Ring gear mounting arrangement with oil scavenge scheme
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United States of America Patent
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Jul 5, 2022
Grant Date -
Jan 21, 2021
app pub date -
Oct 2, 2020
filing date -
Aug 15, 2006
priority date (Note) -
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status (Latency Note)
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Abstract
A gas turbine engine includes a bypass ratio greater than about ten (10). A fan is supported on a fan shaft and has a plurality of fan blades. A gear system is connected to the fan shaft. A plurality of planetary gears and a first set of opposed angled ring gear teeth are separated from a second set of opposed angled ring gear teeth. A lubricant flow path is located axially between the first set of opposed angled ring gear teeth and the second set of opposed angled ring gear teeth. A gear system support is relative to a fixed housing facilitating segregation of vibrations. An annular channel is axially aligned with the lubricant flow path. A low pressure turbine has an inlet, an outlet, and a low pressure turbine pressure ratio greater than 5:1.
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