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US Patent 10371061 Turbine section of high bypass turbofan

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US Patent 11988169 Fan arrangement for a gas turbine engine
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Patent abstract

A turbofan engine has an engine case and a gaspath through the engine case. A fan has a circumferential array of fan blades. The engine further has a compressor, a combustor, a gas generating turbine, and a low pressure turbine section. A speed reduction mechanism couples the low pressure turbine section to the fan. A bypass area ratio is greater than about 6.0. The low pressure turbine section airfoil count to bypass area ratio is below about 170.

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Patent Inventor Names
Frederick M. Schwarz0
Gabriel L. Suciu0
Joseph Brent Staubach0
Paul R. Adams0
Shankar S. Magge0
Wesley K. Lord0
Edits on 31 May, 2023
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US Patent 11661894 Geared turbine engine with relatively lightweight propulsor module
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edited on 25 May, 2023
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Official Website
https://pdfpiw.uspto.gov/.piw?Docid=103710610
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edited on 11 Jan, 2023
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US Patent 11549373 Reduced deflection turbine rotor
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Edits on 26 Sep, 2022
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US Patent 11053947 Turbine engine
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https://pdfpiw.uspto.gov/.piw?Docid=10371061
Edits on 25 May, 2022
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edited on 25 May, 2022
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Patent citations received
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US Patent 11339713 Large-scale bypass fan configuration for turbine engine core and bypass flows
Edits on 12 Feb, 2022
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edited on 12 Feb, 2022
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US Patent 11053947 Turbine engine

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