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公开(公告)号：US20200011238A1
公开(公告)日：2020-01-09
申请号：US16411347
申请日：2019-05-14
Applicant: ROLLS-ROYCE plc
Inventor： Michael O. HALES , Craig W. BEMMENT , Stephane M. M. BARALON , Benjamin J. SELLERS , Christopher BENSON , Benedict R. PHELPS , Mark J. WILSON
Abstract: A gas turbine engine has a cycle operability parameter β in a defined range to achieve improved overall performance, taking into account fan operability and/or bird strike requirements as well as engine efficiency. The defined range of cycle operability parameter β may be particularly beneficial for gas turbine engines in which the fan is driven by a turbine through a gearbox.
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公开(公告)号：US20200018169A1
公开(公告)日：2020-01-16
申请号：US16566383
申请日：2019-09-10
Applicant: ROLLS-ROYCE PLC
Inventor： Stephane M M BARALON , Christopher BENSON , Benedict R. PHELPS
Abstract: A gas turbine engine has a quasi-non-dimensional mass flow rate in a defined range and a specific thrust in a defined range to achieve improved overall performance, taking into account fan operability and/or bird strike requirements as well as engine efficiency. The defined ranges of quasi-non-dimensional mass flow rate and specific thrust may be particularly beneficial for gas turbine engines in which the fan is driven by a turbine through a gearbox.
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公开(公告)号：US20190211750A1
公开(公告)日：2019-07-11
申请号：US16219257
申请日：2018-12-13
Applicant: ROLLS-ROYCE plc
Inventor： Christopher BENSON
CPC classification number: F02C7/36 , F01D25/285 , F01D25/34 , F02C7/32 , F02K3/06 , F05D2220/36 , F05D2230/72 , F05D2240/60 , F05D2260/02 , F05D2260/30 , F05D2260/4031 , F05D2260/40311
Abstract: A gas turbine engine assembly includes a gas turbine engine including a fan with a plurality of fan blades, a compressor, a combustor and a turbine, the turbine including a rotor coupled to the fan through a shaft, the shaft including a first joint arranged within a tail bearing housing; and a driving device including a second joint adapted to be coupled to the first joint, the driving device being adapted to rotate the shaft to position a fan blade of the plurality of fan blades in an inspection and/or removal position.
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公开(公告)号：US20160177787A1
公开(公告)日：2016-06-23
申请号：US14955906
申请日：2015-12-01
Applicant: ROLLS-ROYCE plc
Inventor： Christopher BENSON
CPC classification number: F01D25/243 , F05D2220/32 , F05D2230/60 , F05D2260/36 , F05D2300/501 , F16B5/0004 , F16L37/148 , Y02T50/672
Abstract: A joint assembly has first to third end portions of first to third components and an elongate resilient connection member. The first end portion interconnects with the second in a castellated arrangement. The first and second end portions have repeating arrays of first and second, and third and fourth connection portions. The first connection portion is received inward the third, and its first location feature being aligned with a third location feature of the third forming a first cavity portion, and the second connection portion axially distal surface abutting against that of the fourth, with a second location feature of the second connection portion being aligned with a fourth location feature of the fourth connection portion forming a second cavity portion. The first and second cavity portions are aligned forming an annular cavity, with the connection member being receivable within the annular cavity interlocking the first component to the second.
Abstract translation: 接头组件具有第一至第三部件的第一至第三端部分和细长的弹性连接部件。 第一末端部分与第二末端部分相配合， 第一和第二端部具有第一和第二和第三和第四连接部分的重复阵列。 第一连接部分被接收在第三连接部分的内部，并且其第一位置特征与第三位置特征对准，形成第一空腔部分，并且第二连接部分轴向远端表面与第四部分邻接，第二位置 第二连接部分的特征与形成第二腔部分的第四连接部分的第四位置特征对准。 第一和第二空腔部分对准形成环形空腔，连接构件可接收在环形空腔内，将第一部件与第二部件互锁。
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公开(公告)号：US20190048887A1
公开(公告)日：2019-02-14
申请号：US16039590
申请日：2018-07-19
Applicant: ROLLS-ROYCE plc
Inventor： Christopher BENSON , Dale E. EVANS
Abstract: A fan disc apparatus for a gas turbine engine comprises a fan disc; a first drive arm for connecting the fan disc to a fan drive shaft of the gas turbine engine; and a second drive arm for connecting the fan disc to the fan drive shaft.
