公开(公告)号：US12152542B2

公开(公告)日：2024-11-26

申请号：US18328991

申请日：2023-06-05

Applicant: ROLLS-ROYCE plc

Inventor： Peter Swann ,  David M. Beaven ,  Craig W. Bemment ,  Alastair G. Hobday ,  Benjamin J. Keeler ,  Christopher P. Madden ,  Martin K. Yates

IPC: F02C9/40 ,  F02C9/28

Abstract: The present application provides a method of determining one or more fuel characteristics of an aviation fuel suitable for powering a gas turbine engine of an aircraft. The method includes: passing UV-visual spectrum light through the fuel; measuring a transmittance parameter indicating the transmittance of light through the fuel; determining one or more fuel characteristics of the fuel based on the transmittance parameter; and communicating the one or more fuel characteristic to a control module of the gas turbine engine or the aircraft. Also disclosed is a fuel characteristic determination system, a method of operating an aircraft, and an aircraft.

公开(公告)号：US20240301829A1

公开(公告)日：2024-09-12

申请号：US18663599

申请日：2024-05-14

Applicant: ROLLS-ROYCE plc

Inventor： Craig W BEMMENT ,  Benjamin J. Keeler ,  Christopher P. Madden ,  Andrea Minelli ,  Peter Swann ,  Martin K. Yates

IPC: F02C7/14 ,  F02C7/06 ,  F02C7/10 ,  F02C7/224 ,  F02C7/36

CPC classification number: F02C7/14 ,  F02C7/06 ,  F02C7/10 ,  F02C7/224 ,  F02C7/36 ,  F05D2220/323 ,  F05D2260/205 ,  F05D2260/213 ,  F05D2260/98

Abstract: A gas turbine engine includes an engine core with a combustor; a turbine including turbine blades; a compressor as a source of cooling air for the turbine blades; and an inducer to accelerate and direct the cooling air onto the turbine blades, and a modulating valve to allow or block cooling air flow into a subset of airflow passageways of the inducer; and a fuel management system to provide fuel to the combustor. The fuel management system includes a primary fuel-oil heat exchanger and a secondary fuel-oil heat exchanger through which oil and the fuel flow, to transfer heat between the oil and the fuel. A method of operating the engine includes using the modulating valve to adjust the cooling air flow based on turbine inlet temperature; and transferring 200-600 kJ/m3 of heat to the fuel from the oil in the primary fuel-oil heat exchanger at cruise conditions.

公开(公告)号：US20240263582A1

公开(公告)日：2024-08-08

申请号：US18634305

申请日：2024-04-12

Applicant: Rolls-Royce plc

Inventor： Craig W. BEMMENT ,  Alastair G. Hobday ,  Benjamin J. Keeler ,  Christopher P. Madden ,  Andrea Minelli ,  Andrew T. Smith ,  Peter Swann ,  Martin K. Yates

IPC: F02C7/14 ,  F02C7/224 ,  F02C7/36

CPC classification number: F02C7/14 ,  F02C7/224 ,  F02C7/36 ,  F05D2220/323 ,  F05D2260/213

Abstract: A method of operating a gas turbine engine including an engine core including a turbine, compressor, combustor to combust a fuel, and core shaft connecting the turbine and compressor; a fan upstream of the engine core; a fan shaft; a gearbox that receives an input from the core shaft and outputs drive to the fan via the fan shaft; a primary oil loop system to supply oil to the gearbox; and a heat exchange system. The method includes controlling the heat exchange system to adjust fuel viscosity to be lower than or equal to 0.58 mm2/s on entry to the combustor at cruise conditions.

公开(公告)号：US20240376845A1

公开(公告)日：2024-11-14

申请号：US18777670

申请日：2024-07-19

Applicant: ROLLS-ROYCE plc

Inventor： Craig W. BEMMENT ,  Benjamin J. Keeler ,  Kevin R. McNally ,  Andrea Minelli

IPC: F02C7/14 ,  F02C7/36 ,  F23K5/20

Abstract: A method of operating a gas turbine engine, the gas turbine engine including an engine core comprising a turbine, a compressor, a combustor arranged to combust a fuel, and a core shaft connecting the turbine to the compressor; a fan located upstream of the engine core; a fan shaft; a main gearbox that receives an input from the core shaft and outputs drive to the fan via the fan shaft; a primary oil loop system arranged to supply oil to lubricate the main gearbox; and a heat exchange system arranged to transfer heat between the oil and the fuel, the oil having an average temperature of at least 180° C. on entry to the heat exchange system at cruise conditions. The method includes controlling the heat exchange system so as to raise the fuel temperature to at least 135° C. on entry to the combustor at cruise conditions.

公开(公告)号：US20240287937A1

公开(公告)日：2024-08-29

申请号：US18657237

申请日：2024-05-07

Applicant: ROLLS-ROYCE plc

Inventor： Craig W. BEMMENT ,  Alastair G. Hobday ,  Benjamin J. Keeler ,  Andrea Minelli ,  Andrew T. Smith ,  Martin K. Yates

IPC: F02C7/224 ,  F02C7/14 ,  F02C7/32

CPC classification number: F02C7/224 ,  F02C7/14 ,  F02C7/32 ,  F05D2260/20

Abstract: A method of operating a gas turbine engine having an engine core having a turbine, a compressor, a combustor arranged to combust a fuel, and a core shaft connecting the turbine to the compressor; a fan located upstream of the engine core; a fan shaft; a gearbox that receives an input from the core shaft and outputs drive to the fan via the fan shaft; a heat exchange system having at least one fuel-oil heat exchanger arranged to transfer heat to the fuel; and a fuel pump arranged to deliver the fuel to the combustor, wherein the fuel pump is located downstream of the at least one fuel-oil heat exchanger. The method comprises controlling the heat exchange system so as to raise the fuel temperature to at least 135° C. on entry to the combustor at cruise conditions.