公开(公告)号：US20240228055A9

公开(公告)日：2024-07-11

申请号：US18483106

申请日：2023-10-09

Applicant: ROLLS-ROYCE plc

Inventor： Marko BACIC ,  John COULL

IPC: B64D37/30 ,  B64D37/34 ,  F02C7/22

CPC classification number: B64D37/30 ,  B64D37/34 ,  F02C7/22

Abstract: An aircraft propulsion system fuel system comprises a fuel line configured to receive liquid hydrogen fuel from a fuel tank, a vaporizer configured to vaporize liquid hydrogen fuel from the fuel line to generate a supercritical or gaseous fuel, a main fuel pump configured to receive and to pump the gaseous or supercritical fuel from the vaporizer during operation of the propulsion system, and a heater provided downstream in fuel flow to the main fuel pump, and configured to raise the temperature of the gaseous or supercritical fuel to a propulsion system delivery temperature.

公开(公告)号：US12031493B2

公开(公告)日：2024-07-09

申请号：US18162949

申请日：2023-02-01

Applicant: ROLLS-ROYCE plc

Inventor： Peter Swann

IPC: F02C9/40 ,  F02C7/22

CPC classification number: F02C9/40 ,  F02C7/22 ,  F05D2220/323 ,  F05D2270/053 ,  F05D2270/08 ,  F05D2270/303

Abstract: A system has first and second fuel stores for first and second fuels, an engine, a fuel distribution system, first and second flow rates of the fuel contributing to a total flow rate of fuel; and a controller for controlling the relative fractions of the total flow rate of fuel to the engine according to the required power output of the engine such that the relative fraction of the total flow rate of fuel to the engine represented by the second flow rate increases with increasing required power output of the engine. The fuels are selected such that using only the second fuel results in a lower engine temperature than using only the first fuel, for the same mechanical power and/or the second fuel has a lower specific energy than the first and/or the second fuel produces more water during combustion than the first fuel per unit of fuel energy.

公开(公告)号：US20240217353A1

公开(公告)日：2024-07-04

申请号：US18536570

申请日：2023-12-12

Applicant: ROLLS-ROYCE plc

Inventor： Sivakumar NADARAJAN ,  Shanjiao JIANG ,  Thiha KYAW ,  Amit GUPTA

IPC: B60L53/14 ,  H02J7/00 ,  H02J13/00

CPC classification number: B60L53/14 ,  H02J7/00032 ,  H02J7/0047 ,  H02J13/00022 ,  B60L2200/10

Abstract: A data logging and transmission device is provided for an electric aircraft having a charging port for on-ground charging of an energy storage system of an electric propulsion system of the aircraft. The device includes: a control unit, data storage unit, data transmitter, and sensor configured to detect connection of charging port of the electric aircraft to ground-side charger and then issue a trigger signal to the control unit. The control unit is configured wherein a state of flight of the electric aircraft, the control unit collects inflight data from the electric aircraft and saves the inflight data to the data storage unit. The control unit is also configured such that in a state of on-ground charging of the electric aircraft, the control unit, on receipt of the trigger signal, commands the data transmitter to transmit the inflight data saved on the data storage unit to a remote receiver.

公开(公告)号：US12018840B2

公开(公告)日：2024-06-25

申请号：US18050825

申请日：2022-10-28

Applicant: ROLLS-ROYCE plc

Inventor： Damian Martin ,  James E Clissold

IPC: F02C7/28 ,  F23R3/28

CPC classification number: F23R3/283 ,  F02C7/28 ,  F23R2900/03044

Abstract: A combustor arrangement includes a fuel injector, and a seal arranged around the fuel injector and having an upstream end and a downstream end. The seal includes an annular body at least partially abutting the fuel injector. The annular body includes an inner surface facing the fuel injector and an outer surface radially spaced apart from the inner surface relative to the central axis. The annular body further includes a plurality of slots disposed on the inner surface and circumferentially spaced apart from each other relative to the central axis. Each slot axially extends at least partially from the downstream end to the upstream end. Each slot is disposed in fluid contact with the fuel injector. The seal also includes a flange radially extending from the outer surface of the annular body at the upstream end.

