公开(公告)号：US20180093778A1

公开(公告)日：2018-04-05

申请号：US15284827

申请日：2016-10-04

申请人： General Electric Company

发明人： Jeffrey Michael Spack ,  Albion R. Fletcher, JR. ,  Drew G. Rindner

IPC分类号： B64D31/06 ,  F02C6/20 ,  F02C6/02 ,  F02C7/042 ,  F02C7/057 ,  B64D27/14 ,  F01D21/00

CPC分类号： B64D31/06 ,  B64D27/14 ,  F01D21/003 ,  F02C6/02 ,  F02C6/20 ,  F02C7/042 ,  F02C7/057 ,  F02C9/20 ,  F02C9/42 ,  F05D2220/323 ,  F05D2220/329 ,  F05D2260/80 ,  F05D2260/84 ,  F05D2270/71

摘要： In one aspect, a method for dynamically controlling the operation of an aircraft having a first gas turbine engine and a second gas turbine engine may generally include receiving, by a first engine controller and a second engine controller, one or more operator commands deriving from an operator manipulated input device. The method may also include controlling the operation of the first gas turbine engine via the first engine controller, and the second gas turbine engine via the second engine controller. In addition, the method may include detecting a fault condition associated with the first engine controller, and subsequently switching control of the first gas turbine engine from the first engine controller to the second engine controller. The method may further include dynamically controlling the operation of the first gas turbine engine with the second engine controller.

公开(公告)号：US10099796B2

公开(公告)日：2018-10-16

申请号：US15284827

申请日：2016-10-04

申请人： General Electric Company

发明人： Jeffrey Michael Spack ,  Albion R. Fletcher, Jr. ,  Drew G. Rindner

IPC分类号： B64D31/06 ,  B64D27/14 ,  F01D21/00 ,  F02C6/02 ,  F02C6/20 ,  F02C7/042 ,  F02C7/057

摘要： In one aspect, a method for dynamically controlling the operation of an aircraft having a first gas turbine engine and a second gas turbine engine may generally include receiving, by a first engine controller and a second engine controller, one or more operator commands deriving from an operator manipulated input device. The method may also include controlling the operation of the first gas turbine engine via the first engine controller, and the second gas turbine engine via the second engine controller. In addition, the method may include detecting a fault condition associated with the first engine controller, and subsequently switching control of the first gas turbine engine from the first engine controller to the second engine controller. The method may further include dynamically controlling the operation of the first gas turbine engine with the second engine controller.