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Patent Agency Ranking
公开(公告)号：US20160177779A1
公开(公告)日：2016-06-23
申请号：US14954087
申请日：2015-11-30
Applicant: ROLLS-ROYCE plc
Inventor： Christopher BENSON
CPC classification number: F01D21/045 , F01D5/147 , F01D5/282 , F02C7/05 , F05D2220/32 , F05D2240/303 , F05D2260/311 , F05D2300/10
Abstract: A turbomachine blade comprising a metallic leading edge having a weakened region extending in a spanwise direction; and a crack initiator for selectively initiating cracking of the metallic leading edge along the weakened region.
Abstract translation: 一种涡轮机叶片，包括具有在翼展方向上延伸的弱化区域的金属前缘; 以及用于选择性地启动沿着弱化区域的金属前缘裂纹的裂纹引发剂。
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公开(公告)号：US20150276223A1
公开(公告)日：2015-10-01
申请号：US14640640
申请日：2015-03-06
Applicant: ROLLS-ROYCE PLC
Inventor： Christopher BENSON , Matthew Ashley Charles HOYLAND
CPC classification number: F23R3/002 , F01D25/24 , F01D25/243 , F01D25/28 , F02C7/04 , F02C7/045 , F02C7/24 , F02K3/00 , F02K3/06 , F04D29/663 , F04D29/664 , F04D29/668 , F05D2250/28 , F05D2250/283 , F05D2260/36 , F05D2260/96 , F05D2300/43 , F23R2900/00017 , Y10T29/49323
Abstract: A method of lining a turbofan casing (30) with an array (32) of liner modules (34), including the steps of: providing a liner module (34); and providing a coupling element (48) on the casing for interlocking engagement with the liner module to maintain the liner module in position relative to the casing; and interlockingly engaging the liner module (34) and coupling element (48) by progressive movement of the liner module relative to the coupling element.
Abstract translation: 一种用衬垫模块（34）的阵列（32）衬套涡扇风扇壳体（30）的方法，包括以下步骤：提供衬套模块（34）; 以及在所述壳体上设置耦合元件（48），用于与所述衬垫模块互锁接合以将所述衬垫模块相对于所述壳体保持在适当位置; 并且通过所述衬套模块相对于所述联接元件的逐渐移动而使所述衬垫模块（34）和所述联接元件（48）互锁地接合。
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公开(公告)号：US20200072058A1
公开(公告)日：2020-03-05
申请号：US16554713
申请日：2019-08-29
Applicant: ROLLS-ROYCE plc
Inventor： Christopher BENSON , Stephane M M BARALON
Abstract: A gas turbine engine comprises carbon fibre fan blades. At cruise conditions, the fan tip air angle θ in the range: 64 degrees≤θ≤67 degrees. Additionally or alternatively, the fan blade tip angle β is in the range of from 62 to 69 degrees. Arrangements in accordance with the present disclosure provide advantages which may include improved bird-strike performance. This may allow advantages associated with carbon fibre fan blades to be better exploited.
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公开(公告)号：US20190292912A1
公开(公告)日：2019-09-26
申请号：US16290259
申请日：2019-03-01
Applicant: ROLLS-ROYCE plc
Inventor： Christopher BENSON
Abstract: The blade of a fan of a gas turbine engine situated within an intake duct is removed using apparatus including a support structure supporting a cantilevered platform for an operator and a guide rail which is profiled to receive a blade root of the blade. The operator releases the blade and slides it from its recess in the fan disc into a complementary guide channel in the guide rail. The guide rail follows a path which constrains the blade to move in a direction, and at an orientation, which avoids interference with the intake duct.
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公开(公告)号：US20160177744A1
公开(公告)日：2016-06-23
申请号：US14954355
申请日：2015-11-30
Applicant: ROLLS-ROYCE plc
Inventor： Christopher BENSON
CPC classification number: F01D5/282 , F01D5/147 , F01D21/045 , F02C7/05 , F05D2220/32 , F05D2230/30 , F05D2240/303 , F05D2300/10 , F05D2300/50
Abstract: A turbomachine blade comprising a metallic leading edge having a region having varying fracture resistance in a spanwise direction so as to increase energy absorption by the leading edge in the event of the blade being released from a turbomachine and impacting a casing of the turbomachine.
Abstract translation: 一种涡轮机叶片，其包括具有在翼展方向上具有变化的抗断裂性的区域的金属前缘，以便在叶片从涡轮机释放并冲击涡轮机的壳体的情况下增加前缘的能量吸收。
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