| 摘要 |
PROBLEM TO BE SOLVED: To provide a control device of a gas turbine engine for an aircraft capable of reliably re-igniting without losing a timing at which re-ignition is practicable. SOLUTION: It is decided by a misfire deciding block 3 whether a combustor 2 of a gas turbine engine 1 is in a miss fire state. In this case, when it is decided that the miss fire occurs, a condition that re-ignition is practicable is decided by a re-ignition condition deciding block 4. Prescribed re-ignition operation is effected according to the determined re-ignition condition. A misfire effects decision, depending on whether an operation state represented by a temperature characteristic value TC and a number of revolutions characteristic value NC is in a preset misfire region. A re-ignition condition deciding block 4 effects decision, depending on whether a flying state represented by an aircraft speed Mn and an altitude ALT enters some of a plurality of regions preset in a flight envelope.
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