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公开(公告)号：US11420772B2
公开(公告)日：2022-08-23
申请号：US16717321
申请日：2019-12-17
发明人： Dana Tomescu , James Jarvo , Ella Yakobov
摘要： A sensor signal comprising a first signal pulse having a first voltage amplitude and a second signal pulse having a second voltage amplitude greater than or substantially equal to the first voltage amplitude is obtained from a sensor positioned adjacent a feedback device coupled to rotate with an aircraft-bladed rotor about a longitudinal axis and to move along the axis with adjustment of the rotor's blade pitch angle. The feedback device comprises a reference feature configured to generate the second signal pulse and varying detectable feature(s) configured to generate the first signal pulse and to cause a change in the first voltage amplitude as a function of an axial position of the feedback device along the axis. A voltage ratio is determined based on the first voltage amplitude and the second voltage amplitude, and the axial position of the feedback device is determined from the voltage ratio.
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公开(公告)号：US11412640B2
公开(公告)日：2022-08-09
申请号：US16539226
申请日：2019-08-13
发明人： Dana Tomescu
摘要： A heat exchanger for aircraft electronic components includes a first plate having channels arranged with side-by-side channel inlets fed from a common fluid supply manifold extending to the channel inlets from a manifold inlet. The channel inlets include a first set of inlets spaced further away from the manifold inlet than a second set of inlets. The fluid supply manifold has a flow divider positioned fluidly between the manifold inlet and the channel inlets. The flow divider is configured in use to direct heat exchange fluid entering the manifold from the manifold inlet preferentially toward the first set of inlets. A second plate is coupled with the first plate to seal the channels and the fluid supply manifold.
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公开(公告)号：US11365691B2
公开(公告)日：2022-06-21
申请号：US16600400
申请日：2019-10-11
发明人： Dana Tomescu , James Jarvo
IPC分类号： B64C11/30 , F02C9/22 , F02D29/02 , G01D5/12 , B64D27/10 , F01D7/00 , F01D17/20 , F01D21/00 , B64C27/473 , B64C27/57 , F01D17/06 , G01D5/14 , G01D5/20 , G01P3/487 , G01P3/488 , F02C7/32 , B63H3/00 , B64C11/06 , F02D41/28
摘要： There is provided a blade angle feedback system for an aircraft-bladed rotor rotatable about a longitudinal axis and having an adjustable blade pitch angle. A feedback device is coupled to rotate with the rotor and to move along the axis with adjustment of the blade pitch angle. The feedback device comprises a body having position marker(s) embedded therein, the body made of a first material having a first magnetic permeability and the position marker(s) comprising a second material having a second magnetic permeability greater than the first. Sensor(s) are positioned adjacent the feedback device and configured for producing, as the feedback device rotates about the axis, sensor signal(s) in response to detecting passage of the position marker(s). A control unit is communicatively coupled to the sensor(s) and configured to generate a feedback signal indicative of the blade pitch angle in response to the sensor signal(s) received from the sensor(s).
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公开(公告)号：US11835543B2
公开(公告)日：2023-12-05
申请号：US17748549
申请日：2022-05-19
发明人： Dana Tomescu , James Jarvo
IPC分类号： F03D17/00 , G01P3/488 , B64C11/30 , B64D27/10 , F01D7/00 , F01D17/20 , F01D21/00 , F01D17/06 , G01D5/14 , F01D17/02 , F04D29/36 , B64C27/473 , B64C27/57 , F02C9/22 , F02D29/02 , G01D5/12 , G01D5/20 , G01P3/487 , F02C7/32 , B63H3/00 , B64C11/06 , F02D41/28
CPC分类号： G01P3/488 , B64C11/301 , B64C27/473 , B64C27/57 , B64D27/10 , F01D7/00 , F01D17/02 , F01D17/06 , F01D17/20 , F01D21/003 , F02C9/22 , F02D29/02 , F04D29/362 , G01D5/125 , G01D5/145 , G01D5/2013 , G01P3/487 , B63H2003/006 , B64C11/06 , B64C2027/4733 , F02C7/32 , F02D2041/281 , F02D2041/288 , F05B2270/328 , F05D2220/323 , F05D2260/70 , F05D2270/02 , F05D2270/80 , F05D2270/821 , F05D2300/507
摘要： There is provided a blade angle feedback system for an aircraft-bladed rotor rotatable about a longitudinal axis and having an adjustable blade pitch angle. A feedback device is coupled to rotate with the rotor and to move along the axis with adjustment of the blade pitch angle. The feedback device comprises a body having position marker(s) embedded therein, the body made of a first material having a first magnetic permeability and the position marker(s) comprising a second material having a second magnetic permeability greater than the first. Sensor(s) are positioned adjacent the feedback device and configured for producing, as the feedback device rotates about the axis, sensor signal(s) in response to detecting passage of the position marker(s). A control unit is communicatively coupled to the sensor(s) and configured to generate a feedback signal indicative of the blade pitch angle in response to the sensor signal(s) received from the sensor(s).
