Flexible connection between a wall and a case of a turbine engine
US-9366185-B2 · Jun 14, 2016 · US
Aircraft turbofan comprising an intermediate ring with simplified downstream support
US9528441B2 · US · B2
| Field | Value |
|---|---|
| Publication number | US-9528441-B2 |
| Application number | US-201414272911-A |
| Country | US |
| Kind code | B2 |
| Filing date | May 8, 2014 |
| Priority date | May 16, 2013 |
| Publication date | Dec 27, 2016 |
| Grant date | Dec 27, 2016 |
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Abstract
Official abstract text for this publication.
This invention relates to an assembly ( 100 ) for an aircraft turbofan comprising a flowpath splitter ( 40 ) downstream from which there is firstly a fan flowpath ( 31 ) inner delimitation ring ( 44 ) and secondly a compressor case ( 42 ), the assembly comprising a plurality of outlet guide vanes ( 34 ) provided with an inner platform ( 50 ) located in the downstream continuity of the delimitation ring. According to the invention, the assembly comprises at least one part ( 52 ) to support the delimitation ring ( 44 ), comprising a radially outer end ( 52 b ) fixed to a downstream part of this ring ( 44 ) and a radially inner end ( 52 a ) fixed to the compressor case ( 42 ).
First claim
Opening claim text (preview).
The invention claimed is: 1. An assembly for an aircraft turbofan comprising a flowpath splitter, said assembly comprising, downstream of said flowpath splitter, a fan flowpath inner delimitation ring and a compressor case located radially inwards from the delimitation ring, the assembly also comprising a plurality of outlet guide vanes passing through the fan flowpath and being provided with an inner platform located in the downstream continuity of the delimitation ring, wherein…
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Mechanical Engineering · mapped topic
Mechanical Engineering · mapped topic
- F02C7/04Primary
Mechanical Engineering · mapped topic
Mechanical Engineering · mapped topic
Cross-Sectional Technologies · mapped topic
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Frequently asked questions
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- What does patent US9528441B2 cover?
- This invention relates to an assembly ( 100 ) for an aircraft turbofan comprising a flowpath splitter ( 40 ) downstream from which there is firstly a fan flowpath ( 31 ) inner delimitation ring ( 44 ) and secondly a compressor case ( 42 ), the assembly comprising a plurality of outlet guide vanes ( 34 ) provided with an inner platform ( 50 ) located in the downstream continuity of the delimitat…
- Who is the assignee on this patent?
- Snecma
- What technology area does this patent fall under?
- Primary CPC classification F02C7/04. Mapped technology areas include Mechanical Engineering.
- When was this patent published?
- Publication date Tue Dec 27 2016 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 1 related publication on this page (citations in our corpus or others sharing the same primary CPC).