公开(公告)号：US20190170068A1

公开(公告)日：2019-06-06

申请号：US15829145

申请日：2017-12-01

Applicant: PRATT & WHITNEY CANADA CORP.

Inventor： Michael DARBY ,  Reza PEDRAMI

IPC: F02C9/28 ,  F16C3/02

Abstract: A system and a method for detecting a shaft shear event in a gas turbine engine are disclosed. The system comprises a sensor configured to detect a shaft shear force exerted by a shaft on a support structure supporting the shaft where the shaft shear force is indicative of shearing of the shaft. The system also comprises a controller operatively coupled to the sensor and configured to initiate a shutdown of the gas turbine engine in response to the detection of the shaft shear force by the sensor.

公开(公告)号：US20150291286A1

公开(公告)日：2015-10-15

申请号：US14250035

申请日：2014-04-10

Applicant: PRATT & WHITNEY CANADA CORP.

Inventor： Michael DARBY ,  Brant DUKE

IPC: B64D31/06 ,  F02D25/00

CPC classification number: B64D31/06 ,  F02C9/00 ,  F02C9/42 ,  F02D25/00 ,  F05D2240/40 ,  H04L12/40189

Abstract: The multiple aircraft engine control system having a corresponding engine controller associated with each one of the engines, each one of the engine controllers having at least two independent channels, each one of the at least two independent channels having at least two communication buses, each one of the at least two communicating buses of each channel being connected to a respective one of the at least two communicating buses of each one of the other channels. The method can time-interweave originating data of the channels.

Abstract translation: 多个飞机发动机控制系统具有与每个发动机相关联的对应的发动机控制器，每个发动机控制器具有至少两个独立通道，所述至少两个独立通道中的每一个具有至少两个通信总线，每个 每个信道的至少两个通信总线被连接到每个其他信道的至少两个通信总线中的相应一个。 该方法可以对信道的始发数据进行时间交织。

公开(公告)号：US20210215104A1

公开(公告)日：2021-07-15

申请号：US16743681

申请日：2020-01-15

Applicant: PRATT & WHITNEY CANADA CORP.

Inventor： Michael DARBY ,  Mohammad Khashayar Donyaee ,  Teuvo Saario ,  Frederic Giroux

IPC: F02C9/00 ,  F02C7/26

Abstract: 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.