Patent ID: 8483988

Claim:
An apparatus for estimating temperature for an aeroplane gas turbine engine mounted on an aircraft and having a combustion chamber, a high-pressure turbine rotated by combustion gas exhausted from the combustion chamber, and a low-pressure turbine located downstream of the high-pressure turbine to be rotated by low-pressure gas which has passed through the high-pressure turbine, comprising: a high-pressure turbine rotational speed sensor that detects rotational speed of the high-pressure turbine; a low-pressure turbine rotational speed sensor that detects rotational speed of the low-pressure turbine; a temperature sensor that detects outlet temperature at an outlet of the low-pressure turbine; an estimator that estimates inlet temperature at an inlet of the high-pressure turbine based on the detected outlet temperature of the low-pressure turbine and the rotational speed of the low-pressure turbine; and a corrector that corrects the estimated inlet temperature of the high-pressure turbine with the detected rotational speed of the high-pressure turbine.