Aircraft gas turbine engine with improved response to rotor unbalance
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United States of America Patent
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-
Jun 7, 2022
Grant Date -
Dec 9, 2021
app pub date -
May 27, 2021
filing date -
Jun 3, 2020
priority date (Note) -
In Force
status (Latency Note)
Importance
Abstract
An aircraft gas turbine engine includes a fan system having a reverse traveling wave first flap mode, Fan RTW, and including a fan upstream of the engine core; a fan shaft; and a front engine structure to support the shaft and having a front engine structure nodding mode FSN including two modes at similar, but unequal, natural frequencies in orthogonal directions; and a gearbox. The engine includes a gearbox, and a gearbox output shaft to couple output of the gearbox to the fan shaft. An LP rotor system including the fan system and the gearbox output shaft has a first reverse whirl rotor dynamic mode, Rotor RW. A frequency margin of:
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