公开(公告)号：US20220316410A1

公开(公告)日：2022-10-06

申请号：US17697761

申请日：2022-03-17

Applicant: ROLLS-ROYCE plc

Inventor： Peter SWANN ,  Jonathan E. HOLT

IPC: F02C9/28 ,  B64D37/30 ,  B64D27/16 ,  B64D31/00 ,  F02C3/22 ,  A01G15/00

Abstract: An aircraft propulsion system includes a hydrocarbon fuel store, a hydrogen fuel store, an engine system capable of producing thrust by combusting hydrocarbon fuel and/or combusting or oxidising hydrogen fuel, a conveying system to convey hydrocarbon and hydrogen fuel from the fuel stores to the engine system and a control system to control the respective flow rates of the fuel within the conveying system. The control system adapts the fractions of the total fuel energy flow rate to the engine system represented by the hydrocarbon and hydrogen fuel energy flow rates in order to reduce climate warming impact caused by at least one of carbon dioxide, water vapour and condensation trails and/or increase climate cooling impact caused by condensation trails produced by the aircraft propulsion system compared to a dual-fuel propulsion system in which a reserve of hydrocarbon fuel is entirely combusted before any of a reserve of hydrogen fuel.

公开(公告)号：US20220178307A1

公开(公告)日：2022-06-09

申请号：US17476129

申请日：2021-09-15

Applicant: ROLLS-ROYCE PLC

Inventor： Chloe J. PALMER ,  Guy D. SNOWSILL ,  Jonathan E. HOLT

IPC: F02C7/224 ,  F02C3/22

Abstract: A fuel delivery system (201) is shown for delivering the hydrogen fuel from a cryogenic storage system to a fuel injection system in a gas turbine engine. The fuel delivery system includes a pump (301), a metering device (302), and a fuel heating system (303,304) for heating the hydrogen fuel to an injection temperature for the fuel injection system.

公开(公告)号：US20230304440A1

公开(公告)日：2023-09-28

申请号：US18183989

申请日：2023-03-15

Applicant: ROLLS-ROYCE plc

Inventor： Jonathan E. HOLT ,  Richard SHARPE

IPC: F02C7/224 ,  F02C7/32 ,  B64D13/02 ,  B64D37/30

CPC classification number: F02C7/224 ,  F02C7/32 ,  B64D13/02 ,  B64D37/30 ,  F05D2220/323 ,  F05D2240/36

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：US20230407798A1

公开(公告)日：2023-12-21

申请号：US18174806

申请日：2023-02-27

Applicant: ROLLS-ROYCE plc

Inventor： Marko BACIC ,  Jonathan E. HOLT

IPC: F02C9/46 ,  F02C9/40 ,  F02C3/22

CPC classification number: F02C9/46 ,  F02C9/40 ,  F02C3/22

Abstract: A gas turbine engine system includes a hydrogen-burning gas turbine engine and a fuel system including a fuel line arranged to receive gaseous hydrogen at an input thereof and provide the gaseous hydrogen to combustion apparatus of the hydrogen-burning gas turbine engine and a vent line including a vent valve and having a first end coupled to the fuel line and a second end disposed remotely from the hydrogen-burning gas turbine engine. A controller is arranged to switch the vent valve from a closed state to an open state upon detection of an engine shaft-break or similar condition, thus providing rapid evacuation of gaseous hydrogen from the fuel line and hence rapid shut-down of the engine. The engine may be shut down more rapidly than is possible by means of a shut-off valve within the fuel line.

公开(公告)号：US20230304441A1

公开(公告)日：2023-09-28

申请号：US18181626

申请日：2023-03-10

Applicant: ROLLS-ROYCE plc

Inventor： Jonathan E. HOLT

IPC: F02C7/224

CPC classification number: F02C7/224 ,  F02C3/22

Abstract: Disclosed is a fuel system for a gas turbine engine having a core exhaust and a combustion section. The system comprises a fuel pump for fluid communication with a fuel reservoir; a driving turbine for driving the fuel pump; and an air feed to drive the driving turbine, the air feed being fluidly connectable to the core exhaust of the gas turbine engine. Also disclosed is a fuel system comprising: a fuel pump for fluid communication with a fuel reservoir; a fuel line from the fuel pump for fluid communication with the combustion section of the gas turbine engine; and an air feed to a heat exchanger, the air feed being fluidly connectable to the core exhaust of the gas turbine engine, wherein the fuel line is in thermal communication with the air feed within a heat exchanger.

公开(公告)号：US20170114725A1

公开(公告)日：2017-04-27

申请号：US15277599

申请日：2016-09-27

Applicant: ROLLS-ROYCE plc

Inventor： Jonathan E. HOLT ,  Leo V. LEWIS

IPC: F02C9/18 ,  F01D25/24 ,  F02C7/18 ,  F01D25/12 ,  F01D21/00 ,  F01D21/12 ,  F01D5/02 ,  F01D25/14

CPC classification number: F02C9/18 ,  F01D5/02 ,  F01D11/24 ,  F01D17/02 ,  F01D21/003 ,  F01D21/12 ,  F01D25/12 ,  F01D25/14 ,  F01D25/24 ,  F02C7/18 ,  F05D2220/32 ,  F05D2260/20 ,  F05D2270/112 ,  F05D2270/303

Abstract: A case cooling calibration system for a gas turbine engine comprises a rotor casing, and a rotor stage, rotatably mounted within the rotor casing.The rotor casing comprises in series fluid communication, a duct, a flow control valve, and a manifold. The valve is operable to regulate an air flow through the duct to the manifold, with the manifold arranged radially outwardly around the casing radially coplanar with the rotor stage.A temperature sensing apparatus is positioned on the rotor casing, radially outwardly of the rotor stage. A controller is operable to regulate the valve in a stepwise manner to provide a variable cooling air flow to the rotor casing. A processor is operable to calculate a correction characteristic in dependence on a comparison between the rotor casing temperature and a predicted rotor casing temperature for a given engine power condition.An engine controller is operable to control the valve in dependence on the correction characteristic to maintain a predetermined operational radial clearance between the rotor stage and the rotor casing.