公开(公告)号：US20240200467A1

公开(公告)日：2024-06-20

申请号：US18588409

申请日：2024-02-27

Applicant: ROLLS-ROYCE plc

Inventor： Mark SPRUCE

IPC: F01D25/18 ,  F01D25/16 ,  F02C3/113 ,  F02C7/06 ,  F02C7/36 ,  F02K3/06 ,  F16H57/04 ,  F16H57/08

CPC classification number: F01D25/18 ,  F01D25/166 ,  F02C3/113 ,  F02C7/06 ,  F02C7/36 ,  F02K3/06 ,  F16H57/0469 ,  F16H57/0479 ,  F05D2220/323 ,  F05D2220/36 ,  F05D2260/40311 ,  F16H2057/085

Abstract: Gearboxes for aircraft gas turbine engines, in particular to arrangements for journal bearings such gearboxes, and to related methods of operating such gearboxes and gas turbine engines. Example embodiments include a gearbox for an aircraft gas turbine engine, the gearbox including: a sun gear; a plurality of planet gears surrounding and engaged with the sun gear; and a ring gear surrounding and engaged with the plurality of planet gears, each of the plurality of planet gears being rotatably mounted around a pin of a planet gear carrier with a journal bearing having an internal sliding surface on the planet gear and an external sliding surface on the pin.

公开(公告)号：US20240191658A1

公开(公告)日：2024-06-13

申请号：US18512999

申请日：2023-11-17

Applicant: Rolls-Royce plc

Inventor： David M. Donnelly ,  Derek S. Wall ,  Jonathan Wieland

IPC: F02C7/12 ,  F01D21/00 ,  F01D21/12

CPC classification number: F02C7/12 ,  F01D21/003 ,  F01D21/12 ,  F05D2260/20

Abstract: A method of operating a gas turbine engine having a spool includes executing, by a controller, a pre-shutdown procedure. The pre-shutdown procedure includes: determining a parameter associated with a thermal condition of the gas turbine engine; and calculating an idle period for an idle rotation operation to be performed in a shutdown procedure. Calculation of the idle period is based on the determined parameter.

公开(公告)号：US20240191657A1

公开(公告)日：2024-06-13

申请号：US18583395

申请日：2024-02-21

Applicant: ROLLS-ROYCE PLC

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

IPC: F02C7/08 ,  F01D5/28 ,  F02C7/36 ,  F02C9/16 ,  F02K3/06

CPC classification number: F02C7/08 ,  F01D5/282 ,  F01D5/284 ,  F02C7/36 ,  F02C9/16 ,  F02K3/06 ,  F05D2220/32 ,  F05D2220/323 ,  F05D2220/36 ,  F05D2260/40311 ,  F05D2300/6033

Abstract: A highly efficient gas turbine engine is a system wherein 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：US20240189952A1

公开(公告)日：2024-06-13

申请号：US18525032

申请日：2023-11-30

Applicant: Rolls-Royce plc

Inventor： Adam Thomas CLARE

IPC: B23P6/00 ,  B24B19/14

CPC classification number: B23P6/002 ,  B24B19/14

Abstract: A repair system for repairing a surface of a workpiece includes a first tool configured to rotate in a first direction. The first tool contacts the surface of the workpiece during the rotation of the first tool in order to repair the surface of the workpiece. The repair system further includes a second tool configured to rotate in a second direction opposite to the first direction. The second tool contacts the surface of the workpiece during the rotation of the second tool in order to repair the surface of the workpiece. The repair system further includes a drive mechanism coupled to each of the first tool and the second tool.

公开(公告)号：US20240186889A1

公开(公告)日：2024-06-06

申请号：US18512170

申请日：2023-11-17

Applicant: ROLLS-ROYCE plc

Inventor： Sivakumar NADARAJAN ,  Mohamed Sathik MOHAMED HALICK ,  Viswanathan VAIYAPURI ,  Sundararajan PRASANTH ,  Amit K. GUPTA

IPC: H02M1/32 ,  H02M1/00 ,  H02M7/5387

CPC classification number: H02M1/327 ,  H02M1/0009 ,  H02M7/53871

Abstract: The disclosure relates to thermal management of a power electronics converter. An example embodiment includes a power electronics converter comprising: a first set of terminals connectable to a first voltage supply; a second set of terminals connectable to a second voltage supply; a plurality of semiconductor switches connected between the first and second sets of terminals; a voltage sensor connected to measure a voltage across the second supply; a current sensor connected to measure a current through the second supply; and a controller connected to provide switching signals to the semiconductor switches and to receive voltage and current signals from the voltage and current sensors, the controller configured, for each of the semiconductor switches, to: determine a junction temperature of the semiconductor switch; compare the determined junction temperature to a reference temperature; and adjust a switching gate voltage applied to the semiconductor switch.

公开(公告)号：US20240183273A1

公开(公告)日：2024-06-06

申请号：US18508497

申请日：2023-11-14

Applicant: ROLLS-ROYCE plc

Inventor： John M. HARRISON

IPC: F01D5/02

CPC classification number: F01D5/027 ,  F05D2220/323 ,  F05D2260/96

Abstract: Disclosed is a gas turbine engine rotor balancing apparatus comprising: a rotor configured to rotate about a rotor axis; a substantially annular balancing mass configured to encircle the rotor; and a mass adjustment apparatus for adjusting the position of the balancing mass relative to the rotor.