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公开(公告)号：US20160167789A1
公开(公告)日：2016-06-16
申请号：US14957972
申请日：2015-12-03
Applicant: ROLLS-ROYCE plc
Inventor： Glenn A. KNIGHT , Alan R. MAGUIRE , Daniel ROBINSON
IPC: B64D13/04
CPC classification number: F02C7/277 , B64D13/02 , B64D31/14 , B64D2013/0696 , F02C7/275 , F16H37/086 , F16H2015/383 , F16H2037/088
Abstract: An aircraft cabin blower system comprising a transmission and a compressor is disclosed. The system has a forward configuration in which the compressor is drivable in use via the transmission. The transmission comprises a toroidal continuously variable transmission giving selectively variable control over the rate at which the compressor is driven.
Abstract translation: 公开了一种包括变速器和压缩机的飞机机舱鼓风机系统。 该系统具有正向构造，其中压缩机经由变速器在使用中是可驱动的。 变速器包括环形无级变速器，其给出对压缩机被驱动的速率的选择性可变的控制。
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公开(公告)号：US20200003069A1
公开(公告)日：2020-01-02
申请号：US16451543
申请日：2019-06-25
Applicant: ROLLS-ROYCE plc
Inventor： Alan R. MAGUIRE
Abstract: A gas turbine engine, in particular an aircraft engine, includes: a turbine connected via an input shaft device to a gearbox device having a sun gear, a planet carrier having a plurality of planet gears attached thereto, and a ring gear, the sun gear is connected to the input shaft device, the planet carrier or the ring gear is connected to a propulsive fan via an output shaft device of the gearbox device, with a rear carrier bearing device radially between the planet carrier and a static structure on the input side of the gearbox device, an inter-shaft bearing system being positioned radially between the input shaft device and the planet carrier of the gearbox device. The input shaft device having a high rigidity or the input shaft device having a means for decreasing the rigidity, in particular a diaphragm section.
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公开(公告)号：US20190032574A1
公开(公告)日：2019-01-31
申请号：US16044869
申请日：2018-07-25
Applicant: ROLLS-ROYCE plc
Inventor： Alan R. MAGUIRE , Timothy J. SCANLON , Luis F. LLANO , Paul A. SELLERS
Abstract: A gas turbine engine has a core engine including: a compressor, combustion equipment which receives compressed air from the compressor, a circumferential row of nozzle guide vanes, and a turbine. The nozzle guide vanes defines a throat receiving hot working gases from the combustion equipment into the turbine. The gas turbine engine further has an air system which is switchably operable between an on-position which opens a diversion pathway along which a portion of the compressed air exiting the compressor bypasses the combustion equipment to join the hot working gases at re-entry holes located between the nozzle guide vanes and a rotor at the front of the turbine, thereby increasing the semi-dimensional mass flow ω(T30)0.5/(P30) of the core engine at the exit of the compressor, and an off-position which closes the diversion pathway, thereby decreasing the semi-dimensional mass flow of the core engine at the exit of the compressor.
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公开(公告)号：US20200224554A1
公开(公告)日：2020-07-16
申请号：US16720068
申请日：2019-12-19
Applicant: ROLLS-ROYCE plc
Inventor： Alan R. MAGUIRE , Stewart T. THORNTON , Philip C. BOND , Glenn A. KNIGHT
IPC: F01D25/16
Abstract: A gas turbine engine for an aircraft. The gas turbine engine comprises a rotatable shaft defining a rotational axis extending between rearward and forward ends of the gas turbine engine and a compressor drum surrounding, and coupled to, the shaft so as to define an annular gap therebetween. The gas turbine engine further comprises an intermediate case arranged axially rearward of the compressor drum and comprising a bearing support element extending into the annular gap, and a forward bearing mounted between the bearing support element and the shaft proximate a forward end of the compressor drum.
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公开(公告)号：US20170167273A1
公开(公告)日：2017-06-15
申请号：US15352468
申请日：2016-11-15
Applicant: ROLLS-ROYCE plc
Inventor： Alan R. MAGUIRE , Timothy J. SCANLON
CPC classification number: F01D5/187 , F01D9/041 , F01D11/24 , F01D25/12 , F01D25/24 , F02C3/10 , F02C7/12 , F02C7/18 , F02C9/18 , F05D2220/32 , F05D2260/202 , F05D2270/3062 , F16K1/221 , F23R3/007 , Y02T50/672 , Y02T50/675
Abstract: A gas turbine engine includes a turbine and a turbine cooling arrangement. The turbine includes a turbine rotor surrounded by a static rotor track liner, and a nozzle guide vane downstream of the rotor in a core main gas flow path. The cooling arrangement includes a first air duct that provides cooling airflow to a rotor track liner cooling plenum and a second air duct that provides a cooling airflow to the nozzle guide vane. A common manifold is upstream in the cooling airflow of the ducts and provides cooling air to the ducts. A two-way valve modulates air provided to the ducts from the manifold. The valve is operates in a first or second mode. In the first mode, air flow to the first duct is relatively high and airflow to the second duct is relatively low compared to where the valve is operated in the second mode.
