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1. 发明公开

EP4119801A1 COMPUTER-IMPLEMENTED METHOD FOR DETERMINING THE OPERABILITY OF A GAS TURBINE ENGINE 审中-公开
公开(公告)号：EP4119801A1
公开(公告)日：2023-01-18
申请号：EP22194329.3
申请日：2020-06-09
申请人： Rolls-Royce plc
发明人： Hillel, Malcolm , Conduit, Bryce , Dickens, Anthony , Taylor, James , Miller, Robert , Hall, Christopher
IPC分类号： F04D27/00 , F01D21/00 , F04D29/32 , G05B23/02 , G06N3/08
摘要： A computer-implemented method comprising: controlling input of data quantifying damage received by one or more components of a gas turbine engine into a first machine learning algorithm; receiving data quantifying a first operating parameter of the gas turbine engine as an output of the first machine learning algorithm; and determining operability of the gas turbine engine by comparing the received data quantifying the first operating parameter of the gas turbine engine with a threshold.

2. 发明公开

EP3404212A1 COMPRESSOR AEROFOIL MEMBER 有权转让
公开(公告)号：EP3404212A1
公开(公告)日：2018-11-21
申请号：EP18167527.3
申请日：2018-04-16
申请人： Rolls-Royce plc
发明人： Taylor, James , Miller, Robert
IPC分类号： F01D5/14
摘要： An aerofoil member for a compressor of a gas turbine engine is provided. In use the aerofoil member extends between radially inner and radially outer endwalls which define a gas annulus of the compressor. The aerofoil member has a leading edge, a trailing edge, a pressure surface and a suction surface such that successive cross-sections through the aerofoil member transverse to the radial direction provide respective aerofoil sections. The external shape of the aerofoil member is defined by the stacking of the aerofoil sections on a stacking axis which passes through a reference point common to each aerofoil section. The aerofoil member has lean produced by the projection of the stacking axis onto a plane normal to the engine axis intersecting a first one of the endwalls at an angle of from 5° to 25° to the circumferential direction direction such that the pressure surface faces the first endwall. With increasing distance along the stacking axis from the first endwall, the stacking axis experiences a turning point such that the pressure surface has a convex shape adjacent the first endwall.

3. 发明公开

EP3392459A1 COMPRESSOR BLADES 无效
公开(公告)号：EP3392459A1
公开(公告)日：2018-10-24
申请号：EP17175536.6
申请日：2017-06-12
申请人： Rolls-Royce plc
发明人： Hall, Christopher , Kovanis, Anastasios , Dickens, Anthony , Taylor, James
IPC分类号： F01D5/20 , F04D29/32 , F04D29/68
CPC分类号： F04D29/324 , F01D5/20 , F04D29/384 , F04D29/544 , F04D29/681 , F05D2240/125 , F05D2240/307 , F05D2250/71
摘要： This disclosure concerns aerofoils (24) for an axial flow compressor (14). The compressor (14) has an array of aerofoils (14B, 24) angularly spaced about its axis of rotation (11). The aerofoils (24) have leading (32) and trailing (34) edges extending in a direction spanning a flow region defined between a radially inner rotor component (14A) and a radially outer casing (14C). Each aerofoil (24) has opposing pressure (36) and suction (38) surfaces extending between the leading (32) and trailing (34) edges and terminating at a free end (30) of the aerofoil. Each aerofoil (24) leans towards the pressure surface (36) by an angle of between 10° and 80° in the vicinity of the aerofoil tip (30). The aggressive negative lean towards the tip (30) may help reduce over-tip leakage flow in use.

4. 发明授权

EP3404212B1 COMPRESSOR AEROFOIL MEMBER 有权转让
公开(公告)号：EP3404212B1
公开(公告)日：2020-03-04
申请号：EP18167527.3
申请日：2018-04-16
申请人： Rolls-Royce plc
发明人： Taylor, James , Miller, Robert
IPC分类号： F01D5/14

