Patents Assigned to Rolls-Royce plc
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Patent number: 11149652Abstract: Gearboxes for aircraft gas turbine engines, in particular to arrangements for journal bearings such gearboxes, and to related methods of operating such gearboxes and gas turbine engines. Example embodiments include a gearbox for an aircraft gas turbine engine, the gearbox including: a sun gear; a plurality of planet gears surrounding and engaged with the sun gear; and a ring gear surrounding and engaged with the plurality of planet gears, each of the plurality of planet gears being rotatably mounted around a pin of a planet gear carrier with a journal bearing having an internal sliding surface on the planet gear and an external sliding surface on the pin.Type: GrantFiled: August 18, 2020Date of Patent: October 19, 2021Assignee: ROLLS-ROYCE PLCInventor: Mark Spruce
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Patent number: 11152844Abstract: An electric machine including a stator having a fully non-magnetic core and stator windings formed of a non-superconducting transposed conductor to reduce eddy current losses. It further includes a rotor having a fully non-magnetic core and superconducting windings or superconducting magnets which produce a magnetic field for interaction with the stator windings. A cryogenic cooling system is arranged to cool the stator windings to reduce conduction losses in the stator windings.Type: GrantFiled: August 22, 2019Date of Patent: October 19, 2021Assignee: ROLLS-ROYCE plcInventors: Paul R Miller, Stephen M Husband, Alexander C Smith, Charalampos Manolopoulos, Matteo Iacchetti
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Patent number: 11143112Abstract: An engine for an aircraft comprises an engine core comprising a turbine, a compressor, and a core shaft connecting the turbine to the compressor; a fan located upstream of the engine core, the fan comprising a plurality of fan blades; and a gearbox. The gearbox is an epicyclic gearbox and comprises a sun gear, a plurality of planet gears, a ring gear, and a planet carrier on which the planet gears are mounted. The radial bending stiffness of the planet carrier is equal to or greater than 1.20×109 N/m, and/or the tilt stiffness of the planet carrier is greater than or equal to 6.00×108 Nm/rad. A method of operation of such an engine is also disclosed.Type: GrantFiled: December 11, 2020Date of Patent: October 12, 2021Assignee: ROLLS-ROYCE plcInventor: Mark Spruce
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Patent number: 11146382Abstract: Method and system for cryptographic transformation of a structured data set. The structured data set is partitioned into a first subset and a plurality of further subsets for encryption in parallel. The subsets are divided into a plurality of blocks of predetermined size. A first block for each subset is identified as well as a location of each further block in said subset relative to said first block of its subset. Cryptographic transformation of the data subsets is performed using a key according to a block chain process and an offset value for the first block of each subset from the first block of the first subset is logged. The process allows a block chain to be broken into part way in the chain. The process may allow different partitioning to be used for decryption than was used for encryption, thereby allowing parallel processing on varying numbers of computational cores.Type: GrantFiled: April 23, 2019Date of Patent: October 12, 2021Assignee: ROLLS-ROYCE PLCInventor: Bryan L. Lapworth
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Patent number: 11143101Abstract: A gas turbine engine for an aircraft has an engine core comprising turbine, compressor, and core shaft connecting the turbine to the compressor, the turbine being the lowest pressure turbine of the engine, and having turbine blades, and the compressor being the lowest pressure compressor of the engine; fan located upstream of the engine core; and gearbox that receives an input from the core shaft and outputs drive to the fan. The engine core further has three bearings arranged to support the core shaft, the three bearings having two rearward bearings located downstream of the leading edge of the lowest pressure turbine blade of the turbine at the root of the blade, and/or, when the turbine comprises four sets of turbine blades, downstream of the trailing edge of a turbine blade of the third set of turbine blades from the front of the turbine, at the root of the blade.Type: GrantFiled: February 20, 2020Date of Patent: October 12, 2021Assignee: ROLLS-ROYCE plcInventors: Chathura K Kannangara, Jillian C Gaskell, Punitha Kamesh
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Publication number: 20210310419Abstract: Gearboxes for aircraft gas turbine engines, in particular arrangements for journal bearings such gearboxes, and related methods of operating such gearboxes and gas turbine engines. A gearbox for an aircraft gas turbine engine includes: a sun gear; a plurality of planet gears surrounding and engaged with the sun gear; and a ring gear surrounding and engaged with the plurality of planet gears, each of the plurality of planet gears being rotatably mounted around a pin of a planet gear carrier with a journal bearing having an internal sliding surface on the planet gear and an external sliding surface on the pin.Type: ApplicationFiled: March 10, 2021Publication date: October 7, 2021Applicant: ROLLS-ROYCE PLCInventor: Mark SPRUCE
