Patent ID: 9556800
Date: 2017-01-31
CPC Classifications: F01D,F02C,F05D

Claim:
1. An apparatus for controlling an aeroplane gas turbine engine having a plurality of sensors, a plurality of devices for operating the engine, and first and second control channels first control channel comprising: a first command value calculation unit that calculates a first command value for controlling operation of the engine through the devices based on signals outputted from the sensors; a first outputting unit that sends the first command value calculated by the first command value calculation unit to the devices for operating the engine; a first failure level determiner that determines whether any of the sensors and the devices is abnormal based on the signals outputted from the sensors, determines that the first control channel is failed if any of the sensors and the devices is determined to be abnormal, and determines a failure level of the first control channel in numerical value depending on degree of abnormality; and a first transmitter that transmits the determined failure level of the first control channel to the second control channel, and the second control channel comprising: a second command value calculation unit that calculates a second command value for controlling operation of the engine through the devices based on signals outputted from the sensors; a second outputting unit that sends the second command value calculated by the second command value calculation unit to the devices for operating the engine; a second failure level determiner that determines whether any of the sensors and the devices is abnormal based on the signals outputted from the sensors, determines that the second control channel is failed if any of the sensors and the devices is determined to be abnormal, and determines a failure level of the second control channel in numerical value depending on degree of abnormality; and a second transmitter that transmits the determined failure level of the second control channel to the first control channel, wherein the first control channel further comprises a first receiver that receives the failure level of the second control channel transmitted by the second transmitter, the second control channel further comprises a second receiver that receives the failure level of the first control channel transmitted by the first transmitter, and when both of the first and second control channels are determined to be failed, the first or second outputting units compare the failure levels of the first and second control channels, determines that one of the first and second control channels having a smaller failure level is in an active condition and one of the first and second control channels having a greater failure level is in a standby condition, and sends one of the first and second command values of the one of the first and second control channels in the active condition to the devices for operating the engine.