Gas turbine engine having outlet guide vanes
US-2024418094-A1 · Dec 19, 2024 · US
US8979484B2 · US · B2
| Field | Value |
|---|---|
| Publication number | US-8979484-B2 |
| Application number | US-201213344057-A |
| Country | US |
| Kind code | B2 |
| Filing date | Jan 5, 2012 |
| Priority date | Jan 5, 2012 |
| Publication date | Mar 17, 2015 |
| Grant date | Mar 17, 2015 |
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A casing for an aircraft turbofan bypass engine includes an outer ring, an inner hub and a plurality of struts radially extending therebetween. An annular portion of an engine core casing having an outer wall and an inner wall, is disposed between the outer ring and inner hub, forming an annular splitter supporting an upstream splitter tip structure. The annular splitter further includes an intermediate wall disposed in the annular splitter fixed to the outer wall and the struts, to distribute loads from the annular splitter box to the struts.
Opening claim text (preview).
The invention claimed is: 1. A casing for an aircraft turbofan bypass engine comprising: an outer ring and an inner hub defining an annular space therebetween, the inner hub configured for connection to at least one spool bearing, the outer ring configured for connection to at least one engine mount; a plurality of hollow radial struts arranged in a circumferential array mounting the inner hub to the outer ring; and an annular splitter box disposed between the inner hub and ou…
Mechanical Engineering · mapped topic
Mechanical Engineering · mapped topic
Mechanical Engineering · mapped topic
Mechanical Engineering · mapped topic
Mechanical Engineering · mapped topic
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