US Patent 10280843 Geared turbofan with integral front support and carrier
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Patent abstract
A gas turbine engine includes a fan section including a fan hub. A speed reduction device includes a star gear system. A turbine section is connected to the fan section through the speed reduction device. A first fan bearing for supporting rotation of the fan hub is connected forward of the speed reduction device. A second fan bearing for supporting rotation of the fan hub is connected aft of the speed reduction device. A first outer race of the first fan bearing is attached to the fan hub.
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Patent Inventor Names
William G. Sheridan0
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Official Website
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Patent Citations Received
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US Patent 10280843 Geared turbofan with integral front support and carrier
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Is a
Patent applicant
Patent jurisdiction
Patent number
10280843
Date of patent
May 7, 2019
Patent application number
14633244
Date Filed
February 27, 2015
Patent primary examiner
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