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Publication number: 20210310420Abstract: Gearboxes for aircraft gas turbine engines, in particular arrangements for journal bearings such gearboxes, and related methods of operating such gearboxes and gas turbine engines, including a gearbox for an aircraft gas turbine engine, the gearbox including: a sun gear; a plurality of planet gears surrounding and engaged with the sun gear; and a ring gear surrounding and engaged with the plurality of planet gears, each of the plurality of planet gears being rotatably mounted around a pin of a planet gear carrier with a journal bearing having an internal sliding surface on the planet gear and an external sliding surface on the pin.Type: ApplicationFiled: April 6, 2021Publication date: October 7, 2021Applicant: ROLLS-ROYCE PLCInventor: Mark SPRUCE
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Publication number: 20210310407Abstract: A gas turbine engine for an aircraft comprises an engine core comprising a turbine, a compressor, and a core shaft connecting the turbine to the compressor, wherein a compressor exit temperature is defined as an average temperature of airflow at the exit from the compressor; and a fan located upstream of the engine core, the fan comprising a plurality of fan blades extending from a hub, each fan blade having a leading edge and a trailing edge, wherein a fan rotor entry temperature is defined as an average temperature of airflow across the leading edge of each fan blade at cruise conditions and a fan tip rotor exit temperature is defined as an average temperature of airflow across a radially outer portion of each fan blade at the trailing edge at cruise conditions. A core to fan tip temperature rise ratio is in the range from 2.845 to 3.8.Type: ApplicationFiled: June 11, 2021Publication date: October 7, 2021Applicant: ROLLS-ROYCE PLCInventors: Craig W BEMMENT, Pascal DUNNING
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Publication number: 20210310408Abstract: 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: June 11, 2021Publication date: October 7, 2021Applicant: ROLLS-ROYCE plcInventors: Pascal DUNNING, Michael J. WHITTLE, Roderick M. TOWNES
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Publication number: 20210310418Abstract: Gearboxes for aircraft gas turbine engines, in particular arrangements for journal bearings such gearboxes, and related methods of operating such gearboxes and gas turbine engines. A gearbox for an aircraft gas turbine engine includes: a sun gear; a plurality of planet gears surrounding and engaged with the sun gear; and a ring gear surrounding and engaged with the plurality of planet gears, each of the plurality of planet gears being rotatably mounted around a pin of a planet gear carrier with a journal bearing having an internal sliding surface on the planet gear and an external sliding surface on the pin.Type: ApplicationFiled: March 10, 2021Publication date: October 7, 2021Applicant: ROLLS-ROYCE PLCInventor: Mark SPRUCE
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Publication number: 20210310373Abstract: Gearboxes for aircraft gas turbine engines, in particular to arrangements for journal bearings such gearboxes, and to related methods of operating such gearboxes and gas turbine engines. Example embodiments include a gearbox for an aircraft gas turbine engine, the gearbox including: a sun gear; a plurality of planet gears surrounding and engaged with the sun gear; and a ring gear surrounding and engaged with the plurality of planet gears, each of the plurality of planet gears being rotatably mounted around a pin of a planet gear carrier with a journal bearing having an internal sliding surface on the planet gear and an external sliding surface on the pin.Type: ApplicationFiled: March 18, 2021Publication date: October 7, 2021Applicant: ROLLS-ROYCE plcInventor: Mark SPRUCE
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Publication number: 20210308793Abstract: A method of joining first and second component bodies comprises: cold-spraying a first joining surface of the first component body with a bond material which is harder than the first joining surface; cold-spraying a second joining surface of the second component body with the bond material; and joining the first and second component bodies by way of the first joining surface.Type: ApplicationFiled: March 25, 2021Publication date: October 7, 2021Applicant: ROLLS-ROYCE plcInventors: Iulian MARINESCU, Adrian W Y TAN, Erjia LIU, Feng LI, Wen SUN
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Publication number: 20210310416Abstract: Gearboxes for aircraft gas turbine engines, in particular to arrangements for journal bearings such gearboxes, and to related methods of operating such gearboxes and gas turbine engines. Example embodiments include a gearbox for an aircraft gas turbine engine, the gearbox including: a sun gear; a plurality of planet gears surrounding and engaged with the sun gear; and a ring gear surrounding and engaged with the plurality of planet gears, each of the plurality of planet gears being rotatably mounted around a pin of a planet gear carrier with a journal bearing having an internal sliding surface on the planet gear and an external sliding surface on the pin.Type: ApplicationFiled: August 18, 2020Publication date: October 7, 2021Applicant: ROLLS-ROYCE PLCInventor: Mark SPRUCE
