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公开(公告)号：EP4011786A1
公开(公告)日：2022-06-15
申请号：EP21213562.8
申请日：2021-12-09
发明人： FARRELL, Ian , YAKOBOV, Ella , FETT, Steve , MAROTTE, Josee
摘要： The test rig (321) can be used for testing a blade pitch measurement system (200) of a variable pitch propeller system. The test rig (321) can include a first mount (322) rotatably mounted to the frame (332) and configured to receive the feedback device (203; 304), a rotation motor (324) drivingly coupled to rotatethe ring mount (322) relative to the frame (332) around a rotation axis (A), a second mount (320) configured toreceive the pitch sensor (206; 306), a mechanism configured for moving the second mount (320) along anorientation parallel to the rotation axis (A), and a controller (208) configured to control the rotation of the rotation motor (324) to a variable rotation speed, and for controlling the movement of the second mount (320) to variable positions via the mechanism.
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公开(公告)号：EP3967607A1
公开(公告)日：2022-03-16
申请号：EP21199601.2
申请日：2019-07-01
发明人： YAKOBOV, Ella , JARVO, James , TABAR, Roja
摘要： Herein provided are systems and methods for synchrophasing multi-engine aircraft. A phonic wheel (204) is coupled to a first propeller (130) of a first engine (110) of the aircraft. A sensor (212) is disposed and configured for producing a signal in response to passage of first and second position markers (420) on the phonic wheel (204). A control system (220) is communicatively coupled to the sensor (212) for obtaining the signal, and configured for: determining an expected delay between two subsequent signal pulses of the signal; identifying from within the plurality of signal pulses a particular pulse associated with the second position marker (420); determining, based on a particular time at which the particular pulse associated with the second position marker (420) was produced, that a rotational position of the first propeller (130) corresponds to a reference position at the particular time; and performing at least one synchrophasing operation for the aircraft based on the rotational position of the first propeller (130).
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3.发明公开
公开(公告)号：EP4317655A2
公开(公告)日：2024-02-07
申请号：EP23208052.3
申请日：2020-11-27
发明人： SHENOUDA, Antwan , YAKOBOV, Ella
IPC分类号： F01D17/06
摘要： Methods and systems for measuring an axial position of a rotating component of an engine are described herein. The method comprises obtaining a signal from a sensor (212) coupled to the rotating component, the rotating component having a plurality of position markers (202) distributed about a surface (302) thereof, the position markers (202) having an axially varying characteristic configured to cause a change in a varying parameter of the signal as a function of the axial position of the rotating component. Based on the signal, the method comprises determining a rotational speed of the rotating component from the signal, determining the varying parameter of the signal, and finding the axial position of the rotating component based on a known relationship between the axial position, the rotational speed, and the varying parameter of the signal.
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公开(公告)号：EP3812264A1
公开(公告)日：2021-04-28
申请号：EP20203120.9
申请日：2020-10-21
发明人： YAKOBOV, Ella , JARVO, James
摘要： A phonic wheel (38) having a body (46) and a tooth is disclosed. The body (46) is configured to rotate about a rotation axis (R). The tooth (44) is attached to the body (46). The tooth (44) has a first axial end (63A) relative to the rotation axis (R), a second axial end (63B) opposite the first axial end (63A), and a mid portion (64) extending between the first and second axial ends (63A, 63B). The mid portion (64) has a substantially axially uniform height (69) from the body (46). The first axial end (63A) has a greater height (66) from the body (46) than the height of the mid portion (64).
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公开(公告)号：EP3284666A1
公开(公告)日：2018-02-21
申请号：EP17186725.2
申请日：2017-08-17
发明人： YAKOBOV, Ella , JARVO, James Robert
IPC分类号： B64C11/30
CPC分类号： B64D45/0005 , B64C11/30 , B64C11/301 , B64D35/02
摘要： An aircraft propeller control system for an aircraft propeller (30) with adjustable blade angle has a blade angle feedback ring (104) and a sensor (112), one of which is mounted for rotation with the propeller. The blade angle feedback ring (104) moves longitudinally along with adjustment of the blade angle and has position markers (102) circumferentially spaced apart at distances that vary along a longitudinal axis. The sensor (112) is positioned adjacent the feedback ring (104) for producing signals indicative of passage of the position markers (102). Intervals between signals are indicative of circumferential distances between position markers (102). A controller (115) measures longitudinal position of the feedback ring (104) based on the intervals and is configured to produce a warning signal if the longitudinal position is outside a first threshold range.
