公开(公告)号：US11859565B2

公开(公告)日：2024-01-02

申请号：US17853333

申请日：2022-06-29

Applicant: ROLLS-ROYCE PLC

Inventor： Benjamin J Keeler ,  David M Beaven ,  Craig W Bemment ,  Paul W Ferra ,  Kevin R Mcnally ,  Andrea Minelli ,  Martin K Yates

IPC: F02C9/28

CPC classification number: F02C9/28 ,  F05D2220/323 ,  F05D2240/35 ,  F05D2270/303 ,  F05D2270/309 ,  F05D2270/3013

Abstract: A gas turbine engine includes: a combustor that combust the fuel and having an exit, a combustor exit temperature (T40) is the average temperature of flow and a combustor exit pressure (P40) is the total pressure there; a turbine including a rotor having a leading edge and a trailing edge, and wherein a turbine rotor entry temperature (T41) is an average temperature of flow at the leading edge and a turbine rotor entry pressure (P41) is the total pressure there; and a compressor having an exit, wherein a compressor exit temperature (T30) is the average temperature of flow at the exit from the compressor and a compressor exit pressure (P30) is the total pressure there (all at cruise conditions). A method of determining at least one fuel characteristic includes changing a fuel supplied to the engine; and determining a change in a relationship between T30 or P30, T40 and T41, or of P40 and P41, respectively.

公开(公告)号：US12281614B1

公开(公告)日：2025-04-22

申请号：US18753237

申请日：2024-06-25

Applicant: ROLLS-ROYCE plc

Inventor： Andrea Minelli ,  Benjamin J Keeler ,  Craig W Bemment ,  David M Beaven ,  Kevin R Mcnally

IPC: F02C7/14 ,  F02C7/36

Abstract: A method of operating a gas turbine engine including: an engine core with a turbine, compressor, a fuel combustor, and a core shaft connecting the turbine to the compressor; a fan; a gearbox that receives an input from the core shaft and outputs drive to the fan; an oil loop system arranged to supply oil to the gearbox; and a heat exchange system including: an air-oil heat exchanger through which the oil flows; a fuel-oil heat exchanger through which the oil and the fuel flow; a temperature sensor downstream of the fuel-oil heat exchanger; and a valve arranged to allow oil or air flow rate through at least one heat exchanger to be varied, the method including: determining if the fuel temperature has increased above a set threshold at cruise conditions; and in response, controlling the valve so as to change the flow rate through the heat exchanger.

公开(公告)号：US12158438B2

公开(公告)日：2024-12-03

申请号：US17853184

申请日：2022-06-29

Applicant: ROLLS-ROYCE PLC

Inventor： Craig W Bemment ,  Paul W Ferra ,  Alastair G Hobday ,  Benjamin J Keeler ,  Kevin R Mcnally ,  Andrea Minelli ,  Martin K Yates

IPC: G01N25/22 ,  F02C7/22

Abstract: A method of checking refuelling of an aircraft comprising a gas turbine engine and a fuel tank arranged to provide fuel to the gas turbine engine comprises: receiving an input of calorific value data for fuel provided to the aircraft on refuelling; independently determining at least one of: (i) the calorific value of fuel supplied to the gas turbine engine in use; and (ii) the calorific value of the fuel provided to the aircraft on refuelling; and providing an alert if the determined calorific value is inconsistent with the calorific value data input received.