| 摘要 |
PROBLEM TO BE SOLVED: To provide a gas turbine engine for an airplane which accurately estimates an inlet temperature of a high pressure turbine on the basis of an outlet temperature of a low pressure turbine. SOLUTION: In the gas turbine engine for the airplane which is equipped with the high pressure turbine rotated by high pressure gas injected from an engine combustor and the low pressure turbine arranged downstream of the high pressure turbine rotated by low pressure gas passing through the high pressure turbine, the rotation speed N2 of the high pressure turbine, the rotation speed N1 of the low pressure turbine and an outlet temperature EGT of the low pressure turbine are detected, an inlet temperature (TIT base item TIT_Base) of the high pressure turbine is estimated on the basis of the outlet temperature EGT of the low pressure turbine and the rotation speed N1 of the low pressure turbine, and the estimated inlet temperature of the high pressure turbine is subtraction-corrected by a TIT correction termΔTIT on the basis of the rotation speed N2 of the high pressure turbine. COPYRIGHT: (C)2011,JPO&INPIT |
