Turbine section of high bypass turbofan

US9010085B2 · US · B2

Patent metadata
FieldValue
Publication numberUS-9010085-B2
Application numberUS-201213599175-A
CountryUS
Kind codeB2
Filing dateAug 30, 2012
Priority dateAug 1, 2007
Publication dateApr 21, 2015
Grant dateApr 21, 2015

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  1. Title

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  2. Abstract

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  4. Key dates

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  5. First independent claim

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  7. Citations and related patents

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Abstract

Official abstract text for this publication.

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 ratio is below about 170.

First claim

Opening claim text (preview).

What is claimed is: 1. A turbofan engine comprising: an engine case; a gaspath through the engine case; a fan having a circumferential array of fan blades; a compressor in fluid communication with the fan; a combustor in fluid communication with the compressor; a turbine in fluid communication with the combustor, the turbine having a low pressure turbine section having 3 to 6 blade stages; and a speed reduction mechanism coupling the low pressure turbine section to the…

Assignees

Inventors

Classifications

  • Mechanical Engineering · mapped topic

  • Mechanical Engineering · mapped topic

  • Mechanical Engineering · mapped topic

  • F02C7/36Primary

    Mechanical Engineering · mapped topic

  • F02C3/113Primary

    Mechanical Engineering · mapped topic

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What does patent US9010085B2 cover?
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…
Who is the assignee on this patent?
Adams Paul R, Magge Shankar S, Staubach Joseph B, and 4 more
What technology area does this patent fall under?
Primary CPC classification F02C7/36. Mapped technology areas include Mechanical Engineering.
When was this patent published?
Publication date Tue Apr 21 2015 00:00:00 GMT+0000 (Coordinated Universal Time) (B2). Legal status and post-grant events are not shown on this page.
What related patents are in patentsdb?
We list 8 related publications on this page (citations in our corpus or others sharing the same primary CPC).