-
公开(公告)号：US20240102431A1
公开(公告)日：2024-03-28
申请号：US18215864
申请日：2023-06-29
Applicant: ROLLS-ROYCE plc
Inventor： Stephen J BRADBROOK , William J SMITH , Jonathan P BRADLEY
CPC classification number: F02K3/06 , F01D9/041 , F01D25/24 , F05D2240/35
Abstract: A novel configuration for an axial flow gas turbine engine for aircraft has an engine core having a core length and including a first turbine, an axial compressor, and a drive connecting the first turbine to the axial compressor, the engine core further including a second turbine, and a fan shaft connecting the second turbine to a fan located upstream of the engine core, the fan including a plurality of fan blades extending from a fan hub, the fan having a tip radius from 90 mm to 225 mm and wherein the ratio of fan tip radius to an engine length is 0.15 to 0.25. The engine may have 3, 4 or 5 compressor stages and combustor volume (in litres) which when divided by fan tip radius (in mm) is 0.015 to 0.083. The fan may be multistage fan configured to permit an electric motor to be located within fan hub diameter.
-
公开(公告)号：US20250067434A1
公开(公告)日：2025-02-27
申请号：US18804670
申请日：2024-08-14
Applicant: ROLLS-ROYCE PLC
Inventor： Marcin Damian DUTKA
Abstract: A tile for a gas turbine engine combustor. The tile has a base that has a hot-side surface, a cold-side surface, a first circumferential extremity, a second circumferential extremity and a local radial axis. The tile also has a plurality of cooling channels that have inlets on the cold-side surface and outlets on the hot-side surface, and one or more rail structure attached to the cold-side surface of the base.
-
公开(公告)号：US12234019B2
公开(公告)日：2025-02-25
申请号：US18045857
申请日：2022-10-12
Applicant: ROLLS-ROYCE plc
Inventor： Christopher A Murray
Abstract: A cabin blower system, for an aircraft, comprising: a cabin blower compressor, for compressing air for delivery to a cabin of an aircraft, comprising a compressor drive shaft running on a contactless bearing system; and a transmission comprising an input and an output, the input being arranged to receive power from an engine of the aircraft and the output being arranged to mechanically drive the cabin blower compressor, wherein the output of the transmission is mechanically coupled with the compressor drive shaft via a flexible drive coupling.
-
公开(公告)号：US12228077B2
公开(公告)日：2025-02-18
申请号：US18183989
申请日：2023-03-15
Applicant: ROLLS-ROYCE plc
Inventor： Jonathan E. Holt , Richard Sharpe
Abstract: Disclosed is a fuel system for a gas turbine engine. The system comprises a fuel pump for fluid communication with a fuel reservoir; a driving turbine for driving the fuel pump; and a source of compressed air flow to drive the driving turbine. The source of compressed air may be the engine core, a dedicated fuel system compressor or the compressor of a cabin blower system.
-
公开(公告)号：US20250052425A1
公开(公告)日：2025-02-13
申请号：US18772375
申请日：2024-07-15
Applicant: ROLLS-ROYCE plc
Inventor： Stephen C. HARDING , Paul A. HUCKER , Iain MORGAN
IPC: F23R3/00
Abstract: The present disclosure relates to a combustor assembly for a gas turbine engine. The combustor assembly comprises a combustor liner, a combustor head, a cowl and a fastener. The combustor liner and the cowl define a cavity. The combustor liner has an integral lug that extends into the cavity from a wall of the combustor liner. The fastener extends into the combustor liner lug to fasten the combustor head to the combustor liner.
-
Patent Agency Ranking
公开(公告)号：US12224673B2
公开(公告)日：2025-02-11
申请号：US17956968
申请日：2022-09-30
Applicant: ROLLS-ROYCE plc
Inventor： David R. Trainer , Francisco Javier Chivite Zabalza , Mark Sweet , Luke George
Abstract: There is provided an electrical power system comprising: a DC voltage source, a DC electrical network, a DC to AC to DC converter having a primary side connected to the DC voltage source and a secondary side connected to the DC electrical network, and a controller configured to control the DC to AC to DC converter, wherein the controller is configured to: monitor an electrical current or voltage between the DC voltage source and the DC electrical network; determine, based on the monitored electrical current or voltage, whether the DC electrical network is in a fault condition; and increase a switching frequency of the primary side of the DC to AC to DC converter in response to a positive determination that the DC electrical network is in a fault condition.
