TEMPERATURE ESTIMATION APPARATUS FOR AEROPLANE GAS TURBINE ENGINE

In a temperature estimation apparatus 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, a low-pressure turbine located downstream of the high-pressure turbine to be rota...

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Bibliographische Detailangaben
Hauptverfasser:	MURAMATSU HIRONORI, SAITA TOMOHISA
Format:	Patent
Sprache:	eng
Schlagworte:	MEASURING MEASURING QUANTITY OF HEAT MEASURING TEMPERATURE PHYSICS TESTING THERMALLY-SENSITIVE ELEMENTS NOT OTHERWISE PROVIDED FOR
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Beschreibung
Zusammenfassung:	In a temperature estimation apparatus 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, 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, a high-pressure turbine rotational speed sensor, a low-pressure turbine rotational speed sensor, and a temperature sensor, inlet temperature at an inlet of the high-pressure turbine is estimated based on the detected outlet temperature of the low-pressure turbine and the rotational speed of the low-pressure turbine and is corrected with the detected rotational speed of the high-pressure turbine.