Patents Assigned to Rolls-Royce plc
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Publication number: 20200052552Abstract: An engine system comprises first and second electrical generators coupled to lower and higher pressure (LP, HP) shafts respectively of a gas turbine engine. A controller is arranged to receive a signal corresponding to a total electrical power demand P1 and to output control signals to the electrical generators in response thereto such that the first and second electrical generators output electrical powers (1?y)P1 and yP1 respectively when P1?Pm1, where 0.5<y?1 and Pm1 is the maximum electrical output power of the first electrical generator. By satisfying the demand P1 mostly by extraction of electrical power from the first electrical generator when possible, the additional mechanical stress on the gas turbine engine resulting from electrical power extraction is reduced compared to the case where 50% or more of the demand P1 is satisfied by the second electrical generator.Type: ApplicationFiled: July 19, 2019Publication date: February 13, 2020Applicant: ROLLS-ROYCE plcInventors: Stephen M. HUSBAND, Gian INCERPI
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Publication number: 20200049065Abstract: A gas turbine engine is highly efficient. The fan of the gas turbine engine is driven from a turbine via a gearbox, such that the fan has a lower rotational speed than the driving turbine, thereby providing efficiency gains. The efficient fan system is mated to a core that has low cooling flow requirements and/or high temperature capability, and which may have particularly low mass for a given power.Type: ApplicationFiled: May 14, 2019Publication date: February 13, 2020Applicant: ROLLS-ROYCE plcInventors: Michael J WHITTLE, Roderick M TOWNES, Pascal DUNNING
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Publication number: 20200049104Abstract: A highly efficient gas turbine engine is provided. The fan of the gas turbine engine is driven from a turbine via a gearbox, such that the fan has a lower rotational speed than the driving turbine, thereby providing efficiency gains. The efficient fan system is mated to a core that has low cooling flow requirements and/or high temperature capability, and which may have particularly low mass for a given power.Type: ApplicationFiled: May 28, 2019Publication date: February 13, 2020Applicant: ROLLS-ROYCE plcInventors: Roderick M. TOWNES, Pascal DUNNING, Michael J. WHITTLE
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Publication number: 20200049066Abstract: A highly efficient gas turbine engine is provided. The fan of the gas turbine engine is driven from a turbine via a gearbox, such that the fan has a lower rotational speed than the driving turbine, thereby providing efficiency gains. The efficient fan system is mated to a core that has low cooling flow requirements and/or high temperature capability, and which may have particularly low mass for a given power.Type: ApplicationFiled: May 14, 2019Publication date: February 13, 2020Applicant: ROLLS-ROYCE plcInventors: Pascal DUNNING, Roderick M. TOWNES, Michael J WHITTLE
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Publication number: 20200049063Abstract: A highly efficient gas turbine engine includes a fan which is driven from a turbine via a gearbox, such that the fan has a lower rotational speed than the driving turbine, thereby providing efficiency gains. The efficient fan system is mated to a core that has low cooling flow requirements and/or high temperature capability, and which may have particularly low mass for a given power.Type: ApplicationFiled: April 30, 2019Publication date: February 13, 2020Applicant: ROLLS-ROYCE PLCInventors: Michael J WHITTLE, Pascal DUNNING, Roderick M TOWNES
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Publication number: 20200049072Abstract: A highly efficient gas turbine engine includes a fan which is driven from a turbine via a gearbox, such that the fan has a lower rotational speed than the driving turbine, which results in efficiency gains. The efficient fan system is mated to a core that has low cooling flow requirements and/or high temperature capability, and which may have particularly low mass for a given power.Type: ApplicationFiled: July 31, 2019Publication date: February 13, 2020Applicant: ROLLS-ROYCE PLCInventors: Michael J. WHITTLE, Pascal DUNNING, Roderick M. TOWNES
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Publication number: 20200049064Abstract: A highly efficient gas turbine engine includes the fan of the gas turbine engine driven from a turbine via a gearbox, such that the fan has a lower rotational speed than the driving turbine, thereby providing efficiency gains. The efficient fan system is mated to a core that has low cooling flow requirements and/or high temperature capability, and which may have particularly low mass for a given power.Type: ApplicationFiled: May 14, 2019Publication date: February 13, 2020Applicant: ROLLS-ROYCE plcInventors: Pascal DUNNING, Michael J. WHITTLE, Roderick M. TOWNES
