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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creator | MURAMATSU HIRONORI SAITA TOMOHISA |
description | 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. |
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subjects | MEASURING MEASURING QUANTITY OF HEAT MEASURING TEMPERATURE PHYSICS TESTING THERMALLY-SENSITIVE ELEMENTS NOT OTHERWISE PROVIDED FOR |
title | TEMPERATURE ESTIMATION APPARATUS FOR AEROPLANE GAS TURBINE ENGINE |
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