公开(公告)号：US09114885B2

公开(公告)日：2015-08-25

申请号：US14025995

申请日：2013-09-13

申请人： Pratt & Whitney Canada Corp.

发明人： Salvatore Calandra ,  Frederic Giroux ,  Mark Iacobacci ,  Martin Chabot ,  Simon Hartropp ,  Yusuf Syed ,  Dariusz Chmiel ,  Adrienne Bajaj

IPC分类号： B64D31/06 ,  F01D25/02 ,  F02C7/047 ,  F02C9/28 ,  F02D9/00 ,  G07C3/00 ,  G01K13/02

CPC分类号： B64D31/06 ,  F01D25/02 ,  F02C7/047 ,  F02C9/28 ,  F02D9/00 ,  F05B2260/80 ,  F05B2270/303 ,  F05D2270/094 ,  F05D2270/303 ,  F05D2270/80 ,  G01K1/20 ,  G01K13/02 ,  G01K13/022 ,  G01K2013/024 ,  G01K2205/02 ,  G07C3/00

摘要： Methods for controlling an aircraft turbofan engine during icing of a temperature probe and devices for carrying out such methods are described. The methods may comprise: using one or more signals representative of temperature received from a heated temperature probe to generate one or more control signals for use in controlling the engine; determining that an icing condition associated with the probe exists; and using data representing one or more substitute signals in place of signals representative of temperature received from the heated temperature probe to generate the one or more control signals for use in controlling the engine.

摘要翻译： 描述了在温度探针结冰期间控制飞行器涡扇发动机的方法和用于执行这种方法的装置。 所述方法可以包括：使用代表从加热温度探测器接收的温度的一个或多个信号来产生用于控制发动机的一个或多个控制信号; 确定与探针相关联的结冰条件存在; 并且使用表示一个或多个替代信号的数据代替代表从加热温度探测器接收的温度的信号，以产生用于控制发动机的一个或多个控制信号。

公开(公告)号：US10443512B2

公开(公告)日：2019-10-15

申请号：US15476271

申请日：2017-03-31

申请人： PRATT & WHITNEY CANADA CORP.

发明人： Yusuf Syed ,  Michael Krynski ,  Antwan Shenouda ,  Frederic Giroux ,  Ioan Sabau

IPC分类号： F02C9/46 ,  F02C9/28

摘要： Herein provided are methods and systems for detecting an uncommanded or uncontrollable high thrust (UHT) event in an aircraft, comprising arming a UHT function, detecting a fuel flow error when an actual fuel flow minus a commanded fuel flow exceeds a first threshold, the fuel flow error indicative of a presence of excess thrust, detecting a UHT event based on excess thrust and as a function of a second threshold, upon detection of the fuel flow error, and accommodating the UHT event.

公开(公告)号：US20210215104A1

公开(公告)日：2021-07-15

申请号：US16743681

申请日：2020-01-15

申请人： PRATT & WHITNEY CANADA CORP.

发明人： Michael DARBY ,  Mohammad Khashayar Donyaee ,  Teuvo Saario ,  Frederic Giroux

IPC分类号： F02C9/00 ,  F02C7/26

摘要： Systems and methods for controlling operation of an engine using an engine controller are described herein. A status of the controller is set at an initial state. Pilot input for control of the engine is received and one or more engine parameters are obtained. The status of the controller is updated according to engine specific requirements based on at least one of the pilot input and the one or more engine parameters. The engine specific requirements defining conditions for transitioning the status of the controller for the engine. Operation of the engine is controlled based on the status of the controller, the pilot input, and the one or more engine parameters.

公开(公告)号：US20140012481A1

公开(公告)日：2014-01-09

申请号：US14025995

申请日：2013-09-13

申请人： Pratt & Whitney Canada Corp.

发明人： Salvatore Calandra ,  Frederic Giroux ,  Mark Iacobacci ,  Martin Chabot ,  Simon Hartropp ,  Yusuf Syed ,  Dariusz Chmiel ,  Adrienne Bajaj

IPC分类号： B64D31/06

CPC分类号： B64D31/06 ,  F01D25/02 ,  F02C7/047 ,  F02C9/28 ,  F02D9/00 ,  F05B2260/80 ,  F05B2270/303 ,  F05D2270/094 ,  F05D2270/303 ,  F05D2270/80 ,  G01K1/20 ,  G01K13/02 ,  G01K13/022 ,  G01K2013/024 ,  G01K2205/02 ,  G07C3/00

摘要： Methods for controlling an aircraft turbofan engine during icing of a temperature probe and devices for carrying out such methods are described. The methods may comprise: using one or more signals representative of temperature received from a heated temperature probe to generate one or more control signals for use in controlling the engine; determining that an icing condition associated with the probe exists; and using data representing one or more substitute signals in place of signals representative of temperature received from the heated temperature probe to generate the one or more control signals for use in controlling the engine.

摘要翻译： 描述了在温度探针结冰期间控制飞行器涡扇发动机的方法和用于执行这种方法的装置。 所述方法可以包括：使用代表从加热温度探测器接收的温度的一个或多个信号来产生用于控制发动机的一个或多个控制信号; 确定与探针相关联的结冰条件存在; 并且使用表示一个或多个替代信号的数据代替代表从加热温度探测器接收的温度的信号，以产生用于控制发动机的一个或多个控制信号。