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1. 发明授权

US11619139B1 Method and system for detecting a shaft shear event 有权
公开(公告)号：US11619139B1
公开(公告)日：2023-04-04
申请号：US17592969
申请日：2022-02-04
申请人： PRATT & WHITNEY CANADA CORP.
发明人： Philippe Beauchesne-Martel , Jeremie Hebert , Pramuk Fernando , Jasraj Chahal
IPC分类号： F01D17/04 , F01D21/06 , F02C9/28 , F01D21/04 , F02D35/02 , G01B7/16 , G01B21/32 , F16C3/02
摘要： The method can include: monitoring a current value of a rate of reduction of torque of the shaft; providing a threshold value for the rate of reduction of torque of the shaft; and generating a signal indicative of the shaft shear event when the current value exceeds the threshold value.

2. 发明授权

US11549446B1 Method and apparatus for measuring compressor bleed flow 有权
公开(公告)号：US11549446B1
公开(公告)日：2023-01-10
申请号：US17665184
申请日：2022-02-04
申请人： Pratt & Whitney Canada Corp.
发明人： Martin Drolet , Philippe Beauchesne-Martel , Kevin Ng
IPC分类号： F02C6/08 , F02C9/28 , F01D21/00
摘要： A gas turbine engine includes a compressor, an annular casing surrounding the compressor, and a bleed flow adapter mounted to an exterior side of the annular casing. The annular casing includes the exterior side and an interior side. The interior side surrounds a compressor bleed cavity located downstream of at least a portion of the compressor. The bleed flow adapter is in fluid communication with the bleed cavity. The bleed flow adapter includes an inlet end, an outlet end, and an inner diameter surface extending between the inlet end and the outlet end. The inner diameter surface defines a bleed passage. The bleed flow adapter further includes a fluid port formed through the inner diameter surface. The gas turbine engine further includes a bleed flow measurement system including a first pressure sensor in fluid communication with the bleed passage of the bleed flow adapter via the fluid port.

3. 发明授权

US11299286B2 System and method for operating a multi-engine aircraft 有权
公开(公告)号：US11299286B2
公开(公告)日：2022-04-12
申请号：US16670582
申请日：2019-10-31
申请人： PRATT & WHITNEY CANADA CORP.
发明人： Philippe Beauchesne-Martel , Patrick Manoukian
IPC分类号： B64D31/00 , B64D31/10 , B64C27/12 , B64C27/57 , B64D35/08
摘要： The present disclosure provides methods and systems for operating a rotorcraft comprising a plurality of engines configured to provide motive power to the rotorcraft and at least one rotor coupled to the plurality of engines. Failure of an active engine of the rotorcraft is detected when the rotorcraft is operated in an asymmetric operating regime (AOR), in which at least one first engine of the plurality of engines is the active engine and is operated in an active mode to provide motive power to the rotorcraft and at least one second engine of the plurality of engines is a standby engine and is operated in a standby mode to provide substantially no motive power to the rotorcraft. At least one flight control input is adjusted to compensate for a reduction in rotational speed of the at least one rotor resulting from the failure of the active engine. An increase in a power output of the standby engine of the rotorcraft is commanded.

4. 发明授权

US09322341B2 System and method for engine transient power response 有权
标题翻译：发动机瞬态功率响应的系统和方法
公开(公告)号：US09322341B2
公开(公告)日：2016-04-26
申请号：US13796624
申请日：2013-03-12
申请人： PRATT & WHITNEY CANADA CORP.
发明人： François Belleville , Philippe Beauchesne-Martel , Keith Morgan
IPC分类号： F02D29/02 , F02C9/54
CPC分类号： F02D29/02 , F02C9/54 , F05D2270/044 , F05D2270/053 , F05D2270/304 , F05D2270/335
摘要： There is provided a system and method for controlling an engine. A request signal indicative of a demand for the engine to output a required power level is first receive. A position control signal is then generated in response to the request signal. The position request signal is indicative of a first request for adjusting a present position of a variable geometry mechanism of the engine towards a commanded position to achieve the required power level. An acceleration rate control signal is further generated on the basis of the position control signal. The acceleration rate control signal is indicative of a second request for adjusting an acceleration rate of the engine in accordance with the commanded position of the variable geometry mechanism. The position control signal and the acceleration rate control signal are then output to the engine.
摘要翻译：提供了一种用于控制发动机的系统和方法。首先接收指示发动机输出所需功率水平的要求的请求信号。然后响应于请求信号产生位置控制信号。位置请求信号表示第一请求，用于将发动机的可变几何机构的当前位置调整到指令位置以实现所需的功率水平。基于位置控制信号进一步产生加速度控制信号。加速度控制信号表示根据可变几何机构的指令位置调整发动机的加速度的第二请求。然后将位置控制信号和加速度控制信号输出到发动机。

5. 发明授权

US11352900B2 Method and system for operating a rotorcraft engine 有权
公开(公告)号：US11352900B2
公开(公告)日：2022-06-07
申请号：US16425428
申请日：2019-05-29
申请人： PRATT & WHITNEY CANADA CORP.
发明人： Patrick Manoukian , Philippe Beauchesne-Martel , Olivier Bibor
IPC分类号： F01D21/00 , B64C27/32 , B64D31/06 , B64D45/00 , F01D21/14
摘要： Systems and methods for operating an engine of a rotorcraft are described herein. An engine parameter indicative of torque of the engine is obtained. A decrease of the torque of the engine is detected. At least one rotorcraft parameter indicative of at least one command to control the rotorcraft is obtained and evaluated to determine whether one of an autorotation mode and a powered flight mode of the rotorcraft has been commanded. When the powered flight mode of the rotorcraft has been commanded and the decrease of the torque has been detected, a shaft shear of the engine is detected and a signal indicative of the shaft shear is transmitted. When the autorotation mode of the rotorcraft has been commanded and the decrease of the torque has been detected, detection of the shaft shear is disabled during operation in the autorotation mode.

