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1.发明授权公开(公告)号：US11767769B2
公开(公告)日：2023-09-26
申请号：US17119163
申请日：2020-12-11
Applicant: PRATT & WHITNEY CANADA CORP.
Inventor： Ian Farrell , Ella Yakobov , Steve Fett , Josee Marotte
IPC: F01D21/00
CPC classification number: F01D21/003 , F05D2260/80 , F05D2260/83 , F05D2270/304 , F05D2270/80
Abstract: Methods and systems for testing a sensor of a propeller blade angle position feedback system are described. A sensor signal is received from a sensor at a known position relative to a feedback device, the feedback comprising a ring and at least one pair of position markers spaced from one another around a circumference thereof, the sensor configured for successively detecting passage of the position markers as the feedback device rotates at a known rotational speed and an axial distance between the sensor and the feedback device varies. From the sensor signal a measured position of the sensor relative to the feedback device and a measured rotational speed of the feedback device are determined. The measured position and the measured rotational speed are compared to the known position and the known rotational speed to determine a sensor accuracy.
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公开(公告)号：US20200378259A1
公开(公告)日：2020-12-03
申请号：US16739044
申请日：2020-01-09
Applicant: PRATT & WHITNEY CANADA CORP.
Inventor： Sean DURAND , Richard Kudrna , Ian Farrell
Abstract: A blade angle feedback assembly for an aircraft-bladed rotor is provided. The rotor is rotatable about a longitudinal axis and has an adjustable blade pitch angle. The assembly comprises a feedback device coupled to rotate with the rotor with adjustment of the blade pitch angle, the feedback device having a root surface, a plurality of position makers circumferentially disposed on the root surface, the plurality of position markers circumferentially spaced from one another and non-aligned with the longitudinal axis, and at least one sensor mounted adjacent the feedback device and configured to detect a passage of the plurality of position markers as the feedback device rotates about the longitudinal axis.
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公开(公告)号：US11780561B2
公开(公告)日：2023-10-10
申请号：US17326993
申请日：2021-05-21
Applicant: PRATT & WHITNEY CANADA CORP.
Inventor： Joseph Ernesto Marone , Ella Yakobov , Ian Farrell , Olivier Basse , Martin Dobson , Martin Clermont , Marc Lavoie
CPC classification number: B64C11/06 , B64C11/301 , B64C11/34 , B64D45/02
Abstract: There is provided a blade angle feedback assembly for a propeller of an aircraft engine. The propeller is rotatable about an axis and has propeller blades rotatable about respective spanwise axes to adjust a blade angle thereof. The blade angle feedback assembly comprises a feedback ring having a plurality of position markers disposed thereon, at least one sensor configured to provide feedback on the blade angle of the propeller blades by detecting a relative movement between the feedback ring and the at least one sensor, and at least one shielding element provided between the feedback ring and the propeller, the at least one shielding element configured to shield the feedback ring from electromagnetism.
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公开(公告)号：US11333020B2
公开(公告)日：2022-05-17
申请号：US16739044
申请日：2020-01-09
Applicant: PRATT & WHITNEY CANADA CORP.
Inventor： Sean Durand , Richard Kudrna , Ian Farrell
Abstract: A blade angle feedback assembly for an aircraft-bladed rotor is provided. The rotor is rotatable about a longitudinal axis and has an adjustable blade pitch angle. The assembly comprises a feedback device coupled to rotate with the rotor with adjustment of the blade pitch angle, the feedback device having a root surface, a plurality of position makers circumferentially disposed on the root surface, the plurality of position markers circumferentially spaced from one another and non-aligned with the longitudinal axis, and at least one sensor mounted adjacent the feedback device and configured to detect a passage of the plurality of position markers as the feedback device rotates about the longitudinal axis.
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公开(公告)号：US11168578B2
公开(公告)日：2021-11-09
申请号：US16560295
申请日：2019-09-04
Applicant: PRATT & WHITNEY CANADA CORP.
Inventor： Ian Farrell
Abstract: A system for adjusting a variable position vane in an aircraft engine is disclosed. The system comprises a servo valve operatively connected to the variable position vane and configured to cause adjustment of the variable position vane based on a pressure of air pressurized by a compressor of the aircraft engine.
