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：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.