6. 发明授权

US11236681B2 Systems and methods for operating gas turbine engines 有权
公开(公告)号：US11236681B2
公开(公告)日：2022-02-01
申请号：US16665520
申请日：2019-10-28
申请人： PRATT & WHITNEY CANADA CORP.
发明人： Philippe Beauchesne-Martel , Keith Morgan
IPC分类号： F02C9/20 , F02C9/28 , F02C9/54 , F02C9/46 , F01D17/06 , F04D27/02
摘要： Methods and systems for operating a gas turbine engine having variable geometry mechanisms are described. The method comprises detecting a failure event associated with the gas turbine engine, identifying a location of the failure event, selecting an aerodynamic load modulation schedule for the variable geometry mechanisms of the gas turbine engine as a function of the location of the failure event, and applying the aerodynamic load modulation schedule as selected to the variable geometry mechanisms during the failure event.

7. 发明授权

US10280788B2 Aircraft power outtake management 有权
公开(公告)号：US10280788B2
公开(公告)日：2019-05-07
申请号：US15175467
申请日：2016-06-07
申请人： PRATT & WHITNEY CANADA CORP.
发明人： Bryan Chen , Dariusz Chmiel , Philippe Beauchesne-Martel , James Robert Jarvo
IPC分类号： F01D21/00 , F02C9/28 , F02C9/54 , B64D31/06 , F02C7/042 , F02C9/26 , G05B13/02
摘要： A system and method for controlling the operation of a gas turbine engine supplying power to an aircraft. The engine is controlled according to a reading of an amount of power drawn from the supplied power. The reading is fed directly to a control system, which issues commands for controlling engine parameters comprising an acceleration reference signal, load shedding, variable geometry positioning, and fuel flow. The control system may further issue commands for controlling the amount of power drawn. The control system may further use the reading to monitor the engine's condition.

8. 发明授权

US11326525B2 Aircraft bleed air systems and methods 有权
公开(公告)号：US11326525B2
公开(公告)日：2022-05-10
申请号：US16599336
申请日：2019-10-11
申请人： PRATT & WHITNEY CANADA CORP.
发明人： Patrick Manoukian , Philippe Beauchesne-Martel
IPC分类号： F02C9/16 , F02C7/18 , F02C6/08
摘要： A method of monitoring bleed air provided from a first engine to a second engine of a multi-engine aircraft includes operating the first engine in a powered mode to provide motive power to the multi-engine aircraft; and when the first engine is in the powered mode: actuating an air valve to open an air flow path from a compressor section of the first engine to a plurality of parts of the second engine, after the step of actuating the air valve, determining a change in a temperature in a main gas path of the first engine at a location in the main gas path at or downstream of a combustor of the first engine, and in response to determining that the change is below a threshold, executing an action with respect to the first engine, the air valve, and/or the second engine.

9. 发明授权

US11168621B2 Method and system for operating an engine in a multi-engine aircraft 有权
公开(公告)号：US11168621B2
公开(公告)日：2021-11-09
申请号：US16292684
申请日：2019-03-05
申请人： PRATT & WHITNEY CANADA CORP.
发明人： Sean McCarthy , Patrick Manoukian , Zachary Mounir Faty , Carmine Lisio , Philippe Beauchesne-Martel
IPC分类号： F02C9/42 , B64C27/12 , F02C6/02
摘要： Systems and methods for operating an engine in a multi-engine rotorcraft are described herein. A first parameter indicative of torque of a first engine is obtained. A decrease of the first parameter is detected. In response to detecting the decrease of the first parameter, an autorotation of the rotorcraft is accommodated, A second parameter indicative of torque of a second engine of the rotorcraft is assessed while accommodating the autorotation. If the second parameter has not decreased, a shaft shear of the first engine is identified and accommodating of the autorotation is ended. If the second parameter has decreased, the accommodating is maintained.

10. 发明申请

US20190061969A1 VARIABLE GEOMETRIES TRANSIENT CONTROL LOGIC 审中-公开
公开(公告)号：US20190061969A1
公开(公告)日：2019-02-28
申请号：US16110699
申请日：2018-08-23
申请人： PRATT & WHITNEY CANADA CORP.
发明人： Philippe Beauchesne-Martel
IPC分类号： B64D31/06 , F01D17/16 , F01D17/10
CPC分类号： B64D31/06 , F01D17/105 , F01D17/16 , F02C9/20 , F02C9/54 , F04D27/0246 , F05D2220/323 , F05D2270/03 , F05D2270/053 , F05D2270/061 , F05D2270/304 , F05D2270/309 , F05D2270/54
摘要： Herein provided are methods and systems for controlling an engine having a variable geometry mechanism. A power level difference between a requested engine power level and a current engine power level is determined at a computing device. The power level difference is compared to a predetermined power threshold at the computing device. When the power level difference exceeds the predetermined power threshold, a position control signal for changing a position of the variable geometry mechanism is generated and output at the computing device, the position control signal generated based on a requisite bias level, the requisite bias level being based on the power level difference.

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