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Publication number: 20200049071Abstract: Apparatus for a gas turbine engine, the apparatus comprising: an engine core; a nacelle; and thermal energy transfer apparatus configured to transfer thermal energy from the engine core to the nacelle.Type: ApplicationFiled: August 1, 2019Publication date: February 13, 2020Applicant: ROLLS-ROYCE plcInventors: Edward John HEENEN, Michael J. SHEATH, Neil J. DAVIES
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Publication number: 20200049070Abstract: A highly efficient gas turbine engine is a system wherein the fan of the gas turbine engine is driven from a turbine via a gearbox, such that the fan has a lower rotational speed than the driving turbine, thereby providing efficiency gains. The efficient fan system is mated to a core that has low cooling flow requirements and/or high temperature capability, and which may have particularly low mass for a given power.Type: ApplicationFiled: May 14, 2019Publication date: February 13, 2020Applicant: ROLLS-ROYCE plcInventors: Roderick M. TOWNES, Michael J. WHITTLE, Pascal DUNNING
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Publication number: 20200049021Abstract: A highly efficient gas turbine engine includes a fan driven from a turbine via a gearbox, such that the fan has a lower rotational speed than the driving turbine, thereby providing efficiency gains. The efficient fan system is mated to a core that has low cooling flow requirements and/or high temperature capability, and which may have particularly low mass for a given power.Type: ApplicationFiled: May 28, 2019Publication date: February 13, 2020Applicant: ROLLS-ROYCE plcInventors: Roderick M. TOWNES, Pascal DUNNING, Michael J. WHITTLE
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Publication number: 20200047871Abstract: An aircraft has an internal combustion engine and a wing including a hollow structural member. The aircraft has an electrical network including: an electrical motor configured to drive an aircraft propulsor; at least one conductor configured to electrically couple the electrical motor and an electrical storage device; wherein the electrical conductor is formed of the hollow structural member of the aircraft wing.Type: ApplicationFiled: October 21, 2019Publication date: February 13, 2020Applicant: ROLLS-ROYCE plcInventor: Matthew MOXON
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Publication number: 20200049067Abstract: A highly efficient gas turbine engine has a fan that is driven from a turbine via a gearbox, such that the fan has a lower rotational speed than the driving turbine, thereby providing efficiency gains. The efficient fan system is mated to a core that has low cooling flow requirements and/or high temperature capability, and which may have particularly low mass for a given power.Type: ApplicationFiled: May 28, 2019Publication date: February 13, 2020Applicant: ROLLS-ROYCE plcInventors: Roderick M TOWNES, Pascal DUNNING, Michael J WHITTLE
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Patent number: 10557369Abstract: The invention provides a drain to allow water to flow out of a pressure sensing line. The drain comprises a tube including a plurality of restrictors in flow series, each restrictor comprising a constriction whose internal diameter is less than the internal diameter of the tube.Type: GrantFiled: April 20, 2016Date of Patent: February 11, 2020Assignee: ROLLS-ROYCE plcInventor: Annegret W Siebert
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Patent number: 10557629Abstract: A steam generator comprising a vessel having an inlet and an outlet, and in use a primary fluid flow enters the vessel through the inlet and exits the vessel through the outlet. A plurality of modules are connected in series and at least partially housed within the vessel, and each module comprises at least one tube. The modules are arranged such that at least one tube of one module is coaxial with at least one tube of an adjacent module so as to define a conduit through which a secondary fluid can flow from one module to an adjacent module.Type: GrantFiled: January 21, 2015Date of Patent: February 11, 2020Assignees: ROLLS-ROYCE plc, ROLLS-ROYCE POWER ENGINEERING plcInventors: Ian Michael Bunce, Nigel Alastair Town, Mark Alwyn Thomas Causton, Matthew Charles Blake, David William Mills
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Publication number: 20200040845Abstract: An aircraft gas turbine engine includes a compressor system including a low pressure compressor coupled to a low pressure shaft, and a high pressure compressor coupled to a high pressure shaft. An inner core casing is provided radially inwardly of compressor blades of the compressor system. A fan is coupled to the low pressure shaft via a reduction gearbox. The high pressure compressor includes an outer core casing arrangement provided radially outwardly of compressor blades of the high pressure compressor, the inner and outer core casing arrangements defining a core working gas flow path therebetween; and the outer core casing arrangement includes a first and a second outer core casing spaced radially outward from the first outer core casing. At an axial plane of an inlet to the high pressure compressor, the second outer core casing has a radius greater than 0.25 times a radius of the fan.Type: ApplicationFiled: April 30, 2019Publication date: February 6, 2020Applicant: ROLLS-ROYCE plcInventor: Andrew SWIFT