摘要翻译： 用于具有可调节叶片角度的飞机螺旋桨（30）的飞机螺旋桨控制系统具有叶片角度反馈环（104）和传感器（112），其中一个安装成与螺旋桨一起旋转。 叶片角度反馈环（104）随着叶片角度的调节而纵向移动，并且具有位置标记（102），所述位置标记（102）在沿着纵向轴线变化的距离处沿周向间隔开。 传感器（112）位于反馈环（104）附近，用于产生指示位置标记（102）通过的信号。 信号之间的间隔表示位置标记（102）之间的周向距离。 控制器（115）基于间隔测量反馈环（104）的纵向位置，并且被配置为如果纵向位置在第一阈值范围之外则产生警告信号。
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公开(公告)号：EP4039584A1
公开(公告)日：2022-08-10
申请号：EP22164856.1
申请日：2019-07-16
发明人： MARONE, Joseph Ernesto , YAKOBOV, Ella , FARRELL, Ian , BASSE, Olivier , DOBSON, Martin , LAVOIE, Marc
摘要： A blade angle feedback ring assembly (200) for an aircraft propeller rotatable about a longitudinal axis (A) and having an adjustable blade angle is provided. A feedback ring (204) is coupled to the propeller to rotate therewith and to move along a longitudinal axis (A) with adjustment of the blade angle. A plurality of rods are coupled to the feedback ring (204) and extend along a direction substantially parallel to the longitudinal axis (A), the rods configured to support the feedback ring (204) for longitudinal sliding movement along the longitudinal axis (A) with adjustment of the blade angle. At least one shielding element is provided between the feedback ring (204) and the propeller for shielding the feedback ring (204) from electromagnetism.
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7.发明公开
公开(公告)号：EP3828492A1
公开(公告)日：2021-06-02
申请号：EP20210463.4
申请日：2020-11-27
发明人： SHENOUDA, Antwan , YAKOBOV, Ella
摘要： Methods and systems for measuring an axial position of a rotating component of an engine are described herein. The method comprises obtaining a signal from a sensor (212) coupled to the rotating component, the rotating component having a plurality of position markers (202) distributed about a surface (302) thereof, the position markers (202) having an axially varying characteristic configured to cause a change in a varying parameter of the signal as a function of the axial position of the rotating component. Based on the signal, the method comprises determining a rotational speed of the rotating component from the signal, determining the varying parameter of the signal, and finding the axial position of the rotating component based on a known relationship between the axial position, the rotational speed, and the varying parameter of the signal.
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8.发明公开
公开(公告)号：EP3591409A1
公开(公告)日：2020-01-08
申请号：EP19184537.9
申请日：2019-07-04
发明人： YAKOBOV, Ella , FARRELL, Ian
摘要： A method for controlling a crossing threshold used in determining a rotational speed of a propeller of an aircraft engine. An initial value for the crossing threshold (130) is set. A sensor signal (122) is received that comprises a first series of pulses (135 A , 135 B , 135 C ) indicative of passage of position markers about a circumference of a propeller shaft. A detection signal (150) is generated that comprises a second series of pulses (155 A , 155 B , 155 C ) indicative of within the first series of pulses (13 A , 135 B , 135 C ) that have a zero-crossing transition (140 A , 140 B , 140 C ) and a magnitude that exceeds the crossing threshold (130). The rotational speed of the propeller is determined from the detection signal (150). The crossing threshold (130) is adjusted as a function of the rotational speed.
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公开(公告)号：EP3901419A1
公开(公告)日：2021-10-27
申请号：EP21175722.4
申请日：2019-07-01
发明人： YAKOBOV, Ella
摘要： A phonic wheel (204) for use in a gas turbine engine (110) comprises a circular disk having first and second opposing faces (205). The circular disk defines a root surface (203) that extends between and circumscribes the first and second faces (205). A first plurality of projections (410) extend from the root surface (203) and are oriented substantially parallel to an axis of rotation (A) of the disk. The first plurality of projections (410) are circumferentially spaced substantially equally from one another and each have a first physical configuration. At least one second projection (420) extends from the root surface (203) and is positioned between two adjacent first projections (410), the at least one second projection (420) having a second physical configuration different from the first physical configuration.
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公开(公告)号：EP3838745A1
公开(公告)日：2021-06-23
申请号：EP20215047.0
申请日：2020-12-17
发明人： TOMESCU, Dana , JARVO, James , YAKOBOV, Ella
摘要： A sensor signal comprising a first signal pulse having a first voltage amplitude (V pk-pk1 ) and a second signal pulse having a second voltage amplitude (V pk-pk2 ) greater than or substantially equal to the first voltage amplitude (V pk-pk1 ) is obtained from a sensor (212) positioned adjacent a feedback device (204) coupled to rotate with an aircraft-bladed rotor (130) about a longitudinal axis (A) and to move along the axis (A) with adjustment of the rotor's blade pitch angle. The feedback device (204) comprises a reference feature (502 2 ) configured to generate the second signal pulse and varying detectable feature(s) (502 1 ) configured to generate the first signal pulse and to cause a change in the first voltage amplitude (V pk-pk1 ) as a function of an axial position of the feedback device (204) along the axis (A). A voltage ratio is determined based on the first voltage amplitude (V pk-pk1 ) and the second voltage amplitude (V pk-pk2 ), and the axial position of the feedback device (204) is determined from the voltage ratio.
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