公开(公告)号：US20250003592A1

公开(公告)日：2025-01-02

申请号：US18882197

申请日：2024-09-11

Applicant: ROLLS-ROYCE plc

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

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

Abstract: A method of operating a gas turbine engine; the gas turbine engine includes a combustor. The combustor includes a combustion chamber and a plurality of fuel spray nozzles configured to inject fuel into the combustion chamber. The plurality of fuel spray nozzles includes a first subset of fuel spray nozzles and a second subset of fuel spray nozzles. The combustor is operable in a condition in which the first subset of fuel spray nozzles are supplied with more fuel than the second subset of fuel spray nozzles. A ratio of the number of fuel spray nozzles in the first subset of fuel spray nozzles to the number of fuel spray nozzles in the second subset of fuel spray nozzles is in the range of 1:2 to 1:5. The method includes: providing fuel to the one or more fuel-oil heat exchangers. Also provided is a gas turbine engine for an aircraft.

公开(公告)号：US12180899B2

公开(公告)日：2024-12-31

申请号：US17853191

申请日：2022-06-29

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, including: staged combustion system having pilot fuel injectors and main fuel injectors, staged combustion system being operable in pilot-only range of operation and pilot-and-main range of operation; and fuel delivery regulator arranged to control delivery of fuel to pilot and main fuel injectors. Fuel delivery regulator arranged to receive fuel from a first fuel source containing a first fuel having a first fuel characteristic and a second fuel source containing a second fuel having a different second fuel characteristic. The fuel delivery regulator is arranged to deliver fuel to the pilot fuel injectors during at least part of the pilot-only range of operation having a different fuel characteristic from fuel delivered to one or both of the pilot and main fuel injectors during at least part of the pilot-and-main range of operation. A method of operating a gas turbine engine is also disclosed.

公开(公告)号：US20240426252A1

公开(公告)日：2024-12-26

申请号：US18829971

申请日：2024-09-10

Applicant: ROLLS-ROYCE PLC

Inventor： Mark SPRUCE

IPC: F02C7/36 ,  F02K3/06

Abstract: A gas turbine engine for an aircraft including: an engine core including a turbine, a compressor, and a core shaft connecting the turbine to the compressor; a fan located upstream of the engine core, the fan including a plurality of fan blades; a gearbox that can receive an input from the core shaft, and can output drive to a fan shaft via an output of the gearbox so as to drive the fan at a lower rotational speed than the core shaft; and a fan shaft mounting structure arranged to mount the fan shaft within the engine, the fan shaft mounting structure including at least two supporting bearings connected to the fan shaft.

公开(公告)号：US20240426251A1

公开(公告)日：2024-12-26

申请号：US18825435

申请日：2024-09-05

Applicant: ROLLS-ROYCE plc

Inventor： Pascal DUNNING ,  Roderick M. TOWNES ,  Michael J. WHITTLE

IPC: F02C7/36 ,  F01D5/28 ,  F01D5/30 ,  F02C3/073

Abstract: A highly efficient gas turbine engine is provided. The fan of the gas turbine engine is driven from a turbine via a gearbox, such that the fan has a lower rotational speed than the driving turbine, thereby providing efficiency gains. The efficient fan system is mated to a core that has low cooling flow requirements and/or high temperature capability, and which may have particularly low mass for a given power.

公开(公告)号：US12172763B2

公开(公告)日：2024-12-24

申请号：US18333873

申请日：2023-06-13

Applicant: ROLLS-ROYCE plc

Inventor： David R. Trainer ,  Francisco Javier Chivite Zabalza ,  Mark Sweet ,  Gian Incerpi

IPC: B64D27/24 ,  B64D27/10 ,  H02J1/00 ,  H02M7/219 ,  H02P9/02 ,  B64D27/02

Abstract: The disclosure relates to an electrical power system for connecting an electrical machine to first and second DC networks operating at different voltages. In an embodiment, an electrical power system comprises: an electrical machine having first, second, third and fourth windings; first, second, third and fourth AC:DC power electronics converters each connected to receive an input AC supply from the respective first, second, third and fourth windings, each AC:DC power electronics converter having first and second DC output terminals connecting the AC:DC power electronics converters to first, second and third DC supply output terminals, wherein the first and second windings are arranged to provide an AC supply to the respective first and second AC:DC power electronics converters in quadrature to each other and the third and fourth windings are arranged to provide an AC supply to the respective third and fourth AC:DC power electronics converters in quadrature to each other.

