公开(公告)号：US20240210039A1

公开(公告)日：2024-06-27

申请号：US18337477

申请日：2023-06-20

Applicant: ROLLS-ROYCE PLC

Inventor： Christopher P MADDEN ,  David M BEAVEN ,  Craig W BEMMENT ,  Paul W FERRA ,  Barani P GUNASEKARAN ,  Benjamin J KEELER ,  Peter SWANN ,  Martin K YATES

IPC: F23R3/34 ,  F02C7/22 ,  F23K5/08

CPC classification number: F23R3/346 ,  F02C7/22 ,  F23K5/08 ,  F05D2240/35 ,  F23K2300/204

Abstract: There is provided a method of operating a gas turbine engine. The gas turbine engine comprises a staged combustor having an arrangement of fuel spray nozzles in which fuel flow is biased to a subset of the nozzles adjacent one or more ignitors during a re-light procedure. The method comprises transferring heat from the oil to the fuel before the fuel enters the combustor so as to lower the fuel viscosity to 0.58 mm2/s or lower on entry to the combustor at cruise conditions. Also disclosed is a gas turbine engine.

公开(公告)号：US20240210038A1

公开(公告)日：2024-06-27

申请号：US18211793

申请日：2023-06-20

Applicant: ROLLS-ROYCE PLC

Inventor： Christopher P MADDEN ,  Craig W BEMMENT ,  Paul W FERRA ,  Benjamin J KEELER ,  Andrea MINELLI ,  Peter SWANN ,  Martin K YATES

IPC: F23R3/34 ,  F02C7/224 ,  F23K5/08

CPC classification number: F23R3/346 ,  F02C7/224 ,  F23K5/08 ,  F23K2300/204

Abstract: A method of operating a gas turbine engine having a lean burn staged combustion system having a combustor in which fuel is combusted. The gas turbine engine includes a fuel-oil heat exchanger arranged to transfer heat between oil and fuel that is provided to the combustor. The method includes transferring heat from the oil to the fuel before the fuel enters the combustor so as to lower the fuel viscosity to 0.58 mm2/s or lower on entry to the combustor at cruise conditions.

公开(公告)号：US20230332548A1

公开(公告)日：2023-10-19

申请号：US18208077

申请日：2023-06-09

Applicant: ROLLS-ROYCE plc

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

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

CPC classification number: F02C9/26 ,  B64D27/10 ,  F02C7/22 ,  B64D37/30 ,  F05D2220/323

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：US20230296060A1

公开(公告)日：2023-09-21

申请号：US18324619

申请日：2023-05-26

Applicant: ROLLS-ROYCE plc

Inventor： Peter SWANN ,  Craig W BEMMENT ,  Alastair G HOBDAY ,  Benjamin J KEELER ,  Christopher P MADDEN

IPC: F02C9/28 ,  B64D37/04 ,  G08G5/00 ,  B64D27/10

CPC classification number: F02C9/28 ,  B64D37/04 ,  G08G5/0034 ,  B64D27/10

Abstract: A method of operating an aircraft including a gas turbine engine and a plurality of fuel tanks arranged to provide fuel to the gas turbine engine. At least two of the fuel tanks contain fuels with different fuel characteristics. The method includes obtaining a flight profile for a portion of a flight of the aircraft; and determining a fueling schedule for the portion of the flight based on the flight profile and the fuel characteristics, the fueling schedule governing the variation with time of how much fuel is drawn from each tank. Fuel input to the gas turbine engine may then be controlled in operation in accordance with the fueling schedule.

公开(公告)号：US20230080006A1

公开(公告)日：2023-03-16

申请号：US17896467

申请日：2022-08-26

Applicant: ROLLS-ROYCE plc

Inventor： Peter SWANN ,  Christopher P MADDEN

IPC: F02C9/48

Abstract: A gas turbine engine comprising a variable geometry combustor having pilot fuel injectors and main fuel injectors; a fuel metering system configured to control fuel flow to the pilot fuel injectors and the main fuel injectors; a variable geometry airflow arrangement for the variable geometry combustor, which is configured to vary the airflow through the pilot fuel injectors and/or the main fuel injectors; a control system configured to control the variable geometry airflow arrangement in dependence upon airflow delivered to the combustor, the fuel flow to the pilot fuel injectors and the main fuel injectors, and a target index of soot emissions, thereby controlling airflow through the pilot fuel injectors and/or the main fuel injectors and hence the quantity of soot produced by combustion.

公开(公告)号：US20230072621A1

公开(公告)日：2023-03-09

申请号：US17896442

申请日：2022-08-26

Applicant: ROLLS-ROYCE plc

Inventor： Peter SWANN ,  Christopher P MADDEN

IPC: F02C9/54

Abstract: A gas turbine engine comprising a variable geometry combustor having fuel injectors, a rich-burn zone, a quick-quench zone, and a lean-burn zone, and further comprising quench ports for admitting quench air to the quick-quench zone; a variable geometry airflow arrangement for the variable geometry combustor, which is configured to vary an airflow through the fuel injectors and/or the quench ports; and a control system configured to control the variable geometry airflow arrangement in dependence upon an airflow delivered to the combustor, a fuel flow to the fuel injectors, and a target index of soot emissions to control the quantity of soot produced by combustion.