Rankin, Hill & Clark LLP
Apparatus for discriminating ignition in a gas-turbine aeroengine
An apparatus for discriminating ignition in a gas-turbine aeroengine is configured to discriminate that ignition occurred in a combustion chamber upon discriminating that a calculated high-pressure turbine rotational speed change rate at a detected high-pressure turbine rotational speed equal to or greater than a predetermined rotational speed threshold is equal to or greater than a predetermined rotational speed change rate threshold and that the change rate has been equal to or greater than the predetermined rotational speed change rate threshold continuously for a predetermined time period or longer, whereby whether or not ignition of an air-fuel mixture occurred in a combustion chamber can be accurately discriminated or determined without using a dedicated sensor or detector even when an EGT sensor or detector fails.
HONDA MOTOR CO., LTD.
F F F F F
F02C F02C F01D F02C F05D
inventional inventional inventional inventional additional
Masaharu
Saito