Turbine section of high bypass turbofan

Number of patents in Portfolio can not be more than 2000

United States of America Patent

PATENT NO 11486311
APP PUB NO 20210301731A1
SERIAL NO

17230326

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Abstract

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A turbofan engine according to an example of the present disclosure includes, among other things, a fan including an array of fan blades rotatable about an engine axis, a compressor including a high pressure compressor section and a low pressure compressor section, the low pressure compressor section including a low pressure compressor section inlet with a low pressure compressor inlet annulus area, a fan duct including a fan duct annulus area outboard of the low pressure compressor section inlet, and a turbine having a high pressure turbine section and a low pressure turbine section driving the fan through a speed reduction mechanism, wherein the low pressure turbine section defines a maximum gas path radius and the fan blades define a maximum radius, and a ratio of the maximum gas path radius to the maximum radius of the fan blades is less than 0.6.

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Patent Owner(s)

Patent OwnerAddress
RTX CORPORATION10 FARM SPRINGS ROAD FARMINGTON CT 06032

International Classification(s)

Inventor(s)

Inventor Name Address # of filed Patents Total Citations
Adams, Paul R Glastonbury, US 31 732
Lord, Wesley K South Glastonbury, US 91 1458
Magge, Shankar S South Windsor, US 33 528
Schwarz, Frederick M Glastonbury, US 446 5139
Staubach, Joseph B Colchester, US 119 1115
Suciu, Gabriel L Glastonbury, US 580 8113

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