5. 发明公开

EP3026215A1 ROW OF AEROFOIL MEMBERS FOR AN AXIAL COMPRESSOR 无效
标题翻译： REIHE VONTRAGFLÜGELELEMENTENEINES AXIALVERDICHTERS
公开(公告)号：EP3026215A1
公开(公告)日：2016-06-01
申请号：EP15188508.4
申请日：2015-10-06
申请人： Rolls-Royce plc
发明人： Taylor, James
IPC分类号： F01D5/14 , F04D29/68
CPC分类号： F04D29/681 , F01D5/143 , F01D9/041 , F04D29/324 , F05D2220/323 , F05D2240/12 , F05D2240/30 , F05D2240/80 , Y02T50/673
摘要： A row of aerofoil (46) members for an axial compressor, the row comprises a circumferentially extending endwall (42) and a plurality of aerofoils (46) extending radially from the endwall (42). The endwall (42) is profiled to include an acceleration region and a deceleration region in a location that corresponds to a position of peak fluid pressure. The acceleration region is provided upstream of the deceleration region such that fluid flow through the compressor and adjacent the endwall (42) is accelerated and then decelerated so as to reduce the peak fluid pressure.
摘要翻译：一排用于轴向压缩机的机翼（46）构件，该排包括沿周向延伸的端壁（42）和从端壁（42）径向延伸的多个翼状体（46）。端壁（42）被成形为在对应于峰值流体压力的位置的位置包括加速度区域和减速区域。加速区域设置在减速区域的上游，使得流过压缩机的流体和邻近端壁（42）的流体被加速然后减速以便降低峰值流体压力。

6. 发明公开

EP4119800A1 COMPUTER-IMPLEMENTED METHODS FOR TRAINING A MACHINE LEARNING ALGORITHM 审中-公开
公开(公告)号：EP4119800A1
公开(公告)日：2023-01-18
申请号：EP22194323.6
申请日：2020-06-09
申请人： Rolls-Royce plc
发明人： Hall, Christopher , Hillel, Malcolm , Conduit, Bryce , Dickens, Anthony , Taylor, James , Miller, Robert
IPC分类号： F04D27/00 , F01D21/00 , G06N3/08 , G05B23/02 , F04D29/32
摘要： A computer-implemented method comprising: controlling input of at least a portion of a first training data set into a first machine learning algorithm, the first training data set including: data quantifying damage to one or more components of a first gas turbine engine; and data quantifying a first operating parameter of the first gas turbine engine; receiving data quantifying the first operating parameter as an output of the first machine learning algorithm; and training the first machine learning algorithm using: the received data output from the first machine learning algorithm; and data quantifying the first operating parameter of the first gas turbine engine, the trained first machine learning algorithm being configured to enable determination of operability of a second gas turbine engine.

7. 发明公开

EP3231996A1 A BLADE FOR AN AXIAL FLOW MACHINE 有权转让
标题翻译：用于轴流机的叶片
公开(公告)号：EP3231996A1
公开(公告)日：2017-10-18
申请号：EP17161042.1
申请日：2017-03-15
申请人： Rolls-Royce plc
发明人： Brown, William , Hall, Christopher , Dickens, Anthony , Taylor, James
IPC分类号： F01D5/14
CPC分类号： F04D29/324 , F01D5/141 , F05D2220/32 , F05D2240/301 , F05D2240/304 , F05D2250/70
摘要： There is disclosed a blade 132 for an axial flow machine having a pressure surface, a suction surface and a trailing edge. The blade has a cross-sectional aerofoil profile comprising: a region of maximum curvature corresponding to the trailing edge of the blade and defining a trailing edge radius of curvature r; a trailing edge region 180 extending from the trailing edge and having a chordwise extent equal to the trailing edge radius of curvature r; a taper region 182 adjacent the trailing edge region 180, the taper region 182 having a chordwise extent greater than the trailing edge radius of curvature r and no more than 15% of the chord of the blade; a body region 184 adjacent the taper region; a pressure surface boundary 150 corresponding to the pressure surface of the blade; and a suction surface boundary 152 corresponding to the suction surface of the blade. A thickness between the pressure surface boundary 150 and the suction surface boundary 152 reduces within the taper region 182 towards the trailing edge by at least 50%.
摘要翻译：公开了一种用于具有压力表面，吸力表面和后缘的轴流机器的叶片132。所述叶片具有横截面翼型轮廓，所述翼型轮廓包括：最大曲率区域，所述最大曲率区域对应于所述叶片的后缘并且限定后缘曲率半径r; 从后缘延伸并具有等于后缘曲率半径r的弦向范围的后缘区域180; 与后缘区域180相邻的锥形区域182，锥形区域182具有大于后缘曲率半径r且不大于叶片翼弦的15％的弦向范围; 邻近锥形区域的本体区域184; 对应于叶片的压力表面的压力表面边界150; 以及与叶片的吸力面对应的吸力面边界152。压力表面边界150和吸力表面边界152之间的厚度在锥形区域182内朝向后缘减少至少50％。

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