Ring segment for gas turbine engine
US-2024102394-A1 · Mar 28, 2024 · US
US8998575B2 · US · B2
| Field | Value |
|---|---|
| Publication number | US-8998575-B2 |
| Application number | US-201113295724-A |
| Country | US |
| Kind code | B2 |
| Filing date | Nov 14, 2011 |
| Priority date | Nov 14, 2011 |
| Publication date | Apr 7, 2015 |
| Grant date | Apr 7, 2015 |
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An airfoil comprises a leading edge, a trailing edge, and pressure and suction surfaces defined therebetween. An inner platform is coupled to a root section of the airfoil, with a curvilinear gusset extending along a lower surface of the inner platform, opposite the root section. An outer platform is coupled to a tip section of the airfoil, with a multi-lobed gusset extending along an upper surface of the inner platform, opposite the tip section.
Opening claim text (preview).
The invention claimed is: 1. An airfoil comprising: a leading edge, a trailing edge, and pressure and suction surfaces defined therebetween; an inner platform coupled to a root section of the airfoil, the inner platform comprising a curvilinear gusset extending along a lower surface of the inner platform, opposite the root section, wherein the curvilinear gusset extends along a camber line of the airfoil defined in the root section of the airfoil opposite the curvilinear gusset;…
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Cross-Sectional Technologies · mapped topic
Cross-Sectional Technologies · mapped topic
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