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Publication number: 20200040824Abstract: A crankshaft assembly for a gas turbine engine guide vane actuator. Example embodiments include a crankshaft assembly for a gas turbine engine guide vane actuator, the crankshaft assembly comprising: a crankshaft mounted for rotation about a central axis; a lug mounted to the crankshaft for rotation with the crankshaft about the central axis, the lug having a first end with a crankshaft connection securing the lug to the crankshaft and a second opposing end for connecting the lug to a control rod such that rotation of the crankshaft causes actuation of the control rod in a direction orthogonal to the central axis, wherein the crankshaft connection is adjustable to allow the first end of the lug to be secured relative to the crankshaft over a range of rotational positions about the central axis.Type: ApplicationFiled: July 10, 2019Publication date: February 6, 2020Applicant: ROLLS-ROYCE plcInventors: Neelambaran KARAPURATH, Andrew B. SWANN
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Patent number: 10550700Abstract: A gas turbine engine that has improved fuel burn provides operability and/or maintenance requirements when installed on an aircraft. The gas turbine engine is provided with a core compressor that includes twelve, thirteen or fourteen rotor stages. The gas turbine engine has a ratio of a core compressor aspect ratio divided by a core compressor pressure ratio is in the range of from 0.03 to 0.09. This results in an optimum balance between installation benefits, operability, maintenance requirements and engine efficiency when the gas turbine engine is installed on an aircraft.Type: GrantFiled: June 11, 2019Date of Patent: February 4, 2020Assignee: ROLLS-ROYCE plcInventors: Nicholas Howarth, Gareth M Armstrong
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Patent number: 10550709Abstract: A blade track assembly is disclosed. The blade track assembly comprises a plurality of ceramic matrix composite blade track segments arranged circumferentially adjacent to one another around a central axis. Each of the blade track segments includes an arcuate runner extending in a circumferential direction around a portion of the central axis and is coupled to circumferentially adjacent blade track segments.Type: GrantFiled: April 1, 2016Date of Patent: February 4, 2020Assignees: Rolls-Royce North American Technologies Inc., Rolls-Royce Corporation, Rolls-Royce plc, Rolls-Royce High Temperature Composites Inc.Inventors: Daniel K. Vetters, Aaron D. Sippel, David J. Thomas, Andrew J. Eifert, Paul A. Davis, Simon L. Jones, Steven M. Hillier, Peter Broadhead, Joseph Doyle, Michael Jacquinto, Wesley Thibault, Jun Shi, Roderick Townes
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Publication number: 20200032674Abstract: An aircraft gas turbine engine includes an engine core including a turbine, a compressor, a core shaft connecting the turbine to compressor, and a core casing surrounding the engine core. A fan is located upstream of the engine core and fan casing surrounds the fan. A gearbox receives input from the core shaft and outputs drive to rotate the fan. A single plane support structure connects the core and fan casing. The support structure includes an inner ring, outer ring and plurality of circumferentially spaced radially extending struts connecting the inner and outer ring. The inner ring including a torsion box and a gearbox and fan support structure is connected to the torsion box. A front and rear mount are configured to connect the gas turbine engine to the aircraft, wherein the front mount is coupled to the torque box and the rear mount is coupled to the core casing.Type: ApplicationFiled: June 26, 2019Publication date: January 30, 2020Applicant: ROLLS-ROYCE plcInventor: Andrew SWIFT
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Patent number: 10547258Abstract: An electric machine coupled to rotating machinery includes a rotor and a stator, and the method of control of an electric machine and an electric machine control system. The method includes sensing one or more parameters indicative of one or more resonance conditions of the rotating machinery, and comparing the sensed parameter to a predetermined threshold to determine whether the rotating machinery is operating at the resonance condition. Where the rotating machinery is determined to be operating at the resonance condition, adjusting a magnetic field of one or both of the rotor and the stator to provide a predetermined torque to the rotating machine, to modulate the stiffness of the rotational machinery, and thereby move the resonance condition away from the current rotating machinery conditions.Type: GrantFiled: October 31, 2018Date of Patent: January 28, 2020Assignees: ROLLS-ROYCE plc, ROLLS-ROYCE DEUTSCHLAND LTD & CO KGInventors: Lucia Ciciriello, Kevin Smith