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Patent number: 11136893Abstract: Disclosed herein is a gimbal body comprising: an end part (51) for use in welding the gimbal body to a pipe; and a main body (53) attached to the end part (51); wherein: the end part (51) is made of a first material; and the main body (53) is made of a second material that is different from the first material. Embodiments provide a new method of manufacturing a gimbal that allows the use of the most appropriate materials for high temperature and high pressure performance whilst overcoming manufacturing and installation problems experienced by known gimbals constructed with such materials.Type: GrantFiled: May 8, 2019Date of Patent: October 5, 2021Assignee: ROLLS-ROYCE PLCInventor: Richard N. March
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Patent number: 11136922Abstract: A gas turbine engine for an aircraft includes an engine core including a first, lower pressure, turbine, a first compressor, and a first core shaft connecting the first turbine to the first compressor; and a second, higher pressure, turbine, a second compressor, and a second core shaft connecting the second turbine to the second compressor, and a fan located upstream of the engine core and including a plurality of fan blades extending from a hub. A low pressure turbine temperature change is defined as: the ? ? first ? ? turbine ? ? entrance ? ? temperature the ? ? first ? ? turbine ? ? exit ? ? temperature . A fan tip temperature rise is defined as: the ? ? fan ? ? tip ? ? rotor ? ? exit ? ? temperature the ? ? fan ? ? rotor ? ? entry ? ? temperature .Type: GrantFiled: August 20, 2019Date of Patent: October 5, 2021Assignee: ROLLS-ROYCE plcInventors: Craig W Bemment, Pascal Dunning
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Patent number: 11139716Abstract: 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: GrantFiled: July 19, 2019Date of Patent: October 5, 2021Assignee: Rolls-Royce PLCInventors: Stephen M. Husband, Gian Incerpi
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Publication number: 20210301763Abstract: A gas turbine engine including an engine core with high and low pressure compressors and high and low pressure turbines, the high pressure compressor and high pressure turbine being coupled by a high pressure shaft, and the low pressure compressor and low pressure turbine being coupled by a low pressure shaft, the engine further including a fan coupled to the low pressure shaft by a reduction gearbox. The high pressure compressor consists of 8 or 9 stages and has an average stage loading at cruise conditions of between 1.39 and 1.42, and the low and high pressure compressor together define an overall core pressure ratio at cruise conditions of between 40 and 60.Type: ApplicationFiled: March 9, 2021Publication date: September 30, 2021Applicant: ROLLS-ROYCE PLCInventors: Ian J BOUSFIELD, Michael O. HALES
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Publication number: 20210301718Abstract: A gas turbine engine (10) comprising: a high pressure turbine (17); a low pressure turbine (19); a high pressure compressor (15) coupled to the high pressure turbine (17) by a high pressure shaft (27); a propulsor (23) and a low pressure compressor (14) coupled to the low pressure turbine (19) via a low pressure shaft (26) and a reduction gearbox (30); wherein the low pressure compressor (14) consists of four compressor stages (14) and defines a cruise pressure ratio of between 2.4:1 and 3.3:1; the high pressure compressor (15) defines a cruise pressure ratio of less than 17:1; and the high pressure compressor (15) and low pressure compressor (14) together define a cruise core overall pressure ratio of greater than 36:1.Type: ApplicationFiled: March 9, 2021Publication date: September 30, 2021Applicant: ROLLS-ROYCE plcInventors: Michael O. HALES, Craig W. BEMMENT, Benjamin J. SELLERS, Ian J. BOUSFIELD, Amarveer S. MANN
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Publication number: 20210301719Abstract: A gas turbine engine including: a high pressure turbine, a low pressure turbine, a high pressure compressor coupled to the high pressure turbine by a high pressure shaft, a propulsor and a low pressure compressor coupled to the low pressure turbine via a low pressure shaft and a reduction gearbox; wherein the high pressure compressor defines an average stage pressure ratio at cruise conditions of between 1.25 and 1.35 and consists of 10 or 11 stages; and the high pressure compressor and low pressure compressor together define a core overall pressure ratio at cruise conditions of between 40:1 and 60:1.Type: ApplicationFiled: March 9, 2021Publication date: September 30, 2021Applicant: ROLLS-ROYCE PLCInventors: Ian J BOUSFIELD, Michael O HALES, Rory D STIEGER
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Publication number: 20210301764Abstract: A gas turbine engine includes an engine core having high and low pressure compressors and high and low pressure turbines. The engine further includes a fan coupled to a low pressure shaft and the low pressure turbine by a reduction gearbox. The low pressure compressor includes no more than two compressor stages, and the low and high pressure compressor together define a cruise overall core pressure ratio of between 30 and 50.Type: ApplicationFiled: March 9, 2021Publication date: September 30, 2021Applicant: ROLLS-ROYCE PLCInventor: Rory D STIEGER