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Patent Agency Ranking
公开(公告)号：US20210156313A1
公开(公告)日：2021-05-27
申请号：US17147762
申请日：2021-01-13
Applicant: ROLLS-ROYCE PLC
Inventor： Alan R. MAGUIRE
Abstract: A gas turbine engine, in particular an aircraft engine, includes: a turbine connected via an input shaft device to a gearbox device having a sun gear, a planet carrier having a plurality of planet gears attached thereto, and a ring gear, the sun gear is connected to the input shaft device, the planet carrier or the ring gear is connected to a propulsive fan via an output shaft device of the gearbox device, with a rear carrier bearing device radially between the planet carrier and a static structure on the input side of the gearbox device, an inter-shaft bearing system being positioned radially between the input shaft device and the planet carrier of the gearbox device. The input shaft device having a high rigidity or the input shaft device having a means for decreasing the rigidity, in particular a diaphragm section.
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公开(公告)号：US20200003128A1
公开(公告)日：2020-01-02
申请号：US16451677
申请日：2019-06-25
Applicant: ROLLS-ROYCE plc
Inventor： Alan R. MAGUIRE , Geoffrey HUGHES
Abstract: A gas turbine engine, in particular an aircraft engine, includes: a turbine connected via an input shaft device to a gearbox device having a sun gear, a planet carrier having a plurality of planet gears attached thereto, and a ring gear, the sun gear is connected to the input shaft device, the planet carrier or the ring gear is connected to a propulsive fan via an output shaft device of the gearbox device, with a rear carrier bearing device radially between the planet carrier and a static structure on the input side of the gearbox device or a front carrier bearing device radially between the planet carrier and a static structure on the output side of the gearbox device.
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公开(公告)号：US20170233080A1
公开(公告)日：2017-08-17
申请号：US15415568
申请日：2017-01-25
Applicant: ROLLS-ROYCE PLC
Inventor： Glenn A. KNIGHT , Alan R. MAGUIRE , Richard SHARPE
CPC classification number: B64D13/00 , B64D13/04 , B64D2013/0696 , F01D13/00 , F01D17/16 , F02C7/26 , F02C7/277 , F02C7/32 , F05D2220/323 , F05D2260/406 , F05D2260/85 , Y02T50/44 , Y02T50/671
Abstract: An aircraft cabin blower system is described having a hydraulic circuit comprising a first hydraulic device and a second hydraulic device. The first hydraulic device is mechanically coupled to a cabin blower compressor and the second hydraulic device is arranged in use to be mechanically coupled to a spool of a gas turbine engine. The first hydraulic device is capable of performing as a hydraulic motor and the second hydraulic device is capable of performing as a hydraulic pump. When, in use, the system is operating in a cabin blower configuration, a driving force supplied by the spool of the gas turbine causes the second hydraulic device to pump liquid provided in the hydraulic circuit and thereby to drive the first hydraulic device, which in turn rotates the cabin blower compressor.
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公开(公告)号：US20210246811A1
公开(公告)日：2021-08-12
申请号：US17169624
申请日：2021-02-08
Applicant: ROLLS-ROYCE plc
Inventor： Alan R. MAGUIRE , Richard SHARPE , Neil J. DAVIES
Abstract: A system for supplying lubricant to a component of a gas turbine engine having a fan shaft is provided. The system includes a pump drivably couplable to the fan shaft for pumping lubricant to the component. The pump includes an inlet for receiving lubricant from a lubricant source, an outlet for outputting lubricant to the component and a swashplate movable between at least a first position and a second position. The system also includes a swashplate actuator for actuating the swashplate between the first position and the second position according to whether the fan shaft is rotating in a forward direction or a reverse direction opposite to the forward direction.
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公开(公告)号：US20200011250A1
公开(公告)日：2020-01-09
申请号：US16437907
申请日：2019-06-11
Applicant: ROLLS-ROYCE plc
Inventor： Alan R. MAGUIRE , Richard G. STRETTON
Abstract: Apparatus for a gas turbine engine, the apparatus comprising: a core engine casing having a longitudinal axis and including: an inner wall defining at least part of a core airflow path through the gas turbine engine; an outer wall defining an external surface of the core engine casing, a first cavity being defined between the inner wall and the outer wall of the core engine casing; a plurality of guide vanes extending radially from the outer wall of the core engine casing; a torque box defined within the first cavity of the core engine casing and at least partially overlapping axially with the plurality of guide vanes, the torque box defining a second cavity; and an accessory gear box positioned within the second cavity of the torque box.
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