-
公开(公告)号：US20250035050A1
公开(公告)日：2025-01-30
申请号：US18433932
申请日：2024-02-06
Applicant: Rolls-Royce plc
Inventor： Mark SPRUCE
Abstract: Gas turbine engine for aircraft includes: an engine core including a turbine, compressor, and core shaft connecting the turbine to the compressor; a fan located upstream of the core; a gearbox; and a gearbox support arranged to at least partially support the gearbox. The fan has a mass in a range of 150 kg to 1200 kg. A moment of inertia of the fan is greater than or equal to 7.40×107 kgmm2. A radial bending stiffness to moment of inertia ratio of: the radial bending stiffness of at least one of the fan shaft at the output of the gearbox and the gearbox support the moment of inertia of the fan may be greater than or equal to 2.5×10−2 Nkg−1 m−1 mm−2. A tilt stiffness to moment of inertia ratio of: the tilt stiffness of at least one of the fan shaft at the output of the gearbox and the gearbox support the moment of inertia of the fan may be greater than or equal to 4.0×10−4 Nmrad−1 kg−1 mm−2.
-
公开(公告)号：US20250035037A1
公开(公告)日：2025-01-30
申请号：US18913201
申请日：2024-10-11
Applicant: ROLLS-ROYCE PLC
Inventor： Richard G. Stretton , Michael C. Willmot , Nicholas Grech
Abstract: A gas turbine engine (10) for an aircraft comprises an engine core (11) comprising a turbine (19), a compressor (14), a core shaft (26), and a core exhaust nozzle (20), the core exhaust nozzle (20) having a core exhaust nozzle pressure ratio calculated using total pressure at the core nozzle exit (56); a fan (23) comprising a plurality of fan blades; and a nacelle (21) surrounding the fan (23) and the engine core (11) and defining a bypass duct (22), the bypass duct (22) comprising a bypass exhaust nozzle (18), the bypass exhaust nozzle (18) having a bypass exhaust nozzle pressure ratio calculated using total pressure at the bypass nozzle exit;
wherein a bypass to core ratio of: bypass exhaust nozzle pressure ratio core exhaust nozzle pressure ratio is configured to be in the range from 1.1 to 2.0 under aircraft cruise conditions.-
公开(公告)号：US12203379B2
公开(公告)日：2025-01-21
申请号：US18594226
申请日：2024-03-04
Applicant: ROLLS-ROYCE PLC
Inventor： Guy Stevenson
Abstract: A temperature measurement system for a gas turbine engine, the gas turbine engine including, in axial flow sequence, a compressor section, a combustor section having plural fuel spray nozzles, and a turbine section. The temperature measurement system includes one or more optical thermometers, each optical thermometer configured to measure the temperature of a component washed by the working gas of the engine, the or each component being in the combustor section or the turbine section at a first position along the axis of the engine.
-
公开(公告)号：US20250020546A1
公开(公告)日：2025-01-16
申请号：US18752004
申请日：2024-06-24
Applicant: ROLLS-ROYCE plc
Inventor： Andrew D. NORTON , Alexander R. WALLACE , Liam D. HARRISON
Abstract: A system for inspecting a complex component, the system comprising: a flexible inspection device having a driver for controlling the motion of the flexible inspection device by manipulating the relative positions of a plurality of joints within the device, the flexible device having a sensor on its distal end; a feed mechanism for controlling the insertion or retraction of the flexible device into or from the complex component; a component driver for driving the movement of an aspect of the complex component from at least a first position to a second position; and a computer running a computer program, the computer interfacing with the flexible inspection device, the feed mechanism, and the component driver, so as to link the operation of the flexible inspection device, the feed mechanism and the component driver through a single program.
-
-
-
-
-
-
-
-
-
Search Results
7222
records
(took 0.038 seconds)