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公开(公告)号：US11486310B2
公开(公告)日：2022-11-01
申请号：US16895527
申请日：2020-06-08
发明人： Dana Tomescu
摘要： There is provided a dynamic motoring system and method for an aircraft engine. Motoring of the engine is initiated for an initial motoring duration and at an initial motoring interval. At least one engine parameter is measured in real-time during the motoring, the at least one engine parameter comprising a temperature of the engine. The initial motoring duration and the initial motoring interval are modified in real-time, based on a value of the at least one engine parameter during the motoring, to obtain a modified motoring duration and a modified motoring interval. The motoring continues for the modified motoring duration and at the modified motoring interval, with a speed of rotation of the engine being controlled using the modified motoring interval.
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公开(公告)号：US11108302B2
公开(公告)日：2021-08-31
申请号：US16365229
申请日：2019-03-26
发明人： Dana Tomescu , Daniel Alecu
摘要： A machine includes a liquid system and a shaft. The shaft is rotatable about a rotation axis and includes a first part and a second part engaged coaxially with the first part. The first part is rotatable relative to the second part about the rotation axis to define a liquid pump between the first part and the second part. The pump is hydraulically connected to the liquid system. A method of cooling the machine is also provided.
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公开(公告)号：US11046423B2
公开(公告)日：2021-06-29
申请号：US16516191
申请日：2019-07-18
发明人： Dana Tomescu
IPC分类号： B64C11/06 , G01B7/30 , G01R33/038
摘要： A blade angle feedback assembly for a variable-pitch aircraft propeller rotor rotatable about an axis and having an adjustable blade pitch angle is provided. A feedback device is coupled to rotate with the rotor and to be displaced axially along the axis with adjustment of the blade pitch angle. Sensor(s) mounted adjacent the feedback device are configured to detect a passage of position marker(s) provided on the feedback device as the feedback device rotates. A magnetic shield mounted to the sensor(s) is configured to define a magnetic return path for some magnetic flux of a magnetic field exiting from a first pole of the magnet toward a second pole opposite the first pole. The magnetic shield comprises a wall member positioned adjacent the position marker(s) and configured to span a distance over which the position marker(s) are configured to be displaced with axial displacement of the feedback device.
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公开(公告)号：US11623735B2
公开(公告)日：2023-04-11
申请号：US17327038
申请日：2021-05-21
发明人： Dana Tomescu
IPC分类号： B64C11/06 , G01B7/30 , G01R33/038
摘要： A blade angle feedback assembly for a variable-pitch rotor of an aircraft engine, the rotor rotatable about an axis and having rotor blades rotatable about respective spanwise axes to adjust a blade angle thereof, is provided. A sensor is configured to provide feedback on the blade angle of the rotor blades by detecting a relative movement between the sensor and a feedback device having at least one position marker thereon. The sensor comprises a magnet having a magnetic field and a first pole and a second pole opposite the first pole. A magnetic shield is configured to define a magnetic return path for at least a portion of a magnetic flux of the magnetic field exiting from the first pole of the magnet toward the second pole, the magnetic shield comprising at least one wall member spanning a distance of relative displacement between the feedback device and the sensor.
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公开(公告)号：US11597502B2
公开(公告)日：2023-03-07
申请号：US16697084
申请日：2019-11-26
发明人： Dana Tomescu
摘要： A blade angle feedback system for an aircraft-bladed rotor rotatable about a longitudinal axis and having an adjustable blade pitch angle is provided. A feedback device is coupled to rotate with the rotor and to move along the axis with adjustment of the blade angle. At least one position marker is affixed to a core of the feedback device and extends along a direction angled relative to the axis. The core is made of a first material having a first magnetic permeability and the position marker comprises a second material having a second magnetic permeability greater than the first magnetic permeability. A sensor is positioned adjacent the feedback device and produces, as the feedback device rotates about the axis, a sensor signal in response to detecting passage of the position marker. A control unit generates a feedback signal indicative of the blade angle in response to the sensor signal.
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公开(公告)号：US11480585B2
公开(公告)日：2022-10-25
申请号：US17083551
申请日：2020-10-29
发明人： Dana Tomescu , Nick Stina
摘要： A feedback device is coupled to rotate with a rotating component of an aircraft engine. The feedback device comprises a body having cavities defined therein and circumferentially spaced thereabout, each cavity configured to receive therein a position marker, the body made of a non-ferromagnetic material and the position markers comprising a ferromagnetic material. A sealing member is configured to be secured to the body for retaining the position markers within the cavities. At least one sensor is positioned adjacent the feedback device and configured for producing, as the feedback device rotates about a longitudinal axis with the rotating component, at least one sensor signal in response to detecting passage of the position markers. A processing unit is communicatively coupled to the at least one sensor and configured to determine a rotational speed of the rotating component from the at least one sensor signal received from the at least one sensor.
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