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Patent Agency Ranking
公开(公告)号：US10822105B2
公开(公告)日：2020-11-03
申请号：US16129286
申请日：2018-09-12
Applicant: PRATT & WHITNEY CANADA CORP.
Inventor： Ella Yakobov , Ian Farrell
Abstract: Systems and methods 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 is set. A sensor signal is received that comprises a first series of pulses indicative of passage of position markers about a circumference of a propeller shaft. A detection signal is generated that comprises a second series of pulses indicative of within the first series of pulses that have a zero-crossing transition and a magnitude that exceeds the crossing threshold. The rotational speed of the propeller is determined from the detection signal. The crossing threshold is adjusted as a function of the rotational speed.
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公开(公告)号：US11371825B2
公开(公告)日：2022-06-28
申请号：US16739052
申请日：2020-01-09
Applicant: PRATT & WHITNEY CANADA CORP.
Inventor： Sean Durand , Richard Kudrna , Ian Farrell
Abstract: A blade angle feedback assembly for an aircraft-bladed rotor is provided. The rotor is rotatable about a longitudinal axis and having an adjustable blade pitch angle. The assembly comprises a feedback device coupled to rotate with the rotor with adjustment of the blade pitch angle, the feedback device comprising a non-magnetically permeable body defining a root surface and a plurality of magnetically permeable position markers circumferentially disposed on the root surface, and at least one sensor mounted adjacent the feedback device and configured to detect a passage of the plurality of position markers as the feedback device rotates about the longitudinal axis.
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公开(公告)号：US20210284322A1
公开(公告)日：2021-09-16
申请号：US17326993
申请日：2021-05-21
Applicant: PRATT & WHITNEY CANADA CORP.
Inventor： Joseph Ernesto Marone , Ella Yakobov , Ian Farrell , Olivier Basse , Martin Dobson , Martin Clermont , Marc Lavoie
Abstract: There is provided a blade angle feedback assembly for a propeller of an aircraft engine. The propeller is rotatable about an axis and has propeller blades rotatable about respective spanwise axes to adjust a blade angle thereof. The blade angle feedback assembly comprises a feedback ring having a plurality of position markers disposed thereon, at least one sensor configured to provide feedback on the blade angle of the propeller blades by detecting a relative movement between the feedback ring and the at least one sensor, and at least one shielding element provided between the feedback ring and the propeller, the at least one shielding element configured to shield the feedback ring from electromagnetism.
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公开(公告)号：US11046422B2
公开(公告)日：2021-06-29
申请号：US16036930
申请日：2018-07-16
Applicant: PRATT & WHITNEY CANADA CORP.
Inventor： Joseph Ernesto Marone , Ella Yakobov , Ian Farrell , Olivier Basse , Martin Dobson , Marc Lavoie
Abstract: A blade angle feedback ring assembly for an aircraft propeller rotatable about a longitudinal axis and having an adjustable blade angle is provided. A feedback ring is coupled to the propeller to rotate therewith and to move along a longitudinal axis with adjustment of the blade angle. A plurality of rods are coupled to the feedback ring and extending along a direction substantially parallel to the longitudinal axis, the rods configured to support the feedback ring for longitudinal sliding movement along the longitudinal axis with adjustment of the blade angle. At least one shielding element is provided between the feedback ring and the propeller for shielding the feedback ring from electromagnetism.
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公开(公告)号：US10889367B2
公开(公告)日：2021-01-12
申请号：US15495070
申请日：2017-04-24
Applicant: PRATT & WHITNEY CANADA CORP.
Inventor： Richard Kudrna , Ian Farrell
Abstract: Systems and methods for providing pitch position feedback for pitch-adjustable blades of an aircraft bladed rotor are disclosed. In one embodiment, the systems include a sensor comprising a magnet having a magnetic field, a pole piece coupled to a first pole of the magnet and directing the magnetic field toward the feature and a coil mounted in the magnetic field. The coil generates a sensor signal indicative of a variation in the magnetic field caused by movement of the feature in the magnetic field. The sensor also includes a magnetic shield mounted in the magnetic field. The magnetic shield defines a magnetic return path for some magnetic flux of the magnetic field exiting the pole piece toward an opposite second pole of the magnet.
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