Control system for gas turbine aeroengine

Details Control system for gas turbine aeroengine Control system for gas turbine aeroengine

2006-05-11

2010-11-23

Tran, Khoi (Department: 3664)

Data processing: vehicles, navigation, and relative location

Vehicle control, guidance, operation, or indication

With indicator or control of power plant

C701S100000, C701S101000, C701S102000, C701S103000, C701S104000, C701S107000, C123S319000, C123S399000, C123S403000, C123S445000, C123S472000, C123S480000, C123S488000, C123S495000

Reexamination Certificate

active

07840336

ABSTRACT:
In a gas turbine aeroengine control system, in Ch-A (first control channel), a first CPU monitors the operation of a second CPU and the second CPU monitors the operation of the first CPU; in Ch-B (second control channel), third and fourth CPUs similarly monitor each other, and when the operation of at least one of the first and second CPUs in Ch-A is found not to be normal, the output sent to an FCU (fuel control unit) is switched from the output of one or the other of the first and second CPUs of Ch-A to the output of one or the other of the third and fourth CPUs of Ch-B, thereby achieving improved CPU failure detection and realizing high redundancy and high reliability.

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Japanese Notification of Grounds for Rejection, Japanese Patent Application No. JP2005-143225, Date of Preparation: Jun. 10, 2010, Date of Mailing: Jul. 6, 2010, 3 pages, English Translation; 2 pages.

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