US 12,359,619 B2
Fueldraulic heat management system
Benjamin J Keeler, Chesterfield (GB); Craig W Bemment, Derby (GB); Andrea Minelli, Derby (GB); Alastair G Hobday, Derby (GB); Andrew T Smith, Derby (GB); and Paul W Ferra, Derby (GB)
Assigned to ROLLS-ROYCE plc, London (GB)
Filed by ROLLS-ROYCE PLC, London (GB)
Filed on Jun. 25, 2024, as Appl. No. 18/753,446.
Claims priority of application No. 2319150 (GB), filed on Dec. 14, 2023.
Prior Publication US 2025/0198337 A1, Jun. 19, 2025
Int. Cl. F02C 7/14 (2006.01); F02C 7/224 (2006.01); F02C 7/232 (2006.01)
CPC F02C 7/14 (2013.01) [F02C 7/224 (2013.01); F02C 7/232 (2013.01); F05D 2220/323 (2013.01); F05D 2260/20 (2013.01)] 20 Claims
OG exemplary drawing
 
1. A gas turbine engine for an aircraft comprising:
an engine core comprising a turbine, a combustor, a compressor, and a core shaft connecting the turbine to the compressor;
a fan located upstream of the engine core and arranged to be driven by the core shaft, the fan comprising a plurality of fan blades;
a nacelle surrounding the fan and the engine core and defining a bypass duct located radially outside of the engine core, where the bypass ratio, defined as the ratio of the mass flow rate of the flow through the bypass duct to the mass flow rate of the flow through the core at cruise conditions, is at least 4;
an engine heat management system;
a plurality of actuators, comprising an actuator configured to actuate at least one valve within the engine heat management system;
a controller; and
a fuel supply system, wherein
the fuel supply system is arranged to supply fuel for combustion in the combustor, and to supply fuel to fueldraulically drive the actuator configured to actuate the at least one valve within the engine heat management system,
the actuator configured to actuate the at least one valve within the engine heat management system is configured to actuate the valve so as to enable non-binary position adjustment between an open valve position and a closed valve position, and
the controller is configured to control the actuator so that the non-binary position adjustment is based upon calorific value of the fuel, and
the fuel comprises sustainable aviation fuel with up to 100% of the fuel being the sustainable aviation fuel.