Thrust reverser cascade with offset vane leading edges
US-2024035427-A1 · Feb 1, 2024 · US
US9038367B2 · US · B2
| Field | Value |
|---|---|
| Publication number | US-9038367-B2 |
| Application number | US-201113234213-A |
| Country | US |
| Kind code | B2 |
| Filing date | Sep 16, 2011 |
| Priority date | Sep 16, 2011 |
| Publication date | May 26, 2015 |
| Grant date | May 26, 2015 |
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A fan case of a gas turbine engine includes a fan blade containment section defined about an engine axis, a thrust reverser cascade section downstream of the blade containment section and a Fan Exit Guide Vane section downstream of the thrust reverser cascade section.
Opening claim text (preview).
What is claimed is: 1. A fan case of a gas turbine engine comprising: a fan blade containment section defined about anengine axis; a thrust reverser cascade section downstream of said blade containment section, said thrust reverser cascade section including an array of cascade airfoils and a plurality of inner thrust reverser doors radially inwards of said array of cascade airfoils, said inner thrust reverser doors opening inwards toward said engine axis and being arranged in a…
Mechanical Engineering · mapped topic
Mechanical Engineering · mapped topic
Mechanical Engineering · mapped topic
Mechanical Engineering · mapped topic
Mechanical Engineering · mapped topic
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