公开(公告)号：US12172757B2

公开(公告)日：2024-12-24

申请号：US18155351

申请日：2023-01-17

Applicant: ROLLS-ROYCE plc ,  Rolls-Royce Corporation

Inventor： Christopher A. Murray ,  Nicholas Howarth ,  Daniel Swain ,  Ian J. Bousfield

IPC: B64D13/06 ,  F02C7/32 ,  F04D25/04 ,  F04D29/68

Abstract: There is provided a blower system for providing air to an airframe system, comprising a rotor configured to be mechanically coupled to a spool 440 of a gas turbine engine, wherein the rotor is configured to: in a blower mode, be driven to rotate by the spool to discharge air to an airframe discharge port for supply to an airframe system; and, in an engine drive mode, receive air from an external air source via an impingement port that is configured to direct the received air onto the rotor and thereby drive the rotor to rotate to drive the spool to.

公开(公告)号：US20240417084A1

公开(公告)日：2024-12-19

申请号：US18672375

申请日：2024-05-23

Applicant: ROLLS-ROYCE PLC

Inventor： Chandana J. GAJANAYAKE ,  Devinda A. Molligoda

IPC: B64D27/35 ,  H01M8/04537 ,  H01M8/04858 ,  H01M10/42 ,  H01M16/00 ,  H02J1/08 ,  H02J7/00 ,  H02J7/34

Abstract: An electrical system includes: a battery; a fuel-cell pack; a load electrically coupled to the fuel-cell pack; a switching arrangement electrically coupled to the battery, the fuel-cell pack and the load; a DC-DC converter; and a control system. The switching arrangement configures the electrical system in at least one of a battery-charge mode and a combined-drive mode. In the battery-charge mode the battery is coupled in series to the fuel-cell pack and the load via the DC-DC converter for simultaneous charging of the battery and driving of the load by the fuel-cell pack. In the combined-drive mode, the battery is coupled in series to the fuel-cell pack and the load via the DC-DC converter for driving of the load by both the battery and the fuel-cell pack. The control system is configured to: monitor a parameter of an electrical power provided to the load; and control the DC-DC converter.

公开(公告)号：US12168958B2

公开(公告)日：2024-12-17

申请号：US18211809

申请日：2023-06-20

Applicant: ROLLS-ROYCE PLC

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

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

Abstract: A method of operating a gas turbine engine having a combustor having a combustion chamber and a plurality of fuel spray nozzles configured to inject fuel into the combustion chamber. The fuel spray nozzles have a first subset of fuel spray nozzles and a second subset of fuel spray nozzles. The combustor is operable in a condition in which the first subset of fuel spray nozzles are supplied with more fuel than the second subset of fuel spray nozzles. A ratio of the number of fuel spray nozzles in the first subset of fuel spray nozzles to the number of fuel spray nozzles in the second subset of fuel spray nozzles is in the range of 1:2 to 1:5. The method includes providing a fuel to the plurality of fuel spray nozzles having a calorific value of at least 43.5 MJ/kg. A gas turbine engine can be for an aircraft.

公开(公告)号：US20240410581A1

公开(公告)日：2024-12-12

申请号：US18669683

申请日：2024-05-21

Applicant: ROLLS-ROYCE plc

Inventor： Edward A. WALTERS

IPC: F23R3/00

Abstract: A combustor assembly for a gas turbine engine includes a combustor shell extending along a shell axis. The combustor shell includes a shell wall extending around the shell axis and a meter panel connected to an upstream end of the shell wall. The shell wall and the meter panel together define a combustion space therebetween. The combustor assembly further includes: a tile disposed within the combustor shell and including a tile flange portion extending radially with respect to the shell axis; a heatshield connected to the meter panel and extending at least radially towards the tile; a fastener connecting the tile flange portion to the meter panel; and a compartment thermally shielded from the combustion space. Either the heatshield and the tile together form the compartment or the tile alone forms the compartment. The fastener is spaced apart from the combustion space and at least partially disposed within the compartment.

公开(公告)号：US20240401531A1

公开(公告)日：2024-12-05

申请号：US18420204

申请日：2024-01-23

Applicant: ROLLS-ROYCE plc

Inventor： Craig W BEMMENT ,  Benjamin J KEELER ,  Kevin R MCNALLY ,  Andrea MINELLI

IPC: F02C7/14 ,  F02C7/16 ,  F02C7/22

Abstract: A method of operating a gas turbine engine and a gas turbine engine includes a fuel delivery system arranged to provide fuel, a combustor arranged to combust at least a proportion of the fuel, a primary fuel-oil heat exchanger arranged to have up to 100% of the fuel provided by the fuel delivery system flow therethrough, and a secondary fuel-oil heat exchanger arranged to have a proportion of the fuel from the primary fuel-oil heat exchanger flow therethrough. Fuel is arranged to flow from the primary fuel-oil heat exchanger to the secondary fuel-oil heat exchanger whereas oil is arranged to flow from the secondary fuel-oil heat exchanger to the primary fuel-oil heat exchanger. A fuel viscosity is adjusted to a maximum of 0.58 mm2/s on entry to the combustor at cruise conditions.