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公开(公告)号：US20210310420A1
公开(公告)日：2021-10-07
申请号：US17223200
申请日：2021-04-06
Applicant: ROLLS-ROYCE PLC
Inventor： Mark SPRUCE
Abstract: 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.
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公开(公告)号：US20210310418A1
公开(公告)日：2021-10-07
申请号：US17197279
申请日：2021-03-10
Applicant: ROLLS-ROYCE PLC
Inventor： Mark SPRUCE
Abstract: 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.
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公开(公告)号：US20210310408A1
公开(公告)日：2021-10-07
申请号：US17345328
申请日：2021-06-11
Applicant: ROLLS-ROYCE plc
Inventor： Pascal DUNNING , Michael J. WHITTLE , Roderick M. TOWNES
Abstract: 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.
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公开(公告)号：US20210310407A1
公开(公告)日：2021-10-07
申请号：US17345588
申请日：2021-06-11
Applicant: ROLLS-ROYCE PLC
Inventor： Craig W BEMMENT , Pascal DUNNING
Abstract: 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.
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公开(公告)号：US11139716B2
公开(公告)日：2021-10-05
申请号：US16516796
申请日：2019-07-19
Applicant: ROLLS-ROYCE plc
Inventor： Stephen M. Husband , Gian Incerpi
Abstract: 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
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Patent Agency Ranking
公开(公告)号：US11136893B2
公开(公告)日：2021-10-05
申请号：US16406560
申请日：2019-05-08
Applicant: ROLLS-ROYCE plc
Inventor： Richard N. March
IPC: F16L27/11 , F01D9/06 , B23K20/12 , F16L27/08 , F16L27/02 , F02K3/06 , B23K101/00 , B23K103/08
Abstract: 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.
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公开(公告)号：US20210301764A1
公开(公告)日：2021-09-30
申请号：US17196460
申请日：2021-03-09
Applicant: ROLLS-ROYCE PLC
Inventor： Rory D STIEGER
Abstract: 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.
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公开(公告)号：US11131214B2
公开(公告)日：2021-09-28
申请号：US16382923
申请日：2019-04-12
Applicant: Rolls-Royce Deutschland Ltd & Co KG , Rolls-Royce plc
Inventor： Stefan Menczykalski , Stephan Uhkoetter , John R. Mason , David A. Edwards , Neil Davies , Lynn Hammond , David Williams
Abstract: A gas turbine engine includes a gearbox receiving input from a core shaft and driving a fan at a lower speed than the core shaft. First and second oil circuits fluidly couple with an inlet and outlet of the gearbox. A third oil circuit fluidly couples with an inlet and outlet of the gearbox. The outlet of the gearbox includes a device directing oil from the gearbox to the first oil circuit, to the second oil circuit and to the third oil circuit when feeding to the gearbox exceeds a predefined oil flow rate, or deviates an operational value corresponding with that oil flow rate, and directs oil from the gearbox to the third oil circuit when feeding to the gearbox is ≤ the predefined flow rate or is ≤ a corresponding operational value or is greater than or equal to a further corresponding operational value.
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公开(公告)号：US11125111B2
公开(公告)日：2021-09-21
申请号：US16283085
申请日：2019-02-22
Applicant: ROLLS-ROYCE plc , Rolls-Royce Deutschland Ltd & Co KG
Inventor： John R Mason , Thomas Philip Astley
Abstract: A method (500) and apparatus (50, 60) for lubrication of a gearbox (30) of an aircraft engine comprise provision (502) of oil to the gearbox (30) through a primary oil system (50) driven by a core (11) of the engine (10) in normal conditions; detection (504) of windmilling conditions and/or failure of the primary oil system (50); and in response to the detected condition or failure, activation (506) of an electric pump (61) of an auxiliary oil system (60), to provide oil to the gearbox (30).
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公开(公告)号：US11118470B2
公开(公告)日：2021-09-14
申请号：US16520740
申请日：2019-07-24
Applicant: ROLLS-ROYCE plc
Inventor： Chathura K Kannangara , Jillian C Gaskell , Stewart T Thornton , Timothy Philp
Abstract: A gas turbine engine includes an engine core including: a compressor system including first, lower pressure, compressor, and a second, higher pressure, compressor; and an outer core casing surrounding the compressor system and including a first flange connection arranged to allow separation of the outer core casing at an axial position of the first flange connection, wherein the first flange connection is the first flange connection that is downstream of an axial position defined by the axial midpoint between the mid-span axial location on the trailing edge of the most downstream aerofoil of the first compressor and the mid-span axial location on the leading edge of the most upstream aerofoil of the second compressor; a nacelle surrounding the engine core and defining a bypass duct between the engine core and the nacelle; wherein an axial midpoint of the radially outer edge is defined as the fan OGV tip centrepoint.
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