nozzles are supplied with more fuel than the second subset of nozzles. A ratio of the number of nozzles in the first subset to the number of nozzles in the second subset is in the range of 1:2 to 1:5. A method includes providing fuel to the one or more fuel-oil heat exchangers, transferring heat from oil to the fuel, and providing the fuel from the one or more fuel-oil heat exchangers to the fuel spray nozzles. Heat is transferred from the oil to the fuel to lower a viscosity of the fuel to 0.58 mm2/s or lower on injection of the fuel into the combustion chamber at cruise conditions.

公开(公告)号：US12163468B1

公开(公告)日：2024-12-10

申请号：US18224942

申请日：2023-07-21

Applicant: Pratt & Whitney Canada Corp.

Inventor： Michel Bousquet ,  Richard Freer ,  Kevin Nguyen

IPC: B64D35/02 ,  B64D27/10 ,  F01D15/10 ,  F02C6/20

Abstract: A system is provided for an aircraft. This system includes a propulsor rotor and a powerplant configured to drive rotation of the propulsor rotor. The powerplant includes a turbo-compounded intermittent internal combustion engine and a dual rotor electric machine. The turbo-compounded intermittent internal combustion engine includes a turbine rotor operatively coupled to the propulsor rotor through the dual rotor electric machine. The dual rotor electric machine includes a first rotor, a second rotor, a first stator and a second stator. The first stator and the second stator are arranged radially between and axially aligned with the first rotor and the second rotor.

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：US12129797B2

公开(公告)日：2024-10-29

申请号：US18463641

申请日：2023-09-08

Applicant: Rolls-Royce plc

Inventor： Mark P. Reid

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

CPC classification number: F02C7/14 ,  B64D27/10 ,  F02C7/06 ,  F02C7/224

Abstract: 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

Applicant: Pratt & Whitney Canada Corp.

Inventor： Michel Labrecque ,  Kevin Nguyen

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

CPC classification number: B64D33/04 ,  B64D27/10 ,  B64D29/00 ,  F02K1/06 ,  F02K1/08 ,  F02K1/09 ,  F02K1/36

Abstract: 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.